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AIRPLANE OPERATIONS MANUAL VOLUME 1 Embraer S.A.

This manual is applicable to the EMBRAER 170 airplanes LR, SU and SE models equipped with CF34-8E5 engines, the EMBRAER 175 airplanes LR model equipped with CF34-8E5 engines, operating under FAA certification.

THIS PUBLICATION IS INCOMPLETE WITHOUT AIRPLANE OPERATIONS MANUAL AOM-1502 VOLUME 2.

AOM-1502-003 DECEMBER 10, 2003 REVISION 21 - OCTOBER 20, 2016

In connection with the use of this document, Embraer does not provide any express or implied warranties and expressly disclaims any warranty of merchantability or fitness for a particular purpose. Copyright © 2016 by EMBRAER S.A. All rights reserved.

AIRPLANE OPERATIONS MANUAL

HIGHLIGHTS OF CHANGE

HIGHLIGHTS OF CHANGE REVISION 21 - OCTOBER 20, 2016 Editorial revisions (e.g., spelling corrections) have revision bars and may not be listed below. BLOCK

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DESCRIPTION MAXIMUM RECOMMENDED CROSSWIND Updated maximum recommended crosswind component for static takeoff applicable to EMBRAER 170/175 Models. MAXIMUM RECOMMENDED CROSSWIND Added information that maximum recommended crosswinds include gust. KINDS OF OPERATION Included Extended Overwater Operation for EMBRAER 175 models, FAA certification and EMBRAER 175 models with Enhanced Wingtip, ANAC/FAA certification. TOWING Updated towbarless towing information according to AFM. FUEL TANK TEMPERATURE Updated minimum fuel tank temperature according to AFM. PRESSURIZATION Updated the maximum differential pressure and the maximum differential overpressure values according to the AFM. ICE AND RAIN PROTECTION Added instruction about use of anti-ice protection system in presence of moisture. ICE AND RAIN PROTECTION Editorial changes in accordance with the AFM. NAVIGATION EQUIPMENT Updated Statement of Compliance for ADS-B Out Transponder.

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REVISION 21

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AIRPLANE OPERATIONS MANUAL DESCRIPTION FLIGHT MANAGEMENT SYSTEM Updated information related to RNP 10 Airspace to standardize with AFM. FLIGHT MANAGEMENT SYSTEM Editorial changes. NAVIGATION LIMITATIONS Updated information about RNP operations expiration date due to magnetic database changes. NAVIGATION LIMITATIONS Updated Load effectivities applicable to certain navigation limitations. APPROACH LIMITATIONS Updated limitation regarding RNAV Visual and FMS Visual approaches. POWER UP Emergency lights check moved to power up. BEFORE START Added step to push out the APU bleed button in the ENGINE GROUND PNEUMATIC START. AFTER START Added steps to push out and to push in the APU in the ENGINE GROUND PNEUMATIC START. ON GROUND - IF THE AIRPLANE HAS BEEN HIT BY LIGHTNING Changed Landing and Taxi Lights to Nose Gear Landing and Taxi Lights. POWER UP Included note about transient power state effects on EICAS messages and Display Units. POWER UP Emergency lights check moved to power up.

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DESCRIPTION BEFORE START Updated Before Start procedure. BEFORE START Emergency lights check moved to power up. BEFORE START Added step to select Manual Speeds before MCDU setting. BEFORE START Differentiated the MCDU setting instructions for MAU Load versions prior to 27.1. TAKEOFF Specified the Flight Director guidance during takeoff as Flight Director Pitch Angle. DESCENT Updated information to harmonize the content with SOPM. APPROACH Updated information about inserting flap extension speeds in the MCDU. LEAVING THE AIRPLANE Updated information on turning off the electrical power

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AIRPLANE OPERATIONS MANUAL DESCRIPTION REDUCED VERTICAL SEPARATION MINIMUM (RVSM) Updated the Equipment Required table for RVSM. VERTICAL NAVIGATION - BARO VNAV Updated the Equipment Required table for BARO VNAV operation. REQUIRED NAVIGATION PERFORMANCE - RNP 0.3 (PRE-MOD MAU LOAD 27.1) Updated Equipment Required Table for RNP 0.3 operation. REQUIRED NAVIGATION PERFORMANCE - RNP 1 (PRE-MOD MAU LOAD 27.1) Updated Equipment Required table for RNP 1 operation. REQUIRED NAVIGATION PERFORMANCE - RNP 1 (PRE-MOD MAU LOAD 27.1) Editorial Update. REQUIRED NAVIGATION PERFORMANCE - RNP 4 (PRE-MOD MAU LOAD 27.1) Deleted information. REQUIRED NAVIGATION PERFORMANCE - RNP 10 (PRE-MOD MAU LOAD 27.1) Updated Equipment Required table for RNP 10 operation. PERFORMANCE BASED NAVIGATION - P-RNAV / B-RNAV / RNAV 5 (PRE-MOD MAU LOAD 27.1) Updated Equipment Required table for P-RNAV / B-RNAV / RNAV 5 operations. PERFORMANCE BASED NAVIGATION - RNAV 1 / RNAV 2 (PRE-MOD MAU LOAD 27.1) Updated Equipment Required table for RNAV 1 / RNAV 2 operations. REQUIRED NAVIGATION PERFORMANCE - RNP APCH (PRE-MOD MAU LOAD 27.1) Updated Equipment Required table for RNP APCH operation. RNP AR 0.3 WITH MISSED APPROACH 1.0 (PRE-MOD MAU LOAD 27.1) Updated Minimum Configuration List according to AFM.

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DESCRIPTION ICING CONDITIONS, COLD WEATHER AND COLD SOAK OPERATIONS Improved text related to ice shedding procedure. ICING CONDITIONS, COLD WEATHER AND COLD SOAK OPERATIONS Harmonized minimum fuel temperature with AFM and SOPM. ICING CONDITIONS, COLD WEATHER AND COLD SOAK OPERATIONS Improved text related to taxiing ICING CONDITIONS, COLD WEATHER AND COLD SOAK PROCEDURE Improved text related to ice shedding procedure. ICING CONDITIONS, COLD WEATHER AND COLD SOAK PROCEDURE Harmonized Minimum Fuel Temperature for APU Start with AFM and SOPM . ICING CONDITIONS, COLD WEATHER AND COLD SOAK PROCEDURE Added information related to the check of freedom of movement and full travel of flight controls. Suppl Procedures - Communication Added block. COMMUNICATION MANAGEMENT FUNCTION OPERATION Deleted information. CAT II ENGAGEMENT LOGIC Included information about CAT II operation when the use of RA is not authorized. CRG FWD (AFT) SMOKE Updated EICAS message CRG FWD (AFT) FIRE SYS FAIL in the CRG FWD (AFT) SMOKE procedure

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AIRPLANE OPERATIONS MANUAL DESCRIPTION CARGO COMPARTMENT FIRE Included note in the Cargo Compartment Fire procedure. DUAL ENGINE FAILURE Procedure updated due to AFM change. ENGINE FIRE, SEVERE DAMAGE OR SEPARATION Fuel Leak procedure included in the ENGINE FIRE, SEVERE DAMAGE OR SEPARATION ENGINE FIRE, SEVERE DAMAGE OR SEPARATION Changed maximum speed to VA. FUEL LEAK Removed the consideration about severe fuel leakage. PITCH TRIM RUNAWAY PITCH TRIM RUNAWAY procedure updated to include note regarding trim. ENGINE ABNORMAL VIBRATION Updated procedure in case the vibration is not due to ice accumulation as per GE Specific Operations Instructions. ENGINE AIRSTART ENVELOPE Engine Airstart Envelope changed. GEAR LEVER CAN NOT BE MOVED UP Updated GEAR LEVER CAN NOT BE MOVED UP procedure to comply with AFM revision. LOSS OF COMMUNICATIONS Added information. LOSS OF HYDRAULIC SYSTEM 3 Unified tables of Relevant Inoperative Items (mixed fleet only).

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4-03-02

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DESCRIPTION LOSS OF HYDRAULIC SYSTEM 1 AND 2 Go around flaps changed to 4. LOSS OF HYDRAULIC SYSTEM 1 AND 2 Go around flaps changed to 4. LOSS OF HYDRAULIC SYSTEM 2 AND 3 Go around flaps changed to 4. LOSS OF HYDRAULIC SYSTEM 2 AND 3 Go around flaps changed to 4. STRUCTURAL DAMAGE Changed speed limitation. VOLCANIC ASH Added step do shutdown the engine if ITT increases with engine in idle. BLEED 1 (2) LEAK Procedure updated due to AFM change. PRESN AUTO FAIL Procedure updated due to AFM change. AP FAIL Added information that AP may be re-engaged. AT FAIL Added information that AT may be re-engaged. SHAKER ANTICIPATED Speed limitation modified and added limitation of maximum 20° bank angle.

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4-03-07

4-03-08

AIRPLANE OPERATIONS MANUAL DESCRIPTION ELEC EMERGENCY Changed speed increment and landing factor. DC ESS BUS 1 OFF Updated list of Relevant Inoperative Items from DC ESS BUS 1 OFF DC ESS BUS 1 OFF Removed the instructions to use the Emergency/Parking Brake during landing. DC ESS BUS 2 OFF Updated list of Relevant Inoperative Items from DC ESS BUS 2 OFF DC ESS BUS 2 OFF Removed the instructions to use the Emergency/Parking Brake during landing. DC ESS BUS 3 OFF Removed the step to turn off the APU. ENG 1 (2) FAIL Fuel Leak procedure included in the ENG 1 (2) FAIL ENG REF ECS DISAG Note removed due to Black Label 6 or later. ENG 1 (2) FIRE Fuel Leak procedure included in the ENG 1 (2) FIRE ENG 1 (2) FIRE Changed maximum speed to VA. ELEVATOR LH (RH) FAIL Go around flaps changed to 4. ELEVATOR LH (RH) FAIL Go around flaps changed to 4. FLAP FAIL FLAP/SLAT FAIL table revised with new factors. PITCH TRIM FAIL Go around flaps changed to 4. PITCH TRIM FAIL Go around flaps changed to 4. SLAT FAIL FLAP/SLAT FAIL table revised with new factors.

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4-03-09

4-03-10 4-03-12

4-03-13

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DESCRIPTION AVNX MAU 1A FAIL Removed the instructions to use the Emergency/Parking Brake during landing. AVNX MAU 2B FAIL Removed the instructions to use the Emergency/Parking Brake during landing. FUEL IMBALANCE Text updated due to AFM change. A-I WING FAIL Changed time from 5 to 2 minutes in the A-I WING FAIL procedure BRK LH (RH) FAIL Removed the instructions to use the Emergency/Parking Brake during landing. LG WOW SYS FAIL Included guidance regarding go-around when landing gear lever can not be moved up. BRK LH (RH) FAULT Removed the instructions to use the Emergency/Parking Brake during landing. STAB TRIM SETTING FOR TAKEOFF Updated values of Stab Trim Setting table for airplanes with enhanced wing tip. UNFACTORED LANDING DISTANCE CONTAMINATED RUNWAY Deleted information. UNFACTORED LANDING DISTANCE CONTAMINATED RUNWAY Deleted information. UNFACTORED LANDING DISTANCE CONTAMINATED RUNWAY Deleted information. OPERATIONAL LANDING DISTANCE Added information. OPERATIONAL LANDING DISTANCE Added information. OPERATIONAL LANDING DISTANCE Added information.

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AIRPLANE OPERATIONS MANUAL DESCRIPTION ONE ENGINE INOPERATIVE - DRIFTDOWN Updated driftdown speeds for all conditions and changed Anti-ice & Ice Accretion assumptions. ONE ENGINE INOPERATIVE - DRIFTDOWN Updated driftdown speeds for all conditions and changed Anti-ice & Ice Accretion assumptions. FUEL AS BALLAST Added information. CARGO COMPARTMENT Included note about lithium batteries. CONFIGURATION DEVIATION LIST Updated reference to Dispatch Deviation Procedures Manual (DDPM). PASSENGER AND SERVICE DOORS Updated information about the use of service doors.

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DESCRIPTION GENERAL Improved introduction text. INDEX BY EICAS MESSAGE Deleted information. INDEX BY FAULTS NOT ANNUNCIATED THROUGH EICAS MESSAGES Deleted information. GROUND RESET PROCEDURES Updated the title of MAU Safety Procedures. Included step for Airplane Power Reset. Removed information of Nuisance Eicas Message or Fault. ACARS FROZEN Added information. ADS 1 FAIL Added information. ADS 2 (3) FAIL Added information. ADS PROBE 1 (2) FAIL Added information. ADS PROBE 3 FAIL Added information. ADS PROBE 4 FAIL Added information. A-I ENG 1 (2) FAULT Added information.

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AIRPLANE OPERATIONS MANUAL DESCRIPTION A-I WING FAIL Added information. AOA LIMIT FAIL Added information. APU FAIL Added information. AUDIO CONTROL PANEL INOPERATIVE Added information. AVNX MAU 1 (2,3) A (B) FAIL Added information. AVNX MAU 1 (2, 3) A (B) FAULT Added information. BLEED 1 (2) FAIL Added information. BRK CONTROL FAULT Added information. BRK LH (RH) FAULT Added information. EICAS FAULT Added information. ENG 1 SHORT DISPATCH Added information. ENG 2 SHORT DISPATCH Added information. FLT CTRL BIT EXPIRED Added information. FLT CTRL FAULT Added information. FLT CTRL NO DISPATCH Added information. FUEL FEED 1 (2) FAULT Added information. ICE DETECTOR 1 (2) FAIL Added information. IRS 1 FAIL Added information. IRS 2 FAIL Added information.

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DESCRIPTION LG NO DISPATCH Added information. MCDU 1 FROZEN / BLANK / BLINKING / RED X / TIMEOUT MSG Added information. MCDU 2 FROZEN / BLANK / BLINKING / RED X / TIMEOUT MSG Added information. MFD 1 FAULT Added information. MFD 2 FAULT Added information. PFD 1 FAULT Added information. PFD 2 FAULT Added information. PRINTER FAULT Added information. PRINTER NOT WORKING Added information. STEER FAIL Added information. WINDSHEAR FAIL Added information. WINDSHIELD 1 (2) HTR FAIL Added information. WX FAIL Added information. FLIGHT CONTROL RETURN TO SERVICE Added information. DEICING AND ANTI-ICING FLUIDS Added note to the description of types of fluids applicable to anti-icing and de-icing procedures. Embraer does not recommend the use of Alkali Organic Salt-based fluid. EXTERNAL LIGHTING Updated effectivity for navigation and anti collision lights information.

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14-03-10

14-05-05

14-05-35

14-08-10

14-09-05

AIRPLANE OPERATIONS MANUAL DESCRIPTION ENGINE BLEED SYSTEM Included information about bleed valve behaviour during single AMS pack operations. BLEED SOURCE PRIORITIZATION Updated conditions for APU bleed supply prioritization. OPERATING MODES Updated information regarding nominal differential pressure VERTICAL GUIDANCE CONTROLS Updated ALT SELECTOR KNOB description. LATERAL MODE ANNUNCIATIONS ON FMA Corrected lateral mode annunciation displayed on FMA. LATERAL MODE ANNUNCIATIONS ON FMA FGCS VERTICAL MODES Added effectivity applicable to TO MODE DE-ACTIVATION information. ELECTRICAL AC POWER Updated note about EICAS message IDG 1 (2) OIL. ELECTRICAL SYNOPTIC PAGE ON MFD Updated IDG description. AC/DC BUSSES LOAD DISTRIBUTION Replaced TCAS 2000 with TCAS for Embraer 170/175 models. AC/DC BUSSES LOAD DISTRIBUTION Updated information about optional equipment and equipment powered by buses AC GND SVC, DC GND SVC, AC BUS 2, and DC BUS 1. POWER UP BUILT IN TEST (PBIT) Updated Electrical Power Up Built In Test description. FLIGHT INSTRUMENTS Updated information about green dot use during driftdown for MAU Load 25.5.0.1. FLIGHT INSTRUMENTS Updated information about green dot use during driftdown in ice conditions for MAU Load 25.6. COMMUNICATION Updated BACKUP VOLUME CONTROL BUTTON/KNOB - volume adjustment.

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14-09-20

14-09-35

14-10-10 14-12-10 14-13-15

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DESCRIPTION INTEGRATED ELECTRONIC STANDBY SYSTEM Updated information related to IESS display of airspeed and Mach number. DIGITAL VOICE DATA RECORDER (DVDR) SYSTEM Included capacity of recording 120 min of datakink data. COMMUNICATION MANAGEMENT FUNCTION (CMF) Updated effectivity of DATALINK 1 FAIL and DATALINK 1 (2) FAIL. COMMUNICATION MANAGEMENT FUNCTION (CMF) Updated information of EICAS message related to CMF. RADIO NAVIGATION SYSTEM Improved MCDU representative figures of Transponder system. RADIO NAVIGATION SYSTEM Included information about Enhanced Transponder and ADS-B Out Transponder. EICAS MESSAGES Updated information about CMF and DATALINK messages. EICAS MESSAGES Added FMS messages applicable to airplanes equipped with Load MAU 27.1 and on. EICAS MESSAGES Updated ATC DATALINK 1 (2) FAIL message title and its applicability. FUEL LOW LEVEL WARNING Added note about FUEL 1 (2) LO LEVEL warning EICAS message. AIR DATA SMART PROBE/TAT HEATING SYSTEM Updated ADSP/TAT heating system description. LANDING GEAR OPERATION Updated description of landing gear retraction due to PSEM-5 logic. EICAS MESSAGES Improved description of BRK CONTROL FAULT message.

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14-15-40

AIRPLANE OPERATIONS MANUAL DESCRIPTION MESSAGES ON EICAS Included several messages applicable to airplanes equipped with Load 27.1. MESSAGES ON EICAS Updated applicability of EICAS message related to CMF and CPLDC functionality. WINDSHEAR ESCAPE GUIDANCE MODE Updated the engine thrust mode when following windshear escape guidance. TRAFFIC COLLISION AVOIDANCE SYSTEM (TCAS) Included Statement of Compliance for TCAS change 7.1.

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LIST OF EFFECTIVE PAGES

LIST OF EFFECTIVE PAGES (VOLUME 1) ORIGINAL ...................................0 ................................... DEC 10, 2003 REVISION ...................................1 ................................... FEB 20, 2004 REVISION ...................................2 ................................... MAY 31, 2004 REVISION ...................................3 ................................... DEC 23, 2004 REVISION ...................................4 ................................... SEP 05, 2005 REVISION ...................................5 ................................... JUL 28, 2006 REVISION ...................................6 ................................... MAY 15, 2007 REVISION ...................................7 ................................... SEP 28, 2007 REVISION ...................................8 ................................... APR 29, 2008

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..................................18 .................................. JUL 02, 2014

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..................................19 .................................. OCT 17, 2014

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..................................20 .................................. MAY 04, 2015

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BLOCK 3-60 (rev) 3-60 (rev) 3-60 (add) 3-60 (add) 3-68 3-68 3-68 3-68 3-70 (rev) 3-70 (rev) 3-70 (rev) 3-70 (rev) 3-70 (rev) 3-70 (rev) 3-70 (rev) 3-70 (rev) 3-70 (rev) 3-70 (rev) 3-70 (add) 3-70 (add) 3-72 3-72 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 9 Rev. 9 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

BLOCK 3-80 (rev) 3-80 (rev) 3-80 (add) 3-80 (add) 3-94 3-94 3-95 (rev) 3-95 (rev) 3-95 (rev) 3-95 (rev) 3-95 (rev) 3-95 (rev) 3-95 (rev) 3-95 (rev) 3-97 (rev) 3-97 (rev) 3-97 (rev) 3-97 (rev) 4-TOC 4-TOC 4-INTRO 4-INTRO 4-INTRO 4-INTRO 4-01-01-TOC 4-01-01-TOC 4-01-01 (rev) 4-01-01 (rev) 4-01-01 (rev) 4-01-01 (rev) 4-01-01 (rev) 4-01-01 (rev) 4-01-01 (rev) 4-01-01 (rev) 4-01-01 (rev) 4-01-01 (rev) 4-01-01 (rev) 4-01-01 (rev) 4-02-01-TOC 4-02-01-TOC 4-02-01-TOC 4-02-01-TOC

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 20 Rev. 20 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 10 Rev. 10 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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BLOCK 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-75 (rev) 3-76 (add) 3-76 (add) 3-80 (rev) 3-80 (rev) 3-80 (rev) 3-80 (rev) 3-80 (rev) 3-80 (rev) 3-80 (rev) 3-80 (rev) 3-80 (rev) 3-80 (rev) 3-80 (rev) 3-80 (rev) 3-80 (rev) 3-80 (rev) 3-80 (rev) 3-80 (rev) 3-80 (rev) 3-80 (rev) 3-80 (rev) 3-80 (rev)

AIRPLANE OPERATIONS MANUAL

AIRPLANE OPERATIONS MANUAL

AOM-1502-003

BLOCK 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01 4-02-01

(rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev) (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

BLOCK 4-02-01 (rev) 4-02-01 (rev) 4-02-01 (rev) 4-02-01 (rev) 4-02-01 (rev) 4-02-01 (rev) 4-02-01 (rev) 4-02-01 (rev) 4-02-01 (rev) 4-02-01 (rev) 4-02-01 (rev) 4-02-01 (rev) 4-03-01-TOC 4-03-01-TOC 4-03-01 4-03-01 4-03-01 4-03-01 4-03-01 4-03-01 4-03-02-TOC (rev) 4-03-02-TOC (rev) 4-03-02 (rev) 4-03-02 (rev) 4-03-02 (rev) 4-03-02 (rev) 4-03-02 (rev) 4-03-02 (rev) 4-03-02 (rev) 4-03-02 (rev) 4-03-02 (rev) 4-03-02 (rev) 4-03-02 (rev) 4-03-02 (rev) 4-03-02 (rev) 4-03-02 (rev) 4-03-03-TOC 4-03-03-TOC 4-03-03 (rev) 4-03-03 (rev) 4-03-03 (rev) 4-03-03 (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 13 Rev. 13 Rev. 11 Rev. 11 Rev. 11 Rev. 11 Rev. 11 Rev. 11 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 18 Rev. 18 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 20 Rev. 20 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

BLOCK 4-03-06 (rev) 4-03-06 (rev) 4-03-07-TOC 4-03-07-TOC 4-03-07 (rev) 4-03-07 (rev) 4-03-07 (rev) 4-03-07 (rev) 4-03-07 (rev) 4-03-07 (rev) 4-03-08-TOC 4-03-08-TOC 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-08 (rev) 4-03-09-TOC 4-03-09-TOC 4-03-09-TOC 4-03-09-TOC 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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BLOCK 4-03-03 (rev) 4-03-03 (rev) 4-03-03 (rev) 4-03-03 (rev) 4-03-04-TOC 4-03-04-TOC 4-03-04 4-03-04 4-03-04 4-03-04 4-03-05-TOC (rev) 4-03-05-TOC (rev) 4-03-05 (rev) 4-03-05 (rev) 4-03-05 (rev) 4-03-05 (rev) 4-03-05 (rev) 4-03-05 (rev) 4-03-05 (rev) 4-03-05 (rev) 4-03-05 (rev) 4-03-05 (rev) 4-03-05 (rev) 4-03-05 (rev) 4-03-05 (rev) 4-03-05 (rev) 4-03-05 (rev) 4-03-05 (rev) 4-03-06-TOC 4-03-06-TOC 4-03-06 (rev) 4-03-06 (rev) 4-03-06 (rev) 4-03-06 (rev) 4-03-06 (rev) 4-03-06 (rev) 4-03-06 (rev) 4-03-06 (rev) 4-03-06 (rev) 4-03-06 (rev) 4-03-06 (rev) 4-03-06 (rev)

AIRPLANE OPERATIONS MANUAL

AIRPLANE OPERATIONS MANUAL

AOM-1502-003

BLOCK 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (rev) 4-03-09 (del) 4-03-09 (del) 4-03-10-TOC 4-03-10-TOC 4-03-10 (rev) 4-03-10 (rev) 4-03-10 (rev) 4-03-10 (rev) 4-03-10 (rev) 4-03-10 (rev) 4-03-10 (rev) 4-03-10 (rev) 4-03-11-TOC 4-03-11-TOC 4-03-11 4-03-11 4-03-11 4-03-11 4-03-11 4-03-11 4-03-11 4-03-11 4-03-12-TOC (rev) 4-03-12-TOC (rev) 4-03-12 (rev) 4-03-12 (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 18 Rev. 18 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 21 Rev. 21 Rev. 21 Rev. 21

BLOCK 4-03-12 (rev) 4-03-12 (rev) 4-03-12 (rev) 4-03-12 (rev) 4-03-12 (rev) 4-03-12 (rev) 4-03-13-TOC (rev) 4-03-13-TOC (rev) 4-03-13 (rev) 4-03-13 (rev) 4-03-13 (rev) 4-03-13 (rev) 4-03-13 (rev) 4-03-13 (rev) 4-03-13 (rev) 4-03-13 (rev) 4-03-14-TOC 4-03-14-TOC 4-03-14 4-03-14 4-04-54-TOC 4-04-54-TOC 4-04-54 4-04-54 4-04-54 4-04-54 4-04-57-TOC 4-04-57-TOC 4-04-57 4-04-57 5-TOC (rev) 5-TOC (rev) 5-01 5-01 5-01 5-01 5-10 (rev) 5-10 (rev) 5-10 (rev) 5-10 (rev) 5-10 (rev) 5-10 (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 10 Rev. 10 Rev. 10 Rev. 10 Rev. 21 Rev. 21 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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REVISION Rev. 21 Rev. 21 Rev. 16 Rev. 16 Rev. 16 Rev. 16 Rev. 16 Rev. 16 Rev. 16 Rev. 16 Rev. 16 Rev. 16 Rev. 16 Rev. 16 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

BLOCK 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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BLOCK 5-10 (rev) 5-10 (rev) 5-15 5-15 5-15 5-15 5-15 5-15 5-15 5-15 5-15 5-15 5-15 5-15 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev)

AIRPLANE OPERATIONS MANUAL

AIRPLANE OPERATIONS MANUAL

AOM-1502-003

BLOCK 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

BLOCK 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-20 (rev) 5-25 (rev) 5-25 (rev) 5-25 (rev) 5-25 (rev) 5-25 (rev) 5-25 (rev) 5-25 (rev) 5-25 (rev) 5-25 (rev) 5-25 (rev) 5-25 (rev) 5-25 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

BLOCK 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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BLOCK 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-30 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev)

AIRPLANE OPERATIONS MANUAL

AIRPLANE OPERATIONS MANUAL

AOM-1502-003

BLOCK 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

BLOCK 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev) 5-35 (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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REVISION Rev. 21 Rev. 21 Rev. 14 Rev. 14 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

BLOCK 6-07 (rev) 6-07 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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BLOCK 5-35 (rev) 5-35 (rev) 5-40 5-40 6-TOC (rev) 6-TOC (rev) 6-TOC (rev) 6-TOC (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev) 6-05 (rev)

AIRPLANE OPERATIONS MANUAL

AIRPLANE OPERATIONS MANUAL

AOM-1502-003

BLOCK 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev) 6-10 (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

BLOCK 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15

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REVISION Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18

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REVISION Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 21 Rev. 21

BLOCK 6-20 (rev) 6-20 (rev) 6-20 (rev) 6-20 (rev) 6-20 (rev) 6-20 (rev) 6-20 (rev) 6-20 (rev) 6-20 (rev) 6-20 (rev) 6-20 (rev) 6-20 (rev) 6-20 (rev) 6-20 (rev) 6-25 6-25 6-25 6-25 6-25 6-25 6-25 6-25 6-25 6-25 6-25 6-25 6-25 6-25 6-25 6-25 6-25 6-25 6-25 6-25 6-25 6-25 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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BLOCK 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-15 6-20 (rev) 6-20 (rev)

AIRPLANE OPERATIONS MANUAL

AIRPLANE OPERATIONS MANUAL

AOM-1502-003

BLOCK 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

BLOCK 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-30 (rev) 6-35 (rev) 6-35 (rev) 6-35 (rev) 6-35 (rev) 6-35 (rev) 6-35 (rev) 6-35 (rev) 6-35 (rev) 6-35 (rev) 6-35 (rev) 6-35 (rev) 6-35 (rev) 7-TOC (rev) 7-TOC (rev) 7-INTRO 7-INTRO 7-05 7-05 7-05 7-05 7-10 (rev) 7-10 (rev) 7-10 (rev) 7-10 (rev) 7-10 (rev) 7-10 (rev) 7-10 (rev) 7-10 (rev) 7-10 (rev) 7-10 (rev) 7-10 (rev) 7-10 (rev) 7-10 (rev) 7-10 (rev) 7-10 (rev) 7-10 (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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REVISION Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 20 Rev. 20 Rev. 9 Rev. 9 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 12 Rev. 12 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

BLOCK 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-40 8-40 8-40 8-40 8-40 8-40 8-50 8-50 8-50 8-50 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev)

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 11 Rev. 11 Rev. 11 Rev. 11 Rev. 11 Rev. 11 Rev. 12 Rev. 12 Rev. 12 Rev. 12 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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BLOCK 7-15 7-15 7-15 7-15 7-15 7-15 7-15 7-15 7-15 7-15 7-15 7-15 8-TOC 8-TOC 8-INTRO 8-INTRO 8-10 8-10 8-10 8-10 8-10 8-10 8-10 8-10 8-20 8-20 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev) 8-30 (rev)

AIRPLANE OPERATIONS MANUAL

AIRPLANE OPERATIONS MANUAL

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BLOCK 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-60 (rev) 8-70 8-70 8-70 8-70 8-70 8-70 8-70 8-70 8-70 8-70 8-70 8-70 8-70 8-70 8-70 8-70 8-70 8-70 8-80 8-80 8-80 8-80 8-85 8-85 8-90 8-90 8-90 8-90 9-TOC 9-TOC 9-01 (rev) 9-01 (rev) 10-TOC 10-TOC 10-01 10-01 11-TOC 11-TOC

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 10 Rev. 10 Rev. 10 Rev. 10 Rev. 16 Rev. 16 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 21 Rev. 21 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 20 Rev. 20

BLOCK 11-INTRO 11-INTRO 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-05 (rev) 11-06 11-06 11-06 11-06 11-06 11-06 11-06 11-06 11-06 11-06

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REVISION Rev. 9 Rev. 9 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17

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REVISION Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 13 Rev. 13 Rev. 13 Rev. 13 Rev. 12 Rev. 12 Rev. 17 Rev. 17

BLOCK 11-20 11-20 11-25 11-25 11-30 11-30 12-TOC 12-TOC 12-INTRO 12-INTRO 12-05 12-05 12-40 (rev) 12-40 (rev) 12-40 (rev) 12-40 (rev) 12-40 (rev) 12-40 (rev) 12-40 (rev) 12-40 (rev) 12-40 (rev) 12-40 (rev) 12-40 (rev) 12-40 (rev) 13-TOC (rev) 13-TOC (rev) 13-INTRO 13-INTRO 13-05 13-05 13-05 13-05 13-05 13-05 13-05 13-05 13-10 13-10 13-10 13-10 13-10 13-10

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REVISION Rev. 17 Rev. 17 Rev. 9 Rev. 9 Rev. 12 Rev. 12 Rev. 17 Rev. 17 Rev. 9 Rev. 9 Rev. 14 Rev. 14 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 9 Rev. 9 Rev. 16 Rev. 16 Rev. 16 Rev. 16 Rev. 16 Rev. 16 Rev. 16 Rev. 16 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 17

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BLOCK 11-06 11-06 11-06 11-06 11-06 11-06 11-06 11-06 11-06 11-06 11-06 11-06 11-06 11-06 11-06 11-06 11-06 11-06 11-08 (rev) 11-08 (rev) 11-08 (rev) 11-08 (rev) 11-08 (rev) 11-08 (rev) 11-08 (rev) 11-08 (rev) 11-08 (rev) 11-08 (rev) 11-08 (rev) 11-08 (rev) 11-08 (rev) 11-08 (rev) 11-08 (rev) 11-08 (rev) 11-10 11-10 11-10 11-10 11-15 11-15 11-20 11-20

AIRPLANE OPERATIONS MANUAL

AIRPLANE OPERATIONS MANUAL

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BLOCK 13-10 13-10 13-10 13-10 13-11 13-11 13-11 13-11 13-11 13-11 13-11 13-11 13-11 13-11 13-15 13-15 13-15 13-15 13-25 13-25 13-25 13-25 13-25 13-25 13-25 13-25 13-25 13-25 13-25 13-25 13-30 13-30 13-30 13-30 13-35 13-35 13-35 13-35 13-40 13-40 13-40 13-40

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REVISION Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 12 Rev. 12 Rev. 12 Rev. 12

BLOCK 13-40 13-40 13-45 13-45 13-45 13-45 13-45 13-45 13-50 13-50 13-50 13-50 13-55 13-55 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev) 13-60 (rev)

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REVISION Rev. 12 Rev. 12 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 18 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 9 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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BLOCK 13-60 (rev) 13-60 (rev) 13-60 (add) 13-60 (add) 13-60 (add) 13-60 (add) 13-60 (add) 13-60 (add) 13-60 (add) 13-60 (add) 13-60 (add) 13-60 (add) 13-60 (add) 13-60 (add) 13-60 (add) 13-60 (add) 13-60 (add) 13-60 (add) 13-60 (add) 13-60 (add) 13-70 (rev) 13-70 (rev) 13-70 (rev) 13-70 (rev) 13-70 (rev) 13-70 (rev) 13-70 (rev) 13-70 (rev) 13-70 (rev) 13-70 (rev) 13-70 (rev) 13-70 (rev) 13-70 (rev) 13-70 (rev)

AIRPLANE OPERATIONS MANUAL

AIRPLANE OPERATIONS MANUAL

TABLE OF CONTENTS

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VOLUME 1 TABLE OF CONTENTS

SECTION 1

GENERAL INFORMATION AND DEFINITION OF TERMS

SECTION 2

LIMITATIONS

SECTION 3

NORMAL PROCEDURES

SECTION 4

EMERGENCY AND ABNORMAL PROCEDURES

SECTION 5

PERFORMANCE

SECTION 6

FLIGHT PLANNING

SECTION 7

WEIGHT AND BALANCE

SECTION 8

LOADING

SECTION 9

CONFIGURATION DEVIATION LIST

SECTION 10

MINIMUM EQUIPMENT LIST

SECTION 11

EMERGENCY INFORMATION

SECTION 12

EMERGENCY EVACUATION

SECTION 13

GROUND SERVICING

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General Information............................................. 1-01 ........... GENERAL.............................................................. 1-01 ........... REVISIONS............................................................ 1-01 ........... TEMPORARY REVISIONS.................................... 1-01 ........... LIST OF EFFECTIVE PAGES............................... 1-01 ...........

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EFFECTIVITY........................................................ 1-01 ........... OPERATIONAL REQUIREMENTS AND THE AIRPLANE OPERATIONS MANUAL............... 1-01 ........... EMBRAER AIRPLANE OPERATIONS MANUAL. . 1-01 ........... AIRPLANE OPERATIONS MANUAL STRUCTURE................................................... 1-01 ...........

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Abbreviations and Acronyms............................. 1-20 ........... ABBREVIATIONS AND ACRONYMS.................... 1-20 ...........

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Units Conversion................................................. 1-25 ........... UNITS CONVERSION........................................... 1-25 ...........

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Service Bulletins.................................................. 1-35 ........... SERVICE BULLETIN TABLE................................. 1-35 ...........

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3 4 4

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GENERAL This Airplane Operations Manual provides useful information to complement the Airplane Flight Manual, Weight and Balance Manual and the Master Minimum Equipment List. It must be used in conjunction with those publications to safe and efficiently operate the airplane. Any difference found between the data in the Airplane Operations Manual and the approved manuals is attributable to airplane modifications and scheduling of amendments to publications. In the event of such a difference, the data contained in the approved manuals must prevail.

REVISIONS Embraer may periodically revise this manual as required to update information or to provide information not available at the time of last issue. Revised data may result from either airplane modifications or improved techniques gained through operational experience. Changes to the content are indicated by a vertical line in the outside page margin, at the direction of revised text, graphic or table. A deleted text, graph or table is marked by a vertical line in the outside margin, at the direction of immediate previous line. A deleted table row is marked by a vertical line in the outside margin, at the direction of immediate next row. For relocated or rearranged contents, the vertical line marker is drawn adjacent to the page number. The basic issue date of this Manual is presented on the title page. Subsequent revisions are sequentially numbered (Revision 1, Revision 2, and so forth). The last Revision number is presented on the title page and on the footer of every page affected, replacing the former number.

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The status of each page is presented in the List of Effective Pages (LEP).

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TEMPORARY REVISIONS Temporary revisions may be issued when the need arises. The temporary revision pages will be clearly identified and they are to be inserted adjacent to the affected page. Temporary revisions description are presented at the Log of Temporary Revisions. Temporary revision pages status is not included in the List of Effective Pages. Temporary revision pages shall be removed when the changed content is either incorporated or canceled by a Revision.

LIST OF EFFECTIVE PAGES A List of Effective Pages (LEP) for all the sections is located at the beginning of this Manual. The LEP presents the list of revision numbers with the corresponding revision date, as well as the roll of pages with the current revision number. The LEP is updated at every revision, and it is the reference to verify each Manual page for its proper updating status.

EFFECTIVITY

!Effectivity range to which this information is applicable

Texts, tables and graphics applicable to a specific airplane range are identified by: a preceding start tag and text (presented in a different font type) and an end tag at the final of the marked element. This paragraph constitutes an example of effectivity text.

SUB-EFFECTIVITY

!!Sub-effectivity range to which this information is applicable

When the information is applicable to a specific range within a marked range, they are identified by: a double start tag and text and a double end tag at the final of the marked element. This paragraph constitutes an example of sub-effectivity text.

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"" "

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GENERAL INFORMATION AND DEFINITION OF TERMS

OPERATIONAL REQUIREMENTS AND AIRPLANE OPERATIONS MANUAL

THE

The existence of fleets composed of airplanes or other aircraft types built by different manufacturers, led the Airworthiness Authorities to require operators’ certification, in addition to the airplane’s certification. The idea is to standardize manuals, training and operation, so as to make it easier for a pilot to change equipment. As an example, if a pilot used to fly an EMBRAER airplane (ERJ-145) is scheduled to fly another EMBRAER airplane (EMBRAER 170/175/190/195), the training syllabus required for both airplane families/models needs to be very similar; the operator’s normal, abnormal and emergency procedures presentation must be similar for all airplanes even when there are different AFMs with different presentation for those procedures, as well as the manuals for both airplanes. By doing so, the operator will assure that human factors/errors are minimized. Some Operation Requirements just define the main subjects that must be presented in an Airplane Operations Manual. However, even detailing the AOM at that level, all the requirements let the operators free to use different Airplane Operations Manual structures, depending on the manuals that have been already issued. Therefore, EMBRAER has developed this AOM in an attempt to cover, in the best possible manner, the most currently used requirements. By doing so, it is possible for an operator to use the EMBRAER AOM by just adding some missing information that is specific to that operator. Below is a suggested Airplane Operations Manual structure to comply with most of the Operation Requirements:

PART A Presents operator’s administrative information, such as who are the president, vice-president, the managers, who is the chief pilot for the fleet, who is the responsible for revising manuals, where the offices and bases are located, etc.

PART B

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Presents airplane related information, such as procedures, performance, dispatch, Weight and Balance, bulletins and systems description.

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PART C Presents the operator’s airport and route information (performance and navigation).

PART D Presents training information.

EMBRAER AIRPLANE OPERATIONS MANUAL This Embraer Airplane Operations Manual covers only Part B. Parts A and D should be generated by the operator only. Part C can be generated by the operator with the help of Embraer operations softwares (runway analysis, driftdown, and route analysis).

AIRPLANE OPERATIONS MANUAL STRUCTURE The Embraer Airplane Operations Manual is organized in two volumes, with the following contents: Volume 1: – 1 General – 2 Limitations – 3 Normal Procedures – 4 Emergency and Abnormal Procedures – 5 Performance – 6 Flight Planning – 7 Weight and Balance – – – – –

8 Loading 9 Configuration Deviation List 10 Minimum Equipment List 11 Emergency Information 12 Emergency Evacuation

Volume 2: – 14-01 Airplane Description – 14-02 Air Management System – 14-03 Automatic Flight

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– 13 Ground Servicing

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– 14-04 Auxiliary Power Unit – 14-05 Electrical – 14-06 Engine – 14-07 Fire Protection – 14-08 Flight Controls – 14-09 Flight Instruments, Communication, Navigation and Flight Management System – 14-10 Fuel – 14-11 Hydraulic – – – –

14-12 14-13 14-14 14-15

Ice and Rain Protection Landing Gear and Brakes Oxygen Warning System

Each of the above sections may be divided into smaller parts, called blocks. The number of the section followed by a two-digit number identifies such blocks. For example: Section 14-03 can be divided as follows: – 14-03-01 General Description – 14-03-05 Controls and Indications – 14-03-10 Flight Guidance Control System – 14-03-20 Thrust Management – 14-03-30 EICAS Messages

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The page numbering restarts at each block.

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DEFINITION OF TERMS The following definitions apply to the terms below: WARNING: OPERATING PROCEDURES, TECHNIQUES AND OTHER RELATED INFORMATION, WHICH MAY RESULT IN PERSONAL INJURY OR LOSS OF LIFE, IF NOT FOLLOWED. CAUTION: OPERATING PROCEDURES, TECHNIQUES AND OTHER RELATED INFORMATION, WHICH MAY RESULT IN DAMAGE OR DESTRUCTION OF EQUIPMENT, IF NOT FOLLOWED. Cautionary operating range: Cautionary operating range may indicate a potential hazard or system malfunction.

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NOTE: Operating procedures, techniques and other related information, which are considered essential to emphasize the safety of flight.

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ABBREVIATIONS AND ACRONYMS ABBREVIATION ° °C °F  A A/C A/I ABC ABM ABV AC ACARS ACE ACMP ACN ACP ACT ADA ADC ADF ADI ADS ADS-B

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ADSP AFCS AFE AFM AFT AFU AGL AICC

DESCRIPTION Degree Degree Celsius Degree Fahrenheit Liter Ampere Aircraft Anti-Ice Auxiliary Power Unit Start Bus Contactor Auto Brake Control Module Auxiliary Power-Unit Bleed-Valve Advisory Circular Aircraft Communication Addressing and Reporting System Actuator Control Electronics Alternating-Current Motor-Driven Pump Aircraft Classification Number Audio Control Panel Altitude Compensated Tilt Air Data Application Air Data Computer Automatic Direction Finder Attitude Director Indicator Air Data System Automatic Dependent Surveillance Broadcast Air Data Smart Probe Automatic-Flight Control System Above Field Elevation Airplane Flight Manual Afterward Artificial Feel Unit Above Ground Level Auxiliary Integrated Control Center

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ABBREVIATION AIOP AIP ALD ALT AMI AMM AMS ANR AOA AOC AOM AP APM APP APPR APR APU ARINC ARM ASC ASCB ASEL ASTM AT ATC ATIS ATS ATTCS ATTND AUTO AVAIL AZFW B-RNAV BARO BATT

AIRPLANE OPERATIONS MANUAL

DESCRIPTION Actuator Input-Output Processor Aeronautical Information Publication Actual Landing Distance Altitude Airline Modifiable Information Aircraft Maintenance Manual Air Management System Automatic Navigation Realignment Angle of Attack Airline Operational Communications Airplane Operations Manual Autopilot Aircraft Personality Module Approach Approach Approach Auxiliary Power Unit Aeronautical Radio Incorporated Armed APU Start Contactor Avionics Standard-Communication Bus Altitude Select American Society of Testing Material Autothrottle Air Traffic Control Automatic-Terminal-Information Service Air Turbine Starter Automatic Takeoff-Thrust Control-System Attendant Automatic Available Actual Zero Fuel Weight Basic Required Navigation Barometric Setting Battery

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AIRPLANE OPERATIONS MANUAL ABBREVIATION BC BCM BEW BFO BIT BOD BRG BRK BRT BTC CAB CAFM CAGE CAS CAT I CAT II CB CCD CDI CDL CFR CG CGD CH CKPT CLB CLR cm CMC CMD CMF CMS COMM CON COND

GENERAL INFORMATION AND DEFINITION OF TERMS

DESCRIPTION Back Course Brake Control Module Basic Empty Weight Beat Frequency Oscillator Built-in Test Bottom of Descent Bearing Brake Bright Bus Tie Contactor Cabin Computerized Airplane Flight Manual Commercial and Government Entity Calibrated Airspeed Category I Operation Category II Operation Circuit Breaker Cursor Control Device Course Deviation Indicator Configuration Deviation List Code of Federal Regulations Center of Gravity Corrected Ground Distance Channel Cockpit Climb Clear Centimeter Central Maintenance Computer Command Communications Management Function Configuration Management System Communications Continuous Conditioning

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ABBREVIATION CPC CPCS CRS CRZ CTRL CVR DB DC DDPM DET DGRAD DH DIM DISC DLK DME DMU DN DO DOW DR DU DVDR E-BAY EADI EASA EBV ECAFM ECEF ECL ECS EDP EDS EFB EGPWM

AIRPLANE OPERATIONS MANUAL

DESCRIPTION Cabin Pressure Controller Cabin Pressure Control-System Course Cruise Control Cockpit Voice Recorder Database Direct Current Dispatch Deviation Procedures Manual Detector Degraded Decision Height Dimmer Disconnect Datalink Distance Measuring Equipment Data-Loader Management Unit Down RTCA Document Dry Operating Weight Dead Reckoning Display Unit Digital Voice-Data Recorder Electronic Bay Electronic Attitude Director Indicator European Aviation Safety Agency Engine Bleed Valve Electronic Computerized AFM Earth-Centered Earth-Fixed Electronic Checklist Environmental Control System Engine Driven Pump Electronic Display System Electronic Flight Bag Enhanced Ground-Proximity Warning-Module

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AIRPLANE OPERATIONS MANUAL ABBREVIATION EGPWS EGT EHSI EICAS EICC ELEC ELPU ELT EMERG ENG EPNL EPU ESS ETA ETC ETE ETP FAA FADEC FAF FAP FAR FAWP FBW FCM FCOC FCP FCS FCU FCV FD FDR FGCS FIM FIREX

GENERAL INFORMATION AND DEFINITION OF TERMS

DESCRIPTION Enhanced Ground-Proximity Warning-System Exhaust Gas Temperature Electronic Horizontal Situation-Indicator Engine Indication and Crew Alerting System Emergency Integrated Control Center Electrical Emergency Lights Power Unit Emergency Locator Transmitter Emergency Engine Effective Perceived Noise Level Estimated Position Uncertainty Essential Estimated Time of Arrival Elevator Thrust Compensation Estimated Time Enroute Equal Time Point Federal Aviation Authority Full-Authority Digital Electronic-Control Final Approach Fix Flight Attendant Panel Federal Aviation Regulations Final Approach Waypoint Fly-by-wire Flight Control Module Fuel Cooled Oil Cooler Flight Control Panel Flight Control System Fuel Conditioning Unit Flow Control Valve Flight Director Flight Data Recorder Flight Guidance Control System Fault Isolation Manual Fire Extinguisher

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ABBREVIATION FL FLCH FLEX FMA FMS FMU FOM FPA FPL FPR FSTN ft ft/min ft3 FWD g G/A GA GCU GD GEN GMAP GND GNSS GP GPS GPU GPWS GS h HDG HDOP HDPH HF HGS

AIRPLANE OPERATIONS MANUAL

DESCRIPTION Flight Level Flight Level Change Flexible Flight Mode Annunciator Flight Management System Fuel Metering Unit Figure of Merit Flight Path Angle Flight Plan Flight Path Reference Fasten Foot Foot per Minute Cubic Foot Forward Gravity Acceleration Go-Around Go Around Generator Control Unit Ground Distance Generator Ground Map Ground Global Navigation Satellite System Guidance Panel Global Positioning System Ground Power Unit Ground-Proximity Warning System Glide Slope Hour Heading Horizontal Dilution of Precision Headphone High Frequency Head-up Guidance System

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AIRPLANE OPERATIONS MANUAL ABBREVIATION HI HP hPa HPU

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HS-ACE HSA HSI HYD Hz I/O IAF IAS IATA IBIT ICAO ICC ID IDG IESS IFE IFR IGN ILS in INBD inHg INHIB INIT INOP INPH INT IRS IRU ISA

GENERAL INFORMATION AND DEFINITION OF TERMS

DESCRIPTION High High Pressure Hectopascal High Pressure Unit Horizontal-Stabilizer Actuator-Control Electronics Horizontal Stabilizer Actuator Horizontal Situation Indicator Hydraulic Hertz Input/Output Initial Approach Fix Indicated Air Speed International Air Transport Association Inflight Built In Test International Civil Aviation Organization Integrated Control-Center Identification Integrated Drive Generator Integrated Electronic Standby System In Flight Entertainment Instrument Flight Rules Ignition Instrument Landing System Inch Inboard Inch of Mercury Inhibition Initialization Inoperative Interphone Internal Inertial Reference System Inertial Reference Unit International Standard Atmosphere

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ABBREVIATION ITT IU IU/lb KCAS kg kg/m2 KIAS km km/h kPa KPH kt kVA LAN LAT LAV lb lb/ft2 lb/US gal lb.in lbf LCD LDA LDG LED LEMAC LFE LG LH LICC LIM LNAV LO LOC LOC-BC

AIRPLANE OPERATIONS MANUAL

DESCRIPTION Interturbine Temperature Index Unit index Unit per Pound Calibrated Airspeed in Knots Kilogram Kilogram per Square Meter Indicated Airspeed in Knots Kilometer Kilometer per Hour Kilopascal Kilograms per Hour Knot Kilovolt-Ampere Local Area Network Latitude Lavatory Pound Pound per Square Foot Pound per Gallon Pound Inch Pound Force Liquid-Crystal Display Localizer Directional Aid Landing Gear Light-Emitting Diode Leading Edge Aerodynamic Chord Landing Field Elevation Landing Gear Left-Hand Left Integrated Control Center Limited Thrust Lateral Navigation Low Localizer Localizer-Back Course

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AIRPLANE OPERATIONS MANUAL ABBREVIATION LON LP LRC LRM LRU LSA LSK LT LVTO m m3 MAC MAINT MAP MAU MAX MaxAT mbar MCDU MDA MEA MEL MEW MFD MHz MIC MID min MLG MLS MLW mm MMEL MMO MOD

GENERAL INFORMATION AND DEFINITION OF TERMS

DESCRIPTION Longitude Low Pressure Long Range Cruise Line Replaceable Module Line Replaceable Unit Low Speed Awareness Line Select Key Light Low Visibility Takeoff Meter Cubic Meter Mean Aerodynamic Chord Maintenance Multiple Alarm Panel Modular Avionics Unit Maximum Maximum Assumed Temperature Milibar Multifunction Control Display Unit Minimum Descent Altitude Minimum Enroute Altitude Minimum Equipment List Manufacture Empty Weight Multi-Function Display Megahertz Microphone Middle Minute Main Landing Gear Microwave Landing System Maximum Landing Weight Millimeter Master Minimum Equipment List Maximum Mach Operation Module

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ABBREVIATION MOW mph MPP MRC MRW MSA MSL MTOW MZFW N1 N2 NAD-83 NAS NAV NAVCOM NBPT NDB NIC NIM NLG NM Notam NPRV NVM OAT OBV ODS OEI OEW OFV OOOI OUTBD OVHT OVRD OVSP

AIRPLANE OPERATIONS MANUAL

DESCRIPTION Maximum Design Operating Weight Mile per Hour Maintenance Practices and Procedures Modular Radio Cabinet Maximum Ramp Weight Minimum Safety Altitude Mean Sea Level Maximum Takeoff Weight Maximum Zero Fuel Weight Fan Rotor Speed Core Rotor Speed North American Datum 1983 National Airspace System Navigation Navigation & Communication No-Break Power Transfer Non-Directional Beacon Network Interface Controller Network Interface Module Nose Landing Gear Nautical Miles Notices to Airmen Negative Pressure Relief Valve Non-Volatile Memory Outside Air Temperature Operability Bleed Valve Overheat Detection System One Engine Inoperative Operational Empty Weight Outflow Valve Out, Off, On and In Outboard Overheat Override Overspeed

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AIRPLANE OPERATIONS MANUAL ABBREVIATION OXY P-ACE P-RNAV PA PAX PBE PBIT PC PCN PCU PDU PED Perf PF PFD PIT PM PMA POS PPH PPOS PPU PREV PRI PRN PROX PSEM psi psid psig PSU PTT PTU PWR QFE

GENERAL INFORMATION AND DEFINITION OF TERMS

DESCRIPTION Oxygen Primary Actuator Control Electronics Precision Required Navigation Passenger Address Passenger Protective Breathing Equipment Power Up Built in Test Personal Computer Pavement Classification Number Power Control Unit Power Drive Unit Portable Electronic Device Performance Pilot Flying Primary Flight Display Pitch Pilot Monitoring Permanent Magnet Alternator Position Pounds per Hour Present Position Power Push Unit Previous Primary Pseudo-Random Noise Proximity Proximity Sensor Electronic Module Pounds per Square Inch Pound per Square Inch Differential Pound per Square Inch Gauge Passenger Service Unit Push To Talk Power Transfer Unit Power Local Station Barometric Pressure

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ABBREVIATION QNH QRH RA RAD RAID RAIM RALT RAM RAMP RAT RCT REACT RECIRC REF. RETD REV RH RICC RIPS RNAV RNP rpm RSV RTA RTO RTS RVSM RWY s S-ACE SAD SAI SAT SATCOM

AIRPLANE OPERATIONS MANUAL

DESCRIPTION Local Altimeter Setting Quick Reference Handbook Resolution Advisory Radio Ram Air Inlet Door Receiver Autonomous Integrity Monitor Radio Altitude Random Access Memory Reliability Analysis and Motoring Program Ram Air Turbine Rain Echo Attenuation Rain Echo Attenuation Compensation Technique Recirculation Reference Retard Reverse Right-Hand Right Integrated Control Center Recorder Independent Power Supply Area Navigation Required Navigation Performance Revolutions per Minute Reserve Receiver/Transmitter Antenna Rejected Takeoff Return To Service Reduced Vertical Separation Minimum Runway Second Spoiler Actuator-Control Electronics Still Air Distance Slat Anti-Ice Static Air Temperature Satellite Communications

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AIRPLANE OPERATIONS MANUAL ABBREVIATION SB SCV SDF SECT SEL SF-ACE SID SLD SMKG SOV SPD SPDA SPDE SPDT SPKR SPS SSPC STAB STAR STBY STD SVC SW SYS T/O T2 TA TA/RA TAS TAT TCAS TCS TDS TEMP TERM

GENERAL INFORMATION AND DEFINITION OF TERMS

DESCRIPTION Service Bulletin Starter Control Valve Simplified Directional Facility Sector Selector Slat/Flap Actuator Control Electronics Standard Instrument Departures Super Large Droplet Smoking Shutoff Valve Speed Secondary Power Distribution Assembly Speed on Elevator Speed on Thrust Speaker Stall Protection System Solid State Power Controller Stabilizer Standard Instrument Arrivals Standby Standard Service Switch System Takeoff Fan Inlet Temperature Traffic Advisory Traffic Advisory/ Resolution Advisory True Airspeed Total Air Temperature Traffic Alert and Collision Avoidance System Touch Control Steering Takeoff Data Set Temperature Terminal

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ABBREVIATION TGL TGT TLA TMS TO TO/GA TOC TOD TOGA TRS TRU TSO TWIP ULD US gal UTC V V1 V2 VA VAC VALT VAP VAR VARM VASEL VDC VDOP VDR VEF VFE VFLCH VFR VFS VGP

AIRPLANE OPERATIONS MANUAL

DESCRIPTION Temporary Guidance Leaflet Target Thrust Lever Angle Thrust Management System Takeoff Takeoff/Go-Around Top of Climb Top of Descent Takeoff/Go Around Thrust Rating System Transformer Rectifier Unit Technical Standard Order Terminal Weather Information for Pilots Unfactored Landing Distance Gallon Universal Time Coordinated Volt Takeoff Decision Speed Takeoff Safety Speed Design Maneuvering Speed Approach Climb Speed VNAV Altitude Hold Approach Speed Variable Vertical ARM VNAV Altitude Select Volt Direct Current Vertical Dilution of Precision VHF Data Radio Critical Engine Failure Speed Maximum Flaps Extended Speed VNAV Flight Level Change Visual Flight Rules Final Segment Speed VNAV Glide Path

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AIRPLANE OPERATIONS MANUAL ABBREVIATION VHF VLE VLO VMCA VMCG VMCL VMO VNAV VOR VOR/LOC VPATH VR Vref VREFXX

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VS VSI VTA WGS-84 WML WOW WRN WSHR WX XBLEED XFEED XPDR YD

GENERAL INFORMATION AND DEFINITION OF TERMS

DESCRIPTION Very High Frequency Maximum Landing Gear Extended Speed Maximum Landing Gear Operating Speed Minimum Control Speed in the Air Minimum Control Speed on Ground Minimum Control Speed During Landing Maximum Operating Speed Vertical Navigation VHF Omnidirectional Range VOR Localizer VNAV Path Rotation Speed Reference Speed Landing Reference Speed associated to the flap setting XX Stall Speed Vertical Speed Indicator Vertical Track Alert World Geodetic System 1984 Windmilling Weight-on-Wheels Warning Windshear Weather Radar Cross Bleed Cross Feed Transponder Yaw Damper

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GENERAL INFORMATION AND DEFINITION OF TERMS

AIRPLANE OPERATIONS MANUAL

UNITS CONVERSION TO CONVERT Degree Celsius (°C) Degree Fahrenheit (°F) Feet (ft) Inches (in) Inches of Mercury (inHg) Kilogram (kg) Kilogram force per Square meter (kg/m2)

INTO Degree Fahrenheit (°F) Degree Celsius (°C) Meter (m) Millimeter (mm)

MULTIPLY BY

AND ADD

1.8000

+32

0.5556

-17.7778

0.3048 25.4000

– –

Millibar (mbar)

33.8636

–

Pounds (lb)

2.2046

–

Pound per Square Inch (psi)

0.0014

–

Kilometer (km)

Nautical Mile (NM)

0.5399

–

Kilometer per hour (km/h)

Knot (kt)

0.5399

–

1.852

–

0.4536 3.2808

– –

0.0295

–

0.0394

–

1.852

–

703.0740

–

Knot (kt) Pounds (lb) Meter (m) Millibar (mbar) Millimeter (mm) Nautical Mile (NM)

Kilometer per hour (km/h) Kilogram (kg) Feet (ft) Inches of Mercury (inHg) Inches (in) Kilometer (km)

AOM-1502-003

Kilogram force per Pound per Square Square meter Inch (psi) (kg/m2)

1-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 12

Units Conversion

Page 1

GENERAL INFORMATION AND DEFINITION OF TERMS

AIRPLANE OPERATIONS MANUAL

1-25 Copyright © by Embraer. Refer to cover page for details.

Page 2

Units Conversion

REVISION 12

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

GENERAL INFORMATION AND DEFINITION OF TERMS

SERVICE BULLETIN TABLE EMBRAER 170/175 models SB SB 170-00-0003 SB 170-00-0005

SB 170-00-0006

SB 170-00-0014

SB 170-00-0015 SB 170-00-0016 SB 170-00-0020

SB 170-00-0021

SB 170-00-0022

SB 170-00-0023 SB 170-00-0024

AOM-1502-003

SB 170-00-0025

SUBJECT Installation of placard to increase the maximum landing weight. Installation of placard indicating the Maximum Takeoff Weight (MTOW) of 34850 kg. Removal of the nameplate indicating the Maximum Takeoff Weight (MTOW) from the airplane tail cone. Installation of placard indicating the Maximum Takeoff Weight (MTOW) of 35990 kg. Installation of placard indicating the Maximum Takeoff Weight (MTOW) of 34850 kg. Increase the maximum structural weights. Installation of placard indicating the Maximum Takeoff Weight (MTOW) of 34473 kg. Installation of placard indicating the Maximum Takeoff Weight (MTOW) of 35990 kg. Installation of placard indicating the Maximum Takeoff Weight (MTOW) of 74957 lb. Installation of placard indicating the Maximum Takeoff Weight (MTOW) of 79344 lb. Increase the Maximum Zero Fuel Weight (MZFW) to 30140 kg. Installation of placard indicating the Maximum Takeoff Weight (MTOW) of 34000 kg.

1-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Service Bulletins

Page 1

GENERAL INFORMATION AND DEFINITION OF TERMS

SB 170-00-0026

SB 170-00-0030

SB 170-00-0031

SB 170-00-0042

SB 170-21-0016

SB 170-24-0017 SB 170-24-0049

SB 170-25-0104

SB 170-31-0002

SB 170-31-0010

SUBJECT Installation of placard indicating the Maximum Takeoff Weight (MTOW) of 35990 kg. Installation of placard indicating the Maximum Takeoff Weight (MTOW) of 36000 kg. Installation of placard indicating the Maximum Takeoff Weight (MTOW) of 37500 kg. Installation of a package of modifications to improve the certified noise levels on EMBRAER 175 airplanes, identified as ″SILENT KIT″. Upgrade of AMS controller operational software to black label 6.0 and replacement of the oxygen cylinder servicing graphic placard. SPDA software version update to Block 9.2. Modification of the electrical connectors P0790 and P0791 of SPDA 2. Installation of an additional megaphone and replacement of the nesting door on the G2 galley. Update of Load 13.3 to Load 15.3 version of the PRIMUS EPIC field-loadable software system into the PRIMUS EPIC Integrated Avionics System. Upload to Load 17.2.0.2 version of the PRIMUS EPIC field-loadable software system into the PRIMUS EPIC Integrated Avionics System.

1-35 Copyright © by Embraer. Refer to cover page for details.

Page 2

Service Bulletins

REVISION 18

AOM-1502-003

SB

AIRPLANE OPERATIONS MANUAL

AIRPLANE OPERATIONS MANUAL

SB

SB 170-31-0017

SB 170-31-0019

SB 170-31-0028

SB 170-31-0034

SB 170-32-0014 SB 170-32-0034 SB 170-34-0009 SB 170-34-0017 SB 170-49-0003 SB 170-52-0031

AOM-1502-003

SB 170-73-0002

GENERAL INFORMATION AND DEFINITION OF TERMS

SUBJECT Upload of Load 15.3 to Load 17.5 version of the PRIMUS EPIC field-loadable software system into the PRIMUS EPIC integrated Avionics System. Update of Load 17.5 to Load 19.3 version of the PRIMUS EPIC field-loadable software system into the PRIMUS EPIC Integrated Avionics System. Update of current Load to Load 21.2 version of the PRIMUS EPIC field-loadable software system into the PRIMUS EPIC Integrated Avionics System. Update of current Load to Load 21.4 version of the PRIMUS EPIC field-loadable software system into the Primus Epic Integrated Avionics System. Installation of an Autobrake electronic module in the MAU 2. Installation of Nose Wheel Steering Control Module new version. Upgrade of the software in Air Data SmartProbes. Installation of optional Mode S Transponder System for Enhanced Surveillance. Upgrade of the Electronic Starter Controller. Slide Mechanism Modification. Installation of placard in the cockpit with new time limit for maximum TO thrust.

1-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Service Bulletins

Page 3

GENERAL INFORMATION AND DEFINITION OF TERMS

SB 170-73-0003

SUBJECT Upgrade of engine FADEC software version to 5.30.

1-35 Copyright © by Embraer. Refer to cover page for details.

Page 4

Service Bulletins

REVISION 18

AOM-1502-003

SB

AIRPLANE OPERATIONS MANUAL

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

SECTION 2 LIMITATIONS TABLE OF CONTENTS

AOM-1502-003

Block

Page

Introduction.......................................................... 2-INTRO ....

1

Weight and CG..................................................... 2-05 ........... WEIGHT................................................................. 2-05 ........... LOADING............................................................... 2-05 ........... CENTER OF GRAVITY ENVELOPE..................... 2-05 ...........

1 1 3 4

Operational Limitations....................................... 2-10 ........... OPERATIONAL ENVELOPE.................................. 2-10 ........... AIRSPEEDS........................................................... 2-10 ........... MAXIMUM TIRE GROUND SPEED...................... 2-10 ........... WIND LIMITATIONS............................................... 2-10 ........... MAXIMUM RECOMMENDED CROSSWIND........ 2-10 ........... KINDS OF OPERATION........................................ 2-10 ........... MINIMUM CREW................................................... 2-10 ........... MANEUVERING FLIGHT LOAD FACTORS.......... 2-10 ........... RUNWAY................................................................ 2-10 ........... TOWING................................................................. 2-10 ...........

1 1 3 7 7 7 7 8 8 8 8

Electronic Display................................................ 2-20 ........... ELECTRONIC CHECKLIST................................... 2-20 ...........

1 1

Warning................................................................. 2-30 ........... WARNING.............................................................. 2-30 ...........

1 1

Fuel........................................................................ 2-36 ........... FUEL...................................................................... 2-36 ........... FUEL SPECIFICATION.......................................... 2-36 ........... FUEL ADDITIVES.................................................. 2-36 ........... FUEL TANK TEMPERATURE................................ 2-36 ........... CROSSFEED OPERATION................................... 2-36 ...........

1 1 1 1 1 1

2-TOC Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Table of Contents

Page 1

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

Block Page Auxiliary Power Unit............................................ 2-38 ........... 1 APU SUNDSTRAND APS 2300............................ 2-38 ........... 1 APU STARTER LIMITS.......................................... 2-38 ........... 1 APU APPROVED OILS.......................................... 2-38 ........... 1 Powerplant............................................................ 2-40 ........... ENGINE.................................................................. 2-40 ........... STARTER............................................................... 2-40 ........... ENGINE APPROVED OILS................................... 2-40 ........... ENGINE THRUST.................................................. 2-40 ........... NOISE LEVELS..................................................... 2-40 ...........

1 1 1 2 2 3

Pneumatic, Air Conditioning, Pressurization.... 2-48 ........... PRESSURIZATION................................................ 2-48 ...........

1 1

Ice and Rain Protection....................................... 2-50 ........... ICE AND RAIN PROTECTION.............................. 2-50 ........... WINDSHIELD WIPER OPERATION...................... 2-50 ...........

1 1 2

Navigation, Communication, Autopilot.............. 2-56 ........... NAVIGATION, COMMUNICATION AND AUTOPILOT..................................................... 2-56 ........... NAVIGATION EQUIPMENT................................... 2-56 ........... INERTIAL REFERENCE SYSTEM........................ 2-56 ...........

1

CAT II Limitations................................................. 2-57 ........... CAT II LIMITATIONS.............................................. 2-57 ........... AUTOPILOT SYSTEM........................................... 2-57 ........... APPROACH AND LANDING FLAPS..................... 2-57 ........... DEMONSTRATED WIND COMPONENTS............ 2-57 ...........

1 1 2 2 2

Ozone Concentration........................................... 2-60 ........... OZONE CONCENTRATION.................................. 2-60 ...........

1 1

Flight Management System................................ 2-64 ........... FLIGHT MANAGEMENT SYSTEM........................ 2-64 ........... GENERAL LIMITATIONS....................................... 2-64 ........... NAVIGATION LIMITATIONS.................................. 2-64 ........... APPROACH LIMITATIONS.................................... 2-64 ...........

1 1 5 5 9

RVSM Operation Limitations.............................. 2-68 ........... RVSM OPERATION............................................... 2-68 ...........

1 1

2-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 21

AOM-1502-003

1 1 2

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

INTRODUCTION The airplane must be operated in accordance with the limitations presented in this Section. These limitations also apply to operations in accordance with an approved Supplement or Appendix to the AFM, except as modified by such Supplement or Appendix. The information contained in this section is derived from the Approved Airplane Flight Manual. Flight crewmembers should have all limitations committed to memory (except tables and charts). Some items may not be included herein, as they may be identified in a panel/placard or annunciated by some kind of alarm/warning. Compliance to the Emergency and Abnormal Procedures will also assure that certain limitations are complied with. In the event that a limitation in this manual disagrees with the AFM limitation, the AFM must prevail.

AOM-1502-003

In the event that a placard or instrument marking disagrees with the limitations shown in this manual, the more restrictive limitation must prevail.

2-INTRO Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Page 1

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

2-INTRO Copyright © by Embraer. Refer to cover page for details.

Page 2

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

WEIGHT The maximum structural weights are shown in the table below for the models: EMBRAER 170 LR !170 LR, S/N up to 170.00058, 00060 to 00064 (MZFW = 65256 lb), units in lb

Max. Ramp Weight (MRW) (lb) 82364

Max. Takeoff Weight (MTOW) (lb) 82011

Max. Landing Weight (MLW) (lb) 72310

Max. Zero Fuel Weight (MZFW) (lb) 65256 "

EMBRAER 170 LR !Post-Mod. SB 170-00-0024

Max. Ramp Weight (MRW) (lb) 82364

Max. Takeoff Weight (MTOW) (lb) 82011

Max. Landing Weight (MLW) (lb) 72310

Max. Zero Fuel Weight (MZFW) (lb) 66446 "

EMBRAER 170 SU !170 SU, S/N up to 170.00058, 00060 to 00064 (MZFW = 65256 lb), units in lb

Max. Ramp Weight (MRW) (lb) 82364

Max. Takeoff Weight (MTOW) (lb) 82011

Max. Landing Weight (MLW) (lb) 72310

Max. Zero Fuel Weight (MZFW) (lb) 65256 "

EMBRAER 170 SU !Post-Mod. SB 170-00-0024

AOM-1502-003

Max. Ramp Weight (MRW) (lb) 82364

Max. Takeoff Weight (MTOW) (lb) 82011

Max. Landing Weight (MLW) (lb) 72310

Max. Zero Fuel Weight (MZFW) (lb) 66446 CONTINUED...

2-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Weight and CG

Page 1

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED

"

EMBRAER 170 SE !170 SE, S/N up to 170.00058, 00060 to 00064 (MZFW = 65256 lb), units in lb

Max. Ramp Weight (MRW) (lb) 82364

Max. Takeoff Weight (MTOW) (lb) 82011

Max. Landing Weight (MLW) (kg) 72310

Max. Zero Fuel Weight (MZFW) (lb) 65256 "

EMBRAER 170 SE !170 SE, S/N 170.00059, 00065 and on (MZFW = 66446 lb), units in lb OR Post-Mod. SB 170-00-0024

Max. Ramp Weight (MRW) (lb) 82364

Max. Takeoff Weight (MTOW) (lb) 82011

Max. Landing Weight (MLW) (lb) 72310

Max. Zero Fuel Weight (MZFW) (lb) 66446 "

EMBRAER 175 LR Max. Ramp Weight (MRW) (lb) 85870

Max. Takeoff Weight (MTOW) (lb) 85517

Max. Landing Max. Zero Fuel Weight (MLW) Weight (MZFW) (lb) (lb) 74957

69886

EMBRAER 175 LR POST-MOD SB 0170-00-0016 Max. Ramp Weight (MRW) (lb) 89352

Max. Takeoff Weight (MTOW) (lb) 89000

Max. Landing Max. Zero Fuel Weight (MLW) Weight (MZFW) (lb) (lb) 75177

70547

The takeoff weight (weight at brake release or at start of takeoff run) is CONTINUED...

2-05 Copyright © by Embraer. Refer to cover page for details.

Page 2

Weight and CG

REVISION 21

AOM-1502-003

To comply with the performance and operating limitations of the regulations, the maximum allowable takeoff and landing operational weights may be equal to, but not greater than design limits.

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

...CONTINUED

the lowest between MTOW and the following weights: – Maximum takeoff weight as calculated using the approved software, and as limited by field length, climb and brake energy. – Maximum takeoff weight, as limited by enroute, and landing operating requirements. The landing weight is the lowest among MLW and the following weights calculated using the approved software: – Maximum landing weight as limited by runway. – Maximum approach and landing weight as limited by altitude, temperature and climb gradient.

LOADING

AOM-1502-003

The airplane must be loaded in accordance with the information contained in the Weight and Balance Manual.

2-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Weight and CG

Page 3

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

CENTER OF GRAVITY ENVELOPE The Weight and CG envelope is shown in the graphics below for the models: !170 LR, S/N up to 170.00058, 00060 to 00064 (MZFW 65256 lb), units in lb

90000

INFLIGHT LIMITS (FLAPS AND GEAR UP) TAKEOFF AND LANDING LIMITS NOT ALLOWED FOR TAKEOFF

REGION 1

11.8%

8.8%

85000

27% MTOW

80000

75000

82011 lb

4% 75728 lb

WEIGHT − lb

70000

65000

60000

55000 1 50000

50706 lb

50706 lb 48060 lb 4%

7%

45000

40000

35000 −10

−5

0

5

10

15

20

25

30

35

40

45

CG POSITION − % MAC

EM170AOM020005D.DGN

18.8%

CG ENVELOPE - EMBRAER 170 LR

CONTINUED...

2-05 Copyright © by Embraer. Refer to cover page for details.

Page 4

Weight and CG

REVISION 21

AOM-1502-003

"

LIMITATIONS

AIRPLANE OPERATIONS MANUAL ...CONTINUED !Post-Mod. SB 170-00-0024

90000

INFLIGHT LIMITS (FLAPS AND GEAR UP) TAKEOFF AND LANDING LIMITS NOT ALLOWED FOR TAKEOFF

REGION 1

11.8%

8.8%

85000

27% MTOW

80000

75000

82011 lb

4% 75728 lb

WEIGHT − lb

70000

65000

60000

55000 1 50000

50706 lb

50706 lb 48060 lb 4%

7%

45000

40000

35000 −10

−5

0

5

10

15

20

25

30

35

40

45

CG POSITION − % MAC

EM170AOM020037B.DGN

18.8%

CG ENVELOPE - EMBRAER 170 LR

AOM-1502-003

"

CONTINUED...

2-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Weight and CG

Page 5

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED !170 LR, CG envelope with alternative 16%, units in lb

90000

REGION 1

INFLIGHT LIMITS (FLAPS AND GEAR UP) TAKEOFF AND LANDING LIMITS NOT ALLOWED FOR TAKEOFF

REGION 2

TAKEOFF LIMITS − CG ALTERNATE 1

85000

11.8% 16%

8.8%

80000

MTOW

27% 82011 lb

4% 75728 lb

75000

72310 lb

WEIGHT − lb

70000 2 65256 lb

65000

60000

55000 1 50706 lb

50000

50706 lb 48060 lb 4%

7%

45000

40000

35000 −10

−5

0

5

10

15

20

25

30

35

40

45

CG POSITION − % MAC

EM170AOM020035C.DGN

18.8%

CG ENVELOPE - EMBRAER 170 LR (ALTERNATE 1 - 16%)

CONTINUED...

2-05 Copyright © by Embraer. Refer to cover page for details.

Page 6

Weight and CG

REVISION 21

AOM-1502-003

"

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED !170 SU, S/N up to 170.00058, 00060 to 00064 (MZFW 65256 lb), units in lb

90000

INFLIGHT LIMITS (FLAPS AND GEAR UP) TAKEOFF AND LANDING LIMITS NOT ALLOWED FOR TAKEOFF

REGION 1

11.8%

8.8%

85000

27% MTOW

80000

75000

82011 lb

4% 75728 lb

WEIGHT − lb

70000

65000

60000

55000 1 50000

50706 lb

50706 lb 48060 lb 4%

7%

45000

40000

35000 −10

−5

0

5

10

15

20

25

30

35

40

45

CG POSITION − % MAC

EM170AOM020005D.DGN

18.8%

CG ENVELOPE - EMBRAER 170 SU

AOM-1502-003

"

CONTINUED...

2-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Weight and CG

Page 7

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED !Post-Mod. SB 170-00-0024

90000

INFLIGHT LIMITS (FLAPS AND GEAR UP) TAKEOFF AND LANDING LIMITS NOT ALLOWED FOR TAKEOFF

REGION 1

11.8%

8.8%

85000

27% MTOW

80000

75000

82011 lb

4% 75728 lb

WEIGHT − lb

70000

65000

60000

55000 1 50000

50706 lb

50706 lb 48060 lb 4%

7%

45000

40000

35000 −10

−5

0

5

10

15

20

25

30

35

40

45

CG POSITION − % MAC

EM170AOM020037B.DGN

18.8%

CG ENVELOPE - EMBRAER 170 SU

CONTINUED...

2-05 Copyright © by Embraer. Refer to cover page for details.

Page 8

Weight and CG

REVISION 21

AOM-1502-003

"

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED !170 SE, S/N up to 170.00058, 00060 to 00064 (MZFW 65256 lb), units in lb

90000

INFLIGHT LIMITS (FLAPS AND GEAR UP) TAKEOFF AND LANDING LIMITS NOT ALLOWED FOR TAKEOFF

REGION 1

11.8%

8.8%

85000

27% MTOW

80000

75000

82011 lb

4% 75728 lb

WEIGHT − lb

70000

65000

60000

55000 1 50000

50706 lb

50706 lb 48060 lb 4%

7%

45000

40000

35000 −10

−5

0

5

10

15

20

25

30

35

40

45

CG POSITION − % MAC

EM170AOM020005D.DGN

18.8%

CG ENVELOPE - EMBRAER 170 SE

AOM-1502-003

"

CONTINUED...

2-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Weight and CG

Page 9

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED !170 SE, S/N 170.00059, 00065 and on (MZFW 66446 lb), units in lb OR Post-Mod. SB 170-00-0024

90000

INFLIGHT LIMITS (FLAPS AND GEAR UP) TAKEOFF AND LANDING LIMITS NOT ALLOWED FOR TAKEOFF

REGION 1

11.8%

8.8%

85000

27% MTOW

80000

75000

82011 lb

4% 75728 lb

WEIGHT − lb

70000

65000

60000

55000 1 50000

50706 lb

50706 lb 48060 lb 4%

7%

45000

40000

35000 −10

−5

0

5

10

15

20

25

30

35

40

45

CG POSITION − % MAC

EM170AOM020037B.DGN

18.8%

CG ENVELOPE - EMBRAER 170 SE

CONTINUED...

2-05 Copyright © by Embraer. Refer to cover page for details.

Page 10

Weight and CG

REVISION 21

AOM-1502-003

"

!175 LR, units in lb

LIMITATIONS

AIRPLANE OPERATIONS MANUAL ...CONTINUED

INFLIGHT LIMITS (FLAPS AND GEAR UP) TAKEOFF AND LANDING LIMITS REGION 1 NOT ALLOWED FOR TAKEOFF 92000 8.2%

88000

11.2%

28.1%

25.1% MTOW

85517 lb

84000 80000 76000

WEIGHT − lb

72000 68000 64000 60627 lb

60000 56000 1

52000

49604 lb 4%

44000 40000 −5

0

7%

5

21%

10

15

20

27%

25

30%

30

35

40

CG POSITION − % MAC

EM170AOM020041B.DGN

48000

CG ENVELOPE - EMBRAER 175 LR

AOM-1502-003

"

CONTINUED...

2-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Weight and CG

Page 11

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED !175 LR with enhanced wing tip, CF34-8E5 engines, units in lb

INFLIGHT LIMITS (FLAPS AND GEAR UP) TAKEOFF AND LANDING LIMITS NOT ALLOWED FOR TAKEOFF

REGION 1 96000 92000 13.2%

16.2%

28.1%

31.1%

88000

85517 lb

84000

WEIGHT − lb

80000 76000

74957 lb

72000 69445 lb 68000 64000 27% 60000 57650 lb 54674 lb

52000

1 9%

48000

33% 49604 lb

12% 22.4% 26%

44000 40000 0

5

10

15

20

25

30

35

40

45

CG POSITION − % MAC

EM170AOM020181A.DGN

56000

CG ENVELOPE - EMBRAER 175 LR POST-MOD SB 170-57-0058 (ENHANCED WING TIP)

"

CONTINUED...

2-05 Copyright © by Embraer. Refer to cover page for details.

Page 12

Weight and CG

REVISION 21

AOM-1502-003

!175 STD, LR, SU with increased maximum structural weights, units in lb

LIMITATIONS

AIRPLANE OPERATIONS MANUAL ...CONTINUED

INFLIGHT LIMITS (FLAPS AND GEAR UP) TAKEOFF AND LANDING LIMITS NOT ALLOWED FOR TAKEOFF

REGION 1 96000

24.5% 27%

12.6%

11%

92000

MTOW

8.2%

89000 lb 28.1%

88000 85516 lb

85516 lb

84000

WEIGHT − lb

80000 76000

74957 lb

72000 68000 64000 60627 lb

60000 56000 1

52000

49604 lb 4%

44000

7%

21%

27%

30%

40000 −5

0

5

10

15

20

25

30

35

CG POSITION − % MAC

40

EM170AOM020163A.DGN

48000

CG ENVELOPE - EMBRAER 175 POST-MOD SB 0170-00-0016

AOM-1502-003

"

2-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Weight and CG

Page 13

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

2-05 Copyright © by Embraer. Refer to cover page for details.

Page 14

Weight and CG

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

OPERATIONAL ENVELOPE !EMBRAER 170 operation at runway altitudes up to 8000 ft, temperatures up to ISA + 35

55000

REGION

1

− TAKEOFF, LANDING & GROUND START

50000 45000

−65°C

−21.5°C 41000 ft

40000

ALTITUDE − ft

35000 30000 ISA + 35°C

25000 20000 15000 10000

8000 ft

5000 0

EM170AOM020006C.DGN

1 −1000 ft −54°C

−40°C

52°C

−5000 −80 −70 −60 −50 −40 −30 −20 −10 0

10 20 30 40 50 60

STATIC AIR TEMPERATURE − °C

OPERATIONAL ENVELOPE

NOTE: In the event of a landing below -40°C, the airplane may not takeoff without further maintenance inspection. AOM-1502-003

" CONTINUED...

2-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Operational Limitations

Page 1

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED !EMBRAER 175 operation at runway altitudes up to 8000 ft

55000

REGION

1

− TAKEOFF, LANDING & GROUND START

50000 45000

−65°C

−21.5°C 41000 ft

40000

ALTITUDE − ft

35000 30000 ISA + 35°C

25000 20000 15000

8000 ft

5000 0

1 −1000 ft

−54°C −40°C −5000 −80 −70 −60 −50 −40 −30 −20 −10 0

52°C 10 20 30 40 50 60

STATIC AIR TEMPERATURE − °C

EM170AOM020006C.DGN

10000

OPERATIONAL ENVELOPE

NOTE: In the event of a landing below -40°C, the airplane may not takeoff without further maintenance inspection. "

MAXIMUM ALTITUDE FOR FLAP EXTENDED

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Operational Limitations

REVISION 21

AOM-1502-003

Maximum Altitude For Flap Extended....................... 20000 ft

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

AIRSPEEDS LANDING GEAR OPERATION/EXTENDED SPEED (VLO AND VLE) VLO for retraction....................................................... 250 KIAS VLO for extension....................................................... 250 KIAS VLE............................................................................. 250 KIAS NOTE: – VLO is the maximum speed at which the landing gear can be safely extended and retracted. – VLE is the maximum speed at which the airplane can be safely flown with the landing gear extended and locked.

MAXIMUM SPEED TO OPEN THE DIRECT VISION WINDOW Maximum Speed to Open the Direct Vision Window...................................................................... 160 KIAS

MINIMUM CONTROL SPEED

AOM-1502-003

Refer to Section 5 – Performance.

CONTINUED...

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REVISION 21

Operational Limitations

Page 3

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED

MAXIMUM OPERATING SPEED

45000

40000 MMO = 0.82 35000

ALTITUDE − ft

30000

25000 VMO 20000

15000

5000

0 200 210 220 230 240 250 260 270 280 290 300 310 320 330 340 350 AIRSPEED − KIAS

EM170AOM020007D.DGN

10000

CONTINUED...

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Page 4

Operational Limitations

REVISION 21

AOM-1502-003

NOTE: VMO/MMO may not be deliberated exceeded in any regime of flight (climb, cruise, or descent).

LIMITATIONS

AIRPLANE OPERATIONS MANUAL ...CONTINUED

MANEUVERING SPEED (VA) !EMBRAER 170 Models 45000

40000

M MO = 0.82

35000

ALTITUDE − ft

30000

25000 VA 20000

EM170AOM020008D.DGN

15000

10000

5000

0 200

210

220

230

240 250 260 270 AIRSPEED − KIAS

280

290

300

NOTE: Maneuvers that involve angle of attack near the stall or full application of rudder, elevator, and aileron controls should be confined to speeds below VA. In addition, the maneuvering flight load factor limits, presented in this Section, should not be exceeded. CAUTION: RAPID AND LARGE ALTERNATING CONTROL INPUTS, ESPECIALLY IN COMBINATION WITH LARGE CHANGES IN PITCH, ROLL, OR YAW (E.G. LARGE SIDE SLIP ANGLES) MAY RESULT IN STRUCTURAL FAILURES AT ANY SPEED, EVEN BELOW VA.

AOM-1502-003

"

CONTINUED...

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REVISION 21

Operational Limitations

Page 5

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED

MANEUVERING SPEED (VA) !EMBRAER 175 Models 45000

40000 MMO = 0.82 35000

ALTITUDE − ft

30000

25000

20000 VA

EM170AOM020014D.DGN

15000

10000

5000

0 200

210

220

230

240

250

260

270

280

290

300

AIRSPEED − KIAS

NOTE: Maneuvers that involve angle of attack near the stall or full application of rudder, elevator, and aileron controls should be confined to speeds below VA. In addition, the maneuvering flight load factor limits, presented in this Section, should not be exceeded. CAUTION: RAPID AND LARGE ALTERNATING CONTROL INPUTS, ESPECIALLY IN COMBINATION WITH LARGE CHANGES IN PITCH, ROLL, OR YAW (E.G. LARGE SIDE SLIP ANGLES) MAY RESULT IN STRUCTURAL FAILURES AT ANY SPEED, EVEN BELOW VA. "

Flaps 1....................................................................... 230 KIAS Flaps 2....................................................................... 215 KIAS Flaps 3....................................................................... 200 KIAS CONTINUED...

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Page 6

Operational Limitations

REVISION 21

AOM-1502-003

MAXIMUM FLAP EXTENDED SPEED (VFE)

LIMITATIONS

AIRPLANE OPERATIONS MANUAL ...CONTINUED

Flaps 4....................................................................... 180 KIAS Flaps 5....................................................................... 180 KIAS Flaps Full................................................................... 165 KIAS

MAXIMUM TIRE GROUND SPEED Maximum Tire Ground Speed................................... 225 mph (195 kt)

WIND LIMITATIONS Maximum Takeoff and Landing Tailwind Component................................................................ 10 kt

MAXIMUM RECOMMENDED CROSSWIND The following maximum crosswinds with gust included are recommended for takeoff and landing based on aerodynamics analyses: Dry Runway............................................................... 38 kt Wet Runway.............................................................. 31 kt Runway with Compacted Snow................................ 20 kt Runway with Standing Water/Slush/Wet Snow/Dry Snow.......................................................................... 18 kt Runway with Ice (including Wet Ice)......................... 12 kt NOTE: Due to engine compressor stall possibility, static takeoff is not recommended with crosswind component greater than 25 kt.

KINDS OF OPERATION This airplane may be flown day and night in the following conditions, when the appropriate equipment and instruments required by airworthiness and operating regulations are approved, installed and in an operable condition: – Visual (VFR); – Instrument (IFR);

AOM-1502-003

– Icing conditions; – Category I and II; CONTINUED...

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REVISION 21

Operational Limitations

Page 7

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED

– Extended Overwater Operation; – RVSM. – RNP.

MINIMUM CREW Minimum Flight Crew................................................ PILOT AND COPILOT

MANEUVERING FLIGHT LOAD FACTORS These corresponding accelerations limit the bank angle during turns and limit the pull-up maneuvers.

LOAD FACTOR LIMIT

FLAPS UP

Positive Negative

2.5 g -1.00 g

FLAPS DOWN (1, 2, 3, 4, 5 AND FULL) 2.00 g 0g

RUNWAY Runway Slope........................................................... -2% TO +2% Runway Surface Type............................................... PAVED

TOWING

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Page 8

Operational Limitations

REVISION 21

AOM-1502-003

Towbarless towing is prohibited, unless it is conducted in accordance with the procedures presented in the AMM chapter 9.

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

ELECTRONIC CHECKLIST !MAU load 19.3 and on OR POST-MOD SB 170-31-0019

Operational approval is required in order to load database into the airplane and use the electronic checklist. " !MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

The use of the Electronic Checklist is prohibited.

AOM-1502-003

"

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REVISION 20

Electronic Display

Page 1

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

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Page 2

Electronic Display

REVISION 20

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

WARNING ENHANCED GROUND PROXIMITY WARNING The following limitations are applicable to the Enhanced Ground Proximity Warning System (EGPWS): – Navigation is not to be predicated on the use of the Terrain Awareness System. – The use of predictive EGPWS functions should be manually inhibited when landing to an airport that is not in the EGPWS airport database to avoid unwanted alerts. – Pilots are authorized to deviate from their current Air Traffic Control (ATC) clearance to the extent necessary to comply with an EGPWS warning. – The Terrain Display is intended to be used as a situational tool only and may not provide the accuracy and/or fidelity on which to solely base terrain avoidance maneuvering. – The use of predictive EGPWS functions should be manually inhibited during QFE operations if GPS data is unavailable or inoperative.

TRAFFIC ALERT AND COLLISION AVOIDANCE The following limitations are applicable to the Traffic Alert and Collision Avoidance System (TCAS): – Deviation from the ATC assigned altitude is authorized only to extent necessary to comply with a TCAS Resolution Advisory (RA);

AOM-1502-003

– Maneuvers must not be based solely on information presented in the traffic display.

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REVISION 16

Warning

Page 1

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

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Page 2

Warning

REVISION 16

AOM-1502-003

INTENTIONALLY BLANK

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

FUEL AIRPLANE MODEL Maximum usable quantity per tank Unusable quantity per tank

EMBRAER 170/175 ALL MODELS 1535.5 US Gal (10392.5 lb) [1] 11 US Gal (75 lb) [1]

1. The weights above have been determined for an adopted fuel density of 6.767 lb/US Gal. Different fuel densities may be used provided the volumetric limits are not exceeded. NOTE: Maximum fuel capacity is 3094 US Gal (20935 lb). Maximum permitted imbalance between tanks......... 794 lb

FUEL SPECIFICATION Brazilian Specification............................................... QAV1 ASTM Specification................................................... D1655-JET A AND JET A-1 American Specification.............................................. MIL-T-83133A-JP8

FUEL ADDITIVES For approved additives refer to the GE Specification D50TF2 Manual, latest revision.

FUEL TANK TEMPERATURE Minimum.................................................................... -37°C

CROSSFEED OPERATION

AOM-1502-003

Crossfeed Selector Knob must be set OFF during takeoff and landing.

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REVISION 21

Fuel

Page 1

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

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Page 2

Fuel

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

APU SUNDSTRAND APS 2300 OPERATIONAL LIMITS PARAMETER START: TEMPERATURE ALTITUDE OPERATION: TEMPERATURE ALTITUDE: ELECTRICAL GEN BLEED TO ASSIST ENGINE START ROTOR SPEED EGT: START CONTINUOUS

MIN -54°C -

MAX 30000 ft -

[1]

[1]

-

33000 ft 33000 ft 15000 ft

-

21000 ft

-

108 %

[1]

[2] [3]

1032°C 717°C

1. APU temperature matches the Airplane Operational Envelope temperature. 2. In flight, there is no automatic shutdown if EGT exceeds the limits. 3. There is no time limitation for operating the APU on ground or in flight in the amber range between 662°C and 717°C.

APU STARTER LIMITS Cooling period after each starting attempt: First and Second Attempts........................................ 60 s OFF Third Attempt............................................................. 5 min OFF

APU APPROVED OILS

AOM-1502-003

For APU Oil Types/Brands/Servicing refer to the APU Model Specification Manual (Hamilton Sundstrand, APU Model APS 2300) - ESR 1235, latest revision.

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REVISION 10

Auxiliary Power Unit

Page 1

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

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Page 2

Auxiliary Power Unit

REVISION 10

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INTENTIONALLY BLANK

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

ENGINE Two General Electric CF34-8E5 OPERATIONAL LIMITS !CF34-8E5 engines with takeoff thrust time limited to 5 minutes

PARAMETER

MIN – 58.5% – –

N1 N2 ITT: Start Normal Takeoff and Go Around Maximum Takeoff and Go Around Maximum Continuous OIL PRESSURE OIL TEMPERATURE: Continuous Transient

MAX 99.5% 99.4% – 815°C 965°C [1] 949°C [2] 1006°C [1] 990°C [2] 960°C 95 psi – 155°C 163°C [3]

– – – 25 psi – – –

1. Time limited to the first 2 min of the total 5 min limit. 2. Time limited to the remaining 3 min of the total 5 min limit. 3. Transient operation above 155°C limited to 15 min. "

STARTER DRY MOTORING DUTY CYCLE LIMITS Motoring Number 1 2 through to 5 [1]

Maximum Time 90 Seconds 30 Seconds

Cool-Down Time 5 Minutes 5 Minutes

AOM-1502-003

1. After five sequential motorings, cycle may be repeated following a 15-minute cool-down period.

CONTINUED...

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REVISION 20

Powerplant

Page 1

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED

STARTING DUTY CYCLE LIMITS Motoring Number 1 and 2 3 through to 5

Maximum Time 90 Seconds (On ground) 120 seconds (In-flight) 90 Seconds (On ground) 120 seconds (In-flight)

Cool-Down Time 10 Seconds 5 Minutes

NOTE:– For ground starts, the maximum cumulative starter run time per start attempt is 90 seconds (motoring plus start time). – For in-flight starts, the maximum cumulative starter run time per start attempt is 120 seconds (motoring plus start time).

ENGINE APPROVED OILS For Engines Oil Types/Brands/Servicing refer to the GE Specification D50TF2 Manual, latest revision.

ENGINE THRUST Powerback is prohibited. Operation at reduced takeoff thrust based on the assumed temperature higher than the actual ambient temperature is permissible if the airplane meets all applicable performance requirements at the planned takeoff weight and reduced thrust setting. The total thrust reduction must not exceed 25% of the full takeoff thrust. As a condition to the use of the reduced thrust procedures, operators must establish a means to ensure that the engines are capable of producing full takeoff thrust without exceeding any engine operating limits. Use of reduced takeoff thrust procedures is not allowed on runways contaminated with standing water, slush, snow, or ice, and are not allowed on wet runways unless suitable performance accountability is made for the increased stopping distance on the wet surface. Application of reduced takeoff thrust is always at the pilot discretion. When conducting a takeoff using reduced takeoff thrust, normal takeoff thrust may be selected at any time during the takeoff operation.

THRUST REVERSER

After applying thrust reverser, do not move thrust levers back to the forward thrust range, unless the REV icon on EICAS is shown amber or CONTINUED...

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Page 2

Powerplant

REVISION 20

AOM-1502-003

!Airplanes ANAC, TCCA, FAA certification and Pre-Mod. SB0170-73-0003

LIMITATIONS

AIRPLANE OPERATIONS MANUAL ...CONTINUED

green. "

NOISE LEVELS The following Effective Perceived Noise Levels (EPNL’s) comply with, FAA Part 36, Appendix C, Stage 3 noise limits and were obtained by analysis of approved data from noise tests conducted under the provisions of ICAO Annex 16, Volume 1 - Chapter 3 and FAA Part 36. !170 models, ANAC/FAA certification

If the airplane is equipped with at least one of the following components: – Inlet Assembly P/N 15C0003005. – Inlet Assembly P/N 15C0003301. – Thrust Reverser P/N 15G0001-011. – Thrust Reverser P/N 15G0001-012. The following noise levels table must be used: "

NOISE LEVEL IN EPNdB !170 LR, CF34-8E5 engines

CONDITION Lateral 92.3

Flyover 84.1

Approach 94.9 "

NOISE LEVEL IN dBA !170 LR, CF34-8E5 engines, ANAC/TCCA/FAA certification

CONDITION Flyover 71.5

Approach 85.5

AOM-1502-003

"

CONTINUED...

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REVISION 20

Powerplant

Page 3

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED

NOISE LEVEL IN EPNdB !170 SU, CF34-8E5 engines, ANAC/TCCA/FAA certification

CONDITION Lateral 92.3

Flyover 84.1

Approach 94.9 "

NOISE LEVEL IN dBA !170 SU, CF34-8E5 engines, ANAC/TCCA/FAA certification

CONDITION Flyover 71.5

Approach 85.5 "

NOISE LEVEL IN EPNdB !170 SE, CF34-8E5 engines, ANAC/TCCA/FAA certification

CONDITION Lateral 92.3

Flyover 84.1

Approach 94.9 "

NOISE LEVEL IN dBA !170 SE, CF34-8E5 engines, ANAC/TCCA/FAA certification

CONDITION Flyover 71.5

Approach 85.5 "

For all other airplanes, the noise levels table is the following: NOISE LEVEL IN EPNdB !170 LR, CF34-8E5 engines

Flyover 83.2

CONDITION Lateral 92.0

Approach 94.9

CONTINUED...

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Page 4

Powerplant

REVISION 20

AOM-1502-003

"

LIMITATIONS

AIRPLANE OPERATIONS MANUAL ...CONTINUED

NOISE LEVEL IN dBA !170 LR, CF34-8E5 engines, ANAC/TCCA/FAA certification

CONDITION Flyover 71.0

Approach 84.9 "

NOISE LEVEL IN EPNdB !170 SU, CF34-8E5 engines, ANAC/TCCA/FAA certification

CONDITION Lateral 92.0

Flyover 83.2

Approach 94.9 "

NOISE LEVEL IN dBA !170 SU, CF34-8E5 engines, ANAC/TCCA/FAA certification

CONDITION Flyover 71.0

Approach 84.9 "

NOISE LEVEL IN EPNdB !170 SE, CF34-8E5 engines, ANAC/TCCA/FAA certification

CONDITION Lateral 92.0

Flyover 83.2

Approach 94.9 "

NOISE LEVEL IN dBA !170 SE, CF34-8E5 engines, ANAC/TCCA/FAA certification

CONDITION Flyover 71.0

Approach 84.9

AOM-1502-003

"

The noise level for EMBRAER 170 equipped with APU Hamilton Sundstrand APS 2300 and two GE CF34-8E5 engines were established as follows: CONTINUED...

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REVISION 20

Powerplant

Page 5

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED

– Flyover (takeoff): at maximum takeoff weight, flap setting 1 and thrust power cutback; – Lateral: at maximum takeoff weight, flap setting 1 and with all engines at maximum takeoff power setting; – Approach: at maximum landing weight, 3° glide slope, Vref +10 KIAS and flap setting FULL. NOISE LEVEL IN EPNdB !175 LR, CF34-8E5 engines, ANAC/TCCA/FAA certification

CONDITION Lateral 91.9

Flyover 84.4

Approach 95.0 "

NOISE LEVEL IN dBA !175 LR, CF34-8E5 engines, ANAC/TCCA/FAA certification

CONDITION Flyover 72.4

Approach 85.1 "

NOISE LEVEL IN EPNdB !175 LR POST-MOD SB 0170-00-0016, CF34-8E5 engines, FAA certification

Flyover 85.9

CONDITION Lateral 91.9

Approach 95.0 "

NOISE LEVEL IN dBA !175 LR POST-MOD SB 0170-00-0016, CF34-8E5 engines, FAA certification

CONDITION Flyover 74.1

Approach 85.1

The noise level for EMBRAER 175 equipped with APU Hamilton Sundstrand APS 2300 and two GE CF34-8E5 engines were established as follows: CONTINUED...

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Page 6

Powerplant

REVISION 20

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

...CONTINUED

– Flyover (takeoff): at maximum takeoff weight, flap setting 1 and thrust power cutback; – Lateral: at maximum takeoff weight, flap setting 1 and with all engines at maximum takeoff power setting; – Approach: at maximum landing weight, 3° glide slope, Vref +10 KIAS and flap setting FULL.

AOM-1502-003

No determination has been made by the Federal Aviation Administration that the noise levels in this manual are or should be acceptable or unacceptable for operation at, into, or out of any airport.

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REVISION 20

Powerplant

Page 7

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

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Page 8

Powerplant

REVISION 20

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

PRESSURIZATION

AOM-1502-003

Maximum differential pressure.................................. 8.4 psi Maximum differential overpressure........................... 8.8 psi Maximum differential negative pressure................... -0.5 psi Maximum differential pressure for Takeoff and Landing...................................................................... 0.2 psi

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REVISION 21

Pneumatic, Air Conditioning, Pressurization

Page 1

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

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Page 2

Pneumatic, Air Conditioning, Pressurization

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

ICE AND RAIN PROTECTION OPERATION IN ICING CONDITIONS There is no temperature limitation for anti-icing system automatic operation. On ground: – The TO DATASET MENU on the MCDU must be set to ENG when OAT is from 5-10°C and: – if there is any possibility of encountering visible moisture up to 1700 ft AFE, or – when operating on ramps, taxiways, or runways where surface snow, ice, standing water, or slush may be ingested by the engines, or freeze on engines, nacelles, or engine sensor probes. – The TO DATASET MENU on the MCDU must be set to ALL when OAT is less than 5°C: – if there is any possibility of encountering visible moisture up to 1700 ft AFE, or. – when operating on ramps, taxiways, or runways where surface snow, ice, standing water, or slush may be ingested by the engines, or freeze on engines, nacelles, or engine sensor probes. In flight: – The engine and wing anti-ice systems operate automatically, in case of ice encounter when the ice protection mode selector is in the AUTO position. If either one or both ice detectors are failed, the crew must set the mode selector to ON when icing conditions exist or are anticipated below 10°C TAT with visible moisture.

AOM-1502-003

– Closely monitor the TAT indication and presence of moisture. If environmental ice conditions exist, even intermittent, check the windshield, windshield wiper (if installed), and wing surface for ice accumulation. To visualize ice formation, if necessary, use a flashlight

CONTINUED...

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REVISION 21

Ice and Rain Protection

Page 1

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED

on the windshield and the wing inspection light on the wing. If any ice formation is detected or suspected, select the anti-ice protection system override knob to ON. When flying in detected or suspected ice conditions, use ice speeds as reference. NOTE: – Icing conditions may exist whenever the Outside Air Temperature (OAT) on ground or for takeoff, or Total Air Temperature (TAT) in flight, is 10°C or less and visible moisture in any form is present (such as clouds, fog with visibility of one mile or less, rain, snow, sleet, and ice crystals). – Icing conditions may also exist when the OAT on ground or for takeoff is 10°C or less when operating on ramps, taxiways, or runways where surface snow, ice, standing water, or slush may be ingested by the engines, or freeze on engines, nacelles, or engine sensor probes. CAUTION: ON GROUND, DO NOT RELY ON VISUAL ICING EVIDENCE OR ICE DETECTOR ACTUATION TO TURN ON THE ANTI-ICING SYSTEM. USE THE TEMPERATURE AND VISUAL MOISTURE CRITERIA AS SPECIFIED ABOVE. DELAYING THE USE OF THE ANTI-ICING SYSTEM UNTIL ICE BUILD-UP IS VISIBLE FROM THE COCKPIT MAY RESULT IN ICE INGESTION AND POSSIBLE ENGINE DAMAGE OR FLAMEOUT.

WINDSHIELD WIPER OPERATION

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Page 2

Ice and Rain Protection

REVISION 21

AOM-1502-003

Maximum Airspeed for Windshield Wiper Operation................................................................... 253 KIAS

AIRPLANE OPERATIONS MANUAL

NAVIGATION, AUTOPILOT

COMMUNICATION

LIMITATIONS

AND

AUTOPILOT Minimum Engagement Height................................... 400 ft Minimum Use Height................................................. 50 ft

NAVIGATION EQUIPMENT – TAS, TAT and SAT information are only valid above 60 KIAS. – While transmitting in VHF1 the standby magnetic compass indication is not valid. – Baro altimeter minimums must be used for all Cat I approaches. – Back course approaches using IESS are prohibited. – The ACARS is limited to the transmission and receipt of messages that will not create an unsafe condition if the message is improperly received, unless they are verified per approved operational procedures. !170/175 models equipped with ADS-B Out Non Radar Area OR Post-Mod. SB 170-34-0035, FAA Certification

– The ADS-B Out system complies with EASA AMC 20-24 and was implemented according to DO-260A, change 1 and change 2. " !170/175 models equipped with ADS-B Out Radar Area OR Post-Mod. SB 170-34-0034, FAA Certification

– The installed ADS-B Out system has been shown to meet the equipment requirements of 14 CFR § 91.227 and EU 1207/2011.

AOM-1502-003

"

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REVISION 21

Navigation, Communication, Autopilot

Page 1

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

INERTIAL REFERENCE SYSTEM – The airplanes may be operated within the North and South magnetic polar cut-out regions specified in the table below, but IRS magnetic heading and track angle magnetic data will not be available. MAGNETIC CUT-OUT REGIONS North

South

LATITUDE Between 73.125°N and 82°N North of 82°N Between 60°S and 82°S South of 82°S

LONGITUDE Between 80°W and 130°W Between 0° and 180°W/E Between 120°E and 160°E Between 0° and 180°W/E

NOTE: Whenever operating within North or South magnetic polar cut-out regions, current airplane heading must be referenced to true heading, if not already selected. Otherwise, the Heading Failure Indication flag will be displayed. Maximum latitude for stationary alignment:.............. 78.25° Northern and Southern – IRS stationary alignment will complete only after a valid airplane present position (latitude and longitude) is received from the FMS or automatically from GPS.

CONTINUED...

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Page 2

Navigation, Communication, Autopilot

REVISION 21

AOM-1502-003

– Time to stationary alignment completion:

LIMITATIONS

AIRPLANE OPERATIONS MANUAL ...CONTINUED

15

10

5

0 0

5

10

15

20

25

30

35

40

45

50

55

60

65

70

AOM-1502-003

ALIGNMENT LATITUDE − degrees Northern and Southern

75

80

EM170AOM020009C.DGN

ALIGNMENT TIME − minutes

20

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REVISION 21

Navigation, Communication, Autopilot

Page 3

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

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Page 4

Navigation, Communication, Autopilot

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

CAT II LIMITATIONS MINIMUM EQUIPMENT REQUIRED The performance of CAT II approaches has been demonstrated to meet the airworthiness requirements of FAA AC 120-29A – Appendix 3 and CS AWO Subpart 2 requirement, when the following equipments are installed and operative: – 2 Inertial Reference Systems; – 2 Flight Director Systems; – 2 Primary Flight Displays (PFD); – Windshield Wipers; – 2 VOR/ILS NAV System; – 1 VHF/COMM System; – Cat II Engagement Logic; – 1 Radio Altimeter; – 1 Ground Proximity Warning System (EGPWS); – 2 Air Data System (ADS); – 1 Autopilot System Channel; – Rudder in Normal Mode; – SPOILER FAULT message not presented. For CAT II operation with one engine inoperative, the following also applies:

AOM-1502-003

– 1 Autopilot System Channel must be operative; – Manual FD Category II ILS approaches are prohibited. CONTINUED...

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REVISION 11

CAT II Limitations

Page 1

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED

For CAT II operation with airplanes Pre-Mod. SB 170-31-0010, the following also applies: – The one engine inoperative CAT II operation is prohibited. – 1 autopilot system channel must be operative. – Manual FD Category II ILS approaches are prohibited.

AUTOPILOT SYSTEM Minimum Use Height (MUH)..................................... 50 ft NOTE: Coupled go-around height loss may be 50 ft.

APPROACH AND LANDING FLAPS CAT II approach and landing must be performed with flaps 5.

DEMONSTRATED WIND COMPONENTS Headwind................................................................... 25 kt Tailwind...................................................................... 10 kt Crosswind.................................................................. 12 kt

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CAT II Limitations

REVISION 11

AOM-1502-003

These demonstrated values are not considered to be limiting.

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

OZONE CONCENTRATION The tables below show the airplane altitude limitations due to ozone concentration in atmosphere for airplanes not equipped with the Ozone Converters. Ozone limitations shall be considered any time a flight is planned to fly at or above the latitudes specifically described in the applicable table for each region. Flight outside of the latitudes referenced by the tables are not altitude restricted in regard to ozone. The dashes in the tables mean that the criteria does not impose an altitude limitation below the maximum approved altitude for the airplane at that specific latitude and period of the year. Two criteria are presented: 1 - The Maximum Ozone Criteria is the limiting altitude for every flight and does not depend on flight time. 2 - The Time Weighted Average (TWA) Ozone Criteria tables do not represent the ceiling altitude, but the altitude above which the airplane should not fly for more than 3 continuous hours (RBHA/FAR § 25.832 (a) (2)). This means that the TWA ozone chart shall only be considered if both of the following conditions are met: – The airplane is flying in a latitude range at or above the minimum indicated in the table with an actual limitation (not a dash). – The flight will be conducted at or above FL270 in that latitude range for 3 or more hours. If the latitude considered is in between the ones presented in the table, the altitude value may be interpolated. For calculation purposes, the dashes in the table should be considered the maximum altitude presented in the approved operational envelope (FL410).

AOM-1502-003

For example, if you’re flying If on the west side of the longitude reference

CONTINUED...

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REVISION 21

Ozone Concentration

Page 1

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED

line (100°W), at any latitude above 45°N up to 50ºN on January, the maximum flight level shall be limited to 407 (Maximum Ozone Criteria), but the airplane shall not be above flight level 338 for more than 3 hours (TWA Ozone Criteria). NOTE: – These tables are based on FAA AC 120.38. – The tables show altitude limitations calculated for constant ozone concentration and cabin stabilized at 8000 ft. However, ozone tables shall still be considered regardless of the actual cabin altitude attained during a given flight. – For conditions other than those specified in item 2 above, an optimized flight plan must be approved by regulatory agencies. – For longitudes, the following apply: W = Western E = Eastern Reference = 100°W longitude

CONTINUED...

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Ozone Concentration

REVISION 21

AOM-1502-003

• • •

LIMITATIONS

AIRPLANE OPERATIONS MANUAL ...CONTINUED

NORTH AMERICA - MAXIMUM OZONE CRITERIA NOTE: The North America tables are approved by FAA as Airplane Flight Manual Limitations. FLIGHT LEVEL LATITUDE 80°N 75°N 70°N 65°N 60°N 55°N 50°N 45°N 40°N 35°N

AOM-1502-003

FLIGHT LEVEL LATITUDE 80°N 75°N 70°N 65°N 60°N 55°N 50°N 45°N 40°N 35°N

JAN W 356 376 394 407 410 406 -

FEB

E 323 327 341 346 356 362 376 396 -

JUL W 346 347 356 366 -

W 333 347 376 409 410 366 -

E 323 323 323 326 336 346 362 376 386 -

AUG

E 336 346 346 356 366 382 406 -

W 396 402 406 -

MAR W 328 338 347 366 376 376 -

E 314 321 326 327 334 341 346 366 396 -

SEP

APR W 328 327 327 327 346 382 -

E 313 314 321 321 326 334 336 346 366 -

OCT

MAY W 326 327 327 334 346 402 -

E 307 314 314 321 326 327 336 362 396 -

NOV

E W E W E W E 382 - 394 - 382 - 346 396 - 386 - 382 - 362 406 - 396 - 382 - 382 406 406 406 382 394 406 386 - 396 401 407 394 - 407 401 - 406 -

JUN W 338 341 347 356 376 -

E 326 327 334 336 336 356 366 396 -

DEC W 376 386 401 -

E 346 356 356 366 382 396 -

CONTINUED...

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REVISION 21

Ozone Concentration

Page 3

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED

NORTH AMERICA - TWA OZONE CRITERIA NOTE: – Values below are the altitude limitations which the airplane is allowed to fly more than 3 continuous hours. – The North America tables are approved by FAA as Airplane Flight Manual Limitations.

FLIGHT LEVEL LATITUDE 80°N 75°N 70°N 65°N 60°N 55°N 50°N 45°N 40°N 35°N

JAN W 312 321 332 338 338 332 374

FEB

E 274 278 292 294 298 298 312 314 334 354

JUL W 294 298 301 312 321 294 -

W 298 311 321 354 338 312 374

E 270 274 274 270 278 292 298 312 318 354

AUG

E 270 274 274 294 312 312 318 334 354 394

W 332 332 332 332 354 -

E 298 314 321 332 334 334 334 354 398 -

MAR W 301 303 311 315 315 312 338

E 270 270 270 273 291 291 298 311 317 353

SEP W 334 338 354 374 -

E 298 312 314 318 334 334 334 374 -

APR W 292 274 270 270 274 312 354

E 270 270 270 270 270 274 274 294 311 334

OCT W 321 323 334 354 374 -

E 298 298 312 314 318 334 354 354 374 -

MAY W 270 270 270 274 294 318 374

E 270 270 270 270 270 270 274 294 318 334

NOV W 334 334 338 338 353 394 -

E 292 294 298 298 298 314 334 334 354 398

JUN W 303 311 311 311 318 334 392

E 270 270 274 274 274 292 312 318 334 374

DEC W 318 321 334 354 354 354 -

E 298 298 298 301 312 318 334 334 334 374

CONTINUED...

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Ozone Concentration

REVISION 21

AOM-1502-003

FLIGHT LEVEL LATITUDE 80°N 75°N 70°N 65°N 60°N 55°N 50°N 45°N 40°N 35°N

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

...CONTINUED

JAPAN - MAXIMUM OZONE CRITERIA FLIGHT LEVEL Jan Feb Mar Apr May Jun Jul Aug Sep Oct Nov Dec LATITUDE 43°N 356 341 341 356 346 401 - 386 36°N 406 - 382 396 32°N JAPAN - TWA OZONE CRITERIA NOTE: Values below are the altitude limitations which the airplane is allowed to fly more than 3 continuous hours.

AOM-1502-003

FLIGHT LEVEL Jan Feb Mar Apr May Jun Jul Aug Sep Oct Nov Dec LATITUDE 43°N 298 298 301 312 274 314 354 - 354 354 354 312 36°N 332 314 312 321 334 398 - 394 32°N - 392 374 -

CONTINUED...

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REVISION 21

Ozone Concentration

Page 5

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED

EUROPE - MAXIMUM OZONE CRITERIA FLIGHT LEVEL Jan Feb Mar Apr LATITUDE 52°N 394 356 354 336 47°N 401 376 366 356 39°N - 396 356

May Jun Jul Aug Sep Oct Nov Dec 356 382 406 376 376 361 -

-

-

-

-

406 -

EUROPE - TWA OZONE CRITERIA NOTE: Values below are the altitude limitations which the airplane is allowed to fly more than 3 continuous hours.

Jan Feb Mar Apr May Jun Jul Aug Sep Oct Nov Dec 332 312 311 274 298 315 321 354 354 374 354 332 334 321 312 311 315 312 334 374 394 398 374 338 394 352 332 311 312 334 394 - 358

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Page 6

Ozone Concentration

REVISION 21

AOM-1502-003

FLIGHT LEVEL LATITUDE 52°N 47°N 39°N

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

FLIGHT MANAGEMENT SYSTEM NAVIGATION OPERATIONAL APPROVALS Honeywell Primus Epic FMS installation has been demonstrated to be capable of and has been shown to meet the requirements for the following operations: !Pre-mod MAU load 27.1

– Required Navigation Performance (RNP) Operations – The FMS has been demonstrated compliant with the requirements of RTCA DO–283, Minimum Operational Performance Specification for Required Navigation Performance. The FMS has been demonstrated to provide a minimum RNP level of RNP 0.3 when operated according to the limitations and procedures described in FMS AFM supplement. The airplane capability does not constitute RNP operation approval. The operators must be granted local approval to conduct RNP operations. !!Pre-mod MAU Load 27.1, FAA Certification

– The airplane meets the performance and functional requirements of FAA AC 90-101 for RNP AR approach operations requiring RNP not less than 0.3 for approach and not less than 1.0 for missed approach. "" " !Pre-mod MAU load 27.1

– Navigation using GPS – The FMS has been demonstrated compliant with the requirements of FAA AC 90-94, regarding the use of GPS for IFR navigation in en-route, terminal, and non-precision approach operations. The airplane GPS equipment is approved under TSO-C129a. "

AOM-1502-003

!Pre-mod MAU load 27.1

– Navigation using IRS – The FMS has been demonstrated compliant with the requirements of AC 25-4, AC 121-13, and FAR 121, Appendix G, regarding the use of IRS as a long range navigation system. Pilot CONTINUED...

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REVISION 21

Flight Management System

Page 1

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED

qualification is required to comply with operation under AC 121-13. " !Pre-mod MAU load 27.1

– Remote/Oceanic Operation – The FMS has been demonstrated compliant with the requirements of AC 20-130A, regarding multi-sensor system operation in remote/oceanic flight, when operated as a dual system, with dual installed FMS, GPS, and IRS operational prior to the start of flight. The FMS has been demonstrated compliant with the requirements of AC 121-13 and FAR 121, Appendix G, regarding use of IRS as a primary means of navigation in remote/oceanic flight, with dual installed FMS and IRS operational prior to the start of flight. The FMS has been demonstrated compliant with the requirements of FAA Notice 8110.60, regarding use of GPS as a primary means of navigation in remote/oceanic flight, with dual installed FMS and GPS operational prior to the start of flight. Compliance with Notice 8110.60 also requires the operator to use the Honeywell Sure Flight Off Line RAIM and FDE prediction program prior to flight. "

– North Atlantic Minimum Navigation Performance Specification (NAT-MNPS) Airspace – The FMS has been demonstrated compliant with the requirements of AC 120-33 when operated as a dual system, with dual installed FMS, GPS , and IRS operational prior to the start of flight. !Pre-mod MAU load 27.1

– RNP 10 Airspace – FMS has been demonstrated compliant with the requirements of FAA Order 8400.12A when operated as a dual system, with dual installed FMS, GPS, and IRS operational prior to the start of flight. NOTE: The term RNP 10 must be understood as RNAV 10 as per ICAO nomenclature. "

– Enroute and Terminal Operation – The FMS has been demonstrated compliant with the requirements of AC 20-130A and AC 25-15, regarding multi-sensor system IFR operation in CONTINUED...

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Page 2

Flight Management System

REVISION 21

AOM-1502-003

!Pre-mod MAU load 27.1

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

...CONTINUED

en-route/terminal flight, with at least a single PFD, MFD, FMS, VOR, DME, and IRS in NAV mode operational prior to the start of flight. " !Pre-mod MAU load 27.1

– Approach Operation – The FMS has been demonstrated compliant with the requirements of AC 20-130A and AC 25-15, regarding multi-sensor system instrument non-precision approach operation. The FMS has been demonstrated compliant with AC 90-94, regarding the use of GPS for non-precision approaches. The FMS must be operated as at least a single system, with a minimum of one PFD, MFD, and FMS operational prior to commencing the approach. The signal source(s) used to define the approach and on-board equipment must be verified operational prior to commencing the approach, as explained in the General Limitations of this AOM block. The FMS supports the following non-precision approach types: – GPS only (type III FAA overlay definition); – RNAV (including type II or type III FAA overlay definition); – VOR; – VOR-DME; – NDB; – NDB-DME. NOTE: VOR and NDB based approaches include FAA type II GPS overlays. AC 90-94 deals with the use of GPS in the US National Airspace System (NAS). The general approval to use GPS to fly overlay instrument approaches as described in the AC, is initially limited to the NAS. Refer to General Limitations of this block, for use of GPS for non-precision approaches outside the US NAS. " !Pre-mod MAU load 27.1

AOM-1502-003

– Barometric Vertical Navigation – For airplanes with VNAV enabled, the FMS has been demonstrated compliant with the requirements of AC 20-129, regarding the barometric vertical navigation in en-route, terminal, and non-precision approach operations, when used in accordance with the limitations and operational procedures contained in the AFM FMS Supplement. CONTINUED...

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REVISION 21

Flight Management System

Page 3

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED !!MAU load 19.3 and on OR POST-MOD SB 170-31-0019

– The FMS has been demonstrated compliant with the requirements of AC 90-97, regarding the use of barometric vertical navigation for instrument approach operations using decision altitude, when used in accordance with the limitations and operational procedures contained in the AFM FMS Supplement. "" " !Pre-Mod MAU LOAD 27.1, ANAC/FAA Certification

– Terminal and Enroute Area Navigation (RNAV) Operation – The FMS has been demonstrated compliant with the requirements of AC 90-100A, using GPS and DME/DME/IRU sensors. The airplane capability does not constitute RNAV operation approval. The operators must be granted local approval to conduct RNAV operations. NOTE: For RNAV operations based only on DME/DME/IRU mode, it is necessary for the pilot to enter Notam navaids on the FMS Notam page. – RNP Approach (RNP-APCH) Operation – According to AC 90-105, airplane qualified by AC 90-101 are considered qualified for RNP approach (RNP-APCH) operations (including BARO-VNAV) without further examination. The airplane capability does not constitute RNP operation approval. The operators must be granted local approval to conduct RNP operations.

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Page 4

Flight Management System

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

GENERAL LIMITATIONS FMS PILOT’S OPERATING MANUAL !Pre-mod MAU load 27.1

– Pilot’s Operating Manual P/N A28-1146-179 or other approved manual must be available to the flight crew. "

– The Pilot’s Manual must match the FMS software version installed in the airplane.

FMS DATABASE VERSION !Pre-mod MAU load 27.1

– The Honeywell Primus Epic FMS Airplane Database configuration must be that found on Limitations chapter of airplanes AFM. "

NAVIGATION LIMITATIONS – For RNP navigation, the pilots must compare any procedures/route retrieved from the FMS database with those published on the charts. Differences between the charts and the FMS information up to 3 degrees are acceptable. !170/175 models, Pre-Mod MAU load 25.1.0.1

– RNP operations are prohibited after December 31, 2015 due to magnetic variation tables’ expiration date. " !Pre-mod MAU load 27.1

– RNP operations are prohibited after December 31, 2020 due to magnetic variation tables’ expiration date.

AOM-1502-003

"

CONTINUED...

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REVISION 21

Flight Management System

Page 5

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED !Pre-mod MAU load 27.1

– The RNP-RNAV airworthiness approval has not accounted for database accuracy or compatibility as defined per AC 20-153. " !Embraer 170/175 models, ANAC/TCCA/FAA, Pre-mod MAU Load 27.1

– For operations using RNP 1 to RNP less than 2, the use of Flight Director is required. " !Embraer 170/175 models, ANAC/TCCA/FAA, Pre-mod MAU Load 27.1

– For operations using RNP 0.3 to less than 1, the use of GPS and Flight Director is required. " !Pre-mod MAU load 27.1

– Operations requiring RNP less than 0.3 are not approved. " !Pre-mod MAU load 27.1

– The use of speed mode in FMS is prohibited for one engine operative condition. " !Pre-mod MAU load 27.1

– For operations requiring RNP AR, Embraer General Publication GP-3801 must be used. Refer to the applicable AFM supplements for limitations regarding RNP AR operations. "

– The use of VNAV requires the respective FD vertical guidance mode to be active.

– The use of VNAV is prohibited when the respective FD vertical CONTINUED...

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Page 6

Flight Management System

REVISION 21

AOM-1502-003

– The use of FMS Speed requires the respective FD vertical guidance mode to be active.

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

...CONTINUED

guidance mode is other than VNAV , unless pilots adjust the ALT SEL to each altitude constraint in the Flight Plan. – The use of GPS is limited to areas where GPS is approved. Deselection of GPS should be performed in other non-approved areas. – Prior to flight using the FMS for IFR navigation, a minimum of one VOR, DME, and IRS must be verified to be installed and operational. Also, any appropriate ground facilities (VOR, DME) that are utilized by the procedures to be flown must be verified as operational using an approved method (NOTAM, etc.). – If GPS RAIM is annunciated as not available during terminal, enroute, or remote/oceanic operation, the pilot must monitor FMS guidance data and crosscheck against raw data from an alternate source (i.e. VOR, DME, or IRS). – When a GPS Only Approach is planned prior to dispatch, the crew is required to verify that the predictive RAIM at the destination ETA is within the approach criteria. This information (RAIM AVAILABLE) is displayed on the PREDICTIVE RAIM page on the MCDU. – Due to priority use of GPS by the FMS, IFR Navigation using the FMS is limited to use with procedures that are referenced to the WGS-84 or NAD-83 datum, unless other appropriate authorized procedures are used. – IFR Navigation using the FMS is prohibited unless the pilot verifies the currency of the selected navigation database cycle on the NAV IDENT page. – IFR Navigation using the FMS is limited to geographic regions contained within the navigation database that is installed in the airplane.

AOM-1502-003

– Operation above 72° 30.0’ north latitude and below 59° 30.0’ south latitude is prohibited due to unreliable magnetic heading, unless at least one Inertial Reference System (IRS) is verified operational as a sensor to the FMS. In this case, the system will automatically switch to TRUE. – FMS performance management calculations have not been certified by the Airworthiness Authority. FMS performance management CONTINUED...

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REVISION 21

Flight Management System

Page 7

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED

information is advisory information only, and may not be used as a basis for fuel load planning or airplane range predictions. – Selection of FMS Position Update is prohibited during RNP operations, including RNP 10 operations. – The FMS does not correct the speed targets, including approach and go around speeds, for ice conditions or non-normal conditions. It is the pilot responsibility to ensure that the speeds are within the limits in these conditions. – Entry of a planned speed into the FMS which is below the minimum safe maneuver speed prescribed in the basic AFM is prohibited. !MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

– The FMS Disable selection on MCDU Radio Tune NAV page is prohibited. "

– The selection of course interception to a conditional waypoint (waypoints created automatically by FMS that is not part of nav database, i.e. TOC) is prohibited. – The pilot must ensure that displayed guidance data from non-usable stations is not used for navigation purposes by the flight crew. The Notam function in the FMS does not always inhibit tuning of a Notam selected station by the FMS when in AUTO tune mode. Note that the FMS will not use Notam selected station data for FMS position determination. !Pre-mod MAU load 27.1

– The use of the Step Climb function is prohibited. – FMS LNAV may command bank angles above the local regulations limits (i.e. There is no automatic protection for engine out situation).

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Page 8

Flight Management System

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

APPROACH LIMITATIONS – ILS, LOC, LOC-BC, LDA, SDF, GLS, MLS, Visual, and Radar approaches, using the FMS as the navigation source for guidance, are prohibited. This limitation does not apply to RNAV Visual or FMS Visual approaches. – FMS instrument approaches must be accomplished in accordance with approved instrument approach procedures that are retrievable from the FMS navigation database (as displayed on the APPROACH page on the MCDU). The pilot must review the complete procedure, comparing the waypoints, speeds, and altitudes displayed on the FMS with those on the published procedure charts. If any doubt exists about the integrity of the coded procedure, the procedure should not be used. – Prior to commencing and during the final approach, the APPR annunciator must be visible on the PFD. If the APPR annunciator is not visible, and the appropriate runway visibility indications are not observed, the pilot should request a missed approach. – When using FMS guidance to conduct an instrument approach procedure that does not include GPS in the title of the published procedure, the flight crew must verify that the procedure specified navaids(s) and associated avionics are operational (i.e. VOR, DME, ADF). If GPS RAIM is annunciated as not available during the approach, the pilot must monitor FMS guidance data and crosscheck against raw data from the alternate source(s). – When the reported station temperature exceeds the limits published in the approach chart, the use of VNAV barometric procedures are prohibited unless the pilot uses the VNAV temperature compensation function. – The pilot must rely on the altimeter as the primary vertical reference during the final approach segment, including step down fixes. VNAV path guidance is supplementary guidance information. !MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

AOM-1502-003

– Use of VNAV for a constant glide path approach procedures to a Decision Altitude is prohibited. CONTINUED...

"

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REVISION 21

Flight Management System

Page 9

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

...CONTINUED

– Use of VNAV guidance below the published approach minimums is prohibited. !Airplanes Pre-mod MAU load 21.4

– When using VGP, use of Temperature Compensation is prohibited. " !Airplanes Post-mod MAU load 21.2 and Pre-mod MAU load 21.4 OR POST-MOD SB 170-31-0028/02

– VGP approaches are prohibited. "

– The use of temperature compensation feature must be coordinated with ATC if Baro-VNAV operation is intended.

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Page 10

Flight Management System

REVISION 21

AOM-1502-003

– The use of temperature compensation feature is required if BaroVNAV operation outside the temperature limits published on approach procedure chart is intended.

AIRPLANE OPERATIONS MANUAL

LIMITATIONS

RVSM OPERATION MINIMUM EQUIPMENT REQUIRED During RVSM operation it is necessary that the following equipment and instruments be in proper operating condition: – 2 RVSM Compliant Air Data Systems; – 1 Autopilot with Altitude Hold Mode operative; – 1 Altitude Alerter; – 1 Transponder. NOTE: !Airplanes equipped with Air Data Smartprobe software compatible to RVSM operation OR POST-MOD SB 170-34-0009/01

– The ADS 1, ADS 2 and ADS 3 are compliant with RVSM operation. " !PRE-MOD SB 170-34-0009 OR PRE-MOD SB 170-34-0009/01

– Only the ADS 1 and ADS 3 are compliant with RVSM operation, the ADS 2 must not be used for RVSM operation and the airspeed is limited to Mach 0.8. "

AOM-1502-003

– The ADS 3 is not considered RVSM compliant in case of loss of sideslip compensation, i.e., with the EICAS message ADS 3 SLIPCOMP FAIL displayed. – The IESS must not be used for RVSM operation. – Should any of the required equipment fail prior to the airplane entering RVSM airspace, the pilot should request a new clearance to avoid entering this airspace.

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REVISION 12

RVSM Operation Limitations

Page 1

LIMITATIONS

AIRPLANE OPERATIONS MANUAL

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Page 2

RVSM Operation Limitations

REVISION 12

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

SECTION 3 NORMAL PROCEDURES TABLE OF CONTENTS

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Block

Page

Introduction.......................................................... 3-INTRO ....

1

Normal Checklist.................................................. 3-01 ...........

1

Supplementary Normal Checklist....................... 3-02 ...........

1

Internal Safety Inspection................................... 3-03 ...........

1

Power Up............................................................... 3-05 ...........

1

External Inspection.............................................. 3-07 ...........

1

Before Start........................................................... 3-09 ...........

1

Engine Start.......................................................... 3-11 ...........

1

After Start.............................................................. 3-13 ...........

1

Before Takeoff...................................................... 3-15 ...........

1

Takeoff................................................................... 3-16 ...........

1

After Takeoff......................................................... 3-17 ...........

1

Climb..................................................................... 3-18 ...........

1

Descent................................................................. 3-19 ...........

1

Approach............................................................... 3-21 ...........

1

Before Landing..................................................... 3-23 ...........

1

Go Around............................................................. 3-25 ...........

1

After Landing........................................................ 3-27 ...........

1

Shutdown.............................................................. 3-29 ...........

1

Leaving the Airplane............................................ 3-31 ...........

1

Required Equipment for Special Operations.... 3-60 ...........

1

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REVISION 21

Table of Contents

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

Engine................................................................... 3-70 ...........

1

Bounced Landing................................................. 3-72 ...........

1

Environmental...................................................... 3-75 ...........

1

Communication.................................................... 3-76 ...........

1

Flight Instruments................................................ 3-80 ...........

1

RVSM OPERATION............................................... 3-94 ...........

1

Flight Patterns...................................................... 3-95 ...........

1

Category II............................................................. 3-97 ...........

1

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Table of Contents

REVISION 21

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Block Page Air Management System..................................... 3-68 ........... 1

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

INTRODUCTION NORMAL PROCEDURES The operating procedures defined in this section have been defined with the purpose of providing expanded normal procedures that should be used by trained flight crews to ensure that the airplane is in a proper condition and correctly configured for each phase of flight. In case any discrepancy between a procedure contained in this section and the approved Airplane Flight Manual (AFM) occurs, the AFM procedures must be followed. In the event that any of the procedures is missing or unusable, operations may be continued provided the approved AFM is available for use. The normal procedures established are based on the assumption that all equipment is operating normally. It is the crew’s responsibility to verify proper system response. In case improper indications are observed, verification of the appropriate controls position, checking of circuit breakers and testing of the related system should be performed to determine whether the condition affects dispatch or compliance with the MMEL, and whether any maintenance action is required. NORMAL CHECKLIST The normal checklist is just a memory aid to assist the pilots so they do not forget actions which, if not carried out, can result in some type of risk to the airplane, to any of its systems, to its occupants, to the operational environment or can affect passengers comfort. Specific regulations also ask for items to be included in the checklist. The normal checklist is named and divided according to each specific phase of flight.

AOM-1502-003

The normal checklist further assumes that the pilots previously accomplished the normal procedures.

3-INTRO Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

3-INTRO Copyright © by Embraer. Refer to cover page for details.

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REVISION 9

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AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

INTERNAL SAFETY INSPECTION Maintenance Status.............................................. CHECKED Cockpit Emer Equip.............................................. CHECKED ELECTRIC Panel.................................................. SET FUEL Panel........................................................... CHECKED !ANAC/FAA/TCCA airplanes equipped with NO SMKG Switch and NOT equipped with ashtrays on passenger seats

PASSENGER SIGNS Panel................................. AS REQUIRED "

Windshield Wiper.................................................. OFF HYDRAULIC Panel............................................... CHECKED AIR COND/PNEUMATIC Panel............................ CHECKED PASSENGER OXYGEN Panel............................. CHECKED ELT........................................................................ ARMED Landing Gear Lever.............................................. DOWN START/STOP Selectors........................................ STOP Speed Brake Lever............................................... CLOSED RAT Manual Deploy.............................................. STOWED SLAT/FLAP Lever................................................. VERIFIED POS Circuit Breakers.................................................... CHECKED

POWER UP CAUTION: ENSURE THE AIRPLANE IS NOT MOVED BEFORE THE IESS IS INITIALIZED. Battery 1............................................................... ON

AOM-1502-003

Battery 2............................................................... AUTO CAUTION: VERIFY THAT ONLY DISPLAYS 2 AND 3 ARE AVAILABLE. IF MORE THAN DISPLAYS 2 AND 3 ARE AVAILABLE, THE AIRPLANE MUST NOT BE DISPATCHED. Battery Voltage..................................................... CHECKED CONTINUED...

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REVISION 21

Normal Checklist

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

GPU Button (if applicable).................................... PUSHED IN Emergency Lights Selector Knob......................... ON, THEN ARMED FIRE EXTINGUISHER Panel............................... CHECKED APU....................................................................... AS REQUIRED NAV Light.............................................................. ON HYDRAULIC Panel............................................... AS REQUIRED Electronic CBs...................................................... CHECKED Electronic Checklist (if applicable)........................ CHECKED DVDR Panel......................................................... CHECKED Cockpit Reinforced Door Panel (if applicable)..... CHECKED Photoluminescent Strips....................................... CHECKED

BEFORE START PASSENGER SIGNS Panel................................. SET PRESSURIZATION Panel.................................... SET Oxygen Masks...................................................... CHECKED Flight Instruments................................................. X-CHECKED Thrust Levers........................................................ IDLE .................................................................................................................. Fuel Quantity........................................................ CHECKED MCDU................................................................... SET TRIM Panel........................................................... _SET/ZERO/ZERO Doors and Windows............................................. CLOSED Red Beacon.......................................................... ON Emergency/Parking Brake.................................... AS REQUIRED

AFTER START

SLAT/FLAP........................................................... _SET CONTINUED...

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Page 2

Normal Checklist

REVISION 21

AOM-1502-003

Ground Equipment................................................ REMOVED

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

Flight Controls....................................................... CHECKED

BEFORE TAKEOFF Brakes Temperature............................................. CHECKED EICAS................................................................... CHECKED Transponder.......................................................... TA/RA Takeoff Configuration............................................ CHECKED

AFTER TAKEOFF Landing Gear........................................................ UP SLAT/FLAP........................................................... 0

APPROACH PASSENGER SIGNS Panel................................. SET Altimeters.............................................................. SET/X-CHECKED

BEFORE LANDING Landing Gear........................................................ DOWN SLAT/FLAP........................................................... _SET

SHUTDOWN Emergency/Parking Brake.................................... SET START/STOP Selectors........................................ STOP Hydraulic Pump 3A............................................... OFF

LEAVING THE AIRPLANE PASSENGER SIGNS Panel................................. OFF GPU/APU.............................................................. OFF

AOM-1502-003

Batteries 1 and 2.................................................. OFF

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REVISION 21

Normal Checklist

Page 3

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 4

Normal Checklist

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

ECS OFF TAKEOFF SUPPLEMENTARY NORMAL CHECKLIST FOR ECS OFF TAKEOFF. NOTE: – APU BLEED valve will supply bleed air for both PACKS operation during takeoff until 500 ft. If APU BLEED is unavailable the PACKS will remain OFF until 500 ft AGL. – The APU bleed cannot be used for the anti-ice system operation. If the REF A/I is set to ENG or ALL for takeoff or ice is detected during takeoff with APU BLEED, the APU BLEED VALVE will close and the PACKS will switch OFF.

BEFORE START REF ECS................................................................ OFF

AFTER START APU (if available).................................................... ON

AFTER TAKEOFF

AOM-1502-003

APU......................................................................... OFF

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REVISION 21

Supplementary Normal Checklist

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

ENGINE CROSSBLEED START SUPPLEMENTARY NORMAL CROSSBLEED START.

CHECKLIST

FOR

ENGINE

BEFORE START Operating Engine Thrust Lever.............................. ADVANCE AS REQUIRED Bleed Pressure on ECS Synoptic Page................. CHECK Engine Start............................................................ ACCOMPLISH

AFTER START

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Supplementary Normal Checklist

REVISION 21

AOM-1502-003

Thrust Levers.......................................................... AS REQUIRED

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

ENGINE GROUND PNEUMATIC START SUPPLEMENTARY NORMAL CHECKLIST FOR ENGINE GROUND PNEUMATIC START. This procedure is used to start the RH engine. For LH engine perform a crossbleed start.

BEFORE START APU BLEED Button (if applicable)......................... PUSHED OUT NOTE: Close APU Bleed valve if APU is in use. PACKS.................................................................... PUSHED OUT Ground Cart............................................................ CONNECTED Minimum Duct Pressure on ECS Synoptic Page... CHECK Engine Start............................................................ ACCOMPLISH

AFTER START Ground Cart............................................................ DISCONNECTED PACKS.................................................................... PUSHED IN APU BLEED Button (if applicable)......................... PUSHED IN

AOM-1502-003

NOTE: Open APU Bleed valve if it was closed before engine start.

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REVISION 21

Supplementary Normal Checklist

Page 3

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

ENGINE BATTERY START SUPPLEMENTARY NORMAL CHECKLIST FOR ENGINE BATTERY START.

BEFORE START Internal Safety Inspection....................................... PERFORM Battery 1.................................................................. ON Battery 2.................................................................. AUTO Batteries Voltage..................................................... CHECK FIRE EXTINGUISHER Panel................................. CHECK Hydraulic ENG PUMP SHUTOFF 1 and 2............. PUSH IN Electric Hydraulic Pumps 1, 2, 3A and 3B............. OFF PACKS.................................................................... PUSHED OUT Pneumatic Source................................................... CHECK AVAILABLE Minimum Duct Pressure on STATUS Synoptic Page...................................................................... CHECK Ignition Selector Knob............................................. AUTO Red Beacon............................................................ ON Engine Start............................................................ ACCOMPLISH Ground Cart (If applicable)..................................... DISCONNECTED

AFTER START .............................................Wait 2 minutes............................................. PACKS.................................................................... PUSHED IN After electrical PBIT is completed: Hydraulic ENG PUMP SHUTOFF 1 and 2............. PUSHED OUT Electric Hydraulic Pumps 1, 2 and 3B.................... AUTO Electric Hydraulic Pumps 3A.................................. ON

SECOND ENGINE START

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Supplementary Normal Checklist

REVISION 21

AOM-1502-003

ENGINE CROSSBLEED START Procedure.......... PERFORM

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

SINGLE ENGINE TAXI SUPPLEMENTARY NORMAL CHECKLIST FOR SINGLE ENGINE TAXI.

TAXI OUT After one engine start up: Before starting taxi out with engine 2 running: Electric Hydraulic Pump 1 Selector Knob.............. ON Start the second engine with available time from takeoff to allow 2 minutes of thermal stabilization. Taxi time at or near IDLE can be included in the engine warm up period. Second Engine Start............................................... ACCOMPLISH Electric Hydraulic Pump 1 Selector Knob.............. AUTO

TAXI IN APU......................................................................... AS REQUIRED Before shutting down engine 1 during taxi in: Electric Hydraulic Pump 1 Selector Knob.............. ON

AOM-1502-003

After engines shutdown: Electric Hydraulic Pump 1 Selector Knob.............. AUTO

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REVISION 21

Supplementary Normal Checklist

Page 5

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

HOT WEATHER OPERATION NOTE: When engine is shutdown, apply cool air from the air conditioning cart whenever possible.

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Page 6

Supplementary Normal Checklist

REVISION 21

AOM-1502-003

AIR COND RECIRC Button.................................... PUSHED IN CKPT/PAX CABIN Temperature Controllers.......... MAX COLD Doors and Windows................................................ KEEP CLOSED Passenger Cabin Gasper and Cockpit Outlets...... OPEN Window Shades on the Sun-exposed Side of the Cabin..................................................................... CLOSED

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

ICING CONDITIONS, COLD WEATHER AND COLD SOAK OPERATIONS SUPPLEMENTARY NORMAL CHECKLIST FOR ICING CONDITIONS, COLD WEATHER AND COLD SOAK OPERATIONS.

POWER UP Batteries.................................................................. CHECK INSTALLED/ CONDITIONS External Power (if available)................................... CHECK Accomplish a normal power up. After the electric PBIT is done and the message FLT CTRL TEST IN PROG disappears: Hydraulic System Warm Up................................... ACCOMPLISH Electric Hydraulic Pumps Sys 1 and 3A................. ON PTU......................................................................... ON ..........................................Wait 30 seconds.......................................... PTU......................................................................... AUTO Electric Hydraulic Pump Sys 2............................... ON SLAT/FLAP............................................................. CHECKED Fuel Temperature.................................................... CHECK

AOM-1502-003

EXTERNAL SAFETY INSPECTION Wheel Chocks......................................................... IN PLACE Smart Probes/TAT................................................... CHECK Air Conditioning Inlets/Outlets................................ CLEAR OF ICE All Protective Covers.............................................. CHECK REMOVED Engine..................................................................... CLEAR OF ICE OR SNOW Landing Gear.......................................................... CLEAR OF ICE, UNOBSTRUCTED Fuselage, Wing, Tail and Control Surfaces............ FREE OF FROST, ICE OR SNOW APU Area................................................................ CLEAR OF ICE OR SNOW CONTINUED...

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REVISION 21

Supplementary Normal Checklist

Page 7

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Pressurization Static Port....................................... CLEAR OF ICE

CABIN WARM UP Doors....................................................................... CLOSED Air Conditioning Pneumatic Panel.......................... SET

BEFORE START TO DATASET MENU.............................................. SET ADS Probe Heaters................................................ AS REQUIRED

AFTER START Engine Instruments................................................. MONITOR Main Panel.............................................................. CHECK Steering................................................................... ENGAGE Electric Hydraulic Pumps SYS 1 & 2..................... AUTO ADS Probe Heater.................................................. PUSHED OUT

AIRPLANE ANTI-ICING/DEICING FLUID APPLICATION WITH ENGINES/APU RUNNING CAUTION: APU OPERATION IS NOT RECOMMENDED DURING THE AIRPLANE DEICING/ANTI-ICING PROCEDURE. IF APU OPERATION IS ABSOLUTELY NECESSARY, MAKE SURE THAT DEICING/ANTI-ICING FLUID IS NOT APPLIED DIRECTLY TO OR NEAR THE APU AIR INLET, THE APU BLEED AIR VALVE IS CLOSED, AND THE PACKS ARE SET TO OFF.

After Deicing/Anti-icing Procedure is complete: CONTINUED...

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Supplementary Normal Checklist

REVISION 21

AOM-1502-003

Parking Brake......................................................... ON Doors....................................................................... CHECK CLOSED Thrust Levers.......................................................... IDLE SLAT/FLAP............................................................. CHECK UP Pitch Trim................................................................ FULL NOSE DOWN Engine Bleed........................................................... PUSHED OUT APU Bleed.............................................................. PUSHED OUT Packs...................................................................... PUSHED OUT

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

......................................Wait at least 1 minute...................................... APU Bleed Button................................................... PUSHED IN Engine Bleed Buttons............................................. PUSHED IN .....................................Wait at least 3 minutes..................................... Packs Buttons......................................................... PUSHED IN

TAXI Ground Speed Taxi................................................. AS LOW AS PRACTICAL Engine Run-Up....................................................... AS REQUIRED SLAT/FLAP............................................................. AS REQUIRED WARNING: IF FLAPS/SLATS WERE LEFT UP DURING TAXI, COMPLETE AFTER START CHECKLIST BEFORE TAKING OFF. CAUTION: TAXI AT REDUCED SPEED IN ICE-COVERED RUNWAYS TO AVOID SKIDDING THE AIRPLANE. REDUCE SPEED FOR ALL TURNS AND USE CAUTION WHEN TAXING WITH HIGH CROSSWINDS.

BEFORE TAKEOFF Flight Controls......................................................... CHECK Pitch Trim................................................................ SET SLAT/FLAP............................................................. SET Takeoff Configuration.............................................. CHECK Ice Accumulation..................................................... CHECK Engine Run-Up....................................................... AS REQUIRED

IN FLIGHT Engine Parameters................................................. MONITOR Pitch Attitude and Airspeed..................................... MONITOR

AOM-1502-003

DESCENT If engine vibration increases reduce the thrust to idle, advance thrust levers to obtain 70% N1 for 10-30 s and then return to the desired setting.

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REVISION 21

Supplementary Normal Checklist

Page 9

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

HOLDING Landing Gear.......................................................... UP SLAT/FLAP............................................................. UP Minimum Airspeed.................................................. 210 KIAS

TAXI-IN AND PARKING Engine and Wing Anti Ice Protection...................... AS REQUIRED SLAT/FLAP............................................................. AS REQUIRED CAUTION: TAXI AT REDUCED SPEED IN ICE-COVERED RUNWAYS TO AVOID SKIDDING THE AIRPLANE AND THROWING SLUSH ON WHEEL AND BRAKE ASSEMBLIES. NOTE: – Make sure the slat/flap are free from snow, ice or slush before retracting them. – If any difference is felt while taxiing, verify if tires present any flat spot which may indicate that the brake was blocked at touchdown.

THROUGH-FLIGHTS

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Page 10

Supplementary Normal Checklist

REVISION 21

AOM-1502-003

Doors and Windows................................................ CLOSED APU (if available).................................................... ON Wing, Tail and Control Surfaces............................. FREE OF FROST, ICE OR SNOW Air Data Smart and TAT Probes............................. CLEAR OF ICE Engine/APU Air Inlet............................................... CLEAR OF ICE OR SNOW Landing Gear.......................................................... CLEAR OF ICE, UNOBSTRUCTED Air Conditioning Inlets and Outlets......................... CLEAR OF ICE Fuel Tank Vents...................................................... CLEAR OF ICE OR SNOW Pressurization Static Port....................................... CLEAR OF ICE

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

LEAVING THE AIRPLANE - SECURING FOR COLD SOAK OR AN EXTENDED PERIOD

AOM-1502-003

SLAT/FLAP............................................................. UP Pitch Trim................................................................ FULL DOWN Wheel Chocks......................................................... CHECK IN PLACE Emergency/Parking Brakes.................................... AS REQUIRED Protective Covers.................................................... CHECK INSTALLED Water and Waste System....................................... CHECK DRAINED Batteries.................................................................. CHECK REMOVED Doors....................................................................... CHECK CLOSED

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REVISION 21

Supplementary Normal Checklist

Page 11

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

LIGHTNING STRIKE SUPPLEMENTARY NORMAL CHECKLIST FOR LIGHTNING STRIKE.

ON GROUND - IF THE AIRPLANE HAS BEEN HIT BY LIGHTNING External Safety Inspection Holes, Punctures, Discoloration and De-lamination throughout the Whole Airframe............................. CHECK Loose, Melted or Missing Rivets............................ VERIFY Static Dischargers................................................... NUMBER AND CONDITION Nose Gear Landing and Taxi Lights....................... CONDITION Wing Inspection, Landing and Taxi Lights.............. CONDITION Navigation, Strobe and Red Beacon Lights........... CONDITION Smart Probes/TAT Sensor/Ice Detectors................ CHECK Radome................................................................... CHECK Antennas................................................................. CONDITION Maintenance proceeded in accordance with AMM MPP 05-50-01/601 before flight............................ CONFIRM

IN FLIGHT - IF A LIGHTNING STRIKE IS LIKELY TO OCCUR Penetration of Thunderstorm.................................. AVOID Visual Contact with Thunderstorm and Lightning... MAINTAIN Weather Radar........................................................ CHECK FOR PRECIPITATION

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Supplementary Normal Checklist

REVISION 21

AOM-1502-003

NOTE: Remember that radar detects only liquid droplets, not the cloud itself. Thundercloud Detected........................................... CIRCUMNAVIGATE All Cockpit Lights.................................................... ON/FULL BRIGHTNESS Sunglasses.............................................................. CONSIDER WEAR

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

IN FLIGHT - IF THE AIRPLANE HAS BEEN HIT BY LIGHTNING Apply the associated emergency/abnormal procedure if any failure arises after a lightning strike. If the situation is under control after a lightning strike, apply the following procedure to ascertain whether the flight may proceed safely. Altitude.................................................................... MAINTAIN If not required by performance, obstacle clearance or operational contingencies, stop climbing during airplane check. Circuit Breakers...................................................... CHECK Navigation Systems................................................ CHECK Engine Indication.................................................... CHECK Pressurization......................................................... CHECK Flight Controls......................................................... CHECK Fuel System............................................................ CHECK All Other Airplane Systems..................................... CHECK Communication Systems........................................ CHECK NOTE: Consider discontinuing the flight and land at the nearest suitable airport if any unsafe condition is revealed after checking systems operation. Report lightning strike to maintenance personnel by filling out the LIGHTNING STRIKE INCIDENT REPORT form. Report the difference between magnetic compass and PFD heading indications. Report any effects on the airplane systems.

AFTER LANDING

AOM-1502-003

Lightning Strike Event............................................. REPORT TO MAINTENANCE

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REVISION 21

Supplementary Normal Checklist

Page 13

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

TURBULENT AIR PENETRATION Airspeed.................................................................. ADJUST The recommended turbulent air penetration target speeds are: Altitude Below 10000 ft At or above 10000 ft

Recommended speed 250 KIAS MAX 270 KIAS/0.76 M WHICHEVER IS LOWER

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Page 14

Supplementary Normal Checklist

REVISION 21

AOM-1502-003

NOTE: – Do not extend flaps except for approach and landing. – Do not chase altitude. Let both altitude and airspeed vary and maintain attitude. – If severe turbulence cannot be avoided disconnect Autothrottle and make an initial thrust setting for the target speed. Maintain Attitude and Pitch Trim setting. – During climb or descent with variations in indicated airspeed, the use of FLCH mode may result in airplane pitch changes. The use of FPA mode is recommended to maintain airplane attitude.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

CATEGORY II SUPPLEMENTARY NORMAL CHECKLIST FOR CATEGORY II OPERATION.

APPROACH Descent and Approach Checklists.......................... ACCOMPLISH Approach Speeds................................................... SET RA/BARO Selector Knob........................................ RA CAT II Decision Height........................................... SET ON BOTH SIDES Radio Altimeter (if only one is available)................ TEST ILS frequency.......................................................... SET ON BOTH MCDU

BEFORE LANDING Before Landing Checklist........................................ ACCOMPLISH NOTE: – If the RA is set to OFF, there is no EGPWS approach call outs. – If no visual contact is made upon reaching the decision height or if any malfunction could not be promptly identified during approach, a missed approach must be immediately initiated.

MISSED APPROACH GO-AROUND Procedure........................................ ACCOMPLISH

LANDING Reaching the Decision Height with runway in sight:

AOM-1502-003

Autopilot.................................................................. DISENGAGE Landing................................................................... PERFORM

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REVISION 21

Supplementary Normal Checklist

Page 15

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Supplementary Normal Checklist

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

INTERNAL SAFETY INSPECTION The Internal Safety Inspection procedures must be performed before the Power Up on a particular airplane. Maintenance Status................................................ CHECK Cockpit Emergency Equipment.............................. CHECK Check for the availability, status and proper location of the following equipment: – Protective Breathing Equipment (PBE). – Fire Extinguishers. – Crash Axe. – Life Vests. – Escape Ropes. – Flashlights. ELECTRIC Panel.................................................... SET IDG 1 Selector...................................................... AUTO IDG 2 Selector...................................................... AUTO AC BUS TIES Selector......................................... AUTO GPU Button........................................................... PUSH OUT APU GEN Button.................................................. PUSH IN TRU 1................................................................... AUTO TRU ESS.............................................................. AUTO TRU 2................................................................... AUTO DC BUS TIES....................................................... AUTO Battery 1 Selector................................................. OFF Battery 2 Selector................................................. OFF FUEL Panel............................................................. CHECK Verify all fuel pumps knobs in AUTO position and XFEED in the desired position. !ANAC/FAA/TCCA airplanes equipped with NO SMKG Switch and NOT equipped with ashtrays on passenger seats

PASSENGER SIGNS Panel................................... AS REQUIRED Set the NO SMOKE sign at ON during all flight phases. AOM-1502-003

" CONTINUED...

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REVISION 20

Internal Safety Inspection

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

WINDSHIELD WIPER Selector.............................. OFF HYDRAULIC Panel................................................. CHECK SYS 1 ENG PUMP SHUTOFF Button................. PUSH OUT PTU Selector........................................................ AUTO SYS 2 ENG PUMP SHUTOFF Button................. PUSH OUT SYS 1 and 2 ELEC PUMP Selectors................... AUTO SYS 3 ELEC PUMP A.......................................... OFF SYS 3 ELEC PUMP B.......................................... AUTO AIR COND/PNEUMATIC Panel.............................. CHECK Verify all buttons pushed in. PASSENGER OXYGEN Panel............................... CHECK Verify Masks Deploy Selector Knob in Auto. ELT.......................................................................... ARM Landing Gear Lever................................................ DOWN START/STOP Selectors.......................................... STOP Speed Brake Lever................................................. CLOSE RAT Manual Deploy................................................ STOW SLAT/FLAP Lever................................................... VERIFY POSITION Verify and make sure that the actual SLAT/FLAP Lever position agrees with the surface position. Circuit Breakers...................................................... CHECK

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Page 2

Internal Safety Inspection

REVISION 20

AOM-1502-003

Verify both sidewall panels to ensure agreement with maintenance status.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

POWER UP The POWER UP procedures and checklist must be performed every crew’s first flight of the day on a particular airplane or when a power down was required. If receiving the airplane already powered up, verify compliance with all items and perform FIRE EXTINGUISHER panel, Electronic CBs and DVDR CONTROL panel. CAUTION: ENSURE THE AIRPLANE IS NOT MOVED BEFORE THE IESS IS INITIALIZED. Battery 1.................................................................. ON Battery 2.................................................................. AUTO CAUTION:

• •

VERIFY THAT ONLY DISPLAYS 2 AND 3 ARE AVAILABLE. IF MORE THAN DISPLAYS 2 AND 3 ARE AVAILABLE, THE AIRPLANE MUST NOT BE DISPATCHED.

Batteries Voltage..................................................... CHECK

AOM-1502-003

CAUTION: EACH BATTERY VOLTAGE MUST BE AT LEAST 22 VOLTS. IF BATTERIES VOLTAGE IS BETWEEN 21 VOLTS AND 22 VOLTS, RECHARGE THE BATTERIES PRIOR TO TAKEOFF, THROUGH ANY AC SOURCE (INCLUDING ENGINES DURING TAXI) FOR: • 30 MINUTES IF BATTERIES TEMPERATURE IS AT OR ABOVE 0°C OR; • 35 MINUTES IF BATTERIES TEMPERATURE IS AT OR ABOVE -5°C AND BELOW 0°C OR; • 40 MINUTES IF BATTERIES TEMPERATURE IS AT OR ABOVE -10°C AND BELOW -5°C OR; • 50 MINUTES IF BATTERIES TEMPERATURE IS BELOW -10°C.

CONTINUED...

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REVISION 21

Power Up

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

IF BATTERIES VOLTAGE IS BELOW 21 VOLTS REPORT TO MAINTENANCE. NOTE: Minimize the time the airplane is left with batteries as the unique power source, to avoid discharging. EICAS Messages.................................................... CHECK DISPLAYED NOTE: From the preflight to the taxiing phase, a transient power state may prompt temporary EICAS messages such as: AVNX MAU 1A FAIL AVNX MAU 1B FAIL AVNX MAU 2A FAIL AVNX MAU 2B FAIL AVNX MAU 3A FAIL AVNX MAU 3B FAIL Other EICAS messages may cascade. Also, display units may blink, but these effects are transitory, disappearing within one minute. They do not require action from the flight crew. GPU Button (if applicable)...................................... PUSH IN Verify AVAIL light illuminated before pushing in. When GPU is not available, or is not necessary, maintain GPU Button pushed out. NOTE: – The Electrical PBIT is automatically performed after the airplane is powered by any AC source and takes about 3 min to complete. The Electrical PBIT will be interrupted if any electric hydraulic pump is running, or if the FLIGHT CONTROL MODE Panel switches are cycled, or if AC power is interrupted while the test is running. – A FLT CTRL TEST IN PROG Status message is displayed to inform the pilot that the Electrical PBIT is in progress. – If the displays 2 and/or 4 are configured as PFD, set the respective reversionary panel selector knob to MFD then to AUTO. After 8 seconds, the affected display configuration will return to MFD. Emergency Lights Selector Knob........................... ON

Verify there are no fire protection fail messages displayed on the EICAS after Power Up. CONTINUED...

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Page 2

Power Up

REVISION 21

AOM-1502-003

Verify the EMER LT ON and EMER LT NOT ARMED messages displayed on the EICAS. Emergency Lights Selector Knob........................... ARMED FIRE EXTINGUISHER Panel (Overhead).............. CHECK

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

Press and hold the TEST button and observe the following EICAS messages, lights and warnings: – Aural warning. – Fire handles illuminated. – CARGO SMOKE FWD/AFT Buttons illuminated. – APU Button illuminated. – Upper half of the APU EMER STOP Button illuminated. – WARNING lights flashing. – ″CARGO AFT SMOKE″ EICAS message. – ″CARGO FWD SMOKE″ EICAS message. – ″APU FIRE″ EICAS message. – ″ENG 1 FIRE″ EICAS message. – ″ENG 2 FIRE″ EICAS message. – ″FIRE″ warning annunciation displayed inside ITT indicators. APU CONTROL Panel............................................ AS REQUIRED Verify EMER STOP Button is pushed out and not illuminated. The APU FADEC is ready for use when APU rpm and EGT dashed indications (--) are replaced by numbers. NOTE: If AC source is lost due to unintentional GPU or APU generator disconnection, power down the airplane and perform the power up procedure. Navigation Light...................................................... ON HYDRAULIC Panel................................................. AS REQUIRED

AOM-1502-003

Only after the electrical PBIT is completed and if the FLT CTRL BIT EXPIRED EICAS message is displayed, perform the hydraulic panel checks. – Do not move any flight control surface. – Turn the Electrical Hydraulic Pumps 1, 2 and 3A to ON. – Wait 1 min. At this point the FLT CTRL BIT EXPIRED EICAS message should extinguish. – Turn Electrical Hydraulic Pumps 1 and 2 to AUTO. – Turn Electrical Hydraulic Pump 3A to OFF. NOTE: – The FLT CTRL TEST IN PROG Status message is displayed while hydraulic PBIT is in progress. – If the FLT CTRL BIT EXPIRED EICAS message is still displayed, power down the airplane and perform a power up procedure. Electronic CBs........................................................ CHECK – Select CB OUT/LOCK page on the MCDU and check the CBs status to ensure agreement with maintenance status. – If the NEW TRIP prompt is displayed on the MCDU press it to CONTINUED...

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REVISION 21

Power Up

Page 3

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

check the electronic CBs status. Electronic Checklist (if applicable).......................... CHECK Verify that this ECL database corresponds to the paper QRH revision present in the cockpit. DVDR CONTROL Panel......................................... CHECK Honeywell DVDR or L3 DVDR: Press and hold the TEST button for three seconds and verify no fail messages displayed on EICAS. Universal DVDR: Press and hold the TEST button for two seconds. Verify no fail messages displayed on EICAS and observe the following test result: – The FDR 1 and CVR 1 PASS/FAIL lights flash during ten seconds. After ten seconds the FDR 1 and CVR 1 PASS/FAIL lights illuminate steady in green, indicating the completion of a successful test. After DVDR 1 test finishes, the DVDR 2 test will automatically start. Verify the following test result: – The FDR 2 and CVR 2 PASS/FAIL lights flash during ten seconds. After ten seconds the FDR 2 and CVR 2 PASS/FAIL lights illuminate steady in green, indicating the completion of a successful test. If a failure is found, the corresponding FDR/CVR fail light indicator will illuminate steady in amber. Cockpit Door Control Panel.................................... CHECK – Close the cockpit door; – Press and hold the TEST button; – Check DING-DONG alarm and UNLOCKED indication on; – Push in the LOCK button and check the electromechanical latch normal operation; – Press the EMERG ENTRY button on the door control panel in the passenger cabin. Check the UNLOCKED indication flashing and check normal operation of the DING-DONG alarm sequence according to the system logic (refer to AOM 14-01-22 and 14-01-60); – Push out the LOCK button. Photoluminescent Strips......................................... CHECK

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Page 4

Power Up

REVISION 21

AOM-1502-003

Be sure that at least 15 min of ceiling and entrance lighting exposure in bright or daylight to charge the photoluminescent strips.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

EXTERNAL INSPECTION While conducting the external inspection, pilots must be aware of moving vehicles around the airplane and surroundings. In case of suspicious object is identified, inform immediately the security staff. Prior to starting the external inspection: External Lights........................................................ AS REQUIRED If the external lights check was not performed by the maintenance, turn the external lights ON and check them. Turn the lights OFF immediately after checking them. Emergency/Parking Brake...................................... ON

AOM-1502-003

Check if there is sufficient hydraulic pressure to activate the Emergency/Parking Brake to check the Brake Wear Indicators.

CONTINUED...

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REVISION 20

External Inspection

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

EM170AOM980019.DGN

...CONTINUED

Recommended walk-around sequence

1. LEFT FWD FUSELAGE FWD Pax Door........................................................ CHECKED External Power Receptacle.................................... SECURED Left Smart Probes/TAT Sensor/Ice Detector.......... CHECKED Verify condition with no obstructions, covers or damage. 2. NOSE SECTION Windshield Wipers.................................................. CHECKED Radome................................................................... CONDITION, LATCHED Forward Avionics Compartment.............................. SECURED If not in use, visibly secured. Lower FWD Antenna............................................... CONDITION 3. NOSE LANDING GEAR CONTINUED...

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Page 2

External Inspection

REVISION 20

AOM-1502-003

Undamaged.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

Nose Gear............................................................ CHECKED Wheels and Tires.................................................. CONDITION Up Lock Hook....................................................... UNLOCKED Strut/Wheel Well/Doors........................................ CONDITION, NO LEAKS Ground Locking Pin.............................................. REMOVED Landing and Taxi Lights........................................ CONDITION Clean and undamaged. 4. RIGHT FWD FUSELAGE Right Smart Probes/TAT Sensor/Ice Detector........ CHECKED Verify condition with no obstructions, covers or damage. RAT Safety Lock Pin............................................... REMOVED FWD Service Door.................................................. CHECKED If not in use, visibly secured. Oxygen Discharge Indicator................................... GREEN DISC FWD Cargo Door.................................................... CHECKED If not in use, visibly secured. 5. LOWER CENTER FUSELAGE Lower FWD Antennas/FWD Drain Mast................. CONDITION Undamaged. Lower Red Beacon Light........................................ CONDITION Clean and undamaged. 6. RIGHT CENTER WING Wing Inspection Landing and Taxi Lights............... CONDITION Clean and undamaged. Right Ram Air Inlet.................................................. NO OBSTRUCTION No obstruction or damage. Air Inlets and Outlets.............................................. NO OBSTRUCTION

AOM-1502-003

No obstruction or damage. Collector Tank Water Drain Valve Door.................. SECURED If not in use, visibly secured. CONTINUED...

3-07 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

External Inspection

Page 3

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Wing Tank Water Drain Valve................................. CONDITION, NO LEAKS Clean and undamaged. RH 1 Magnetic Level Indicator............................... PUSHED IN, NO LEAKS Pylon....................................................................... CONDITION 7. ENGINE 2 LH SIDE Turbine Exhaust...................................................... CLEAR, NO LEAKS After engine shutdown the scavenge system is no longer effective. A small amount of oil may leak through the aft sump drain and pool in the engine chevron nozzle. If the puddle size exceeds 4 in (102 mm), maintenance should be contacted. Core Pressure Relief Door..................................... CLOSED LH Thrust Reverser................................................ CONDITION AND LATCHED LH Nacelle Strake................................................... CONDITION LH Fan Cowl Doors................................................ CONDITION AND LATCHED Anti-ice Pressure Relief Door................................. CLOSED AND LATCHED Engine Inlet............................................................. CONDITION Check for Foreign Objects and leaks inside air inlet. Ensure that there is no damage to the T12 Sensor and that the FADEC Cooling Inlet is clear. Fan Blades.............................................................. CHECKED Check for damaged Fan Blades and ensure Fan is free to rotate. Check for damages on spinner.

9. RIGHT WING LEADING EDGE CONTINUED...

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Page 4

External Inspection

REVISION 20

AOM-1502-003

8. ENGINE 2 RH SIDE RH Nacelle Strake.................................................. CONDITION Oil Fill Access Door................................................ CLOSED FADEC Cooling Vent.............................................. CLEAR RH Fan Cowl Doors................................................ CONDITION AND LATCHED RH Thrust Reverser................................................ CONDITION AND LATCHED

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

Wing Leading Edges............................................... CONDITION Refueling Compartment Door................................. SECURED RH 2 and RH 3 Magnetic Level Indicators............. PUSHED IN, NO LEAKS Access Doors and Panels...................................... SECURED Pressure Relief Valve............................................. CHECKED Wing Vents.............................................................. NO OBSTRUCTION Navigation and Strobe Lights................................. CONDITION Clean and undamaged. 10. RIGHT WING TRAILING EDGE Static Dischargers................................................... NUMBER AND CONDITION Verify 3 static dischargers on the aileron and 6 static dischargers on the winglet. Refer to the CDL for dispatch with missing items. Flight Control Surfaces and Fairings...................... CONDITION Surfaces clear and unobstructed. 11. RIGHT MAIN GEAR Right Main Gear .................................................... CHECKED Wheels and Tires.................................................... CONDITION Up Lock Hook......................................................... UNLOCKED Strut/Wheel Well/Doors........................................... CONDITION, NO LEAKS Ground Locking Pin................................................ REMOVED Brakes Wear Indicators.......................................... CHECKED 12. RIGHT AFT FUSELAGE Access Doors and Panels...................................... SECURED If not in use, visibly secured. Drain Mast............................................................... CONDITION No obstruction or damage. AFT Cargo Door..................................................... CHECKED

AOM-1502-003

If not in use, visibly secured. AFT Service Door................................................... CHECKED If not in use, visibly secured. Lower AFT Antennas/AFT Drain Mast.................... CONDITION CONTINUED...

3-07 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

External Inspection

Page 5

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Undamaged. Battery Air Outlet..................................................... NO OBSTRUCTION No obstruction or damage. 13. TAIL SECTION Flight Control Surfaces........................................... CONDITION Surfaces Clear and Unobstructed. Empennages Leading Edges.................................. CONDITION Static Dischargers................................................... NUMBER AND CONDITION Verify 4 Static Dischargers on the rudder, 4 on each elevator and 1 on vertical stabilizer. Refer to the CDL for dispatch with missing items. APU......................................................................... CONDITION 14. LEFT AFT FUSELAGE APU External Power Receptacle............................ CHECKED If not in use, visibly secured. Overboard Vent....................................................... NO OBSTRUCTION No obstruction or damage. Pressurization Static Port....................................... NO OBSTRUCTION No obstruction or damage. Potable Water Service Panel.................................. SECURED If not in use, visibly secured. AFT Pax Door......................................................... CHECKED If not in use, visibly secured. Lower AFT Antennas.............................................. CONDITION Undamaged. Access Doors and Panels...................................... SECURED If not in use, visibly secured. Left Main Gear ....................................................... CHECKED Wheels and Tires.................................................... CONDITION Up Lock Hook......................................................... UNLOCKED CONTINUED...

3-07 Copyright © by Embraer. Refer to cover page for details.

Page 6

External Inspection

REVISION 20

AOM-1502-003

15. LEFT MAIN GEAR

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

Strut/Wheel Well/Doors........................................... CONDITION, NO LEAKS Ground Locking Pin................................................ REMOVED Brakes Wear Indicators.......................................... CHECKED 16. LEFT WING TRAILING EDGE Flight Control Surfaces and Fairings...................... CONDITION Surfaces clear and unobstructed. Static Dischargers................................................... NUMBER AND CONDITION Verify 3 static dischargers on the aileron and 6 static dischargers on the winglet. Refer to the CDL for dispatch with missing items. Navigation, Strobe Lights and Upper Beacon Lights..................................................................... CONDITION Clean and undamaged. Upper Antennas...................................................... CONDITION Undamaged. 17. LEFT WING LEADING EDGE Wing Leading Edges............................................... CONDITION Wing Vents.............................................................. NO OBSTRUCTION Pressure Relief Valve............................................. CHECKED Access Doors and Panels...................................... SECURED LH 3 and LH 2 Magnetic Level Indicators.............. PUSHED IN, NO LEAKS 18. ENGINE 1 LH SIDE Turbine Exhaust...................................................... CLEAR, NO LEAKS

AOM-1502-003

After engine shutdown the scavenge system is no longer effective. A small amount of oil may leak through the aft sump drain and pool in the engine chevron nozzle. If the puddle size exceeds 4 in (102 mm), maintenance should be contacted. Core Pressure Relief Door..................................... CLOSED LH Thrust Reverser................................................ CONDITION AND LATCHED LH Nacelle Strake................................................... CONDITION LH Fan Cowl Doors................................................ CONDITION AND LATCHED CONTINUED...

3-07 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

External Inspection

Page 7

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Anti-ice Pressure Relief Door................................. CLOSED AND LATCHED Engine Inlet............................................................. CONDITION Check for Foreign Objects and leaks inside air inlet. Ensure that there is no damage to the T12 Sensor and that the FADEC Cooling Inlet is clear. Fan Blades.............................................................. CHECKED Check for damaged Fan Blades and ensure Fan is free to rotate. Check for damages on spinner. 19. ENGINE 1 RH SIDE RH Nacelle Strake.................................................. CONDITION Oil Fill Access Door................................................ CLOSED FADEC Cooling Vent.............................................. CLEAR RH Fan Cowl Doors................................................ CONDITION AND LATCHED RH Thrust Reverser................................................ CONDITION AND LATCHED 20. LEFT CENTER WING LH 1 Magnetic Level Indicator................................ PUSHED IN, NO LEAKS Landing, Taxi and Wing Inspection Light................ CONDITION Clean and undamaged. Left Ram Air Inlet.................................................... NO OBSTRUCTION No obstruction or damage. Air Inlets and Outlets.............................................. NO OBSTRUCTION No obstruction or damage. Wing Tank Water Drain Valve................................. CONDITION, NO LEAKS Clean and undamaged. Collector Tank Water Drain Valve Door.................. SECURED If not in use, visibly secured. Air Conditioning Connection Access Door.............. CHECKED

3-07 Copyright © by Embraer. Refer to cover page for details.

Page 8

External Inspection

REVISION 20

AOM-1502-003

No obstruction or damage.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

BEFORE START Airplane Manuals and Documents.......................... ON BOARD Check all the required documents including: – Technical Log. – AOM. – QRH. !Airplanes with Electronic Checklist

– Verify if the ECL database version is compatible with the paper QRH revision. "

– Airworthiness Certificate. – Weight and Balance. – Radio Station Certificate. – Navigation Kit. Jump Seat Oxy Masks, Regulators and Audio Panel..................................................................... CHECKED

AOM-1502-003

Verify the observer’s masks. Carry out the test as follows: – Set the regulator control knob to “100%“. – Press and hold the “TEST/RESET“ button. – Verify a short illumination or “blink“ of the flow indicator. – Verify audible oxygen flow in the headset or loudspeakers. – Once the mask fully pressurizes the indicator must go out, showing that the system is leak free. – Release the “TEST/RESET“ button. ELECTRIC Panel.................................................... SET – IDG 1 and IDG 2 Selectors knobs to AUTO. – AC BUS TIES selector knob to AUTO. – GPU button as required. – APU GEN button to PUSHED IN. – TRU 1 toggle switch to AUTO. – TRU ESS toggle switch to AUTO. – TRU 2 toggle switch to AUTO. – DC BUS TIES toggle switch to AUTO. – Battery 1 selector knob to ON. – Battery 2 selector knob to AUTO. COCKPIT LIGHTS Panel........................................ AS REQUIRED – Adjust Main Panel, Overhead Panel and Pedestal lights. CONTINUED...

3-09 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Before Start

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

– Push ANNUNCIATORS TEST button and verify all associated lights. – Set DOME light as required. Engine 1 Fire Handle.............................................. STOWED FUEL Panel............................................................. SET – FUEL XFEED selector knob as required. – DC PUMP selector knob to AUTO. – AC PUMP 1 and AC PUMP 2 selectors knobs to AUTO. PASSENGER SIGNS Panel................................... SET !Airplanes equipped with NO SMKG Switch

– NO SMKG and FSTN BELTS switches to ON. " !Airplanes equipped with NO ELEC DEVICES switch

– NO ELEC DEVICES and FSTN BELTS switches to ON. "

– STERILE light as required. – Turn FSTN BELTS switch to ON after finishing refueling the airplane. FIRE EXTINGUISHER Panel (Overhead).............. CHECKED – Cargo Smoke FWD/AFT buttons pushed out and not illuminated. – APU Fire Extinguishing button pushed out and not illuminated. APU CONTROL Panel............................................ AS REQUIRED The APU FADEC is ready for use when APU rpm and EGT dashed indications (--) are replaced by numbers. EXTERNAL LIGHTS Panel..................................... AS REQUIRED Engine 2 Fire Handle.............................................. STOWED HYDRAULIC Panel................................................. CHECKED/SET – Verify ENG PUMP SHUTOFF 1 and 2 buttons with no lights and guarded. – Verify PTU selector knob to AUTO. – Verify the HYDRAULIC SYS 1 and SYS 2 ELEC PUMPs selector knob to AUTO. – Verify the HYDRAULIC SYS 3 ELEC PUMP A selector knob to OFF. – Verify the HYDRAULIC SYS 3 ELEC PUMP B selector knob to AUTO. PRESSURIZATION Panel...................................... SET – CABIN ALT selector knob to STOP. – MODE selector knob to AUTO. CONTINUED...

3-09 Copyright © by Embraer. Refer to cover page for details.

Page 2

Before Start

REVISION 21

AOM-1502-003

EMER STOP button pushed out and not illuminated.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

– LFE selector knob to STOP. – DUMP button, no lights and guarded. WINDSHIELD HEATING Button............................. PUSHED IN ICE PROTECTION Panel....................................... SET – WINDSHIELD and ENGINE buttons pushed in. – MODE selector knob to AUTO. – WING button pushed in. – TEST selector knob to OFF. AIR COND/PNEUMATIC Panel.............................. SET – CKPT and PAX CABIN temperature control knobs as required. – RECIRC, PACK 1, PACK 2, XBLEED, APU BLEED, BLEED 1 and BLEED 2 buttons pushed in. PASSENGER OXYGEN Panel............................... SET – MASK DEPLOY selector knob to AUTO. – MASK DEPLOYED indicator no light. Oxygen Masks and Regulators.............................. CHECKED/100% Check masks for oxygen supply and for microphone functionality. The MFD Status page must be checked and the available oxygen supply and pressure must be adequate for use.

AOM-1502-003

Carry out the test as follows: – Set the regulator controller to “100%”. – Press and hold the “TEST/RESET” button. – Verify a short illumination or “blink” of the flow indicator. – Verify audible oxygen flow in the headset or loudspeakers. – Once the mask fully pressurizes the indicator must go out, showing that the system is leak free. – Release the “TEST/RESET” button. Glareshield Lights Control Panel............................ AS REQUIRED DISPLAY CONTROLLER Panel............................. SET – Set BARO SET knob to actual pressure. – Push HSI button for Full Compass, ARC or MAP. – Select the FMS as the primary NAV source (if raw data information is intended, use preview mode or Bearing pointers). – BRG circle (O) to OFF, VOR1, ADF1 or FMS1 as required. – BRG diamond (◊) to OFF, VOR2, ADF2 or FMS2 as required. Speed Selector Knob.............................................. MAN REVERSIONARY Panel......................................... SET – Displays selectors knob to AUTO. – Sensors selectors (ADS/IRS) in normal configuration. Flight Instruments................................................... SET/XCHECKED Verify: CONTINUED...

3-09 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Before Start

Page 3

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

– – – – – – –

AIRSPEED TAPES not showing speed. Set altimeter setting and cross check it with the field elevation. EADIs leveled and flag-free. Initial assigned altitude on the ALT SEL. Altitude tape indications cross-check. Both VSIs showing zero. EHSIs with the courses selected according to the intended departure procedure and NAV source selected. – EHSIs and magnetic compass flag free and showing the same magnetic heading. – HDG bug set according to the proposed departure procedure. – Check IESS and adjust the altimeter setting. – Weather set on PFD and/or MFDs MAP page as required. – It is recommended that PM sets the Terrain on MFD up to MSA. – Set the MFDs MAP page menu as required. – TCAS should be always displayed on both MFDs. STATUS Page......................................................... CHECKED Verify on the status page ENG OIL LEVEL and BRAKES EMER ACCU pressure. – Left Seat Pilot should select FLIGHT CONTROL synoptic page. – Right Seat Pilot should remain on STATUS synoptic page. !Airplanes equipped with Autobrake OR POST-MOD SB 170-32-0014

Autobrake................................................................ RTO "

GND PROX TERR INHIB Button........................... CHECKED Verify button pushed out and no striped white bar illuminated. EICAS..................................................................... CHECKED Check EICAS messages to ensure agreement with airplane status. Clock ...................................................................... SET Select GPS on the GPS/INT/SET selector. If the clock displays dashes (-- -- --), adjust the clock INT position. GND PROX G/S INHIB Button............................... CHECKED

Verify no striped white bar illuminated. FLIGHT CONTROLS MODE Panel ....................... CHECKED CONTINUED...

3-09 Copyright © by Embraer. Refer to cover page for details.

Page 4

Before Start

REVISION 21

AOM-1502-003

Verify no striped white bar illuminated. LG WRN INHIB Button........................................... CHECKED

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

Verify ELEVATORS, RUDDER and SPOILER buttons guarded and no striped white bar illuminated. SHAKER 1 and 2 CUTOUT Buttons...................... CHECKED Verify the SHAKER 1 CUTOUT and SHAKER 2 CUTOUT buttons pushed out and no striped white bar illuminated. IGNITION Selector Knobs...................................... AUTO EICAS FULL........................................................... CHECKED Verify the EICAS Full button in the desired position. Speedbrake Lever................................................... CLOSED Thrust Levers.......................................................... IDLE GND PROX FLAP OVRD....................................... CHECKED Verify button pushed out, guarded and no striped white bar illuminated. AUDIO CONTROL Panel........................................ AS REQUIRED Select the microphone and audio reception buttons as required and adjust the volume levels. To avoid background noise do not set the SPKR volume higher than 55. TRIM Panel............................................................. CHECKED Verify that ROLL, YAW and PITCH (Captain, First Officer and Backup) trims are operating properly both ways and check that Position Indication on EICAS changes accordingly. Verify system’s 3 second protection working properly. Adjust YAW and ROLL trims to the neutral position and PITCH trim to the green band. NOTE: The PITCH TRIM Backup Switch may be checked once a day only, by flight crew or maintenance personnel, at the operator′s discretion. Flight Controls DISCONNECT Handles................. CHECKED Alternate Gear Extension Compartment................. CHECKED Verify the alternate gear extension lever is fully down and the electrical override switch is in the “NORMAL” position.

AOM-1502-003

!Pre-mod MAU load 27.1

MCDU..................................................................... SET – On PROGRESS page, activate the FMS AUTOTUNE by deleting the NAV1 frequency for FMS1 and NAV2 frequency for FMS2 displayed on LSK 5L and 5R, respectively. In case of FMS AUTOTUNE OFF takeoff is selected in order to hard-tune a specific VOR, return to FMS AUTOTUNE ON as soon as the VOR frequency is no longer necessary; CONTINUED...

3-09 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Before Start

Page 5

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

– Select NAV IDENT page and check its contents; – Select POSITION INIT page and load the present position; – It is recommended that PF sets the applicable FLIGHT ID and the route in the FMS ROUTE page according to the flight plan and both pilots check course, distance, time, altitude on each waypoint and LFE in the EICAS according to the destination landing field elevation; – It is recommended that PF sets on PERF INIT page 1/1 the CLIMB, CRUISE, DESCENT and DEP/APPROACH speed schedule, select page 2/3 and check/set its contents, on page 3/3 set all fields with the available data; !!Airplanes Post-Mod Load 25.4 or airplanes Post-Mod Load 25.3

– FLIGHT ID information is not removed when the flight complete logic becomes active. The Flight ID information will remain even after a complete power reset is performed (power down – power up). "" "

..............................SHORTLY BEFORE STARTUP.............................. Fuel Quantity........................................................... CHECKED

MCDU..................................................................... SET – Insert the intended SID or the departing runway on the FMS and both pilots must check the accuracy of the procedure retrieved by FMS database. Select LNAV if intended to takeoff with lateral mode armed on ground. – Set the Performance initialization data on PERF INIT page. If it is already available enter the zero fuel weight and press CONFIRM INIT prompt on page 3/3. If performance is confirmed and taking off with vertical mode armed on ground is desired, select VNAV. – Select TAKEOFF DATASET MENU page on the MCDU and set the data below: – Thrust Rate Mode (TO-1, TO-2 or, when applicable,TO-3). – TO TEMP (__ºC). – ATTCS (ON or OFF). – REF ECS (ON or OFF). – REF A/I (OFF, ENG or ALL). – FLEX T/O (ON or OFF). – FLEX TEMP (__ºC). – Press ENTER Prompt to confirm the settings. CONTINUED...

3-09 Copyright © by Embraer. Refer to cover page for details.

Page 6

Before Start

REVISION 21

AOM-1502-003

!Pre-mod MAU load 27.1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL ...CONTINUED

– Select TAKEOFF page and set all data in accordance with the runway analysis and airplane configuration for takeoff. – Select RADIO page 1/2 and insert assigned transponder code and for LVTO using HGS set the ILS frequency for the departing runway on both NAV windows. "

VSPEED READOUTS AND BUGS Four speeds are displayed prior to takeoff:

4O

1OO 12O 13O 14O

V 2 ..........2..........WHITE V FS .......FS.......GREEN

EM170AOM980001B.DGN

V1 ..........1..........MAGENTA V R..........R..........CYAN 1 R 2 FS

VSpeed Readouts and Bugs

NOTE: Green Dot speed can be used for immediate return when the scenario does not allow pilots to calculate landing performance. !Pre-mod MAU load 27.1

SPEED Selector Knob............................................ SET At pilot’s discretion set the SPEED Selector knob to FMS or MANUAL. If MANUAL, set Vfs on the speed window. In case of Noise Abatement procedure set V2 + 10. If FMS, set the departure speed on the DEP/APP speeds page on the FMS.

AOM-1502-003

"

CONTINUED...

3-09 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Before Start

Page 7

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED !Pre-mod MAU load 27.1

TOGA Button........................................................... PRESSED " !Pre-mod MAU load 27.1

TRIM Panel............................................................. SET/ZERO/ZERO Set the PITCH trim according to load sheet and verify YAW and ROLL trims to the neutral position. "

Doors and Windows................................................ CLOSED Verify that the cockpit windows are closed and check all airplane doors closed indications on MFD status page. It is recommended to assure that escape slides are armed. Check the cockpit door securely closed. Takeoff Briefing....................................................... COMPLETED The takeoff briefing should be performed by the PF and the left seat pilot must state the Reject Takeoff procedures. The takeoff briefing shall be performed prior to engines start in order to not interfere with takeoff preparation. The briefing shall cover all actions for both normal, such as flaps and autobrake settings, and non-normal takeoff procedures expected to be used during the takeoff phase. Additional briefing items may be required when different elements exist, such as adverse weather, runway in use, runway conditions, noise abatement requirements, dispatch using the MEL, terrain clearance, special engine failure departure procedure or any other situation or special consideration that differ from routine. Red beacon............................................................. ON Electric Hydraulic Pump 3A.................................... ON Ground Equipment.................................................. AS REQUIRED If performing a push back assure that the ground equipment not used for this procedure is removed. Emergency/Parking Brake...................................... AS REQUIRED

Verify the STEER OFF message displayed on the EICAS.

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Page 8

Before Start

REVISION 21

AOM-1502-003

Verify if the Emergency/Parking Brake is set in accordance with the engine start procedures. Steering Disengage Switch..................................... PRESSED

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

ENGINE START BASIC STATEMENT NOTE: – Engine start can be done simultaneously with push back, requiring the parking brake released and disengagement of the steering (verify EICAS message STEER OFF). In case of a static engine start be sure that the parking brake is set. – Check if the jet way and stairs are removed and the doors are closed. – Obtain ATC and ground clearance. – Confirm nose gear green towing light prior to start pushback with the ground personnel.

ENGINE WARMUP In order to allow thermal stabilization of the engines, operate them at or near IDLE for at least 2 minutes before selecting high trust settings. Taxi time at or near IDLE can be included in the warm up period.

NO BREAK POWER TRANSFER (NBPT) To avoid power interruptions it is recommended to wait 30 s after the %N2 stabilizes before shutting the APU down or GPU disconnection, or to use the Electrical Synoptic Page to follow the power transfer.

ENGINE START PROCEDURE

Associated START/STOP Selector......................... START, then RUN Hold the selector knob at START position for at least 2 s. NOTE: During ground starts only, the transition of the cockpit START/STOP switch from STOP to START must be less than 30 s or the FADEC will prevent an engine start until the switch is cycled through STOP. Engine Parameters................................................. MONITOR Repeat the sequence for the other engine.

AOM-1502-003

!Airplanes with MAU Load 25.4 or airplanes Pre-Mod MAU Load 25.3

PACKS LOGIC DURING ENGINE START

CONTINUED...

3-11 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Engine Start

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

When REF ECS is selected ON in the MCDU T/O DATASET MENU page, the caution EICAS message ENG REF ECS DISAG may be temporarily displayed after both engines have started and are stabilized at idle. Refer to AOM 14-02-15 for details. "

ABNORMAL ENGINE START INDICATIONS Although FADEC provides automatic over-temperature protection and will automatically abort the start in the event of a hot start, hot restart or hung start, the engine start must be manually aborted when: – No positive oil pressure indication within 10 s after N2 speed starts to increase. – During engine start with tailwind, if a positive increase of N1 is not indicated before starter cutout (50% N2). In this case the airplane should be repositioned prior to engine start to minimize tailwind effects. – No ITT indication within 30 s after fuel is applied. – ITT exceeds start limit (hot start). – If oil pressure stabilizes below the engine limits. – N1 and/or N2 failing to accelerate to stable idle speed (hung start). – An intermittent electrical pneumatic or starter malfunction occurs before the starter disengagement. NOTE: – In case an automatic abort occurs or engine start is manually aborted due to abnormal engine indications, its cause must be investigated and corrected before further attempts to start the engines. !170/175 models equipped with ENGINE FADEC 5.60 and on, or airplanes POST-MOD SB 170-73-0007

– The FADEC commands an automatic abort when ITT is 10°C lower than the engine hot start limit. This will prevent ENG EXCEEDANCE EICAS message to be displayed. In this case, two additional engine starts are allowed without any cause investigation.

3-11 Copyright © by Embraer. Refer to cover page for details.

Page 2

Engine Start

REVISION 20

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

AFTER START Ground Equipment.................................................. REMOVED Be sure that the emergency/parking brake is set and nose gear/RAT pins and ground equipment have been removed. N1 Target................................................................ CHECKED The N1 target indication on the EICAS must be equivalent to the N1 target indication available via performance calculation. The difference between N1 given by FADEC (indicated on EICAS) and the computed value is zero or this difference is positive and lower than or equal to 0.5%. Transponder............................................................ AS REQUIRED Select the transponder to TA/RA or in accordance with local requirements. SLAT/FLAP............................................................. SET__ Adjust SLAT/FLAP to a setting consistent with the intended takeoff configuration and performance. !MAU load 19.3 and on OR POST-MOD SB 170-31-0019

If the SLAT/FLAP lever setting is different from the input made on the FMS TAKEOFF page the aural message “NO TAKEOFF FLAP” will sound during the takeoff configuration check. "

APU......................................................................... AS REQUIRED Set APU ON or OFF according to the electrical and pressurization systems. The APU usage shall be defined for a specific operation in order to minimize the overall costs. APU shutting down can only be performed after confirmation of the power transfer through the Electrical Synoptic page or wait 30 s after %N2 stabilizes. Flight Controls......................................................... CHECKED Press the STEERING DISENGAGE SWITCH, check the control column and rudder pedals.

AOM-1502-003

Flight controls should be checked for freedom of movement in a smooth and continuous manner. A full green box indication on the synoptic page is not a requirement for a successful check. – The flight controls check must be performed with the flight controls synoptic page displayed; CONTINUED...

3-13 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

After Start

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

– – – –

Elevator - full up, neutral, full down and neutral; Aileron - full left, neutral, full right and neutral; Rudder - full left, neutral, full right and neutral; Press the steering handle to engage the STEERING and select MAP on the MFD prior to start the taxi.

NOTE: – The Hydraulic PBIT starts when all the three hydraulic systems are pressurized and takes about one minute to complete. Performing the flight controls check while the Hydraulic PBIT is running may interrupt the PBIT. !MAU load 21.2 and on OR POST-MOD SB 170-31-0028

– FLT CTRL TEST IN PROG Status message is displayed while hydraulic PBIT is in progress.

3-13 Copyright © by Embraer. Refer to cover page for details.

Page 2

After Start

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

BEFORE TAKEOFF The Before Takeoff Procedures and checklist must be performed when cleared to line up on the runway. Use all available information such as heading and FMS course indication (PFD), lateral profile (MFD) and departure runway (MCDU) to ensure the airplane is at the assigned runway for takeoff. Cabin Crew............................................................. ADVISED After receiving “Cabin OK” from the Purser, inform the cabin crew through PA: “Cabin Crew prepare for takeoff”. Taxi Ligths............................................................... OFF Turn off the taxi lights. Taxi (side) may be used to assist takeoff from takeoff to 10000 ft AFE at pilots discretion. Landing Lights......................................................... ON Strobe Lights........................................................... ON Brake Temperature................................................. CHECK Brake temperature indication must be in the green range for takeoff. Select MAP on MFD. EICAS..................................................................... CHECKED Check: – No EICAS messages displayed or only EICAS advisory and status messages related to a given airplane configuration resulted by crew action should be displayed. – Thrust Rate Mode: TO-1, TO-2 or, when applicable, TO-3. – ATTCS ON or OFF. – FLEX TEMP (__°C). Transponder............................................................ TA/RA Takeoff Configuration.............................................. CHECKED Press the T/O button and “TAKEOFF OK” synthetic message shall be heard.

AOM-1502-003

NOTE: Arm the AT when the airplane is lined up and ready for takeoff.

3-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Before Takeoff

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 2

Before Takeoff

REVISION 20

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

TAKEOFF

Thrust Levers.......................................................... TO/GA Adjust thrust to 40% N1. When engines stabilize at 40% N1, advance thrust levers to TO/GA detent. Engine Parameters................................................. MONITOR NOTE: During takeoff roll, after checking thrust levers to TO/GA, check N1 equal to N1 target and green ATTCS indication presented on EICAS if ATTCS ON is selected in MCDU. At VR rotate the airplane according to the Flight Director pitch angle.

!170/175 models, MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

In case of Flight Director inoperative, rotate the airplane according to the following schedule: T/O PITCH ANGLE SLAT/FLAP PITCH ANGLE

1 11°

2 10°

4 12° "

!MAU load 19.3 and on OR POST-MOD SB 170-31-0019

In case of Flight Director inoperative, rotate the airplane according to the takeoff pitch angle displayed on TAKEOFF page on the MCDU. "

With Positive Rate: Landing Gear........................................................ UP

AOM-1502-003

Minimum Airspeed................................................ V 2 + 10

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REVISION 21

Takeoff

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 2

Takeoff

REVISION 21

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

AFTER TAKEOFF This checklist should be initiated as soon as possible after FLAPS are retracted. Landing Gear.......................................................... UP Confirm the three white UP indications on the EICAS. SLAT/FLAP............................................................. 0

AOM-1502-003

Select SLAT/FLAP to zero following F-Bug reference. In case F-Bug disappears before total accomplishment of Slat/Flap retraction, retract Slat/Flap following Greed Dot + 10 kt.

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REVISION 20

After Takeoff

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 2

After Takeoff

REVISION 20

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

CLIMB This procedure can be initiated as soon as the After Takeoff Checklist is completed. APU......................................................................... AS REQUIRED Set the APU ON or OFF according to the electrical and pressurization systems. The APU usage shall be defined for a specific operation in order to minimize the overall costs. Air Conditioning and Pressurization....................... CHECKED Check for the proper air conditioning and pressurization settings and parameters. .......................................At Transition Altitude....................................... !Pre-mod MAU load 27.1

Altimeters................................................................ SET/X-CHECKED Set the altimeters to standard (as required by local regulations). The IESS altimeter must be set also. "

.......................................Above 10000 ft AFE....................................... FSTN BELTS.......................................................... AS REQUIRED !Airplanes equipped with NO SMKG Switch

NO SMKG............................................................... AS REQUIRED Verify in accordance with local regulations. " !Airplanes equipped with NO ELEC DEVICES switch

NO ELEC DEVICES............................................... AS REQUIRED Verify in accordance with local regulations. "

External lights......................................................... OFF

AOM-1502-003

Upon passing 10000 ft AFE switch off the external lights according to the operating policies.

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REVISION 21

Climb

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 2

Climb

REVISION 21

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

DESCENT Approach Briefing................................................... COMPLETED – It is recommended to perform the approach briefing before starting descent. – The items to be covered are: inoperative airplane components, weather at destination/alternate airports, fuel status/delays, runway conditions, low visibility procedures, terrain/MSA, descent profile and missed approach procedures. – Set performance data on EFB and check the information. Assess the landing distance for current conditions and compare with the runway length available. If conditions affecting airplane performance change during the approach, reassess the evaluation. Note that the EFB must be kept secured and viewable below 10000 ft. – If the destination airport runway is reported to be slippery or contaminated, it is necessary to discuss the outcome on the landing distance during the approach briefing. The same discussion is applicable if the crew has planned to use additional speed for the approach due to wind/gust conditions. – If any failure that affects the required landing distance occurs in the final approach, consider a missed approach in order to better evaluate the situation and an appropriate runway length. Failures that affect the landing distance are commonly associated to brakes, ground spoilers and/or thrust reversers. – On EFB, if applicable, prepare the approach charts. A thorough understanding by the PF and PM of all the applicable approach charts and Notam is essential, including taxi-in procedures. – Both pilots should set RA/BARO minimums, pre-select radios and courses for the approach. – With VNAV engaged, select the ALT SEL only to altitudes cleared by ATC. !Airplanes equipped with Autobrake OR POST-MOD SB 170-32-0014

AUTOBRAKE.......................................................... SET Set the AUTOBRAKE OFF, LOW, MED or HI in accordance with the runway analysis calculations for landing.

AOM-1502-003

"

Landing Data........................................................... SET – Verify on the LANDING page the expected landing weight. Insert all data according to the type of approach and runway conditions CONTINUED...

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REVISION 21

Descent

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

to set VREF, VAP, VAC and VFS.

14O 16O 15O 14O 13O

1 25 12O 11O 1OO 9O

19O M

GSPD

13O KT

AC

AP RF

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Page 2

Descent

REVISION 21

AOM-1502-003

VAC ..........AC..........MAGENTA V FS ..........FS..........GREEN

FS

EM170AOM980002A.DGN

VREF ..........RF..........WHITE VAP ..........AP..........CYAN

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

APPROACH PASSENGER SIGNS Panel................................... SET !Pre-mod MAU load 27.1

SPEED Selector Knob............................................ AS REQUIRED – The use of FMS SPEEDS after the Final Approach Fix (FAF) is not allowed, as per AFM. Select the speed selector knob to manual when passing the FAF. – If FMS speeds is intended to be used during approach, insert manually in the DEP/APP Speeds page 2/3, or APPROACH Speeds page 2/3 on MCDU the speeds according to the table that follows. SPEED (KIAS) 210 174 [1] 150 140 140 130

FLAP UP 2 3 4 5 FULL

1. FLAP 2 speed resulting in 180 KIAS FLAP 1 speed. "

!Pre-mod MAU load 27.1

Altimeters................................................................ SET/X-CHECKED If flight is being conducted in ICAO airspace, set the altimeters to QNH when passing the Transition Level. Otherwise, set as required by local regulations. "

AOM-1502-003

Approach Aids......................................................... SET/X-CHECKED Verify that the frequencies and courses that were selected and pre-selected are correct for the intended approach. CONTINUED...

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REVISION 21

Approach

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

If using preview mode to set the courses for final approach, assure that the course selected is the one desired (on-side or cross-side). Pressing the preview button once displays the on-side VOR/LOC preview on PFD; pressing twice shows the cross-side VOR/LOC preview and a third time deactivates the preview mode. Ensure that both PFDs are displaying appropriate information.

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Page 2

Approach

REVISION 21

AOM-1502-003

Also verify that the approach minimums and the FMS are properly selected for the type of approach in use.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

BEFORE LANDING Landing Lights......................................................... AS REQUIRED

AOM-1502-003

Taxi (side) lights may be used to assist landing from 10000 ft AFE at pilots discretion. Landing Gear.......................................................... DOWN Slat/Flap.................................................................. SET--

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REVISION 20

Before Landing

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 2

Before Landing

REVISION 20

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

GO-AROUND !Pre-mod MAU load 27.1

TOGA button........................................................... PRESSED "

Thrust Levers.......................................................... TO/GA SLAT/FLAP............................................................. GA FLAPS SET Rotate or verify that autopilot rotates the airplane following the flight director guidance. NOTE: In case of flight director is inoperative, rotate the airplane to 8° nose up. Landing SLAT/FLAP FULL 5

Go Around SLAT/FLAP 4 2

With positive climb: Landing Gear........................................................ UP Minimum Airspeed................................................ V REF + 20

AOM-1502-003

At the acceleration altitude proceed as in a normal takeoff.

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REVISION 21

Go Around

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 2

Go Around

REVISION 21

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

AFTER LANDING NOTE: Upon landing, thrust reversers should be set to MIN REV at 60 KIAS and be closed at 30 KIAS. During RTO the thrust reversers can be used until the airplane comes to a complete stop. APU......................................................................... AS REQUIRED Turn the APU On when it is required. The APU FADEC is ready for use when APU RPM and EGT dashed indications (--) are replaced by numbers. External Lights........................................................ AS REQUIRED Turn off the unnecessary lights. Transponder............................................................ AS REQUIRED Select the transponder to STBY or in accordance with local requirements. SLAT/FLAP............................................................. 0 Select the SLAT/FLAP control lever to zero. PITCH Trim............................................................. SET

AOM-1502-003

Set Pitch Trim to 4 UP.

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REVISION 20

After Landing

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 2

After Landing

REVISION 20

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

SHUTDOWN Thrust Levers.......................................................... IDLE It is recommended to keep the engine running at idle during 2 min to permit engine thermal stabilization prior to shutdown the engine. Time of operation at or near idle, such as taxiing, is included in this 2 min minutes period. Emergency/Parking Brake...................................... SET – Pull the Emergency/Parking Brake to the set position after airplane has stopped. Make sure that the airplane is static before doing so. – Verify brake temperature. If close to the cautionary range, verify that chocks are on and release the Emergency/Parking Brake to reduce the brake cooling time. Electrical.................................................................. ON GPU/APU – If APU GEN is not available, an AC GPU should be plugged in. – Check the AVAIL light illuminated before pushing in the GPU button. NOTE: To prevent electrical power interruptions, it is recommended to wait 10 s after GPU button is pushed in or after APU is stabilized before shutting down one of the engines. If one of the engines is shut down prior to using the APU, wait 10 s until the electrical system has stabilized on the remaining IDG before starting the APU. START/STOP Selectors.......................................... STOP – The engines will not shut down with START/STOP Selectors unless Thrust Levers are first moved to IDLE. If STOP is selected before Thrust Lever is retarded to IDLE, momentarily cycle START/STOP Selector do RUN and back to STOP. Electric Hydraulic Pump System 3A....................... OFF Red Beacon............................................................ OFF FSTN Belts.............................................................. OFF Make sure that the scape slides are disarmed before turning OFF the fasten belts signs.

AOM-1502-003

Turn FSTN BELTS switch to OFF after complete engine stop.

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REVISION 20

Shutdown

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 2

Shutdown

REVISION 20

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

LEAVING THE AIRPLANE NOTE: This procedure applies when a power down is required. PASSENGER SIGNS Panel................................... OFF Set all switches to OFF. Turn off electrical power: APU (if available).................................................. OFF Wait until the APU label OFF is displayed. Wait additional 80 s until APU FUEL SOV CLOSED is momentarily displayed. GPU (if available)................................................. PUSH OUT

AOM-1502-003

Batteries 1 and 2.................................................. OFF

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REVISION 21

Leaving the Airplane

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 2

Leaving the Airplane

REVISION 21

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

REQUIRED EQUIPMENT OPERATIONS

NORMAL PROCEDURES

FOR

SPECIAL

This section is intended to be used as guidance about the minimum equipment required when operating under the following special operations requirements: • RVSM Airspace;

• • • •

BARO RNAV Operations; Low Visibility Operations (LVTO, ILS CAT II, AUTOLAND and HUD A3); Required Navigation Performance Operations (RNP); P-RNAV and B-RNAV;

Additional restrictions on inoperative items may apply based on operator’s practices or local authorities’ requests and/or requirements.

AOM-1502-003

In case of any discrepancies, the AFM/MMEL/Local Operational requirements must prevail over this guidance.

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REVISION 21

Required Equipment for Special Operations

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

REDUCED VERTICAL SEPARATION MINIMUM (RVSM) Equipment Required

Radar Altimeter System Traffic Alert and Collision Avoidance System II (TCAS II) ATC Transponder and Automatic Altitude Reporting System

RVSM Compliant Air Data Systems

Number Required 1 1 Not Disconected/No EICAS message.

Remarks — — Required for autopilot engagement.

1

Required for TCAS operation (if TCAS is required).

-

As required by local regulations.

1

—

2

The ADS 1, ADS 2 and ADS 3 are compliant with RVSM operation. The ADS 3 is not considered RVSM compliant in case of loss of sideslip compensation, i.e., with the EICAS message ADS 3 SLIPCOMP FAIL displayed. TAT sensor failure does not affect ADS compliance with RVSM.

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Page 2

Required Equipment for Special Operations

REVISION 21

AOM-1502-003

Item Autopilot Channels Autopilot (AP) Button ROLL CONTROL DISC and PITCH CONTROL DISC Advisory EICAS Message

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

VERTICAL NAVIGATION - BARO VNAV Equipment Required Item

Number Required

FMS Source Selector Buttons

1

AOM-1502-003

Flight Management System (FMS) Approach (APP) mode button

Remarks Not required if FMS is already selected as navigation source.

1

—

1

—

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REVISION 21

Required Equipment for Special Operations

Page 3

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

LOW VISIBILITY OPERATIONS - ILS CAT II Equipment Required Number Required

Flight Director Channels

2

Autopilot (AP) Button

1

Approach (APP) 1 Mode Button Autopilot/Trim Disengage (AP/TRIM 2 DISC) Buttons ROLL CONTROL DISC and PITCH Not Disconnected/No CONTROL DISC EICAS message. Advisory EICAS Message Windshield Wiper 2 System RA/BARO Selector 2 Knobs Decision Height/Minimum Descent Altitude 2 (MINIMUMS) Selector Knobs VOR/Localizer (V/L) Source Selector Buttons Radar Altimeter System VOR/ILS Systems

1

Remarks For CAT II operation with one engine inoperative, manual FD approaches are prohibited. If Autopilot is required. — If Autopilot is required.

—

— 2 knobs set to RA required.

—

1 required only if PREV button is inoperative on the same side.

1

—

2

— CONTINUED...

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Page 4

Required Equipment for Special Operations

REVISION 21

AOM-1502-003

Item

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

AOM-1502-003

Item Marker Beacon Systems Ground Proximity Warning System (GPWS) VHF/COMM System Air Data Systems (ADS) Primary Flight Displays (PFD) Inertial Reference Systems

Number Required 1

Remarks Unless otherwise authorized.

1

—

1

—

2

—

2

—

2

—

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REVISION 21

Required Equipment for Special Operations

Page 5

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

REQUIRED NAVIGATION PERFORMANCE - RNP 0.3 (PRE-MOD MAU LOAD 27.1)

Item

Number Required

FMS Source Selector Buttons

1

VOR System Distance Measuring Equipment (DME) Systems Global Positioning System (GPS) Flight Management System (FMS) Inertial Reference System MCDU Display Units

RVSM Compliant Air Data Systems

1

Remarks Not required if FMS is already selected as navigation source. —

1

—

1

—

1

—

1

—

1 4

— — The ADS 1, ADS 2 and ADS 3 are compliant with RVSM operation. The ADS 3 is not considered RVSM compliant in case of loss of sideslip compensation, i.e., with the EICAS message ADS 3 SLIPCOMP FAIL displayed. TAT sensor failure does not affect ADS compliance with RVSM.

2

CONTINUED...

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Page 6

Required Equipment for Special Operations

REVISION 21

AOM-1502-003

Equipment Required

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

AOM-1502-003

Item Flight Director Channels

Number Required

Remarks

1

—

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REVISION 21

Required Equipment for Special Operations

Page 7

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

REQUIRED NAVIGATION PERFORMANCE - RNP 1 (PRE-MOD MAU LOAD 27.1) Equipment Required

FMS Source Selector Buttons

Number Required

Remarks

1

—

1 1

VOR System 0 Distance Measuring Equipment (DME) Systems

1 0

1

Global Positioning System (GPS)

0 Flight Management System (FMS)

Not required if FMS is already selected as navigation source. Required when GPS is not available. Not required when GPS operates normally. Required when GPS is not available. Not required when GPS operates normally. Required when VOR and DME are not available. Not required when VOR and DME operate normally.

1

—

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Page 8

Required Equipment for Special Operations

REVISION 21

AOM-1502-003

Item Flight Director Channels

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

REQUIRED NAVIGATION PERFORMANCE - RNP 2 (PRE-MOD MAU LOAD 27.1) Equipment Required Item FMS Source Selector Buttons

Number Required

Remarks

1

—

VOR System

0

1 Required if GPS is not available.

Distance Measuring Equipment (DME) Systems

0

1 Required if GPS is not available.

1 Global Positioning System (GPS) 0

AOM-1502-003

Flight Management System (FMS)

1 Required if VOR and DME are not available. May be inoperative provided VOR and DME operate normally

1

—

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REVISION 21

Required Equipment for Special Operations

Page 9

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

REQUIRED NAVIGATION PERFORMANCE - RNP 10 (PRE-MOD MAU LOAD 27.1) Equipment Required Number Required

FMS Source Selector Buttons

1

Global Positioning System (GPS) Flight Management System (FMS) Inertial Reference System (IRS)

Remarks Not required if FMS is already selected as navigation source.

2

—

2

—

2

—

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Page 10

Required Equipment for Special Operations

REVISION 21

AOM-1502-003

Item

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

PERFORMANCE BASED NAVIGATION - P-RNAV / B-RNAV / RNAV 5 (PRE-MOD MAU LOAD 27.1) Equipment Required Item Flight Director Channels FMS Source Selector Buttons Flight Management System (FMS)

Number Required

Remarks

1

—

1

—

1

—

1 VOR Systems 0 1

Distance Measuring Equipment (DME) System

0

1 Global Positioning System (GPS) 0

Required if GPS is not available. May be inoperative provided GPS operates normally. Required if GPS is not available. May be inoperative provided GPS operates normally. Required if DME or VOR are not available. May be inoperative provided DME and VOR operate normally.

PERFORMANCE BASED NAVIGATION - RNAV 1 / RNAV 2 (PRE-MOD MAU LOAD 27.1)

AOM-1502-003

Equipment Required Item Flight Director Channels FMS Source Selector Buttons

Number Required

Remarks

1

—

1

— CONTINUED...

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REVISION 21

Required Equipment for Special Operations

Page 11

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Item

Number Required 1

Inertial Reference System (IRS)

0 1

Distance Measuring Equipment (DME) Systems

0 1

Global Positioning System (GPS)

0 Flight Management System (FMS)

Remarks Required if GPS is not available. May be inoperative provided GPS operates normally. Required if GPS is not available. May be inoperative provided GPS operates normally. Required if DME or IRS are not available. May be inoperative provided DME and IRS operate normally.

1

—

REQUIRED NAVIGATION PERFORMANCE - RNP APCH (PRE-MOD MAU LOAD 27.1) Equipment Required Number Required

FMS Source Selector Buttons

1

Global Positioning System (GPS) Flight Management System (FMS) MCDU Display Units

Remarks Not required if FMS is already selected as navigation source.

1

—

1

—

1 4

— —

CONTINUED...

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Page 12

Required Equipment for Special Operations

REVISION 21

AOM-1502-003

Item

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

Item

Number Required

RVSM Compliant Air Data Systems

2

Flight Director Channels

1

Remarks The ADS 1, ADS 2 and ADS 3 are compliant with RVSM operation. The ADS 3 is not considered RVSM compliant in case of loss of sideslip compensation, i.e., with the EICAS message ADS 3 SLIPCOMP FAIL displayed. TAT sensor failure does not affect ADS compliance with RVSM. —

AOM-1502-003

NOTE: VGP mode and APP button must be available for RNP APCH with BARO – VNAV.

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REVISION 21

Required Equipment for Special Operations

Page 13

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

RNP AR 0.3 WITH MISSED APPROACH 1.0 (PRE-MOD MAU LOAD 27.1) Equipment Required

VGP

Number Required

Remarks

1

—

1

Radar Altimeter System Enhanced Ground Proximity Warning System (EGPWS) Global Positioning System (GPS) Flight Management System (FMS) Inertial Reference System MCDU Display Units TAT RVSM Compliant Air Data Systems Flight Director

1 1

VGP UNAVAILABLE message not presented on the MCDU scratchtpad. Due to EGPWS inoperative. All modes are required.

1

—

1

—

1

—

1 4 1

— — —

2

—

1

—

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Page 14

Required Equipment for Special Operations

REVISION 21

AOM-1502-003

Item FMS Source Selector Buttons

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

MANUAL PRESSURIZATION OPERATION Pressurization Mode Selector................................. MAN Cabin Altitude Controller......................................... AS REQUIRED The airplane/cabin altitude conversion table must be consulted to determine the cabin altitude according to airplane altitude. Refer to the Quick Reference Handbook. Check on the EICAS the proper cabin altitude, cabin rate and differential pressure values. Selection to UP momentarily position causes an increase of cabin rate. Selection to DOWN momentarily position causes a decrease in cabin rate. At the traffic pattern altitude, slowly position the knob to full UP. The maximum differential pressure at takeoff and landing is 0.2 psi. During descent the thrust levers should be moved as slowly as possible to prevent bumps.

ECS OFF TAKEOFF The Engines or the APU can supply bleed air for the air conditioning packs during takeoff. To have an additional engine thrust during takeoff, the FADEC may send an ECS OFF signal to the AMS controller requesting that no air is extracted from the Engines and the bleed air for packs operation can be provided by the APU. On the MCDU Takeoff Data Set Menu the ECS ON or OFF option is displayed. Selecting ECS ON commands the ENG BLEED to remain ON and selecting ECS OFF commands the ENG BLEED to OFF until the first 500 ft AGL. It is possible to maintain the airplane pressurized during the initial 500 ft, if all the following conditions occur: – ECS is selected to OFF, – APU is available, and

AOM-1502-003

– APU BLEED is PUSHED IN. By accomplishing the recommended procedure, the ENG BLEED valves will remain closed and the APU BLEED valve will supply bleed air for CONTINUED...

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REVISION 20

Suppl Procedures - Air Management System

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

PACKS operation during takeoff until 500 ft AGL. If APU BLEED is unavailable the PACKS will remain OFF until 500 ft AGL.

ECS OFF TAKEOFF PROCEDURE NOTE: – APU BLEED valve will supply bleed air for both PACKS operation during takeoff until 500 ft. If APU BLEED is unavailable, the PACKS will remain OFF until 500 ft AGL. – The APU bleed cannot be used for the anti-ice system operation. If the REF A/I is set to ENG or ALL for takeoff or ice is detected during takeoff with APU BLEED, the APU BLEED VALVE will close and the PACKS will switch OFF. BEFORE START REF ECS.............................................................. OFF Select REF ECS OFF on the MCDU Takeoff Data Set. AFTER START APU (if available).................................................. ON

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Page 2

Suppl Procedures - Air Management System

REVISION 20

AOM-1502-003

AFTER TAKEOFF APU....................................................................... OFF

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

UNPRESSURIZED FLIGHT BASIC STATEMENT Limit flight level to 10000 ft if carrying passengers. For flights without passengers, flight level may be greater than 10000 ft provided crew uses oxygen (Refer to appropriate regulations). For flights with Air Conditioning Packs inoperative (MMEL Item 21-51-00) or not running (MMEL Item 36-11-03), the following recommendations apply: – Prior to flight, if a Ground Air Conditioning System is available, precondition the cabin in order to avoid high peak temperatures, – Consideration should be given to passenger comfort and TAT expected to be encountered in flight. When carrying passengers or TAT is hotter than 20°C, close passenger window shades and turn off unnecessary lights in order to minimize cabin heat. Operating at TAT hotter than 32°C is not recommended due to the resulting high temperatures in the cabin and cockpit, – Using the Recirculation Fans to ON cools down the cabin temperature, – Flight crews can use Total Air Temperature to predict cabin and cockpit temperatures during Ram Air operation, especially at longer duration flights.

BEFORE START Pressurization Mode Selector Knob....................... MAN Outflow Valve on MFD ECS Synoptic Page........... Check fully OPEN If the Outflow Valve is not fully open: CABIN ALT Selector Knob...................................... UP

AOM-1502-003

Hold the cabin altitude selector knob UP until the Outflow Valve is verified fully OPEN on MFD ECS Synoptic Page. If Outflow Valve Indication is inoperative, hold the Cabin Altitude Selector Knob UP for at least 60 s. Except for ditching, the outflow valve should be kept OPEN during the flight in order to avoid pressurizing the cabin. If Outflow Valve may not be moved or is inoperative, it should be secured OPEN and extended overwater operations are prohibited. CONTINUED...

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REVISION 20

Suppl Procedures - Air Management System

Page 3

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

On the MCDU Takeoff Data set: REF ECS................................................................ OFF

CLIMB AND DESCENT

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Page 4

Suppl Procedures - Air Management System

REVISION 20

AOM-1502-003

If possible, maintain climb and descent rates to a maximum of 500 ft/min in order to improve comfort.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

ENGINE CROSSBLEED START ENGINE CROSSBLEED START PROCEDURE It is recommended to leave the Packs in automatic before proceeding with the crossbleed start, as the HPSOV closes when there is no bleed air demand with the airplane on ground. BEFORE START Operating Engine Thrust Lever............................ ADVANCE The minimum recommended bleed duct pressure prior to start is 40 minus 0.5 psi for every 1000 ft above sea level. Smoothly advance operating engine thrust lever to obtain the recommended duct pressure required. Bleed Pressure on Status or ECS Synoptic Page.................................................................... CHECK Engine Start.......................................................... ACCOMPLISH A bleed pressure drop is expected, but no thrust levers adjustment is necessary. AFTER START Thrust Levers........................................................ AS REQUIRED

ENGINE TRANSFER HOSE START This procedure gives the necessary instructions to start one engine of the affected airplane with pneumatic pressure from a source airplane APU or CF34 series engine.

BEFORE START For both airplanes, affected and source, set or keep these switches and controls as follows:

AOM-1502-003

Engine Thrust Levers........................................... IDLE ELECTRIC Panel.................................................. SET – IDG 1 Selector AUTO – IDG 2 Selector AUTO – AC BUS TIES Selector AUTO – GPU Button AS REQUIRED – APU GEN Button PUSHED IN – TRU 1 AUTO – TRU ESS AUTO CONTINUED...

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REVISION 21

Suppl Procedures - Engine

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

– TRU 2 AUTO – DC BUS TIES AUTO – Battery 1 Selector ON – Battery 2 Selector AUTO IGNITION Selector Knobs.................................... AUTO START/STOP Selector......................................... STOP FUEL Panel........................................................... SET – DC PUMP 1 Selector AUTO – AC PUMP 1 and AC PUMP 2 selectors AUTO AIR COND/PNEUMATIC Panel............................ SET – PACK 1 Button PUSHED OUT – PACK 2 Button PUSHED OUT – XBLEED Button PUSHED IN – BLEED 1 Button PUSHED OUT – BLEED 2 Button PUSHED OUT ICE PROTECTION Panel..................................... SET – ENGINE 1 Button PUSHED OUT – ENGINE 2 Button PUSHED OUT – WING Button PUSHED OUT

ENGINE START WITH SOURCE AIRPLANE APU BLEED This procedure gives the necessary instructions to start one engine of the affected airplane with pneumatic pressure being supplied by the source airplane APU. Source Airplane APU....................................................................... START APU BLEED Button.............................................. PUSH IN Affected Airplane Bleed Pressure on ECS Synoptic Page............... CHECK

CONTINUED...

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Page 2

Suppl Procedures - Engine

REVISION 21

AOM-1502-003

The recommended bleed duct pressure for engine start varies with altitude and ambient temperature (OAT) according to the table below. Check on the ECS synoptic page on MFD the bleed pressure before starting the engines.

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL ...CONTINUED

SEA LEVEL OAT (°C) -40 -20 -10 0 10 20 40 54 Altitude (ft)

Pressure (psig) 40 39 38 37 36 35 34 33 CORRECTION Pressure (psig) minus 0.5 psig per 1000 ft ASL.

For instance, at an airport where the field elevation is 2000 ft and the OAT is 10°C, the recommended bleed duct pressure for engine start using a ground pneumatic cart is 35 psig. Engine Start.......................................................... ACCOMPLISH AFTER START Transfer Hose and Ground Equipment................ DISCONNECT Thrust Levers........................................................ AS REQUIRED After engine start reconfigure the airplane as required.

ENGINE START WITH SOURCE AIRPLANE ENGINE BLEED This procedure gives the necessary instructions to start one engine of the affected airplane with pneumatic pressure being supplied by the source airplane engine. Source Airplane ENGINE 2............................................................. START APU BLEED Button.............................................. PUSH OUT BLEED 2 Button................................................... PUSH IN

AOM-1502-003

Engine 2 Thrust Lever.......................................... ADVANCE CONTINUED...

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REVISION 21

Suppl Procedures - Engine

Page 3

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Smoothly advance engine 2 thrust lever on the source airplane until the recommended duct pressure required is achieved on the affected airplane. The minimum recommended bleed duct pressure prior to start is 40 minus 0.5 psi for every 1000 ft above sea level. Affected Airplane Bleed Pressure on ECS Synoptic Page............... CHECK The minimum recommended bleed duct pressure prior to start is 40 minus 0.5 psi for every 1000 ft above sea level. Engine Start.......................................................... ACCOMPLISH A bleed pressure drop is expected, but no thrust levers adjustment on the source airplane is necessary. AFTER START Transfer Hose and Ground Equipment................ DISCONNECT Thrust Levers........................................................ AS REQUIRED After engine start reconfigure the airplane as required.

ENGINE GROUND PNEUMATIC START Engine starts using pneumatic carts usually presents higher ITT values. It is recommended to use pneumatic carts to start the RH engine. At operator’s discretion pneumatic carts can be used to start the LH engine. However, due to airplane’s pneumatic system ducts geometry the pneumatic cart may provide less pneumatic pressure when used to start the LH engine. All safety measures for ground personnel must be observed and the crew must guarantee that the recommended bleed duct pressure for engine start is achieved before attempting an engine start. Perform an engine crossbleed start on the second engine. AIR CONDITIONING PACKS

BEFORE START APU Bleed Button (if applicable).......................... PUSH OUT CONTINUED...

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Page 4

Suppl Procedures - Engine

REVISION 21

AOM-1502-003

Before connecting the ground pneumatic cart, the packs must be pushed out in order to avoid any cabin air contamination.

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL ...CONTINUED

Close APU Bleed valve if APU is in use. PACKS.................................................................. PUSH OUT Ground Cart.......................................................... CONNECT Bleed Pressure on ECS Synoptic Page............... CHECK The recommended bleed duct pressure for engine start varies with altitude and ambient temperature (OAT) according to the table below. Check on the ECS synoptic page on MFD the bleed pressure before starting the engines. SEA LEVEL OAT (°C) -40 -20 -10 0 10 20 40 54 Altitude (ft)

Pressure (psig) 40 39 38 37 36 35 34 33 CORRECTION Pressure (psig) minus 0.5 psig per 1000 ft ASL.

For instance, at an airport where the field elevation is 2000 ft and the OAT is 10°C, the recommended bleed duct pressure for engine start using a ground pneumatic cart is 35 psig. Engine Start.......................................................... ACCOMPLISH Engine start using pneumatic cart usually presents higher ITT values. Consider performing a crossbleed start on the second engine. AFTER START Ground Cart.......................................................... DISCONNECT PACKS.................................................................. PUSH IN

AOM-1502-003

APU Bleed Button (if applicable).......................... PUSH IN Open APU Bleed Valve if it was closed before engine start.

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REVISION 21

Suppl Procedures - Engine

Page 5

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

ENGINE BATTERY START This procedure allows engine starts with batteries as the only electrical power and a pneumatic source (i.e. HPU or APU bleed air). Engine starts using pneumatic carts usually presents higher ITT values. It is recommended to use pneumatic carts to start the RH engine. At operator’s discretion pneumatic carts can be used to start the LH engine. However, due to airplane’s pneumatic system ducts geometry the pneumatic cart may provide less pneumatic pressure when used to start the LH engine. All safety measures for ground personnel must be observed and the crew must guarantee that the recommended bleed duct pressure for engine start is achieved before attempting an engine start. Perform an engine crossbleed start on the second engine. Considerations about the logistic regarding passengers boarding and ground personal clearance must be taken into account prior to the engine start, according to local authority allowances. EICAS MESSAGES Expect EICAS messages related to hydraulic system not being pressurized and PACKs being shutoff. Wait until the procedure is complete before acknowledging any EICAS message not related to an abnormal engine start.

ENGINE BATTERY START PROCEDURE BEFORE START Perform the cabin inspection normally. Internal Safety Inspection..................................... PERFORM Battery 1............................................................... ON Battery 2............................................................... AUTO Batteries Voltage................................................... CHECK FIRE EXTINGUISHER Panel............................... CHECK Electric Hydraulic Pumps 1, 2, 3A AND 3B.......... OFF CONTINUED...

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Page 6

Suppl Procedures - Engine

REVISION 21

AOM-1502-003

Hydraulic ENG PUMP SHUTOFF 1 and 2........... PUSH IN

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

No hydraulic pump may be turned on for at least 3 min after AC power is established or, for airplanes Post-Mod. SB 190-31-0007 (Primus Epic Load 4.5) or an equivalent modification factory incorporated, the FLT CTRL TEST IN PROG Status message is no longer presented. Otherwise the electrical PBIT will not run. PACKS.................................................................. PUSH OUT Before connecting the ground pneumatic cart, the packs must be pushed out in order to avoid any cabin air contamination. Pneumatic Source................................................ CHECK AVAILABLE Minimum Duct Pressure on STATUS Synoptic Page.................................................................... CHECK The minimum recommended bleed duct pressure is 40 minus 0.5 psi for every 1000 ft above sea level. Ignition Selector Knob.......................................... AUTO Red Beacon.......................................................... ON Engine Start.......................................................... ACCOMPLISH Ground Cart (if applicable)................................... DISCONNECT AFTER START ................................................Wait 2 min................................................ PACKS.................................................................. PUSH IN After electrical PBIT is completed: Hydraulic ENG PUMP SHUTOFF 1 and 2...... PUSH OUT Electric Hydraulic Pumps 1, 2 and 3B............. AUTO Electric Hydraulic Pump 3A............................. ON SECOND ENGINE START ENGINE CROSSBLEED START Procedure........ PERFORM

MANUAL STARTER VALVE OPERATION ENGINE START

AOM-1502-003

Accomplish the engine start through the following steps: – Establish good coordination with the ground personnel about the opening of the Starter Control Valve (SCV). Make sure that the safety hazards are assessed, that the ground personnel is CONTINUED...

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REVISION 21

Suppl Procedures - Engine

Page 7

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

protected from heat and air blast from the starters. A safe distance must be kept from the engine air intake and exhaust areas during the start operation. – Use the ramp interphone to communicate with the ground personnel during the start operation. – Turn the START/STOP selector to START and hold it in this position. – Immediately after turning the START/STOP selector to START, ask the ground personnel to open the Starter Control Valve (SCV). – Release the START/STOP selector to the RUN position. – When N2 reaches 50%, ask the ground personnel to close the SCV.

SINGLE ENGINE TAXI To improve fuel savings a single engine taxi can be used, delaying the start of the second engine prior to takeoff and/or shutting one engine just after landing when taxiing in. Single engine taxi may be performed when operating under icing conditions provided that the Engine Run-Up procedure is used before takeoff. However, single engine taxi should be avoided when operating on slippery or contaminated taxiways.

BASIC STATEMENT When performing a single engine taxi with engine 2 running, the Electric Hydraulic Pump 1 Selector knob must be set to ON to ensure that the hydraulic system 1 is pressurized. !Airplanes equipped with SPDA previous than Block 12.1 OR PRE MOD SB170-240056

LOAD SHED EICAS message may be displayed on ground if airplane is powered by only one AC power source and indicated airspeed is at or above 50 kt. "

TAXI OUT CONTINUED...

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Page 8

Suppl Procedures - Engine

REVISION 21

AOM-1502-003

Additional considerations should be taken into account to evaluate the viability of this procedure.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

When taxiing out, check if the following statements permit the single engine taxi. – Ramp gradient: positive ramp gradients demand more power. – Ramp weight: heavier airplanes demand more power. – Taxi time to active runway. – Engines warm up. If performing the Flight Controls check during Single Engine Taxi, check one surface at a time (aileron, rudder or elevator) to avoid spurious FLT CTRL NO DISPATCH message display. SECOND ENGINE START The engine start should be preferably performed with the airplane static to avoid heads down condition during taxi. Prior to takeoff, the second engine warm up cycle must be performed: – Keep the engine running at or near IDLE for at least 2 minutes before selecting high trust settings. TAXI IN When taxiing in, engines cool down cycle must be performed: – Keep engines running for at least 2 minutes after IDLE thrust has been set before engine shutdown to allow engine thermal stabilization. ENGINE 2 SHUTDOWN The APU start cycle must be performed as follows: – The APU start must be accomplished with the engine 2 running or after the engine 2 shutdown cycle has been completed. This procedure is necessary to ensure that battery 2 is available to the airplane’s electrical network as a back-up and not isolated for APU start only. !170/175 models, MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

AOM-1502-003

Nose Wheel Steering System:

CONTINUED...

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REVISION 21

Suppl Procedures - Engine

Page 9

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

The information contained in the NOTE below is applicable to airplanes Pre-Mod. SB 170-31-0017 (Load 17.5). "

!MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

NOTE: – The Electric Hydraulic Pump 2 must be turned ON before engine 2 shut down to ensure hydraulic pressure on steering system. – 30 s after engine 2 shutdown, set the Electric Hydraulic Pump 2 back to AUTO. "

ENGINE 1 SHUTDOWN In order to maintain hydraulic pressure on both brake systems the Electric Hydraulic Pump 1 must be kept ON throughout the taxi.

SINGLE ENGINE TAXI PROCEDURE TAXI OUT After one engine start up: Before starting taxi out with engine 2 running: Electric Hydraulic Pump 1 Selector knob............. ON Start the second engine within an available time from takeoff, to allow 2 min of thermal stabilization. Taxi time at or near IDLE can be included in the engine warm up period. Second engine start.............................................. ACCOMPLISH Electric Hydraulic Pump 1 Selector knob............. AUTO After start procedure............................................. ACCOMPLISH !MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

TAXI IN APU......................................................................... AS REQUIRED Electric Hydraulic Pump 1 or 2 Selector knob....... ON START/STOP Selector............................................ STOP

TAXI IN CONTINUED...

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Page 10

Suppl Procedures - Engine

REVISION 21

AOM-1502-003

"

!MAU load 17.5 and on

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

APU......................................................................... AS REQUIRED Before shutting down engine 1 during taxi in: Electric Hydraulic Pump 1 Selector knob............... ON After engines shutdown: Electric Hydraulic Pump 1 Selector knob............... AUTO

AOM-1502-003

"

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REVISION 21

Suppl Procedures - Engine

Page 11

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 12

Suppl Procedures - Engine

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

BOUNCED LANDING RECOVERY The key factor for a successful landing is a stabilized approach and proper thrust/flare coordination. Do not extend the flare at idle thrust as it will significantly increase landing distance. Reducing to idle before the flare will also require an increase in pitch. Flaring high and quickly reducing thrust to idle can cause the plane to settle abruptly. Do not apply stabilizer trim during the flare.

AOM-1502-003

When a light bounce occurs, maintain or re-establish a normal landing attitude. Increasing pitch can lead to a tail strike. Beware of the increased landing distance and use power as required to soften the second touchdown. When a more severe bounce occurs, initiate a go around – do not attempt to land. Press the go-around button and advance thrust levers to TOGA. Hold the flare attitude until the engines spool up and reset stabilizer trim, then follow normal go-around procedures.

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REVISION 9

Suppl Procedures - Bounced Landing

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 2

Suppl Procedures - Bounced Landing

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

HOT WEATHER OPERATION The following procedures will improve cockpit and cabin cooling during ground operations: NOTE: When engine is shutdown, apply cool air from the air conditioning cart whenever possible. AIR COND RECIRC Button.................................... PUSH IN CKPT/PAX CABIN Temperature Controllers.......... MAX COLD Doors and Windows................................................ KEEP CLOSED Passenger Cabin Gasper and Cockpit Outlets...... OPEN Window Shades on the Sun-exposed Side of the Cabin..................................................................... CLOSE

ICING CONDITIONS, COLD WEATHER AND COLD SOAK OPERATIONS This Section contains the procedures and techniques to operate in icing, cold weather and cold soak conditions and supplements those procedures published in the AFM. In case of differences, the AFM shall govern. Strict reference to AFM procedures throughout the flight is necessary. The procedure begins with information on several systems and then continues with the procedures and checklists to perform before, during and after flight. BASIC STATEMENTS FREEZING RAIN AND FREEZING DRIZZLE Atmospheric conditions involving freezing rain or freezing drizzle associated to supercooled large droplets (SLD), may present a condition that is beyond those for which the airplane was certified.

AOM-1502-003

Both freezing rain and freezing drizzle can exist down to ground level and cause ice to form quite rapidly on all surfaces even during short exposures and on areas not normally known to be subjected to ice accretion. This means that the airplane is not designed to fly under freezing rain/drizzle (SLD) conditions. If the crew notices abnormal ice formation on areas not usually affected by this phenomenon, or ice formation on the previously treated upper surface of the wings, they must consider to be flying under severe icing CONTINUED...

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REVISION 21

Suppl Procedures Environmental

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

conditions. In this case, the anti-ice system is failing to reduce or control ice formation. The crew must then exit freezing rain/drizzle conditions as soon as possible since continuous flight under such conditions is, indeed, quite hazardous. BATTERIES Certain temperatures require batteries removal to prevent cold soaking. Verify that batteries have been reinstalled.

AMBIENT TEMPERATURE VERSUS EXPOSURE TIME

12 REMOVE BATTERIES

8

6

4

NO ACTION

0 −30

−25

−20

−15

−10

AMBIENT TEMPERATURE (°C)

EM170AOM030002A.DGN

EXPOSURE TIME − PARKING (HOURS)

16 OR MORE

NOTE: – The time count starts when the airplane is powered down. – The temperature used to enter the graphic must be the lowest one that the airplane has been exposed during the parking time. – If the airplane is heated (external pneumatic heat source) during the parking, there is no need to remove the batteries, regardless of time and temperature.

CONTINUED...

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Page 2

Suppl Procedures Environmental

REVISION 21

AOM-1502-003

APU

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

Check the APU air inlet, cooling air inlet and APU outlet to ensure that it is clear of ice or snow. If APU cannot be started, apply heat from a ground cart directly into the APU compartment. CAUTION: DO NOT ALLOW THE HOT AIR FROM THE GROUND CART TO EXCEED 100°C (212°F), IN ORDER TO PREVENT ANY DAMAGE TO THE COMPONENTS INSIDE THE COMPARTMENT. EXTERNAL INSPECTION Operating regulations clearly state that no takeoff is allowed when snow, ice or frost is adhering to the airplane. The captain has the final responsibility for ensuring that the airplane is clear of ice, frost or snow. The primary method for the flight crew to ensure a clean airplane is through close visual and physical inspection of the critical surfaces prior to takeoff. Even at intermediate stops, an external walk around is necessary due to the possibility of ice forming after landing from either cold soaking frost, conventional frost or precipitation freezing on the airplane. Make sure wheel chocks are in place. Remove covers from engine air inlet/outlet, APU air outlet, APU oil cooler air inlet, smart probes, TAT probes and wheels. If required, leave engine covers installed until engine start. Visually check the wing, control surfaces, engines and fuselage prior to takeoff. In addition, as no frozen contamination is allowed on the wing upper surface, if ice accretion is suspected, perform a physical (hands-on) inspection to ensure that there is no ice accumulation. Do not touch the surfaces with bare hands, as the skin may stick to a freezing surface.

AOM-1502-003

Check that the fuselage, wing upper and lower surfaces, tail and control surfaces are free of frost, ice or snow. Inspect control surfaces, gaps and hinges for signs of residual fluid or gel. A 3 mm (1/8 in) frost layer is permitted on the underwing surfaces. Frost is not permitted on the lower or upper surface of the horizontal stabilizer or the upper surface of the wing. Cold-soaked fuel frost may form on the ground on the wing upper surface after long flights at low temperatures. CONTINUED...

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REVISION 21

Suppl Procedures Environmental

Page 3

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Expect this kind of frost when fuel remaining in each tank exceeds 2385 kg (5258 lb). A thin layer of hoarfrost is permitted on the fuselage provided the layer is thin enough to distinguish surface features underneath, such as painting and markings. No contamination is permitted on the lower/upper surface of the horizontal stabilizer or the upper surface of the wing. If any degree of contamination is found, de-icing and/or anti-icing has to be requested by the pilot in command. All snow and ice must also be cleared from nose radome and fuselage nose forward of windshield, as it is likely to blow back into windshields during taxi or takeoff. The fan must be able to rotate freely. Heavy accumulation of ice or snow in the inlet, on the spinner, on the fan blades or on the booster area must be removed prior to start. Light ice (similar to hoar frost) or light snow in the inlet, on the spinner, on the fan blades or on the booster area may be removed by performing the engine run-up procedure. A small area of thin ice formed at the basis of the inlet near the drain in front of the fan blades is allowed as long as the fan is free to rotate prior to engine start. During the pre-flight walk-around check that the Air Data Smart Probes (ADSPs) are free from residual deicing and anti-icing fluid and that there is no residual hardened residue on any part of the ADSPs, especially if Type II or IV fluid were used recently. If any contamination is found on Smart Probes, call maintenance.

CONTINUED...

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Page 4

Suppl Procedures Environmental

REVISION 21

AOM-1502-003

Check TAT probes, pressurization static port, all inlets, outlets and vents are clear of ice and unobstructed.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

ANTI−ICING FLUID RESIDUE

EM170AOM030010A.DGN

ANTI−ICING FLUID RESIDUE

AOM-1502-003

SAMPLE OF SMART PROBE ANTI-ICE FLUID CONTAMINATION

CONTINUED...

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REVISION 21

Suppl Procedures Environmental

Page 5

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

EM170AOM130034A.DGN

...CONTINUED

LEGEND: A THIN LAYER HOAR FROST WHERE YOU CAN SEE THE AIRCRAFT MARKINGS ON THE FUSELAGE IS PERMITTED. OTHERWISE, DEICING FLUID MUST BE APPLIED. DEICING FLUID APPLICATION AREAS. DEICING FLUID NON−APPLICATION AREAS.

CONTINUED...

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Page 6

Suppl Procedures Environmental

REVISION 21

AOM-1502-003

DEICING FLUID APPLICATION

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

EM170AOM130035A.DGN

...CONTINUED

LEGEND: ANTI−ICING FLUID APPLICATIONS AREAS. ANTI−ICING FLUID NON−APPLICATION AREAS.

TYPE II/III/IV ANTI-ICING FLUID APPLICATION

AOM-1502-003

If the airplane has become cold soaked as a result of flight at very cold temperatures, fuel might be at a subfreezing temperature. This can cause ice accumulation if the airplane is subjected to high humidity, fog, drizzle or rain even when the outside air temperature is substantially above freezing. At the completion of the walk-around, if ice, snow or frost is discovered, de-icing, and possibly anti-icing will be required. The check for ice accumulation should be done in a well-lit area. CONTINUED...

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REVISION 21

Suppl Procedures Environmental

Page 7

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Recommended practice is to use holdover times in conjunction with a pre-takeoff check to ascertain that frozen deposits have not started to accumulate on treated surfaces. This is a check normally conducted from inside the cockpit. Although only the wing tips and leading edges can be seen from the cockpit, the entire wing is visible from a cabin window. If checking the wing tips is not enough to make sure the holdover times is still appropriate, look at the entire upper surface and not just the leading edge or wing tip. A pre-takeoff contamination check is normally accomplished when the airplane cannot be effectively inspected by a pre-takeoff check or when the holdover times has been exceeded. It must be completed within 5 min prior to beginning takeoff and from the outside the airplane, unless the operator’s program specifies otherwise. The assistance of ground personnel trained and qualified to inspect the wing, empennage and fuselage may be required. The upper surface of the horizontal stabilizer/elevator is not visible either from the ground or the cockpit. A comparative analysis may be used to validate the condition of these surfaces. The upper surface of the wing should be used as the comparative surface. If the inspection of the upper wing surface dictates that there is a requirement to de-ice/anti-ice then the horizontal stabilizer/elevator upper surface must also be de-iced/anti-iced. Conversely, if the inspection of the upper wing surface dictates that there is no requirement to de-ice/anti-ice then the horizontal stabilizer/elevator upper surface need not be de-iced/anti-iced. When contamination is in evidence, the de-icing/anti-icing operation must be repeated. It is the pilot’s responsibility to decide whether or not to accept the airplane for flight. If contamination is suspected, the airplane should return for additional deicing or anti-icing.

DOORS CONTINUED...

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Page 8

Suppl Procedures Environmental

REVISION 21

AOM-1502-003

Holdover time should not be considered an exact figure. It is just an average time, which can be reduced by many factors affecting the fluid effectiveness. In the case of ice build up after deicing/anti-icing fluid application, do not assume that ice will be blown off during takeoff roll.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

All doors and windows must be closed to prevent snow and humidity from entering into the airplane. Whenever possible, to maintain cabin warmth, keep the passenger, cargo and service doors closed at intermediate stops. Check that doors, gear locks and mechanisms are unobstructed and clear of ice and snow and ensure no leaks exist. NOTE: In case the cargo door vent panel is stuck due to cold soak, heat should be applied for at least 5 min to the door latch mechanism at the bottom edge of the door, around the inspection windows. Use a heat gun or heater equipment with maximum hot air temperature of 80°C. ENGINE START Do not start the engine until heavy accumulation of ice or snow in the inlet, on the spinner, on the fan blades or on the booster area is removed. NOTE: The only exception is a small area of thin ice that forms at the base of the inlet near the drain in front of the fan blades. If a thin layer of ice is present in this area, verify fan rotation before engine start. Fuel temperature limits for engine start are the same as those prescribed for APU start. Perform normal engine start. If the engine does not start, maintenance procedures may be required or ground heating may be necessary to warm the nacelle, Air Turbine Starter (ATS) and Starting Control Valve (SCV). CAUTION:

•

AOM-1502-003

•

TO PREVENT DAMAGE TO NACELLE COMPONENTS, DO NOT ALLOW THE HOT AIR FROM THE GROUND CART TO EXCEED 100°C (212°F). DURING COLD WEATHER OPERATIONS, OIL PRESSURE PEAKS TO FULL SCALE MAY OCCUR DUE TO HIGH OIL VISCOSITY. OIL PRESSURE SHOULD DECREASE AS THE OIL TEMPERATURE INCREASES. IF THE OIL PRESSURE REMAINS ABOVE NORMAL OPERATING RANGE, THE ENGINE SHOULD BE SHUTDOWN AND THE CAUSE INVESTIGATED.

TAXI CONTINUED...

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REVISION 21

Suppl Procedures Environmental

Page 9

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Use minimum thrust for breakaway and taxiing, to avoid blowing snow or slush on personnel or airplanes nearby. Maintain ground speed as low as practical when taxiing in snow covered or icy runways. Lower speeds will also avoid throwing slush on the wheel and brake assembly. Use firm brake pressure on taxi stops whenever pavement conditions permit in order to warm up the brakes and dry moisture buildup within the disk stack. Anti-skid protection is not provided below 10 kt, so apply brakes accordingly. During taxi, “cold set” (the condition where the tire retains the flat shape it had while parked) may induce vibration in the airplane. Vibration should disappear as the tires recover their elasticity during taxi. Do not initiate your takeoff run before the “cold set” disappears. Turns should be performed at the largest turning radius, preferably at a speed which do not required braking during the turn. Maintain a greater than normal distance behind other airplanes while taxiing in snow or slush-covered runways, to avoid contamination by snow blown by jet blasts. ENGINE RUN-UP The engine run-up procedure is recommended to be used in the following conditions: – In icing conditions for ground operations of more than 30 min. – In case of increased fan vibration due to fan ice accumulation. – To remove light ice (similar to hoar frost) or light snow in the inlet, on the spinner, on the fan blades or on the booster area as observed during the external inspection. Perform at the earliest convenient moment, not to exceed 30 min after engine start. The engine run-up procedure is as follows: The engine thrust level must be increased at maximum 30 min intervals to a minimum of 54% N1 and held at that thrust level for 30 s or until fan vibration level returns to normal.

Do not apply reverse thrust during taxi, unless absolutely necessary. CONTINUED...

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– If airport surface conditions and the concentration of airplane do not permit the engine thrust level to be increased to 54% N1, then set a thrust level and time at that thrust level as high as practical.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

TAKEOFF It is recommended that the ice shedding engine run-up procedure be completed just before, or in conjunction with the takeoff procedure. Particular attention should be given to engine parameters prior to final advance to takeoff thrust. NOTE: Engine vibration may indicate maximum display value before shedding ice, however, it has no adverse effect on the engine. GENERAL REMARKS WHEN FLYING IN ICING CONDITIONS – Continuously monitor engine parameters, airplane pitch attitude and airspeed. !MAU Load 21.2 up to Load 25.4 - Pentium M or Load 25.3 - Pentium II

– The green dot does not account for ice accretion. Therefore, when flying in icing conditions (EICAS message STALL PROT ICE SPEED displayed) it is recommended to add 10 kt to the green dot. " !MAU Load 25.5.0.1 and on

– The green dot accounts for ice accretion. "

– Be careful for any mistrimmed condition that may be masked by the autopilot - keep the airplane trimmed at all the times. Consider turning autopilot off if you suspect you are flying in severe icing conditions. – Monitor anti-ice systems for proper operation. Apply the associated AFM abnormal procedure in case of system failure. If the failure persists, exit and avoid icing conditions. Make the air traffic controller know you are requesting a change due to icing conditions and keep him informed about it. – Strictly follow AFM Operation In Icing Condition normal procedures.

AOM-1502-003

– Avoid landing in an airport where icing conditions exist or are anticipated if anti-ice system, brakes, thrust reverser, ground spoilers, nosewheel steering or flight controls have failed. – Do not hesitate to leave icing conditions when icing cannot be handled, even with anti-ice system operating properly. CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

– Typically as ice is shed asymmetrically from the fan, a fan unbalance will occur resulting in higher than normal vibration indications. When the ice shedding is complete the vibration levels will typically return to normal indication levels for the particular engine. This reduction in vibration indication is a sign to the flight crew that the ice shed was successful and it may take several minutes or more for this to occur. Likewise, an increase in vibration level would be a sign that fan ice was possibly accumulating. NOTE: Engine and Wing Ice Protection Systems operation is automatic and based on the primary ice detection system. However the crew remains responsible for monitoring icing conditions and for manual activation of the ice protection system if icing conditions are present and the ice detection system is not activating the ice protection system. CLIMB/CRUISE Operation in moderate to severe icing conditions may allow ice to build up on the fan spinner and/or blades. If allowed to accumulate, asymmetrical ice shedding may result in high fan vibration. For operations in moderate to severe icing conditions, reduce one thrust lever at a time towards idle, then advance to a minimum of 70% N1 for 10 - 30 s, then return thrust lever to position required for flight conditions. Accomplish the periodic engine run up every 15 min if fan ice build up is suspected (high indicated or perceived vibration). Operation of the ignition system is not required for this procedure provided the FADEC automatic relight system is operating normally. NOTE: Engine vibration indication may peek to the maximum value prior to ice shedding, however, this will not affect the engine. DESCENT If engine vibration increases reduce the thrust to idle, advance thrust levers to obtain 70% N1 and then return to the desired setting.

CONTINUED...

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When using the autopilot, monitor pitch attitude and speed continuously.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

CAUTION: EVEN SMALL ACCUMULATIONS OF ICE ON THE WING LEADING EDGE MAY CHANGE THE STALL CHARACTERISTICS OR THE STALL PROTECTION SYSTEM WARNING MARGIN. LANDING ON WET OR SLIPPERY RUNWAYS Conduct a positive landing to ensure initial wheel spin-up and initiate firm ground contact upon touchdown, achieving wheel load as quickly as possible. Such technique avoids hydroplaning on wet runways and reduces the strength of any ice bond that might have been eventually formed on brake and wheel assemblies during flight. The factors that influence the occurrence of hydroplaning are high speed, standing water and poor runway macrotexture. When hydroplaning occurs, it causes a substantial loss of tire friction and wheel spin-up may not occur. Icy runways can be very slippery at all speeds depending on temperature. Stopping the airplane with the least landing run must be emphasized when landing on wet or slippery runways. – Anticipate the approach procedures and speeds: a well-planned and executed approach, flare and touchdown minimize the landing distance; – Immediately after touchdown, check the ground spoiler automatic deployment when thrust levers are reduced to IDLE; – Lower nose wheel immediately to the runway. It will decrease lift and will increase main gear loading; – Apply thrust reversers cautiously and observe how the airplane responds before full reverse is used. Normal procedure is to move the thrust levers out of reverse when ground speed is reduced to 60 kt. In a emergency, reverse thrust may be used to bring the airplane to a full stop; – Do not use asymmetric reverse thrust on slippery and icy runways;

AOM-1502-003

– Apply brakes with moderate-to-firm pressure, smoothly and symmetrically, and let the anti-skid do its job; CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

– If no braking action is felt, hydroplaning is probably occurring. Do not apply Emergency/Parking Brake, as it will remove anti-skid protection. Maintain runway centerline and keep braking until airplane is decelerated. LEAVING THE AIRPLANE - SECURING FOR COLD SOAK OR AN EXTENDED PERIOD Anti-icing fluid can be applied to the airplane surfaces at the time of arrival, on short turn arounds during freezing precipitation, and on overnight stops. This will minimize ice accumulation before departure and usually makes subsequent deicing easier. The procedure ″LEAVING THE AIRPLANE - SECURING FOR COLD SOAK OR AN EXTENDED PERIOD″ should be performed in the event of extended airplane exposure to low temperatures. At non-maintenance stations, the crew should ensure that the actions have been accomplished. For an icy ramp, leave Emergency/Parking Brakes applied. Otherwise, Emergency/Parking Brakes must not be applied to avoid brakes freezing. Wheel and tires may melt snow or ice by the heat retained in the brakes. Parking main tires on a layer of sand or on a mat may prevent tires from freezing on pavement surfaces. Install protective covers at engines and APU inlets/outlets, APU oil cooler air inlet, smart probes, TAT probes, and wheels. Drain water and waste from all water tanks if cold soak temperature is expected to be lower than 0°C (32°F).

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REVISION 21

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If the airplane is heated (external pneumatic heat source) during the parking, there is no need to remove the batteries, regardless of time and temperature.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

ICING CONDITIONS, COLD WEATHER AND COLD SOAK PROCEDURE POWER UP Batteries.................................................................. CHECK INSTALLED/ CONDITIONS Minimum Battery Temperature................................ -20°C (-4°F) Minimum Battery 2 Voltage..................................... 22.0 V External Power (if available)................................... CHECK Minimum temperature (to start the APU) using external electrical power....................................... -54°C (-65°F) Accomplish a normal power up. Wait for PBIT completeness and the message FLT CTRL TEST IN PROG disappearance. Hydraulic System Warm Up................................... ACCOMPLISH Warm up must be accomplished before starting the engines in case of reservoir temperatures below -18°C (-0.4°F). Electric Hydraulic Pump Sys 1 and 3A.................. ON PTU......................................................................... ON ...............................................WAIT 30 s............................................... PTU......................................................................... AUTO Electric Hydraulic Pump Sys 2............................... ON SLAT/FLAP............................................................. CHECK Leave the flaps and slats up if application of anti-icing/deicing fluids is expected. Ensure they are free from ice or snow. Extend and retract them. Fuel Temperature.................................................... CHECK Minimum Fuel Temperature for APU Start: For Jet A Fuel......................................................... -37°C (-34°F) For Jet A1 Fuel....................................................... -44°C (-47°F) NOTE: For minimum temperature limits applicable to other fuel types, refer to the AFM.

AOM-1502-003

EXTERNAL SAFETY INSPECTION Wheel Chocks......................................................... IN PLACE CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Smart Probes/TAT................................................... CHECK Free of ice and residual deicing and anti-icing fluids. Air Conditioning Inlets/Outlets................................ CLEAR OF ICE Ice Protective Covers.............................................. CHECK REMOVED If required, leave engine covers installed until engine start. Engine..................................................................... CLEAR OF ICE OR SNOW NOTE: The only exception is a small area of thin ice that forms at the base of the inlet near the drain in front of the fan blades. If a thin layer of ice is present in this area, verify fan rotation before engine start. Landing Gear.......................................................... CLEAR OF ICE, UNOBSTRUCTED Fuselage, Wing, Tail and Control Surfaces............ FREE OF FROST, ICE OR SNOW If ice accretion is suspected, perform a physical (hands on) inspection to ensure that there is no ice accumulation. APU Area................................................................ CLEAR OF ICE OR SNOW CABIN WARM UP Doors....................................................................... CLOSE Air Conditioning Pneumatic Panel.......................... SET Keep all pushbuttons pushed in, while bleeding air from the APU, or use a ground cart to warm up the interior of the airplane. Set Cockpit and Cabin rotating knobs to full hot for rapid cabin warm up in low ambient temperature. The warm-up should be accomplished with all doors closed and the toilets doors open, if possible. BEFORE START TO DATASET MENU.............................................. SET

CONTINUED...

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Ensure that the TO DATASET MENU page on the MCDU and Ice Protection Mode Selector are set according to the table OAT/visible moisture table.

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL ...CONTINUED

ON GROUND Outside Air Temperature

Visible Moisture

Higher than 10°C Equal to or higher than 5°C and equal to or lower than10°C Lower than 5°C Any

YES

MCDU (TAKEOFF DATASET MENU) OFF

YES

ENG

YES NO

ALL OFF

Ice Protection Mode Selector

AUTO

If moisture presence is in question, visible moisture should be assumed. ADS Probe Heaters................................................ AS REQUIRED If probes are contaminated, push in and verify light illuminates. NOTE: Do not turn on the heaters while the airplane is energized by batteries, to avoid battery discharge. ENGINE START Minimum Oil Temperature....................................... CHECK Minimum Oil Temperature is -40°C (-40°F). Accomplish normal engine start procedure. AFTER START Engine Instruments................................................. MONITOR Continue to monitor engine instruments, mainly oil pressure and temperature. Apply associated abnormal procedure if any failure arises. Main Panel.............................................................. CHECK Check proper operation of all instruments and systems. Confirm engine anti-ice system is operating normally. Steering................................................................... ENGAGE

AOM-1502-003

NOTE: If steering had been disengaged for push-back, reengage it and keep it engaged while the electric hydraulic pumps are running.

CONTINUED...

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REVISION 21

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

After reservoir temperatures are higher than 0°C (32°F) for systems 1, 2 and 3: Electric Hydraulic Pumps Sys 1 and 2................. AUTO NOTE: – When attempting a single engine taxi with engine 2, select the Electric Hydraulic Pump 1 knob to ON. – After starting engine 1, select Electric Hydraulic Pump 1 knob to AUTO. AIRPLANE ANTI-ICING/DEICING ENGINES/APU RUNNING

FLUID

APPLICATION

WITH

CAUTION: APU OPERATION IS NOT RECOMMENDED DURING THE AIRPLANE DEICING/ANTI-ICING PROCEDURE. IF APU OPERATION IS ABSOLUTELY NECESSARY, MAKE SURE THAT DEICING/ANTI-ICING FLUID IS NOT APPLIED DIRECTLY TO OR NEAR THE APU AIR INLET, THE APU BLEED AIR VALVE IS CLOSED, AND THE PACKS ARE SET TO OFF. Parking Brake......................................................... ON Doors....................................................................... CLOSE Thrust Levers.......................................................... IDLE SLAT/FLAP............................................................. CHECK UP Pitch Trim................................................................ FULL NOSE DOWN Engine Bleed Buttons............................................. PUSH OUT APU Bleed Button................................................... PUSH OUT Packs Buttons......................................................... PUSH OUT Packs should be off to avoid contamination of cabin air with fumes generated from ingestion of fluids in engine/APU. After Deicing/Anti-icing Procedure is complete: ..........................................Wait at least 1 min.......................................... APU Bleed Button................................................. PUSH IN Engine Bleed Buttons........................................... PUSH IN

Wait at least three minutes to push in the air conditioning packs pushbuttons, thereby avoiding contaminating the airframe air conditioning system with deicing/anti-icing fluid gases. CONTINUED...

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..........................................Wait at least 3 min.......................................... Packs Buttons....................................................... PUSH IN

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

TAXI Ground Speed Taxi................................................. AS LOW AS PRACTICAL Engine Run-Up....................................................... AS REQUIRED SLAT/FLAP............................................................. AS REQUIRED When taxiing through slush or standing water, slat/flap should be retracted to avoid snow and slush contamination from the main gear wheels. WARNING: IF FLAPS/SLATS WERE LEFT UP DURING TAXI, COMPLETE AFTER START CHECKLIST BEFORE TAKING OFF. CAUTION: TAXI AT REDUCED SPEED IN ICE-COVERED RUNWAYS TO AVOID SKIDDING THE AIRPLANE. REDUCE SPEED FOR ALL TURNS AND USE CAUTION WHEN TAXING WITH HIGH CROSSWINDS. BEFORE TAKEOFF Takeoff Briefing....................................................... COMPLETE Flight Controls......................................................... CHECK Check freedom of movement and full travel of all flight controls (including trims). A full green box indication on the synoptic page or a full trim travel indication on the EICAS are not a requirement for a successful check. Pitch Trim................................................................ SET Set the PITCH trim according to load sheet and verify YAW and ROLL trims to the neutral position. SLAT/FLAP............................................................. SET Set SLAT/FLAP to takeoff setting (if flaps were left up after starting the engines). Takeoff Configuration.............................................. CHECK Ice Accumulation..................................................... CHECK Engine Run-Up....................................................... AS REQUIRED TAKEOFF

AOM-1502-003

Accomplish takeoff procedure normally. IN FLIGHT CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Engine Parameters................................................. MONITOR Pitch Attitude and Airspeed..................................... MONITOR !MAU Load 21.2 up to Load 25.4 - Pentium M or Load 25.3 - Pentium II

– The green dot does not account for ice accretion. Therefore, when flying in icing conditions (EICAS message STALL PROT ICE SPEED displayed) it is recommended to add 10 kt to the green dot. " !MAU Load 25.5.0.1 and on

– The green dot accounts for ice accretion. "

HOLDING Landing Gear.......................................................... UP SLAT/FLAP............................................................. UP Minimum Airspeed.................................................. 210 KIAS CAUTION: EVEN SMALL ACCUMULATIONS OF ICE ON THE WING LEADING EDGE MAY CHANGE THE STALL CHARACTERISTICS OR THE STALL PROTECTION SYSTEM WARNING MARGIN. APPROACH AND LANDING Observe normal approach and landing procedures. TAXI-IN AND PARKING Engine and Wing Ice Protection............................. AS REQUIRED After landing, set the Engine and Wing Ice Protection systems using the overhead panel Ice Protection Mode Switches according to weather conditions. SLAT/FLAP............................................................. AS REQUIRED

NOTE: – Make sure the slat/flap are free from snow, ice or slush before retracting them. CONTINUED...

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CAUTION: TAXI AT REDUCED SPEED IN ICE-COVERED RUNWAYS TO AVOID SKIDDING THE AIRPLANE AND THROWING SLUSH ON WHEEL AND BRAKE ASSEMBLIES.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

– If any difference is felt while taxiing, verify if tires present any flat spot which may indicate that the brake was blocked at touchdown. THROUGH-FLIGHTS Doors and Windows................................................ CLOSE Whenever possible, to maintain cabin warmth, keep the passenger, cargo and service doors closed at intermediate stops. APU......................................................................... ON APU should be on to provide bleed air to the air conditioning packs in order to maintain cabin heat. Walk around the airplane and check the following items: Wing, Tail and Control Surfaces........................... FREE OF FROST, ICE OR SNOW Air Data Smart and TAT Probes........................... CLEAR OF ICE Engine/APU Air Inlet............................................. CLEAR OF ICE OR SNOW NOTE: The only exception is a small area of thin ice that forms at the base of the inlet near the drain in front of the fan blades. If a thin layer of ice is present in this area, verify fan rotation before engine start. Landing Gear ....................................................... CLEAR OF ICE, UNOBSTRUCTED Air Conditioning Inlets and Outlets....................... CLEAR OF ICE Fuel Tank Vents.................................................... CLEAR OF ICE OR SNOW Pressurization Static Port..................................... CLEAR OF ICE In case of deice/anti-ice fluid application is necessary, perform ″AIRPLANE ANTI-ICING/DEICING FLUID APPLICATION WITH ENGINES/APU RUNNING″.

AOM-1502-003

LEAVING THE AIRPLANE - SECURING FOR COLD SOAK OR AN EXTENDED PERIOD SLAT/FLAP............................................................. UP Pitch Trim................................................................ FULL DOWN Wheel Chocks......................................................... CHECK IN PLACE CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

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Emergency/Parking Brakes.................................... AS REQUIRED Protective Covers.................................................... CHECK INSTALLED Water and Waste System....................................... CHECK DRAINED Batteries.................................................................. CHECK REMOVED Doors....................................................................... CHECK CLOSED

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

LIGHTNING STRIKE Even though the airplane is adequately protected against lightning strike effects, operating procedures should be established in an attempt to avoid such phenomenon. In-flight lightning avoidance is closely associated with thunderstorm avoidance. Therefore, avoid penetration of thunderstorms. Maintain visual contact with thunderstorms during the daytime and lightning at night. Check the radar for precipitation, review all available types of weather information, examine other pilot reports and follow ATC instructions. Even with a good weather report received and understood, pay close attention to storms that develop rapidly along the route in a given area which cannot be predicted. While enroute, continuously update weather briefings through the use of radio contact and airborne equipment for actual storm avoidance. Remember that radar detects only liquid droplets, not the cloud itself. Only rain suspended in the cloud will produce a radar echo, which may lead to occasional encounters with hail and lightning. If possible, circumnavigate the detected thundercloud or area by 25 miles or more when traffic conditions permit. Be aware that lightning can strike an airplane miles away from the extreme side of a developed thunderstorm. Reports of airplane receiving strikes in clear air at 25 NM or more from the nearest storm are common.

AOM-1502-003

The following paragraphs summarize the conditions in which strikes are most common: Meteorological conditions: incident reports show that an airplane must be within or beneath a cloud to receive a strike, or in or near regions of precipitation. Incident reports show that in over 80% of the strikes, the airplane was within a cloud and experiencing some precipitation and turbulence. But other strikes may occur in a cloud where there is no precipitation nearby, in clear air reasonably distant from a thundercloud, during snowstorms and in clouds over erupting volcanoes. Flight through or in the vicinity of a cold front, warm front, stationary front, unstable air or squall lines increases the probability of lightning strikes. Incident reports also show that lightning strikes occur most commonly under light or heavy turbulence conditions. CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

– Flight regime: Takeoff, climb, level flight, descent or approach. – Altitude: strikes are more common between 5000 ft and 20000 ft, but may occur at virtually all flight altitudes. Lightning strike incidents at lower altitudes are far more frequent since at higher altitudes airplanes can divert around thunderclouds with greater ease. – Outside air temperature: most strike incidents have occurred when the airplane is flying in temperatures near or at freezing level. Strikes may also occur at temperatures as high as 25°C, or as low as - 45°C. Metal airplanes produce a phenomenon called Faraday Cage effect, which distributes electrical charges along the airframe in such a manner that occupants and internal components will not receive the high current that causes injury and damage. Internal components and systems have also special protections against side effects of the lightning strike. Direct effects which result from a lightning strike may be: – Pit marks often seen along the fuselage or holes in the trailing edge of wing and tail tips. – Melting of rivets. – Puncturing of nonmetallic structures. – Puncturing and de-lamination of composites. – Slight deformation of metal skins and structure. – Welding or roughening of moveable hinges and bearings. – Damage to other parts that may conduct lightning current other than the airframe, such as bonding or diverted straps and pitot tubes. Effects caused by the flash-induced electromagnetic field and the increase of the voltage due to the current at the airplane structure are defined as indirect effects and may be: – Interruption of instruments and navigation equipment. – Damage to electronic and electrical equipment. – Popping of circuit breakers. – Engine flame-out. CONTINUED...

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– Loss of electrical power.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

Report the lightning strike to maintenance personnel, by filling out the LIGHTNING STRIKE INCIDENT REPORT form.

AOM-1502-003

Make sure that maintenance proceed is in accordance with AMM MPP 05-50-01/ 601 before flying the airplane again.

CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED !EMBRAER 170 Models

EMB−170 LIGHTN I N G STRIKE INCIDENT REPORT Part I (to be com pleted by flight crew) Conditions at tim e of strike:

· · · ·

Operator:

Date of incident:

ACFT S/N:

Flight no.:

Route: From

To:

·

Flight phase:

·

Other: W eather: Cloud type % Cover Ceiling (ft) Top at (ft) OAT (°C)

Altitude:

ft Approach

Rain

· ·

Sleet

Airspeed: Clim b

Hail

kt Level Flight

Snow

W as St. Elm o’s fire visible before strike?

None

Yes

No

Any effects on:

Electrical power system : Flight controls: Engine: Avionics: Other (describe): Any effects on personnel, such as: Flash blindness: EM170AOM030001A.DGN

·

Electrical shock:

Part I com pleted by:

" CONTINUED...

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EMB-170 LIGHTNING STRIKE INCIDENT REPORT

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL ...CONTINUED !EMBRAER 175 Models

EMB − 1 7 5 LIGHTN I N G STRIKE INCIDENT REPORT Part I (to be com pleted by flight crew) Conditions at tim e of strike:

· · · ·

Operator:

Date of incident:

ACFT S/N:

Flight no.:

Route: From

To:

·

Flight phase:

·

Other: W eather: Cloud type % Cover Ceiling (ft) Top at (ft) OAT (°C)

Altitude:

ft Approach

Rain

· ·

Sleet

Airspeed: Clim b

Hail

kt Level Flight

Snow

W as St. Elm o’s fire visible before strike?

None

Yes

No

Any effects on:

Electrical power system : Flight controls: Engine: Avionics: Other (describe): Any effects on personnel, such as: Flash blindness: Electrical shock:

Part I com pleted by:

EM170AOM030014A.DGN

·

AOM-1502-003

EMB-175 LIGHTNING STRIKE INCIDENT REPORT

"

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

LIGHTNING STRIKE PROCEDURE IN-FLIGHT OPERATIONS IF A LIGHTNING STRIKE IS LIKELY TO OCCUR Indication of imminent lightning strike event: – Buildup of static discharge which causes interference on ADF indicators or noise in communication receivers. – Elmo’s Fire, which is visible at night as small electrical discharges running across the windshields and sparking on the wings. Penetration in the Thunderstorm............................ AVOID Visual Contact with Thunderstorm and Lightning... MAINTAIN Weather Radar........................................................ CHECK FOR PRECIPITATION NOTE: Remember that radar detects only liquid droplets, not the cloud itself. Thundercloud Detected........................................... CIRCUMNAVIGATE Circumnavigate the detected thundercloud or area at 25 miles or more when traffic conditions permit. All Cockpit Lights.................................................... ON/FULL BRIGHTNESS Sunglasses.............................................................. CONSIDER WEAR Consider wearing sunglasses to protect your eyes from the flash or have one pilot keep eyes downward. IF THE AIRPLANE HAS BEEN HIT BY LIGHTNING Apply the associated emergency/abnormal procedure if any failure arises after a lightning strike. If the situation is under control after a lightning strike, apply the following procedure to ascertain whether the flight may proceed safely. Altitude.................................................................. MAINTAIN If not required by performance, obstacle clearance or operational contingencies, stop climbing during airplane check. Circuit Breakers.................................................... CHECK

CONTINUED...

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Navigation Systems.............................................. CHECK

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

Check magnetic compass and heading system for normal indications. Report on the LIGHTNING STRIKE INCIDENT REPORT the difference between the magnetic compass and the heading indication on PFDs. Engine Indication.................................................. CHECK Check engine for normal indications. In case of engine shutdown, the flight crew must analyze the circumstances of the event and consider an engine airstart. Pressurization....................................................... CHECK Check for no evidences of pressurization leaks. Flight Controls....................................................... CHECK Check all flight controls for freedom of movement. Verify that slats/flaps and speed brakes are working properly. Fuel System.......................................................... CHECK Check fuel system for normal operation. Monitor fuel remaining and fuel consumption to ascertain that no fuel leak exists. All Other Airplane Systems................................... CHECK Check for EICAS messages and airplane instruments following a panel scan sequence to ascertain that safety of flight prevails. Communication Systems...................................... CHECK NOTE: Consider discontinuing the flight and land at the nearest suitable airport if any unsafe condition is revealed after checking systems operation. AFTER LANDING Lightning Strike Event............................................. REPORT TO MAINTENANCE Report any effects on the airplane systems. Report the lightning strike to the maintenance personnel by filling out the LIGHTNING STRIKE INCIDENT REPORT form. ON GROUND OPERATIONS

AOM-1502-003

ON THE GROUND IF THE AIRPLANE HAS BEEN HIT BY LIGHTNING CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

External safety inspection Holes, Punctures, Discoloration and Delamination throughout the Whole Airframe............................. CHECK Loose, Melted or Missing Rivets............................ VERIFY Verify that there are no loose, melted or missing rivets. Static Dischargers................................................... NUMBER AND CONDITION Verify 3 static dischargers on each aileron and 6 static dischargers on each winglet. E170/175: Verify 4 Static Dischargers on the rudder, 4 on each elevator and 1 on vertical stabilizer. E190/195: Verify 4 Static Dischargers on the rudder, 3 on each elevator, 3 on each horizontal stabilizer and 1 on vertical stabilizer. Refer to CDL for dispatch with missing items. Landing and Taxi Lights.......................................... CONDITION Clean and undamaged. Wing Inspection, Landing and Taxi Lights.............. CONDITION Clean and undamaged. Navigation, Strobe and Red Beacon Lights........... CONDITION Clean and undamaged. Smart Probes/TAT Sensor/Ice Detectors................ CHECK Verify condition with no obstructions, covers or damage. Radome................................................................... CHECK Antennas................................................................. CONDITION Maintenance procedure is in accordance with AMM MPP 05-50-01/601 before the airplane next flight.. CONFIRM

TURBULENT AIR PENETRATION If possible, flight through severe turbulence must be avoided. If not possible, the following procedure is recommended for turbulent air penetration. The recommended turbulent air penetration target speeds are:

CONTINUED...

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Airspeed.................................................................. ADJUST Below 10000 ft........................................................ MAX 250 KIAS

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

At or above 10000 ft............................................... MAX 270 KIAS/0.76 M WHICHEVER IS LOWER Severe turbulence causes large and often rapid variations in indicated airspeed. Do not chase the airspeed. NOTE: – Do not extend flaps except for approach and landing. – Large altitude variations are possible in severe turbulence, do not chase altitude. Let both altitude and airspeed vary and maintain attitude. – If severe turbulence cannot be avoided disconnect Autothrottle and make an initial thrust setting for the target airspeed. Change thrust setting only in case of unacceptable airspeed variation. – Maintain wings level and pitch attitude. Use attitude indicator as the primary instrument. Do not use sudden large control inputs. – Maintain control of the airplane with the elevators. After establishing the trim setting for penetration speed, do not change pitch trim.

VOLCANIC ASH Flight in areas of known volcanic activity must be avoided. This is particularly crucial while flying at night or in daytime with instrument meteorological conditions when volcanic dust may not be visible. When a flight is planned into an area with a known potential for volcanic activity, it is recommended that all NOTAMs and air traffic control directives be reviewed for current status of volcanic activity. If volcanic activity is reported, the planned flight should remain well clear of the area and, if possible, stay on the upwind side of the volcanic dust. The airplane’s weather radar is not capable of detecting volcanic ash/dust clouds and is therefore not reliable under these circumstances. The presence of volcanic ash/dust may be indicated by: – Smoke of dust appearing inside the airplane; – Odor similar to electrical smoke;

AOM-1502-003

– Engine malfunctions such as power loss, engine stalls, increasing ITT, fluctuating engine rpm, etc; CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

– At night, Saint Elmo’s fire/static discharges may be observed around the windshield or windows; – Orange glow from engine inlets. Flight into volcanic ash/dust clouds can result in the degradation of airplane and engine performance. The adverse effects cause by volcanic ash/dust encounters may be: – Rapid erosion and damage to the internal engine components; – Ash/dust build-up and blockage of the guide vanes and cooling holes, which may cause surge, loss of thrust and/or high ITT; – Ash/dust blockage of the pitot system, resulting in unreliable airspeed indications; – The abrasive properties of volcanic material may cause serious damage to the engines, wing and tail leading edge surfaces, windshields, landing lights, etc;

CONTINUED...

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– Windshield and windows may become opaque, reducing visibility.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

ON GROUND OPERATIONS The following recommendations apply to starting and operating engines on airports where volcanic ash has fallen and ground contamination is present: – When the airplane is parked install engine covers or reposition the aircraft to limit blowing ash accumulation from wind and jet blasts from other airplane; – During preflight, check that the engine inlet and exhaust areas have been cleared of volcanic ash; – Check that all volcanic ash has been cleaned away from the area within 14 ft of the engine inlets; – Use APU for engine starting only, not for air conditioning. – Prior to starting, dry motor the engine for 90 s in order to blow out any ash that may have entered the engine bypass duct area; – Use minimum required thrust for breakaway and taxi; therefore single engine taxi must be avoided. – Keep bleed valves closed during taxi. Limit exposure to contaminated surfaces by selecting alternate cleaner taxi routes if available; – Avoid static engine operation above idle; – Be aware of loose ash being blown by the exhaust wake of other aircraft. Maintain adequate ground separation and allow for dust to set on the runway before starting the takeoff roll; – Use a rolling takeoff technique. Avoid setting high thrust at low airspeeds; – After landing at an airport contaminated with volcanic ash, minimize the use of reverse thrust to prevent any recirculation ingestion.

IN FLIGHT OPERATIONS

AOM-1502-003

Flight operations in volcanic ash are extremely hazardous and must be avoided. However, volcanic ash/dust clouds may sometimes extend for hundreds of miles, reaching altitudes above 60000 ft and an encounter may be unavoidable. In case of an inadvertent encounter, proceed as follows: CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Volcanic Ash Area................................................... EXIT/AVOID Consider performing a 180° turn. Due to the dimensions of the ash clouds, a 180° turn could be the fastest way to exit an ash cloud. Crew Oxygen Masks (if necessary)........................ DON, 100% If a significant amount of volcanic ash fills the cockpit or if there is a strong smell of sulphur, don an oxygen mask and select 100%. Ignition Selectors.................................................... OVRD Autothrottle.............................................................. DISENGAGE The autothrottle must be kept disconnected to prevent thrust increase due to smart probes contamination. Ice Protection Mode Selector................................. ON This action will increase bleed air extraction from the engines and further improve the engine stall margin. Thrust Levers (If altitude permits)........................... IDLE APU......................................................................... START Recirculation Button................................................ PUSH OUT Airspeed.................................................................. MONITOR Monitor airspeed for any abnormal indication. If necessary perform the Unreliable Airspeed procedure. ITT........................................................................... MONITOR NOTE: If the ITT is still increasing even with the thrust levers in idle: Affected Engine.................................................... Shutdown If engine is shutdown or flames-out, restart the engine (refer to Quick Reference Handbook) once it has cooled down. If engine fails to start, repeated attempts should be made immediately. NOTE: A successful start may not be possible until the airplane is clear of the volcanic ash/dust, and the airspeed and altitude is within the airstart envelope. The engines may accelerate slowly to idle at high altitudes and this could be interpreted as a failure to start or as an engine malfunction.

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After exiting the area of volcanic ash/dust cloud and with the engine(s) restarted, restore systems to normal operation. Inform ATC of the encounter.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

SANDSTORM OPERATION A Sandstorm Operation is characterized when the airplane: – Flies through a sandstorm. – Lands or takes off during a sandstorm. – Operates on ground (towing, taxiing, parking) during a sandstorm. – Operates the APU or the Packs in during a sandstorm. In many deserts, the prevailing wind blows steadily from one cardinal direction for most of the year, and eventually switches to another direction for the remaining months. The equinoctial gales raise huge sandstorms that rise to several thousand feet and may last for several days. Gales and sandstorms in the winter months may be very cold. Desert winds can be very destructive to large and relatively light items attached to the airplane, such as antennas and cover caps. Especially in the deserts, dust and sand represent serious danger to equipment, since it is almost impossible to avoid particles settling on moving parts. Sand mixed with oil forms an abrasive and corrosive paste. Therefore, fuselage areas must be routinely checked and cleaned to prevent an undesirable OEW increase and payload reduction. Landing gear and flaps/slats are critical items for sand accumulation. Static electricity is also relevant and poses a danger in the desert. Poor grounding conditions may cause fire and damage circuit boards and other electronic equipment. Sandstorms are difficult to forecast and are likely to occur and stop suddenly.

AOM-1502-003

During a severe sandstorm, sand permeates everything and compromises visibility, which may become as low as 30 ft in the worst cases. Besides, blowing sand damages the wings leading edges and other airplane moving parts, especially the engine intakes. Rubber components such as gaskets and seals may become fragile and oil leaks may be more frequent. The effects of a sandstorm are very similar to those identified for Volcanic Ash. CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

If a sandstorm occurs when the airplane is on ground, with the applicable protective covers installed, and if there is no dust or sand behind the covers, it is not necessary to inspect the respective components or systems, as described in the Airplane Maintenance Manual. The critical items to be considered after the airplane has been exposed to a sandstorm are: – Airplane external cleaning – Airplane structure – External lights and sensors – Flight control system (actuators, tracks, rollers and cables) – Forward and middle avionics compartments – Forward and after cargo compartments – Airplane interior – Fuel system – APU – Air management system – Hydraulic system – Engines

CRITICAL AIRPLANE SYSTEMS AVIONICS It is recommended to protect computers from exposure to sand or dust by using plastic bags. Compressed air can be used to clean keyboards and other computer systems components. Keep the Air Data Smart Probes (ADSP) protected whenever possible to avoid contamination. During airplane inspection give special attention to the probes and contact the maintenance team if necessary. ENGINE

The fan by itself separates a significant amount of sand and dust away CONTINUED...

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In the event of a sandstorm occurs, it is not recommended to increase thrust. Sand or dust entering the engines with high airspeed will cause damage to internal components and affect the engines performance.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

from the compressor via the bypass duct, but high abrasive particles will strike the spinner, fan blades, vanes and splitter, leading to erosion of these items. Solid particles that are not separated through the fan will enter the compressor chamber, strike the compressor blades or vanes, leading to erosion of these items. Sand or dust under entering the engines will be under high temperatures, with potential to melt and choke the airflow, causing a backpressure increase and consequently decreasing the engines performance. Besides, if damaged or choked, the fuel injectors might lead to an engine shutoff. Exposure to sandstorms may lead the airfoils to change shape over time and therefore their aerodynamic efficiency will drop. Fan blade deterioration will also reduce thrust, since about 3/5 of an engine’s total thrust is generated through the FAN. Thus, when regularly operating in sandstorm condition, is recommended to wash the engines frequently to prevent a buildup of sand and dust. This will help minimize the possibility of inlet air and lubricating oil contamination and permit normal engine cooling. Active monitoring of the engines performance trends is also very important. POWER PLANT Considering operations of high bypass turbofan engines in desert environments, high concentrations of dust and sand in the airflow are the most impacting factors. Both sand and dust are considered erosive FOD that can significantly reduce the lifetime of all of the engines’ moving parts. AIR MANAGEMENT SYSTEM

AOM-1502-003

Bleed air comes from the engines and APU, passes through valves, ducts, filters, heat exchangers, turbines and electronic components, to supply air to the Air Conditioning, Pressurization and Anti-Ice systems. If the air ingested by the engines is humid and/or contaminated with dust and/or sand, it may damage AMS components and demand more frequent maintenance actions to prevent failures.

CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

SERVICING PROCEDURES If the airport has records of sandstorm occurrences, the airplane and fuel vehicles have to be well secured on ground at all the times to avoid damage. Securing of vehicles and equipment should be accomplished in accordance with appropriate procedures specified in the respective maintenance manuals. When cleaning any surface of the airplane contaminated with dust or sand, do not rub the surface. Dust and sand are very abrasive. In order to prevent accumulation of dust and sand, covers and shields must be properly installed to ensure a good fit. In addition to the normal servicing requirements and procedures referred in the AMM give special attention to the following: – When practical, position the airplane heading into the wind. – Maintain full engine oil tank to provide maximum heat absorption capability and help prevent excessive oil temperatures. – Prior to servicing ensure that filler openings and caps are clean before opening and closing servicing caps. Clean up fluid spills as they occur during servicing. – Verify that all engine inlet air ducts are free of sand. Use a lint-free cloth to remove any accumulation.

OPERATIONAL PROCEDURES PRE-FLIGHT INSPECTION Verify that no accumulation of sand exists in the engines inlet. Use a lint-free cloth to remove any accumulated sand. POWER UP – If available, prefer using a GPU for the airplane power up. – Minimize thrust for crossbleed starts. – Apply thrust just high enough for adequate manifold pressure.

TAXI CONTINUED...

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– Consider location for minimum FOD ingestion prior to crossbleed start.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

– Avoid engine overhanging unpaved surfaces. – If possible, leave engines at idle. – Minimize thrust assist from outboard engine in 180° turn, particularly if outboard engine overhangs unpaved surfaces. – Minimize breakaway thrust. – If possible, apply less than 40% N1. – Minimize taxi thrust. – Avoid allowing airplane to come to complete stop. – Avoid taxing closely behind other airplane where FOD may be blown. TAKEOFF – If possible, accomplish rolling takeoffs. Initial 30 KIAS taxi speed before applying thrust eliminates vortices formed at typical takeoff thrust settings. – Whenever possible, take off with FLAP 4 in order to reduce the airplane ground run and the engines sand/dust ingestion. – If allowed, extend the flaps shortly before initiating the takeoff procedure. This will reduce sand/dust accumulation on the flap/slats mechanisms. – Minimize breakaway thrust. – Use derated thrust settings whenever practical. This will help reduce the engines degradation. IN-FLIGHT – Avoid airborne sand whenever possible. – Consider reducing thrust to maintain ITT as low as possible. LANDING AND TAXING – Avoid using reverse thrust on dry runways.

AOM-1502-003

ENGINE SHUTDOWN If ground power is supplied to the airplane after engine shutdown, turn off all electrical equipment which is not required. This practice will CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

reduce the heat generated unnecessarily and will substantially prolong the service life of the equipment. AFTER SHUTDOWN – Install covers and shields. – Inspect for evidence of fluid leaks that might accumulate sand. – Clean the area appropriately and try to eliminate source of fluid leak.

EXTERNAL PNEUMATIC POWER SOURCE AND AIR CONDITIONING GROUND CART UTILIZATION The contaminated air ingested by the engines can result in malfunctions and operational problems due to degradation or malfunction of AMS components. Therefore, when an external pneumatic power source or an air conditioning ground cart is available, it is recommended to use these alternative sources to power up the engines or to condition the cabin temperature following the Ground Servicing section of this manual. The external pneumatic power source provides pressurized air that is used to power up the engines, eliminating the need to keep APU or engines running during servicing and reducing the demand for bleed air.

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The air conditioning ground cart provides clean, pressurized and cool air that is used to maintain the cabin air temperature at the desired level without using the PACKs. It also reduces the use of the APU and bleed air demand during servicing.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

COMMUNICATION MANAGEMENT FUNCTION OPERATION Specific operational procedures are required for the ACARS function use in accordance with CFR 14, Part 25, Subpart G - Operating Limitations and Information, § 25.1529,§ 25.1581, § 25.1583 and § 25.1585.

AOM-1502-003

DO-296 - Safety Requirements for Aeronautical Operational Control (AOC) Datalink Messages provides a guideline for hazard identification and risk reduction strategies related to ACARS operation.

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

ALTIMETERS MISCOMPARE TOLERANCES The Air Data System (ADS) relies on total of four Air Data Smart Probes (ADSPs) and two Total Air Temperature probes (TATs) to determine air total pressure, static pressure and total temperature. Three Air Data Applications (ADAs) compute these informations to provide air data to PFDs and other airplane systems. IESS (Integrated Electronic Standby System) performs both the functions of computing air information and presenting air data to flight crew. There are four ADS, which interact with flight crew. In normal operation, ADS 1 provides information to captain’s PFD, ADS 2 provides information to co-pilot’s PFD and ADS 3 is the backup source for both PFDs whereas ADS 4 is the IESS. Differences between pilot and co-pilot altitude readings may occur due to a number of reasons. Altitude, airspeed, airplane configuration and the ADSPs locations influence the altitude reading miscompare. As long as the miscompare is within a certain tolerance, it is acceptable. To verify if altimeter difference is within tolerance, the flight crew should proceed as follows: Altitude.................................................................... STABILIZE Maintain variation within ± 50 ft. Air Speed................................................................ STABILIZE Maintain variation within ± 5 kt.

AOM-1502-003

Wait a minimum of 15 s in straight and leveled flight, preferably with Autopilot engaged, to compare the difference between altitudes using the following table:

CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

MAXIMUM DIFFERENCE BETWEEN ALTITUDES [1] ADS 1 to ADS 2 ADS 1 to ADS 3/IESS [2] ADS 2 to ADS 3/IESS [3] 50 ft 120 ft 180 ft

AIRPLANE ALTITUDE

-2000 ft up to 10000 ft 10000 ft up to 20000 ft 20000 ft up to 41000 ft

1. These are comparative, not absolute values. 2. Message ADS 3 (4) SLIPCOMP FAIL must not be displayed. 3. ADS 3 and IESS use the same pressure sensors. Comparison between them is not applicable.

If a difference above the tolerance is noticed, report to the maintenance personnel.

PERFORMANCE BASED NAVIGATION INTRODUCTION

!Pre-mod MAU load 27.1

The material contain herein is a guidance to perform PBN operation. It does not consider AC-90-101 or AMC-20-26 which deal with RNP AR operation. For RNP AR operation, refer to GP-3801 – RNP AR Operation. "

In addition to the guidance of this section, the operator must continue to ensure they comply with the general operating requirements; checking Notices to Airmen (NOTAMS), availability of Navigational Aids (NAVAID), airworthiness of airplane systems, and flight crew qualification.

NAVIGATION DATA VALIDATION

NOTE: If the AIRAC cycle will change during the flight, the locations of the waypoints used to define routes and procedures must be verified with current navigational charts. CONTINUED...

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The navigation database must be obtained by a supplier complying with AC 20-153 or equivalent and is expected to be current for the duration of the flight.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

GENERAL GUIDANCE While operating on RNP segments, pilots are encouraged to use flight director and/or autopilot in lateral navigation mode and vertical navigation mode. RNP approach procedures require flight crew monitoring of lateral and vertical track deviations on the PFD to ensure the airplane remains within the bounds defined by the procedure. Since the lateral scale and CDI are automatically changed by the RNP value set on FMS, pilots must ensure the RNP set is suitable for each of the various segments of the procedure. All pilots are expected to maintain centerlines, as depicted by onboard lateral deviation indicators and/or flight guidance during all RNP operations, unless authorized to deviate by ATC or under emergency conditions. For normal operations, cross-track error/deviation should be limited to half the navigation accuracy associated with the procedure (i.e., 0.5 NM for RNP 1). Brief deviations from this standard (e.g., overshoots or undershoots) during and immediately after turns, up to a maximum of one times the navigation accuracy (i.e., 1.0 NM for RNP 1), are allowable.

PRIOR TO FLIGHT Airplane minimum configuration........................... CHECK Check the airplane configuration complies with the applicable list below:

!Pre-mod MAU load 27.1

– 1 FMS. – 1 GPS. – 1 IRU. – 1 MCDU. – 4 Display units. – 2 RVSM Compliant Air Data Systems. – 1 Flight Director. – 1 VOR. AOM-1502-003

" CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED !Pre-mod MAU load 27.1

FMS Position........................................................ INITIALIZE "

Flight Plan............................................................. ACTIVATE Procedure ............................................................ CONFIRM Crew must confirm that the correct procedure has been selected by comparing the FMS waypoints with the approach chart, and ensure the reasonableness of track angles and distances, and other parameters that can be altered, such as altitude and speed constraints. NOTE: – The procedure may subsequently be modified through the insertion or deletion of specific waypoints in response to ATC clearances. The manual entry or creation of new waypoints, by manual entry of latitude and longitude or rho/theta values is not permitted. Additionally, pilots must not change any database waypoint type from a fly-by to a fly-over or vice versa. – Differences of 3° or less between navigation information on the charts and the PFDs heading are acceptable. After an RTO, the performance init must be checked. RNP predictive performance capability................ CONFIRM AVAILABLE The performance capability may be checked from an offline station, or with the airplane own capability. If using the airplane capability, insert the appropriate GPS NOTAMS to allow for an accurate predictive RAIM. NOTAM NAVAIDS................................................. INSERT Insert the appropriate NAVAIDS in accordance with NOTAMs.

Verify that the Navigation Data Base (NDB) is current for the duration of the flight. CONTINUED...

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NOTE: For RNP 1 with approval based on DME/DME, critical DME facilities (listed on the approach chart) must be operative. NAV Database...................................................... VERIFY CURRENCY

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

Takeoff Page......................................................... SET/CONFIRM PFD NAV Source.................................................. SELECT FMS Speed Selector Knob............................................ AS REQUIRED LNAV..................................................................... AS REQUIRED VNAV.................................................................... AS REQUIRED

DEPARTURE, ROUTE AND ARRIVAL Navigation Sensor (Progress Page on MCDU).... CHECK If DME-DME or IRS is the current navigation sensor, a manual runway position update needs to be performed by the crew. Ensure the runway for departure is selected on the FMS and use the LSK 2R on the POS INIT page to update FMS position when aligned for departure. Track deviation...................................................... MONITOR The deviation can be monitored through the lateral deviation scale on CDI and PFD or cross track error on MFD MAP page.

AOM-1502-003

Lateral deviation should not exceed half of the RNP value. Slight deviations up to 1xRNP during or immediately after turns are allowable.

CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

MFD

FMS1

36 O

ZUN 55.6 NM 23 MIN

5

PUMPS

N

33

3O

GUP44

15 SAT ^C 25 TAT ^C 3OO TAS KTS

DME1 LAX 65.3 NM 2O MIN

3

6

GUP

5 A WX/R/T S STAB TGT LX

1OO

1OO

1 EM170AOM980132B.DGN

WEATHER

E

W

ZUN

O.O5 L

PROGRESS

NEXT DEST

WPT ZUN GUP

DIST ETE FUEL 55.6 O1+32 11.4 95 O2+52 1O.4

1 - Cross Track Error. NOTE: If ATC issues a heading assignment taking the airplane off a procedure, the crew should not modify the primary flight plan, until a clearance is received to rejoin the route or the controller confirms a new route clearance. The specified accuracy requirement does not apply when the airplane is not on the published RNP 1 procedure.

APPROACH Track deviation...................................................... MONITOR The deviation can be monitored through the vertical and lateral scales and CDI on PFD.

Lateral deviation must not exceed the half RNP value at any time during the approach. CONTINUED...

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Vertical deviation must not exceed 100 ft high or 50 ft low during the approach segment.

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL ...CONTINUED

If the deviation exceeds the limits perform a missed approach.

MAIN PANEL

SPD T

LNAV ALT

AP AT

21O 24O

O6OOO 2O

2O

1O

1O

731O

4

VTA

2 1

1 2 1O 9

8O

776O

17O

1O

1O

2O

2O

4 RA

1O13 HPA

2OO

HDG

DTK

21O

3O2

21O

FMS2 YOCUL

S

21

2 DME2 29.7 NM MIN RNP 1.OO TERM

3O

12

W

3

E

33

N

3

VHF1 118 5O 119 25

O O

24

15

2.O NM O MIN

1 2

75OO

FS

18O

GSPD 235 KT

1

EM170AOM980131B.DGN

19O

8OOO

NAV2 116.2O 114.8O

6

1 - Vertical deviation scale. 2 - Lateral deviation scale.

AOM-1502-003

3 - CDI Lateral deviation scale. In the horizontal deviation scale, full-scale deflection (two dots) corresponds to 1xRNP lateral (both on the CDI and PFD). CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

The vertical deviation scale is 250 ft/Dot on terminal. Upon reaching 2 NM from the FAF, the scale changes to 75 ft/Dot during approach. At the IAF: Altimeters.............................................................. SET Obtain and set a current, local altimeter setting. If a current, local altimeter setting is not available, do not start the approach. NOTE: The use of a remote altimeter setting is not authorized. Altimeters.............................................................. COMPARE When crossing a known waypoint on the approach procedure, crosscheck the primary barometric altimeters against one another. The difference between the altimeter indications must not exceed 100 ft. If the difference exceeds 100 ft, abandon the approach and begin a missed approach. 2 NM before the FAF: APPR Annunciation.............................................. CHECK

CONTINUED...

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The annunciation indicates that the EPU value is inside the RNP value and the GPS is functional.

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL ...CONTINUED

PFD

HDG

DTK

21O

3O2

21O

FMS2 JEXOT

S

2.O NM

DME2 29.7 NM MIN RNP O.3O APPR

3O

12

W

1

E

33 N

3

VHF1 118 5O 119 25

O O

24

15

O MIN

21

NAV2 116.2O 114.8O

EM170AOM980133B.DGN

GSPD 235 KT

6

1 - APPR Annunciation.

MISSED APPROACH TO/GA................................................................... PRESS NOTE: The missed approach prompt is automatically activated and displayed on the MCDU MISSED APPROACH page after passing the initial approach fix (IAF) without pressing TO/GA button. The missed approach prompt only activates the lateral part of the procedure, so the pilot is still responsible for selecting the vertical navigation mode. !Airplanes not equipped with Auto LNAV, Pre-mod MAU load 27.1

AOM-1502-003

LNAV..................................................................... SELECT

CONTINUED...

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AIRPLANE OPERATIONS MANUAL

...CONTINUED

The pilot flying must immediately re-select LNAV after the TO/GA and follow the flight director’s guidance to ensure airplane compliance with the procedure’s track. "

!170/175 models, Pre-Mod MAU load 25.1.0.1

NOTE: When a go around is initiated (TO/GA button is pressed) far away and GA mode on FMA is not active prior to 2 NM from the FAF, the missed approach procedure will not be automatically activated. To activate the missed approach in the flight plan, the TO/GA button must be pressed again when within 2 NM of the FAF. After pressing TO/GA a second time, the NAV button must also be pressed again to re-engage LNAV, guaranteeing the missed approach path will be correctly followed. "

ADVANCED FEATURES - VGP The information below applies to the use of VGP during approach operations. TEMPERATURE COMPENSATION Due to the effect of nonstandard temperature on VGP operations, temperature limits may apply to some procedures (temperature limits presented in the notes section of the chart). By using the temperature compensation function it is possible to disregard those limits, provided the function is activated prior to commencing the approach. Temperature compensation (if applicable)........... ACTIVATE The temperature value used should be the current, local temperature for the airport and runway of intended landing. NOTE: Prior to applying temperature compensation, the flight crew must coordinate its use with ATC. Failure to do so could result in a loss of vertical separation with other traffic. LOSS OF VGP

CONTINUED...

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REVISION 21

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Should any system failure affect the VGP functionality, if a VNAV MDA (DA) is in use, the crew must immediately revert to LNAV only MDA (DA) or perform a go around.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

ADVANCED FEATURES - RF LEGS Radius to Fix Legs (RF Legs) are turn segments with constant radius between to fixes. RF legs may appear on RNAV/RNP procedures during the initial, intermediate and missed approach segments of instrument approaches, RNP departure procedures and RNP STARS. RF legs are not used in the final approach segment. Additional requirements for RF legs are indicated in the charts, in the notes section, or at the applicable initial approach fix for instrument approaches. Common additional requirements are airspeed restrictions during the legs that must be complied with.

ABNORMAL PROCEDURES In case of loss of RNP capability, alternate airports or alternate non-RNP procedures at the destination airport must be available. LOSS OF SIGNAL IN SPACE If at any time GNSS signal is lost, it will be annunciated to the crew as a dual GPS failure (MCDU scratchpad messages), and the DGRAD PFD annunciation will be displayed. DEGRADED NAVIGATION

AOM-1502-003

The navigation will be degraded whenever the EPU value is greater than RNP or if the navigation sensors required for the approach are not available on final approach (2 NM before the FAF).

CONTINUED...

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REVISION 21

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

PFD

GSPD

HDG

3OO KT

33O

MAG1

36 O 1O

PUMPS

N

FMS1

33

CHR O7:12

3

GUP44

ZUN

55.6 NM

RNP 1.1O

GUP

DGRAD ZUN

1

1OO

VHF1 118 5O 119 25

NAV1 119 1O 119 15

O.4 R

EM170AOM980135C.DGN

23 MIN

1 - DGRAD Annunciation. The UNABLE RNP, GPS RAIM ABOVE LIMIT and GPS RAIM UNAVAILABLE scratchpad message will also be displayed. If the DGRAD annunciation is displayed: Select the non-affected FMS. For single FMS installations or in case of both FMS are affected, use the procedures from the following table:

Non-RNP Terminal or En-route (including B-RNAV) P-RNAV

Required Action Crosscheck FMS data with raw data from VOR, DME, and NDB. De-select sensor causing error, if detectable. Contact ATC, advise inability to continue P-RNAV. CONTINUED...

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Operation

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

Operation RNP Terminal, En-route, Remote Non-RNP (excluding GPS required) Approach RNP APCH, RNP 0.3 and GPS required Approach Non-RNP Remote

Required Action Contact ATC and advise inability to continue RNP operations. Use alternate source (VOR, NDB or visual references) if available. If not, declare Missed Approach. If not visual, declare Missed Approach. Crosscheck FMS data with raw data from GPS, IRS. De-select error causing sensor, if detectable.

NOTE: P-RNAV can also be read as RNAV 1. B-RNAV can also be read as RNAV 5. FMS 1 (2) FAILURE Select the cross-side FMS. In case both FMS are unavailable, use the procedures from the following table: Operation Non-RNP Terminal or En-route B-RNAV, P-RNAV, or RNP operations Non-RNP (excluding GPS required) Approach RNP APCH, RNP 0.3 or GPS required approach Remote Operations

Required Action Use alternate source (VOR, NDB, DME). Contact ATC and declare inability to continue B-RNAV, P-RNAV, or RNP operations. Use alternate source, if available (VOR, NDB or visual references). If not available, declare missed approach. If not visual, declare Missed Approach. Contact ATC and declare loss of long range navigation capability.

AOM-1502-003

NOTE: P-RNAV can also be read as RNAV 1.

CONTINUED...

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REVISION 21

Suppl Procedures - Flight Instruments

Page 13

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

B-RNAV can also be read as RNAV 5.

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REVISION 21

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END

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

!Pre-mod MAU load 27.1

PRNAV OPERATIONS The material contained herein is a guidance material prepared based on TGL-10. NOTE: To fly into an airspace designated as RNAV 1, is necessary to comply with the deltas from TGL No. 10 to the criteria of the RNAV 1 navigation specification. The P-RNAV operations satisfies a required track keeping accuracy of ±1 NM for at least 95% of the flight time, and the automatic selection, verification and, where appropriate, de-selection of navaids. P-RNAV operations determine airplane position on the horizontal plane using inputs from the following types of positioning sensors: – Distance Measurement Equipment (DME) giving measurements from two or more ground station (DME/DME). – VHF Omni-directional Range (VOR) with a co-located DME (VOR/DME), where it is identified as meeting the requirements of the procedures. – Global Navigation Satellite System (GNSS) GPS or GALILEO. – Inertial Reference System (IRS), with automatic updating from suitable radio based navigation equipment. P-RNAV is used for departures, arrivals and approaches down to (FAWP). The final APPR segment down to the RWY threshold and the associated missed approach are not covered by P-RNAV procedures. NOTE: The FMS VNAV and the FMS SPEED are not required for P-RNAV.

LIMITATIONS MINIMUM EQUIPMENT LIST – 1 FMS. FMS 1 (2) FAIL displayed on the EICAS. – 1 FD.

AOM-1502-003

FD FAULT displayed on the EICAS. – 1 DME. CONTINUED...

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REVISION 21

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

– 1 VOR. – 1 GPS. – 1 MCDU. NOTE: For procedures specified in the Aeronautical Information Publication (AIP) as requiring dual P-RNAV, both FMS must be operative at dispatch. If an FMS in-flight failure occurs, the procedure must be discontinued. The sensors status can be checked in FMS MAINTENANCE PAGE.

FMS 1 MAINTENANCE

2/3

FAILED SENSORS IRS 1

IRS 2

DME 1

DME 2

1R

2L

2R

3L

3R

4L

4R

5L

5R

6L

SETUP

SENSOR HISTORY

6R

EM170AOM030029A.DGN

1L

FMS MAINTENANCE PAGE 2/3

GENERAL LIMITATIONS

– Although the magnetic heading and track angle provided by the IRS are available up to 73° latitude north and 60° latitude south, the FMS uses the IRS as sensor in the range 72° 30.0’ latitude north and 59° 30.0’ latitude south. The P-RNAV operation is prohibited outside of the IRS FMS usable range. CONTINUED...

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– If GPS RAIM is annunciated as not available during any phase of flight, the pilot must monitor FMS guidance data and crosscheck with raw data from an alternate source (i.e. VOR, DME, or IRS).

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

– The RNP-RNAV airworthiness approval has not accounted for database accuracy or compatibility as defined per FAA AC 20-153. – P-RNAV requires the use of the Flight Director. – Prior to flight using FMS for IFR navigation any appropriate ground facilities that are utilized by the procedures to be flown must be verified as operational using an approved method. – The Approved FMS Pilot’s Operating Manual or other approved manual must be available to the flight crew. The Pilot’s Manual must match the FMS software version installed in the airplane. – The creation of new waypoints by manual entry into the RNAV system by the flight crew is not permitted as it would invalidate the affected P-RNAV procedure. Route modifications in the terminal area may take the form of radar headings or ‘direct to’ clearances and the flight crew must be capable of reacting in a timely fashion. This may include the insertion in the flight plan of waypoints loaded from the database. !!EMBRAER 170 Models

– Honeywell Primus Epic FMS Database version E170-C6 or later approved version must be installed. ""

– The FMS software version NZ7.01 or later approved version must be installed. – P-RNAV operations with FMS software v7.0, v7.01 or v7.02 are prohibited. – When a GPS Only Approach is planned (GPS only in title or GPS required by operational rules), prior to dispatch, the crew is required to verify that the predictive RAIM at the destination ETA is within the approach criteria. This information (RAIM AVAILABLE), is displayed on the PREDICTIVE RAIM page on the MCDU.

AOM-1502-003

– The FMS Disable selection on MCDU Radio Tune NAV page is prohibited. – The pilot must ensure that the displayed guidance data from non-usable stations is not used for navigation purposes by the flight crew. The NOTAM function in the FMS does not always inhibit tuning of a NOTAM selected station by the FMS when in CONTINUED...

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REVISION 21

Suppl Procedures - Flight Instruments

Page 17

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

AUTO tune mode. Note that the FMS will not use NOTAM selected station data for FMS position determination.

NORMAL PROCEDURES PRIOR TO FLIGHT Verify NOTAM for the availability of the intended P-RNAV procedure. Verify also if any navaid identified in the AIP as critical for the intended P-RNAV procedure is unavailable. FMS Identification................................................. VERIFY NAV DB FMS Position........................................................ INITIALIZE Flight Plan............................................................. ACTIVATE At system initialization, the flight crew must confirm that the navigation database is current and verify that the aircraft position has been entered correctly. The active flight plan should be checked by comparing the charts, SID or other applicable documents, with the MFD MAP display and the MCDU. This includes confirmation of the waypoint sequence, reasonableness of track angles and distances, any altitude or speed constraints, and, where possible, which waypoints are fly-by and which are fly-over. If required by a procedure, a check will need to be made to confirm that updating will use a specific navigation aid(s), or to confirm exclusion of a specific navigation aid. A procedure shall not be used if doubt exists as to the validity of the procedure in the navigation database. FMS AUTOTUNE MODE...................................... ON PFD NAVSource on PF Side................................ SELECT FMS Contigency Procedure.......................................... REVIEW AFTER TAKEOFF LNAV..................................................................... SELECT

ARRIVAL Verify NOTAM for the availability of the intended P-RNAV procedure. Verify also if any navaid identified in the AIP as critical for the intended P-RNAV procedure is unavailable. CONTINUED...

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The LNAV mode can command bank angles up to 30°, which is above the maximum allowable bank angle for OEI conditions below the level OFF. Do not engage the LNAV mode until the airplane is above the level off if the departure procedure may cause the airplane to bank over the 15° limit.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

Flight Plan............................................................. LOAD At the desired flight plan loading, the flight crew must confirm that the navigation database is current and verify that the aircraft position has been entered correctly. The loaded procedure must be checked by comparing the charts or other applicable documents with the MFD MAP display and the MCDU. This includes confirmation of the waypoint sequence, reasonableness of track angles and distances, any altitude or speed constraints, and, where possible, which waypoints are fly-by and which are fly-over. If required by a procedure, a check will need to be made to confirm that updating will use a specific navigation aid(s), or to confirm exclusion of a specific navigation aid. A procedure shall not be used if doubt exists as to the validity of the procedure in the navigation database. PFD NAV Source on PF Side.............................. SELECT FMS Contigency Procedure.......................................... REVIEW NOTE: During the procedure and where feasible, flight progress should be monitored for navigational reasonableness, by cross-checks, with conventional navigation aids using the primary displays in conjunction with the MCDU.

EMERGENCY AND ABNORMAL PROCEDURES NAVIGATION DEGRADATION The navigation degradation is annunciated by: – The DGRAD annunciator on the PFD. – The DEAD REACKONING scratchpad message. – The UNABLE RNP scratchpad message. Non Affected FMS................................................ SELECT In case the procedure requires dual P-RNAV capability, single FMS installations failures or dual FMS failures in dual FMS configuration, accomplish the contingency procedure.

AOM-1502-003

FMS 1 (2) FAIL Non Affected FMS................................................ SELECT In case the procedure requires dual P-RNAV capability, single FMS installations failures or dual FMS failures in dual FMS configuration, accomplish the contingency procedure. CONTINUED...

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REVISION 21

Suppl Procedures - Flight Instruments

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

FD FAULT Non Affected Side................................................. SELECT AS NAVIGATION SOURCE In case of FD FAIL occurs, apply the P-RNAV contingency procedure. NOTE: A single channel FD loss is annunciated through the FD FAULT EICAS message. In the affected side, the FD cue comes out of view. "

FMS USAGE IN AREAS NOT COVERED BY WGS-84 OR NAD-83 DATUM BASIC STATEMENTS This procedure is to be used in cases when operating in areas not covered by coordinates method WGS – 84 or NAD-83 datum and the use of the FMS is desired. When applying this procedure by deselecting the GPS 1 and 2 on both MCDUs the FMS may be used normally as long as no DEGRADED message appears, meaning that the EPU (estimate position uncertainty) is meeting the required navigation performance for the flight phase. When the GPS is deselected an inscription DESEL is displayed confirming that the GPS is disabled.

POSITION INITIALIZATION The inertial component requires system initialization (entry of latitude and longitude). Initialization may take place either from a FMS from input that the crew manually enters via the MCDU, or automatically from the GPS. A pilot-entered position has priority over a position from a GPS. FLIGHTS ORIGINATING ON AREAS NOT COVERED AFTER AIRPLANE POWER UP If the airplane is at the same position it was on the last power down. LAST POS.............................................................. LOAD CONTINUED...

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AOM-1502-003

POS INIT page (from the NAV INDEX).................. SELECT

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

For other cases, set the proper position coordinate using the airport or the gate position. REF WPT................................................................ SET and LOAD POS SENSORS page............................................. SELECT On MCDU 1: GPS 1 (LSK 4L)...................................................... DISABLE – Press DELETE key – LINE SELECT on GPS 1 GPS 2 (LSK 5L)...................................................... DISABLE – Press DELETE key – LINE SELECT on GPS 2 On MCDU 2: GPS 1 (LSK 4L)...................................................... DISABLE – Press DELETE key – LINE SELECT on GPS 1 GPS 2 (LSK 5L)...................................................... DISABLE – Press DELETE key – LINE SELECT on GPS 2 DURING THRU FLIGHTS POS SENSORS page............................................. SELECT On MCDU 1: GPS 1 (LSK 4L)...................................................... DISABLE – Press DELETE key – LINE SELECT on GPS 1 GPS 2 (LSK 5L)...................................................... DISABLE – Press DELETE key – LINE SELECT on GPS 2 On MCDU 2: GPS 1 (LSK 4L)...................................................... DISABLE

AOM-1502-003

– Press DELETE key – LINE SELECT on GPS 1 GPS 2 (LSK 5L)...................................................... DISABLE CONTINUED...

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NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

– Press DELETE key – LINE SELECT on GPS 2 AFTER TAKEOFF AFTER TRANSITION ALTITUDE POS SENSORS page............................................. SELECT On MCDU 1: GPS 1 (LSK 4L)...................................................... ENABLE – Press DELETE key – LINE SELECT on GPS 1 GPS 2 (LSK 5L)...................................................... ENABLE – Press DELETE key – LINE SELECT on GPS 2 On MCDU 2: GPS 1 (LSK 4L)...................................................... ENABLE – Press DELETE key – LINE SELECT on GPS 1 GPS 2 (LSK 5L)...................................................... ENABLE – Press DELETE key – LINE SELECT on GPS 2 FLIGHTS APPROACHING TO AREAS NOT COVERED DESCENT PHASE AFTER TRANSITION LEVEL POS SENSORS page............................................. SELECT On MCDU 1: GPS 1 (LSK 4L)...................................................... DISABLE – Press DELETE key – LINE SELECT on GPS 1 GPS 2 (LSK 5L)...................................................... DISABLE – LINE SELECT on GPS 2 CONTINUED...

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REVISION 21

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– Press DELETE key

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

...CONTINUED

On MCDU 2: GPS 1 (LSK 4L)...................................................... DISABLE – Press DELETE key – LINE SELECT on GPS 1 GPS 2 (LSK 5L)...................................................... DISABLE – Press DELETE key – LINE SELECT on GPS 2

QFE OPERATION This procedure is accomplished when ATC altitude assignments are referenced to QFE altimeter settings. NOTE: Do not use VNAV below transition altitude/level. Altitudes in the navigation database are not referenced to QFE. Do not use FMS LNAV information in procedures that contain conditional waypoints. Use only raw data for navigation. Altimeters................................................................ SET Set altimeters to QFE when below transition altitude/level. Prior to descent: Pressurization Mode Selector................................. LFE CTRL LFE Selector........................................................... SET ZERO Perform a normal descent approach and landing procedures. After engines shutdown:

AOM-1502-003

Pressurization Mode Selector................................. AUTO

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REVISION 21

Suppl Procedures - Flight Instruments

Page 23

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

RVSM OPERATION The RVSM operation reduces the airplane minimum vertical separation from 2000 ft to 1000 ft between FL 290 and FL 410. Airworthiness approval alone, does not authorize the flight into the airspace for which a RVSM operational approval is required by an ICAO Regional Navigation Agreement.

NORMAL PROCEDURES EXTERNAL SAFETY INSPECTION NOSE SECTION Air Data Smart Probes......................................... NO DAMAGE OR OBSTRUCTION Particular attention should be paid to the condition of the pressure ports and to the marked area on the fuselage skin near each Air Data Smart Probe.

BEFORE TAKEOFF Altimeters.............................................................. SET TO THE AIRFIELD QNH Altitude Indications................................................ CHECK NOTE: – An alternative procedure using QFE may also be used; – The maximum difference between altimeters indication, and also, the maximum difference between field elevation and altimeters, should not exceed 23 m (75 ft).

CRUISE Be sure that all required equipment are in proper operating condition.

AOM-1502-003

Ensure that the airplane is flown at the cleared flight level and that ATC clearances are fully understood and followed. Do not depart from cleared flight level without a positive clearance from ATC except for a contingency or emergency situation. While changing flight levels, do not overshoot or undershoot the cleared flight level by more than 45 m (150 ft). CONTINUED...

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REVISION 20

RVSM OPERATION

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

The autopilot should be operative and engaged during level cruise, except for circumstances such as the need to re-trim the airplane or when it must be disengaged due to turbulence. When altitude difference between PFD 1 and PFD 2 exceeds 100 ft, select ADS 3 on the PFD that does not agree with IESS.

AFTER LANDING In case of failure or malfunction, the following information should be recorded when appropriate: – ADS 1, ADS 2, ADS 3 altimeter readings; – Altitude selector setting; – Baro Set value and Baro Set unit (INHG/HPA); – Flight Director used with the Autopilot to control the airplane and any differences when the other Flight Director was coupled; – Use of air data system reversion for fault diagnosis procedure;

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RVSM OPERATION

REVISION 20

AOM-1502-003

– The transponder selected to provide altitude information to ATC and any difference noted when an alternative transponder was selected.

AOM-1502-003

REVISION 21

Flight Patterns

80 Knots

EM170AOM980007E.DGN

THRUST SET ROTATE

V1

· GEAR UP · V2 +10 Knots

POSITIVE RATE

· CLIMB SEQUENCE · VNAV · RETRACT FLAPS ON SCHEDULE

ACCELERATION ALTITUDE

TAKEOFF − ALL ENGINES OPERATING

FLAP 0 · CLIMB SPEED · AFTER TAKEOFF CHECKLIST

AIRPLANE OPERATIONS MANUAL NORMAL PROCEDURES

FLIGHT PATTERNS

TAKEOFF

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3-95

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Flight Patterns

REVISION 21

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THRUST SET

80 kt

· GEAR UP · V2 + 10 kt

POSITIVE RATE

ROTATE

V1 AT 800 ft (NADP 1) OR 1500 ft (ICAO A) AFE · SELECT VNAV · MAINTAIN V2 + 10 to 20 kt UNTIL 3000 ft AFE · SET SPEED TARGET AS REQUIRED · RETRACT FLAPS ON SCHEDULE

AT 3000 AFE

NOISE ABATEMENT TAKEOFF NADP 1 / ICAO A

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

NOISE ABATEMENT TAKEOFF A EM170AOM980013E.DGN

AOM-1502-003

THRUST SET

80 kt

REVISION 21

Flight Patterns · GEAR UP · V2 + 10 kt

POSITIVE RATE

ROTATE

V1 AT 800 ft (NADP 2) OR 1000 ft (ICAO B) AFE · RETRACT FLAPS ON SCHEDULE · SET VNAV · MAINTAIN VFS + 10 to 20 kt UNTIL 3000 ft AFE

AT 3000 AFE · SET SPEED TARGET AS REQUIRED

NOISE ABATEMENT TAKEOFF NADP 2 / ICAO B

AIRPLANE OPERATIONS MANUAL NORMAL PROCEDURES

NOISE ABATEMENT TAKEOFF B

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3-95

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EM170AOM980020E.DGN

Page 4

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3-95

Flight Patterns

REVISION 21

AOM-1502-003

· GEAR DOWN · FLAPS 3

TURNING BASE

700 − 500 FT

· LANDING FLAPS · BEFORE LANDING CHECKLIST

BASE

30 SEC

· FLAPS 2

ABEAM THRESHOLD

1500 FT

2 nm

VISUAL APPROACH

· PUSH TO/GA SWITCH · GO AROUND THRUST · GO AROUND ATTITUDE · SET GO AROUND FLAPS · POSITIVE RATE / GEAR UP · COMPLETE GO AROUND PROCEDURE · AFTER TAKEOFF CHECKLIST

MISSED APPROACH

· FLAPS 1

ENTERING DOWNWIND

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

VISUAL APPROACH EM170AOM980009B.DGN

APPROACHING INTERCEPT HEADING

REVISION 21

Flight Patterns

· GEAR DOWN · FLAPS 3

ONE DOT

· PRESELECT GO AROUND HEADING

LOCALIZER CAPTURE

· ARM APP MODE · INTERCEPT WITH FLAPS 2 FIX

· SET LANDING FLAPS · SET GO AROUND ALTITUDE · BEFORE LANDING CHECKLIST

GLIDE SLOPE INTERCEPT

· COMPLETE APPROACH CHECKLIST

APPROACHING FIELD · APPROPRIATE VERTICAL AND LATERAL MODES

· PUSH TO/GA SWITCH · GO AROUND THRUST · GO AROUND ATTITUDE · SET GO AROUND FLAPS · POSITIVE RATE / GEAR UP · COMPLETE GO AROUND PROCEDURE · AFTER TAKEOFF CHECKLIST

MISSED APPROACH

PRECISION APPROACH (ILS)

EM170AOM980011C.DGN

AOM-1502-003

AIRPLANE OPERATIONS MANUAL NORMAL PROCEDURES

PRECISION APPROACH (ILS)

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Flight Patterns

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REVISION 21

AOM-1502-003

APPROACHING FAF · SET LANDING FLAPS · SET MDA (DA) OR GO AROUND ALTITUDE (VGP) ON ALTITUDE PRE SELECTOR · BEFORE LANDING CHECKLIST · FOR GPS APPROACH CHECK APPR ANNUNCIATION

RUNWAY INSIGHT · INTERCEPT LANDING PROFILE · SET GO AROUND ALTITUDE (NON − VGP)

· PERFORM A PRECISION − LIKE APPROACH

DESCENDING TO MDA

· COMPLETE APPROACH CHECKLIST

· GEAR DOWN · FLAPS 3

FAF

INBOUND

· INTERCEPT WITH FLAPS 2

APPROACHING INTERCEPT HEADING

· PUSH TO/GA SWITCH · GO AROUND THRUST · GO AROUND ATTITUDE · SET GO AROUND FLAPS · POSITIVE RATE / GEAR UP · COMPLETE GO AROUND PROCEDURE · AFTER TAKEOFF CHECKLIST

MISSED APPROACH

· APPROPRIATE VERTICAL AND LATERAL MODES

APPROACHING FIELD

NON−PRECISION/GPS/RNAV APPROACH

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

NON−PRECISION APPROACH EM170AOM980010E.DGN

AOM-1502-003

REVISION 21

INITIAL APPROACH CONFIGURATION

· GEAR DOWN · FLAPS 3 · SET CIRCLING MINIMUMS

Flight Patterns · START CHRONOMETER · MAINTAIN VISUAL REFERENCES

ABEAM THRESHOLD

· LEVEL OFF AT CIRCLING ALTITUDE · PROCEED TO DOWNWIND LEG

RUNWAY INSIGHT

· LANDING FLAPS · BEFORE LANDING CHECKLIST · SET GO AROUND ALTITUDE

TURNING BASE

· INTERCEPT VISUAL PATH · AUTO PILOT DISCONNECTED

FINAL

· PUSH TO/GA SWITCH · GO AROUND THRUST · GO AROUND ATTITUDE · SET GO AROUND FLAPS · POSITIVE RATE / GEAR UP · COMPLETE GO AROUND PROCEDURE · AFTER TAKEOFF CHECKLIST

MISSED APPROACH

CIRCLING APPROACH

AIRPLANE OPERATIONS MANUAL NORMAL PROCEDURES

CIRCLING APPROACH

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EM170AOM980012D.DGN

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Flight Patterns

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REVISION 21

AOM-1502-003

EM170AOM030023A.DGN

· GEAR UP · FLAPS 2 · SET CIRCLING MINIMUMS

INITIAL APPROACH CONFIGURATION

· START CHRONOMETER · MAINTAIN VISUAL REFERENCES

ABEAM THRESHOLD

· LEVEL OFF AT CIRCLING ALTITUDE · PROCEED TO DOWNWIND LEG

RUNWAY INSIGHT

· GEAR DOWN · FLAPS 3

TURNING BASE

· FLAPS 5 · INTERCEPT VISUAL PATH · AUTOPILOT DISCONNECTED · SET RUDDER TRIM TO NEUTRAL · BEFORE LANDING CHECKLIST

FINAL

· PUSH TO/GA SWITCH · GO AROUND THRUST · GO AROUND ATTITUDE · SET GO AROUND FLAPS · POSITIVE RATE / GEAR UP · COMPLETE GO AROUND PROCEDURE · AFTER TAKEOFF CHECKLIST

MISSED APPROACH

ONE ENGINE INOPERATIVE − CIRCLING APPROACH

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

ONE ENGINE INOPERATIVE - CIRCLING APPROACH

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

CAT II ENGAGEMENT LOGIC The Primus Epic integrated Avionics has a CAT II logic which is automatically activated whenever the RA/BARO minimums selector knob is set to RA position. A green APPR 2 annunciator indicates the correct setting and a white or amber APPR 1 ONLY annunciator indicates an incorrect setting. The green APPR 2 annunciator is displayed in the Autopilot Approach Status Annunciator above each FMA. NOTE: Although the radio altitude setting may be adjusted down to 80 ft, if requested by an ILS CAT II Approved Chart, the Decision Height (DH) is limited to 100 ft above ground level.

CAT II CONDITIONS OF OPERATION CAT II operation is allowed only with the green APPR 2 annunciator enabled. To obtain a green APPR 2 annunciator the following conditions must be met: – Radio altitude below 1500 ft. – SLAT/FLAP 5. – NAV 1 on pilot’s side and NAV 2 on copilot’s side, both NAVs tuned to the same LOC frequency. – An active approach GS/LOC mode selected. Both courses set to same value. – Both Flight Directors operational. – Attitude and Heading valid on both PFDs. – Glide slope and Localizer deviation valid on both PFDs. – No reversions (IRS and ADC) modes selected on both PFDs. – Valid Airspeed and Baro Altitude on both PFDs. – No comparison monitors are tripped (FPA, Attitude, Heading, Airspeed, Baro Altitude, Localizer, Glide slope and Radio altitude) on both PFDs. – No back course selected.

AOM-1502-003

– The EICAS message APPR 2 NOT AVAIL not presented. – RA/BARO Minimums Selector knob set to RA. CONTINUED...

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REVISION 21

Suppl Procedures - Category II

Page 1

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

– Both Display Control Panels set to the same CAT II Decision Height. – No TCS Button pressed. NOTE: – If the CAT II Instrument Approach Landing chart does not authorize the use of RA, set the RA to OFF (setting minimums knob to 0 ft). In this case there is no EGPWS call outs “APPROACHING MINIMUMS” and “MINIMUMS, MINIMUMS”. – When the green APPR 2 annunciator is enabled, the localizer lateral deviation scale is expanded with the external limits representing the excessive deviation points. If one of these conditions is not met, the green APPR 2 annunciator will not appear. If the green APPR 2 annunciation is displayed and one of the following conditions is achieved, the amber APPR 1 ONLY annunciation will flash active characters inverse video for 5 s then steady in conjunction with the RA Minimum Selected Digital Readout: – No valid Radio Altitude displayed. – Airplane no longer APPR 2 capable. – Crew selects flaps position other than 5 below 800 ft. – EICAS message SLAT/FLAP LEVER DISAG displayed. – Either Minimums Selected Readouts change from RA to BARO.

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Suppl Procedures - Category II

REVISION 21

AOM-1502-003

– LOC frequency or inbound course mismatch.

AIRPLANE OPERATIONS MANUAL

NORMAL PROCEDURES

NORMAL PROCEDURES CAT II APPROACH APPROACH – Perform the Descent and Approach checklists. – Set approach speeds. – Set the RA/BARO Minimums Selector knob to RA and the CAT II DH minimum on both Display Control Panels. – Test Radio Altimeter if only one is available. – Select the same ILS frequency on both MCDU. NOTE: A minimum distance of 4 NM to the Outer Marker is recommended for interception and stabilization along the approach course. BEFORE LANDING – Perform the before landing checklist. – Set the airspeed bug to the approach speed (VAP). – Set the airspeed bug to the Approach Speed and bled off in such a way that over the threshold the target speed is at reference speed. – At 80 ft above the decision height, the EGPWS will call out “APPROACHING MINIMUMS”. NOTE: – If the RA is set to OFF (setting minimums knob to 0 ft), there is no EGPWS approach call outs. – If no visual contact is made upon reaching the decision height or if any malfunction could not be promptly identified during approach, a missed approach must be immediately initiated. !MAU load 21.2 and on OR POST-MOD SB 170-31-0028

AOM-1502-003

NOTE: If CAT II Instrument Approach Landing chart does not authorize the use of RA, set the RA to OFF (setting minimums knob to 0 ft). In this case there is no EGPWS call outs ″APPROACHING MINIMUMS″ and “MINIMUMS”. CONTINUED...

"

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REVISION 21

Suppl Procedures - Category II

Page 3

NORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

MISSED APPROACH GO-AROUND Procedure........................................ APPLY

LANDING Reaching the Decision Height with runway in sight: Autopilot................................................................ DISENGAGE

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Suppl Procedures - Category II

REVISION 21

AOM-1502-003

Landing................................................................. PERFORM

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES

SECTION 4 EMERGENCY AND ABNORMAL PROCEDURES TABLE OF CONTENTS

AOM-1502-003

Block

Page

Introduction.......................................................... 4-INTRO ....

1

Smoke.................................................................... 4-01-01 ......

1

Non Annunciated.................................................. 4-02-01 ......

1

Airplane General (Cargo Compartment/Doors/Lighting)...................... 4-03-01 ......

1

Pneumatic/Air Conditioning/Pressurization...... 4-03-02 ......

1

Autoflight.............................................................. 4-03-03 ......

1

Auxiliary Power Unit............................................ 4-03-04 ......

1

Electrical............................................................... 4-03-05 ......

1

Engine................................................................... 4-03-06 ......

1

Fire Protection...................................................... 4-03-07 ......

1

Flight Controls...................................................... 4-03-08 ......

1

FMS/NAV/COMM/Flight Instruments.................. 4-03-09 ......

1

Fuel........................................................................ 4-03-10 ......

1

Hydraulics............................................................. 4-03-11 ......

1

Ice and Rain Protection....................................... 4-03-12 ......

1

Landing Gear and Brakes................................... 4-03-13 ......

1

Oxygen.................................................................. 4-03-14 ......

1

Category II Operation.......................................... 4-04-54 ......

1

RVSM OPERATION............................................... 4-04-57 ......

1

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REVISION 10

Table of Contents

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EMERGENCY AND ABNORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 2

Table of Contents

REVISION 10

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES

INTRODUCTION This section provides the emergency and abnormal procedures to be performed in case of a system malfunction or failure, in order to protect passengers and/or crew from serious harm and to maintain the airworthiness of the airplane. In case any discrepancy between a procedure contained in this section and the approved Airplane Flight Manual (AFM) occurs, the AFM procedures must be followed. In the event that any of the procedures are missing or unusable, operations may be continued provided the approved AFM is available for use. The Emergency/Abnormal Procedures contained herein are based on system conditions annunciated on EICAS and non-annunciated conditions. System information displayed on synoptic pages is informative only and flight crew should always rely on EICAS messages for system status. Any failure of safety-critical parameter represented on the MFD synoptic page would also generate an EICAS message. The Emergency/Abnormal Procedures, in this section, are ordered in alphabetical sequence and divided into four blocks: – Smoke Procedures: contain all annunciated and non-annunciated smoke related procedures. – Non Annunciated Procedures: procedures, which are not related to an EICAS message but rather to a condition presented in the airplane. – Annunciated Procedures: procedures related to an EICAS message. These procedures are grouped by system and titled with the correspondent EICAS message wording. – Supplementary Procedures: procedures related to a special operation, like CAT II or HGS or Steep Approach which have specific procedures. These procedures are divided in Non-annunciated and Annunciated procedures, both in alphabetical order. Flight crew should use the Ground Resets procedures to clear nuisance EICAS messages and miscellaneous nuisance faults, detected during power on and other ground operations. CHECKLIST OPERATION

AOM-1502-003

The emergency/abnormal procedures have priority over the normal checklist, except when the crew judges that this is not the safest course of action. Flying the airplane is always the priority in any emergency/abnormal situation. Checklists should only be called by the PF after the flight path

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REVISION 18

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EMERGENCY AND ABNORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

is under control, critical phases of flight (takeoff and landing) have ended and all memory items have been accomplished. Some EICAS messages do not have an associated QRH procedure. In those cases, “Crew Awareness” identifies the EICAS message as noted in the Index Table. If a Crew Awareness message is displayed on the EICAS, takeoff is prohibited, unless at least one of the following conditions is met: – The message is an expected result of an intentional operation; – Flight crew action is taken to clear the message; – Maintenance personnel take action to clear the message; – The airplane is dispatched in accordance with all approved company MEL provisions. The procedures contained herein assume that: – Airplane systems were operating normally prior to the failure. – All emergency/abnormal actions are performed in the order they are presented in the procedure. – Normal procedures have been properly accomplished. – System controls were in normal condition prior to initiation of the associated procedure. – Aural warnings are silenced as applicable. Master Warning/Caution lights are reset as soon as the failure is recognized. – In case of depressurization and presence of smoke, full-face oxygen masks have been donned and communication has been established. – A tripped circuit breaker is usually a result of an abnormality in the electrical load or in associated wiring. Circuit breakers must not be reset in-flight, unless it is imperative to reset the circuit breaker for the safe completion of the flight. Should the circuit breaker trip again, no further attempt should be made to reset that circuit breaker. The reset of a circuit breaker is also permitted where the checklist specifically directs to do so. All tasks foreseen in the procedures have the indication END stating that the specific task for that condition is over. No task is over until END has been reached.

In the event of multiple failures (excluding cascade failures) with different

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Page 2

REVISION 18

AOM-1502-003

Upon completion of the procedure the pilot reading it should state: “___________Procedure Complete”.

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES

landing configurations and/or landing distance correction factors, the crew should use good judgment to determine the safest course of action. CHECKLIST STRUCTURE Some procedures bring a characterization below the title in case any relevant emergency/abnormal condition is present, such as aural warnings, lights, EICAS indications, flight instrument flags and the airplane condition itself. The actions contained in the bold square boxes are memory items. They must be performed expeditiously, from memory. Some procedures require landing at the nearest suitable airport. This statement may be presented below the associated emergency/abnormal characterization or at the beginning of a task that requires so. When the crew determines that significant threat to safety is present, they should always accomplish the earliest possible descent and landing regardless of having this statement present in the procedure. Some procedures contain “Lists of Relevant Inoperative Items” for that particular condition. Those lists presents only the most relevant items and for the full list, the AOM should be consulted. As SMOKE events are very time critical, on those procedures the lists contain only items that significantly affect airplane performance and/or controllability. For the entire list of relevant inoperative items on those conditions, the pilot can refer to the procedures associated with the electrical busses off. Procedures for failures affecting the landing distance presents an ″abnormal landing correction factor″. This factor must be multiplied by the applicable unfactored landing distance. The factor presented in the procedure is applicable to dry runways. Additional factors for other conditions are presented in the performance section of this manual. Throughout this manual, a text followed by () means that either condition apply. A text followed by “-” means that both conditions apply simultaneously. Whenever a question is necessary in the checklist it will be in a Yes/No format and presented inside a box, with arrows pointing where the checklist will continue depending on the answer, being that the “Yes” will always be directly below the question box. In some cases the arrows may be presented as a dashed line, to avoid confusion when there are two arrows close to each other.

AOM-1502-003

NOTE: Circuit Breakers reset may be performed when following the limitations and procedures specified in the GROUND RESETS.

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REVISION 18

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EMERGENCY AND ABNORMAL PROCEDURES

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REVISION 18

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INTENTIONALLY BLANK

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EMERGENCY AND ABNORMAL PROCEDURES SMOKE PROCEDURES

SMOKE TABLE OF CONTENTS Block

Page

AOM-1502-003

WARNING CRG FWD (AFT) SMOKE ...................................... 4-01-01......

1

LAV SMOKE.......................................................... 4-01-01......

2

SMOKE EVACUATION........................................... 4-01-01......

2

SMOKE / FIRE / FUMES ....................................... 4-01-01......

3

CAUTION RECIRC SMOKE ................................................... 4-01-01......

11

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REVISION 21

Table of Contents

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EMERGENCY AND ABNORMAL PROCEDURES SMOKE PROCEDURES

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES SMOKE PROCEDURES

CRG FWD (AFT) SMOKE Light:

Associated Cargo Fire-Extinguishing Button illuminates.

Associated Cargo Fire Extinguishing Button........ PUSH LAND AT THE NEAREST SUITABLE AIRPORT. ON GROUND?

No

Yes After CRG AFT (FWD) FIREX LO ARM message is displayed and the associated Cargo Fire Extinguishing Button is illuminated: Associated Cargo Fire Extinguishing Button........ AS REQUIRED NOTE: – Advise Ground Crew of possible Halon vapors after discharging the extinguishing bottle. – After the bottle discharge and with the airplane on ground, the message CRG FWD (AFT) FIRE SYS FAIL will appear. END

AOM-1502-003

END

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REVISION 21

Smoke

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EMERGENCY AND ABNORMAL PROCEDURES SMOKE PROCEDURES

AIRPLANE OPERATIONS MANUAL

LAV SMOKE Establish contact with the cabin crew. If necessary: Diversion............................................................... CONSIDER SMOKE EVACUATION Procedure....................... ACCOMPLISH END

SMOKE EVACUATION Crew Oxygen Masks............................................ DON, EMER Crew Communication........................................... ESTABLISH Pressurization Dump Button................................. PUSH IN LAND AT THE NEAREST SUITABLE AIRPORT. Cockpit Door........................................................... CLOSE Cabin Rate.............................................................. VERIFY CABIN RATE IS LESS THAN 1000 FT/MIN?

No

Yes Pressurization Mode Selector................................. MAN Pack 1 Button.......................................................... PUSH OUT Pack 2 Button.......................................................... PUSH OUT

Fstn Belts Signs...................................................... ON Altitude.................................................................... 10000 ft OR MEA, WHICHEVER IS HIGHER Thrust Lever............................................................ IDLE CONTINUED...

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Smoke

REVISION 21

AOM-1502-003

Recirc Fan Button................................................... PUSH OUT

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES SMOKE PROCEDURES

...CONTINUED

Speedbrake............................................................. FULL OPEN Airspeed.................................................................. MAX/ APPROPRIATE Transponder............................................................ 7700 ATC......................................................................... NOTIFY END

SMOKE / FIRE / FUMES CONDITION:

Smoke fire or fumes have been spotted by the crew without an EICAS warning.

Crew Oxygen Masks............................................ DON, 100% Crew Communication........................................... ESTABLISH LAND AT THE NEAREST SUITABLE AIRPORT. Recirc Fan Button................................................... PUSH OUT NOTE: Any time the smoke becomes dense, perform the SMOKE EVACUATION Procedure. SMOKE ORIGIN IS OBVIOUS AND CAN BE REMOVED?

No

Yes Affected source....................................................... REMOVE SMOKE STOPS OR DECREASES?

No

Yes SMOKE EVACUATION Procedure.......................... AS REQUIRED

AOM-1502-003

END

CONTINUED...

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REVISION 21

Smoke

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EMERGENCY AND ABNORMAL PROCEDURES SMOKE PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Fstn Belts Signs...................................................... ON Altitude.................................................................... 10000 ft OR MEA, WHICHEVER IS HIGHER Thrust Levers.......................................................... IDLE Speedbrake............................................................. FULL OPEN Airspeed.................................................................. MAX/ APPROPRIATE Transponder............................................................ 7700 ATC......................................................................... NOTIFY Pressurization DUMP Button.................................. PUSH NOTE: Smoke will initially decrease due to pressurization dumping, even if the correct source has not yet been removed. Bleed 1 Button........................................................ PUSH OUT Bleed 2 Button........................................................ PUSH OUT Emergency Lights................................................... OFF RAT Manual Deploy Lever...................................... PULL Airspeed.................................................................. MIN 130 KIAS IDG 1 Selector........................................................ OFF IDG 2 Selector........................................................ OFF APU Gen Button..................................................... PUSH OUT NOTE: Do not accomplish THE ELEC EMERGENCY Procedure. BATT DISCHARGING MESSAGE PRESENTED?

No

Yes IDG 1 or 2 Selector................................................. AUTO

Yes

No CONTINUED...

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Smoke

REVISION 21

AOM-1502-003

SMOKE STOPS OR DECREASES?

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES SMOKE PROCEDURES

...CONTINUED

Relevant Inoperative Items All Engine Reversers All Ground Spoilers All Multi Function Spoilers Display Unit 1

Display Unit 4 Display Unit 5 Nosewheel Steering Service Interphone System (Normal Mode)

Icing Conditions...................................................... EXIT/AVOID Landing Configuration: Emergency Lights................................................. ARMED Gnd Prox Flap Ovrd Button.................................. PUSH IN Slat/Flap................................................................ 3 Set Vref = Vref

FULL

+ 20 KIAS or 130 KIAS (whichever is higher).

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 2.10.

UNFACTORED

If a go around is required: Slat/Flap................................................................ 3 Airspeed................................................................ Vref FULL+ 20 or 130 KIAS WHICHEVER IS HIGHER NOTE: On ground, steer the airplane using differential braking and rudder. END

SUITABLE AIRPORT IS DISTANT?

No

AOM-1502-003

Yes IDG 1 Selector........................................................ AUTO IDG 2 Selector........................................................ AUTO CONTINUED...

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REVISION 21

Smoke

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EMERGENCY AND ABNORMAL PROCEDURES SMOKE PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

DC BUS TIES Switch............................................. OFF TRU 1 Switch.......................................................... OFF Battery 1.................................................................. OFF DC ESS BUS 1 AND DC BUS 1 ARE DEENERGIZED. SMOKE STOPS OR DECREASES?

Yes

No

Relevant Inoperative Items

Engine 1 Reverser Multi function spoilers L5 and R5

Outboard Brakes

Icing Conditions...................................................... EXIT/AVOID Landing Configuration: Emergency Lights................................................. ARMED Gnd Prox Flap Ovrd Button.................................. PUSH IN Slat/Flap ............................................................... 3 Set Vref = Vref

FULL

+ 20 KIAS.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 2.30.

UNFACTORED

If a go around is required: Slat/Flap................................................................ 3 Airspeed................................................................ Vref FULL+ 20 until the acceleration altitude is reached.

CAUTION:

• •

APPLY THE EMERGENCY/PARKING BRAKE MONITORING THE EMERGENCY/PARKING BRAKE LIGHT. WHEN THE EMERGENCY/PARKING BRAKE LIGHT IS ON, MAINTAIN STEADY PRESSURE SINCE THE ANTI-SKID PROTECTION IS NOT CONTINUED...

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Smoke

REVISION 21

AOM-1502-003

If necessary, on Ground: Emergency/Parking Brake.................................... PULL

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES SMOKE PROCEDURES

...CONTINUED

AVAILABLE. END

Battery 1.................................................................. ON TRU 1 Switch.......................................................... AUTO TRU 2 Switch.......................................................... OFF Battery 2.................................................................. OFF DC ESS BUS 2 AND DC BUS 2 ARE DEENERGIZED. SMOKE STOPS OR DECREASES?

Yes

No

Relevant Inoperative Items

All Engine Reversers Inboard Brakes Multi Function Spoilers L3, R3, L4 and R4

Nosewheel Steering Speedbrakes

Icing Conditions...................................................... EXIT/AVOID Landing Configuration: Emergency Lights................................................. ARMED Gnd Prox Flap Ovrd Button.................................. PUSH IN Slat/Flap ............................................................... 3 Set Vref = Vref

FULL

+ 20 KIAS.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 2.50.

UNFACTORED

AOM-1502-003

If a go around is required: Slat/Flap................................................................ 3 Airspeed................................................................ Vref FULL+ 20 until the acceleration altitude is reached. CONTINUED...

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REVISION 21

Smoke

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EMERGENCY AND ABNORMAL PROCEDURES SMOKE PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

If necessary, on Ground: Emergency/Parking Brake.................................... PULL CAUTION:

• •

APPLY THE EMERGENCY/PARKING BRAKE MONITORING THE EMERGENCY/PARKING BRAKE LIGHT. WHEN THE EMERGENCY/PARKING BRAKE LIGHT IS ON, MAINTAIN STEADY PRESSURE SINCE THE ANTI-SKID PROTECTION IS NOT AVAILABLE.

NOTE: On ground, steer the airplane using differential braking and rudder. END

Battery 2.................................................................. AUTO TRU 2 Switch.......................................................... AUTO TRU ESS Switch..................................................... OFF DC ESS BUS 3 ARE DEENERGIZED. SMOKE STOPS OR DECREASES?

No

Yes Landing Configuration: Emergency Lights................................................. ARMED Gnd Prox Flap Ovrd Button.................................. PUSH IN Slat/Flap ............................................................... 3 Set Vref = Vref

FULL

+ 20 KIAS.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 2.10.

UNFACTORED

CONTINUED...

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Smoke

REVISION 21

AOM-1502-003

If a go around is required: Slat/Flap................................................................ 3

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES SMOKE PROCEDURES

...CONTINUED

Airspeed................................................................ Vref FULL+ 20 until the acceleration altitude is reached. END

WARNING: CONSIDER AN IMMEDIATE LANDING. TRU ESS Switch..................................................... AUTO DC BUS TIES Switch............................................. AUTO Landing Configuration: Emergency Lights................................................. ARMED Gnd Prox Flap Ovrd Button.................................. PUSH IN Slat/Flap ............................................................... 3 Set Vref = Vref

FULL

+ 20 KIAS.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 2.10.

UNFACTORED

If a go around is required: Slat/Flap................................................................ 3 Airspeed................................................................ Vref FULL+ 20 until the acceleration altitude is reached.

AOM-1502-003

END

CONTINUED...

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REVISION 21

Smoke

Page 9

EMERGENCY AND ABNORMAL PROCEDURES SMOKE PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Relevant Inoperative Items All Engine Reversers All Ground Spoilers All Multi Function Spoilers Display Unit 1

Display Unit 4 Display Unit 5 Nosewheel Steering Service Interphone System (Normal Mode)

Icing Conditions...................................................... EXIT / AVOID Landing Configuration: Emergency Lights................................................. ARMED Gnd Prox Flap Ovrd Button.................................. PUSH IN Slat/Flap................................................................ 3 Set Vref = Vref

FULL

+ 20 KIAS or 130 KIAS (whichever is higher).

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 2.10.

UNFACTORED

NOTE: On ground, steer the airplane using differential braking and rudder. If a go around is required: Slat/Flap................................................................ 3 Airspeed................................................................ Vref FULL+ 20 or 130 KIAS WHICHEVER IS HIGHER

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Smoke

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES SMOKE PROCEDURES

RECIRC SMOKE

LAND AT THE NEAREST SUITABLE AIRPORT. Recirc Fan Button................................................... PUSH OUT

AOM-1502-003

END

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REVISION 21

Smoke

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EMERGENCY AND ABNORMAL PROCEDURES SMOKE PROCEDURES

AIRPLANE OPERATIONS MANUAL

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REVISION 21

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

NON ANNUNCIATED TABLE OF CONTENTS Block

Page

EMERGENCY CARGO COMPARTMENT FIRE ............................. 4-02-01......

1

DITCHING............................................................. 4-02-01......

2

DUAL ENGINE FAILURE ....................................... 4-02-01......

3

EMERGENCY DESCENT ...................................... 4-02-01......

6

EMERGENCY EVACUATION ................................. 4-02-01......

7

ENGINE ABNORMAL START ................................. 4-02-01......

7

ENGINE FIRE, SEVERE DAMAGE OR SEPARATION .................................................. 4-02-01......

8

FORCED LANDING ............................................... 4-02-01......

10

FUEL LEAK ........................................................... 4-02-01......

12

FUEL LOW LEVEL ................................................ 4-02-01......

13

JAMMED CONTROL COLUMN (PITCH)................. 4-02-01......

13

JAMMED CONTROL WHEEL (ROLL)..................... 4-02-01......

14

JAMMED RUDDER PEDALS ................................. 4-02-01......

15

PITCH TRIM RUNAWAY ........................................ 4-02-01......

16

REJECTED TAKEOFF ........................................... 4-02-01......

17

ROLL (YAW) TRIM RUNAWAY ............................... 4-02-01......

18

STEERING RUNAWAY .......................................... 4-02-01......

19

TAKEOFF WITH ENGINE FAILURE AT OR ABOVE V1 ................................................................... 4-02-01......

19

ABNORMAL ABNORMAL LANDING GEAR EXTENSION ........... 4-02-01...... APU EGT AMBER INDICATION ............................. 4-02-01......

20 21

O.B Nº 170-006/05 - AP quick disconnect button malfunctions AOM-1502-003

"AUTOPILOT" AURAL CAN NOT BE CANCELED... 4-02-01......

21

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REVISION 21

Table of Contents

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EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL Block

ABNORMAL BLANK DISPLAY UNIT WITHOUT AUTOMATIC REVERSION.................................................... EICAS MESSAGE MISCOMPARISON.................... ENGINE ABNORMAL VIBRATION.......................... ENGINE AIRSTART ............................................... ENGINE AIRSTART ENVELOPE ............................ ENGINE ITT OVERTEMPERATURE....................... ENGINE OIL OVERTEMPERATURE ...................... ENGINE OIL PRESSURE ABNORMAL INDICATION .................................................... ENGINE SHUTDOWN ........................................... ENGINE TAILPIPE FIRE ........................................ GEAR LEVER CAN NOT BE MOVED UP...............

Page

4-02-01...... 4-02-01...... 4-02-01...... 4-02-01...... 4-02-01...... 4-02-01...... 4-02-01......

23 23 24 25 28 29 29

4-02-01...... 4-02-01...... 4-02-01...... 4-02-01......

30 31 31 32

IESS ATTITUDE OSCILLATION WITH RAT DEPLOYED ..................................................... 4-02-01...... IMPAIRED OR CRACKED WINDSHIELD................ 4-02-01......

33 34

O.B Nº 170-011/08 - IESS operation with RAT deployed

O.B Nº 170-003/11 - Continuous in flight LANDING GEAR aural warning due to radar altimeter misbehavior

"LANDING GEAR" AURAL CAN NOT BE CANCELED ..................................................... LOSS OF APU INDICATIONS ................................ LOSS OF COMMUNICATIONS .............................. LOSS OF HYDRAULIC SYSTEM 1 ........................ LOSS OF HYDRAULIC SYSTEM 2 ........................ LOSS OF HYDRAULIC SYSTEM 3 ........................ LOSS OF HYDRAULIC SYSTEM 1 AND 2 ............. LOSS OF HYDRAULIC SYSTEM 1 AND 3 ............. LOSS OF HYDRAULIC SYSTEM 2 AND 3 ............. LOSS OF PRESSURIZATION INDICATION ............

4-02-01...... 4-02-01...... 4-02-01...... 4-02-01...... 4-02-01...... 4-02-01...... 4-02-01...... 4-02-01...... 4-02-01...... 4-02-01......

35 37 37 38 38 39 40 41 42 43

O.B Nº 170-006/05 - AP quick disconnect button malfunctions

45 46

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NON ANNUNCIATED LOSS OF ALL TRIMS AND AUTOPILOT .................................................... 4-02-01...... ONE ENGINE INOPERATIVE APPROACH AND LANDING ........................................................ 4-02-01......

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

Block

AOM-1502-003

ABNORMAL OXYGEN LEAKAGE .............................................. PARTIAL OR GEAR UP LANDING ......................... STRUCTURAL DAMAGE ....................................... UNRELIABLE AIRSPEED ...................................... VOLCANIC ASH ....................................................

Page

4-02-01...... 4-02-01...... 4-02-01...... 4-02-01...... 4-02-01......

47 47 48 50 53

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INTENTIONALLY BLANK

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EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

CARGO COMPARTMENT FIRE Associated Cargo Fire Extinguishing Button........ PUSH LAND AT THE NEAREST SUITABLE AIRPORT. After CRG AFT (FWD) FIREX HI ARM message is displayed and the associated Cargo Fire Extinguishing Button is illuminated: Associated Cargo Fire Extinguishing Button........ PUSH AGAIN ON GROUND?

No

Yes After CRG AFT (FWD) FIREX LO ARM message is displayed and the associated Cargo Fire Extinguishing Button is illuminated: Associated Cargo Fire Extinguishing Button........ AS REQUIRED NOTE: – Advise Ground Crew of possible Halon vapors after discharging the extinguishing bottle. – After the bottle discharge and with the airplane on ground, the message CRG FWD (AFT) FIRE SYS FAIL will appear. END

AOM-1502-003

END

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AIRPLANE OPERATIONS MANUAL

...CONTINUED

DITCHING Descent: Cabin Crew........................................................... NOTIFY ATC....................................................................... NOTIFY Transponder.......................................................... 7700 Aural Warning CBs (C7; C31).............................. PULL No Smkg/Fstn Belts Signs.................................... ON ELT........................................................................ ON Landing Data........................................................ SET At 10000 ft AGL: Pressurization Dump Button................................. PUSH IN When differential pressure reaches 0.2 psid or below: Airspeed................................................................ MAX 160 KIAS If necessary extend Flap/Slat as required to maintain airspeed below 160 KIAS. Direct Vision Window............................................ OPEN Approach: Altimeters.............................................................. SET At 5000 ft AGL: Pressurization Mode Selector............................... MAN Cabin Alt Controller............................................... HOLD DOWN FOR 50 s Ditching Configuration: Terrain Inhibit Button............................................. IN Landing Gear........................................................ UP Slat/Flap................................................................ MAXIMUM AVAILABLE

NOTE: If engines are not running maintain minimum speed of 130 KIAS. CONTINUED...

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APU Emergency Stop Button............................... PUSH IN

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

...CONTINUED

Just Before Water Contact: Cabin..................................................................... ANNOUNCE IMPACT After Ditching: Thrust Levers........................................................ IDLE Start/Stop Selectors.............................................. STOP Fire Extinguishing Handles................................... PULL AND ROTATE Emergency Evacuation......................................... ANNOUNCE Batteries................................................................ OFF END

DUAL ENGINE FAILURE EICAS Indication: FAIL icon inside both N1 indicators. EICAS Indication: Both oil pressure indications in red. Airspeed................................................................ 250 KIAS MIN RAT Manual Deploy Lever.................................... PULL LAND AT THE NEAREST SUITABLE AIRPORT. APU......................................................................... START Emergency Lights................................................... OFF Thrust Levers.......................................................... IDLE BOTH ENGINES SUCCESSFUL AUTORELIGHT?

No

Yes Flight Controls Mode Buttons (Spoilers, Elevators, Rudder)................................................................... PUSH IN, then OUT

AOM-1502-003

Landing Configuration: Emergency Lights................................................. ARMED Gnd Prox Flap Ovrd Button.................................. PUSH IN CONTINUED...

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...CONTINUED

Slat/Flap................................................................ 3 !170/175 models, FAA certification

Set VREF = VREF

FULL

+ 15 KIAS. "

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.31.

UNFACTORED

NOTE: – During engine auto relight, if N2 is steady accelerating while ITT remains within start limit, the start is progressing normally. – During inflight starts, FADEC has no protection for hot starts, hung starts or failure to light off. – Crew must take appropriate action in case of abnormal engine indications. END

ENGINE AIRSTART ENVELOPE........................... CHECK Fuel Xfeed Selector................................................ LOW 1 Inoperative Engine(s): Start/Stop Selector(s)........................................... STOP Ignition(s).............................................................. OVRD Start/Stop Selector(s)........................................... START, then RUN DUAL ENGINE FAILURE CONDITION PERSISTS?

No

Yes Landing Configuration: Emergency Lights................................................. ARMED Set VREF = VREF FULL + 20 KIAS or VREF = 130 KIAS (whichever is higher). CONTINUED...

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Slat/Flap................................................................ 3

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

...CONTINUED

FORCED LANDING or DITCHING Procedure....... ACCOMPLISH END

Flight Controls Mode Buttons (Spoilers, Elevators, Rudder)................................................................. PUSH IN, then OUT After engine(s) stabilized at idle: Ignition(s).............................................................. AUTO Fuel....................................................................... BALANCE ONE ENGINE INOPERATIVE?

No

Yes Inoperative Engine START/STOP Selector............. STOP Transponder............................................................ TA ONLY

Descent: Landing Data........................................................ SET Approach Aids....................................................... SET Altimeters.............................................................. SET/CHECK Landing Configuration: Emergency Lights................................................. ARMED Gnd Prox Flap Ovrd Button.................................. PUSH IN Landing Gear........................................................ DOWN Slat/Flap................................................................ 3 Set VREF = VREF

FULL

+ 20 KIAS.

AOM-1502-003

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 2.10.

UNFACTORED CONTINUED...

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...CONTINUED

If a go around is required: Slat/Flap................................................................ 3 Airspeed................................................................ VREF FULL + 20 KIAS END

EMERGENCY DESCENT Fstn Belts Signs.................................................... ON Altitude.................................................................. 10000 ft OR MEA, WHICHEVER IS HIGHER Thrust Levers........................................................ IDLE Speedbrake........................................................... FULL OPEN Airspeed................................................................ MAX/ APPROPRIATE Transponder.......................................................... 7700 ATC....................................................................... NOTIFY

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END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

EMERGENCY EVACUATION Emergency/Parking Brake.................................... ON Thrust Levers........................................................ IDLE Start/Stop Selectors.............................................. STOP Fire Extinguishing Handles................................... PULL AND ROTATE (1-L and 2-R) APU Emergency Stop Button............................... PUSH IN APU Fire Extinguishing Button............................. PUSH Pressurization Dump Button................................. PUSH IN ATC....................................................................... NOTIFY Emergency Evacuation......................................... ANNOUNCE Batteries................................................................ OFF END

ENGINE ABNORMAL START Affected engine: Start/Stop Selector............................................. STOP ENGINE DRY MOTORING CONSIDERED?

No

Yes Affected engine: Ignition.................................................................. OFF Start/Stop Selector................................................ START, then RUN

AOM-1502-003

.......................................Wait 30 seconds....................................... Start/Stop Selector................................................ STOP

CONTINUED...

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...CONTINUED

Ignition.................................................................. AUTO

If applicable: Transponder.......................................................... TA ONLY ONE ENGINE INOPERATIVE APPROACH AND LANDING Procedure.......................................... ACCOMPLISH END

ENGINE FIRE, SEVERE DAMAGE OR SEPARATION Autothrottle............................................................ DISENGAGE Affected engine: Thrust Lever....................................................... IDLE Start/Stop Selector............................................. STOP Fire Extinguishing Handle.................................. PULL LAND AT THE NEAREST SUITABLE AIRPORT. Fire Extinguishing Handle....................................... ROTATE (L or R) ........................................Wait 30 seconds........................................ FIRE PERSISTS?

No

Yes Fire Extinguishing Handle (remaining bottle).......... ROTATE

No

Yes

CONTINUED...

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REVISION 21

AOM-1502-003

ON GROUND?

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

...CONTINUED

EMERGENCY EVACUATION Procedure................ AS REQUIRED END

HIGH VIBRATION?

No

Yes Airspeed.................................................................. REDUCE Airspeeds below VA are recommended to reduce vibration.

Icing Conditions...................................................... EXIT/AVOID Transponder............................................................ TA ONLY EICAS ASSOCIATED FUEL INDICATION LOST?

No

Yes NOTE: Assume that fuel is leaking from tank associated to engine failed side. Fuel Xfeed Selector................................................ OFF LEAK ON THE RH TANK?

No

Yes

APU......................................................................... OFF ONE ENGINE INOPERATIVE APPROACH AND LANDING Procedure............................................... ACCOMPLISH

AOM-1502-003

END

CONTINUED...

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...CONTINUED

APU......................................................................... AS REQUIRED ONE ENGINE INOPERATIVE APPROACH AND LANDING Procedure............................................... ACCOMPLISH END

APU......................................................................... START Fuel......................................................................... BALANCE Autothrottle.............................................................. AS REQUIRED When appropriate: ONE ENGINE INOPERATIVE APPROACH AND LANDING Procedure.......................................... ACCOMPLISH END

FORCED LANDING Descent: Cabin Crew........................................................... NOTIFY ATC....................................................................... NOTIFY Transponder.......................................................... 7700 Aural Warning CBs (C7; C31).............................. PULL No Smkg/Fstn Belts Signs.................................... ON ELT........................................................................ ON Landing Data........................................................ SET

CONTINUED...

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At 10000 ft: Pressurization Dump Button................................. PUSH IN

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

...CONTINUED

Approach: Altimeters.............................................................. SET Landing Configuration: Terrain Inhibit Button............................................. IN Landing Gear........................................................ DOWN Slat/Flap................................................................ MAXIMUM AVAILABLE APU Emergency Stop Button............................... PUSH IN NOTE: If engines are not running maintain minimum speed of 130 KIAS and alternate gear extension may be required. Just Before Touchdown: Cabin..................................................................... ANNOUNCE IMPACT After Landing: Thrust Levers........................................................ IDLE Start/Stop Selectors.............................................. STOP Fire Extinguishing Handles................................... PULL AND ROTATE Emergency Evacuation......................................... ANNOUNCE Batteries................................................................ OFF

AOM-1502-003

END

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FUEL LEAK LAND AT THE NEAREST SUITABLE AIRPORT. A fuel leak may be detected by either:

• • • • • •

A fuel imbalance develops; or Excessive fuel flow in one of the engines; or Fuel quantity from one tank decreases at abnormal rate; or Fuel smell; or Fuel spray from the wings; or With both engines operative, an unexpected difference between the total fuel quantity indicated on EICAS and the total fuel quantity indicated on the FMS Fuel Management page or PERF INIT page 3/3.

Fuel Xfeed Selector................................................ OFF Affected Fuel Tank.................................................. IDENTIFY Identify the affected fuel tank using the fuel flow, fuel quantity or visually. Asymmetric Thrust.................................................. AS REQUIRED Use asymmetric thrust to improve or maintain wing fuel balance to counteract the effect of the suspected wing fuel leak. LEAK ON THE RH TANK?

No

Yes APU......................................................................... OFF Right tank supplies fuel to the APU. END

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APU......................................................................... AS REQUIRED

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

END

FUEL LOW LEVEL CONDITION:

The Fuel Quantity indication on EICAS is displayed in red but the EICAS message is not presented.

FUEL 1 (2) LO LEVEL Procedure.......................... ACCOMPLISH END

JAMMED CONTROL COLUMN (PITCH) Elev Disc Handle.................................................. PULL Unrestricted Control Column.................................. IDENTIFY Maximum Airspeed................................................. CURRENT OR 175 KIAS, WHICHEVER IS HIGHER NOTE: Expect lower pitch rates and authority. Relevant Inoperative Items: AOA Limit Autopilot Avoid sidesliping the airplane. NOTE: The stick shaker remains operative. Landing configuration: Slat/Flap................................................................ 5 Set VREF = VREF

FULL

+ 15 KIAS.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.40.

UNFACTORED

AOM-1502-003

If a go around is required: Slat/Flap................................................................ 4 CONTINUED...

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...CONTINUED

Airspeed................................................................ VREF FULL + 15 KIAS (limited to 175 KIAS) END

JAMMED CONTROL WHEEL (ROLL) Aileron Disc Handle.............................................. PULL Unrestricted Control Wheel..................................... IDENTIFY Maximum Airspeed................................................. CURRENT OR 175 KIAS, WHICHEVER IS HIGHER NOTE: – – – – –

Expect lower roll rates. Avoid abrupt and large aileron inputs. Maintain bank angle below 25°. Rudder may be used to help controlling the airplane. Do not accomplish the Spoiler Fault procedure. Relevant Inoperative Items: Multi Function Spoiler L3 and R3 Another Multi Function Spoiler pair depending on the affected side

Affected side aileron Autopilot

Landing configuration: Slat/Flap................................................................ 5 Set VREF = VREF

• •

+ 15 KIAS.

DURING LANDING, A CROSSWIND COMPONENT GREATER THAN 10 KT MUST BE AVOIDED. MULTIPLY THE FULL FLAPS UNFACTORED LANDING DISTANCE BY 1.40. CONTINUED...

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CAUTION:

FULL

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

...CONTINUED

If a go around is required: Slat/Flap................................................................ 4 Airspeed................................................................ VREF FULL + 15 KIAS (limited to 175 KIAS) END

JAMMED RUDDER PEDALS Maximum Airspeed................................................. CURRENT OR 175 KIAS, WHICHEVER IS HIGHER Relevant Inoperative Items: Yaw trim NOTE: Use asymmetric thrust for directional control. Landing configuration: Slat/Flap................................................................ FULL Set VREF FULL. CAUTION: DURING LANDING, A CROSSWIND COMPONENT GREATER THAN 10 KT MUST BE AVOIDED. Before Landing: Steer Disc Switch (Pilot non flying)...................... PRESS and HOLD Asymmetric Thrust................................................ MAINTAIN UNTIL NOSEWHEEL TOUCHDOWN

AOM-1502-003

After nosewheel touchdown: Nosewheel Steering Handle................................. PRESS and HOLD Steer Disc Switch................................................. RELEASE CONTINUED...

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...CONTINUED

Thrust Levers........................................................ IDLE Asymmetric Braking.............................................. AS REQUIRED CAUTION: DO NOT RELEASE THE NOSEWHEEL STEERING HANDLE UNTIL THE AIRPLANE IS COMPLETELY STOPPED. If a go around is required, proceed as a normal go around limiting the airspeed to 175 KIAS. NOTE: As asymmetric thrust may be required to help controlling the airplane, maximum thrust on both engines may not be possible. END

PITCH TRIM RUNAWAY A/P Disc Button.................................................... PRESS AND HOLD Pitch Trim Systems 1 and 2 Cutout Button.......... PUSH IN A/P Disc Button....................................................... RELEASE WARNING: DO NOT OPEN THE SPEEDBRAKE. NOTE: Continuous turns helps to alleviate excessive pitch up tendencies. Prepare to overcome unwanted pitch change: Pitch Trim System 1 Cutout Button...................... PUSH OUT Pitch Trim Switch.................................................. ACTUATE PITCH TRIM NORMAL?

No

Yes

CONTINUED...

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NOTE: Manual trim command through Pitch Trim Switches is available with at least one functional HS-ACE channel. With one HS-ACE channel available expect the following differences on the pitch trim indication on EICAS: • Pitch trim readout display showing amber dashes.

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

...CONTINUED

•

Pitch trim scale without the solid green pointer.

END

Pitch Trim System 1 Cutout Button........................ PUSH IN Pitch Trim System 2 Cutout Button........................ PUSH OUT NOTE: Manual trim command through Pitch Trim Switches is available with at least one functional HS-ACE channel. With one HS-ACE channel available expect the following differences on the pitch trim indication on EICAS: • Pitch trim readout display showing amber dashes. • Pitch trim scale without the solid green pointer. END

REJECTED TAKEOFF Thrust Levers.......................................................... IDLE Reverse Thrust....................................................... AS REQUIRED Brake Pedals (If Autobrake is not armed).............. MAXIMUM APPLY NOTE: During RTO the thrust reversers can be used until the airplane comes to a complete stop. When airplane has stopped: Emerg/Parking Brake............................................ ON If applicable: EMERGENCY EVACUATION Procedure............. ACCOMPLISH

AOM-1502-003

END

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ROLL (YAW) TRIM RUNAWAY A/P Disc Button.................................................... PRESS AND HOLD Do not engage the autopilot. Prepare to overcome unexpected roll (yaw): A/P Disc Button.................................................... RELEASE ROLL (YAW) TRIM NORMAL?

No

Yes

END

A/P Disc Button....................................................... PRESS AND HOLD Roll (Yaw) Trim Electronic CB................................ OUT Select on the MCDU: CB → CB MENU → CB BY SYSTEM → NEXT → FLT CTRL → ROLL TRIM PWR or YAW TRIM PWR. A/P Disc Button....................................................... RELEASE

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END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

STEERING RUNAWAY Steer Disc Switch................................................. PRESS Use differential braking and rudder to steer the airplane.

END

TAKEOFF WITH ENGINE FAILURE AT OR ABOVE V1 At VR rotate the airplane following the flight director guidance. In case of flight director is inoperative, rotate the airplane according to the following schedule: !170/175 models, MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

Rotate the airplane to 12º nose up for a flap 4 takeoff, to 10º nose up for a flap 2 takeoff or 11º nose up for a flap 1 takeoff. " !MAU load 19.3 and on OR POST-MOD SB 170-31-0019

Rotate the airplane according to the takeoff pitch angle displayed on TAKEOFF page 3/3 on the MCDU. "

With positive climb: Landing Gear..................................................... UP Airspeed............................................................. MIN V2

AOM-1502-003

Maintain V2 minimum up to the acceleration altitude. At the acceleration altitude, select flaps up according to the flap retraction speed reference indication.

CONTINUED...

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...CONTINUED

Accelerate the airplane to the final segment speed (VFS) and set the engine thrust rate to continuous. NOTE: If the airplane is at low weight and the selected altitude is low, TO/GA vertical mode may be reverted to ASEL. After retracting flaps, accomplish the ENG 1 (2) FAIL Procedure. END

ABNORMAL LANDING GEAR EXTENSION Landing Gear Lever................................................ DOWN Electrical Override Switch....................................... GEAR DOWN LG INDICATIONS DOWN?

No

Yes END

Alternate Gear Extension Lever............................. PULL NOTE: Ensure the Alternate Gear Extension Lever is completely actuated and locked. Landing Gear Indications........................................ CHECK LG INDICATIONS DOWN?

Yes

No

Relevant Inoperative Items

Nosewheel Steering

CONTINUED...

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REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

...CONTINUED

PARTIAL OR GEAR UP LANDING Procedure...... ACCOMPLISH END

APU EGT AMBER INDICATION APU ESSENTIAL FOR FLIGHT?

No

Yes

END

APU......................................................................... OFF END !O.B Nº 170-006/05 - AP quick disconnect button malfunctions

"AUTOPILOT" AURAL CAN NOT BE CANCELED Autopilot.................................................................. ENGAGE Autopilot Quick Disconnect Button......................... PRESS TWO TIMES AURAL IS CANCELED?

No

AOM-1502-003

Yes

CONTINUED...

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...CONTINUED

END

NOTE: The aural warning can only be canceled by powering down the airplane. Relevant Inoperative Items: Autopilot Pitch trim indication

Roll trim Yaw trim

Pitch Trim System 1 Cutout Button........................ PUSH IN PITCH TRIM NORMAL?

No

Yes END

Pitch Trim System 1 Cutout Button........................ PUSH OUT Pitch Trim System 2 Cutout Button........................ PUSH IN END

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AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

BLANK DISPLAY UNIT WITHOUT AUTOMATIC REVERSION Select the affected side reversionary panel display selector to PFD or EICAS, as required. END

EICAS MESSAGE MISCOMPARISON INDICATION:

CAS MSG flag on PFD.

CAS SOURCE SELECTION................................... ALTERNATE BETWEEN CAS 1 AND CAS 2 AND COMPARE Select on the MCDU: MENU→MISC (LSK 1L)→SETUP (LSK 2L)→CAS SOURCE SELECTION (LSK 2R)→CAS 1→CAS 2. Compare the messages of the two CAS sources displayed on the EICAS to check which is the discrepant message. Analyze the situation to check whether the discrepant message is spurious or not, and take the appropriate corrective action.

AOM-1502-003

END

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ENGINE ABNORMAL VIBRATION EICAS Indication: Engine vibration indication displayed in amber. Autothrottle.............................................................. DISENGAGE ENG VIBRATION DUE TO ICE ACCUMULATION?

No

Yes NOTE: If both engines are affected, perform the following steps for one engine at a time. Associated Thrust Lever......................................... IDLE, THEN MINIMUM 70% N1 ........................................Wait 30 seconds........................................ Associated Thrust Lever......................................... AS REQUIRED END

Associated Thrust Lever......................................... REDUCE Reduce thrust to achieve green range vibration. Associated Thrust Lever......................................... AS REQUIRED ENG ABNORMAL VIBRATION REMAINS?

No

Yes Associated Thrust Lever......................................... REDUCE Reduce thrust to keep vibration within limits. Transponder............................................................ TA ONLY

CONTINUED...

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REVISION 21

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If unable to keep vibration within limits and engine parameters become abnormal or exceed operating limits:

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

...CONTINUED

ENGINE SHUTDOWN Procedure........................ CONSIDER

END

ENGINE AIRSTART NOTE: – Windmilling starts accomplished with residual ITT below 90°C are more reliable. – After an engine airstart, if flight conditions permit operate the engine at idle for 2 minutes prior to apply engine thrust. – If N2 has gone to 0, more than one start attempt may be required to get a successful engine start. Autothrottle.............................................................. DISENGAGE Airstart Envelope..................................................... CHECK ENGINE AIRSTART ASSISTED?

No

Yes N2 (Operative Engine)............................................ MIN 80% Inoperative engine: Ignition.................................................................. OVRD Start/Stop Selector................................................ START, THEN RUN ENGINE NORMAL START?

No

Yes After engine stabilizes at idle: Ignition.................................................................. AUTO

AOM-1502-003

Autothrottle............................................................ AS REQUIRED CONTINUED...

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NON ANNUNCIATED PROCEDURES

...CONTINUED

Transponder.......................................................... TA/RA END

Start/Stop Selector.................................................. STOP Ignition..................................................................... AUTO Fuel......................................................................... BALANCE Transponder............................................................ TA ONLY ONE ENGINE INOPERATIVE APPROACH AND LANDING Procedure............................................... ACCOMPLISH END

Perform a windmilling start: Xbleed Button....................................................... PUSH OUT APU Bleed Button (if engine 1 affected).............. PUSH OUT Inoperative engine: N2..................................................................... MIN 7.2% Ignition.............................................................. OVRD Start/Stop Selector........................................... START, THEN RUN NOTE: – During engine auto relight, if N2 is steady accelerating while ITT remains within start limit, the start is progressing normally. – During inflight starts, FADEC has no protection for hot starts, hung starts or failure to light off. – Crew must take appropriate action in case of abnormal engine indications.

Yes

No CONTINUED...

4-02-01 Copyright © by Embraer. Refer to cover page for details.

Page 26

Non Annunciated

REVISION 21

AOM-1502-003

ENGINE NORMAL START?

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

...CONTINUED

After engine stabilizes at idle: Xbleed Button....................................................... PUSH IN APU Bleed Button................................................. PUSH IN Ignition.................................................................. AUTO Autothrottle............................................................ AS REQUIRED Transponder.......................................................... TA/RA END

Xbleed Button......................................................... PUSH IN APU Bleed Button................................................... PUSH IN Start/Stop Selector.................................................. STOP Ignition..................................................................... AUTO Fuel......................................................................... BALANCE Transponder............................................................ TA ONLY ONE ENGINE INOPERATIVE APPROACH AND LANDING Procedure............................................. ACCOMPLISH

AOM-1502-003

END

4-02-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Non Annunciated

Page 27

EMERGENCY AND ABNORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

NON ANNUNCIATED PROCEDURES

ENGINE AIRSTART ENVELOPE

30000 REGION 1 − ASSISTED START ONLY REGION 2 − WINDMILLING START ONLY REGION 3 − ASSISTED OR WINDMILLING START

320 KIAS 25000 2

140 KIAS 21000 ft

ALTITUDE − FT

20000

3 15000

1 10000 8000 ft

0

50

100

150

200

250

300

INDICATED AIRSPEED − KIAS

350

4-02-01 Copyright © by Embraer. Refer to cover page for details.

Page 28

Non Annunciated

REVISION 21

AOM-1502-003

0

EM170AOM040002F.DGN

5000

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

ENGINE ITT OVERTEMPERATURE CONDITION:

ITT pointer in white, dial and readout in red inverse video.

Autothrottle.............................................................. DISENGAGE Associated Thrust Lever......................................... REDUCE Reduce thrust to keep ITT within limits. Transponder............................................................ TA ONLY ITT WITHIN LIMITS?

No

Yes

END

ENGINE SHUTDOWN Procedure........................ ACCOMPLISH END

ENGINE OIL OVERTEMPERATURE Autothrottle.............................................................. DISENGAGE Associated Thrust Lever......................................... ADJUST TO KEEP TEMPERATURE WITHIN LIMITS NOTE: If oil temperature rise follows thrust reduction, advancing the thrust lever may reduce oil temperature. Transponder............................................................ TA ONLY OVERTEMPERATURE REMAINS?

No

AOM-1502-003

Yes CONTINUED...

4-02-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Non Annunciated

Page 29

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

If other parameters of affected engine become abnormal or exceed operating limits: ENGINE SHUTDOWN Procedure........................ ACCOMPLISH END

END

ENGINE OIL PRESSURE ABNORMAL INDICATION INDICATION:

Oil pressure indication on EICAS is displayed in amber dashes or displays zero PSI.

ENG 1 (2) OIL LO PRESS MESSAGE PRESENTED?

No

Yes ENGINE SHUTDOWN Procedure........................... ACCOMPLISH END

Engine Parameters................................................. MONITOR

4-02-01 Copyright © by Embraer. Refer to cover page for details.

Page 30

Non Annunciated

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

ENGINE SHUTDOWN LAND AT THE NEAREST SUITABLE AIRPORT. Autothrottle.............................................................. DISENGAGE Affected Engine: Thrust Lever.......................................................... IDLE Start/Stop Selector................................................ STOP APU......................................................................... START Associated Fuel Pump............................................ AUTO Fuel......................................................................... BALANCE Transponder............................................................ TA ONLY When appropriate: ONE ENGINE INOPERATIVE APPROACH AND LANDING Procedure.......................................... ACCOMPLISH END

ENGINE TAILPIPE FIRE CONDITION:

Tailpipe fire was detected visually by crew or ground personnel. No EICAS message displayed.

Affected Engine: Thrust Lever.......................................................... IDLE Start/Stop Selector................................................ STOP Ignition.................................................................. OFF Start/Stop Selector................................................ START, then RUN ITT........................................................................... MONITOR ATC......................................................................... NOTIFY

AOM-1502-003

........................................Wait 90 Seconds........................................

CONTINUED...

4-02-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Non Annunciated

Page 31

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Associated Start/Stop Selector............................... STOP NOTE: If fire is not extinguished while the engine is motored, it must be extinguished using ground equipment, and maintenance procedures applied. END

GEAR LEVER CAN NOT BE MOVED UP LG WOW SYS FAIL MESSAGE DISPLAYED?

No

Yes Landing Gear Lever................................................ DOWN NOTE: The DN LOCK REL button may be pressed to move the landing gear lever up if climb performance is required to clear obstacles. LG WOW SYS FAIL Procedure.............................. ACCOMPLISH END

DN LOCK REL Button............................................ PRESS and HOLD Landing Gear Lever................................................ UP DN LOCK REL Button............................................ RELEASE

4-02-01 Copyright © by Embraer. Refer to cover page for details.

Page 32

Non Annunciated

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

!O.B Nº 170-011/08 - IESS operation with RAT deployed

IESS ATTITUDE OSCILLATION WITH RAT DEPLOYED Maintain leveled flight: Airspeed................................................................ MAINTAIN CURRENT SPEED CAGE Button........................................................ PRESS AND HOLD FOR 2 SECONDS ........................................Wait 10 seconds........................................ IESS ATTITUDE INDICATION OSCILLATION PERSISTS?

No

Yes Maintain leveled flight: Airspeed................................................................ REDUCE OR INCREASE BY 15 KIAS CAGE Button........................................................ PRESS AND HOLD FOR 2 SECONDS ........................................Wait 10 seconds........................................ END

END

AOM-1502-003

"

4-02-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Non Annunciated

Page 33

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

IMPAIRED OR CRACKED WINDSHIELD Affected Windshield Heating Button....................... PUSH OUT Cockpit Door .......................................................... CLOSE NOTE: There is a windshield heating wire between the middle and outer layers that can be used as a reference to determine which layer is cracked. If the wire can be seen without a gap the crack is in the outer layer, and if there is a wire discontinuity, the crack may be located in the middle and/or inner layers. ONLY OUTER LAYER CRACKED?

No

Yes

END

CAUTION: ACCOMPLISH THE DESCENT IN A MAXIMUM OF 15 MINUTES. Airspeed.................................................................. MAX 220 KIAS Altitude.................................................................... 10000 ft OR MEA, WHICHEVER IS HIGHER During Descent: Pressurization Mode Selector............................... MAN Cabin Altitude........................................................ INCREASE NOTE: Maintain cabin altitude at 10000 ft while descending the airplane.

Pack 2 Button....................................................... PUSH OUT CONTINUED...

4-02-01 Copyright © by Embraer. Refer to cover page for details.

Page 34

Non Annunciated

REVISION 21

AOM-1502-003

At or below 10000 ft: Pack 1 Button....................................................... PUSH OUT

AIRPLANE OPERATIONS MANUAL ...CONTINUED

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

No

ONLY ONE SIDE IMPAIRED

Yes Pilot flying must be on the non-impaired side. END

Airspeed.................................................................. MAX 140 KIAS Direct Vision Window.............................................. OPEN END !O.B Nº 170-003/11 - Continuous in flight LANDING GEAR aural warning due to radar altimeter misbehavior

"LANDING GEAR" AURAL CAN NOT BE CANCELED CONDITION:

Continuous LANDING GEAR aural warning with no RALT 1 (2) FAIL EICAS message.

Crosscheck both LH and RH PFD RALT digital readouts for any non-reliable readings. FLYING ABOVE 2500 ft AGL?

No

Yes

LH PFD RALT NON-RELIABLE READINGS?

No

AOM-1502-003

Yes

CONTINUED...

4-02-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Non Annunciated

Page 35

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Radar Altimeter 1 Electronic CB............................. OUT

NOTE: Select on the MCDU: CB → CB MENU → CB BY SYSTEM → NAV → RALT 1. RALT 1 (2) FAIL Procedure..................................... ACCOMPLISH END

Radar Altimeter 2 Electronic CB............................. OUT NOTE: Select on the MCDU: CB → CB MENU → CB BY SYSTEM → NAV → RALT 2. RALT 1 (2) FAIL Procedure..................................... ACCOMPLISH END

END

4-02-01 Copyright © by Embraer. Refer to cover page for details.

Page 36

Non Annunciated

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

LOSS OF APU INDICATIONS CONDITION:

APU RPM or APU EGT indication on EICAS is displayed in amber dashes.

APU ESSENTIAL FOR THE FLIGHT?

No

Yes Monitor the APU for the remainder of the flight. If any APU fault message is displayed on EICAS:

APU Emergency Stop Button................................. PUSH IN APU Master Selector.............................................. OFF Do not restart the APU. END

LOSS OF COMMUNICATIONS ACP 1 BKUP Button............................................... PUSH OUT AND ADJUST VOLUME NOTE: Only VHF1 is available for the Captain. ACP 2 BKUP Button............................................... PUSH OUT AND ADJUST VOLUME NOTE: Only VHF2 is available for the First Officer.

AOM-1502-003

END

4-02-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Non Annunciated

Page 37

EMERGENCY AND ABNORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

NON ANNUNCIATED PROCEDURES

LOSS OF HYDRAULIC SYSTEM 1 Autopilot.................................................................. DISENGAGE NOTE: – Expect lower roll rates and lower speedbrake efficiency. – Do not accomplish the SPOILER FAULT procedure. – Do not command the engine 1 reverser. Relevant Inoperative Items: Autopilot Engine 1 Reverser Ground Spoiler L2 and R2

Multi Function Spoilers L3, R3, L4 and R4 Outboard Brakes

Plan a long final approach. Landing configuration: Slat/Flap................................................................ FULL Set VREF

FULL.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.90.

UNFACTORED

END

LOSS OF HYDRAULIC SYSTEM 2 NOTE: – Expect lower roll rates and lower speedbrake efficiency. – Do not accomplish the SPOILER FAULT procedure. – Do not command the engine 2 reverser. Relevant Inoperative Items:

Ground Spoilers L1 and R1 Inboard Brakes

Landing Gear Retraction and Normal Extension (Fluid quantity loss only) Multi Function Spoilers L5 and R5 Nosewheel Steering

Plan a long final approach. CONTINUED...

4-02-01 Copyright © by Embraer. Refer to cover page for details.

Page 38

Non Annunciated

REVISION 21

AOM-1502-003

Engine 2 Reverser

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

...CONTINUED

Landing configuration: Landing Gear Lever.............................................. DOWN LANDING GEAR FAILED TO EXTEND AND LOCK DOWN?

No

Yes Alternate Gear Extension Lever........................... PULL

Slat/Flap................................................................ FULL Set VREF

FULL.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.80.

UNFACTORED

If a go around is required: Landing Gear........................................................ DOWN NOTE: If hydraulic system 2 still has hydraulic fluid, the PTU may be available to retract the landing gear in the event of a go-around. END

LOSS OF HYDRAULIC SYSTEM 3 Back up hydraulic power to the R.H. elevator, rudder and ailerons will not be available. Relevant Inoperative Items: Outboard Aileron Actuators.

AOM-1502-003

END

4-02-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Non Annunciated

Page 39

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

LOSS OF HYDRAULIC SYSTEM 1 AND 2 LAND AT THE NEAREST SUITABLE AIRPORT. NOTE: – Expect lower roll and pitch rates. – Do not accomplish the ELEVATOR FAULT and the SPOILER FAULT procedures. – Apply the Emergency/Parking Brake to stop the airplane monitoring the Emergency/Parking Brake light. – Braking action starts after Emergency/Parking Brake light illumination. Apply the brake carefully since the Anti-Skid protection is not available. Relevant Inoperative Items: Multi Function Spoilers L3, R3, L4, R4, L5 and R5

Autopilot

Engine 1 and Engine 2 Nosewheel Steering Reversers Ground Spoilers L1, R1, L2 and Outboard and Inboard Brakes R2 Landing Gear Retraction and Speedbrake Normal Extension L.H. Elevator Plan a long final approach. Landing configuration: Landing Gear Lever.............................................. DOWN Alternate Gear Extension Lever........................... PULL Slat/Flap................................................................ 5 Set VREF = VREF

• •

+ 10 KIAS.

AVOID LANDING WITH CROSSWIND COMPONENTS ABOVE 10 KT. MULTIPLY THE FULL FLAPS UNFACTORED LANDING DISTANCE BY 2.70.

If a go around is required: Landing Gear Lever.............................................. DOWN CONTINUED...

4-02-01 Copyright © by Embraer. Refer to cover page for details.

Page 40

Non Annunciated

REVISION 21

AOM-1502-003

CAUTION:

FULL

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

...CONTINUED

Slat/Flap................................................................ 4 Airspeed................................................................ VREF FULL + 10 KIAS Maintain go-around configuration until the acceleration altitude is reached. END

LOSS OF HYDRAULIC SYSTEM 1 AND 3 LAND AT THE NEAREST SUITABLE AIRPORT. Autopilot.................................................................. DISENGAGE NOTE: – Expect lower roll rates and lower speedbrake efficiency. – Do not accomplish the SPOILER FAULT procedure. – Do not command the engine 1 reverser. Relevant Inoperative Items: Autopilot Engine 1 Reverser Ground Spoilers L2 and R2 Multi Function Spoilers L3, R3, L4 and R4

Outboard aileron actuators. Outboard Brakes Rudder

Landing configuration: Slat/Flap................................................................ 5 Set VREF = VREF CAUTION:

• •

FULL

+ 10 KIAS.

AVOID LANDING WITH CROSSWIND COMPONENTS ABOVE 10 KT. MULTIPLY THE FULL FLAPS UNFACTORED LANDING DISTANCE BY 2.30.

AOM-1502-003

END

4-02-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Non Annunciated

Page 41

EMERGENCY AND ABNORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

NON ANNUNCIATED PROCEDURES

LOSS OF HYDRAULIC SYSTEM 2 AND 3 LAND AT THE NEAREST SUITABLE AIRPORT. NOTE: – Expect lower roll and pitch rates and lower speedbrake efficiency. – Do not accomplish the ELEVATOR FAULT and the SPOILER FAULT procedures. – Do not command the engine 2 reverser. Relevant Inoperative Items: Ailerons Autopilot Engine 2 Reverser Ground Spoilers L1 and R1 Inboard Brakes

Landing Gear Retraction and Normal Extension (Sys 2 fluid quantity loss only) Multi Function Spoilers L5 and R5 NoseWheel Steering R.H. Elevator

Plan a long final approach. Landing configuration: Landing Gear Lever.............................................. DOWN LANDING GEAR FAILED TO EXTEND AND LOCK DOWN?

No

Yes Alternate Gear Extension Lever........................... PULL

Slat/Flap................................................................ 5 CAUTION:

•

FULL

+ 10 KIAS.

AVOID LANDING WITH COMPONENTS ABOVE 10 KT.

CROSSWIND CONTINUED...

4-02-01 Copyright © by Embraer. Refer to cover page for details.

Page 42

Non Annunciated

REVISION 21

AOM-1502-003

Set VREF = VREF

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

...CONTINUED

•

MULTIPLY THE FULL FLAPS UNFACTORED LANDING DISTANCE BY 2.20.

If a go around is required: Landing Gear Lever.............................................. DOWN Slat/Flap................................................................ 4 Airspeed................................................................ VREF FULL + 10 KIAS NOTE: If hydraulic system 2 still has hydraulic fluid, the PTU may be available to retract the landing gear in the event of a go-around. END

LOSS OF PRESSURIZATION INDICATION CONDITION:

Cabin altitude or cabin ∆P is not being presented, or during use of the pressurization manual control.

NOTE: This table must be used to control the cabin altitude/∆P, when operating in manual mode only. AIRPLANE/CABIN ALTITUDE CONVERSION TABLE

AOM-1502-003

AIRPLANE ALTITUDE (ft) 10000 11000 12000 13000 14000 15000 16000 17000 18000 19000 20000

CABIN ALTITUDE (ft) 900 1000 1200 1300 1500 1700 1900 2100 2300 2600 2800

DIFFERENTIAL PRESSURE (psid) 4.2 4.5 4.8 5.1 5.3 5.6 5.8 6.0 6.2 6.4 6.6 CONTINUED...

4-02-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Non Annunciated

Page 43

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

AIRPLANE ALTITUDE (ft) 21000 22000 23000 24000 25000 26000 27000 28000 29000 30000 31000 32000 33000 34000 35000 36000 37000 38000 39000 40000 41000

CABIN ALTITUDE (ft) 3000 3300 3600 3900 4200 4500 4800 5100 5400 5700 6000 6300 6700 7000 7300 7600 8000 8000 8000 8000 8000

DIFFERENTIAL PRESSURE (psid) 6.7 6.9 7.0 7.1 7.2 7.3 7.4 7.5 7.5 7.6 7.7 7.7 7.7 7.8 7.8 7.8 7.8 8.0 8.1 8.3 8.4

4-02-01 Copyright © by Embraer. Refer to cover page for details.

Page 44

Non Annunciated

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

!O.B Nº 170-006/05 - AP quick disconnect button malfunctions

NON ANNUNCIATED LOSS OF ALL TRIMS AND AUTOPILOT Pitch Trim System 1 Cutout Button........................ PUSH IN PITCH TRIM NORMAL?

Yes

No

Relevant Inoperative Items:

Autopilot Pitch trim indication

Roll trim Yaw trim

END

Pitch Trim System 1 Cutout Button........................ PUSH OUT Pitch Trim System 2 Cutout Button........................ PUSH IN Relevant Inoperative Items: Autopilot Pitch trim indication

Roll trim Yaw trim

END

AOM-1502-003

"

4-02-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Non Annunciated

Page 45

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

ONE ENGINE INOPERATIVE APPROACH AND LANDING Descent: Landing Data ....................................................... SET Approach Aids....................................................... SET Altimeters ............................................................. SET/CHECK Landing Configuration: Landing Gear........................................................ DOWN Slat/Flap................................................................ 5 Set VREF = VREF

FULL

+ 20 KIAS.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.40.

UNFACTORED

If a go around is required: TOGA Button........................................................ PRESS Thrust Levers........................................................ TO/GA Rotate the airplane following the flight director guidance. NOTE: In case of flight director guidance is inoperative, rotate the airplane to 8° nose up. Slat/Flap................................................................ 2

4-02-01 Copyright © by Embraer. Refer to cover page for details.

Page 46

Non Annunciated

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

OXYGEN LEAKAGE CONDITION:

Evidence of oxygen leakage through the crew masks, mask hose, flow indicator (blinker), or oxygen lines.

No Smoking............................................................ ON Oxygen Test/Reset Button...................................... ACTUATE Altitude.................................................................... AS REQUIRED END

PARTIAL OR GEAR UP LANDING NOTE: – Plan to land on available gear. – Burn off fuel to reduce touchdown speed. Prior to approach: Cabin Crew........................................................... NOTIFY Aural Warning CBs (C7; C31).............................. PULL APU....................................................................... OFF Pressurization Dump Button ................................ PUSH IN Landing Configuration: Landing Gear Lever.............................................. DOWN Slat/Flap................................................................ FULL Just Before Touchdown: Cabin..................................................................... ANNOUNCE IMPACT After Landing: Thrust Levers........................................................ IDLE Start/Stop Selectors.............................................. STOP Fire Extinguishing Handles................................... PULL and ROTATE

AOM-1502-003

Emergency Evacuation......................................... ANNOUNCE Batteries................................................................ OFF CONTINUED...

4-02-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Non Annunciated

Page 47

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

If a go around is required: Landing Gear Lever.............................................. DOWN END

STRUCTURAL DAMAGE LAND AT THE NEAREST SUITABLE AIRPORT. Airspeed.................................................................. MAX VA Maneuvering speed (VA) table: VA - EMBRAER 170 !EMBRAER 170 Models

ALTITUDE (ft) ABOVE 34000 34000 30000 28000 24000 20000 0

SPEED (KIAS) MMO = 0.82 285 272 270 256 245 240 "

VA - EMBRAER 175 !EMBRAER 175 Models

SPEED (KIAS) MMO = 0.82 287 284 277 268 262 254 CONTINUED...

4-02-01 Copyright © by Embraer. Refer to cover page for details.

Page 48

Non Annunciated

REVISION 21

AOM-1502-003

ALTITUDE (ft) ABOVE 34000 34000 30000 25000 20000 15000 10000

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

...CONTINUED

ALTITUDE (ft) 5000 0

SPEED (KIAS) 248 242 "

Avoid high maneuvering loads. FUSELAGE IS DAMAGED?

No

Yes Altitude.................................................................... 10000 ft OR MEA, WHICHEVER IS HIGHER When reaching 10000 ft: Pressurization Dump Button................................. PUSH IN

Establish landing configuration early.

AOM-1502-003

END

4-02-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Non Annunciated

Page 49

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

UNRELIABLE AIRSPEED Autothrottle.............................................................. DISENGAGE Avoid quick Thrust Lever movements. Autopilot.................................................................. DISENGAGE Flight Director.......................................................... OFF Yaw Damper........................................................... OFF CAUTION: AVOID USING THE SPEEDBRAKE. Attitude/Thrust......................................................... ADJUST Maintain airplane control. Refer to Unreliable Airspeed tables. Altitude and/or Vertical Speed indications may also be unreliable. Ground speed indication is available on the PFD for reference. GPS altitude may also be used as a reference if PFD indication is unreliable.

UNRELIABLE AIRSPEED TABLES CLIMB, Flaps UP, CLB-1 Thrust Rating Mode

0

(FT) Pitch ATT

(250 KIAS)

V/S (ft/min)

10000

Pitch ATT

(250 KIAS)

V/S (ft/min)

20000

Pitch ATT

(290 KIAS)

V/S (ft/min)

30000

Pitch ATT

(0.70 Mach)

V/S (ft/min)

40000

Pitch ATT

(0.70 Mach)

V/S (ft/min)

50000

60000

WEIGHT (LB) 70000 80000

85000

15

13

12

12

11

6200

5100

4300

3600

3300

8

7

7

7

7

3200

2700

2200

1800

1700

5

5

5

5

5

3100

2600

2000

1700

1400

5

5

5

5

5

2400

1900

1400

1000

700

-

-

-

5

5

900

500

CONTINUED...

4-02-01 Copyright © by Embraer. Refer to cover page for details.

Page 50

Non Annunciated

REVISION 21

AOM-1502-003

PRESSURE ALTITUDE

EMERGENCY AND ABNORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

NON ANNUNCIATED PROCEDURES

...CONTINUED

CRUISE, Flaps UP, %N1 for Level Flight PRESSURE ALTITUDE 50000

(FT) 10000

(250 KIAS) 15000

(270 KIAS) 20000

(270 KIAS) 25000

(270 KIAS) 30000

(0.70 Mach) 35000

(0.70 Mach) 40000

(0.70 Mach)

60000

WEIGHT (LB) 70000 80000

85000

Pitch ATT

1

2

3

4

4

%N1

64.3

65.2

66.4

67.9

68.8

Pitch ATT

1

2

2

3

3

%N1

71.2

71.8

72.8

74.4

75.3

Pitch ATT

1

2

2

3

3

%N1

75.1

75.8

77.2

78.4

79

Pitch ATT

1

2

2

3

3

%N1

78.6

79.8

80.9

82.1

82.8

Pitch ATT

1

2

3

3

4

%N1

81.4

82.6

84.0

85.7

86.8

Pitch ATT

2

3

4

5

5

%N1

81.4

83.1

85.7

88.8

91.0

-

-

-

Pitch ATT

3

4

%N1

83.8

87.0

DESCENT, Flaps UP, IDLE Thrust PRESSURE ALTITUDE

AOM-1502-003

0

(FT) Pitch ATT

(250 KIAS)

V/S (ft/min)

10000

Pitch ATT

(250 KIAS)

V/S (ft/min)

20000

Pitch ATT

(290 KIAS)

V/S (ft/min)

30000

Pitch ATT

(0.70 Mach)

V/S (ft/min)

50000

60000

WEIGHT (LB) 70000 80000

85000

-3

-2

-1

0

0

-2100

-1800

-1700

-1600

-1500

-2

-1

0

1

2

-1600

-1400

-1300

-1200

-1200

-4

-3

-3

-2

-1

-3000

-3000

-3000

-2800

-2700

-3

-2

-1

-1

0

-3000

-3000

-3000

-3000

-3000

CONTINUED...

4-02-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Non Annunciated

Page 51

EMERGENCY AND ABNORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

NON ANNUNCIATED PROCEDURES

...CONTINUED PRESSURE ALTITUDE (FT) Pitch ATT 40000

(0.70 Mach)

V/S (ft/min)

50000

60000

WEIGHT (LB) 70000 80000

0

1

2

2

-2700

-2600

-2600

-2600

85000 -

HOLDING, %N1 for Level Flight PRESSURE ALTITUDE (FT) Pitch ATT 5000

10000

%N1 KIAS

50000 3

60000 4

54.8 210

56.4 210

WEIGHT (LB) 70000 80000 5 6

58.4 210

60.4 210

85000 6

61.3 210

Pitch ATT

3

4

5

6

6

%N1 KIAS

58.1 210

60.0 210

62.2 210

64.5 210

65.4 210

TERMINAL AREA (5000FT Pressure Altitude), Gear UP, %N1 for Level Flight SLAT/FLAP POSITION

SLAT/FLAP 0

(VREF FULL + 60) SLAT/FLAP 1

(VREF FULL + 35) SLAT/FLAP 2

(VREF FULL + 25 SLAT/FLAP 3

(VREF FULL + 15) SLAT/FLAP 4

(VREF FULL + 10)

WEIGHT (LB) 50000

60000

70000

80000

Pitch ATT

6

7

7

8

%N1

49.5

53.4

56.9

60.0

Pitch ATT

6

7

8

8

%N1

52.0

56.1

59.8

63.5

Pitch ATT

6

7

7

8

%N1

52.2

56.5

60.3

64.2

Pitch ATT

4

5

5

6

%N1

55.0

59.3

63.4

67.3

Pitch ATT

6

7

7

7

%N1

55.2

59.5

63.7

67.6

CONTINUED...

4-02-01 Copyright © by Embraer. Refer to cover page for details.

Page 52

Non Annunciated

REVISION 21

AOM-1502-003

(VREF FULL + INCREMENT)

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES NON ANNUNCIATED PROCEDURES

...CONTINUED

FINAL APPROACH (1500FT Pressure Altitude), Gear Down, %N1 for 3° GLIDESLOPE SLAT/FLAP POSITION

(VREF FULL + INCREMENT) SLAT/FLAP 5

(VREF FULL + 10)

WEIGHT (LB) 50000

60000

70000

80000

Pitch ATT

4

4

4

4

%N1

45.8

50.3

53.7

56.9

SLAT/FLAP FULL

Pitch ATT

0

0

0

1

(VREF FULL + 10)

%N1

52.5

56.5

60.0

63.4

NOTE: With the airplane stabilized under correct pitch attitude and power setting, the crew should crosscheck the instruments in order to identify any possible reliable instrument. In case a reliable source is identified, ADS reversion may be attempted. END

VOLCANIC ASH

LAND AT THE NEAREST SUITABLE AIRPORT. Volcanic Ash Area................................................... EXIT/AVOID Consider performing a 180° turn. Crew Oxygen Masks (if necessary)........................ DON, 100% If a significant amount of volcanic ash fills the cockpit, or if there is a strong smell of sulphur, don an oxygen mask and select 100%. Ignition Selectors.................................................... OVRD Autothrottle.............................................................. DISENGAGE Ice Protection Mode Selector................................. ON

AOM-1502-003

If altitude permits: Thrust Lever.......................................................... IDLE APU......................................................................... START Recirculation Button................................................ PUSH OUT CONTINUED...

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REVISION 21

Non Annunciated

Page 53

EMERGENCY AND ABNORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

NON ANNUNCIATED PROCEDURES

...CONTINUED

ITT........................................................................... MONITOR ITT INCREASING EVEN WITH AFFECTED ENGINE IN IDLE?

No

Yes ENGINE SHUTDOWN Procedure........................... ACCOMPLISH

ANY ENGINE FLAMEOUT?

No

Yes Ice Protection Mode Selector.................................. AUTO ENG 1 (2) FAIL or DUAL ENGINE FAILURE Procedure................................................................ ACCOMPLISH

ABNORMAL AIRSPEED INDICATIONS?

No

Yes UNRELIABLE AIRSPEED Procedure..................... ACCOMPLISH END

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Page 54

Non Annunciated

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE GENERAL (CARGO COMPARTMENT/DOORS/LIGHTING) TABLE OF CONTENTS Block

Page

WARNING DOOR CRG FWD (AFT) OPEN.............................. 4-03-01......

1

DOOR PAX (SERV) FWD (AFT) OPEN .................. 4-03-01......

2

CAUTION DOOR CENTER (FWD) EBAY OPEN ..................... DOOR HYD OPEN ................................................ EMER LT NOT ARMED.......................................... EMER LT ON ........................................................

3 3 3 3

4-03-01...... 4-03-01...... 4-03-01...... 4-03-01......

ADVISORY MAU load 15.3 and on OR POST-MOD SB 170-31-0002

AOM-1502-003

DOOR FUELING OPEN ........................................ Crew Awareness EMER LT BATT FAULT ......................................... Crew Awareness

4-03-01-TOC Copyright © by Embraer. Refer to cover page for details.

REVISION 13

Table of Contents

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

4-03-01-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 13

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

DOOR CRG FWD (AFT) OPEN NORMAL PRESSURIZATION?

No

Yes

END

LAND AT THE NEAREST SUITABLE AIRPORT. Altitude.................................................................... 10000 ft OR MEA, WHICHEVER IS HIGHER At 10000 ft : Pressurization Dump Button................................. PUSH IN

AOM-1502-003

END

4-03-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 11

Airplane General (Cargo Compartment/Doors/Lighting)

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

DOOR PAX (SERV) FWD (AFT) OPEN Fstn Belts Signs...................................................... ON NORMAL PRESSURIZATION?

No

Yes Check the affected door lock and latch indicators. MINIMUM OF 2 INDICATORS IN GREEN?

No

Yes

END

LAND AT THE NEAREST SUITABLE AIRPORT. Altitude.................................................................... 10000 ft OR MEA, WHICHEVER IS HIGHER At 10000 ft: Pressurization Dump Button................................. PUSH IN

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Page 2

Airplane General (Cargo Compartment/Doors/Lighting)

REVISION 11

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

DOOR CENTER (FWD) EBAY OPEN NORMAL PRESSURIZATION?

No

Yes

END

Altitude.................................................................... 10000 ft OR MEA, WHICHEVER IS HIGHER END

DOOR HYD OPEN Airspeed.................................................................. MAX 250 KIAS END

EMER LT NOT ARMED Emergency Lights................................................... ARMED END

EMER LT ON

AOM-1502-003

Emergency Lights................................................... OFF, then ARMED

4-03-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 11

Airplane General (Cargo Compartment/Doors/Lighting)

Page 3

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

4-03-01 Copyright © by Embraer. Refer to cover page for details.

Page 4

Airplane General (Cargo Compartment/Doors/Lighting)

REVISION 11

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

!MAU load 15.3 and on OR POST-MOD SB 170-31-0002

DOOR FUELING OPEN Crew Awareness. END "

EMER LT BATT FAULT Crew Awareness.

AOM-1502-003

END

4-03-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 11

Airplane General (Cargo Compartment/Doors/Lighting)

Page 5

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

4-03-01 Copyright © by Embraer. Refer to cover page for details.

Page 6

Airplane General (Cargo Compartment/Doors/Lighting)

REVISION 11

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AMS - PNEUMATIC/AIR CONDITIONING/PRESSURIZATION TABLE OF CONTENTS Block

Page

WARNING

AOM-1502-003

CABIN ALTITUDE HI ............................................. 4-03-02......

1

CAUTION AMS CTRL FAIL .................................................... BLEED 1 (2) FAIL .................................................. BLEED 1 (2) LEAK ................................................ BLEED 1 (2) OVERPRESS .................................... BLEED APU LEAK................................................. CABIN DIFF PRESS FAIL...................................... CENTER EBAY FANS FAIL.................................... CRG FWD VENT FAIL ........................................... FWD EBAY FANS FAIL .......................................... PACK 1 (2) FAIL .................................................... PACK 2 LEAK ....................................................... PRESN AUTO FAIL ............................................... PRESN MAN FAIL ................................................. PRESSURIZATION CONVERSION TABLE ............. RECIRC SMK DET FAIL ........................................

4-03-02...... 4-03-02...... 4-03-02...... 4-03-02...... 4-03-02...... 4-03-02...... 4-03-02...... 4-03-02...... 4-03-02...... 4-03-02...... 4-03-02...... 4-03-02...... 4-03-02...... 4-03-02...... 4-03-02......

ADVISORY AMS CTRL FAULT ................................................ BLEED 1 (2) OFF ................................................. PACK 1 (2) OFF ................................................... PRESN AUTO FAULT ........................................... RAM AIR FAULT ................................................... XBLEED FAIL ....................................................... XBLEED SW OFF.................................................

Crew Awareness 4-03-02...... 13 4-03-02...... 13 Crew Awareness Crew Awareness Crew Awareness Crew Awareness

2 2 3 4 5 7 8 8 8 9 9 10 11 11 13

4-03-02-TOC Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Table of Contents

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

4-03-02-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

CABIN ALTITUDE HI EICAS Indication: Cabin Altitude indication in red. Aural Warning:

CABIN

Crew Oxygen Masks............................................ DON, 100% Crew Communication........................................... ESTABLISH Altitude.................................................................. 10000 ft or MEA, WHICHEVER IS HIGHER Thrust Levers........................................................ IDLE Speed Brake......................................................... FULL OPEN Airspeed................................................................ MAX/ APPROPRIATE Transponder.......................................................... 7700 ATC....................................................................... NOTIFY Cabin Altitude.......................................................... MONITOR CABIN ALTITUDE REACHES 14500 ft?

No

Yes Passenger Oxygen Selector................................... OVRD

At 10000 ft: Pressurization DUMP Button................................ PUSH

AOM-1502-003

END

4-03-02 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

AMS - Pneumatic/Air Conditioning/Pressurization

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

AMS CTRL FAIL CONDITION:

Cabin Pressurization and temperature control is lost.

Icing Conditions...................................................... EXIT/AVOID Altitude.................................................................... 10000 ft OR MEA, WHICHEVER IS HIGHER NOTE: Monitor Cabin Altitude and increase rate of descent accordingly. An emergency descent may be required. At 10000 ft: Pressurization Dump Button................................. PUSH IN NOTE: – Assisted crossbleed start is not available. – Pneumatic assisted engine start with APU is not available. END

BLEED 1 (2) FAIL Affected Bleed Button............................................. PUSH OUT ..........................................Wait 1 minute.......................................... BLEED 1 (2) FAIL MESSAGE EXTINGUISHES?

No

Yes Affected Bleed Button............................................. PUSH IN BLEED 1(2) FAIL MESSAGE REMAINS EXTINGUISHED?

No

Yes

CONTINUED...

4-03-02 Copyright © by Embraer. Refer to cover page for details.

Page 2

AMS - Pneumatic/Air Conditioning/Pressurization

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

...CONTINUED

Affected Bleed Button............................................. PUSH OUT

BOTH BLEEDS AFFECTED?

No

Yes Icing Conditions....................................................... EXIT/AVOID APU......................................................................... START Altitude.................................................................... MAX 15000 ft END

Altitude.................................................................... MAX 31000 ft

Operative Bleed Button........................................... PUSH OUT, then IN END

BLEED 1 (2) LEAK Light:

Amber striped bar illuminates inside the affected bleed button. Affected Bleed Button............................................. PUSH OUT APU Bleed Button (if applicable)............................ PUSH OUT XBleed Button......................................................... PUSH OUT Icing Conditions...................................................... EXIT/AVOID Altitude.................................................................... MAX 31000 ft

.........................................Wait 3 minutes.........................................

AOM-1502-003

BLEED 1 (2) LEAK MESSAGE EXTINGUISHES?

Yes

No CONTINUED...

4-03-02 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

AMS - Pneumatic/Air Conditioning/Pressurization

Page 3

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

END

NOTE: Consider the possibility of leaking occurring in the opposite side. Opposite Side Bleed Button................................... PUSH OUT APU Bleed Button................................................... PUSH OUT Altitude.................................................................... 10000 FT OR MEA WHICHEVER IS HIGHER At 10000 ft: Pressurization Dump Button................................... PUSH IN END

BLEED 1 (2) OVERPRESS

Affected Bleed Button............................................. PUSH OUT then IN BLEED 1 (2) OVERPRESS MESSAGE EXTINGUISHES?

No

Yes

CONTINUED...

4-03-02 Copyright © by Embraer. Refer to cover page for details.

Page 4

AMS - Pneumatic/Air Conditioning/Pressurization

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

...CONTINUED

Affected Bleed Button............................................. PUSH OUT APU Bleed Button (if applicable)............................ PUSH OUT XBleed Button......................................................... PUSH OUT Icing Conditions...................................................... EXIT/AVOID Altitude.................................................................... MAX 31000 ft BLEED 1 (2) OVERPRESS MESSAGE EXTINGUISHES?

No

Yes

END

Associated Thrust Lever......................................... IDLE Transponder............................................................ TA ONLY When applicable: ONE ENGINE INOPERATIVE APPROACH AND LANDING Procedure.......................................... ACCOMPLISH END

BLEED APU LEAK APU Bleed Button................................................... PUSH OUT .........................................Wait 3 minutes......................................... BLEED APU LEAK MESSAGE EXTINGUISHES?

No

Yes

AOM-1502-003

END

CONTINUED...

4-03-02 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

AMS - Pneumatic/Air Conditioning/Pressurization

Page 5

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

APU Emergency Stop Button................................. PUSH IN APU......................................................................... OFF BLEED APU LEAK MESSAGE EXTINGUISHES?

No

Yes END

Bleed 1 Button........................................................ PUSH OUT XBleed Button......................................................... PUSH OUT Verify BLEED 1 OFF and XBLEED SW OFF messages displayed on EICAS. Icing Conditions...................................................... EXIT/AVOID Altitude.................................................................... MAX 31000 ft

4-03-02 Copyright © by Embraer. Refer to cover page for details.

Page 6

AMS - Pneumatic/Air Conditioning/Pressurization

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

CABIN DIFF PRESS FAIL EICAS Indication: Abnormal cabin altitude indication may be presented. If Cabin Differential Pressure red limit is reached: CABIN DIFFERENTIAL PRESSURE POSITIVE?

No

Yes Pack 1 Button.......................................................... PUSH OUT Pack 2 Button.......................................................... PUSH OUT Altitude.................................................................... 10000 ft OR MEA, WHICHEVER IS HIGHER END

Airplane Descent Rate............................................ REDUCE

AOM-1502-003

END

4-03-02 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

AMS - Pneumatic/Air Conditioning/Pressurization

Page 7

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

CENTER EBAY FANS FAIL LAND AT THE NEAREST SUITABLE AIRPORT. END

CRG FWD VENT FAIL LAND AT THE NEAREST SUITABLE AIRPORT. END

FWD EBAY FANS FAIL TRU 1 (2) FAIL MESSAGE DISPLAYED?

No

Yes LAND AT THE NEAREST SUITABLE AIRPORT. END

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Page 8

AMS - Pneumatic/Air Conditioning/Pressurization

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

PACK 1 (2) FAIL Associated Temperature Controller........................ 12 O’CLOCK Affected Pack Button.............................................. PUSH OUT .........................................Wait 1 minute......................................... Affected Pack Button.............................................. PUSH IN PACK 1 (2) FAIL MESSAGE EXTINGUISHES?

No

Yes After 1 minute: Associated Temperature Controller...................... OPERATE NORMALLY END

Affected Pack Button.............................................. PUSH OUT Altitude.................................................................... MAX 31000 ft END

PACK 2 LEAK Pack 2 Button......................................................... PUSH OUT Altitude.................................................................... MAX 31000 ft .........................................Wait 3 minutes......................................... PACK 2 LEAK MESSAGE EXTINGUISHES?

No

Yes

AOM-1502-003

END CONTINUED...

4-03-02 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

AMS - Pneumatic/Air Conditioning/Pressurization

Page 9

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Icing Conditions...................................................... EXIT/AVOID Bleed 2 Button........................................................ PUSH OUT XBleed Button......................................................... PUSH OUT END

PRESN AUTO FAIL EICAS Indication: Landing Field Elevation indications showing amber dashes. Pressurization Mode Selector................................. MAN, THEN AUTO PRESN AUTO FAIL MESSAGE EXTINGUISHES?

No

Yes

END

Pressurization Mode Selector................................. MAN Cabin Alt Controller................................................. AS REQUIRED Operate the cabin altitude control knob to set pressurization according to the PRESSURIZATION CONVERSION TABLE. When appropriate: Cabin Alt Controller............................................... HOLD UP FOR 50 s

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Page 10

AMS - Pneumatic/Air Conditioning/Pressurization

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

PRESN MAN FAIL Altitude ................................................................... 10000 ft OR MEA, WHICHEVER IS HIGHER At 25000 ft: Pack 1 Button....................................................... PUSH OUT At 10000 ft: Pack 2 Button....................................................... PUSH OUT END

PRESSURIZATION CONVERSION TABLE NOTE: This table must be used to control the cabin altitude/ ∆P when operating in manual mode only. AIRPLANE/CABIN ALTITUDE CONVERSION TABLE

AOM-1502-003

AIRPLANE ALTITUDE (ft) 10000 11000 12000 13000 14000 15000 16000 17000 18000 19000 20000 21000 22000 23000

CABIN ALTITUDE (ft) 900 1000 1200 1300 1500 1700 1900 2100 2300 2600 2800 3000 3300 3600

DIFFERENTIAL PRESSURE (psid) 4.2 4.5 4.8 5.1 5.3 5.6 5.8 6.0 6.2 6.4 6.6 6.7 6.9 7.0 CONTINUED...

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REVISION 21

AMS - Pneumatic/Air Conditioning/Pressurization

Page 11

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

AIRPLANE ALTITUDE (ft) 24000 25000 26000 27000 28000 29000 30000 31000 32000 33000 34000 35000 36000 37000 38000 39000 40000 41000

CABIN ALTITUDE (ft) 3900 4200 4500 4800 5100 5400 5700 6000 6300 6700 7000 7300 7600 8000 8000 8000 8000 8000

DIFFERENTIAL PRESSURE (psid) 7.1 7.2 7.3 7.4 7.5 7.5 7.6 7.7 7.7 7.7 7.8 7.8 7.8 7.8 8.0 8.1 8.3 8.4

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Page 12

AMS - Pneumatic/Air Conditioning/Pressurization

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

RECIRC SMK DET FAIL Recirc Fan Button................................................... PUSH OUT END

AMS CTRL FAULT Crew Awareness. END

BLEED 1 (2) OFF Altitude.................................................................... MAX 31000 ft END

PACK 1 (2) OFF Altitude.................................................................... MAX 31000 ft

AOM-1502-003

END

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REVISION 21

AMS - Pneumatic/Air Conditioning/Pressurization

Page 13

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

PRESN AUTO FAULT Crew Awareness. END

RAM AIR FAULT Crew Awareness. END

XBLEED FAIL Crew Awareness. END

XBLEED SW OFF Crew Awareness.

4-03-02 Copyright © by Embraer. Refer to cover page for details.

Page 14

AMS - Pneumatic/Air Conditioning/Pressurization

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AUTOFLIGHT TABLE OF CONTENTS

AOM-1502-003

Block

Page

CAUTION AP FAIL................................................................. AP PITCH MISTRIM .............................................. AP PITCH TRIM FAIL ............................................ AP ROLL MISTRIM................................................ AT FAIL ................................................................. AT NOT IN HOLD .................................................. FD LATERAL MODE OFF ...................................... FD VERT MODE OFF............................................ SHAKER ANTICIPATED......................................... STALL PROT FAIL.................................................

4-03-03...... 4-03-03...... 4-03-03...... 4-03-03...... 4-03-03...... 4-03-03...... 4-03-03...... 4-03-03...... 4-03-03...... 4-03-03......

ADVISORY AFCS FAULT ........................................................ AFCS PANEL FAIL................................................ AFCS PANEL FAULT ............................................ AP FAULT............................................................. AP PITCH TRIM FAULT ........................................ AP RUDDER NOT AVAIL....................................... APPR 2 NOT AVAIL .............................................. AT FAULT ............................................................. FD FAIL................................................................ FD FAULT............................................................. SHAKER 1 (2) FAIL .............................................. STALL PROT FAULT ............................................. YD FAIL................................................................ YD FAULT ............................................................ YD OFF ................................................................

Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness

1 1 1 2 2 2 2 3 3 4

4-03-03-TOC Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Table of Contents

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

4-03-03-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 18

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AP FAIL Fly the airplane manually. RVSM capability is lost. NOTE: The AP may be available for re-engagement 10 seconds after disengagement. END

AP PITCH MISTRIM Control Wheel......................................................... HOLD FIRMLY A/P Disc Button ..................................................... PRESS Pitch Trim................................................................ AS REQUIRED Autopilot.................................................................. AS REQUIRED END

AP PITCH TRIM FAIL Control Wheel......................................................... HOLD FIRMLY A/P Disc Button....................................................... PRESS Pitch Trim................................................................ AS REQUIRED Autopilot.................................................................. AS REQUIRED

AOM-1502-003

END

4-03-03 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Autoflight

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

AP ROLL MISTRIM Roll Trim.................................................................. AS REQUIRED END

AT FAIL Operate thrust levers manually. NOTE: The AT may be available for re-engagement 10 seconds after disengagement. END

AT NOT IN HOLD Disengage the autothrottle. END

FD LATERAL MODE OFF Select a flight director lateral mode.

4-03-03 Copyright © by Embraer. Refer to cover page for details.

Page 2

Autoflight

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

FD VERT MODE OFF Select a flight director vertical mode. END

SHAKER ANTICIPATED Avoid side slipping the airplane. AIRSPEED ABOVE 0.5 M?

No

Yes Airspeed.................................................................. MIN 250 KIAS NOTE: Above 0.5 M, stick shaker and LSA are not Available.

FLAP FAIL MESSAGE PRESENTED?

No

Yes FLAP FAIL Procedure............................................. ACCOMPLISH END

SLAT FAIL MESSAGE PRESENTED?

No

Yes SLAT FAIL Procedure.............................................. ACCOMPLISH

AOM-1502-003

END CONTINUED...

4-03-03 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Autoflight

Page 3

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Landing Configuration: Slat/Flap................................................................ FULL Set VREF

FULL.

NOTE: Limit bank angle to 20° maximum. END

STALL PROT FAIL Condition:

Stick Shaker and AOA Limiting are inoperative.

Avoid side slipping the airplane. Landing Configuration: For flaps 5, set VREF = VREF

FULL

+ 15 KIAS.

CAUTION: MULTIPLY THE FULL FLAPS UNFACTORED LANDING DISTANCE BY 1.40. For flaps FULL, set VREF = VREF FULL + 10 KIAS. CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.22.

UNFACTORED

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Page 4

Autoflight

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AFCS FAULT Crew Awareness END

AFCS PANEL FAIL Crew Awareness. END

AFCS PANEL FAULT Crew Awareness. END

AP FAULT Crew Awareness. END

AP PITCH TRIM FAULT Crew Awareness.

AOM-1502-003

END

4-03-03 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Autoflight

Page 5

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

AP RUDDER NOT AVAIL Crew Awareness. END

APPR 2 NOT AVAIL Crew Awareness. END

AT FAULT Crew Awareness. END

FD FAIL Crew Awareness. END

FD FAULT Crew Awareness.

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Page 6

Autoflight

REVISION 21

AOM-1502-003

END

EMERGENCY AND ABNORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

ANNUNCIATED PROCEDURES

SHAKER 1 (2) FAIL INADVERTENT SHAKER ACTUATION?

No

Yes NOTE: – Autopilot may disengage. Affected Shaker Cutout Button............................... PUSH IN END

END

STALL PROT FAULT Crew Awareness. END

YD FAIL Crew Awareness.

AOM-1502-003

END

4-03-03 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Autoflight

Page 7

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

YD FAULT Crew Awareness. END

YD OFF Crew Awareness.

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Page 8

Autoflight

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AUXILIARY POWER UNIT TABLE OF CONTENTS Block

Page

CAUTION MAU load 21.2 and on OR POST-MOD SB 170-31-0028

AOM-1502-003

APU ALTITUDE EXCEED ...................................... APU FAIL .............................................................. APU FAULT........................................................... APU OIL HI TEMP ................................................. APU OIL LO PRESS..............................................

4-03-04...... 4-03-04...... 4-03-04...... 4-03-04...... 4-03-04......

1 1 2 3 3

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REVISION 20

Table of Contents

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

4-03-04-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 20

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

!MAU load 21.2 and on OR POST-MOD SB 170-31-0028

APU ALTITUDE EXCEED APU IS ESSENTIAL FOR FLIGHT?

No

Yes Descend until the message is no longer displayed. END

APU......................................................................... OFF END "

APU FAIL APU FAILED DURING START?

No

Yes APU can be restarted according to the APU starter limitations. END

APU......................................................................... OFF Do not restart the APU.

AOM-1502-003

END

4-03-04 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Auxiliary Power Unit

Page 1

EMERGENCY AND ABNORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

ANNUNCIATED PROCEDURES

APU FAULT EICAS Indication: Abnormal APU presented. ABNORMAL INDICATION?

EGT

indication

may

be

No

Yes APU Bleed Button................................................... PUSH OUT ..........................................Wait 1 minute.......................................... ABNORMAL INDICATION REMAINS?

No

Yes

APU Emergency Stop Button................................. PUSH IN APU......................................................................... OFF END

NOTE: If the APU is not essential for the flight, turn off the APU.

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Page 2

Auxiliary Power Unit

REVISION 20

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

APU OIL HI TEMP APU FAULT Procedure........................................... ACCOMPLISH END

APU OIL LO PRESS APU FAULT Procedure........................................... ACCOMPLISH

AOM-1502-003

END

4-03-04 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Auxiliary Power Unit

Page 3

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

4-03-04 Copyright © by Embraer. Refer to cover page for details.

Page 4

Auxiliary Power Unit

REVISION 20

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

ELECTRICAL TABLE OF CONTENTS Block

Page

WARNING BATT 1 (2) OVERTEMP......................................... 4-03-05......

1

BATT 1-2 OFF ....................................................... 4-03-05......

1

BATT DISCHARGING ............................................ 4-03-05......

1

ELEC EMERGENCY.............................................. 4-03-05......

1

AOM-1502-003

CAUTION AC BUS 1 OFF...................................................... AC BUS 2 OFF...................................................... AC ESS BUS OFF................................................. AC STBY BUS OFF............................................... APU GEN OFF BUS .............................................. BATT 1 (2) DISCHARGING .................................... BATT 1 (2) TEMP SENS FAULT ............................. BATT 1 OFF .......................................................... BATT 2 OFF .......................................................... DC BUS 1 OFF ..................................................... DC BUS 2 OFF ..................................................... DC ESS BUS 1 OFF.............................................. DC ESS BUS 2 OFF.............................................. DC ESS BUS 3 OFF.............................................. GPU CONNECTED ............................................... IDG 1 (2) OFF BUS ............................................... IDG 1 (2) OIL ........................................................ INVERTER FAIL .................................................... RAT FAIL............................................................... TRU 1 (2) FAIL ...................................................... TRU ESS FAIL ......................................................

4-03-05...... 5 4-03-05...... 5 4-03-05...... 6 4-03-05...... 6 4-03-05...... 7 4-03-05...... 7 Crew Awareness 4-03-05...... 8 4-03-05...... 8 4-03-05...... 8 4-03-05...... 9 4-03-05...... 10 4-03-05...... 11 4-03-05...... 13 4-03-05...... 14 4-03-05...... 14 4-03-05...... 15 Crew Awareness Crew Awareness 4-03-05...... 15 4-03-05...... 16

ADVISORY LOAD SHED......................................................... Crew Awareness

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REVISION 21

Table of Contents

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL Block

Page

4-03-05-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 21

AOM-1502-003

ADVISORY REMOTE CB TRIP................................................ Crew Awareness SPDA FAIL ........................................................... 4-03-05...... 16

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

BATT 1 (2) OVERTEMP Associated Battery................................................ OFF NOTE: Do not start the APU. END

BATT 1-2 OFF LAND AT THE NEAREST SUITABLE AIRPORT. NOTE: APU start is not available. END

BATT DISCHARGING LAND AT THE NEAREST SUITABLE AIRPORT. END

ELEC EMERGENCY LAND AT THE NEAREST SUITABLE AIRPORT. Airspeed.................................................................. MIN 150 KIAS !O.B Nº 170-011/08 - IESS operation with RAT deployed

NOTE: When flying below 200 KIAS the IESS attitude indication may oscillate. At any time this oscillation occurs perform the IESS ATTITUDE OSCILLATION WITH RAT DEPLOYED procedure.

AOM-1502-003

"

APU......................................................................... START CONTINUED...

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REVISION 21

Electrical

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

IDG 1 Selector........................................................ OFF, THEN AUTO IDG 2 Selector........................................................ OFF, THEN AUTO Emergency Lights................................................... OFF CAUTION: ONLY TWO APU START ATTEMPTS ARE ALLOWED. ELEC EMERGENCY MESSAGE PERSISTS?

No

Yes

BATT DISCHARGING MESSAGE PRESENTED?

No

Yes RAT Manual Deploy Lever...................................... PULL TRU 1 Switch ......................................................... OFF TRU 2 Switch ......................................................... OFF

Icing Conditions....................................................... EXIT/AVOID Altitude.................................................................... 10000 ft OR MEA, WHICHEVER IS HIGHER Relevant Inoperative Items:

AOA Limit Autopilot Autothrottle CCD 2

IRS 2 MCDU 1 Multi Function Spoilers L3, R3, L4, R4, L5 and R5 NAVCOM 2 Nosewheel Steering Pack 1 and 2 CONTINUED...

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Page 2

Electrical

REVISION 21

AOM-1502-003

ADS 1 and 2 Anti-Ice System

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

...CONTINUED

Display Unit 1, 4 and 5 Engine 1 and Engine 2 Reversers

Pax Masks Auto Deploy Radio Altimeters 1 and 2

FMS 1 Flight Director 1 and 2 Fuel AC Pump 1 GPS 1 Ground Spoilers L1, R1, L2 and R2 Hyd Sys 1 Elec Pump Hyd Sys 2 Elec Pump Hyd Sys 3 Elec Pump B Ice Detectors 1 and 2 Electromechanical Door Latch

Service Interphone System (Normal Mode) Speedbrake TAT 1 and 2 TCAS Yaw Damper Weather Radar Windshear Detection Windshield Heater 1 and 2 Windshield Wiper 1 and 2

NOTE: – Avoid side slipping the airplane. – On ground, use differential braking and rudder to steer the airplane. – The slats and flaps will operate at low rate. – The reinforced cockpit door can only be opened manually. Landing configuration: Emergency Lights................................................. ARMED Gnd Prox Flap Ovrd Button.................................. PUSH IN LG WRN INHIB Button......................................... PUSH IN Slat/Flap................................................................ 3 Set VREF = VREF FULL + 20 KIAS or 130 KIAS (whichever is higher). CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 2.10.

UNFACTORED

AOM-1502-003

If a go around is required: Slat/Flap................................................................ 3

CONTINUED...

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REVISION 21

Electrical

Page 3

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Airspeed................................................................ VREF FULL + 20 KIAS or 130 KIAS (whichever is higher) END

Flight Controls Mode Buttons (Spoilers, Elevators and Rudder).......................................................... PUSH IN, THEN OUT Landing configuration: Emergency Lights ................................................ ARMED Gnd Prox Flap Ovrd Button.................................. PUSH IN Slat/Flap................................................................ 3 Set VREF = VREF

FULL

+15 KIAS.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.31.

UNFACTORED

If a go around is required: Slat/Flap................................................................ 3 Airspeed................................................................ VREF FULL + 15 KIAS

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Page 4

Electrical

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AC BUS 1 OFF Relevant Inoperative Items: Fuel AC Pump 1 Hyd Sys 2 Elec Pump Ice Detector 1

Windshield Wiper 2 Windshield Heater 2

NOTE: – The slats will operate at low rate mode. – Fuel Crossfeed Low 2 is not available. When flying in icing conditions: Ice Protection Mode Selector............................... ON Two minutes after exiting icing conditions: Ice Protection Mode Selector........................... AUTO END

AC BUS 2 OFF Relevant Inoperative Items: Hyd Sys 1 Elec Pump Hyd Sys 3 Elec Pump B Ice Detector 2

Windshield Wiper 1 Windshield Heater 1

NOTE: The flaps will operate at low rate. When flying in icing conditions: Ice Protection Mode Selector............................... ON Two minutes after exiting icing conditions: Ice Protection Mode Selector........................... AUTO

AOM-1502-003

END

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REVISION 21

Electrical

Page 5

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

AC ESS BUS OFF TRU ESS Switch..................................................... OFF Relevant Inoperative Items: AC Fuel Pump 2 Hyd Sys 3 Elec Pump A NOTE: – The flaps and slats will extend at low rate mode. – Fuel Crossfeed Low 1 is not available. END

AC STBY BUS OFF Monitor the electrical system. Relevant Inoperative Items: Ignition 1A Ignition 2A NOTE: Engine Start, with batteries only, is not available.

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Page 6

Electrical

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

APU GEN OFF BUS APU Gen Button..................................................... PUSH OUT, THEN IN APU GEN OFF BUS MESSAGE EXTINGUISHES?

No

Yes

END

APU Gen Button..................................................... PUSH OUT END

BATT 1 (2) DISCHARGING Associated TRU Switch.......................................... OFF, THEN AUTO BATT 1 (2) DISCHARGING MESSAGE EXTINGUISHES?

No

Yes

END

Associated TRU Switch.......................................... OFF

AOM-1502-003

END

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REVISION 21

Electrical

Page 7

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

BATT 1 (2) TEMP SENS FAULT Crew Awareness. END

BATT 1 OFF Battery 1.................................................................. VERIFY ON NOTE: If battery 1 selector is off, APU start is not available. END

BATT 2 OFF Battery 2.................................................................. VERIFY AUTO END

DC BUS 1 OFF Autothrottle.............................................................. DISENGAGE Emergency Lights................................................... OFF Altitude.................................................................... MAX 31000 ft

ADS 1

Nosewheel Steering

Autopilot

Pax Oxy Masks Auto Deploy

Autothrottle 1

Pack 1

CCD 2

Pitch Trim Indication

Display Unit 1

PTU

Display Unit 4

Radio Altimeter 1

Engine 1 Reverser

Weather Radar CONTINUED...

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Page 8

Electrical

REVISION 21

AOM-1502-003

Relevant Inoperative Items:

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

...CONTINUED Hyd Sys 2 Elec Pump

Windshield Heater 2

MCDU 1

Windshield Wiper 2

Multi Function Spoiler L5 and R5

NOTE: The slats will operate at low rate. Landing Configuration: Emergency Lights................................................. ARMED Slat/Flap................................................................ FULL Set VREF

FULL.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.15.

UNFACTORED

On ground: Use differential braking and rudder to steer the airplane. END

DC BUS 2 OFF Autothrottle.............................................................. DISENGAGE Altitude.................................................................... MAX 31000 ft Relevant Inoperative Items:

AOM-1502-003

ADS 2 Autobrakes Autothrottle 2 Display Unit 5 Engine 2 Reverser Engines Vibration Indications Electromechanical Door Latch FMS 1 HF Transceiver Hyd Sys 1 Elec Pump Hyd Sys 3 Elec Pump B

Nosewheel Steering Pack 2 Pax Oxy Masks Auto Deploy Pedal Adjustment Switch Pitch Trim indication Radio Altimeter 2 Roll Trim TCAS Transponder 2 Windshield Heater 1 CONTINUED...

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REVISION 21

Electrical

Page 9

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Multi Function Spoilers L3, R3, L4 and R4 NAVCOM 2

Windshield Wiper 1

NOTE: The reinforced cockpit door can only be opened manually. Landing Configuration: Slat/Flap................................................................ FULL Set VREF

FULL.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.20.

UNFACTORED

On ground: Use differential braking and rudder to steer the airplane. END

DC ESS BUS 1 OFF LAND AT THE NEAREST SUITABLE AIRPORT. Icing Conditions...................................................... EXIT/AVOID Battery 1.................................................................. OFF

ADS 1

Ignition 1A

APU

Master Warning/Caution 1

Autopilot

MCDU 1 (except circuit breakers page)

Digital Audio Panel 1

Multi Function Spoilers L5 and R5

Display Unit 3

NAVCOM 1

Engine 1 Start Valve

Engine 1 oil pressure indication

Fuel Quantity 1 Indication

Outboard Brakes

Fwd LAV Smoke Detection

RAT Automatic Deployment

Hyd Sys 2 Depressurization Valve

Transponder 1

Hyd Sys 3 Elec Pump A

Weather Radar CONTINUED...

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Page 10

Electrical

REVISION 21

AOM-1502-003

Relevant Inoperative Items:

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

...CONTINUED

NOTE: – – – – –

Compass internal light will be lost. FADEC will set flight idle on ground. The flaps will operate at low rate. Engine 2 windmill start is not available. Thrust Reversers, Wing Anti-Ice and Ground Idle may not be available. – Expect lower roll rates and lower speedbrake efficiency. – Do not accomplish the SPOILER FAULT procedure.

Landing Configuration: Slat/Flap................................................................ FULL Set VREF

FULL.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.70.

UNFACTORED

On Ground: Brakes................................................................... APPLY NORMALLY END

DC ESS BUS 2 OFF LAND AT THE NEAREST SUITABLE AIRPORT. Icing Conditions ..................................................... EXIT/AVOID Battery 2.................................................................. OFF Relevant Inoperative Items:

AC Fuel Pump 1 ADS 3 Aft Lavatory Smoke Detection APU Fire Extinguishing APU Fuel Shutoff Valve AOM-1502-003

Aural Warning 2

Engine 1 and Engine 2 Reversers Engine 2 oil pressure indication Fuel Crossfeed Operation Fuel Quantity 2 Indication Hydraulic System 1 Depressurization Valve Ignition 2A CONTINUED...

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REVISION 21

Electrical

Page 11

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Autopilot CCD 1 DC Fuel Pump Digital Audio Panel 2 Display Unit 2

Inboard Brakes Master Warning/Caution 2 MCDU 2 Multi Function Spoilers L3, R3, L4 and R4 Pitch Trim Indication

NOTE: – – – –

The slats will operate at low rate. FADEC will set flight idle on ground. Engine 1 windmill start is not available. Thrust Reversers, Wing Anti-Ice and Ground Idle may not be available. – Expect lower roll rates and lower speedbrake efficiency. – Do not accomplish the SPOILER FAULT procedure. APU......................................................................... OFF

Landing Configuration: Slat/Flap................................................................ FULL Set VREF

FULL.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.80.

UNFACTORED

On Ground: Brakes................................................................... APPLY NORMALLY

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Page 12

Electrical

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

DC ESS BUS 3 OFF TRU ESS Switch..................................................... OFF DC ESS BUS 3 OFF MESSAGE EXTINGUISHES?

No

Yes

END

Relevant Inoperative Items: ADS 2

Landing Gear Override Switch

Fire Extinguisher Button Lights

Landing Gear Control Lever Locking Solenoid

Fuel Crossfeed Valve

PAX Address (Cabin Interphone and PA Handset)

Internal Light of all Switches

Rudder Trim

NOTE:

• • •

The flaps will operate at low rate. IESS Speed and Altitude tape are not available. The PA button on the Audio Control Panel lights green when selected, but Cabin Interphone and PA Handset are not available.

AOM-1502-003

END

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REVISION 21

Electrical

Page 13

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

GPU CONNECTED Before Taxi: GPU...................................................................... DISCONNECT END

IDG 1 (2) OFF BUS Affected IDG Selector............................................. OFF, THEN AUTO IDG 1 (2) OFF BUS MESSAGE EXTINGUISHES?

No

Yes

END

Affected IDG Selector ............................................ OFF APU......................................................................... AS REQUIRED

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Page 14

Electrical

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

IDG 1 (2) OIL Light:

Affected IDG light becomes amber.

Affected IDG Selector............................................. DISC APU......................................................................... AS REQUIRED END

INVERTER FAIL Crew Awareness. END

RAT FAIL Crew Awareness. END

TRU 1 (2) FAIL Affected TRU Switch............................................... OFF, THEN AUTO TRU 1 (2) FAIL MESSAGE EXTINGUISHES?

No

Yes

END

AOM-1502-003

Affected TRU Switch............................................... OFF

4-03-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Electrical

Page 15

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

END

TRU ESS FAIL TRU ESS Switch..................................................... OFF END

LOAD SHED Crew Awareness. END

REMOTE CB TRIP Crew Awareness. END

SPDA FAIL Both thrust reversers may be inoperative.

4-03-05 Copyright © by Embraer. Refer to cover page for details.

Page 16

Electrical

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

ENGINE TABLE OF CONTENTS Block

Page

AOM-1502-003

WARNING ENG 1 (2) OIL LO PRESS ..................................... 4-03-06......

1

ENG 1 (2) REV DEPLOYED .................................. 4-03-06......

1

CAUTION ENG 1 (2) CONTROL FAULT ................................. ENG 1 (2) FADEC OVERTEMP.............................. ENG 1 (2) FAIL...................................................... ENG 1 (2) FUEL IMP BYPASS ............................... ENG 1 (2) FUEL LO PRESS .................................. ENG 1 (2) NO DISPATCH ...................................... ENG 1 (2) OIL LO LEVEL ...................................... ENG 1 (2) REV FAIL.............................................. ENG 1 (2) REV PROT FAULT ................................ ENG 1 (2) REV TLA FAIL....................................... ENG 1 (2) START VLV OPEN ................................ ENG 1 (2) T2 HEAT FAIL ....................................... ENG 1 (2) TLA FAIL............................................... ENG EXCEEDANCE.............................................. ENG NO TAKEOFF DATA ...................................... ENG REF A-I DISAG ............................................. ENG REF ECS DISAG .......................................... ENG THR RATING DISAG ..................................... ENG TLA NOT TOGA ............................................

4-03-06...... 2 4-03-06...... 3 4-03-06...... 3 4-03-06...... 6 4-03-06...... 6 Crew Awareness Crew Awareness Crew Awareness Crew Awareness 4-03-06...... 9 4-03-06...... 9 4-03-06...... 10 4-03-06...... 10 Crew Awareness 4-03-06...... 11 4-03-06...... 11 4-03-06...... 12 Crew Awareness 4-03-06...... 12

ADVISORY ENG 1 (2) FADEC FAULT ..................................... ENG 1 (2) FUEL SW FAIL ..................................... ENG 1 (2) OIL IMP BYPASS ................................. ENG 1 (2) OIL SW FAIL ........................................ ENG 1 (2) SHORT DISPATCH...............................

Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness

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REVISION 20

Table of Contents

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

4-03-06-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 20

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

ENG 1 (2) OIL LO PRESS EICAS Indication: Oil pressure indication in red or amber may be presented. OIL PRESSURE INDICATION ABNORMAL?

No

Yes ENGINE SHUTDOWN Procedure........................... ACCOMPLISH

END

ENG 1 (2) REV DEPLOYED EICAS Indication: REV icon above the associated ITT indication. LAND AT THE NEAREST SUITABLE AIRPORT. Autothrottle.............................................................. DISENGAGE Associated Thrust Lever......................................... IDLE ANY BUFFETING NOTICED?

No

Yes Start/Stop Selector (affected engine)...................... STOP APU ........................................................................ START Fuel ........................................................................ BALANCE Autothrottle.............................................................. AS REQUIRED

AOM-1502-003

Transponder............................................................ TA ONLY When appropriate: ONE ENGINE INOPERATIVE APPROACH AND CONTINUED...

4-03-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Engine

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

LANDING Procedure.......................................... ACCOMPLISH END

ENG 1 (2) CONTROL FAULT Autothrottle.............................................................. DISENGAGE CAUTION: AVOID QUICK THRUST LEVER MOVEMENT, HIGH ENGINE THRUST AND THRUST REVERSER OPERATION ON THE AFFECTED ENGINE. ABLE TO CONTROL AFFECTED ENGINE THRUST?

No

Yes END

AFFECTED ENGINE THRUST STABLE AT IDLE?

No

Yes Associated Thrust Lever......................................... IDLE Transponder............................................................ TA ONLY Continue the flight monitoring engine parameters. When appropriate: ONE ENGINE INOPERATIVE APPROACH AND LANDING Procedure.......................................... ACCOMPLISH

ENGINE SHUTDOWN Procedure.......................... ACCOMPLISH

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Page 2

Engine

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

END

ENG 1 (2) FADEC OVERTEMP ENGINE PARAMETERS ABNORMAL?

No

Yes ENGINE SHUTDOWN Procedure........................... ACCOMPLISH

CAUTION: IF THE ENGINE DOES NOT SHUTDOWN, PULL (DO NOT ROTATE) THE ASSOCIATED FIRE-EXTINGUISHING HANDLE. NOTE: Exit and avoid icing conditions if the associated Fire Extinguishing Handle has been pulled.

END

ENG 1 (2) FAIL EICAS Indication: FAIL icon on N1 indication. EICAS Indication: Oil press indication in red. LAND AT THE NEAREST SUITABLE AIRPORT. Associated Thrust Lever......................................... IDLE ENGINE AUTO RELIGHTS?

No

Yes

AOM-1502-003

The EICAS message may be caused by a fuel leak. Fuel leak may be detected by either:

• • •

A fuel imbalance develops; or Excessive fuel flow in one of the engines; or Fuel quantity from one tank decreases at abnormal rate; or CONTINUED...

4-03-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Engine

Page 3

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

• •

Fuel smell; or Fuel spray from the wings.

NOTE: – If flight conditions permit, operate the engine at idle for 2 min prior to apply engine thrust. – During engine auto relight, if N2 is steady accelerating while ITT remains within start limit, the start is progressing normally. – During inflight starts, FADEC has no protection for hot starts, hung starts or failure to light off. – Crew must take appropriate action in case of abnormal engine indications. END

Associated Start/Stop Selector............................... STOP APU......................................................................... START Transponder............................................................ TA ONLY The EICAS message may be caused by a fuel leak. Fuel leak may be detected by either:

• • • • •

A fuel imbalance develops; or Excessive fuel flow in one of the engines; or Fuel quantity from one tank decreases at abnormal rate; or Fuel smell; or Fuel spray from the wings.

FUEL LEAK SUSPECTED?

No

Yes

Fuel Xfeed Selector................................................ OFF CONTINUED...

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Page 4

Engine

REVISION 21

AOM-1502-003

NOTE: Assume that fuel is leaking from tank associated to engine failed side.

AIRPLANE OPERATIONS MANUAL ...CONTINUED

LEAK ON THE RH TANK?

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

No

Yes

APU......................................................................... OFF ONE ENGINE INOPERATIVE APPROACH AND LANDING Procedure............................................... ACCOMPLISH END

APU......................................................................... AS REQUIRED ONE ENGINE INOPERATIVE APPROACH AND LANDING Procedure............................................... ACCOMPLISH END

RESTART CONSIDERED?

No

Yes ENGINE AIRSTART Procedure.............................. ACCOMPLISH

AOM-1502-003

END

NOTE: Engine failure may cause scavenge pump to stop fuel transfer to the Collector Box. The loss of fuel transfer system to the Collector Box may trigger the EICAS WARNING message FUEL 1 (2) LO LEVEL. The EICAS message may display even though fuel quantity indication on the EICAS or MFD FUEL System Synoptic Page is up to 3970 lb in that tank. Fuel......................................................................... BALANCE CONTINUED...

4-03-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Engine

Page 5

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

ONE ENGINE INOPERATIVE APPROACH AND LANDING Procedure............................................. ACCOMPLISH END

ENG 1 (2) FUEL IMP BYPASS CAUTION: IF BOTH ENGINES ARE AFFECTED, LAND AT THE NEAREST SUITABLE AIRPORT. END

ENG 1 (2) FUEL LO PRESS

Fuel Xfeed Selector................................................ OFF Autothrottle.............................................................. DISENGAGE Engine Parameters................................................. MONITOR The EICAS message may be caused by a fuel leak. Fuel leak may be detected by either:

• • • • • •

A fuel imbalance develops; or Excessive fuel flow in one of the engines; or Fuel quantity from one tank decreases at abnormal rate; or Fuel smell; or Fuel spray from the wings; or With both engines operative, an unexpected difference between the total fuel quantity indicated on EICAS and the total fuel quantity indicated on the FMS Fuel Management page or PERF INIT page 3/3.

FUEL LEAK SUSPECTED?

No

Yes END CONTINUED...

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Page 6

Engine

REVISION 21

AOM-1502-003

FUEL LEAK Procedure........................................... ACCOMPLISH

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

...CONTINUED

DESIRED THRUST MAINTAINED?

No

Yes

ENGINE PARAMETERS FLUCTUATE?

No

Yes Altitude.................................................................... DESCEND AS REQUIRED END

END

Altitude.................................................................... DESCEND AS REQUIRED

AOM-1502-003

END

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REVISION 21

Engine

Page 7

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

ENG 1 (2) NO DISPATCH Crew Awareness. END

ENG 1 (2) OIL LO LEVEL Crew Awareness. END

ENG 1 (2) REV FAIL Crew Awareness. END

ENG 1 (2) REV PROT FAULT Crew Awareness.

4-03-06 Copyright © by Embraer. Refer to cover page for details.

Page 8

Engine

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

ENG 1 (2) REV TLA FAIL Inflight, do not move the thrust levers below idle. On ground, the associated thrust reverser is not available. END

ENG 1 (2) START VLV OPEN XBleed Button......................................................... PUSH OUT Associated Bleed Button......................................... PUSH OUT ON GROUND?

No

Yes

ENGINE 1 AFFECTED?

No

Yes

APU Bleed Button................................................... PUSH OUT

Engine 1: Thrust Lever.......................................................... IDLE Start/Stop Selector................................................ STOP END

AOM-1502-003

Engine Start Ground Cart....................................... REMOVE Engine 2: CONTINUED...

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REVISION 21

Engine

Page 9

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Thrust Lever.......................................................... IDLE Start/Stop Selector................................................ STOP END

APU Bleed Button................................................... PUSH OUT Icing Conditions ..................................................... EXIT/AVOID Altitude.................................................................... MAX 31000 ft CAUTION: IN FLIGHT ASSISTED STARTS ARE NOT POSSIBLE FOR THE AFFECTED ENGINE. END

ENG 1 (2) T2 HEAT FAIL Icing Conditions ..................................................... EXIT/AVOID END

ENG 1 (2) TLA FAIL CONDITION:

Associated engine thrust control may be lost.

ABLE TO CONTROL AFFECTED ENGINE THRUST?

No

Yes END

Associated Thrust Lever......................................... IDLE CONTINUED...

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Page 10

Engine

REVISION 21

AOM-1502-003

NOTE: The engine thrust will be set to idle automatically.

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

...CONTINUED

Transponder............................................................ TA ONLY When appropriate: ONE ENGINE INOPERATIVE APPROACH AND LANDING Procedure.......................................... ACCOMPLISH END

ENG EXCEEDANCE Crew Awareness. END

ENG NO TAKEOFF DATA Engine Takeoff Data............................................... ENTER END

ENG REF A-I DISAG Configure the airplane according to takeoff data or re-enter the takeoff data according to the airplane configuration.

AOM-1502-003

END

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REVISION 21

Engine

Page 11

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

ENG REF ECS DISAG Configure the airplane according to takeoff data or re-enter the takeoff data according to the airplane configuration. END

ENG THR RATING DISAG Crew Awareness. END

ENG TLA NOT TOGA Move the thrust levers to TOGA position. END

ENG 1 (2) FADEC FAULT Crew Awareness.

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Engine

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

ENG 1 (2) FUEL SW FAIL Crew Awareness. END

ENG 1 (2) OIL IMP BYPASS Crew Awareness. END

ENG 1 (2) OIL SW FAIL Crew Awareness. END

ENG 1 (2) SHORT DISPATCH Crew Awareness.

AOM-1502-003

END

4-03-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Engine

Page 13

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

4-03-06 Copyright © by Embraer. Refer to cover page for details.

Page 14

Engine

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

FIRE PROTECTION TABLE OF CONTENTS Block

Page

AOM-1502-003

WARNING APU FIRE ............................................................. 4-03-07......

1

ENG 1 (2) FIRE ..................................................... 4-03-07......

1

CAUTION APU FIRE DET FAIL.............................................. APU FIREX FAIL ................................................... CRG AFT (FWD) FIRE SYS FAIL ........................... ENG 1 (2) FIRE DET FAIL ..................................... LAV SMOKE DET FAIL ..........................................

4-03-07...... 4 4-03-07...... 4 4-03-07...... 4 4-03-07...... 5 Crew Awareness

ADVISORY APU FIREXBTL DISCH ......................................... CRG AFT FIREX HI (LO) ARM .............................. CRG FIRE PROT FAULT....................................... CRG FWD FIREX HI (LO) ARM............................. ENG 1 (2) FIREXBTL A (B) FAIL ........................... ENG FIREXBTL A (B) DISCH ................................

Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness

4-03-07-TOC Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Table of Contents

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

4-03-07-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

EMERGENCY AND ABNORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

ANNUNCIATED PROCEDURES

APU FIRE Light:

APU Emergency Stop Button upper half illuminates in red.

APU Emergency Stop Button............................... PUSH IN APU......................................................................... OFF APU FIRE MESSAGE EXTINGUISHES?

No

Yes

END

APU Fire Extinguishing Button............................... PUSH END

ENG 1 (2) FIRE EICAS Indication: FIRE icon on the associated ITT indicator. Light:

Associated fire handle illuminates.

Autothrottle............................................................ DISENGAGE Affected engine: Thrust Lever....................................................... IDLE Start/Stop Selector............................................. STOP Fire Extinguishing Handle.................................. PULL

AOM-1502-003

LAND AT THE NEAREST SUITABLE AIRPORT. Fire Extinguishing Handle....................................... ROTATE (L or R) CONTINUED...

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REVISION 21

Fire Protection

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

........................................Wait 30 seconds........................................ FIRE PERSISTS?

No

Yes Fire Extinguishing Handle (remaining bottle).......... ROTATE

ON GROUND?

No

Yes EMERGENCY EVACUATION Procedure................ AS REQUIRED END

HIGH VIBRATION?

No

Yes Airspeed.................................................................. REDUCE Airspeeds below VA are recommended to reduce vibration.

Icing Conditions...................................................... EXIT/AVOID Transponder............................................................ TA ONLY EICAS ASSOCIATED FUEL INDICATION LOST?

No

Yes

Fuel Xfeed Selector................................................ OFF CONTINUED...

4-03-07 Copyright © by Embraer. Refer to cover page for details.

Page 2

Fire Protection

REVISION 21

AOM-1502-003

NOTE: Assume that fuel is leaking from tank associated to engine failed side.

AIRPLANE OPERATIONS MANUAL ...CONTINUED

LEAK ON THE RH TANK?

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

No

Yes APU......................................................................... OFF ONE ENGINE INOPERATIVE APPROACH AND LANDING Procedure............................................... ACCOMPLISH END

APU......................................................................... AS REQUIRED ONE ENGINE INOPERATIVE APPROACH AND LANDING Procedure............................................... ACCOMPLISH END

APU......................................................................... START Fuel......................................................................... BALANCE Autothrottle.............................................................. AS REQUIRED When appropriate: ONE ENGINE INOPERATIVE APPROACH AND LANDING Procedure.......................................... ACCOMPLISH

AOM-1502-003

END

4-03-07 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Fire Protection

Page 3

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

APU FIRE DET FAIL APU......................................................................... OFF END

APU FIREX FAIL APU......................................................................... OFF END

CRG AFT (FWD) FIRE SYS FAIL AFFECTED CARGO COMPARTMENT IS EMPTY?

No

Yes

END

LAND AT THE NEAREST SUITABLE AIRPORT.

4-03-07 Copyright © by Embraer. Refer to cover page for details.

Page 4

Fire Protection

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

ENG 1 (2) FIRE DET FAIL If fire is suspected in the affected engine: ENGINE FIRE, SEVERE DAMAGE OR SEPARATION Procedure.................................... ACCOMPLISH END

LAV SMOKE DET FAIL Crew Awareness. END

APU FIREXBTL DISCH Crew Awareness. END

CRG AFT FIREX HI (LO) ARM Crew Awareness.

AOM-1502-003

END

4-03-07 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Fire Protection

Page 5

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

CRG FIRE PROT FAULT Crew Awareness. END

CRG FWD FIREX HI (LO) ARM Crew Awareness. END

ENG 1 (2) FIREXBTL A (B) FAIL Crew Awareness. END

ENG FIREXBTL A (B) DISCH Crew Awareness.

4-03-07 Copyright © by Embraer. Refer to cover page for details.

Page 6

Fire Protection

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

FLIGHT CONTROLS TABLE OF CONTENTS Block

Page

AOM-1502-003

WARNING ELEV NML MODE FAIL ......................................... 4-03-08......

1

GROUND SPOILERS FAIL .................................... 4-03-08......

1

RUDDER NML MODE FAIL.................................... 4-03-08......

2

SPOILER NML MODE FAIL ................................... 4-03-08......

2

CAUTION AOA LIMIT FAIL..................................................... ELEV THR COMP FAIL ......................................... ELEVATOR FAULT ................................................ ELEVATOR LH (RH) FAIL ...................................... FLAP FAIL............................................................. FLT CTRL BIT EXPIRED........................................ FLT CTRL NO DISPATCH ...................................... FLT CTRL TEST FAILED ....................................... PITCH TRIM FAIL.................................................. RUDDER FAIL....................................................... RUDDER FAULT ................................................... RUDDER LIMITER FAIL ........................................ SLAT FAIL ............................................................. SLAT-FLAP LEVER DISAG .................................... SPOILER FAULT ................................................... STAB LOCK FAULT ...............................................

4-03-08...... 3 4-03-08...... 3 4-03-08...... 3 4-03-08...... 4 4-03-08...... 5 Crew Awareness Crew Awareness Crew Awareness 4-03-08...... 8 4-03-08...... 9 4-03-08...... 10 4-03-08...... 11 4-03-08...... 11 4-03-08...... 15 4-03-08...... 15 4-03-08...... 17

ADVISORY AILERON LH (RH) FAIL ........................................ AUTO CONFIG TRIM FAIL.................................... FLAP (SLAT) LO RATE ......................................... FLT CTRL FAULT.................................................. PITCH CONTROL DISC ........................................ PITCH TRIM BKUP FAIL .......................................

4-03-08...... 17 Crew Awareness 4-03-08...... 18 Crew Awareness Crew Awareness Crew Awareness

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REVISION 21

Table of Contents

Page 1

ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL Block

ADVISORY PITCH TRIM LO RATE.......................................... PITCH TRIM SW 1 (2) FAIL .................................. ROLL CONTROL DISC ......................................... SPDBRK LEVER DISAG ....................................... STALL PROT ICE SPEED .....................................

Page

Crew Awareness Crew Awareness Crew Awareness Crew Awareness 4-03-08...... 20

4-03-08-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 21

AOM-1502-003

EMERGENCY AND ABNORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

ELEV NML MODE FAIL Flight Controls Mode Elevators Button................... PUSH IN NOTE: Do not accomplish the ELEVATOR FAULT Procedure. Relevant Inoperative Items: AOA Limit Auto Configuration Trim

Autopilot Elevator Thrust Compensation

Avoid side slipping the airplane. END

GROUND SPOILERS FAIL CONDITION:

One or more ground spoiler panels have extended inadvertently, have failed to extend when commanded or are unavailable to extend.

In flight: Speedbrake........................................................... CLOSE Landing configuration: Slat/Flap........................................................... FULL Set VREF

FULL.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.30.

UNFACTORED

AOM-1502-003

END

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REVISION 21

Flight Controls

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

RUDDER NML MODE FAIL Flight Controls Mode Rudder Button...................... PUSH IN NOTE: Do not accomplish the RUDDER FAULT Procedure. Relevant Inoperative Items: Turn Coordination

Yaw Damper

END

SPOILER NML MODE FAIL Speedbrake............................................................. CLOSE Flight Controls Mode Spoilers Button..................... PUSH IN NOTE: Do not accomplish the SPOILER FAULT Procedure. Relevant Inoperative Items: Ground Spoilers

SpeedBrake

Landing configuration: Slat/Flap................................................................ FULL Set VREF

FULL.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.45.

UNFACTORED

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Page 2

Flight Controls

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AOA LIMIT FAIL Avoid side slipping the airplane. NOTE: The stick shaker remains operative. END

ELEV THR COMP FAIL Compensate manually any pitch tendency following thrust variations. END

ELEVATOR FAULT NOTE: If the SPOILER FAULT message is also displayed, accomplish the Spoiler Fault procedure prior to this procedure. Flight Controls Mode Elevators Button................... PUSH IN, THEN OUT ELEVATOR FAULT MESSAGE EXTINGUISHES?

No

Yes

END

Relevant Inoperative Items:

AOM-1502-003

AOA Limit Auto Configuration Trim

Autopilot Elevator Thrust Compensation CONTINUED...

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REVISION 21

Flight Controls

Page 3

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Avoid side slipping the airplane. END

ELEVATOR LH (RH) FAIL Maximum Airspeed................................................. CURRENT OR 175 KIAS, WHICHEVER IS HIGHER NOTE: Expect less elevator control authority and slower response, especially during landing flare. Landing configuration: Slat/Flap................................................................ 5 Set VREF = VREF FULL + 15 KIAS. Apply brakes only after nose landing gear touches down. CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.40.

UNFACTORED

If a go around is required: Slat/Flap................................................................ 4 Airspeed................................................................ VREF FULL + 15 KIAS (limited to 175 KIAS)

4-03-08 Copyright © by Embraer. Refer to cover page for details.

Page 4

Flight Controls

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

FLAP FAIL SLAT/FLAP LEVER ACTUATED?

No

Yes Altitude.................................................................... MAX 20000 ft Slat/Flap Lever........................................................ RETURN TO THE PREVIOUS POSITION ........................................Wait 10 seconds........................................ Slat/Flap Lever........................................................ RESELECT DESIRED POSITION MESSAGE EXTINGUISHES?

No

Yes

END

Slat/Flap Lever........................................................ RETURN TO THE PREVIOUS POSITION

AOM-1502-003

........................................Wait 10 seconds........................................ Slat/Flap Lever........................................................ RESELECT DESIRED POSITION MESSAGE EXTINGUISHES?

Yes

No CONTINUED...

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REVISION 21

Flight Controls

Page 5

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

END

NOTE: For landing, the Slat/Flap lever can be moved to select the desired Slat position. Landing Configuration: Select the desired slat position and use the landing data according to the FLAP/SLAT FAIL LANDING CONFIGURATION TABLE, or FLAP/SLAT FAIL WITH SHAKER ANTICIPATED LANDING CONFIGURATION TABLE. The Actual Landing Distance is equal to the Unfactored Landing Distance for flaps FULL multiplied by the listed LDG Coef provided on the table below. NOTE: – If amber dashes are displayed on the EICAS, use the most conservative position to enter the table (e.g. for a failure between 1 and 2, consider 1). – Flaps external marks can be used to determine flap position. Autothrottle............................................................ DISENGAGE Bank Angle............................................................ 20° MAXIMUM Gnd Prox Flap Ovrd Button.................................. PUSH IN If a go-around is required: Slat/Flap................................................................ MAINTAIN

CONTINUED...

4-03-08 Copyright © by Embraer. Refer to cover page for details.

Page 6

Flight Controls

REVISION 21

AOM-1502-003

Maintain the Vref presented in the respective Landing Configuration Table.

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

...CONTINUED

FLAP/SLAT FAIL WITHOUT SHAKER ANTICIPATED LANDING CONFIGURATION TABLE

FLAP VREF (KIAS) LDG Coef VREF (KIAS) LDG Coef VREF (KIAS) LDG Coef VREF (KIAS) LDG Coef VREF (KIAS) LDG Coef

SLAT 0

1 (2) (3)

4 (5 ) (FULL)

VREF FULL+60 VREF FULL+50 VREF FULL+50

0

1.85

1.74

1.72

VREF FULL+35 VREF FULL+35 VREF FULL+35

1

1.53

1.51

1.50

VREF FULL+30 VREF FULL+25 VREF FULL+20

2

1.38

3 (4) (5) FULL

1.55

1.28

VREF FULL+15 VREF FULL+10 NOT USABLE

1.31

1.29

VREF FULL+5

VREF FULL

1.06

1.00

FLAP/SLAT FAIL WITH SHAKER ANTICIPATED LANDING CONFIGURATION TABLE SLAT FLAP VREF (KIAS) LDG Coef VREF (KIAS) LDG Coef VREF (KIAS) LDG Coef VREF (KIAS) LDG Coef VREF (KIAS) LDG Coef

0

1 (2) (3)

4 (5 ) (FULL)

VREF FULL+60 VREF FULL+60 VREF FULL+60

0

1.85

1.83

1.82

VREF FULL+40 VREF FULL+40 VREF FULL+40

1

1.62

1.60

1.60

VREF FULL+30 VREF FULL+25 VREF FULL+25

2

1.38

3 (4) (5) FULL

1.55

1.57

VREF FULL+15 VREF FULL+10 NOT USABLE

1.31

1.29

VREF FULL+5

VREF FULL

1.06

1.00

AOM-1502-003

END

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REVISION 21

Flight Controls

Page 7

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

FLT CTRL BIT EXPIRED Crew Awareness. END

FLT CTRL NO DISPATCH Crew Awareness. END

FLT CTRL TEST FAILED Crew Awareness. END

PITCH TRIM FAIL Maximum Airspeed................................................. CURRENT OR 175 KIAS, WHICHEVER IS HIGHER Pitch Trim System 1 and 2 Cutout Buttons............ PUSH IN, THEN OUT Pitch Trim Switches................................................ ACTUATE PITCH TRIM NORMAL?

No

Yes

CONTINUED...

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Page 8

Flight Controls

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

...CONTINUED

Pitch Trim System 1 and 2 Cutout Buttons............ PUSH IN NOTE: – No more pitch trim is available. – Continuous turns helps to alleviate excessive pitch up tendencies. Landing configuration: Slat/Flap................................................................ 5 Set VREF = VREF FULL + 15 KIAS. Establish landing configuration early. CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.40.

UNFACTORED

If a go around is required: Slat/Flap................................................................ 4 Airspeed................................................................ VREF FULL + 15 KIAS (limited to 175 KIAS) END

RUDDER FAIL LAND AT THE NEAREST SUITABLE AIRPORT. Maximum Airspeed................................................. CURRENT OR 175 KIAS, WHICHEVER IS HIGHER Relevant Inoperative Items: Turn Coordination Yaw Damper

Yaw Trim

Landing configuration: Slat/Flap................................................................ FULL AOM-1502-003

Set VREF FULL. CONTINUED...

4-03-08 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Controls

Page 9

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

CAUTION: AVOID LANDING WITH CROSSWIND COMPONENTS ABOVE 10 KT. If a go around is required, proceed as a normal go around limiting the airspeed to 175 KIAS. NOTE: As assymetric thrust may be required to help controlling the airplane, maximum thrust on both engines may not be possible. END

RUDDER FAULT NOTE: If the SPOILER FAULT message is also displayed, accomplish the SPOILER FAULT procedure prior to this procedure. Flight Controls Mode Rudder Button...................... PUSH IN, THEN OUT

No

RUDDER FAULT MESSAGE EXTINGUISHES?

Yes

END

RUDDER LIMITER FAIL MESSAGE DISPLAYED?

No

Yes Flight Controls Mode Rudder Button...................... PUSH IN, THEN OUT RUDDER FAULT MESSAGE EXTINGUISHES?

No

CONTINUED...

4-03-08 Copyright © by Embraer. Refer to cover page for details.

Page 10

Flight Controls

REVISION 21

AOM-1502-003

Yes

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

...CONTINUED

END

Relevant Inoperative Items: Yaw Damper Turn Coordination END

RUDDER LIMITER FAIL CONDITION: WARNING:

• •

Rudder position limiter is inoperative and rudder authority in flight is 30°. DO NOT APPLY ABRUPT PEDAL COMMANDS. DO NOT APPLY FULL RUDDER DEFLECTION.

END

SLAT FAIL SLAT/FLAP LEVER ACTUATED?

No

Yes Altitude.................................................................... MAX 20000 ft Slat/Flap Lever........................................................ RETURN TO THE PREVIOUS POSITION

AOM-1502-003

........................................Wait 10 seconds........................................ CONTINUED...

4-03-08 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Controls

Page 11

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Slat/Flap Lever........................................................ RESELECT DESIRED POSITION MESSAGE EXTINGUISHES?

No

Yes

END

Slat/Flap Lever........................................................ RETURN TO THE PREVIOUS POSITION ........................................Wait 10 seconds........................................ Slat/Flap Lever........................................................ RESELECT DESIRED POSITION MESSAGE EXTINGUISHES?

No

CONTINUED...

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Page 12

Flight Controls

REVISION 21

AOM-1502-003

Yes

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

...CONTINUED

END

NOTE: For landing, the Slat/Flap lever can be moved to select the desired Flap position. Landing Configuration: Select the desired flap position and use the landing data according to the FLAP/SLAT FAIL LANDING CONFIGURATION TABLE, or FLAP/SLAT FAIL WITH SHAKER ANTICIPATED LANDING CONFIGURATION TABLE. The Actual Landing Distance is equal to the Unfactored Landing Distance for flaps FULL multiplied by the listed LDG Coef provided on the table below. NOTE: – If amber dashes are displayed on the EICAS, use the most conservative position to enter the table (e.g. for a failure between 1 and 2, consider 1). – Slats external marks can be used to determine slat position. Autothrottle............................................................ DISENGAGE Bank Angle............................................................ 20° MAXIMUM Gnd Prox Flap Ovrd Button.................................. PUSH IN If a go-around is required: Slat/Flap................................................................ MAINTAIN

AOM-1502-003

Maintain the Vref presented in the respective Landing Configuration Table.

CONTINUED...

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...CONTINUED

FLAP/SLAT FAIL WITHOUT SHAKER ANTICIPATED LANDING CONFIGURATION TABLE

FLAP VREF (KIAS) LDG Coef VREF (KIAS) LDG Coef VREF (KIAS) LDG Coef VREF (KIAS) LDG Coef VREF (KIAS) LDG Coef

SLAT 0

1 (2) (3)

4 (5 ) (FULL)

VREF FULL+60 VREF FULL+50 VREF FULL+50

0

1.85

1.74

1.72

VREF FULL+35 VREF FULL+35 VREF FULL+35

1

1.53

1.51

1.50

VREF FULL+30 VREF FULL+25 VREF FULL+20

2

1.38

3 (4) (5) FULL

1.55

1.28

VREF FULL+15 VREF FULL+10 NOT USABLE

1.31

1.29

VREF FULL+5

VREF FULL

1.06

1.00

FLAP/SLAT FAIL WITH SHAKER ANTICIPATED LANDING CONFIGURATION TABLE SLAT FLAP VREF (KIAS) LDG Coef VREF (KIAS) LDG Coef VREF (KIAS) LDG Coef VREF (KIAS) LDG Coef VREF (KIAS) LDG Coef

0

1 (2) (3)

4 (5 ) (FULL)

VREF FULL+60 VREF FULL+60 VREF FULL+60

0

1.85

1.83

1.82

VREF FULL+40 VREF FULL+40 VREF FULL+40

1

1.62

1.60

1.60

VREF FULL+30 VREF FULL+25 VREF FULL+25

2

1.38

3 (4) (5) FULL

1.55

1.57

VREF FULL+15 VREF FULL+10 NOT USABLE

1.31

1.29

VREF FULL+5

VREF FULL

1.06

1.00

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AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

SLAT-FLAP LEVER DISAG Return the slat/flap lever to previous position and then use it as required. END

SPOILER FAULT CONDITION:

One or more Multifunction Spoilers Panels have reverted to Direct Mode, have extended inadvertently or have failed to extend.

Autopilot.................................................................. DISENGAGE Speedbrake............................................................. CLOSE Flight Controls Mode Spoilers Button..................... PUSH IN, THEN OUT SPOILER FAULT MESSAGE EXTINGUISHES?

No

Yes Speedbrake............................................................. AS REQUIRED END

Relevant Inoperative Items: Ground Spoilers (partially or fully lost) SpeedBrake (partially or fully lost) NOTE: In case of Speedbrake partially lost, the remaining panels may be used. In this case the advisory message SPDBRK LEVER DISAG may be displayed.

AOM-1502-003

ALL SPOILER PANELS POSITION DETERMINED?

No

Yes CONTINUED...

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...CONTINUED

ALL SPOILER PANELS FAILED CLOSED?

No

Yes Landing configuration: Slat/Flap................................................................ FULL Set VREF

FULL.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.45.

UNFACTORED

END

Landing configuration: Slat/Flap................................................................ 5 Set VREF = VREF

FULL

+ 15 KIAS.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.78.

UNFACTORED

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AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

STAB LOCK FAULT CONDITION:

The Horizontal Stabilizer may have a drift rate up to 0.5 deg/min nose up or nose down.

LAND AT THE NEAREST SUITABLE AIRPORT. Pitch Trim................................................................ AS REQUIRED CAUTION: DO NOT PRESS ANY PITCH TRIM SYSTEM CUTOUT BUTTON. END

AILERON LH (RH) FAIL On ground, do not takeoff. In flight: Avoid abrupt and large aileron inputs and limit bank angle to 25°. Establish landing configuration early. Landing configuration: Slat/Flap........................................................... 5 Set VREF

FULL+10

KIAS.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.30.

UNFACTORED

AOM-1502-003

END

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AUTO CONFIG TRIM FAIL Crew Awareness. END

FLAP (SLAT) LO RATE During approach: Slat/Flap Actuation................................................ ANTICIPATE END

FLT CTRL FAULT Crew Awareness. END

PITCH CONTROL DISC Crew Awareness.

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REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

PITCH TRIM BKUP FAIL Crew Awareness. END

PITCH TRIM LO RATE Crew awareness. END

PITCH TRIM SW 1 (2) FAIL Crew Awareness. END

ROLL CONTROL DISC Crew Awareness. END

SPDBRK LEVER DISAG Crew Awareness.

AOM-1502-003

END

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REVISION 21

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STALL PROT ICE SPEED Set landing reference speeds for ice accretion. LANDING IN ICING CONDITIONS OR ACCRETION?

WITH

ICE No

Yes Use landing performance data for ice accretion. END

Landing Configuration: For flap 5: CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.35.

UNFACTORED

For flap FULL: CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.10.

UNFACTORED

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END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

FMS/NAV/COMM/FLIGHT INSTRUMENTS TABLE OF CONTENTS Block

Page

WARNING

AOM-1502-003

NO TAKEOFF CONFIG.......................................... 4-03-09...... CAUTION ADS 1 (2) FAIL ...................................................... ADS 3 FAIL ........................................................... ADS 1 (2) (3) HTR FAIL......................................... ADS 4 HTR FAIL ................................................... APM FAIL.............................................................. APM MISCOMP..................................................... AURAL WRN SYS FAIL ......................................... AVNX ASCB FAULT ............................................... AVNX MAU 1A FAIL............................................... AVNX MAU 1B FAIL .............................................. AVNX MAU 2A FAIL............................................... AVNX MAU 2B FAIL .............................................. AVNX MAU 3A FAIL............................................... AVNX MAU 3B FAIL .............................................. AVNX MAU 1A (1B) OVHT..................................... AVNX MAU 2A (2B) OVHT..................................... AVNX MAU 3A (3B) OVHT..................................... AVNX MAU 1 (2) (3) FAN FAIL............................... CMS FAIL.............................................................. CREW WRN SYS FAULT....................................... DISPLAY CTRL FAIL ............................................. DISPLAY CTRL FAULT .......................................... EICAS FAULT........................................................ EICAS OVHT......................................................... FMS POS DISAG .................................................. FMS1 (2) - GPS POS DISAG ................................. GND PROX FAIL ...................................................

1

4-03-09...... 1 4-03-09...... 1 4-03-09...... 1 4-03-09...... 2 Crew Awareness Crew Awareness 4-03-09...... 2 Crew Awareness 4-03-09...... 3 4-03-09...... 4 4-03-09...... 4 4-03-09...... 5 4-03-09...... 5 4-03-09...... 6 4-03-09...... 6 4-03-09...... 7 4-03-09...... 7 Crew Awareness Crew Awareness Crew Awareness 4-03-09...... 8 Crew Awareness 4-03-09...... 9 4-03-09...... 9 4-03-09...... 9 4-03-09...... 10 4-03-09...... 10

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REVISION 21

Table of Contents

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AIRPLANE OPERATIONS MANUAL Block

Page

CAUTION IRS EXCESSIVE MOTION ..................................... 4-03-09...... IRS 1 (2) FAIL ....................................................... 4-03-09......

10 11

MCDU 1 (2) OVHT ................................................ MFD 1 (2) FAULT .................................................. MFD 1 (2) OVHT ................................................... NAVCOM 1 (2) FAIL .............................................. NAVCOM 1 (2) OVHT ............................................ PFD 1 (2) FAULT ................................................... PFD 1 (2) OVHT.................................................... SYS CONFIG FAIL ................................................ TERRAIN FAIL ...................................................... VALIDATE CONFIG ............................................... VHF 1 (2) (3) OVHT............................................... VHF 3 FAIL ........................................................... WINDSHEAR FAIL................................................. XPDR 1 (2) IN STBY .............................................

4-03-09...... 11 4-03-09...... 11 4-03-09...... 12 4-03-09...... 12 4-03-09...... 12 4-03-09...... 13 4-03-09...... 13 Crew Awareness 4-03-09...... 14 Crew Awareness 4-03-09...... 14 4-03-09...... 14 4-03-09...... 15 4-03-09...... 15

ADVISORY ADS PROBE 1 (2) (3) (4) FAIL .............................. ADS 1 (2) HTR FAULT .......................................... ADS 3 SLIPCOMP FAIL ........................................ ADS 4 SLIPCOMP FAIL ........................................ APM FAULT.......................................................... ATC 1 (2) DATALINK FAIL..................................... AURAL WRN SYS FAULT ..................................... AVNX DB MODULE FAIL ...................................... AVNX MAU 1A (1B) FAULT ................................... AVNX MAU 2A (2B) FAULT ................................... AVNX MAU 3A (3B) FAULT ................................... AVNX MAU 1 (2) (3) FAN FAULT........................... CCD 1 (2) FAULT.................................................. CMC FAIL.............................................................

Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness 4-03-09...... 17 Crew Awareness Crew Awareness

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REVISION 21

AOM-1502-003

170/175 models, MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

Block

AOM-1502-003

ADVISORY CMF 1 (2) FAIL ..................................................... CMS FAULT.......................................................... CVR AFT (FWD) FAIL ........................................... DATALINK 1 (2) FAIL ............................................ FDR AFT (FWD) FAIL ........................................... FLT CTRL ADS FAIL ............................................. FMS 1 (2) FAIL ..................................................... IRS 1 (2) NAV MODE FAIL.................................... IRS ALIGNING ...................................................... IRS PRES POS INVALID....................................... RALT 1 (2) FAIL .................................................... TAT 1 (2) FAIL ...................................................... TCAS FAIL ........................................................... TERRAIN NOT AVAILABLE ................................... XPDR 1 (2) FAIL ...................................................

Page

Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness 4-03-09...... 19 4-03-09...... 20 Crew Awareness 4-03-09...... 20 4-03-09...... 20 4-03-09...... 21 Crew Awareness Crew Awareness 4-03-09...... 22

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REVISION 21

Table of Contents

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REVISION 21

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

NO TAKEOFF CONFIG Configure the airplane for takeoff. END

ADS 1 (2) FAIL Confirm the affected ADS automatic reversion. If necessary: Associated Reversionary Panel ADS Button........ PUSH END

ADS 3 FAIL Reversion................................................................ AS REQUIRED END

ADS 1 (2) (3) HTR FAIL Revert the affected ADS.

AOM-1502-003

END

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ADS 4 HTR FAIL Disregard IESS altitude and airspeed indication. END

APM FAIL Crew Awareness. END

APM MISCOMP Crew Awareness. END

AURAL WRN SYS FAIL Monitor visual indications. NOTE: Aural warnings, including EGPWS callouts, are lost. TCAS aural will be operative.

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REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AVNX ASCB FAULT Crew Awareness. END

AVNX MAU 1A FAIL Icing Conditions...................................................... EXIT/AVOID Relevant Inoperative Items: ACARS ADS 1 Autopilot 1 FMS 1 Left Aileron Indication MCDU1 (except circuit breakers page)

Multi Function Spoilers L5 and R5 Nosewheel Steering Outboard Brakes Pitch Trim Indication Weather Radar

Landing Configuration: Slat/Flap................................................................ FULL Set VREF

FULL.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.70.

UNFACTORED

On ground: Brakes................................................................... APPLY NORMALLY Steer the airplane using differential braking and rudder. The nosewheel steering operates normally if the EICAS message AVNX MAU 1A FAIL is displayed after the engagement of nosewheel steering.

AOM-1502-003

END

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AVNX MAU 1B FAIL Relevant Inoperative Items: GPS 1 Multi Function Spoilers L5 and R5

Pitch Trim Indication

Landing Configuration: Slat/Flap................................................................ FULL Set VREF

FULL.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.15.

UNFACTORED

END

AVNX MAU 2A FAIL Relevant Inoperative Items: Autobrake FMS 1.

Nosewheel Steering.

On ground: Steer the airplane using rudder and differential braking.

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END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AVNX MAU 2B FAIL Relevant Inoperative Items: ADS 2

Inboard Brakes MCDU 2 (except circuit breakers page) Right Side Weather Radar Control

Autopilot 2 EGPWS IESS - Localizer and Glide Slope Indication

Landing Configuration: Slat/Flap................................................................ FULL Set VREF

FULL.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.65.

UNFACTORED

On ground: Brakes................................................................... APPLY NORMALLY END

AVNX MAU 3A FAIL Icing Conditions...................................................... EXIT/AVOID Relevant Inoperative Items: ADS 3 APU

AOM-1502-003

Autothrottle Autopilot 2 FMS 2

GPS 2 Multi Function Spoiler L3, R3, L4 and R4 Right Aileron Indication Speedbrake

Landing Configuration: Slat/Flap................................................................ FULL CONTINUED...

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Page 5

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...CONTINUED

Set VREF

FULL.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.20.

UNFACTORED

END

AVNX MAU 3B FAIL Relevant Inoperative Items: Engine Vibration Indication Multi Function Spoilers L3, R3, L4 and R4

Pitch Trim Indication

Landing Configuration: Slat/Flap................................................................ FULL Set VREF

FULL.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.20.

UNFACTORED

END

AVNX MAU 1A (1B) OVHT Associated CB........................................................ PULL NOTE: – For MAU 1A OVHT, pull the B6 and B7 CB. – For MAU 1B OVHT, pull the B15 CB. Associated AVNX MAU 1A FAIL or AVNX MAU 1B FAIL Procedure..................................................... ACCOMPLISH

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END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AVNX MAU 2A (2B) OVHT Associated CB........................................................ PULL NOTE: – For MAU 2A OVHT, pull the B25 CB. – For MAU 2B OVHT, pull the B26 and B35 CB. Associated AVNX MAU 2A FAIL or AVNX MAU 2B FAIL Procedure..................................................... ACCOMPLISH END

AVNX MAU 3A (3B) OVHT Associated CB........................................................ PULL NOTE: – For MAU 3A OVHT, pull the B34 CB. – For MAU 3B OVHT, pull the B27 CB. Associated AVNX MAU 3A FAIL or AVNX MAU 3B FAIL Procedure..................................................... ACCOMPLISH END

AVNX MAU 1 (2) (3) FAN FAIL Crew Awareness.

AOM-1502-003

END

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CMS FAIL Crew Awareness. END

CREW WRN SYS FAULT Crew Awareness. END

DISPLAY CTRL FAIL NOTE: – PFD selections of VOR, FMS, RA/BARO, Minimums and Baro setting will be locked at the last setting position prior to the failure. – Disregard altitude callouts from aural system. – Use IESS for barometric setting and ILS approach. Relevant Inoperative Items: Bearing “” Pushbutton Bearing “O” Pushbutton FMS Pushbutton FPR Pushbutton HSI Pushbutton IN/Hpa baro setting knob

PREV Pushbutton RAD/BARO Minimums Knob STD Pushbutton V/L Pushbutton WX Pushbutton

NOTE: The items above are inoperative on both pilot and copilot display controllers.

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AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

DISPLAY CTRL FAULT Crew Awareness. END

EICAS FAULT Crosscheck EICAS information and revert if necessary. END

EICAS OVHT B11 CB.................................................................... PULL Reversionary Panel Selector.................................. EICAS END

FMS POS DISAG Do not use FMS as navigation source.

AOM-1502-003

END

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REVISION 21

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Page 9

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FMS1 (2) - GPS POS DISAG DUAL FMS INSTALLED?

No

Yes Select another FMS source. END

Select another navigation source. END

GND PROX FAIL Increase awareness in relation to ground proximity. END

IRS EXCESSIVE MOTION Airplane................................................................... STOP The IRS will restart the alignment after the motion is stopped.

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AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

IRS 1 (2) FAIL Reversionary Panel IRS Button.............................. PUSH END !170/175 models, MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

MCDU 1 (2) OVHT Associated CB........................................................ PULL NOTE: – For MCDU 1 OVHT, pull the B16 CB. – For MCDU 2 OVHT, pull the B31 CB. END "

MFD 1 (2) FAULT Crosscheck the affected MFD display information (System Synoptics, MAP, TAS, TAT, SAT, TCAS info, WX radar and Terrain Data) with the opposite side MFD display information and revert if necessary. Disregard any non reliable information from the affected MFD.

AOM-1502-003

END

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MFD 1 (2) OVHT Associated CB........................................................ PULL Reversion................................................................ AS REQUIRED NOTE: – For MFD 1 OVHT, pull the B29 CB. – For MFD 2 OVHT, pull the B20 CB. END

NAVCOM 1 (2) FAIL Select and use the remaining NAVCOM (VHF, VOR, DME and Transponder). END

NAVCOM 1 (2) OVHT Associated MRC CB............................................... PULL NOTE: – For NAVCOM 1 OVHT, pull the C10 CB. – For NAVCOM 2 OVHT, pull the MRC 2 Electronic CB. Select on the MCDU: CB → CB MENU → CB BY SYSTEM → NEXT → NEXT→NAV → MRC 2. NAVCOM 1 (2) FAIL Procedure.............................. ACCOMPLISH

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END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

PFD 1 (2) FAULT Crosscheck the affected PFD display information (Attitude, Airspeed, Altitude, FMA, FPA, Minimums, Baro setting, NAVCOM radio frequencies, HDG and CRS) with the opposite side PFD display information and revert if necessary. Disregard any non-reliable information from the affected PFD. END

PFD 1 (2) OVHT Associated CB........................................................ PULL Reversionary Panel Selector.................................. AS REQUIRED NOTE: – For PFD 1 OVHT, pull the B19 CB – For PFD 2 OVHT, pull the B21 CB. END

SYS CONFIG FAIL Crew Awareness.

AOM-1502-003

END

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ANNUNCIATED PROCEDURES

TERRAIN FAIL Increase awareness in relation to terrain proximity. END

VALIDATE CONFIG Crew Awareness. END

VHF 1 (2) (3) OVHT Associated CB........................................................ PULL NOTE: – For VHF 1 OVHT, pull the C11 CB. – For VHF 2 OVHT, pull the VHF 2 Electronic CB. – For VHF 3 OVHT, pull the VHF 3 Electronic CB. END

VHF 3 FAIL Select another VHF source.

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END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

WINDSHEAR FAIL Increase awareness in relation to weather, wind and speed variations. END

XPDR 1 (2) IN STBY Transponder............................................................ TA/RA OR AS REQUIRED END

ADS PROBE 1 (2) (3) (4) FAIL Crew Awareness. END

ADS 1 (2) HTR FAULT Crew Awareness.

AOM-1502-003

END

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ADS 3 SLIPCOMP FAIL Crew Awareness. END

ADS 4 SLIPCOMP FAIL Crew Awareness. END

APM FAULT Crew Awareness. END

ATC 1 (2) DATALINK FAIL Crew Awareness. END

AURAL WRN SYS FAULT Crew Awareness.

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AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AVNX DB MODULE FAIL Crew Awareness. END

AVNX MAU 1A (1B) FAULT Crew Awareness. END

AVNX MAU 2A (2B) FAULT Crew Awareness. END

AVNX MAU 3A (3B) FAULT Crew Awareness. END

AVNX MAU 1 (2) (3) FAN FAULT Crew Awareness.

AOM-1502-003

END

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CCD 1 (2) FAULT Crew Awareness. END

CMC FAIL Crew Awareness. END

CMF 1 (2) FAIL Crew Awareness. END

CMS FAULT Crew Awareness. END

CVR AFT (FWD) FAIL Crew Awareness.

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AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

DATALINK 1 (2) FAIL Crew Awareness. END

FDR AFT (FWD) FAIL Crew Awareness. END

FLT CTRL ADS FAIL Crew Awareness. END

FMS 1 (2) FAIL ANOTHER FMS AVAILABLE?

No

Yes Select another FMS source.

NOTE: Operative FMS is controlled only by same side MCDU. END

Select another navigation source.

AOM-1502-003

END

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IRS 1 (2) NAV MODE FAIL Associated Reversionary Panel IRS Button........... PUSH END

IRS ALIGNING Crew Awareness. END

IRS PRES POS INVALID FMS Present Position............................................. ENTER OR REENTER END

RALT 1 (2) FAIL ANOTHER RADIO ALTIMETER AVAILABLE?

No

Yes During approach: Increase awareness in relation to autothrottle operation.

CONTINUED...

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Page 20

FMS/NAV/COMM/Flight Instruments

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

...CONTINUED

During approach: Autothrottle............................................................ DISENGAGE END

TAT 1 (2) FAIL TAT 1 FAILED?

No

Yes TAS data from ADS 1 and 3 is not reliable anymore.

Do not couple AP and AT source to a PFD using ADS 1 or 3. END

TAS data from ADS 2 is not reliable anymore. Do not couple AP and AT source to a PFD using ADS 2.

AOM-1502-003

END

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REVISION 21

FMS/NAV/COMM/Flight Instruments

Page 21

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

TCAS FAIL Crew Awareness. END

TERRAIN NOT AVAILABLE Crew Awareness. END

XPDR 1 (2) FAIL Select and use the remaining Transponder.

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Page 22

FMS/NAV/COMM/Flight Instruments

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

FUEL TABLE OF CONTENTS Block

Page

WARNING FUEL 1 (2) LO LEVEL ........................................... 4-03-10......

1

CAUTION APU FUEL SOV FAIL ............................................ 4-03-10...... ENG 1 (2) FUEL SOV FAIL .................................... 4-03-10...... FUEL IMBALANCE ................................................ 4-03-10......

2 2 2

MAU load 19.3 and on OR POST-MOD SB 170-31-0019

FUEL TANK LO TEMP ........................................... 4-03-10...... FUEL XFEED FAIL ................................................ 4-03-10......

4 5

ADVISORY DEFUEL SOV OPEN............................................. Crew Awareness MAU load 19.3 and on OR POST-MOD SB 170-31-0019

AOM-1502-003

FUEL AC PUMP 1 (2) FAIL.................................... FUEL DC PUMP FAIL ........................................... FUEL EQUAL-XFEED OPEN................................. FUEL FEED 1 (2) FAULT ...................................... FUEL KG-LB MISMATCH ......................................

4-03-10...... 6 4-03-10...... 6 Crew Awareness 4-03-10...... 7 Crew Awareness

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REVISION 18

Table of Contents

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 2

Table of Contents

REVISION 18

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

FUEL 1 (2) LO LEVEL EICAS Indication: Associated fuel quantity indication in red. LAND AT THE NEAREST SUITABLE AIRPORT. CAUTION: AVOID ATTITUDES IN EXCESS OF 15° NOSE UP OR DOWN, UNCOORDINATED MANEUVERS AND NEGATIVE G’S. Associated Fuel AC Pump...................................... ON The EICAS message may be caused by a fuel leak. Fuel leak may be detected by either:

• • • • • •

A fuel imbalance develops; or Excessive fuel flow in one of the engines; or Fuel quantity from one tank decreases at abnormal rate; or Fuel smell; or Fuel spray from the wings; or With both engines operative, an unexpected difference between the total fuel quantity indicated on EICAS and the total fuel quantity indicated on the FMS Fuel Management page or PERF INIT page 3/3.

FUEL LEAK SUSPECTED?

No

Yes FUEL LEAK Procedure........................................... ACCOMPLISH END

Fuel Xfeed Selector................................................ AS REQUIRED

AOM-1502-003

END

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REVISION 21

Fuel

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

APU FUEL SOV FAIL Do not restart the APU. END

ENG 1 (2) FUEL SOV FAIL AFTER PULLING FIRE HANDLE?

No

Yes Associated Fuel AC Pump...................................... OFF Fuel Xfeed Selector................................................ OFF END

END

FUEL IMBALANCE CONDITION:

Imbalance between wing tanks greater than the limit.

The EICAS message may be caused by a fuel leak. Fuel leak may be detected by either: Excessive fuel flow in one of the engines; or Fuel quantity from one tank decreases at abnormal rate; or Fuel smell; or Fuel spray from the wings; or With both engines operative, an unexpected difference between the total fuel quantity indicated on EICAS and the total fuel quantity indicated on the FMS Fuel Management page or PERF INIT page 3/3. CONTINUED...

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Page 2

Fuel

REVISION 21

AOM-1502-003

• • • • •

AIRPLANE OPERATIONS MANUAL ...CONTINUED

FUEL LEAK SUSPECTED?

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

No

Yes FUEL LEAK Procedure........................................... ACCOMPLISH END

Attitude.................................................................... WING LEVEL

•

Compare total fuel quantity indication on EICAS with fuel remaining information indicated on FMS Fuel Management page. If FMS fuel remaining quantity is lower than EICAS total fuel indication, disregard FMS fuel remaining information. Monitor fuel quantities using the EICAS indications.

NOTE: – The guidance to compare the total fuel quantity indication on EICAS with fuel remaining information indicated on FMS Fuel Management page is not valid when flying with one engine inoperative. In this case only the fuel indications presented on EICAS must be used. – Crossfeed performance may be reduced in a high thrust asymmetry condition with both engines operating. On those conditions fuel imbalance above 360 kg (790 lb) may be observed. – Crossfeed performance is restored with any thrust reduction below maximum continuous. RH WING LOWER LEVEL?

No

Yes Fuel Xfeed Selector................................................ LOW 2 When the desired balance is achieved: Fuel Xfeed Selector.............................................. OFF

AOM-1502-003

Monitor total fuel indication in EICAS with FMS fuel remaining information. END

CONTINUED...

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REVISION 21

Fuel

Page 3

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Fuel Xfeed Selector................................................ LOW 1 When the desired balance is achieved: Fuel Xfeed Selector.............................................. OFF Monitor total fuel indication in EICAS with FMS fuel remaining information. END !MAU load 19.3 and on OR POST-MOD SB 170-31-0019

FUEL TANK LO TEMP Airspeed.................................................................. ACCELERATE AS MUCH AS POSSIBLE UP TO VMO/MMO .........................................Wait 3 minutes......................................... FUEL TANK LO TEMP MESSAGE PERSISTS?

No

Yes Altitude ................................................................... DESCEND AS REQUIRED

END

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Page 4

Fuel

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

FUEL XFEED FAIL FUEL XFEED SELECTOR OFF?

No

Yes

END

FUEL IS BEING EQUALIZED?

No

Yes When appropriate: Fuel Xfeed Selector.............................................. OFF END

Fuel Xfeed Selector................................................ OFF Asymmetric Thrust.................................................. AS REQUIRED

AOM-1502-003

END

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REVISION 21

Fuel

Page 5

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

DEFUEL SOV OPEN Crew Awareness. END !MAU load 19.3 and on OR POST-MOD SB 170-31-0019

FUEL AC PUMP 1 (2) FAIL Fuel Xfeed Selector................................................ OFF END "

FUEL DC PUMP FAIL Fuel DC Pump Selector ......................................... OFF END

FUEL EQUAL-XFEED OPEN Crew Awareness.

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Page 6

Fuel

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

FUEL FEED 1 (2) FAULT IN FLIGHT?

No

Yes Continue the flight monitoring the systems. END

Emergency/Parking Brake.................................... SET Associated FUEL AC PUMP................................. AUTO Associated Thrust Lever....................................... ADVANCE to 65% N2 Associated FUEL AC PUMP................................. ON .........................................Wait 5 seconds......................................... Associated FUEL AC PUMP................................. AUTO FUEL FEED 1 (2) FAULT MESSAGE PERSISTS?

No

Yes Do not takeoff.

Associated Thrust Lever......................................... IDLE

AOM-1502-003

END

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REVISION 21

Fuel

Page 7

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

FUEL KG-LB MISMATCH Crew Awareness.

4-03-10 Copyright © by Embraer. Refer to cover page for details.

Page 8

Fuel

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

HYDRAULICS TABLE OF CONTENTS Block

Page

AOM-1502-003

WARNING HYD 1 (2) OVERHEAT........................................... 4-03-11 ......

1

HYD 3 OVERHEAT................................................ 4-03-11 ......

1

CAUTION HYD PTU FAIL ...................................................... HYD 1 (2) EDP NOT D-PRESS.............................. HYD 1 (2) HI TEMP ............................................... HYD 3 HI TEMP .................................................... HYD 1 (2) LO PRESS............................................ HYD 3 LO PRESS ................................................. HYD 3 VLV FAIL....................................................

4-03-11 ...... 4-03-11 ...... 4-03-11 ...... 4-03-11 ...... 4-03-11 ...... 4-03-11 ...... 4-03-11 ......

2 2 3 3 3 4 4

ADVISORY HYD PTU NOT AUTO ........................................... HYD PUMP NOT AUTO ........................................ HYD TEMP SENS FAIL......................................... HYD 1 (2) EDP FAIL ............................................. HYD 1 (2) ELEC PUMP FAIL................................. HYD 3 ELEC PUMP A FAIL................................... HYD 3 ELEC PUMP B FAIL .................................. HYD 1 (2) (3) LO QTY .......................................... HYD 1 (2) SOV FAIL ............................................. HYD 3 PUMP A NOT ON ......................................

Crew Awareness Crew Awareness Crew Awareness Crew Awareness 4-03-11 ...... 5 4-03-11 ...... 6 4-03-11 ...... 7 Crew Awareness Crew Awareness Crew Awareness

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REVISION 17

Table of Contents

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 2

Table of Contents

REVISION 17

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

HYD 1 (2) OVERHEAT Associated Electric Hydraulic Pump Selector ....... OFF Associated Engine Pump Shutoff Button............... PUSH IN HYD 1 (2) SOV FAIL MESSAGE PRESENTED?

No

Yes LAND AT THE NEAREST SUITABLE AIRPORT. ENGINE SHUTDOWN Procedure ......................... ACCOMPLISH

Appropriate LOSS OF HYDRAULIC SYSTEM 1 or LOSS OF HYDRAULIC SYSTEM 2 Procedure.... ACCOMPLISH END

HYD 3 OVERHEAT Electric HYD SYS 3 Pump A Selector ................... OFF Electric HYD SYS 3 Pump B Selector .................. OFF LOSS OF HYDRAULIC SYSTEM 3 Procedure..... ACCOMPLISH

AOM-1502-003

END

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REVISION 17

Hydraulics

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

HYD PTU FAIL PTU Selector........................................................... ON HYD PTU FAIL MESSAGE PERSISTS?

No

Yes PTU Selector Knob................................................. OFF END

NOTE: During cruise flight, the PTU Selector Knob may be turned to AUTO. END

HYD 1 (2) EDP NOT D-PRESS An engine windmill restart will not be available.

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Page 2

Hydraulics

REVISION 17

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

HYD 1 (2) HI TEMP Associated Electric Hydraulic Pump Selector ....... OFF END

HYD 3 HI TEMP Electric Hydraulic Pump A Selector........................ OFF END

HYD 1 (2) LO PRESS Associated Electric Hydraulic Pump Selector ....... ON HYD 1 (2) LO PRESS MESSAGE PERSISTS?

No

Yes Associated Electric Hydraulic Pump Selector......... OFF Appropriate LOSS OF HYDRAULIC SYSTEM 1 or LOSS OF HYDRAULIC SYSTEM 2........................ ACCOMPLISH END

AOM-1502-003

END

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REVISION 17

Hydraulics

Page 3

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

HYD 3 LO PRESS Electric Hydraulic Pump B Selector ...................... ON Electric Hydraulic Pump A Selector........................ OFF HYD 3 LO PRESS MESSAGE PERSISTS?

No

Yes Electric Hydraulic Pump B Selector........................ OFF LOSS OF HYDRAULIC SYSTEM 3 Procedure...... ACCOMPLISH END

END

HYD 3 VLV FAIL Airspeed.................................................................. MIN 130 KIAS

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Page 4

Hydraulics

REVISION 17

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

HYD PTU NOT AUTO Crew Awareness. END

HYD PUMP NOT AUTO Crew Awareness. END

HYD TEMP SENS FAIL Crew Awareness. END

HYD 1 (2) EDP FAIL Crew Awareness. END

HYD 1 (2) ELEC PUMP FAIL BOTH PUMPS AFFECTED AND ASSOCIATED WITH ANY FLAP No OR SLAT MALFUNCTION MESSAGE?

Yes Both Electric Hydraulic Pump Selectors................. ON HYD 1 ELEC PUMP FAIL AND HYD 2 ELEC PUMP FAIL No MESSAGES DISAPPEAR?

AOM-1502-003

Yes

CONTINUED...

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REVISION 17

Hydraulics

Page 5

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Both Electric Hydraulic Pump Selectors................. AUTO

NOTE: – The messages will be posted again after the pumps are turned back to AUTO. Consider the messages spurious. – At any moment, if the Slat/Flap lever is moved out of position 0, the messages will extinguish. END

Associated Electric Hydraulic Pump Selector ....... OFF END

HYD 3 ELEC PUMP A FAIL Electric Hydraulic Pump A Selector........................ OFF

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Page 6

Hydraulics

REVISION 17

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

HYD 3 ELEC PUMP B FAIL Electric Hydraulic Pump B Selector........................ OFF END

HYD 1 (2) (3) LO QTY Crew Awareness. END

HYD 1 (2) SOV FAIL Crew Awareness. END

HYD 3 PUMP A NOT ON Crew Awareness.

AOM-1502-003

END

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REVISION 17

Hydraulics

Page 7

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 8

Hydraulics

REVISION 17

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

ICE AND RAIN PROTECTION TABLE OF CONTENTS Block

Page

AOM-1502-003

WARNING A-I WING 1 (2) LEAK............................................. 4-03-12......

1

CAUTION A-I ENG 1 (2) FAIL ................................................ A-I LO CAPACITY.................................................. A-I WING FAIL....................................................... A-I WING NO DISPATCH ....................................... ICE DETECTOR 1 (2) FAIL .................................... WINDSHIELD 1 (2) HTR FAIL ................................

4-03-12...... 4-03-12...... 4-03-12...... 4-03-12...... 4-03-12...... 4-03-12......

2 3 4 5 5 6

ADVISORY A-I ENG 1 (2) FAULT ............................................ A-I ENG 1 (2) LEAK .............................................. A-I MODE NOT AUTO........................................... A-I SWITCH OFF .................................................. ICE CONDITION ...................................................

Crew Awareness Crew Awareness Crew Awareness Crew Awareness Crew Awareness

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REVISION 21

Table of Contents

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 2

Table of Contents

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

A-I WING 1 (2) LEAK

Ice Protection Wing Button..................................... PUSH OUT Icing Conditions ..................................................... EXIT/AVOID A-I WING 1 (2) LEAK MESSAGE PERSISTS?

No

Yes Affected Bleed Button............................................. PUSH OUT XBleed Button......................................................... PUSH OUT Altitude.................................................................... MAX 31000 ft AFFECTED BLEED 1?

No

Yes APU Bleed Button................................................... PUSH OUT

During Landing: ICE CONDITIONS OR ICE ACCRETION?

No

Yes Landing Configuration: Slat/Flap................................................................ 5

AOM-1502-003

Set VREF FLAP 5 ICE.

CONTINUED...

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REVISION 21

Ice and Rain Protection

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.30.

UNFACTORED

NOTE: Do not perform the A-I WING FAIL procedure. END

A-I ENG 1 (2) FAIL Affected Ice Protection Engine Button.................... PUSH OUT, THEN IN A-I ENG 1 (2) FAIL MESSAGE EXTINGUISHES?

No

Yes

END

Ice Protection Mode Selector................................. ON A-I ENG 1 (2) FAIL MESSAGE PERSISTS?

No

Yes Icing Conditions....................................................... EXIT/AVOID HIGH ENGINE VIBRATION?

No

Yes

CONTINUED...

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Page 2

Ice and Rain Protection

REVISION 21

AOM-1502-003

ENGINE ABNORMAL VIBRATION Procedure........ ACCOMPLISH

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

...CONTINUED

Two minutes after exiting icing conditions: Ice Protection Mode Selector............................... AUTO END

A-I LO CAPACITY Thrust Levers.......................................................... ADVANCE A-I LO CAPACITY MESSAGE PERSISTS?

No

Yes Icing Conditions....................................................... EXIT/AVOID END

AOM-1502-003

END

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REVISION 21

Ice and Rain Protection

Page 3

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

A-I WING FAIL Ice Protection Wing Button..................................... PUSH OUT, THEN IN A-I WING FAIL MESSAGE EXTINGUISHES?

No

Yes

END

Ice Protection Mode Selector................................. ON A-I WING FAIL MESSAGE PERSISTS?

No

Yes Ice Protection Mode Selector.................................. AUTO Ice Protection Wing Button..................................... PUSH OUT Icing Conditions ..................................................... EXIT/AVOID LANDING IN ICING CONDITION OR WITH ICE ACCRETION?

No

Yes Landing Configuration: Slat/Flap................................................................ 5

CONTINUED...

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Page 4

Ice and Rain Protection

REVISION 21

AOM-1502-003

Set VREF FLAP 5 ICE .

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

...CONTINUED

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.30.

UNFACTORED

NOTE: Limit bank angle to 20°.

END

Two minutes after exiting icing conditions: Ice Protection Mode Selector............................... AUTO END

A-I WING NO DISPATCH Do not perform an assisted engine start. END

ICE DETECTOR 1 (2) FAIL When flying in icing conditions: Ice Protection Mode Selector............................... ON Two minutes after exiting icing conditions: Ice Protection Mode Selector........................... AUTO

AOM-1502-003

END

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REVISION 21

Ice and Rain Protection

Page 5

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

WINDSHIELD 1 (2) HTR FAIL Affected Windshield Heating Button....................... PUSH OUT, THEN IN WINDSHIELD 1 (2) HTR FAIL MSG EXTINGUISHES?

No

Yes

END

Affected Windshield Heating Button....................... PUSH OUT END

A-I ENG 1 (2) FAULT Crew Awareness.

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Page 6

Ice and Rain Protection

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

A-I ENG 1 (2) LEAK Crew Awareness. END

A-I MODE NOT AUTO Crew Awareness. END

A-I SWITCH OFF Crew Awareness. END

ICE CONDITION Crew Awareness.

AOM-1502-003

END

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REVISION 21

Ice and Rain Protection

Page 7

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 8

Ice and Rain Protection

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

LANDING GEAR AND BRAKES TABLE OF CONTENTS Block

Page

WARNING

AOM-1502-003

LG LEVER DISAG ................................................. 4-03-13......

1

CAUTION AUTOBRAKE FAIL ................................................ BRK LH (RH) FAIL................................................. BRK OVERHEAT ................................................... EMER BRK FAIL ................................................... LG NO DISPATCH ................................................. LG NOSE DOOR OPEN ........................................ LG WOW SYS FAIL............................................... PRKG BRK NOT RELEASED................................. STEER FAIL..........................................................

4-03-13...... 2 4-03-13...... 2 4-03-13...... 2 4-03-13...... 3 Crew Awareness 4-03-13...... 3 4-03-13...... 4 4-03-13...... 5 4-03-13...... 6

ADVISORY BRK CONTROL FAULT ......................................... BRK LH (RH) FAULT............................................. BRK PEDL LH (RH) SEAT FAIL............................. EMER BRK FAULT ............................................... LG TEMP EXCEEDANCE ..................................... STEER FAULT ......................................................

4-03-13...... 6 4-03-13...... 6 Crew Awareness Crew Awareness Crew Awareness Crew Awareness

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REVISION 21

Table of Contents

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 2

Table of Contents

REVISION 21

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

LG LEVER DISAG EICAS Indication: One or more landing gear indications disagree with the landing gear lever. Landing Gear Lever................................................ CYCLE LG LEVER DISAG MESSAGE PERSISTS?

No

Yes

DURING EXTENSION?

No

Yes

ABNORMAL LANDING GEAR EXTENSION Procedure................................................................ ACCOMPLISH END

Landing Gear.......................................................... DOWN Icing Conditions ..................................................... EXIT/AVOID END

AOM-1502-003

END

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REVISION 21

Landing Gear and Brakes

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

AUTOBRAKE FAIL Apply brakes normally. END

BRK LH (RH) FAIL NOTE: Thrust reverser may also be used to stop the airplane. During landing run gradually apply the normal brake, using rudder pedals to steer the airplane. Landing configuration: Slat/Flap................................................................ FULL Set VREF

FULL.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.65.

UNFACTORED

END

BRK OVERHEAT ON GROUND?

No

Yes Airplane................................................................... STOP Chocks.................................................................... ON Emergency/Parking Brake...................................... OFF END

Landing Gear.......................................................... DOWN

Yes

No CONTINUED...

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Page 2

Landing Gear and Brakes

REVISION 21

AOM-1502-003

BRK OVERHEAT MESSAGE PERSISTS?

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

...CONTINUED

After the BRK OVERHEAT message disappears: .........................................Wait 5 minutes.........................................

Landing Gear.......................................................... UP END

EMER BRK FAIL CONDITION:

Emergency/Parking Brake is inoperative.

When parking the airplane, use wheel chocks. END

LG NO DISPATCH Crew Awareness. END

LG NOSE DOOR OPEN Airspeed.................................................................. MAX 250 KIAS GEAR LEVER DOWN?

No

Yes CAUTION: DO NOT MOVE THE LANDING GEAR LEVER UP, EXCEPT FOR CLIMB PERFORMANCE TO CLEAR OBSTACLES.

AOM-1502-003

END

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REVISION 21

Landing Gear and Brakes

Page 3

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

END

LG WOW SYS FAIL LAND AT THE NEAREST SUITABLE AIRPORT. Icing Conditions ..................................................... EXIT/AVOID Landing configuration: Slat/Flap................................................................ FULL Set VREF

FULL.

CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.30.

UNFACTORED

NOTE: – Thrust Reversers, Steering, Ground Spoilers, Wing Anti-Ice and Ground Idle may not be available. – If the Weather Radar is inoperative, the Forced Standby option may be available to allow its use. If a go-around is required, keep the landing gear lever DOWN in case the gear lever can not be moved up.

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Page 4

Landing Gear and Brakes

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

PRKG BRK NOT RELEASED Emergency/Parking Brake Lever............................ CYCLE Ensure that the lever is completely stowed. MESSAGE PERSISTS?

No

Yes Parking Brake may or may not be locked.

Expect a potential tire burst during landing.

Landing Configuration: Slat/Flap................................................................ FULL Set VREF FULL. After Landing: If no unusual brake action is noticed, apply brakes normally. END

AOM-1502-003

END

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REVISION 21

Landing Gear and Brakes

Page 5

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

STEER FAIL Steer the airplane using differential braking and rudder. NOTE: During taxi, smooth radius turns must be performed. END

BRK CONTROL FAULT Brakes..................................................................... APPLY NORMALLY Landing configuration: Slat/Flap................................................................ FULL Set VREF FULL. END

BRK LH (RH) FAULT NOTE: During landing run, expect a slight directional tendency. Landing Configuration: Slat/Flap................................................................ FULL Set Vref FULL. Brakes..................................................................... APPLY NORMALLY CAUTION: MULTIPLY THE FULL FLAPS LANDING DISTANCE BY 1.28.

UNFACTORED

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Page 6

Landing Gear and Brakes

REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

BRK PEDL LH (RH) SEAT FAIL Crew Awareness. END

EMER BRK FAULT Crew Awareness. END

LG TEMP EXCEEDANCE Crew Awareness. END

STEER FAULT Crew Awareness.

AOM-1502-003

END

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REVISION 21

Landing Gear and Brakes

Page 7

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 8

Landing Gear and Brakes

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

OXYGEN TABLE OF CONTENTS Block

Page

CAUTION CREW OXY LO PRESS......................................... 4-03-14...... PAX OXY NOT DEPLOYED ................................... 4-03-14......

1 1

AOM-1502-003

ADVISORY OBSERVER OXY LO PRESS................................ 4-03-14...... 1 PAX OXY SW NOT AUTO ..................................... Crew Awareness

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REVISION 17

Table of Contents

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Table of Contents

REVISION 17

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

CREW OXY LO PRESS Altitude.................................................................... 10000 ft or MEA, WHICHEVER IS HIGHER END

PAX OXY NOT DEPLOYED If required: Passenger Oxygen Selector................................. OVRD END

OBSERVER OXY LO PRESS OBSERVER SEAT OCCUPIED?

No

Yes Altitude ................................................................... 10000 ft or MEA, WHICHEVER IS HIGHER END

AOM-1502-003

END

4-03-14 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Oxygen

Page 1

EMERGENCY AND ABNORMAL PROCEDURES ANNUNCIATED PROCEDURES

AIRPLANE OPERATIONS MANUAL

PAX OXY SW NOT AUTO Crew Awareness.

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Page 2

Oxygen

REVISION 17

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES SUPPLEMENTARY PROCEDURES

CATEGORY II OPERATION TABLE OF CONTENTS Block

AOM-1502-003

ABNORMAL ABNORMALITIES .................................................. ALTITUDE LOSS ................................................... AUTOPILOT MALFUNCTION ................................. ENGINE FAILURE ON FINAL APPROACH OR DURING GO-AROUND .................................... HARDOVER .......................................................... SLOWOVER..........................................................

Page

4-04-54...... 4-04-54...... 4-04-54......

4 1 3

4-04-54...... 4-04-54...... 4-04-54......

2 1 2

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REVISION 9

Table of Contents

Page 1

EMERGENCY AND ABNORMAL PROCEDURES SUPPLEMENTARY PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 2

Table of Contents

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

EMERGENCY AND ABNORMAL PROCEDURES

AIRPLANE OPERATIONS MANUAL

SUPPLEMENTARY PROCEDURES

ALTITUDE LOSS The demonstrated altitude loss due to a pitch down hardover during flight test is presented in the graph below. – Recovery initiated 1 second after failure recognition:

300

250

FAILURE OCCURS

AIRPLANE WHEEL 150

100

50

FAILURE RECOGNIZED RECOVERY INITIATED

0 −800 −600 −400 −200 RUNWAY THRESHOLD

SLOPE 1/29

0

200

400

600

800

EM170AOM050003C.DGN

ALTITUDE − ft

200

1000 1200 1400

HORIZONTAL DISTANCE − m

HARDOVER ALTITUDE LOSS

NOTE: The maximum demonstrated altitude loss due to autopilot malfunction is 20 ft. END

AOM-1502-003

HARDOVER If any unusual acceleration or motion is noticed on the airplane flight path the approach must be discontinued, and: Autopilot................................................................ DISENGAGE CONTINUED...

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REVISION 9

Category II Operation

Page 1

EMERGENCY AND ABNORMAL PROCEDURES SUPPLEMENTARY PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

MISSED APPROACH Procedure......................... PERFORM AS REQUIRED Perform a normal MISSED APPROACH Procedure, unless the approach is continued under visual conditions and the airplane position and attitude assure a safe landing. END

SLOWOVER The Slowover consists in a smooth and slow airplane attitude change due to an autopilot system malfunction. It may be recognized if one of the following symptoms occurs during approach: – Unusual glide slope small deviation. – Change in the rate of descent (small or large). – Excessive glide slope deviation and the GS indications becoming amber. – Autopilot self disconnection. If a Slowover tendency is confirmed: Autopilot................................................................ DISENGAGE MISSED APPROACH Procedure......................... PERFORM AS REQUIRED NOTE: Consider the possibility of continuing and performing the landing if under visual conditions and the airplane position and attitude assure a safe landing. END

ENGINE FAILURE ON FINAL APPROACH OR DURING GO-AROUND Go-Around............................................................... PERFORM

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Page 2

Category II Operation

REVISION 9

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES SUPPLEMENTARY PROCEDURES

AUTOPILOT MALFUNCTION BEFORE REACHING FAF If the autopilot disengages or has to be disengaged, try to reengage it. If the autopilot disengages again: MISSED APPROACH Procedure..................... PERFORM AS REQUIRED NOTE: Consider the possibility of continuing and performing the landing if under visual conditions and the airplane position and attitude assure a safe landing. AFTER REACHING FAF If the autopilot disengages or has to be disengaged, do not reengage the autopilot. MISSED APPROACH Procedure........................... PERFORM AS REQUIRED NOTE: Consider the possibility of continuing and performing the landing if under visual conditions and the airplane position and attitude assure a safe landing. DISPLAY WARNINGS DURING FINAL APPROACH Discontinue the approach if any of the following warnings occur: – APPR 1 ONLY displayed on Autopilot Approach Status Annunciator, – EICAS message APPR 2 NOT AVAIL presented, – RALT FAIL (cyan), – RA (amber), – GS (amber), – LOC (amber), – PIT (amber),

AOM-1502-003

– HDG (amber), – CAS (amber), CONTINUED...

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REVISION 9

Category II Operation

Page 3

EMERGENCY AND ABNORMAL PROCEDURES SUPPLEMENTARY PROCEDURES

AIRPLANE OPERATIONS MANUAL

...CONTINUED

– FPA (amber). Perform a normal MISSED APPROACH Procedure, unless the approach is continued under visual conditions and the airplane position and attitude assure a safe landing. EXCESSIVE DEVIATION WARNING If warning occurs above 200 ft Radio Altitude: Monitor the ILS deviation to ensure that the airplane returns to the center beam. If not recovered up to 200 ft radio altitude: Discontinue the approach. If warning occurs below 200 ft Radio Altitude: Discontinue the approach. In both cases, perform a normal MISSED APPROACH Procedure, unless the approach is continued under visual conditions and the airplane position and attitude assure a safe landing. END

ABNORMALITIES The following abnormalities are deviation from CAT II ILS tracking normal range and must be called out: – Excessive LOC or GS deviations. – Airspeed 10 kt higher or 5 kt lower than the Landing Reference Speed (VREF 5). – Roll angle in excess of 25°. – Pitch angle below -5° or above 5°. – Rate of descent in excess of 1200 ft/min.

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Page 4

Category II Operation

REVISION 9

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES SUPPLEMENTARY PROCEDURES

RVSM OPERATION TABLE OF CONTENTS Block

Page

AOM-1502-003

ABNORMAL EMERGENCY AND ABNORMAL PROCEDURES ... 4-04-57......

1

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REVISION 10

Table of Contents

Page 1

EMERGENCY AND ABNORMAL PROCEDURES SUPPLEMENTARY PROCEDURES

AIRPLANE OPERATIONS MANUAL

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Page 2

Table of Contents

REVISION 10

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY AND ABNORMAL PROCEDURES SUPPLEMENTARY PROCEDURES

EMERGENCY AND ABNORMAL PROCEDURES – In case of either emergency, abnormal situation or contingencies (equipment failures, weather, etc.), which affect the ability to maintain the cleared flight level, notify ATC and co-ordinate an action plan that is appropriate to the airspace concerned; – Notify ATC when encountering greater than moderate turbulence;

AOM-1502-003

– If unable to notify ATC and obtain an ATC clearance prior to deviating from the cleared flight level, follow any established contingency procedures and obtain ATC clearance as soon as possible.

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REVISION 10

RVSM OPERATION

Page 1

EMERGENCY AND ABNORMAL PROCEDURES SUPPLEMENTARY PROCEDURES

AIRPLANE OPERATIONS MANUAL

4-04-57 Copyright © by Embraer. Refer to cover page for details.

Page 2

RVSM OPERATION

REVISION 10

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

SECTION 5 PERFORMANCE TABLE OF CONTENTS Block

Page

Configuration and Definitions............................ 5-01 ........... AIRSPEED DEFINITIONS..................................... 5-01 ........... METEOROLOGICAL DEFINITIONS...................... 5-01 ........... CONTAMINATED RUNWAY.................................. 5-01 ...........

1 1 3 3

Data Conversion................................................... 5-10 ........... DEMONSTRATED CROSSWIND.......................... 5-10 ........... WIND AND ALTITUDE CONVERSION.................. 5-10 ........... ALTIMETER SETTING TO STATION PRESSURE.. 5-10 ........... GEOMETRIC HEIGHT TO PRESSURE HEIGHT.. 5-10 ...........

1 1 1 3 6

Thrust Setting....................................................... 5-15 ........... THRUST SETTING TABLES................................. 5-15 ...........

1 1

Takeoff................................................................... 5-20 ........... TAKEOFF ANALYSIS DESCRIPTION AND USE.. 5-20 ........... ASSUMED TEMPERATURE REDUCED THRUST........................................................... 5-20 ........... FLEXIBLE TEMPERATURE DETERMINATION TABLES............................................................ 5-20 ........... SIMPLIFIED TAKEOFF ANALYSIS TABLES......... 5-20 ........... TAKEOFF SPEEDS............................................... 5-20 ........... FLAP RETRACTION SPEED SCHEDULE............ 5-20 ........... FINAL SEGMENT SPEED..................................... 5-20 ........... STAB TRIM SETTING FOR TAKEOFF................. 5-20 ...........

1 1 4 8 28 65 78 79 81

EMBRAER 170 Models

CLIMB GRADIENT - ALL ENGINES OPERATING.. 5-20 ........... 82 EMBRAER 175 Models

AOM-1502-003

CLIMB GRADIENT - ALL ENGINES OPERATING.. 5-20 ........... 108 Supplementary Takeoff Information................... 5-25 ........... SUPPLEMENTARY TAKEOFF INFORMATION.... 5-25 ........... ACN........................................................................ 5-25 ...........

1 1 7

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REVISION 21

Table of Contents

Page 1

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

Block Page Approach............................................................... 5-30 ........... 1 APPROACH AND LANDING SPEEDS.................. 5-30 ........... 1 EMBRAER 170 Models

APPROACH CLIMB GRADIENT........................... 5-30 ........... 5 APPROACH AND LANDING SPEEDS.................. 5-30 ........... 18 EMBRAER 175 Models

APPROACH CLIMB GRADIENT........................... 5-30 ........... 22 Landing................................................................. 5-35 ...........

1

EMBRAER 170 Models

UNFACTORED LANDING DISTANCE.................. 5-35 ...........

1

EMBRAER 175 Models

UNFACTORED LANDING DISTANCE.................. 5-35 ........... 28 OPERATIONAL LANDING DISTANCE.................. 5-35 ........... 54 EMBRAER 170 Models, except J-Air, except Operational Landing Braking Action

OPERATIONAL LANDING DISTANCE.................. 5-35 ........... 57 EMBRAER 175 Models, except Operational Landing Braking Action

OPERATIONAL LANDING DISTANCE.................. 5-35 ........... 78 EMBRAER 170 Models

QUICK TURN AROUND WEIGHT......................... 5-35 ........... 119 EMBRAER 175 Models

QUICK TURN AROUND WEIGHT......................... 5-35 ........... 132 1 1

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Table of Contents

REVISION 21

AOM-1502-003

Supplementary Operations................................. 5-40 ........... CAT II OPERATION............................................... 5-40 ...........

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

AIRSPEED DEFINITIONS INDICATED AIRSPEED – KIAS It is the reading on the airspeed indicator (knots), as installed in the airplane, uncorrected for static source position error. Zero instrument error is assumed.

CALIBRATED AIRSPEED – KCAS It is the indicated airspeed (knots), corrected for static source position error.

TRUE AIRSPEED – TAS It is the equivalent airspeed corrected for atmospheric density effects.

CRITICAL ENGINE FAILURE SPEED – VEF It is the speed at which the critical engine fails. May not be less than VMCG.

1-G STALL SPEED – VS1G Is the minimum speed at which the lift provided by the wing is capable of supporting the weight of the airplane.

REFERENCE STALL SPEED – VSR It is stall speed used as the reference in determining the various airplane speeds. VSR may not be less than VS1G.

TAKEOFF DECISION SPEED – V1 It is the speed at which, following a failure of one engine at VEF, the decision to continue the takeoff results in:

•

A takeoff distance to a height of 35 ft at V2 speed, that will not exceed the available takeoff distance;

•

A distance to bring the airplane to a full stop that will not exceed the accelerate-stop distance available.

AOM-1502-003

V1 must not be greater than the rotation speed (VR).

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REVISION 18

Configuration and Definitions

Page 1

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

ROTATION SPEED – VR It is the speed at which rotation is initiated during the takeoff, to attain the takeoff safety speed at or before a height of 35 ft above runway surface.

TAKEOFF SAFETY SPEED – V2 The target speed to be attained at a height of 35 ft during a takeoff with an engine failure.

AIR MINIMUM CONTROL SPEED – VMCA The minimum flight speed at which the airplane is controllable with a maximum 5° bank, when one engine suddenly becomes inoperative with the remaining engine operating at takeoff power. The value presented represents the most critical combination of power, weight, and center of gravity.

GROUND MINIMUM CONTROL SPEED – VMCG The minimum speed on the ground at which the takeoff can be continued, utilizing aerodynamic controls alone, when one engine suddenly becomes inoperative and the remaining engine is operating at takeoff power. The value presented represents the most critical combination of power, weight, and center of gravity.

LANDING REFERENCE SPEED – VREFXX The speed at a height of 50 ft in a normal landing. This speed is equal to 1.23 VS1G in the landing configuration (gear down and specific landing flaps XX).

MANEUVERING SPEED – VA The maximum speed at which application of full available aileron or rudder will not overstress the airplane. Maneuver involving pitching control must not exceed the limit load factor defined in Section 2 – Limitations.

VMCL is the minimum control speed during landing and approach with all engines operating, when the critical engine is suddenly made inoperative.

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Page 2

Configuration and Definitions

REVISION 18

AOM-1502-003

MINIMUM CONTROL SPEEDS DURING LANDING AND APPROACH – VMCL

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

FINAL TAKEOFF SEGMENT SPEED – VFS It is the speed to be achieved during final segment, with landing gear up and flaps retracted.

METEOROLOGICAL DEFINITIONS INTERNATIONAL STANDARD ATMOSPHERE – ISA As accepted by the International Civil Aviation Organization.

STATIC AIR TEMPERATURE – SAT Outside air temperature as indicated on the MFD.

TRUE OUTSIDE AIR TEMPERATURE The free air static (ambient) temperature.

WIND VELOCITY The actual wind velocity at a height of 10 m (32.8 ft), reported from the tower and corrected by the wind component chart to a headwind or tailwind component parallel to the flight path.

CONTAMINATED RUNWAY A runway is considered to be contaminated when more than 25% of the runway surface area (whether in isolated areas or not) within the required length and width being used is covered by the following: – surface water more than 3 mm (0.125 in) deep, or by slush, or loose snow, equivalent to more than 3 mm (0.125 in) of water; – snow which has been compressed into a solid mass which resists further compression and will hold together or break into lumps if picked up (compacted snow); or

AOM-1502-003

– ice, including wet ice.

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REVISION 18

Configuration and Definitions

Page 3

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

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Page 4

Configuration and Definitions

REVISION 18

AOM-1502-003

INTENTIONALLY BLANK

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

DEMONSTRATED CROSSWIND The maximum demonstrated crosswind component for landing is 28 kt. This maximum demonstrated value is not considered to be limiting.

WIND AND ALTITUDE CONVERSION

WIND COMPONENT 80 WIND DIRECTION RELATIVE TO RUNWAY (STRAIGHT LINES)

60 0°

50

10°

20° 30° 40°

40

50° 30 60° 20

70°

10

EFFECTIVE TAILWIND COMPONENT − kt

0

80° 90° 0

10

20

30

40

50 100°

−10

CROSSWIND COMPONENT − kt

110°

−20

120° −30 130° 140°

−40 150° −50 180°

170°

REPORTED WIND SPEED (CURVED LINES)

160°

EM170AOM050004A.DGN

EFFECTIVE HEADWIND COMPONENT − kt

70

−60 −70 −80

AOM-1502-003

WIND COMPONENT

CONTINUED...

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REVISION 21

Data Conversion

Page 1

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

...CONTINUED

USE

Enter the chart with the reported wind velocity and the relative angle to the runway, to read the wind component parallel to the runway and the crosswind.

EXAMPLE Given: Wind velocity............................................................. 20 kt Wind direction............................................................ 60°

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Page 2

Data Conversion

REVISION 21

AOM-1502-003

Determine: Wind component parallel to the runway................... 10 kt Crosswind.................................................................. 17.5 kt

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

ALTIMETER SETTING TO STATION PRESSURE QNH TO PRESSURE ALTITUDE QNH inHg 28.81 28.92 29.03 29.13 29.24 29.35 29.45 29.56 29.67 29.77 29.88 29.98 30.09 30.20 30.31 30.42 30.53 30.64 30.75 30.86 30.97

AOM-1502-003

Example:

to to to to to to to to to to to to to to to to to to to to to

28.91 29.02 29.12 29.23 29.34 29.44 29.55 29.66 29.76 29.87 29.97 30.08 30.19 30.30 30.41 30.52 30.63 30.74 30.85 30.96 31.07

hPa 976 to 979 980 to 983 984 to 986 987 to 990 991 to 994 995 to 997 998 to 1001 1002 to 1004 1005 to 1008 1009 to 1012 1013 to 1015 1016 to 1019 1020 to 1022 1023 to 1026 1027 to 1030 1031 to 1034 1035 to 1037 1038 to 1041 1042 to 1045 1046 to 1048 1049 to 1052

CORRECTION TO ELEVATION FOR PRES. ALT. (ft) 1000 900 800 700 600 500 400 300 200 100 0 -100 -200 -300 -400 -500 -600 -700 -800 -900 -1000

Elevation = 2000 ft QNH = 29.60 in.Hg Correction = 300 ft Pressure Altitude = 2300 ft

CONTINUED...

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REVISION 21

Data Conversion

Page 3

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

...CONTINUED

QFE TO STATION PRESSURE QFE

PRESSURE

PRESSURE

inHg

hPa

ALTITUDE (ft)

inHg

hPa

ALTITUDE (ft)

31.01

1050

-989

25.55

865

4313

30.86

1045

-856

25.40

860

4468

30.71

1040

-723

25.25

855

4625

30.57

1035

-589

25.10

850

4781

30.42

1030

-454

24.96

845

4939

30.27

1025

-319

24.81

840

5097

30.12

1020

-184

24.66

835

5257

29.98

1015

-48

24.51

830

5417

29.83

1010

89

24.36

825

5579

29.68

1005

227

24.21

820

5740

29.53

1000

364

24.07

815

5903

29.38

995

503

23.92

810

6065

29.23

990

641

23.77

805

6230

29.09

985

781

23.62

800

6394 6561

28.94

980

921

23.48

795

28.79

975

1062

23.33

790

6727

28.64

970

1202

23.18

785

6895

28.50

965

1344

23.03

780

7063

28.35

960

1486

22.89

775

7233

28.20

955

1630

22.74

770

7402

28.05

950

1773

22.59

765

7574

27.91

945

1918

22.44

760

7745

27.76

940

2062

22.30

755

7920

27.61

935

2208

22.15

750

8095

27.46

930

2353

22.00

745

8269

27.32

925

2500

21.85

740

8442

27.17

920

2647

21.71

735

8619

27.02

915

2796

21.56

730

8796

26.87

910

2944

21.41

725

8975

26.73

905

3094

21.26

720

9154

26.58

900

3243

21.12

715

9335

26.43

895

3394

20.97

710

9516

CONTINUED...

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Page 4

Data Conversion

REVISION 21

AOM-1502-003

QFE

PERFORMANCE

AIRPLANE OPERATIONS MANUAL ...CONTINUED

AOM-1502-003

QFE

QFE

PRESSURE

PRESSURE

inHg

hPa

ALTITUDE (ft)

26.28

890

3545

20.82

705

9699

26.14

885

3698

20.67

700

9882

25.99

880

3850

20.53

695

10068

25.84

875

4004

20.38

690

10253

25.69

870

4157

20.19

685

10439

inHg

hPa

ALTITUDE (ft)

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REVISION 21

Data Conversion

Page 5

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

GEOMETRIC HEIGHT TO PRESSURE HEIGHT Pressure altimeters are calibrated to indicate true altitude under International Standard Atmosphere (ISA) conditions. Any deviation from ISA will therefore result in an erroneous reading on the altimeter. When the temperature is higher than ISA, the true altitude will be higher than the figure indicated by the altimeter. When the temperature is lower than ISA, the true altitude will be lower than the figure indicated by the altimeter. The altimeter error may be significant under conditions of extremely cold temperature (ICAO PANS-OPS Vol I 3.1.4.5.2). AERODROME TEMP. (°C) 0 -10 -20 -30 -40 -50 AERODROME TEMP. (°C) 0 -10 -20 -30 -40 -50

HEIGHT ABOVE THE ELEVATION OF THE ALTIMETER SETTING SOURCE (ft) 200 300 400 500 600 700 800 20 20 30 30 40 40 50 20 30 40 50 60 70 80 30 50 60 70 90 100 120 40 60 80 100 120 140 150 50 80 100 120 150 170 190 60 90 120 150 180 210 240 HEIGHT ABOVE THE ELEVATION OF THE ALTIMETER SETTING SOURCE (ft) 900 1000 1500 2000 3000 4000 5000 50 60 90 120 170 230 280 90 100 150 200 290 390 490 130 140 210 280 420 570 710 170 190 280 380 570 760 950 220 240 360 480 720 970 1210 270 300 450 590 890 1190 1500

The tables above are based on an aerodrome at sea level. However, they can be used operationally at any aerodrome elevation.

Airport Elevation........................................................ 1500 ft Airport Temperature................................................... -20°C CONTINUED...

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Page 6

Data Conversion

REVISION 21

AOM-1502-003

Example:

PERFORMANCE

AIRPLANE OPERATIONS MANUAL ...CONTINUED

Obstacle Height above airport elevation................... 800 ft Altimeter adjusted to airport QNH (on ground altimeter reads 1500 ft). Refer to table at 800 ft and -20°C and read 120 ft. Therefore, when the airplane reaches the obstacle geometric height, the altimeter will read 1500 + 800 + 120 = 2420 ft.

EM170AOM050005C.DGN

ALTIMETERS READ 2420 ft

AOM-1502-003

ELEVATION=1500 ft T=−20°C ALTIMETERS READ 1500 ft

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REVISION 21

Data Conversion

Page 7

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

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Page 8

Data Conversion

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

THRUST SETTING TABLES Thrust settings tables are presented for various pressure altitudes and static air temperatures, with engine bleed closed or open, and anti-ice on or off.

AOM-1502-003

The following tables present Takeoff N1 regarding T/O-1 and T/O-2 mode and Go-around N1 for CF34-8E5 engines.

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REVISION 16

Thrust Setting

Page 1

PERFORMANCE

AIRPLANE OPERATIONS MANUAL N1 FOR T/O-1 ECS ON — ANTI-ICE OFF AIRSPEED: 0 KCAS CF34-8E5 ENGINE Static Air Temperature — °C

-40 79.1 80.4 80.7 81.1 81.5 81.8 82.2 82.6 83.1 83.5

-35 79.9 81.2 81.6 81.9 82.3 82.7 83.1 83.4 83.9 84.3

-30 80.8 82.0 82.4 82.8 83.1 83.5 83.9 84.3 84.7 85.1

-25 81.6 82.9 83.2 83.6 83.9 84.3 84.7 85.1 85.5 85.8

-20 82.4 83.7 84.0 84.3 84.7 85.0 85.5 86.0 86.3 86.6

-15 83.1 84.5 84.8 85.1 85.5 85.8 86.3 86.8 87.1 87.4

-10 83.9 85.3 85.6 85.9 86.3 86.6 87.1 87.6 87.9 88.2

-5 84.6 86.1 86.4 86.7 87.0 87.4 87.9 88.4 88.7 88.9

0 85.4 86.9 87.2 87.5 87.8 88.2 88.6 89.2 89.4 89.6

5 86.2 87.7 87.9 88.2 88.6 88.9 89.4 90.0 90.2 90.4

Pressure Altitude (ft) -1000

10 86.9

15 87.6

20 88.4

25 89.1

30 89.8

35 89.6

40 88.6

45 87.2

50 85.6

Static Air Temperature — °C

0

88.5

89.2

90.0

90.8

91.6

90.3

89.3

87.7

86.1

1000 2000 3000 4000

88.7 89.0 89.3 89.7

89.5 89.7 90.1 90.4

90.2 90.5 90.8 91.2

91.0 91.2 91.3 91.2

91.2 91.0 90.8 90.7

90.3 90.4 90.2 90.1

89.1 89.3 89.2 89.1

87.7 87.9 87.9 88.0

86.2 86.4 86.6 86.9

5000

90.2

90.9

91.7

91.0

90.6

89.9

89.0

88.1

87.2

6000 7000 8000

90.8 90.9 91.1

91.5 91.7 91.7

91.7 91.4 91.3

90.9 90.7 90.7

90.3 90.1 90.1

89.6 89.5 89.5

88.9 88.8 88.9

88.1 88.2 88.2

87.3 87.5 ---

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Page 2

Thrust Setting

REVISION 16

AOM-1502-003

Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

N1 FOR T/O-1 ECS ON — WING AND ENGINE ANTI-ICE ON AIRSPEED: 0 KCAS CF34-8E5 ENGINE

AOM-1502-003

Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000

Static Air Temperature — °C -35 79.8 81.0 81.4 81.7 82.0 82.4 82.8 83.2 83.7 84.0

-30 80.6 81.9 82.2 82.5 82.9 83.2 83.6 84.1 84.5 84.8

-25 81.4 82.7 83.0 83.3 83.7 84.0 84.4 85.0 85.3 85.6

-20 82.2 83.5 83.8 84.1 84.5 84.9 85.3 85.8 86.1 86.4

-15 82.9 84.4 84.7 85.0 85.4 85.8 86.2 86.7 87.0 87.3

-10 83.8 85.3 85.6 85.9 86.3 86.6 87.1 87.6 87.9 88.1

-5 84.6 86.2 86.4 86.7 87.0 87.4 87.9 88.4 88.7 88.9

0 85.4 87.0 87.2 87.5 87.8 88.1 88.7 89.2 89.4 89.6

5 86.2 87.7 87.9 88.2 88.6 88.9 89.4 90.0 90.2 90.3

10 86.9 88.5 88.7 88.9 89.3 89.7 90.2 90.8 91.0 90.7

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REVISION 16

Thrust Setting

Page 3

PERFORMANCE

AIRPLANE OPERATIONS MANUAL N1 FOR T/O-1 ECS OFF — ANTI-ICE OFF AIRSPEED: 0 KCAS CF34-8E5 ENGINE Static Air Temperature — °C

-40 79.7 80.9 81.3 81.8 82.1 82.5 82.9 83.3 83.8 84.3

-35 80.5 81.8 82.2 82.6 83.0 83.3 83.7 84.2 84.7 85.1

-30 81.3 82.6 83.0 83.4 83.8 84.2 84.6 85.1 85.5 85.9

-25 82.1 83.4 83.9 84.2 84.6 85.0 85.4 85.9 86.3 86.7

-20 82.9 84.3 84.7 85.0 85.4 85.8 86.2 86.7 87.1 87.5

-15 83.7 85.1 85.5 85.8 86.2 86.6 87.0 87.5 87.9 88.3

-10 84.5 85.9 86.3 86.7 87.0 87.4 87.8 88.4 88.7 89.1

-5 85.3 86.7 87.1 87.4 87.8 88.2 88.7 89.2 89.5 89.8

0 86.0 87.5 87.9 88.2 88.6 89.0 89.4 90.0 90.3 90.6

5 86.8 88.3 88.7 89.0 89.4 89.7 90.2 90.8 91.1 91.3

Pressure Altitude (ft) -1000

10 87.5

15 88.3

20 89.0

25 89.8

30 90.5

35 90.3

40 89.3

45 88.0

50 86.5

Static Air Temperature — °C

0

89.1

89.9

90.7

91.5

92.3

91.0

90.0

88.5

86.9

1000 2000 3000 4000

89.4 89.7 90.1 90.5

90.2 90.5 90.9 91.3

90.9 91.2 91.6 92.0

91.7 92.0 92.2 92.0

91.9 91.7 91.6 91.5

91.1 91.2 91.0 90.9

89.9 90.1 90.0 90.0

88.5 88.7 88.7 88.9

87.1 87.3 87.5 87.8

5000

91.0

91.8

92.5

91.9

91.4

90.8

89.9

89.0

88.1

6000 7000 8000

91.6 91.8 92.0

92.4 92.6 92.6

92.6 92.3 92.2

91.7 91.7 91.6

91.1 91.1 91.0

90.5 90.4 90.4

89.8 89.8 89.9

89.1 89.2 89.3

88.4 88.5 ---

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Page 4

Thrust Setting

REVISION 16

AOM-1502-003

Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

N1 FOR T/O-1 ECS OFF — WING AND ENGINE ANTI-ICE ON AIRSPEED: 0 KCAS CF34-8E5 ENGINE

AOM-1502-003

Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000

Static Air Temperature — °C -35 80.5 81.8 82.2 82.6 83.0 83.3 83.8 84.3 84.7 85.0

-30 81.3 82.6 83.0 83.4 83.8 84.2 84.6 85.1 85.5 85.8

-25 82.1 83.5 83.9 84.3 84.6 85.0 85.4 85.9 86.3 86.7

-20 82.9 84.3 84.7 85.0 85.4 85.8 86.2 86.8 87.1 87.5

-15 83.7 85.2 85.5 85.8 86.2 86.6 87.0 87.6 87.9 88.2

-10 84.5 86.0 86.3 86.6 87.0 87.4 87.9 88.4 88.7 89.0

-5 85.3 86.8 87.1 87.4 87.8 88.2 88.7 89.3 89.5 89.8

0 86.0 87.6 87.9 88.2 88.6 89.0 89.5 90.1 90.3 90.5

5 86.8 88.4 88.7 89.0 89.4 89.7 90.2 90.9 91.1 91.3

10 87.6 89.2 89.4 89.7 90.1 90.5 91.0 91.7 91.9 91.6

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REVISION 16

Thrust Setting

Page 5

PERFORMANCE

AIRPLANE OPERATIONS MANUAL N1 FOR T/O-2 ECS ON — ANTI-ICE OFF AIRSPEED: 0 KCAS CF34-8E5 ENGINE Static Air Temperature — °C

-40 77.0 78.1 78.4 78.7 78.9 79.1 79.4 79.7 80.1 80.5

-35 77.8 78.9 79.2 79.5 79.7 79.9 80.2 80.6 80.9 81.3

-30 78.6 79.7 80.0 80.2 80.5 80.7 81.0 81.3 81.7 82.1

-25 79.4 80.5 80.7 81.0 81.3 81.5 81.8 82.1 82.5 82.9

-20 80.1 81.2 81.5 81.8 82.0 82.3 82.6 82.9 83.3 83.7

-15 80.9 82.0 82.3 82.6 82.8 83.0 83.3 83.7 84.1 84.4

-10 81.6 82.7 83.0 83.3 83.6 83.8 84.1 84.5 84.9 85.2

-5 82.4 83.5 83.8 84.1 84.3 84.6 84.9 85.2 85.6 86.0

0 83.1 84.2 84.5 84.8 85.1 85.3 85.6 86.0 86.4 86.8

5 83.8 85.0 85.2 85.5 85.8 86.1 86.4 86.7 87.1 87.5

Pressure Altitude (ft) -1000

10 84.5

15 85.2

20 85.9

25 86.6

30 87.3

35 87.1

40 86.2

45 85.3

50 84.4

Static Air Temperature — °C

0

85.7

86.4

87.1

87.8

88.5

87.7

86.9

85.9

85.0

1000 2000 3000 4000

86.0 86.3 86.5 86.8

86.7 87.0 87.3 87.5

87.4 87.7 88.0 88.3

88.1 88.4 88.4 88.1

88.2 87.9 87.6 87.3

87.4 87.1 86.8 86.4

86.5 86.2 85.9 85.5

85.6 85.3 84.9 84.5

84.7 84.3 83.9 83.5

5000

87.1

87.8

88.6

87.8

87.1

86.1

85.2

84.2

83.1

6000 7000 8000

87.5 87.9 88.3

88.2 88.6 88.8

88.4 88.2 88.1

87.6 87.5 87.3

86.8 86.6 86.5

85.9 85.7 85.6

84.9 84.8 84.7

84.0 83.8 83.7

82.9 82.8 ---

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Page 6

Thrust Setting

REVISION 16

AOM-1502-003

Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

N1 FOR T/O-2 ECS ON — WING AND ENGINE ANTI-ICE ON AIRSPEED: 0 KCAS CF34-8E5 ENGINE

AOM-1502-003

Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000

Static Air Temperature — °C -35 77.6 78.7 79.0 79.2 79.5 79.7 80.0 80.3 80.7 81.0

-30 78.4 79.5 79.7 80.0 80.3 80.5 80.8 81.1 81.5 81.8

-25 79.1 80.2 80.5 80.8 81.0 81.3 81.6 81.9 82.3 82.6

-20 79.9 81.0 81.3 81.6 81.8 82.1 82.3 82.7 83.1 83.5

-15 80.7 81.8 82.1 82.4 82.6 82.8 83.1 83.5 84.0 84.4

-10 81.4 82.6 82.9 83.2 83.4 83.7 84.0 84.4 84.9 85.2

-5 82.3 83.5 83.7 84.0 84.3 84.5 84.9 85.3 85.6 86.0

0 83.0 84.2 84.5 84.8 85.1 85.3 85.6 86.0 86.4 86.8

5 83.8 84.9 85.3 85.6 85.8 86.1 86.4 86.7 87.1 87.5

10 84.5 85.7 86.0 86.3 86.6 86.8 87.1 87.5 87.9 87.7

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REVISION 16

Thrust Setting

Page 7

PERFORMANCE

AIRPLANE OPERATIONS MANUAL N1 FOR T/O-2 ECS OFF — ANTI-ICE OFF AIRSPEED: 0 KCAS CF34-8E5 ENGINE Static Air Temperature — °C

-40 77.6 78.7 79.0 79.3 79.5 79.7 80.1 80.4 80.8 81.2

-35 78.4 79.5 79.8 80.1 80.3 80.6 80.9 81.2 81.6 82.1

-30 79.2 80.3 80.6 80.8 81.1 81.4 81.7 82.0 82.4 82.9

-25 79.9 81.0 81.3 81.6 81.9 82.2 82.5 82.8 83.2 83.7

-20 80.7 81.8 82.1 82.4 82.7 83.0 83.3 83.6 84.0 84.5

-15 81.5 82.6 82.9 83.2 83.5 83.7 84.1 84.4 84.8 85.3

-10 82.2 83.4 83.7 84.0 84.3 84.5 84.9 85.2 85.7 86.0

-5 83.0 84.2 84.5 84.8 85.0 85.3 85.6 86.0 86.4 86.8

0 83.7 84.9 85.2 85.5 85.8 86.1 86.4 86.8 87.2 87.6

5 84.5 85.6 85.9 86.2 86.5 86.8 87.1 87.5 87.9 88.4

Pressure Altitude (ft) -1000

10 85.2

15 85.9

20 86.6

25 87.3

30 88.0

35 87.8

40 87.0

45 86.1

50 85.2

Static Air Temperature — °C

0

86.3

87.1

87.8

88.5

89.3

88.4

87.6

86.8

85.9

1000 2000 3000 4000

86.7 87.0 87.3 87.6

87.4 87.7 88.0 88.3

88.1 88.5 88.8 89.1

88.9 89.2 89.2 88.9

89.0 88.7 88.4 88.2

88.2 87.9 87.6 87.3

87.4 87.1 86.7 86.4

86.5 86.2 85.8 85.5

85.6 85.3 84.9 84.5

5000

87.9

88.6

89.4

88.7

87.9

87.0

86.1

85.2

84.2

6000 7000 8000

88.3 88.7 89.2

89.0 89.5 89.7

89.2 89.1 89.0

88.5 88.4 88.3

87.7 87.6 87.5

86.8 86.7 86.6

85.9 85.8 85.7

85.0 84.9 84.8

84.0 84.0 ---

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Page 8

Thrust Setting

REVISION 16

AOM-1502-003

Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

N1 FOR T/O-2 ECS OFF — WING AND ENGINE ANTI-ICE ON AIRSPEED: 0 KCAS CF34-8E5 ENGINE

AOM-1502-003

Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000

Static Air Temperature — °C -35 78.3 79.5 79.8 80.0 80.3 80.6 80.9 81.2 81.6 82.1

-30 79.1 80.3 80.6 80.9 81.1 81.4 81.7 82.0 82.4 82.9

-25 80.0 81.0 81.3 81.7 81.9 82.2 82.5 82.8 83.2 83.7

-20 80.7 81.8 82.1 82.4 82.7 83.0 83.3 83.6 84.0 84.5

-15 81.5 82.6 82.9 83.2 83.5 83.8 84.1 84.4 84.9 85.3

-10 82.2 83.4 83.7 84.0 84.3 84.5 84.9 85.2 85.7 86.1

-5 83.0 84.2 84.5 84.7 85.0 85.3 85.6 86.0 86.4 86.9

0 83.7 84.9 85.2 85.5 85.8 86.1 86.4 86.8 87.2 87.6

5 84.5 85.6 85.9 86.3 86.6 86.8 87.2 87.5 88.0 88.4

10 85.2 86.4 86.7 87.0 87.3 87.6 87.9 88.3 88.7 88.6

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REVISION 16

Thrust Setting

Page 9

PERFORMANCE

AIRPLANE OPERATIONS MANUAL N1 FOR GO-AROUND ECS OFF — ANTI-ICE OFF CF34-8E5 ENGINE

Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000

-40 81.5 82.8 83.7 84.2 84.6 84.9 85.4 85.9 86.3

-35 82.4 83.7 84.5 85.0 85.4 85.8 86.3 86.7 87.1

-30 83.2 84.5 85.4 85.9 86.3 86.6 87.1 87.5 87.9

-25 84.0 85.3 86.2 86.7 87.1 87.4 87.9 88.3 88.7

-20 84.8 86.2 87.0 87.5 87.9 88.2 88.7 89.1 89.4

-15 85.7 87.0 87.8 88.3 88.7 89.0 89.4 89.9 90.2

-10 86.5 87.8 88.7 89.2 89.5 89.8 90.2 90.7 90.9

-5 87.2 88.6 89.5 90.0 90.2 90.5 91.0 91.4 91.6

0 88.0 89.4 90.2 90.7 91.0 91.3 91.7 92.2 92.3

5 88.8 90.1 91.0 91.5 91.8 92.1 92.5 92.9 93.0

8000

86.7

87.5

88.2

89.0

89.7

90.4

91.2

91.8

92.5

93.2

Static Air Temperature — °C

Pressure Altitude (ft) -1000

10 89.5

15 90.3

20 91.1

25 91.8

30 92.6

35 92.8

40 92.0

45 90.8

50 90.3

0

90.9

91.7

92.4

93.2

94.0

93.1

92.0

90.8

90.9

1000 2000 3000 4000

91.8 92.3 92.5 92.8

92.5 93.0 93.3 93.6

93.3 93.8 94.0 94.2

94.0 94.4 94.4 94.3

94.1 94.1 93.9 93.9

93.1 93.2 93.1 93.1

92.0 92.1 92.2 92.4

91.4 91.9 -----

---------

5000

93.2

94.0

94.4

94.2

93.7

93.0

92.5

---

---

6000 7000 8000

93.6 93.8 93.9

94.1 94.2 94.2

94.3 94.3 94.4

94.1 94.0 94.0

93.6 93.6 93.5

93.1 93.0 ---

-------

-------

-------

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Page 10

Thrust Setting

REVISION 16

AOM-1502-003

Static Air Temperature — °C

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

AOM-1502-003

N1 FOR GO-AROUND ECS OFF — WING AND ENGINE ANTI-ICE ON CF34-8E5 ENGINE Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000

-35 82.4 83.7 84.6 85.1 85.4 85.8 86.2 86.7 87.0

-30 83.2 84.5 85.4 85.9 86.3 86.6 87.0 87.5 87.8

-25 84.1 85.4 86.2 86.8 87.1 87.4 87.8 88.3 88.5

-20 84.9 86.2 87.0 87.6 87.9 88.2 88.6 89.1 89.3

-15 85.7 87.0 87.9 88.4 88.7 89.0 89.4 89.8 90.1

-10 86.5 87.8 88.7 89.2 89.5 89.8 90.2 90.6 90.8

-5 87.2 88.6 89.5 90.0 90.2 90.5 91.0 91.3 91.5

0 88.0 89.4 90.3 90.8 91.0 91.3 91.7 92.1 92.2

5 88.8 90.2 91.0 91.5 91.8 92.0 92.5 92.7 92.7

10 89.6 91.0 91.8 92.3 92.6 92.8 92.9 92.9 92.9

8000

87.3

88.0

88.8

89.5

90.3

91.0

91.7

92.3

92.7

92.9

Static Air Temperature — °C

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REVISION 16

Thrust Setting

Page 11

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

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Page 12

Thrust Setting

REVISION 16

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

TAKEOFF ANALYSIS DESCRIPTION AND USE Using Embraer Runway Analysis Software, airlines can produce takeoff analysis tables. Using these tables the crew is able to get the following information for a certain ambient conditions and airplane configuration: – Maximum takeoff weight and the performance limitation code; – Takeoff speeds;

AOM-1502-003

– Takeoff N1.

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REVISION 21

Takeoff

Page 1

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

PART A

NOTE: FOR REFERENCE ONLY

EMBRAER XXX − TAKEOFF ANALYSIS

GTY/GOTA GOTHAM CITY 30

CF34−YYY Engines ZZZ Certification Auto Brakes: On

Brakes: ABSC 90002340PR

ATTCS: On Air Conditioning: Off V2/Vs: Fixed 1.18 Reverse: No reverse thrust credit

Thrust: T/O−1

Elevation: 0 ft Align Allow TODA: 0,0 m

Length: 2890 m Clearway: 0 m Stopway: 0 m

Slop: 0,00 %

Align Allow ASDA: 0 m

Flaps: 1 App Flaps: 2 Anti Ice: OFF MTOW User Defined: 48000 kg

Rwy Condition: DRY

2°seg. obst. clearance preferred Stop Margin: No Stop Margin V1/Vr: Optimum V1 CG: Standard

Gross Level Off Altitude: 400ft Gross Level Off Height: 400ft

Obstacle Data (measured from ETORA) Obst.#: 1 Height(ft): 400 Dist.(ft):

4000

Remarks:

Output Description(Weights in kg, Speeds in KIAS): MTOW−LIM V1/Vr/V2

Wind (Kt) Temp (°C)

N1

−10

0

10

20

0

82.6

42000−S 92/135/137

42000−S 92/135/137

42000−S 92/135/137

42000−S 92/135/137

6

83.4

42000−S 92/135/137

42000−S 92/135/137

42000−S 92/135/137

42000−S 92/135/137

12

84.3

42000−S 92/135/137

42000−S 92/135/137

42000−S 92/135/137

42000−S 92/135/137

18

85.1

42000−S 92/135/137

42000−S 92/135/137

42000−S 92/135/137

42000−S 92/135/137

24

86.0

42000−S 92/135/137

42000−S 92/135/137

42000−S 92/135/137

42000−S 92/135/137

30

86.8

42000−S 92/135/137

42000−S 92/135/137

42000−S 92/135/137

42000−S 92/135/137

36

86.0

42000−S 93/136/137

#42000−S #89/136/137

#42000−S #89/136/137

#42000−S #89/136/137

42

85.2

42000−S 112/136/137

42000−S 97/136/137

#42000−S #90/136/137

#42000−S #87/136/137

48

84.5

41294−W 119/136/136

41294−W 109/136/136

41294−W 104/136/136

41294−W 99/136/136

A54

83.6

38946−W 113/132/132

38946−W 102/132/132

38946−W 96/132/132

#38946−W #89/132/132

A60

82.9

37239−W 109/129/129

37239−W 97/129/129

37239−W 91/129/129

#37239−W #84/129/129

84.5

PART B

41294−W 99/136/136

Codes

Field Length AEO (RA) Field Length OEI (RO) Approach Climb OEI (A) Climb Accel Segment (AS) Climb 1° Seg. (FS) Climb 2° Seg. (W) Brake Energy (B) MTOW Max str TOW [S] Obstade # (1,2,3) A − Temperatures for assumed temperature only # − Minimum V1 check must be done RW−000−A Version 0.0.0 Date: (day−month−year): 00−00−0000 SCAP Module Version: 000−00000−000

Tire Speed (P) Climb Final Seg. (SF) No operation ******* Database: 000−00000−000.DAT

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 2

Takeoff

REVISION 21

AOM-1502-003

48

EM170AOM050066A.DGN

Air conditioning off after engine failure.

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

DESCRIPTION OF THE OUTPUTS OF THE CHART Part A: Head Lines with the following information: – Airplane Configuration (engine, thrust, flap, brakes, etc); – Runway Characteristics (elevation, length, obstacles, clearway, stopway, slope, etc). Part B: Performance Information: – OAT: Outside Air Temperature (if a letter A follow the temperature it means that the weight can be used only for assumed temperature calculation); – Takeoff N1; – Maximum Takeoff Weight; – V1: Takeoff decision speed; – VR: Rotation speed; – V2: Safety speed;

AOM-1502-003

– Limitation code.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 3

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

ASSUMED TEMPERATURE REDUCED THRUST In many situations, the airplane takes off at weights lower than the maximum permissible takeoff weight. In consequence, it is possible to continue complying with performance limitations using a decreased engine thrust adapted to the actual weight. This is called assumed temperature reduced thrust method. Certification authorities permit the use of up to 25% of takeoff thrust reduction for operation with assumed temperature reduced thrust.

UTILIZATION OF ASSUMED TEMPERATURE REDUCED THRUST Assumed temperature reduced thrust method can only be used when the actual weight is lower than the maximum permissible takeoff weight for the actual temperature.

AIRWORTHINESS REQUIREMENTS

•

Maximum Assumed Temperature (MaxAT) (25% reduction). See Maximum Assumed Temperature Table.

•

Assumed temperature reduced thrust is not allowed when runway is contaminated with water, ice, slush or snow.

•

The operator shall at regular intervals check the maximum thrust in order to detect any possible engine deterioration, unless the operators has an adequate engine performance monitoring program.

RECOMMENDATION Assumed temperature reduced thrust should be used whenever possible in order to save engine life.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 4

Takeoff

REVISION 21

AOM-1502-003

Always use the flaps configuration, that provides the greatest maximum takeoff weight in order to maximize thrust reduction.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

FLEXIBLE TEMPERATURE DETERMINATION The following flowcharts are only applicable to takeoff analysis generated with ANTI-ICE OFF.

Verify if actual weight is lower than or equal to the maximum takeoff weight in takeoff analysis for correspondent OAT and wind.

E n t er w i th actu al w ei gh t an d act u al w i n d o n tak eo f f an al y si s an d f i n d th e co r r esp o n d en t tem p er atu r e ( T ) .

Enter with pressure altitude and tem perature in Maximum Assum ed Tem perature table and find Maxim um Assum ed Tem perature (MaxAT).

Com pare T and MaxAT and choose the lower value as Assum ed Tem perature value (AT).

If AT is higher than MinAT: Take this tem perature (AT) as Assum ed Tem perature.

AOM-1502-003

If AT is lower than MinAT: No Flexible takeoff is possible, use m axim um thrust.

EM170AOM050009D.DGN

E n ter w i th p r essu r e al ti tu d e i n M i n i m u m A ssu m ed Temp er a ture table and find Minimum Assumed Temp er a ture (MinAT ) .

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 5

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

N1 % FOR FLEXIBLE TAKEOFF The following flowcharts are only applicable to takeoff analysis generated with ANTI-ICE OFF.

Enter with AT and pressure altitude in N1 for T/O−X m ode and find out N1 reference (N1ref).

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 6

Takeoff

REVISION 21

AOM-1502-003

Reduced N1% is: N1red = N1ref − N1corr.

EM170AOM050010A.DGN

Enter with the difference between AT and OAT in N1 adjustm ent for tem perature difference table and find out N1corr.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

TAKEOFF SPEEDS The following flowcharts are only applicable to takeoff analysis generated with ANTI-ICE OFF.

Using Runway Analysis, enter with the Actual Takeoff Weight in the reported wind column to find out V1, VR, V2. (Step 1).

Using Minimum V1 and VR tables find out V1min and VRmin.

If V1 and VR are higher than V1min and VRmin, use takeoff speeds found out in Step 1.

If V1 and VR are lower than V1min and VRmin.

AOM-1502-003

Determine again N1% and use this V1, VR and V2 of previous step as a takeoff speeds.

EM170AOM050011D.DGN

Use Runway analysis and find out in what Temperature V1 and VR are equal or higher than V1min and VRmin.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 7

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

FLEXIBLE TEMPERATURE DETERMINATION TABLES ECS ON – ANTI-ICE OFF

PRESSURE ALTITUDE (x 1000 ft) OAT (°C) -1 0 1 2 3 4 5 6 52 59 --------------50 58 57 ------------45 54 53 54 55 --------40 50 50 50 51 52 53 55 --35 47 46 46 47 47 48 49 51 30 45 43 43 43 44 44 45 45 25 43 42 41 41 40 40 40 40 20 43 42 40 39 39 38 36 35 15 43 41 40 39 38 36 34 32 10 43 41 40 39 37 36 34 31 5 43 41 40 39 37 36 33 31 0 and 43 41 40 39 37 36 33 30 below RMK: FOR ECS OFF ADD 2°C ON MAXIMUM ASSUMED TEMPERATURE MINIMUM ASSUMED TEMPERATURE Engine: CF34-8E5 — T/O-1

MinAt

-1 32

0 30

7 --------51 46 40 35 31 29 29

8 ----------46 40 35 30 28 27

29

26

ANTI-ICE OFF

PRESSURE ALTITUDE (x 1000 ft) 1 2 3 4 5 6 28 26 24 22 20 18

7 16

8 14

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 8

Takeoff

REVISION 21

AOM-1502-003

MAXIMUM ASSUMED TEMPERATURE Engine: CF34-8E5 — T/O-1

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

N1% ADJUSTMENT FOR TEMPERATURE DIFFERENCE Engine: CF34-8E5 — T/O-1 ANTI-ICE OFF

AOM-1502-003

AT MINUS OAT -40 -20 (°C) 5 ----10 ----20 ----30 ----40 --- 6.5 50 --- 7.9 60 9.9 9.0 70 11.3 10.0

OUTSIDE AIR TEMPERATURE (OAT) – (°C) 0

5

10

15

20

25

30

35

40

45

50

52

----3.2 4.6 5.9 7.0 -----

--1.6 3.1 4.5 5.7 6.8 -----

0.8 1.6 3.1 4.4 5.6 -------

0.8 1.5 3.0 4.3 5.4 -------

0.8 1.5 2.9 4.2 ---------

0.8 1.5 2.8 4.0 ---------

0.7 1.4 2.7 -----------

0.7 1.4 2.7 -----------

0.7 1.4 -------------

0.7 1.3 -------------

0.7 ---------------

0.6 ---------------

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 9

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

ECS ON – ANTI-ICE OFF

PRESSURE ALTITUDE (x 1000 ft) OAT (°C) -1 0 1 2 3 4 5 6 52 58 --------------50 56 57 ------------45 51 51 50 50 --------40 46 46 45 45 44 44 43 --35 41 41 40 40 39 38 38 38 30 38 37 36 35 34 33 33 33 25 37 35 33 32 30 29 28 28 20 37 35 32 29 28 26 24 23 15 36 35 31 29 27 24 22 21 10 36 34 31 29 27 24 21 19 5 36 34 31 29 26 24 21 19 0 and 36 34 31 29 26 24 21 19 below RMK: FOR ECS OFF ADD 2°C ON MAXIMUM ASSUMED TEMPERATURE MINIMUM ASSUMED TEMPERATURE Engine: CF34-8E5 — T/O-2

MinAt

-1 32

0 30

7 --------38 33 28 23 20 17 17

8 ----------33 28 23 18 16 15

17

15

ANTI-ICE OFF

PRESSURE ALTITUDE (x 1000 ft) 1 2 3 4 5 6 28 26 24 22 20 18

7 16

8 14

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 10

Takeoff

REVISION 21

AOM-1502-003

MAXIMUM ASSUMED TEMPERATURE Engine: CF34-8E5 — T/O-2

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

N1% ADJUSTMENT FOR TEMPERATURE DIFFERENCE Engine: CF34-8E5 — T/O-2 ANTI-ICE OFF

AOM-1502-003

AT MINUS OAT -40 (°C) 5 --10 --20 --30 --40 --50 --60 9.6 70 10.9

OUTSIDE AIR TEMPERATURE (OAT) – (°C) -20

0

5

10

15

20

25

30

35

40

45

50

52

--------6.3 7.6 8.8 9.8

----3.1 4.5 5.7 6.9 -----

--1.6 3.0 4.4 5.6 6.7 -----

0.8 1.5 3.0 4.3 5.4 -------

0.8 1.5 2.9 4.2 5.3 -------

0.7 1.5 2.8 4.0 ---------

0.7 1.4 2.7 3.9 ---------

0.7 1.4 2.7 -----------

0.7 1.4 2.6 -----------

0.7 1.3 -------------

0.7 1.3 -------------

0.6 ---------------

0.6 ---------------

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 11

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

MINIMUM V1 Engine: CF34-8E5 — T/O-1

EMBRAER 170

Altitude: Sea Level and Below WEIGHT (lb)

OAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10

97

97

96

96

96

97

97

98

15

97

96

96

96

96

97

97

97

20

97

96

96

96

96

97

97

97

25

97

96

96

96

96

96

97

97

30

97

96

96

96

96

96

97

97

35

94

93

93

93

93

94

94

95

40

91

91

90

90

91

91

91

92

45

88

88

88

88

88

88

89

89

50

86

85

85

85

85

86

86

86

Altitude: 2000 ft 47000

52000

57000

62000

67000

72000

77000

82000

10

94

94

93

94

94

94

95

95

15

94

94

93

93

94

94

94

95

20

94

94

93

93

94

94

94

95

25

94

94

93

93

93

94

94

95

30

93

92

92

92

92

92

93

93

35

90

90

90

90

90

90

91

91

40

88

87

87

87

87

88

88

88

45

85

85

84

84

85

85

85

86

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 12

Takeoff

REVISION 21

AOM-1502-003

WEIGHT (lb)

OAT (°C)

PERFORMANCE

AIRPLANE OPERATIONS MANUAL MINIMUM V1 Engine: CF34-8E5 — T/O-1

EMBRAER 170

Altitude: 4000 ft WEIGHT (lb)

OAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10

91

91

91

91

91

91

92

92

15

91

91

90

91

91

91

92

92

20

91

91

90

90

91

91

91

92

25

90

90

89

89

90

90

90

91

30

88

88

88

88

88

88

89

89

35

87

86

86

86

86

87

87

87

40

84

84

84

84

84

85

85

85

Altitude: 6000 ft WEIGHT (lb)

OAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10

88

88

88

88

88

88

89

89

15

88

88

87

87

88

88

88

89

20

87

87

87

87

87

87

88

88

25

86

86

85

86

86

86

87

87

30

85

84

84

84

84

85

85

85

35

83

82

82

82

83

83

83

84

AOM-1502-003

Altitude: 8000 ft WEIGHT (lb)

OAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10

85

84

84

84

85

85

85

86

15

85

84

84

84

84

85

85

85

20

84

83

83

83

84

84

84

85

25

83

82

82

82

82

83

83

84

30

81

80

80

80

81

81

81

82

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 13

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

MINIMUM V1 Engine: CF34-8E5 — T/O-2

EMBRAER 170

Altitude: Sea Level and Below WEIGHT (lb)

OAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10

93

92

92

92

92

92

93

93

15

93

92

92

92

92

92

93

93

20

92

92

91

92

92

92

92

93

25

92

92

91

91

92

92

92

93

30

92

92

91

91

92

92

92

93

35

90

90

89

89

90

90

90

91

40

88

87

87

87

87

88

88

89

45

86

85

85

85

85

86

86

87

50

84

83

83

83

83

84

84

84

Altitude: 2000 ft 47000

52000

57000

62000

67000

72000

77000

82000

10

90

89

89

89

89

90

90

90

15

90

89

89

89

89

90

90

90

20

90

89

89

89

89

90

90

90

25

90

89

89

89

89

89

90

90

30

88

87

87

87

88

88

88

89

35

86

85

85

85

86

86

86

87

40

84

83

83

83

84

84

84

85

45

82

81

81

81

82

82

82

83

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 14

Takeoff

REVISION 21

AOM-1502-003

WEIGHT (lb)

OAT (°C)

PERFORMANCE

AIRPLANE OPERATIONS MANUAL MINIMUM V1 Engine: CF34-8E5 — T/O-2

EMBRAER 170

Altitude: 4000 ft WEIGHT (lb)

OAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10

87

87

86

86

87

87

87

88

15

87

87

86

86

87

87

87

88

20

87

86

86

86

87

87

87

88

25

86

85

85

85

85

86

86

87

30

84

83

83

83

84

84

84

85

35

82

82

81

81

82

82

82

83

40

80

80

79

79

80

80

80

81

Altitude: 6000 ft WEIGHT (lb)

OAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10

84

84

84

84

84

84

85

85

15

84

84

84

84

84

84

85

85

20

84

83

83

83

83

84

84

85

25

82

81

81

81

82

82

82

83

30

80

80

79

80

80

80

81

81

35

78

78

77

78

78

78

79

79

AOM-1502-003

Altitude: 8000 ft WEIGHT (lb)

OAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10

81

81

81

81

81

81

82

82

15

81

81

80

81

81

81

82

82

20

80

80

79

80

80

80

81

81

25

78

78

78

78

78

78

79

79

30

76

76

76

76

76

77

77

77

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 15

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

MINIMUM VR Engine: CF34-8E5 — T/O-1

EMBRAER 170

Altitude: Sea Level and Below WEIGHT (lb)

OAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10

104

101

98

96

96

97

97

98

15

104

101

98

96

96

97

97

97

20

104

101

98

96

96

97

97

97

25

104

101

97

96

96

96

97

97

30

103

100

97

96

96

96

97

97

35

99

96

93

93

93

94

94

95

40

95

92

90

90

91

91

91

92

45

90

88

88

88

88

88

89

89

50

86

85

85

85

85

86

86

86

Altitude: 2000 ft 47000

52000

57000

62000

67000

72000

77000

82000

10

100

97

94

94

94

94

95

95

15

100

97

94

93

94

94

94

95

20

100

97

93

93

94

94

94

95

25

100

96

93

93

93

94

94

95

30

97

94

92

92

92

92

93

93

35

94

91

90

90

90

90

91

91

40

90

87

87

87

87

88

88

88

45

85

85

84

84

85

85

85

86

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 16

Takeoff

REVISION 21

AOM-1502-003

WEIGHT (lb)

OAT (°C)

PERFORMANCE

AIRPLANE OPERATIONS MANUAL MINIMUM VR Engine: CF34-8E5 — T/O-1

EMBRAER 170

Altitude: 4000 ft WEIGHT (lb)

OAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10

95

92

91

91

91

91

92

92

15

95

92

90

91

91

91

92

92

20

95

91

90

90

91

91

91

92

25

93

90

89

89

90

90

90

91

30

91

88

88

88

88

88

89

89

35

88

86

86

86

86

87

87

87

40

84

84

84

84

84

85

85

85

Altitude: 6000 ft WEIGHT (lb)

OAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10

91

88

88

88

88

88

89

89

15

90

88

87

87

88

88

88

89

20

89

87

87

87

87

87

88

88

25

87

86

85

86

86

86

87

87

30

85

84

84

84

84

85

85

85

35

83

82

82

82

83

83

83

84

AOM-1502-003

Altitude: 8000 ft WEIGHT (lb)

OAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10

85

84

84

84

85

85

85

86

15

85

84

84

84

84

85

85

85

20

84

83

83

83

84

84

84

85

25

83

82

82

82

82

83

83

84

30

81

80

80

80

81

81

81

82

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 17

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

MINIMUM VR Engine: CF34-8E5 — T/O-2

EMBRAER 170

Altitude: Sea Level and Below WEIGHT (lb)

OAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10

97

93

92

92

92

92

93

93

15

97

93

92

92

92

92

93

93

20

96

93

91

92

92

92

92

93

25

96

93

91

91

92

92

92

93

30

96

93

91

91

92

92

92

93

35

93

90

89

89

90

90

90

91

40

89

87

87

87

87

88

88

89

45

86

85

85

85

85

86

86

87

50

84

83

83

83

83

84

84

84

Altitude: 2000 ft 47000

52000

57000

62000

67000

72000

77000

82000

10

93

89

89

89

89

90

90

90

15

93

89

89

89

89

90

90

90

20

92

89

89

89

89

90

90

90

25

92

89

89

89

89

89

90

90

30

90

87

87

87

88

88

88

89

35

86

85

85

85

86

86

86

87

40

84

83

83

83

84

84

84

85

45

82

81

81

81

82

82

82

83

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 18

Takeoff

REVISION 21

AOM-1502-003

WEIGHT (lb)

OAT (°C)

PERFORMANCE

AIRPLANE OPERATIONS MANUAL MINIMUM VR Engine: CF34-8E5 — T/O-2

EMBRAER 170

Altitude: 4000 ft WEIGHT (lb)

OAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10

88

87

86

86

87

87

87

88

15

88

87

86

86

87

87

87

88

20

88

86

86

86

87

87

87

88

25

86

85

85

85

85

86

86

87

30

84

83

83

83

84

84

84

85

35

82

82

81

81

82

82

82

83

40

80

80

79

79

80

80

80

81

Altitude: 6000 ft WEIGHT (lb)

OAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10

84

84

84

84

84

84

85

85

15

84

84

84

84

84

84

85

85

20

84

83

83

83

83

84

84

85

25

82

81

81

81

82

82

82

83

30

80

80

79

80

80

80

81

81

35

78

78

77

78

78

78

79

79

AOM-1502-003

Altitude: 8000 ft WEIGHT (lb)

OAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10

81

81

81

81

81

81

82

82

15

81

81

80

81

81

81

82

82

20

80

80

79

80

80

80

81

81

25

78

78

78

78

78

78

79

79

30

76

76

76

76

76

77

77

77

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 19

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

MINIMUM V1 Engine: CF34-8E5 — T/O-1

EMBRAER 175

Altitude: Sea Level and Below WEIGHT (lb)

OAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10

97

96

96

96

97

97

97

98

15

97

96

96

96

97

97

97

98

20

96

96

96

96

97

97

97

98

25

96

96

96

96

96

97

97

98

30

96

96

96

96

96

97

97

98

35

94

93

93

93

94

94

94

95

40

91

90

90

91

91

91

92

92

45

88

88

88

88

88

89

89

89

50

85

85

85

85

85

86

86

87

Altitude: 2000 ft 51000

56000

61000

66000

71000

76000

81000

86000

10

94

94

94

94

94

95

95

95

15

94

93

93

94

94

94

95

95

20

94

93

93

94

94

94

95

95

25

94

93

93

93

94

94

95

95

30

92

92

92

92

92

93

93

94

35

90

90

90

90

90

91

91

91

40

87

87

87

87

88

88

88

89

45

85

84

84

85

85

85

86

86

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 20

Takeoff

REVISION 21

AOM-1502-003

WEIGHT (lb)

OAT (°C)

PERFORMANCE

AIRPLANE OPERATIONS MANUAL MINIMUM V1 Engine: CF34-8E5 — T/O-1

EMBRAER 175

Altitude: 4000 ft WEIGHT (lb)

OAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10

91

91

91

91

91

92

92

92

15

91

90

90

91

91

91

92

92

20

91

90

90

90

91

91

92

92

25

90

89

89

90

90

90

91

91

30

88

88

88

88

88

89

89

90

35

86

86

86

86

87

87

87

88

40

84

84

84

84

84

85

85

86

Altitude: 6000 ft WEIGHT (lb)

OAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10

88

88

88

88

88

89

89

90

15

88

87

87

88

88

88

89

89

20

87

87

87

87

87

88

88

89

25

86

85

86

86

86

87

87

87

30

84

84

84

84

85

85

85

86

35

82

82

82

83

83

83

84

84

AOM-1502-003

Altitude: 8000 ft WEIGHT (lb)

OAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10

85

84

84

84

85

85

86

86

15

84

84

84

84

85

85

85

86

20

83

83

83

84

84

84

85

85

25

82

82

82

82

83

83

83

84

30

81

80

80

81

81

81

82

82

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 21

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

MINIMUM V1 Engine: CF34-8E5 — T/O-2

EMBRAER 175

Altitude: Sea Level and Below WEIGHT (lb)

OAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10

92

92

92

92

92

93

93

93

15

92

92

92

92

92

92

93

93

20

92

91

91

92

92

92

93

93

25

92

91

91

92

92

92

93

93

30

92

91

91

92

92

92

93

93

35

90

89

89

89

90

90

91

91

40

88

87

87

87

88

88

88

89

45

85

85

85

85

86

86

86

87

50

83

83

83

83

84

84

84

85

Altitude: 2000 ft 51000

56000

61000

66000

71000

76000

81000

86000

10

89

89

89

89

90

90

90

91

15

89

89

89

89

90

90

90

91

20

89

89

89

89

89

90

90

91

25

89

89

89

89

89

90

90

91

30

88

87

87

87

88

88

89

89

35

86

85

85

85

86

86

87

87

40

84

83

83

83

84

84

85

85

45

82

81

81

81

82

82

83

83

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 22

Takeoff

REVISION 21

AOM-1502-003

WEIGHT (lb)

OAT (°C)

PERFORMANCE

AIRPLANE OPERATIONS MANUAL MINIMUM V1 Engine: CF34-8E5 — T/O-2

EMBRAER 175

Altitude: 4000 ft WEIGHT (lb)

OAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10

87

86

86

87

87

87

88

88

15

87

86

86

87

87

87

88

88

20

87

86

86

86

87

87

88

88

25

85

85

85

85

86

86

86

87

30

84

83

83

83

84

84

85

85

35

82

81

81

82

82

82

83

83

40

80

79

79

80

80

80

81

81

Altitude: 6000 ft WEIGHT (lb)

OAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10

84

84

84

84

84

85

85

86

15

84

84

84

84

84

85

85

86

20

83

83

83

83

84

84

84

85

25

82

81

81

82

82

82

83

83

30

80

79

79

80

80

80

81

81

35

78

78

78

78

78

79

79

79

AOM-1502-003

Altitude: 8000 ft WEIGHT (lb)

OAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10

81

81

81

81

81

82

82

83

15

81

80

80

81

81

81

82

82

20

80

79

79

80

80

80

81

81

25

78

78

78

78

78

79

79

80

30

76

76

76

76

77

77

77

78

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 23

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

MINIMUM VR Engine: CF34-8E5 — T/O-1

EMBRAER 175

Altitude: Sea Level and Below WEIGHT (lb)

OAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10

102

98

96

96

97

97

97

98

15

101

98

96

96

97

97

97

98

20

101

98

96

96

97

97

97

98

25

101

98

96

96

96

97

97

98

30

101

98

96

96

96

97

97

98

35

97

94

93

93

94

94

94

95

40

92

90

90

91

91

91

92

92

45

88

88

88

88

88

89

89

89

50

85

85

85

85

85

86

86

87

Altitude: 2000 ft 51000

56000

61000

66000

71000

76000

81000

86000

10

98

94

94

94

94

95

95

95

15

97

94

93

94

94

94

95

95

20

97

94

93

94

94

94

95

95

25

97

94

93

93

94

94

95

95

30

95

92

92

92

92

93

93

94

35

91

90

90

90

90

91

91

91

40

87

87

87

87

88

88

88

89

45

85

84

84

85

85

85

86

86

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 24

Takeoff

REVISION 21

AOM-1502-003

WEIGHT (lb)

OAT (°C)

PERFORMANCE

AIRPLANE OPERATIONS MANUAL MINIMUM VR Engine: CF34-8E5 — T/O-1

EMBRAER 175

Altitude: 4000 ft WEIGHT (lb)

OAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10

93

91

91

91

91

92

92

92

15

93

90

90

91

91

91

92

92

20

92

90

90

90

91

91

92

92

25

91

89

89

90

90

90

91

91

30

88

88

88

88

88

89

89

90

35

86

86

86

86

87

87

87

88

40

84

84

84

84

84

85

85

86

Altitude: 6000 ft WEIGHT (lb)

OAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10

88

88

88

88

88

89

89

90

15

88

87

87

88

88

88

89

89

20

87

87

87

87

87

88

88

89

25

86

85

86

86

86

87

87

87

30

84

84

84

84

85

85

85

86

35

82

82

82

83

83

83

84

84

AOM-1502-003

Altitude: 8000 ft WEIGHT (lb)

OAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10

85

84

84

84

85

85

86

86

15

84

84

84

84

85

85

85

86

20

83

83

83

84

84

84

85

85

25

82

82

82

82

83

83

83

84

30

81

80

80

81

81

81

82

82

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 25

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

MINIMUM VR Engine: CF34-8E5 — T/O-2

EMBRAER 175

Altitude: Sea Level and Below WEIGHT (lb)

OAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10

94

92

92

92

92

93

93

93

15

94

92

92

92

92

92

93

93

20

94

91

91

92

92

92

93

93

25

94

91

91

92

92

92

93

93

30

94

91

91

92

92

92

93

93

35

90

89

89

89

90

90

91

91

40

88

87

87

87

88

88

88

89

45

85

85

85

85

86

86

86

87

50

83

83

83

83

84

84

84

85

Altitude: 2000 ft 51000

56000

61000

66000

71000

76000

81000

86000

10

90

89

89

89

90

90

90

91

15

90

89

89

89

90

90

90

91

20

90

89

89

89

89

90

90

91

25

90

89

89

89

89

90

90

91

30

88

87

87

87

88

88

89

89

35

86

85

85

85

86

86

87

87

40

84

83

83

83

84

84

85

85

45

82

81

81

81

82

82

83

83

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 26

Takeoff

REVISION 21

AOM-1502-003

WEIGHT (lb)

OAT (°C)

PERFORMANCE

AIRPLANE OPERATIONS MANUAL MINIMUM VR Engine: CF34-8E5 — T/O-2

EMBRAER 175

Altitude: 4000 ft WEIGHT (lb)

OAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10

87

86

86

87

87

87

88

88

15

87

86

86

87

87

87

88

88

20

87

86

86

86

87

87

88

88

25

85

85

85

85

86

86

86

87

30

84

83

83

83

84

84

85

85

35

82

81

81

82

82

82

83

83

40

80

79

79

80

80

80

81

81

Altitude: 6000 ft WEIGHT (lb)

OAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10

84

84

84

84

84

85

85

86

15

84

84

84

84

84

85

85

86

20

83

83

83

83

84

84

84

85

25

82

81

81

82

82

82

83

83

30

80

79

79

80

80

80

81

81

35

78

78

78

78

78

79

79

79

AOM-1502-003

Altitude: 8000 ft WEIGHT (lb)

OAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10

81

81

81

81

81

82

82

83

15

81

80

80

81

81

81

82

82

20

80

79

79

80

80

80

81

81

25

78

78

78

78

78

79

79

80

30

76

76

76

76

77

77

77

78

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 27

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

SIMPLIFIED TAKEOFF ANALYSIS TABLES Simplified Takeoff Analysis tables are presented for a set of pressure altitudes, temperatures and runway lengths for the conditions below: – Dry runway; – Zero wind; – Zero slope; – No clearway; – No stopway; – Obstacles are not considered; – Maximum manual braking; – ECS and ATTCS ON; – Balanced V1; – Landing flap 5. Following limitation factors and codes were considered in the calculation of these tables: – R – Runway Length; – W – WAT (Climb); – B – Brake energy; – S – Structural; – A – Approach Climb; – SF – Final Segment; – P – Tire speed. – L– Maximum Lift-off Speed.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 28

Takeoff

REVISION 21

AOM-1502-003

NOTE: The Maximum Structural Takeoff Weight defined in the AFM must be checked.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.20 – ANTI-ICE OFF

Airport Pressure Altitude: Sea Level TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

76382 R

80724 R

84844 R

85097 S

85097 S

85097 S

85097 S

132/140/144

137/145/148

142/149/152

142/149/152

142/149/152

142/149/152

142/149/152

75667 R

79978 R

84046 R

85097 S

85097 S

85097 S

85097 S

131/139/144

136/144/148

141/148/151

142/149/152

142/149/152

142/149/152

142/149/152

74991 R

79241 R

83263 R

85097 S

85097 S

85097 S

85097 S

130/138/143

135/143/147

140/147/151

142/149/152

142/149/152

142/149/152

142/149/152

74339 R

78534 R

82493 R

85097 S

85097 S

85097 S

85097 S

129/138/142

134/142/146

139/147/150

142/149/152

142/149/152

142/149/152

142/149/152

73670 R

77817 R

81723 R

85097 S

85097 S

85097 S

85097 S

128/137/142

134/142/146

138/146/149

142/149/152

142/149/152

142/149/152

142/149/152

73016 R

77116 R

80977 R

84679 R

85097 S

85097 S

85097 S

127/136/141

133/141/145

138/145/149

142/149/152

142/149/152

142/149/152

142/149/152

72351 R

76412 R

80239 R

83896 R

85097 S

85097 S

85097 S

127/135/140

132/140/144

137/144/148

141/148/151

142/149/152

142/149/152

142/149/152

71716 R

75715 R

79519 R

83132 R

85097 S

85097 S

85097 S

126/135/140

131/139/144

136/144/147

140/147/151

142/149/152

142/149/152

142/149/152

71095 R

75057 R

78806 R

82387 R

85097 S

85097 S

85097 S

125/134/139

130/139/143

135/143/147

139/147/150

142/149/152

142/149/152

142/149/152

70488 R

74416 R

78122 R

81655 R

85025 R

85097 S

85097 S

124/133/139

129/138/142

134/142/146

138/146/149

142/149/152

142/149/152

142/149/152

69893 R

73791 R

77452 R

80932 R

84285 R

85097 S

85097 S

123/132/138

129/137/142

133/141/145

138/145/149

141/149/152

142/149/152

142/149/152

67308 R

71104 R

74614 R

77984 R

81148 R

83886 R

85097 S

122/130/135

127/135/139

131/139/143

136/143/146

139/146/149

143/149/151

145/150/152

64763 R

68397 R

71777 R

75024 R

77838 R

80507 R

83095 R

120/128/133

125/133/137

130/137/140

134/140/143

138/143/146

141/146/148

144/149/151

62092 R

65582 R

68862 R

71863 R

74438 R

76985 R

77937 W

118/126/130

123/130/134

128/134/137

132/137/140

135/140/142

139/143/145

140/144/146

59382 R

62725 R

65906 R

68608 R

71087 R

72548 W

72548 W

116/123/127

121/127/131

125/131/134

130/134/137

133/137/139

135/139/141

135/139/141

For ANTI-ICE ON, decrease weight by 450 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 29

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.20 – ANTI-ICE OFF

Airport Pressure Altitude: 500 ft RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

75348 R

79628 R

83680 R

85097 S

85097 S

85097 S

85097 S

131/139/143

136/144/147

141/148/151

142/149/152

142/149/152

142/149/152

142/149/152

-15

74647 R

78896 R

82894 R

85097 S

85097 S

85097 S

85097 S

130/138/143

135/143/147

140/147/150

142/149/152

142/149/152

142/149/152

142/149/152

-10

73987 R

78168 R

82127 R

85097 S

85097 S

85097 S

85097 S

129/137/142

134/142/146

139/146/150

142/149/152

142/149/152

142/149/152

142/149/152

-5

73340 R

77469 R

81364 R

85097 S

85097 S

85097 S

85097 S

128/136/141

133/141/145

138/145/149

142/149/152

142/149/152

142/149/152

142/149/152

0

72687 R

76769 R

80619 R

84322 R

85097 S

85097 S

85097 S

127/136/141

133/140/145

137/145/148

142/149/152

142/149/152

142/149/152

142/149/152

5

72049 R

76082 R

79897 R

83542 R

85097 S

85097 S

85097 S

126/135/140

132/140/144

136/144/148

141/148/151

142/149/152

142/149/152

142/149/152

10

71400 R

75400 R

79175 R

82777 R

85097 S

85097 S

85097 S

126/134/139

131/139/143

136/143/147

140/147/150

142/149/152

142/149/152

142/149/152

15

70776 R

74729 R

78472 R

82030 R

85097 S

85097 S

85097 S

125/134/139

130/138/143

135/142/146

139/146/150

142/149/152

142/149/152

142/149/152

20

70165 R

74083 R

77771 R

81300 R

84658 R

85097 S

85097 S

124/133/138

129/138/142

134/142/146

138/146/149

142/149/152

142/149/152

142/149/152

25

69549 R

73435 R

77082 R

80568 R

83901 R

85097 S

85097 S

123/132/138

128/137/141

133/141/145

137/145/148

141/148/151

142/149/152

142/149/152

30

68588 R

72421 R

76000 R

79438 R

82730 R

85097 S

85097 S

122/131/137

127/136/140

132/140/144

136/144/147

140/147/150

143/150/152

143/150/152

35

66098 R

69822 R

73267 R

76574 R

79642 R

82331 R

84951 R

121/129/134

126/134/138

130/138/141

134/141/144

138/145/147

142/147/150

145/150/152

40

63588 R

67172 R

70487 R

73686 R

76396 R

79013 R

81552 R

119/127/132

124/131/135

129/135/139

133/139/142

136/142/144

140/145/147

143/147/149

45

60968 R

64409 R

67631 R

70586 R

73113 R

75579 R

76267 W

117/125/129

122/129/132

127/133/136

131/136/139

134/139/141

138/142/144

139/142/144

50 A

58344 R

61625 R

64757 R

67408 R

69853 R

71253 W

71253 W

115/122/126

120/126/130

124/130/133

128/133/136

132/136/138

134/138/139

134/138/139

For ANTI-ICE ON, decrease weight by 400 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 30

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.20 – ANTI-ICE OFF

Airport Pressure Altitude: 1000 ft TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 A

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

74332 R

78539 R

82522 R

85097 S

85097 S

85097 S

85097 S

130/138/142

135/142/146

140/147/150

143/149/152

143/149/152

143/149/152

143/149/152

73659 R

77818 R

81750 R

85097 S

85097 S

85097 S

85097 S

129/137/142

134/142/146

139/146/149

143/149/152

143/149/152

143/149/152

143/149/152

72989 R

77098 R

80995 R

84709 R

85097 S

85097 S

85097 S

128/136/141

133/141/145

138/145/149

142/149/152

143/149/152

143/149/152

143/149/152

72345 R

76406 R

80250 R

83938 R

85097 S

85097 S

85097 S

127/135/140

132/140/144

137/144/148

141/148/151

143/149/152

143/149/152

143/149/152

71713 R

75724 R

79528 R

83175 R

85097 S

85097 S

85097 S

126/135/140

131/139/144

136/144/147

140/147/151

143/149/152

143/149/152

143/149/152

71086 R

75064 R

78820 R

82410 R

85097 S

85097 S

85097 S

125/134/139

131/139/143

135/143/147

140/147/150

143/149/152

143/149/152

143/149/152

70449 R

74402 R

78117 R

81663 R

85055 R

85097 S

85097 S

125/133/139

130/138/142

134/142/146

139/146/149

143/149/152

143/149/152

143/149/152

69836 R

73745 R

77426 R

80932 R

84296 R

85097 S

85097 S

124/133/138

129/137/142

134/141/145

138/145/149

142/149/152

143/149/152

143/149/152

69235 R

73112 R

76741 R

80215 R

83539 R

85097 S

85097 S

123/132/137

128/137/141

133/141/145

137/144/148

141/148/151

143/149/152

143/149/152

68612 R

72456 R

76044 R

79482 R

82779 R

85097 S

85097 S

122/131/137

127/136/141

132/140/144

136/144/147

140/147/150

143/150/152

143/150/152

67285 R

71055 R

74566 R

77934 R

81174 R

84015 R

85097 S

121/130/135

126/135/139

131/139/143

135/142/146

139/146/149

142/149/151

144/150/152

64906 R

68552 R

71928 R

75166 R

78141 R

80789 R

83353 R

120/128/133

125/132/137

129/136/140

133/140/143

137/143/146

141/146/148

144/149/151

62417 R

65943 R

69202 R

72346 R

74990 R

77531 R

80022 R

118/126/130

123/130/134

127/134/137

131/138/140

135/141/143

139/143/145

142/146/148

59855 R

63228 R

66403 R

69308 R

71808 R

74217 R

74819 W

116/123/128

121/128/131

125/132/135

129/135/137

133/138/140

137/140/142

137/141/143

57316 R

60533 R

63614 R

66210 R

68619 R

70022 W

70022 W

114/121/125

119/125/128

123/129/132

127/132/134

131/135/137

133/136/138

133/136/138

For ANTI-ICE ON, decrease weight by 400 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 31

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.20 – ANTI-ICE OFF

Airport Pressure Altitude: 1500 ft RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

73196 R

77324 R

81254 R

84967 R

85097 S

85097 S

85097 S

129/137/141

134/141/145

139/146/149

143/149/152

143/150/152

143/150/152

143/150/152

-15

72531 R

76614 R

80493 R

84197 R

85097 S

85097 S

85097 S

128/136/141

133/141/145

138/145/148

142/149/152

143/150/152

143/150/152

143/150/152

-10

71872 R

75908 R

79750 R

83418 R

85097 S

85097 S

85097 S

127/135/140

132/140/144

137/144/147

141/148/151

143/150/152

143/150/152

143/150/152

-5

71233 R

75229 R

79022 R

82656 R

85097 S

85097 S

85097 S

126/134/139

131/139/143

136/143/147

140/147/150

143/150/152

143/150/152

143/150/152

0

70606 R

74570 R

78305 R

81906 R

85097 S

85097 S

85097 S

125/134/139

130/138/143

135/143/146

139/146/149

143/150/152

143/150/152

143/150/152

5

69984 R

73914 R

77606 R

81153 R

84477 R

85097 S

85097 S

124/133/138

130/138/142

134/142/145

138/146/149

142/149/152

143/150/152

143/150/152

10

69361 R

73265 R

76917 R

80420 R

83772 R

85097 S

85097 S

124/132/138

129/137/141

133/141/145

138/145/148

141/148/151

143/150/152

143/150/152

15

68756 R

72620 R

76240 R

79703 R

83028 R

85097 S

85097 S

123/132/137

128/136/141

133/140/144

137/144/147

141/148/151

143/150/152

143/150/152

20

68163 R

71996 R

75567 R

78999 R

82287 R

85097 S

85097 S

122/131/136

127/135/140

132/140/144

136/143/147

140/147/150

143/150/152

143/150/152

25

67554 R

71355 R

74895 R

78277 R

81536 R

84454 R

85097 S

121/130/136

126/135/139

131/139/143

135/143/146

139/146/149

143/149/152

143/150/152

30

66056 R

69774 R

73239 R

76519 R

79699 R

82458 R

85063 R

120/129/134

125/133/138

130/137/141

134/141/144

138/145/147

141/147/150

145/150/152

35

63790 R

67381 R

70709 R

73898 R

76791 R

79398 R

81919 R

119/127/132

124/131/136

128/135/139

132/139/142

136/142/145

140/145/147

143/147/149

40

61318 R

64780 R

67985 R

71072 R

73661 R

76131 R

78579 R

117/125/129

122/129/133

126/133/136

130/136/139

134/139/142

138/142/144

141/145/146

45

58795 R

62114 R

65236 R

68072 R

70529 R

72896 R

73468 W

115/122/127

120/127/130

124/130/133

128/134/136

132/137/139

135/139/141

136/140/142

50 A

56295 R

59465 R

62506 R

65053 R

67422 R

68818 W

68818 W

113/120/124

118/124/127

122/128/131

126/131/133

130/134/136

132/135/137

132/135/137

For ANTI-ICE ON, decrease weight by 450 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 32

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.20 – ANTI-ICE OFF

Airport Pressure Altitude: 2000 ft TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 A

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

72061 R

76113 R

79990 R

83661 R

85097 S

85097 S

85097 S

128/136/140

133/140/144

138/144/148

142/148/151

144/150/152

144/150/152

144/150/152

71404 R

75418 R

79241 R

82902 R

85097 S

85097 S

85097 S

127/135/140

132/139/143

137/144/147

141/147/150

144/150/152

144/150/152

144/150/152

70755 R

74738 R

78511 R

82130 R

85097 S

85097 S

85097 S

126/134/139

131/139/143

136/143/146

140/147/150

144/150/152

144/150/152

144/150/152

70122 R

74070 R

77793 R

81378 R

84595 R

85097 S

85097 S

125/133/138

130/138/142

135/142/146

139/146/149

143/149/152

144/150/152

144/150/152

69502 R

73419 R

77086 R

80641 R

83882 R

85097 S

85097 S

124/133/138

129/137/142

134/141/145

138/145/148

142/149/151

144/150/152

144/150/152

68887 R

72770 R

76395 R

79909 R

83184 R

85097 S

85097 S

123/132/137

129/137/141

133/141/144

137/144/148

141/148/151

144/150/152

144/150/152

68276 R

72131 R

75719 R

79181 R

82493 R

85097 S

85097 S

123/131/136

128/136/140

132/140/144

137/144/147

140/147/150

144/150/152

144/150/152

67680 R

71494 R

75064 R

78478 R

81764 R

84602 R

85097 S

122/130/136

127/135/140

132/139/143

136/143/146

140/146/149

143/149/152

144/150/152

67094 R

70883 R

74414 R

77787 R

81037 R

83919 R

85097 S

121/130/135

126/134/139

131/139/142

135/142/146

139/146/149

142/149/151

144/150/152

66499 R

70258 R

73755 R

77077 R

80296 R

83174 R

85097 S

120/129/135

125/134/138

130/138/142

134/142/145

138/145/148

142/148/151

144/150/152

64832 R

68495 R

71907 R

75122 R

78247 R

80911 R

83471 R

119/128/133

124/132/137

129/136/140

133/140/143

136/143/146

140/146/149

143/149/151

62679 R

66218 R

69495 R

72635 R

75455 R

78014 R

80499 R

117/126/131

123/130/134

127/134/138

131/138/141

135/141/143

138/144/146

142/146/148

60227 R

63625 R

66775 R

69805 R

72340 R

74754 R

76981 W

116/124/128

121/128/132

125/132/135

129/135/138

133/138/140

136/141/143

139/143/145

57741 R

61005 R

64078 R

66849 R

69260 R

71588 R

72199 W

114/121/125

119/125/129

123/129/132

127/133/135

131/135/137

134/138/140

135/139/140

55288 R

58416 R

61403 R

63911 R

66234 R

67721 W

67721 W

112/119/123

117/123/126

121/127/129

125/130/132

129/133/134

131/134/136

131/134/136

For ANTI-ICE ON, decrease weight by 450 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 33

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.20 – ANTI-ICE OFF

Airport Pressure Altitude: 2500 ft RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

70947 R

74939 R

78745 R

82352 R

85097 S

85097 S

85097 S

127/134/139

132/139/143

136/143/147

141/147/150

144/150/152

144/150/152

144/150/152

-15

70294 R

74255 R

78002 R

81610 R

84683 R

85097 S

85097 S

126/134/138

131/138/142

136/143/146

140/146/149

144/149/152

144/150/152

144/150/152

-10

69649 R

73575 R

77277 R

80846 R

83970 R

85097 S

85097 S

125/133/138

130/138/142

135/142/145

139/146/149

143/149/151

144/150/152

144/150/152

-5

69022 R

72915 R

76562 R

80098 R

83254 R

85097 S

85097 S

124/132/137

129/137/141

134/141/145

138/145/148

142/148/151

144/150/152

144/150/152

0

68408 R

72268 R

75862 R

79367 R

82546 R

85097 S

85097 S

123/132/137

128/136/140

133/140/144

137/144/147

141/147/150

144/150/152

144/150/152

5

67797 R

71628 R

75189 R

78642 R

81853 R

84656 R

85097 S

122/131/136

128/135/140

132/140/143

136/143/146

140/147/149

144/150/152

144/150/152

10

67192 R

70997 R

74530 R

77923 R

81176 R

83933 R

85097 S

122/130/135

127/135/139

131/139/143

135/143/146

139/146/149

143/149/151

144/150/152

15

66603 R

70365 R

73885 R

77228 R

80461 R

83239 R

85097 S

121/129/135

126/134/139

131/138/142

135/142/145

138/145/148

142/148/151

144/150/152

20

66023 R

69760 R

73235 R

76540 R

79740 R

82558 R

85097 S

120/129/134

125/133/138

130/137/141

134/141/145

138/145/148

141/147/150

144/150/152

25

65299 R

68996 R

72433 R

75687 R

78852 R

81645 R

84240 R

119/128/133

124/133/137

129/137/141

133/140/144

137/144/147

140/147/149

144/149/152

30

63551 R

67148 R

70491 R

73653 R

76690 R

79276 R

81796 R

118/126/132

123/131/135

127/135/139

132/139/142

135/142/145

139/145/147

142/147/149

35

61470 R

64948 R

68171 R

71245 R

74011 R

76468 R

78920 R

116/124/129

121/129/133

126/133/136

130/136/139

134/140/142

137/142/144

140/145/147

40

59114 R

62456 R

65561 R

68534 R

71026 R

73403 R

75322 W

115/122/127

120/127/130

124/131/134

128/134/137

132/137/139

135/140/142

138/142/143

45

56740 R

59943 R

62966 R

65700 R

68076 R

70373 R

70966 W

113/120/124

118/124/128

122/128/131

126/131/134

130/134/136

133/137/139

134/137/139

50 A

54414 R

57484 R

60416 R

62898 R

65189 R

66673 W

66673 W

111/118/122

116/122/125

120/126/128

124/129/131

128/131/133

130/133/135

130/133/135

For ANTI-ICE ON, decrease weight by 500 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 34

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.20 – ANTI-ICE OFF

Airport Pressure Altitude: 3000 ft TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 A 50 A

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

69837 R

73779 R

77508 R

81055 R

84065 R

85097 S

85097 S

126/133/138

131/138/142

135/142/145

140/146/149

144/149/152

145/150/152

145/150/152

69175 R

73096 R

76772 R

80327 R

83344 R

85097 S

85097 S

125/133/137

130/137/141

134/141/145

139/145/148

143/148/151

145/150/152

145/150/152

68551 R

72411 R

76051 R

79568 R

82639 R

85097 S

85097 S

124/132/137

129/137/141

134/141/144

138/144/147

142/148/150

145/150/152

145/150/152

67931 R

71766 R

75347 R

78828 R

81925 R

84735 R

85097 S

123/131/136

128/136/140

133/140/143

137/144/147

141/147/150

144/150/152

145/150/152

67321 R

71127 R

74665 R

78102 R

81219 R

84013 R

85097 S

122/130/136

127/135/139

132/139/143

136/143/146

140/146/149

144/149/151

145/150/152

66716 R

70492 R

74000 R

77385 R

80529 R

83291 R

85097 S

121/130/135

127/134/139

131/139/142

135/142/145

139/146/148

143/148/151

145/150/152

66114 R

69868 R

73348 R

76672 R

79856 R

82586 R

85097 S

121/129/134

126/134/138

130/138/141

134/141/145

138/145/148

142/148/150

145/150/152

65534 R

69249 R

72710 R

75985 R

79171 R

81886 R

84502 R

120/128/134

125/133/137

130/137/141

134/141/144

137/144/147

141/147/150

144/150/152

64962 R

68643 R

72064 R

75309 R

78453 R

81208 R

83794 R

119/128/133

124/132/137

129/136/140

133/140/143

137/143/146

140/146/149

143/149/151

64105 R

67742 R

71119 R

74323 R

77415 R

80122 R

82679 R

118/127/132

123/131/136

128/135/139

132/139/142

136/142/145

139/145/148

143/148/150

62276 R

65816 R

69087 R

72188 R

75120 R

77659 R

80125 R

117/125/130

122/130/134

126/134/137

130/137/140

134/140/143

138/143/146

141/146/148

60264 R

63680 R

66847 R

69864 R

72562 R

74967 R

77344 R

115/123/128

120/128/132

125/132/135

129/135/138

132/138/141

136/141/143

139/143/145

57998 R

61288 R

64350 R

67268 R

69718 R

72052 R

73983 W

114/121/126

119/126/129

123/129/132

127/133/135

131/136/138

134/138/140

137/140/142

55748 R

58891 R

61858 R

64551 R

66891 R

69152 R

69802 W

112/119/123

117/123/127

121/127/130

125/130/133

129/133/135

132/136/137

133/136/138

53547 R

56561 R

59439 R

61898 R

64150 R

65715 W

65715 W

110/117/121

115/121/124

119/125/127

123/128/130

127/130/132

129/132/134

129/132/134

For ANTI-ICE ON, decrease weight by 500 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 35

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.20 – ANTI-ICE OFF

Airport Pressure Altitude: 3500 ft RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

68741 R

72626 R

76280 R

79765 R

82727 R

85097 S

85097 S

124/132/137

130/137/141

134/141/144

138/145/148

142/148/150

145/150/152

145/150/152

-15

68098 R

71956 R

75558 R

79056 R

82013 R

84861 R

85097 S

124/132/136

129/136/140

133/140/144

138/144/147

141/147/150

145/150/152

145/150/152

-10

67473 R

71284 R

74855 R

78305 R

81312 R

84124 R

85097 S

123/131/136

128/135/139

133/140/143

137/143/146

141/146/149

144/149/152

145/150/152

-5

66858 R

70642 R

74167 R

77577 R

80611 R

83380 R

85097 S

122/130/135

127/135/139

132/139/142

136/143/146

140/146/148

143/149/151

145/150/152

0

66254 R

70008 R

73492 R

76859 R

79913 R

82664 R

85097 S

121/129/134

126/134/138

131/138/142

135/142/145

139/145/148

142/148/150

145/150/152

5

65659 R

69382 R

72836 R

76155 R

79237 R

81954 R

84583 R

120/129/134

125/133/138

130/137/141

134/141/144

138/144/147

142/147/150

145/150/152

10

65068 R

68767 R

72196 R

75456 R

78575 R

81263 R

83848 R

120/128/133

125/133/137

129/137/140

133/140/144

137/144/146

141/146/149

144/149/151

15

64491 R

68152 R

71563 R

74783 R

77907 R

80569 R

83143 R

119/127/133

124/132/136

128/136/140

133/140/143

136/143/146

140/146/148

143/148/151

20

63895 R

67527 R

70900 R

74093 R

77175 R

79863 R

82413 R

118/127/132

123/131/136

128/135/139

132/139/142

135/142/145

139/145/148

142/148/150

25

62854 R

66428 R

69754 R

72889 R

75915 R

78523 R

81035 R

117/126/131

122/130/135

127/134/138

131/138/141

134/141/144

138/144/146

141/147/149

30

61084 R

64564 R

67778 R

70838 R

73702 R

76158 R

78587 R

116/124/129

121/128/133

125/132/136

129/136/139

133/139/142

136/142/144

140/144/146

35

59132 R

62481 R

65596 R

68563 R

71211 R

73577 R

75889 R

114/122/127

119/126/131

124/130/134

128/134/137

131/137/139

135/140/142

138/142/144

40

56989 R

60213 R

63223 R

66090 R

68498 R

70792 R

72704 W

113/120/125

118/124/128

122/128/131

126/132/134

129/134/137

133/137/139

136/139/141

45 A

54851 R

57943 R

60859 R

63526 R

65818 R

68037 R

68673 W

111/118/122

116/122/126

120/126/129

124/129/132

128/132/134

131/134/136

132/135/137

50 A

52738 R

55703 R

58533 R

60983 R

63196 R

64799 W

64799 W

109/116/120

114/120/123

118/124/126

122/127/129

126/129/131

128/131/133

128/131/133

For ANTI-ICE ON, decrease weight by 500 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 36

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.20 – ANTI-ICE OFF

Airport Pressure Altitude: 4000 ft TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 A 50 A

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

67652 R

71481 R

75071 R

78483 R

81399 R

84242 R

85097 S

123/131/136

129/136/140

133/140/143

137/144/146

141/147/149

145/150/152

146/150/152

67019 R

70824 R

74367 R

77795 R

80695 R

83496 R

85097 S

123/131/135

128/135/139

132/139/142

136/143/146

140/146/148

144/149/151

146/150/152

66400 R

70172 R

73675 R

77052 R

79997 R

82765 R

85097 S

122/130/135

127/134/138

132/139/142

136/142/145

140/145/148

143/148/150

146/150/152

65792 R

69523 R

72997 R

76336 R

79308 R

82035 R

84691 R

121/129/134

126/134/138

131/138/141

135/141/144

139/145/147

142/147/150

146/150/152

65194 R

68895 R

72328 R

75629 R

78619 R

81326 R

83949 R

120/128/133

125/133/137

130/137/141

134/141/144

138/144/147

141/147/149

145/149/151

64608 R

68279 R

71681 R

74941 R

77952 R

80629 R

83219 R

119/128/133

124/132/136

129/136/140

133/140/143

137/143/146

140/146/148

144/149/151

64025 R

67671 R

71048 R

74256 R

77298 R

79945 R

82495 R

119/127/132

124/132/136

128/136/139

132/139/142

136/143/145

140/145/148

143/148/150

63456 R

67063 R

70420 R

73591 R

76650 R

79259 R

81795 R

118/126/132

123/131/135

127/135/139

132/139/142

135/142/145

139/145/147

142/147/149

62834 R

66416 R

69747 R

72889 R

75906 R

78525 R

81042 R

117/126/131

122/130/135

127/134/138

131/138/141

134/141/144

138/144/146

141/147/149

61608 R

65120 R

68383 R

71463 R

74430 R

76933 R

79393 R

116/124/130

121/129/133

126/133/137

130/137/140

133/140/143

137/143/145

140/145/147

59902 R

63314 R

66472 R

69482 R

72289 R

74691 R

77056 R

115/123/128

120/127/131

124/131/135

128/135/138

132/138/140

135/141/143

138/143/145

58009 R

61289 R

64352 R

67276 R

69863 R

72192 R

74459 R

113/121/126

118/125/129

122/129/132

126/133/135

130/136/138

133/138/140

137/141/143

55984 R

59148 R

62105 R

64916 R

67285 R

69540 R

71432 W

112/119/124

117/123/127

121/127/130

125/130/133

128/133/135

132/136/138

134/138/140

53955 R

56997 R

59867 R

62505 R

64752 R

66926 R

67606 W

110/117/121

115/121/125

119/125/128

123/128/131

127/131/133

130/133/135

131/134/136

51936 R

54851 R

57634 R

60071 R

62248 R

63914 W

63914 W

109/115/119

113/119/122

117/123/125

121/126/128

125/128/130

127/130/132

127/130/132

For ANTI-ICE ON, decrease weight by 500 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 37

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: Sea Level RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

84545 R

85097 S

85097 S

85097 S

85097 S

85097 S

85097 S

127/128/131

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

-15

83742 R

85097 S

85097 S

85097 S

85097 S

85097 S

85097 S

126/127/130

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

-10

82959 R

85097 S

85097 S

85097 S

85097 S

85097 S

85097 S

125/127/130

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

-5

82200 R

85097 S

85097 S

85097 S

85097 S

85097 S

85097 S

124/126/129

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

0

81429 R

85097 S

85097 S

85097 S

85097 S

85097 S

85097 S

123/125/128

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

5

80673 R

85097 S

85097 S

85097 S

85097 S

85097 S

85097 S

123/124/128

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

10

79912 R

84758 R

84941 L

84941 L

84941 L

84941 L

84941 L

122/124/127

127/128/131

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

15

79181 R

83979 R

84727 L

84727 L

84727 L

84727 L

84727 L

121/123/127

126/128/130

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

20

78468 R

83206 R

84512 L

84512 L

84512 L

84512 L

84512 L

120/122/126

125/127/130

127/128/131

126/128/131

126/128/131

127/128/131

127/128/131

25

77772 R

82462 R

84301 L

84301 L

84301 L

84301 L

84301 L

119/122/125

124/126/129

126/128/131

126/128/131

126/128/131

126/128/131

126/128/131

30

77092 R

81738 R

84088 L

84088 L

84088 L

84088 L

84088 L

119/121/125

124/126/129

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

35

74154 R

78612 R

78944 L

78944 L

78944 L

78944 L

78944 L

117/119/122

122/124/126

122/124/126

122/124/126

122/124/126

122/124/126

122/124/126

40

71379 R

74131 L

74131 L

74131 L

74131 L

74131 L

74131 L

116/117/120

119/120/122

119/120/122

119/120/122

119/120/122

119/120/122

119/120/122

45

68443 R

69825 L

69825 L

69825 L

69825 L

69825 L

69825 L

114/115/118

115/116/119

115/116/119

115/116/119

115/116/119

115/116/119

115/116/119

50

65255 W

65255 W

65255 W

65255 W

65255 W

65255 W

65255 W

112/113/115

112/113/115

112/113/115

112/113/115

112/113/115

112/113/115

112/113/115

For ANTI-ICE ON, decrease weight by 450 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 38

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: 500 ft TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 A

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

83357 R

85097 S

85097 S

85097 S

85097 S

85097 S

85097 S

126/127/130

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

82551 R

85004 L

85004 L

85004 L

85004 L

85004 L

85004 L

125/126/129

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

81778 R

84917 L

84917 L

84917 L

84917 L

84917 L

84917 L

124/126/129

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

127/129/131

81028 R

84810 L

84810 L

84810 L

84810 L

84810 L

84810 L

123/125/128

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

80276 R

84607 L

84607 L

84607 L

84607 L

84607 L

84607 L

122/124/127

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

79536 R

84364 R

84401 L

84401 L

84401 L

84401 L

84401 L

122/123/127

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

78792 R

83577 R

84196 L

84196 L

84196 L

84196 L

84196 L

121/123/126

126/127/130

126/128/131

126/128/131

126/128/131

126/128/131

126/128/131

78077 R

82813 R

83990 L

83990 L

83990 L

83990 L

83990 L

120/122/126

125/127/129

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

77378 R

82055 R

83784 L

83784 L

83784 L

83784 L

83784 L

119/121/125

124/126/129

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

76677 R

81309 R

83465 L

83465 L

83465 L

83465 L

83465 L

119/121/125

123/125/128

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

75591 R

80151 R

82224 L

82224 L

82224 L

82224 L

82224 L

118/120/124

123/124/127

125/126/129

125/126/129

125/126/129

125/126/129

125/126/129

72827 R

77176 R

77234 L

77234 L

77234 L

77234 L

77234 L

116/118/121

121/122/125

121/123/125

121/123/125

121/123/125

121/123/125

121/123/125

70083 R

72818 L

72818 L

72818 L

72818 L

72818 L

72818 L

114/116/119

118/119/121

118/119/121

118/119/121

118/119/121

118/119/121

118/119/121

67217 R

68568 L

68568 L

68568 L

68568 L

68568 L

68568 L

113/114/117

114/115/118

114/115/118

114/115/118

114/115/118

114/115/118

114/115/118

64107 W

64107 W

64107 W

64107 W

64107 W

64107 W

64107 W

111/112/114

111/112/114

111/112/114

111/112/114

111/112/114

111/112/114

111/112/114

For ANTI-ICE ON, decrease weight by 850 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 39

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: 1000 ft RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

82156 R

84340 L

84340 L

84340 L

84340 L

84340 L

84340 L

125/126/129

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

-15

81369 R

84257 L

84257 L

84257 L

84257 L

84257 L

84257 L

124/125/128

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

-10

80604 R

84173 L

84173 L

84173 L

84173 L

84173 L

84173 L

123/125/128

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

-5

79864 R

84045 L

84045 L

84045 L

84045 L

84045 L

84045 L

122/124/127

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

0

79131 R

83852 L

83852 L

83852 L

83852 L

83852 L

83852 L

121/123/127

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

5

78405 R

83181 R

83656 L

83656 L

83656 L

83656 L

83656 L

121/122/126

126/127/130

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

10

77679 R

82399 R

83451 L

83451 L

83451 L

83451 L

83451 L

120/122/125

125/126/129

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

15

76978 R

81651 R

83246 L

83246 L

83246 L

83246 L

83246 L

119/121/125

124/126/129

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

20

76293 R

80908 R

83050 L

83050 L

83050 L

83050 L

83050 L

118/120/124

123/125/128

125/127/130

125/127/130

125/127/130

125/127/130

125/127/130

25

75591 R

80159 R

82621 L

82621 L

82621 L

82621 L

82621 L

118/120/124

122/124/127

125/127/129

125/127/129

125/127/129

125/127/129

125/127/129

30

74130 R

78570 R

80337 L

80337 L

80337 L

80337 L

80337 L

117/119/122

121/123/126

123/125/128

123/125/128

123/125/128

123/125/128

123/125/128

35

71515 R

75574 L

75574 L

75574 L

75574 L

75574 L

75574 L

115/117/120

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

40

68790 R

71499 L

71499 L

71499 L

71499 L

71499 L

71499 L

113/115/118

117/118/120

117/118/120

117/118/120

117/118/120

117/118/120

117/118/120

45

65995 R

67280 L

67280 L

67280 L

67280 L

67280 L

67280 L

112/113/116

113/114/117

113/114/117

113/114/117

113/114/117

113/114/117

113/114/117

50 A

63024 W

63024 W

63024 W

63024 W

63024 W

63024 W

63024 W

110/111/113

110/111/113

110/111/113

110/111/113

110/111/113

110/111/113

110/111/113

For ANTI-ICE ON, decrease weight by 700 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 40

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: 1500 ft TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 A

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

80838 R

82860 L

82860 L

82860 L

82860 L

82860 L

82860 L

124/125/128

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

80062 R

82747 L

82747 L

82747 L

82747 L

82747 L

82747 L

123/124/127

126/127/129

126/127/129

126/127/129

126/127/129

126/127/129

126/127/129

79303 R

82625 L

82625 L

82625 L

82625 L

82625 L

82625 L

122/124/127

125/127/129

125/127/129

125/127/129

125/127/129

125/127/129

125/127/129

78572 R

82479 L

82479 L

82479 L

82479 L

82479 L

82479 L

121/123/126

125/127/129

125/127/129

125/127/129

125/127/129

125/127/129

125/127/129

77853 R

82297 L

82297 L

82297 L

82297 L

82297 L

82297 L

120/122/126

125/127/129

125/127/129

125/127/129

125/127/129

125/127/129

125/127/129

77140 R

81833 R

82103 L

82103 L

82103 L

82103 L

82103 L

120/122/125

125/126/129

125/126/129

125/126/129

125/126/129

125/126/129

125/126/129

76430 R

81083 R

81924 L

81924 L

81924 L

81924 L

81924 L

119/121/124

124/125/128

125/126/129

125/126/129

125/126/129

125/126/129

125/126/129

75741 R

80338 R

81708 L

81708 L

81708 L

81708 L

81708 L

118/120/124

123/125/128

124/126/129

124/126/129

124/126/129

124/126/129

124/126/129

75086 R

79613 R

81482 L

81482 L

81482 L

81482 L

81482 L

117/120/123

122/124/127

124/126/128

124/126/128

124/126/128

124/126/128

124/126/128

74421 R

78883 R

81098 L

81098 L

81098 L

81098 L

81098 L

117/119/123

122/123/126

124/126/128

124/126/128

124/126/128

124/126/128

124/126/128

72782 R

77094 R

78472 L

78472 L

78472 L

78472 L

78472 L

116/118/121

120/122/125

122/124/126

122/124/126

122/124/126

122/124/126

122/124/126

70301 R

74285 L

74285 L

74285 L

74285 L

74285 L

74285 L

114/116/119

119/120/123

119/120/123

119/120/123

119/120/123

119/120/123

119/120/123

67592 R

70229 L

70229 L

70229 L

70229 L

70229 L

70229 L

112/114/117

116/117/119

116/117/119

116/117/119

116/117/119

116/117/119

116/117/119

64835 R

66026 L

66026 L

66026 L

66026 L

66026 L

66026 L

111/112/115

112/113/116

112/113/116

112/113/116

112/113/116

112/113/116

112/113/116

61968 W

61968 W

61968 W

61968 W

61968 W

61968 W

61968 W

109/110/112

109/110/112

109/110/112

109/110/112

109/110/112

109/110/112

109/110/112

For ANTI-ICE ON, decrease weight by 750 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 41

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: 2000 ft RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

79534 R

81380 L

81380 L

81380 L

81380 L

81380 L

81380 L

123/124/127

125/126/128

125/126/128

125/126/128

125/126/128

125/126/128

125/126/128

-15

78765 R

81234 L

81234 L

81234 L

81234 L

81234 L

81234 L

122/123/126

124/126/128

124/126/128

124/126/128

124/126/128

124/126/128

124/126/128

-10

78011 R

81071 L

81071 L

81071 L

81071 L

81071 L

81071 L

121/123/126

124/126/128

124/126/128

124/126/128

124/126/128

124/126/128

124/126/128

-5

77289 R

80907 L

80907 L

80907 L

80907 L

80907 L

80907 L

120/122/125

124/125/128

124/125/128

124/125/128

124/125/128

124/125/128

124/125/128

0

76586 R

80744 L

80744 L

80744 L

80744 L

80744 L

80744 L

120/121/125

124/125/128

124/125/128

124/125/128

124/125/128

124/125/128

124/125/128

5

75882 R

80507 R

80562 L

80562 L

80562 L

80562 L

80562 L

119/121/124

124/125/128

124/125/128

124/125/128

124/125/128

124/125/128

124/125/128

10

75206 R

79772 R

80402 L

80402 L

80402 L

80402 L

80402 L

118/120/123

123/124/127

123/125/128

123/125/128

123/125/128

123/125/128

123/125/128

15

74552 R

79047 R

80173 L

80173 L

80173 L

80173 L

80173 L

117/119/123

122/124/127

123/125/127

123/125/127

123/125/127

123/125/127

123/125/127

20

73904 R

78326 R

79915 L

79915 L

79915 L

79915 L

79915 L

116/119/122

121/123/126

123/125/127

123/125/127

123/125/127

123/125/127

123/125/127

25

73256 R

77617 R

79569 L

79569 L

79569 L

79569 L

79569 L

116/118/122

121/123/125

123/124/127

123/124/127

123/124/127

123/124/127

123/124/127

30

71446 R

75632 R

76659 L

76659 L

76659 L

76659 L

76659 L

114/117/120

119/121/124

120/122/125

120/122/125

120/122/125

120/122/125

120/122/125

35

69093 R

73029 L

73029 L

73029 L

73029 L

73029 L

73029 L

113/115/118

118/119/122

118/119/122

118/119/122

118/119/122

118/119/122

118/119/122

40

66400 R

68930 L

68930 L

68930 L

68930 L

68930 L

68930 L

112/113/116

115/116/118

115/116/118

115/116/118

115/116/118

115/116/118

115/116/118

45

63684 R

64802 L

64802 L

64802 L

64802 L

64802 L

64802 L

110/111/113

111/112/114

111/112/114

111/112/114

111/112/114

111/112/114

111/112/114

50 A

60917 L

60917 L

60917 L

60917 L

60917 L

60917 L

60917 L

108/109/111

108/109/111

108/109/111

108/109/111

108/109/111

108/109/111

108/109/111

For ANTI-ICE ON, decrease weight by 850 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 42

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: 2500 ft TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 A

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

78258 R

80003 L

80003 L

80003 L

80003 L

80003 L

80003 L

122/123/126

124/125/127

124/125/127

124/125/127

124/125/127

124/125/127

124/125/127

77496 R

79856 L

79856 L

79856 L

79856 L

79856 L

79856 L

121/122/125

123/125/127

123/125/127

123/125/127

123/125/127

123/125/127

123/125/127

76758 R

79698 L

79698 L

79698 L

79698 L

79698 L

79698 L

120/122/125

123/125/127

123/125/127

123/125/127

123/125/127

123/125/127

123/125/127

76044 R

79507 L

79507 L

79507 L

79507 L

79507 L

79507 L

119/121/124

123/124/127

123/124/127

123/124/127

123/124/127

123/124/127

123/124/127

75358 R

79312 L

79312 L

79312 L

79312 L

79312 L

79312 L

119/120/124

123/124/127

123/124/127

123/124/127

123/124/127

123/124/127

123/124/127

74681 R

79113 L

79113 L

79113 L

79113 L

79113 L

79113 L

118/120/123

123/124/127

123/124/127

123/124/127

123/124/127

123/124/127

123/124/127

74017 R

78470 R

78911 L

78911 L

78911 L

78911 L

78911 L

117/119/122

122/123/126

122/124/126

122/124/126

122/124/126

122/124/126

122/124/126

73370 R

77757 R

78678 L

78678 L

78678 L

78678 L

78678 L

116/118/122

121/123/125

122/124/126

122/124/126

122/124/126

122/124/126

122/124/126

72732 R

77047 R

78433 L

78433 L

78433 L

78433 L

78433 L

115/118/121

120/122/125

122/124/126

122/124/126

122/124/126

122/124/126

122/124/126

71942 R

76182 R

77706 L

77706 L

77706 L

77706 L

77706 L

115/117/121

120/121/124

121/123/125

121/123/125

121/123/125

121/123/125

121/123/125

70025 R

74151 R

74850 L

74850 L

74850 L

74850 L

74850 L

113/115/119

118/120/123

119/121/123

119/121/123

119/121/123

119/121/123

119/121/123

67747 R

71491 L

71491 L

71491 L

71491 L

71491 L

71491 L

112/114/117

117/118/120

117/118/120

117/118/120

117/118/120

117/118/120

117/118/120

65169 R

67613 L

67613 L

67613 L

67613 L

67613 L

67613 L

110/112/115

114/115/117

114/115/117

114/115/117

113/115/117

113/115/117

113/115/117

62583 R

63773 L

63773 L

63773 L

63773 L

63773 L

63773 L

109/110/113

110/111/114

110/111/114

110/111/114

110/111/114

110/111/114

110/111/114

60025 R

60069 L

60069 L

60069 L

60069 L

60069 L

60069 L

107/108/110

107/108/110

107/108/110

107/108/110

107/108/110

107/108/110

107/108/110

For ANTI-ICE ON, decrease weight by 950 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 43

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: 3000 ft RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

76992 R

78645 L

78645 L

78645 L

78645 L

78645 L

78645 L

121/122/125

123/124/126

123/124/126

123/124/126

123/124/126

123/124/126

123/124/126

-15

76237 R

78507 L

78507 L

78507 L

78507 L

78507 L

78507 L

120/121/124

122/124/126

122/124/126

122/124/126

122/124/126

122/124/126

122/124/126

-10

75519 R

78355 L

78355 L

78355 L

78355 L

78355 L

78355 L

119/121/124

122/124/126

122/124/126

122/124/126

122/124/126

122/124/126

122/124/126

-5

74838 R

78130 L

78130 L

78130 L

78130 L

78130 L

78130 L

118/120/123

122/123/126

122/123/126

122/123/126

122/123/126

122/123/126

122/123/126

0

74168 R

77907 L

77907 L

77907 L

77907 L

77907 L

77907 L

118/119/123

122/123/126

122/123/126

122/123/126

122/123/126

122/123/126

122/123/126

5

73493 R

77690 L

77690 L

77690 L

77690 L

77690 L

77690 L

117/119/122

121/123/125

121/123/125

121/123/125

121/123/125

121/123/125

121/123/125

10

72837 R

77181 R

77449 L

77449 L

77449 L

77449 L

77449 L

116/118/121

121/123/125

121/123/125

121/123/125

121/123/125

121/123/125

121/123/125

15

72194 R

76475 R

77208 L

77208 L

77208 L

77208 L

77208 L

115/117/121

120/122/124

121/123/125

121/123/125

121/123/125

121/123/125

121/123/125

20

71567 R

75776 R

76955 L

76955 L

76955 L

76955 L

76955 L

115/117/120

119/121/124

121/122/125

121/122/125

121/122/125

121/122/125

121/122/125

25

70634 R

74792 R

75832 L

75832 L

75832 L

75832 L

75832 L

114/116/120

119/120/123

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

30

68613 R

72671 R

73171 L

73171 L

73171 L

73171 L

73171 L

112/114/118

117/119/121

118/119/122

118/119/122

118/119/122

118/119/122

118/119/122

35

66416 R

69943 L

69943 L

69943 L

69943 L

69943 L

69943 L

111/113/116

115/117/119

115/117/119

115/117/119

115/117/119

115/117/119

115/117/119

40

63947 R

66316 L

66316 L

66316 L

66316 L

66316 L

66316 L

109/111/114

112/114/116

112/114/116

112/114/116

112/114/116

112/114/116

112/114/116

45 A

61488 R

62739 L

62739 L

62739 L

62739 L

62739 L

62739 L

108/109/112

109/110/113

109/110/113

109/110/113

109/110/113

109/110/113

109/110/113

50 A

59040 R

59205 L

59205 L

59205 L

59205 L

59205 L

59205 L

106/107/109

106/107/109

106/107/109

106/107/109

106/107/109

106/107/109

106/107/109

For ANTI-ICE ON, decrease weight by 1050 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 44

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: 3500 ft TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 A 50 A

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

75733 R

77284 L

77284 L

77284 L

77284 L

77284 L

77284 L

120/121/124

122/123/125

122/123/125

121/123/125

121/123/125

121/123/125

121/123/125

75025 R

77138 L

77138 L

77138 L

77138 L

77138 L

77138 L

119/120/123

121/123/125

121/123/125

121/123/125

121/123/125

121/123/125

121/123/125

74333 R

76951 L

76951 L

76951 L

76951 L

76951 L

76951 L

118/120/123

121/122/125

121/122/125

121/122/125

121/122/125

121/122/125

121/122/125

73658 R

76726 L

76726 L

76726 L

76726 L

76726 L

76726 L

117/119/122

121/122/125

121/122/125

121/122/125

121/122/125

121/122/125

121/122/125

72993 R

76499 L

76499 L

76499 L

76499 L

76499 L

76499 L

117/118/122

121/122/124

121/122/124

121/122/124

121/122/124

121/122/124

121/122/124

72330 R

76272 L

76272 L

76272 L

76272 L

76272 L

76272 L

116/118/121

120/122/124

120/122/124

120/122/124

120/122/124

120/122/124

120/122/124

71685 R

75923 R

76034 L

76034 L

76034 L

76034 L

76034 L

115/117/120

120/122/124

120/122/124

120/122/124

120/122/124

120/122/124

120/122/124

71050 R

75246 R

75795 L

75795 L

75795 L

75795 L

75795 L

114/116/120

119/121/123

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

70393 R

74546 R

75422 L

75422 L

75422 L

75422 L

75422 L

114/116/119

118/120/123

119/121/124

119/121/124

119/121/124

119/121/124

119/121/124

69250 R

73340 R

74215 L

74215 L

74215 L

74215 L

74215 L

113/115/118

118/119/122

119/120/123

119/120/123

119/120/123

119/120/123

119/120/123

67309 R

71296 R

71702 L

71702 L

71702 L

71702 L

71702 L

111/113/117

116/118/120

117/118/120

117/118/120

117/118/120

117/118/120

117/118/120

65168 R

68647 L

68647 L

68647 L

68647 L

68647 L

68647 L

110/112/115

114/116/118

114/116/118

114/116/118

114/116/118

114/116/118

114/116/118

62826 R

65224 L

65224 L

65224 L

65224 L

65224 L

65224 L

108/110/113

112/113/115

112/113/115

111/113/115

111/113/115

111/113/115

111/113/115

60487 R

61849 L

61849 L

61849 L

61849 L

61849 L

61849 L

107/108/111

109/110/112

109/110/112

109/110/112

109/110/112

109/110/112

109/110/112

58160 R

58483 W

58483 W

58483 W

58483 W

58483 W

58483 W

105/106/108

106/107/109

106/107/109

106/107/109

106/107/109

106/107/109

106/107/109

For ANTI-ICE ON, decrease weight by 1050 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 45

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: 4000 ft RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

74539 R

75950 L

75950 L

75950 L

75950 L

75950 L

75950 L

119/120/123

120/122/124

120/122/124

120/122/124

120/122/124

120/122/124

120/122/124

-15

73842 R

75784 L

75784 L

75784 L

75784 L

75784 L

75784 L

118/119/122

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

-10

73155 R

75608 L

75608 L

75608 L

75608 L

75608 L

75608 L

117/119/122

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

-5

72481 R

75426 L

75426 L

75426 L

75426 L

75426 L

75426 L

116/118/121

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

0

71825 R

75228 L

75228 L

75228 L

75228 L

75228 L

75228 L

116/117/121

120/121/123

120/121/123

120/121/123

120/121/123

120/121/123

120/121/123

5

71176 R

75030 L

75030 L

75030 L

75030 L

75030 L

75030 L

115/117/120

119/121/123

119/121/123

119/121/123

119/121/123

119/121/123

119/121/123

10

70539 R

74710 R

74833 L

74833 L

74833 L

74833 L

74833 L

114/116/120

119/121/123

119/121/123

119/121/123

119/121/123

119/121/123

119/121/123

15

69913 R

74046 R

74635 L

74635 L

74635 L

74635 L

74635 L

113/115/119

118/120/122

119/121/123

119/121/123

119/121/123

119/121/123

119/121/123

20

69227 R

73324 R

74086 L

74086 L

74086 L

74086 L

74086 L

113/115/118

118/119/122

118/120/123

118/120/123

118/120/123

118/120/123

118/120/123

25

67877 R

71897 R

72597 L

72597 L

72597 L

72597 L

72597 L

112/114/117

116/118/121

117/119/121

117/119/121

117/119/121

117/119/121

117/119/121

30

66008 R

69931 R

70239 L

70239 L

70239 L

70239 L

70239 L

110/112/116

115/117/119

115/117/119

115/117/119

115/117/119

115/117/119

115/117/119

35

63925 R

67310 L

67310 L

67310 L

67310 L

67310 L

67310 L

109/111/114

113/114/117

113/114/117

113/114/117

113/114/117

113/114/117

113/114/117

40

61707 R

64099 L

64099 L

64099 L

64099 L

64099 L

64099 L

108/109/112

111/112/114

111/112/114

111/112/114

111/112/114

111/112/114

111/112/114

45 A

59486 R

60950 L

60950 L

60950 L

60950 L

60950 L

60950 L

106/107/110

108/109/111

108/109/111

108/109/111

108/109/111

108/109/111

108/109/111

50 A

57284 R

57700 W

57700 W

57700 W

57700 W

57700 W

57700 W

104/105/108

105/106/108

105/106/108

105/106/108

105/106/108

105/106/108

105/106/108

For ANTI-ICE ON, decrease weight by 900 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 46

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF

Airport Pressure Altitude: Sea Level TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

75901 R

80253 R

84399 R

88344 R

89000 S

89000 S

89000 S

132/137/140

137/141/144

142/145/148

146/149/151

147/150/152

147/150/152

147/150/152

75221 R

79522 R

83618 R

87515 R

89000 S

89000 S

89000 S

131/136/140

137/140/144

141/144/147

146/148/151

147/150/152

147/150/152

147/150/152

74569 R

78808 R

82856 R

86713 R

89000 S

89000 S

89000 S

130/135/139

136/140/143

140/144/147

145/147/150

147/150/152

147/150/152

147/150/152

73932 R

78119 R

82113 R

85927 R

89000 S

89000 S

89000 S

129/134/138

135/139/142

139/143/146

144/147/149

147/150/152

147/150/152

147/150/152

73286 R

77409 R

81368 R

85137 R

88726 R

89000 S

89000 S

128/134/138

134/138/142

139/142/145

143/146/149

147/149/152

147/150/152

147/150/152

72658 R

76735 R

80640 R

84359 R

87925 R

89000 S

89000 S

128/133/137

133/137/141

138/141/145

142/145/148

146/149/151

147/150/152

147/150/152

72031 R

76037 R

79903 R

83594 R

87111 R

89000 S

89000 S

127/133/137

132/137/140

137/141/144

141/144/147

145/148/150

147/150/152

147/150/152

71414 R

75374 R

79202 R

82844 R

86325 R

89000 S

89000 S

126/132/136

131/136/140

136/140/143

140/144/147

144/147/150

147/150/152

147/150/152

70818 R

74727 R

78499 R

82105 R

85549 R

88849 R

89000 S

125/131/135

130/135/139

135/139/143

139/143/146

143/146/149

147/150/152

147/150/152

70242 R

74098 R

77825 R

81392 R

84804 R

88063 R

89000 S

124/131/135

130/135/139

134/139/142

138/142/145

142/146/148

146/149/151

147/150/152

69673 R

73490 R

77166 R

80693 R

84075 R

87302 R

89000 S

124/130/134

129/134/138

133/138/141

138/142/145

141/145/148

145/148/150

147/150/152

67031 R

70769 R

74324 R

77734 R

80998 R

84124 R

87095 R

122/128/132

127/132/135

132/136/139

136/139/142

139/142/145

143/146/148

146/148/150

64456 R

68057 R

71485 R

74746 R

77899 R

80935 R

82200 W

120/125/129

125/129/133

130/133/136

134/137/139

137/140/142

141/143/145

142/144/146

61741 R

65228 R

68540 R

71687 R

74678 R

76772 W

76772 W

118/123/126

123/127/130

128/131/133

132/134/136

135/137/139

138/139/141

138/139/141

58996 R

62352 R

65560 R

68583 R

71467 R

71637 W

71637 W

116/120/124

121/124/127

126/128/130

130/131/133

133/134/136

133/135/136

133/135/136

For ANTI-ICE ON, decrease weight by 450 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 47

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF

Airport Pressure Altitude: 500 ft RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

74885 R

79166 R

83250 R

87133 R

89000 S

89000 S

89000 S

131/136/139

136/140/143

141/144/147

145/148/150

147/150/152

147/150/152

147/150/152

-15

74225 R

78448 R

82478 R

86320 R

89000 S

89000 S

89000 S

130/135/139

135/139/143

140/143/146

144/147/150

147/150/152

147/150/152

147/150/152

-10

73583 R

77744 R

81732 R

85536 R

89000 S

89000 S

89000 S

129/134/138

134/139/142

139/143/146

143/146/149

147/150/152

147/150/152

147/150/152

-5

72958 R

77064 R

81001 R

84759 R

88342 R

89000 S

89000 S

128/134/137

134/138/141

138/142/145

143/146/148

146/149/151

147/150/152

147/150/152

0

72334 R

76375 R

80276 R

83991 R

87536 R

89000 S

89000 S

127/133/137

133/137/141

137/141/144

142/145/148

145/148/151

147/150/152

147/150/152

5

71719 R

75714 R

79565 R

83233 R

86750 R

89000 S

89000 S

127/132/136

132/136/140

137/140/144

141/144/147

145/148/150

147/150/152

147/150/152

10

71094 R

75036 R

78845 R

82485 R

85955 R

89000 S

89000 S

126/132/136

131/136/139

136/140/143

140/143/146

144/147/149

147/150/152

147/150/152

15

70490 R

74391 R

78158 R

81752 R

85188 R

88468 R

89000 S

125/131/135

130/135/139

135/139/142

139/143/146

143/146/149

146/149/151

147/150/152

20

69904 R

73760 R

77471 R

81029 R

84430 R

87687 R

89000 S

124/130/135

129/134/138

134/138/142

138/142/145

142/145/148

146/149/151

147/150/152

25

69323 R

73125 R

76791 R

80321 R

83684 R

86904 R

89000 S

123/130/134

129/134/138

133/138/141

137/141/144

141/145/147

145/148/150

147/150/152

30

68371 R

72120 R

75719 R

79200 R

82519 R

85698 R

88745 R

122/129/133

128/133/137

132/137/140

136/140/143

140/144/146

144/147/149

147/150/152

35

65832 R

69501 R

72979 R

76321 R

79528 R

82601 R

85540 R

121/127/131

126/131/134

130/134/137

135/138/141

138/141/144

142/144/146

145/147/149

40

63284 R

66837 R

70198 R

73400 R

76493 R

79462 R

80550 W

119/124/128

124/128/132

129/132/135

133/135/138

136/139/141

140/142/143

141/143/144

45

60626 R

64047 R

67309 R

70408 R

73362 R

75258 W

75258 W

117/122/125

122/126/129

127/129/132

131/133/135

134/136/138

136/138/140

136/138/140

50 A

57965 R

61261 R

64406 R

67390 R

70227 R

70369 W

70369 W

115/119/122

120/123/126

125/127/129

128/130/132

132/133/135

132/133/135

132/133/135

For ANTI-ICE ON, decrease weight by 450 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 48

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF

Airport Pressure Altitude: 1000 ft TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 A

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

73892 R

78097 R

82109 R

85933 R

89000 S

89000 S

89000 S

130/135/138

135/139/142

140/143/146

144/147/149

147/150/152

147/150/152

147/150/152

73233 R

77392 R

81359 R

85135 R

88744 R

89000 S

89000 S

129/134/138

134/138/142

139/142/145

143/146/149

147/149/152

147/150/152

147/150/152

72599 R

76688 R

80625 R

84365 R

87945 R

89000 S

89000 S

128/133/137

133/138/141

138/142/145

142/145/148

146/149/151

147/150/152

147/150/152

71978 R

76014 R

79895 R

83608 R

87134 R

89000 S

89000 S

127/133/137

133/137/140

137/141/144

141/145/147

145/148/150

147/150/152

147/150/152

71377 R

75346 R

79190 R

82853 R

86350 R

89000 S

89000 S

126/132/136

132/136/140

136/140/143

141/144/147

144/147/150

147/150/152

147/150/152

70776 R

74706 R

78494 R

82114 R

85580 R

88884 R

89000 S

126/131/135

131/136/139

135/139/143

140/143/146

143/146/149

147/150/152

147/150/152

70159 R

74047 R

77802 R

81381 R

84815 R

88075 R

89000 S

125/131/135

130/135/139

135/139/142

139/142/145

143/146/148

146/149/151

147/150/152

69572 R

73417 R

77122 R

80665 R

84055 R

87295 R

89000 S

124/130/134

129/134/138

134/138/141

138/142/145

142/145/148

145/148/150

147/150/152

68996 R

72798 R

76446 R

79957 R

83318 R

86533 R

89000 S

123/129/134

128/134/137

133/137/141

137/141/144

141/144/147

144/147/150

147/150/152

68402 R

72157 R

75761 R

79246 R

82568 R

85748 R

88784 R

122/129/133

127/133/137

132/137/140

136/140/143

140/144/146

144/147/149

147/150/152

67078 R

70763 R

74285 R

77688 R

80964 R

84099 R

87094 R

121/128/132

126/132/135

131/135/139

135/139/142

139/142/145

142/145/148

146/148/150

64641 R

68244 R

71650 R

74919 R

78065 R

81084 R

83970 R

120/125/129

125/129/133

129/133/136

133/137/139

137/140/142

140/143/145

143/146/148

62114 R

65612 R

68912 R

72079 R

75090 R

78000 R

78996 W

118/123/127

123/127/130

127/131/134

131/134/137

135/137/139

138/140/142

139/141/143

59521 R

62885 R

66078 R

69132 R

72043 R

73888 W

73888 W

116/121/124

121/125/128

126/128/131

129/132/134

133/135/137

135/137/138

135/137/138

56953 R

60181 R

63268 R

66203 R

68994 R

69161 W

69161 W

115/118/121

119/122/125

124/126/128

127/129/131

131/132/134

131/132/134

131/132/134

For ANTI-ICE ON, decrease weight by 450 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 49

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF

Airport Pressure Altitude: 1500 ft RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

72761 R

76882 R

80850 R

84620 R

88220 R

89000 S

89000 S

129/134/137

134/138/141

139/142/145

143/146/148

147/149/151

148/150/152

148/150/152

-15

72110 R

76188 R

80111 R

83837 R

87404 R

89000 S

89000 S

128/133/137

133/137/141

138/141/144

142/145/147

146/148/151

148/150/152

148/150/152

-10

71483 R

75508 R

79381 R

83079 R

86610 R

89000 S

89000 S

127/132/136

132/136/140

137/140/143

141/144/147

145/148/150

147/150/152

147/150/152

-5

70868 R

74843 R

78669 R

82334 R

85819 R

89000 S

89000 S

126/132/136

131/136/139

136/140/143

140/143/146

144/147/149

147/150/152

147/150/152

0

70273 R

74189 R

77975 R

81591 R

85045 R

88349 R

89000 S

125/131/135

131/135/139

135/139/142

139/143/145

143/146/149

147/149/151

147/150/152

5

69680 R

73560 R

77287 R

80860 R

84287 R

87551 R

89000 S

125/130/134

130/134/138

134/138/142

139/142/145

142/145/148

146/149/151

147/150/152

10

69077 R

72916 R

76598 R

80145 R

83528 R

86758 R

89000 S

124/130/134

129/134/137

134/138/141

138/141/144

142/145/147

145/148/150

147/150/152

15

68495 R

72297 R

75941 R

79443 R

82793 R

85994 R

89000 S

123/129/133

128/133/137

133/137/140

137/141/144

141/144/147

144/147/149

147/150/152

20

67927 R

71686 R

75278 R

78747 R

82069 R

85248 R

88284 R

122/128/133

127/133/136

132/136/140

136/140/143

140/143/146

143/146/149

146/149/151

25

67348 R

71061 R

74613 R

78041 R

81329 R

84474 R

87490 R

121/128/132

127/132/136

131/136/139

135/139/142

139/143/145

143/146/148

146/149/151

30

65837 R

69483 R

72952 R

76292 R

79497 R

82576 R

85525 R

120/126/131

125/130/134

130/134/137

134/138/141

138/141/144

141/144/146

144/147/149

35

63521 R

67076 R

70432 R

73653 R

76736 R

79708 R

82552 R

119/124/128

124/128/132

128/132/135

132/135/138

136/139/141

139/142/144

142/145/146

40

61022 R

64454 R

67702 R

70810 R

73768 R

76616 R

77480 W

117/122/126

122/126/129

126/130/132

130/133/135

134/136/138

137/139/141

138/140/142

45

58463 R

61771 R

64921 R

67919 R

70776 R

72563 W

72563 W

115/120/123

120/123/126

125/127/130

128/130/133

132/134/135

134/135/137

134/135/137

50 A

55943 R

59121 R

62165 R

65057 R

67802 R

67981 W

67981 W

114/117/120

118/121/124

123/125/127

126/128/130

130/131/133

130/131/133

130/131/133

For ANTI-ICE ON, decrease weight by 450 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 50

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF

Airport Pressure Altitude: 2000 ft TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 A

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

71632 R

75682 R

79595 R

83315 R

86865 R

89000 S

89000 S

128/132/136

133/137/140

138/141/144

142/145/147

146/148/150

148/150/152

148/150/152

70987 R

74999 R

78867 R

82548 R

86063 R

89000 S

89000 S

127/132/136

132/136/139

137/140/143

141/144/146

145/147/149

148/150/152

148/150/152

70368 R

74338 R

78152 R

81800 R

85284 R

88608 R

89000 S

126/131/135

131/135/139

136/139/142

140/143/146

144/146/149

147/150/152

148/150/152

69758 R

73686 R

77452 R

81062 R

84503 R

87788 R

89000 S

125/131/134

130/135/138

135/139/142

139/142/145

143/146/148

146/149/151

148/150/152

69172 R

73041 R

76764 R

80333 R

83742 R

87004 R

89000 S

124/130/134

130/134/138

134/138/141

138/142/144

142/145/147

146/148/150

148/150/152

68585 R

72418 R

76083 R

79610 R

82995 R

86221 R

89000 S

123/129/133

129/133/137

133/137/140

138/141/144

141/144/147

145/147/150

148/150/152

67998 R

71790 R

75409 R

78910 R

82253 R

85457 R

88506 R

123/129/133

128/133/136

133/137/140

137/140/143

140/144/146

144/147/149

147/150/152

67424 R

71179 R

74766 R

78223 R

81533 R

84696 R

87731 R

122/128/132

127/132/136

132/136/139

136/140/142

140/143/145

143/146/148

146/149/151

66860 R

70577 R

74120 R

77540 R

80821 R

83964 R

86970 R

121/127/132

126/132/135

131/135/139

135/139/142

139/142/145

142/145/148

145/148/150

66297 R

69967 R

73474 R

76849 R

80095 R

83204 R

86185 R

120/127/131

126/131/135

130/135/138

134/138/141

138/141/144

141/145/147

145/147/150

64612 R

68201 R

71628 R

74897 R

78053 R

81068 R

83961 R

119/125/129

124/129/133

129/133/136

133/137/139

137/140/142

140/143/145

143/146/148

62432 R

65908 R

69217 R

72390 R

75415 R

78340 R

81055 W

118/123/127

123/127/131

127/131/134

131/134/137

135/138/140

138/141/143

141/143/145

59939 R

63306 R

66497 R

69539 R

72453 R

75246 R

75919 W

116/121/125

121/125/128

125/128/131

129/132/134

133/135/137

136/138/140

137/139/140

57410 R

60661 R

63768 R

66716 R

69522 R

71321 W

71321 W

114/119/122

119/122/125

123/126/129

127/129/131

131/132/134

133/134/136

133/134/136

54940 R

58067 R

61065 R

63915 R

66617 R

66910 W

66910 W

113/116/119

117/120/123

121/123/126

125/127/129

129/130/131

129/130/132

129/130/132

For ANTI-ICE ON, decrease weight by 450 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 51

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF

Airport Pressure Altitude: 2500 ft RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

70520 R

74515 R

78361 R

82025 R

85523 R

88864 R

89000 S

127/131/135

132/136/139

137/140/143

141/143/146

145/147/149

148/150/152

148/150/152

-15

69891 R

73843 R

77639 R

81266 R

84730 R

88035 R

89000 S

126/131/135

131/135/138

136/139/142

140/143/145

144/146/148

147/149/151

148/150/152

-10

69279 R

73186 R

76927 R

80522 R

83949 R

87227 R

89000 S

125/130/134

130/134/138

135/138/141

139/142/145

143/145/148

146/148/150

148/150/152

-5

68681 R

72540 R

76233 R

79792 R

83184 R

86423 R

88920 W

124/129/133

129/134/137

134/138/141

138/141/144

142/145/147

145/148/150

148/150/152

0

68090 R

71907 R

75553 R

79069 R

82427 R

85642 R

88718 R

123/129/133

129/133/137

133/137/140

137/140/143

141/144/146

144/147/149

148/150/152

5

67505 R

71283 R

74882 R

78354 R

81688 R

84867 R

87914 R

122/128/132

128/132/136

132/136/139

136/140/143

140/143/146

144/146/148

147/149/151

10

66922 R

70662 R

74224 R

77661 R

80955 R

84111 R

87114 R

122/128/132

127/132/135

131/136/139

136/139/142

139/142/145

143/146/148

146/148/150

15

66354 R

70058 R

73583 R

76981 R

80243 R

83356 R

86345 R

121/127/131

126/131/135

131/135/138

135/138/141

139/142/144

142/145/147

145/148/150

20

65805 R

69460 R

72948 R

76304 R

79531 R

82629 R

85593 R

120/126/131

125/130/134

130/134/138

134/138/141

138/141/144

141/144/146

144/147/149

25

65095 R

68709 R

72157 R

75466 R

78656 R

81717 R

84652 R

119/126/130

124/130/133

129/133/137

133/137/140

137/140/143

140/143/146

143/146/148

30

63330 R

66859 R

70213 R

73426 R

76510 R

79481 R

82314 R

118/124/128

123/128/132

128/132/135

132/135/138

135/138/141

139/141/144

142/144/146

35

61222 R

64641 R

67894 R

71003 R

73971 R

76831 R

79321 W

117/122/126

122/126/129

126/130/133

130/133/136

134/136/138

137/139/141

140/142/143

40

58826 R

62133 R

65282 R

68279 R

71142 R

73879 R

74387 W

115/120/123

120/124/127

124/127/130

128/131/133

132/134/136

135/137/138

135/137/139

45

56421 R

59609 R

62662 R

65560 R

68324 R

70113 W

70113 W

113/117/121

118/121/124

122/125/127

126/128/130

130/131/133

132/133/135

132/133/135

50 A

54076 R

57149 R

60089 R

62886 R

65550 R

65888 W

65888 W

112/115/118

116/119/122

120/122/125

124/126/128

127/129/130

128/129/131

128/129/131

For ANTI-ICE ON, decrease weight by 850 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 52

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF

Airport Pressure Altitude: 3000 ft TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 A 50 A

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

69425 R

73363 R

77137 R

80745 R

84188 R

87479 R

87903 W

126/130/134

131/135/138

136/139/141

140/142/145

143/146/148

147/149/151

147/149/151

68804 R

72695 R

76419 R

79993 R

83405 R

86665 R

87842 W

125/130/134

130/134/137

135/138/141

139/142/144

143/145/147

146/148/150

147/149/151

68200 R

72044 R

75710 R

79252 R

82634 R

85865 R

87776 W

124/129/133

129/133/137

134/137/140

138/141/143

142/144/146

145/147/149

147/149/151

67604 R

71404 R

75025 R

78529 R

81873 R

85065 R

87658 W

123/128/132

128/133/136

133/136/139

137/140/143

141/143/146

144/147/149

147/149/151

67016 R

70776 R

74358 R

77814 R

81122 R

84291 R

87324 R

122/128/132

128/132/135

132/136/139

136/139/142

140/143/145

143/146/148

146/149/151

66423 R

70156 R

73700 R

77113 R

80390 R

83523 R

86525 R

121/127/131

127/131/135

131/135/138

135/139/141

139/142/144

142/145/147

146/148/150

65853 R

69539 R

73051 R

76415 R

79668 R

82772 R

85736 R

121/127/131

126/131/134

130/134/138

135/138/141

138/141/144

142/144/147

145/147/149

65292 R

68941 R

72416 R

75747 R

78960 R

82025 R

84976 R

120/126/130

125/130/134

130/134/137

134/137/140

137/141/143

141/144/146

144/147/148

64748 R

68352 R

71785 R

75077 R

78253 R

81304 R

84223 R

119/125/130

124/129/133

129/133/136

133/137/140

137/140/142

140/143/145

143/146/148

63893 R

67459 R

70848 R

74098 R

77224 R

80237 R

83126 R

118/125/129

123/129/132

128/132/136

132/136/139

136/139/142

139/142/144

142/145/147

62050 R

65523 R

68821 R

71962 R

74981 R

77892 R

80686 R

117/123/127

122/127/130

126/130/134

130/134/137

134/137/139

137/140/142

140/143/145

60012 R

63376 R

66585 R

69628 R

72542 R

75333 R

77670 W

115/121/125

120/125/128

125/128/131

129/132/134

132/135/137

136/138/140

138/140/142

57715 R

60968 R

64076 R

67017 R

69830 R

72519 R

73074 W

114/119/122

119/123/126

123/126/129

127/129/132

130/133/135

134/135/137

134/136/138

55440 R

58575 R

61562 R

64409 R

67125 R

68980 W

68980 W

112/116/120

117/120/123

121/124/126

125/127/129

128/130/132

131/132/134

131/132/134

53210 R

56238 R

59126 R

61874 R

64490 R

64956 W

64956 W

111/114/117

115/118/121

119/121/124

123/125/127

126/128/129

127/128/130

127/128/130

For ANTI-ICE ON, decrease weight by 950 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 53

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF

Airport Pressure Altitude: 3500 ft RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

68339 R

72218 R

75921 R

79479 R

82867 R

86110 R

86625 W

125/129/133

130/134/137

134/138/140

139/141/144

142/145/147

146/148/150

146/148/150

-15

67727 R

71563 R

75217 R

78735 R

82093 R

85304 R

86557 W

124/129/133

129/133/136

134/137/140

138/140/143

141/144/146

145/147/149

146/148/150

-10

67129 R

70919 R

74524 R

78002 R

81332 R

84512 R

86487 W

123/128/132

128/132/136

133/136/139

137/140/142

141/143/145

144/146/148

146/148/150

-5

66538 R

70286 R

73854 R

77290 R

80583 R

83723 R

86408 W

122/127/131

127/132/135

132/135/138

136/139/142

140/142/145

143/145/147

146/148/150

0

65947 R

69664 R

73192 R

76583 R

79839 R

82960 R

85945 R

121/127/131

126/131/134

131/135/138

135/138/141

139/142/144

142/145/147

145/148/149

5

65375 R

69043 R

72542 R

75892 R

79116 R

82206 R

85164 R

120/126/130

126/130/134

130/134/137

134/138/140

138/141/143

141/144/146

145/147/149

10

64813 R

68444 R

71902 R

75209 R

78406 R

81468 R

84388 R

120/126/130

125/130/133

129/133/137

134/137/140

137/140/143

141/143/145

144/146/148

15

64259 R

67852 R

71272 R

74547 R

77709 R

80726 R

83634 R

119/125/129

124/129/133

129/133/136

133/136/139

136/140/142

140/143/145

143/145/147

20

63676 R

67239 R

70622 R

73868 R

76982 R

79990 R

82867 R

118/124/128

123/128/132

128/132/135

132/136/138

136/139/141

139/142/144

142/145/147

25

62641 R

66148 R

69480 R

72668 R

75732 R

78682 R

81515 R

117/123/127

122/127/131

127/131/134

131/134/137

135/138/140

138/141/143

141/144/145

30

60862 R

64279 R

67513 R

70606 R

73566 R

76422 R

79160 R

116/122/126

121/126/129

125/129/132

129/133/135

133/136/138

136/139/141

139/142/143

35

58888 R

62185 R

65328 R

68327 R

71196 R

73935 R

76052 W

114/120/124

119/124/127

124/127/130

128/131/133

131/134/136

134/137/138

137/139/140

40

56714 R

59903 R

62955 R

65844 R

68608 R

71253 R

71819 W

113/118/121

118/121/125

122/125/128

126/128/131

129/131/133

133/134/136

133/135/136

45 A

54550 R

57634 R

60572 R

63370 R

66038 R

67884 W

67884 W

111/115/119

116/119/122

120/123/125

124/126/128

127/129/131

130/131/133

130/131/133

50 A

52413 R

55385 R

58230 R

60937 R

63513 R

64063 W

64063 W

110/113/116

114/117/120

118/120/123

122/124/126

125/127/128

126/127/129

126/127/129

For ANTI-ICE ON, decrease weight by 850 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 54

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF

Airport Pressure Altitude: 4000 ft TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 A 50 A

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

67260 R

71081 R

74716 R

78218 R

81562 R

84750 R

85431 W

124/128/132

129/133/136

133/136/139

137/140/142

141/143/146

145/147/148

145/147/149

66657 R

70437 R

74034 R

77487 R

80792 R

83953 R

85363 W

123/128/131

128/132/135

133/136/139

137/139/142

140/143/145

144/146/148

145/147/149

66063 R

69799 R

73352 R

76763 R

80041 R

83174 R

85295 W

122/127/131

127/131/135

132/135/138

136/139/141

139/142/144

143/145/147

145/147/149

65470 R

69174 R

72689 R

76061 R

79304 R

82394 R

85226 W

121/126/130

126/131/134

131/134/137

135/138/140

139/141/143

142/144/146

145/147/149

64896 R

68558 R

72033 R

75362 R

78566 R

81639 R

84585 R

120/126/130

125/130/133

130/134/137

134/137/140

138/140/143

141/144/146

144/146/148

64333 R

67948 R

71393 R

74683 R

77853 R

80897 R

83812 R

119/125/129

125/129/133

129/133/136

133/137/139

137/140/142

140/143/145

143/146/148

63780 R

67357 R

70761 R

74013 R

77155 R

80169 R

83046 R

119/125/129

124/129/132

128/132/135

132/136/139

136/139/142

139/142/144

143/145/147

63232 R

66771 R

70137 R

73360 R

76461 R

79440 R

82299 R

118/124/128

123/128/132

128/132/135

132/135/138

135/138/141

139/141/144

142/144/146

62618 R

66135 R

69467 R

72665 R

75728 R

78690 R

81527 R

117/123/127

122/127/131

127/131/134

131/134/137

135/138/140

138/141/143

141/144/145

61397 R

64842 R

68114 R

71244 R

74245 R

77132 R

79913 R

116/122/126

121/126/130

126/130/133

130/133/136

133/136/139

137/139/141

140/142/144

59683 R

63032 R

66208 R

69249 R

72158 R

74948 R

77644 R

115/120/124

120/124/128

124/128/131

128/131/134

132/134/137

135/137/139

138/140/142

57774 R

61004 R

64087 R

67031 R

69852 R

72546 R

74508 W

113/119/122

118/122/126

123/126/129

126/129/132

130/132/135

133/135/137

135/137/139

55718 R

58854 R

61848 R

64680 R

67396 R

69992 R

70568 W

112/117/120

117/120/123

121/124/127

125/127/129

128/130/132

131/133/135

132/134/135

53660 R

56696 R

59589 R

62335 R

64956 R

66833 W

66833 W

110/115/118

115/118/121

119/122/124

123/125/127

126/128/130

129/130/132

129/130/132

51626 R

54540 R

57339 R

60006 R

62540 R

63197 W

63197 W

109/112/116

113/116/119

117/120/122

121/123/125

124/126/127

125/126/128

125/126/128

For ANTI-ICE ON, decrease weight by 800 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 55

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: Sea Level RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

84351 R

84744 L

84744 L

84744 L

84744 L

84744 L

84744 L

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

-15

83567 R

84668 L

84668 L

84668 L

84668 L

84668 L

84668 L

126/127/130

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

-10

82797 R

84577 L

84577 L

84577 L

84577 L

84577 L

84577 L

125/127/129

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

-5

82053 R

84501 L

84501 L

84501 L

84501 L

84501 L

84501 L

124/126/129

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

0

81297 R

84309 L

84309 L

84309 L

84309 L

84309 L

84309 L

123/125/128

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

127/128/131

5

80556 R

84129 L

84129 L

84129 L

84129 L

84129 L

84129 L

123/124/128

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

10

79811 R

83938 L

83938 L

83938 L

83938 L

83938 L

83938 L

122/124/127

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

15

79095 R

83737 L

83737 L

83737 L

83737 L

83737 L

83737 L

121/123/127

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

20

78396 R

83041 R

83547 L

83547 L

83547 L

83547 L

83547 L

120/122/126

125/127/130

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

25

77714 R

82314 R

83358 L

83358 L

83358 L

83358 L

83358 L

120/122/125

124/126/129

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

30

77046 R

81603 R

83168 L

83168 L

83168 L

83168 L

83168 L

119/121/125

124/126/129

125/127/130

125/127/130

125/127/130

125/127/130

125/127/130

35

74122 R

78537 R

78587 L

78587 L

78587 L

78587 L

78587 L

117/119/122

122/124/126

122/124/126

122/124/126

122/124/126

122/124/126

122/124/126

40

71349 R

74043 L

74043 L

74043 L

74043 L

74043 L

74043 L

116/117/120

119/120/122

119/120/122

119/120/122

119/120/122

119/120/122

119/120/122

45

68413 R

69733 L

69733 L

69733 L

69733 L

69733 L

69733 L

114/115/118

115/116/119

115/116/119

115/116/119

115/116/119

115/116/119

115/116/119

50

65176 W

65176 W

65176 W

65176 W

65176 W

65176 W

65176 W

112/112/115

112/112/115

112/112/115

112/112/115

112/112/115

112/112/115

112/112/115

For ANTI-ICE ON, decrease weight by 900 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 56

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: 500 ft TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 A

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

83183 R

84068 L

84068 L

84068 L

84068 L

84068 L

84068 L

126/127/130

127/128/130

127/128/130

127/128/130

127/128/130

127/128/130

127/128/130

82397 R

83994 L

83994 L

83994 L

83994 L

83994 L

83994 L

125/126/129

127/128/130

127/128/130

127/128/130

127/128/130

127/128/130

127/128/130

81640 R

83918 L

83918 L

83918 L

83918 L

83918 L

83918 L

124/126/129

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

80906 R

83824 L

83824 L

83824 L

83824 L

83824 L

83824 L

123/125/128

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

80168 R

83640 L

83640 L

83640 L

83640 L

83640 L

83640 L

122/124/127

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

126/128/130

79442 R

83455 L

83455 L

83455 L

83455 L

83455 L

83455 L

122/123/127

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

78714 R

83273 L

83273 L

83273 L

83273 L

83273 L

83273 L

121/123/126

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

78012 R

82655 R

83091 L

83091 L

83091 L

83091 L

83091 L

120/122/126

125/127/129

125/127/130

125/127/130

125/127/130

125/127/130

125/127/130

77327 R

81914 R

82909 L

82909 L

82909 L

82909 L

82909 L

119/121/125

124/126/129

125/127/130

125/127/130

125/127/130

125/127/130

125/127/130

76641 R

81181 R

82622 L

82622 L

82622 L

82622 L

82622 L

119/121/125

123/125/128

125/127/129

125/127/129

125/127/129

125/127/129

125/127/129

75569 R

80049 R

81521 L

81521 L

81521 L

81521 L

81521 L

118/120/124

123/124/127

124/126/128

124/126/128

124/126/128

124/126/128

124/126/128

72795 R

77059 L

77059 L

77059 L

77059 L

77059 L

77059 L

116/118/121

121/122/125

121/122/125

121/122/125

121/122/125

121/122/125

121/122/125

70054 R

72720 L

72720 L

72720 L

72720 L

72720 L

72720 L

114/116/119

118/119/121

118/119/121

118/119/121

118/119/121

118/119/121

118/119/121

67187 R

68476 L

68476 L

68476 L

68476 L

68476 L

68476 L

113/114/117

114/115/118

114/115/118

114/115/118

114/115/118

114/115/118

114/115/118

64029 W

64029 W

64029 W

64029 W

64029 W

64029 W

64029 W

111/111/114

111/111/114

111/111/114

111/111/114

111/111/114

111/111/114

111/111/114

For ANTI-ICE ON, decrease weight by 750 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 57

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: 1000 ft RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

82012 R

83394 L

83394 L

83394 L

83394 L

83394 L

83394 L

125/126/129

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

-15

81234 R

83323 L

83323 L

83323 L

83323 L

83323 L

83323 L

124/125/128

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

-10

80491 R

83251 L

83251 L

83251 L

83251 L

83251 L

83251 L

123/125/128

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

-5

79763 R

83126 L

83126 L

83126 L

83126 L

83126 L

83126 L

122/124/127

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

0

79046 R

82963 L

82963 L

82963 L

82963 L

82963 L

82963 L

121/123/126

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

126/127/130

5

78335 R

82773 L

82773 L

82773 L

82773 L

82773 L

82773 L

121/122/126

125/127/129

125/127/129

125/127/129

125/127/129

125/127/129

125/127/129

10

77621 R

82254 R

82595 L

82595 L

82595 L

82595 L

82595 L

120/122/125

125/126/129

125/127/129

125/127/129

125/127/129

125/127/129

125/127/129

15

76935 R

81520 R

82420 L

82420 L

82420 L

82420 L

82420 L

119/121/125

124/126/128

125/127/129

125/127/129

125/127/129

125/127/129

125/127/129

20

76263 R

80789 R

82244 L

82244 L

82244 L

82244 L

82244 L

118/120/124

123/125/128

125/126/129

125/126/129

125/126/129

125/126/129

125/126/129

25

75569 R

80053 R

81858 L

81858 L

81858 L

81858 L

81858 L

118/120/124

122/124/127

124/126/129

124/126/129

124/126/129

124/126/129

124/126/129

30

74099 R

78496 R

79832 L

79832 L

79832 L

79832 L

79832 L

117/119/122

121/123/126

123/125/127

123/125/127

123/125/127

123/125/127

123/125/127

35

71483 R

75533 L

75533 L

75533 L

75533 L

75533 L

75533 L

115/117/120

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

40

68760 R

71412 L

71412 L

71412 L

71412 L

71412 L

71412 L

113/115/118

117/118/120

117/118/120

117/118/120

117/118/120

117/118/120

117/118/120

45

65966 R

67205 L

67205 L

67205 L

67205 L

67205 L

67205 L

112/113/116

113/114/117

113/114/117

113/114/117

113/114/117

113/114/117

113/114/117

50 A

62948 W

62948 W

62948 W

62948 W

62948 W

62948 W

62948 W

110/111/113

110/111/113

110/111/113

110/111/113

110/111/113

110/111/113

110/111/113

For ANTI-ICE ON, decrease weight by 600 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 58

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: 1500 ft TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 A

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

80721 R

82077 L

82077 L

82077 L

82077 L

82077 L

82077 L

124/125/128

125/126/129

125/126/129

125/126/129

125/126/129

125/126/129

125/126/129

79959 R

81976 L

81976 L

81976 L

81976 L

81976 L

81976 L

123/124/127

125/126/129

125/126/129

125/126/129

125/126/129

125/126/129

125/126/129

79212 R

81867 L

81867 L

81867 L

81867 L

81867 L

81867 L

122/124/127

125/126/129

125/126/129

125/126/129

125/126/129

125/126/129

125/126/129

78498 R

81737 L

81737 L

81737 L

81737 L

81737 L

81737 L

121/123/126

125/126/129

125/126/129

125/126/129

125/126/129

125/126/129

125/126/129

77793 R

81574 L

81574 L

81574 L

81574 L

81574 L

81574 L

120/122/125

124/126/129

125/126/129

125/126/129

125/126/129

125/126/129

125/126/129

77095 R

81413 L

81413 L

81413 L

81413 L

81413 L

81413 L

120/122/125

124/126/128

124/126/128

124/126/128

124/126/128

124/126/128

124/126/128

76397 R

80960 R

81236 L

81236 L

81236 L

81236 L

81236 L

119/121/124

124/125/128

124/126/128

124/126/128

124/126/128

124/126/128

124/126/128

75720 R

80226 R

81044 L

81044 L

81044 L

81044 L

81044 L

118/120/124

123/125/127

124/126/128

124/126/128

124/126/128

124/126/128

124/126/128

75055 R

79520 R

80841 L

80841 L

80841 L

80841 L

80841 L

117/120/123

122/124/127

124/125/128

124/125/128

124/125/128

124/125/128

124/125/128

74389 R

78804 R

80500 L

80500 L

80500 L

80500 L

80500 L

117/119/123

122/123/126

123/125/128

123/125/128

123/125/128

123/125/128

123/125/128

72751 R

77047 R

78162 L

78162 L

78162 L

78162 L

78162 L

116/118/121

120/122/125

122/123/126

122/123/126

122/123/126

122/123/126

122/123/126

70271 R

74195 L

74195 L

74195 L

74195 L

74195 L

74195 L

114/116/119

119/120/123

119/120/123

119/120/123

119/120/123

119/120/123

119/120/123

67563 R

70134 L

70134 L

70134 L

70134 L

70134 L

70134 L

112/114/117

116/117/119

116/117/119

116/117/119

116/117/119

116/117/119

116/117/119

64806 R

65945 L

65945 L

65945 L

65945 L

65945 L

65945 L

111/112/114

112/113/115

112/113/115

112/113/115

112/113/115

112/113/115

112/113/115

61893 W

61893 W

61893 W

61893 W

61893 W

61893 W

61893 W

109/110/112

109/110/112

109/110/112

109/110/112

109/110/112

109/110/112

109/110/112

For ANTI-ICE ON, decrease weight by 700 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 59

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: 2000 ft RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

79443 R

80749 L

80749 L

80749 L

80749 L

80749 L

80749 L

123/124/127

124/125/128

124/125/128

124/125/128

124/125/128

124/125/128

124/125/128

-15

78687 R

80620 L

80620 L

80620 L

80620 L

80620 L

80620 L

122/123/126

124/125/128

124/125/128

124/125/128

124/125/128

124/125/128

124/125/128

-10

77947 R

80473 L

80473 L

80473 L

80473 L

80473 L

80473 L

121/123/126

124/125/128

124/125/128

124/125/128

124/125/128

124/125/128

124/125/128

-5

77239 R

80326 L

80326 L

80326 L

80326 L

80326 L

80326 L

120/122/125

124/125/128

124/125/128

124/125/128

124/125/128

124/125/128

124/125/128

0

76549 R

80180 L

80180 L

80180 L

80180 L

80180 L

80180 L

120/121/124

123/125/127

123/125/127

123/125/127

123/125/127

123/125/127

123/125/127

5

75860 R

80036 L

80036 L

80036 L

80036 L

80036 L

80036 L

119/121/124

123/125/127

123/125/127

123/125/127

123/125/127

123/125/127

123/125/127

10

75176 R

79676 R

79893 L

79893 L

79893 L

79893 L

79893 L

118/120/123

123/124/127

123/125/127

123/125/127

123/125/127

123/125/127

123/125/127

15

74520 R

78956 R

79689 L

79689 L

79689 L

79689 L

79689 L

117/119/123

122/124/126

123/125/127

123/125/127

123/125/127

123/125/127

123/125/127

20

73872 R

78257 R

79458 L

79458 L

79458 L

79458 L

79458 L

116/119/122

121/123/126

123/124/127

123/124/127

123/124/127

123/124/127

123/124/127

25

73226 R

77561 R

79147 L

79147 L

79147 L

79147 L

79147 L

116/118/122

121/123/125

122/124/127

122/124/127

122/124/127

122/124/127

122/124/127

30

71415 R

75609 R

76528 L

76528 L

76528 L

76528 L

76528 L

114/117/120

119/121/124

120/122/124

120/122/124

120/122/124

120/122/124

120/122/124

35

69062 R

72932 L

72932 L

72932 L

72932 L

72932 L

72932 L

113/115/118

118/119/122

118/119/122

118/119/122

118/119/122

118/119/122

118/119/122

40

66372 R

68843 L

68843 L

68843 L

68843 L

68843 L

68843 L

112/113/116

115/116/118

115/116/118

115/116/118

115/116/118

114/116/118

114/116/118

45

63656 R

64717 L

64717 L

64717 L

64717 L

64717 L

64717 L

110/111/113

111/112/114

111/112/114

111/112/114

111/112/114

111/112/114

111/112/114

50 A

60837 L

60837 L

60837 L

60837 L

60837 L

60837 L

60837 L

108/109/111

108/109/111

108/109/111

108/109/111

108/109/111

108/109/111

108/109/111

For ANTI-ICE ON, decrease weight by 750 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 60

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: 2500 ft TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 A

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

78189 R

79530 L

79530 L

79530 L

79530 L

79530 L

79530 L

122/123/126

123/124/127

123/124/127

123/124/127

123/124/127

123/124/127

123/124/127

77440 R

79404 L

79404 L

79404 L

79404 L

79404 L

79404 L

121/122/125

123/124/127

123/124/127

123/124/127

123/124/127

123/124/127

123/124/127

76719 R

79262 L

79262 L

79262 L

79262 L

79262 L

79262 L

120/122/125

123/124/127

123/124/127

123/124/127

123/124/127

123/124/127

123/124/127

76015 R

79092 L

79092 L

79092 L

79092 L

79092 L

79092 L

119/121/124

123/124/127

123/124/127

123/124/127

123/124/127

123/124/127

123/124/127

75331 R

78916 L

78916 L

78916 L

78916 L

78916 L

78916 L

119/120/124

122/124/126

122/124/126

122/124/126

122/124/126

122/124/126

122/124/126

74650 R

78738 L

78738 L

78738 L

78738 L

78738 L

78738 L

118/120/123

122/124/126

122/124/126

122/124/126

122/124/126

122/124/126

122/124/126

73985 R

78399 R

78557 L

78557 L

78557 L

78557 L

78557 L

117/119/122

122/123/126

122/124/126

122/124/126

122/124/126

122/124/126

122/124/126

73338 R

77698 R

78348 L

78348 L

78348 L

78348 L

78348 L

116/118/122

121/123/125

122/123/126

122/123/126

122/123/126

122/123/126

122/123/126

72701 R

77002 R

78127 L

78127 L

78127 L

78127 L

78127 L

115/118/121

120/122/125

122/123/126

122/123/126

122/123/126

122/123/126

122/123/126

71911 R

76154 R

77472 L

77472 L

77472 L

77472 L

77472 L

115/117/121

120/121/124

121/123/125

121/123/125

121/123/125

121/123/125

121/123/125

69995 R

74118 R

74761 L

74761 L

74761 L

74761 L

74761 L

113/115/119

118/120/122

119/121/123

119/121/123

119/121/123

119/121/123

119/121/123

67719 R

71411 L

71411 L

71411 L

71411 L

71411 L

71411 L

112/114/117

116/118/120

116/118/120

116/118/120

116/118/120

116/118/120

116/118/120

65142 R

67523 L

67523 L

67523 L

67523 L

67523 L

67523 L

110/112/115

113/115/117

113/115/117

113/115/117

113/115/117

113/115/117

113/115/117

62555 R

63689 L

63689 L

63689 L

63689 L

63689 L

63689 L

109/110/112

110/111/114

110/111/114

110/111/114

110/111/114

110/111/114

110/111/114

59989 L

59989 L

59989 L

59989 L

59989 L

59989 L

59989 L

107/108/110

107/108/110

107/108/110

107/108/110

107/108/110

107/108/110

107/108/110

For ANTI-ICE ON, decrease weight by 850 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 61

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: 3000 ft RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

76948 R

78317 L

78317 L

78317 L

78317 L

78317 L

78317 L

121/122/125

122/123/126

122/123/126

122/123/126

122/123/126

122/123/126

122/123/126

-15

76206 R

78192 L

78192 L

78192 L

78192 L

78192 L

78192 L

120/121/124

122/123/126

122/123/126

122/123/126

122/123/126

122/123/126

122/123/126

-10

75497 R

78054 L

78054 L

78054 L

78054 L

78054 L

78054 L

119/121/124

122/123/126

122/123/126

122/123/126

122/123/126

122/123/126

122/123/126

-5

74805 R

77852 L

77852 L

77852 L

77852 L

77852 L

77852 L

118/120/123

122/123/126

122/123/126

122/123/126

122/123/126

122/123/126

122/123/126

0

74135 R

77652 L

77652 L

77652 L

77652 L

77652 L

77652 L

118/119/123

122/123/125

122/123/125

122/123/125

122/123/125

122/123/125

122/123/125

5

73463 R

77457 L

77457 L

77457 L

77457 L

77457 L

77457 L

117/119/122

121/123/125

121/123/125

121/123/125

121/123/125

121/123/125

121/123/125

10

72806 R

77133 R

77241 L

77241 L

77241 L

77241 L

77241 L

116/118/121

121/123/125

121/123/125

121/123/125

121/123/125

121/123/125

121/123/125

15

72165 R

76439 R

77022 L

77022 L

77022 L

77022 L

77022 L

115/117/121

120/122/124

121/122/125

121/122/125

121/122/125

121/122/125

121/122/125

20

71536 R

75754 R

76810 L

76810 L

76810 L

76810 L

76810 L

115/117/120

119/121/124

121/122/125

121/122/125

121/122/125

121/122/125

121/122/125

25

70603 R

74759 R

75793 L

75793 L

75793 L

75793 L

75793 L

114/116/120

119/120/123

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

30

68585 R

72638 R

73087 L

73087 L

73087 L

73087 L

73087 L

112/114/118

117/119/121

118/119/122

118/119/122

118/119/122

118/119/122

118/119/122

35

66386 R

69857 L

69857 L

69857 L

69857 L

69857 L

69857 L

111/113/116

115/117/119

115/117/119

115/117/119

115/117/119

115/117/119

115/117/119

40

63919 R

66229 L

66229 L

66229 L

66229 L

66229 L

66229 L

109/111/114

112/113/116

112/113/116

112/113/116

112/113/116

112/113/116

112/113/116

45 A

61461 R

62656 L

62656 L

62656 L

62656 L

62656 L

62656 L

108/109/112

109/110/113

109/110/113

109/110/113

109/110/113

109/110/113

109/110/113

50 A

59013 R

59146 L

59146 L

59146 L

59146 L

59146 L

59146 L

106/107/109

106/107/109

106/107/109

106/107/109

106/107/109

106/107/109

106/107/109

For ANTI-ICE ON, decrease weight by 950 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 62

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: 3500 ft TEMP

(°C) -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 A 50 A

RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

75716 R

77092 L

77092 L

77092 L

77092 L

77092 L

77092 L

120/121/124

121/123/125

121/123/125

121/123/125

121/123/125

121/123/125

121/123/125

74995 R

76959 L

76959 L

76959 L

76959 L

76959 L

76959 L

119/120/123

121/122/125

121/122/125

121/122/125

121/122/125

121/122/125

121/122/125

74300 R

76795 L

76795 L

76795 L

76795 L

76795 L

76795 L

118/120/123

121/122/125

121/122/125

121/122/125

121/122/125

121/122/125

121/122/125

73625 R

76587 L

76587 L

76587 L

76587 L

76587 L

76587 L

117/119/122

121/122/125

121/122/125

121/122/125

121/122/125

121/122/125

121/122/125

72961 R

76382 L

76382 L

76382 L

76382 L

76382 L

76382 L

117/118/122

121/122/124

121/122/124

121/122/124

121/122/124

121/122/124

121/122/124

72298 R

76180 L

76180 L

76180 L

76180 L

76180 L

76180 L

116/118/121

120/122/124

120/122/124

120/122/124

120/122/124

120/122/124

120/122/124

71653 R

75899 R

75979 L

75979 L

75979 L

75979 L

75979 L

115/117/120

120/122/124

120/122/124

120/122/124

120/122/124

120/122/124

120/122/124

71019 R

75216 R

75767 L

75767 L

75767 L

75767 L

75767 L

114/116/120

119/121/123

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

70364 R

74512 R

75363 L

75363 L

75363 L

75363 L

75363 L

114/116/119

118/120/123

119/121/124

119/121/124

119/121/124

119/121/124

119/121/124

69222 R

73307 R

74119 L

74119 L

74119 L

74119 L

74119 L

113/115/118

118/119/122

118/120/123

118/120/123

118/120/123

118/120/123

118/120/123

67279 R

71266 R

71616 L

71616 L

71616 L

71616 L

71616 L

111/113/117

116/118/120

117/118/120

117/118/120

117/118/120

117/118/120

117/118/120

65141 R

68555 L

68555 L

68555 L

68555 L

68555 L

68555 L

110/112/115

114/115/118

114/115/118

114/115/118

114/115/118

114/115/118

114/115/118

62798 R

65137 L

65137 L

65137 L

65137 L

65137 L

65137 L

108/110/113

111/113/115

111/113/115

111/113/115

111/113/115

111/113/115

111/113/115

60460 R

61767 L

61767 L

61767 L

61767 L

61767 L

61767 L

107/108/111

109/110/112

109/110/112

109/110/112

109/110/112

109/110/112

109/110/112

58134 R

58412 W

58412 W

58412 W

58412 W

58412 W

58412 W

105/106/108

106/107/109

106/107/109

106/107/109

106/107/109

106/107/109

106/107/109

For ANTI-ICE ON, decrease weight by 950 lb.

AOM-1502-003

The certified MTOW of the airplane has to be respected.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 63

PERFORMANCE

AIRPLANE OPERATIONS MANUAL SIMPLIFIED TAKEOFF ANALYSIS TABLES EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF

Airport Pressure Altitude: 4000 ft RUNWAY LENGTH (ft) TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS) 5000 5600 6200 6800 7400 8000 8600

TEMP

(°C) -20

74506 R

75885 L

75885 L

75885 L

75885 L

75885 L

75885 L

119/120/123

120/122/124

120/122/124

120/122/124

120/122/124

120/122/124

120/122/124

-15

73810 R

75753 L

75753 L

75753 L

75753 L

75753 L

75753 L

118/119/122

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

-10

73124 R

75571 L

75571 L

75571 L

75571 L

75571 L

75571 L

117/119/122

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

-5

72452 R

75355 L

75355 L

75355 L

75355 L

75355 L

75355 L

116/118/121

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

120/121/124

0

71794 R

75140 L

75140 L

75140 L

75140 L

75140 L

75140 L

116/117/121

119/121/123

120/121/123

120/121/123

120/121/123

120/121/123

120/121/123

5

71145 R

74929 L

74929 L

74929 L

74929 L

74929 L

74929 L

115/117/120

119/121/123

119/121/123

119/121/123

119/121/123

119/121/123

119/121/123

10

70510 R

74677 R

74731 L

74731 L

74731 L

74731 L

74731 L

114/116/119

119/121/123

119/121/123

119/121/123

119/121/123

119/121/123

119/121/123

15

69883 R

74013 R

74534 L

74534 L

74534 L

74534 L

74534 L

113/115/119

118/120/122

119/120/123

119/120/123

119/120/123

119/120/123

119/120/123

20

69197 R

73291 R

74000 L

74000 L

74000 L

74000 L

74000 L

113/115/118

118/119/122

118/120/122

118/120/122

118/120/122

118/120/122

118/120/122

25

67846 R

71867 R

72511 L

72511 L

72511 L

72511 L

72511 L

112/114/117

116/118/121

117/119/121

117/119/121

117/119/121

117/119/121

117/119/121

30

65980 R

69900 R

70159 L

70159 L

70159 L

70159 L

70159 L

110/112/116

115/117/119

115/117/119

115/117/119

115/117/119

115/117/119

115/117/119

35

63898 R

67235 L

67235 L

67235 L

67235 L

67235 L

67235 L

109/111/114

113/114/117

113/114/117

113/114/117

113/114/117

113/114/117

113/114/117

40

61680 R

64028 L

64028 L

64028 L

64028 L

64028 L

64028 L

108/109/112

110/112/114

110/112/114

110/112/114

110/112/114

110/112/114

110/112/114

45 A

59460 R

60869 L

60869 L

60869 L

60869 L

60869 L

60869 L

106/107/110

108/109/111

108/109/111

108/109/111

108/109/111

108/109/111

108/109/111

50 A

57259 R

57630 W

57630 W

57630 W

57630 W

57630 W

57630 W

104/105/108

105/106/108

105/106/108

105/106/108

105/106/108

105/106/108

105/106/108

For ANTI-ICE ON, decrease weight by 950 lb.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 64

Takeoff

REVISION 21

AOM-1502-003

The certified MTOW of the airplane has to be respected.

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

TAKEOFF SPEEDS The following tables present V1, VR and V2 for balanced runway and fixed V2/VS ratio. The tables have been generated with the settings below: – ATTCS ON; – Balanced V1; – Minimum V2/VS; – Dry runway; – Anti-ice ON/OFF;

AOM-1502-003

– ECS ON/OFF.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 65

PERFORMANCE

AIRPLANE OPERATIONS MANUAL V1/VR/V2 SPEEDS

EMBRAER 170 – CF34-8E5 – T/O-1 – FLAP 1 – V2/VS = 1.20 PRESSURE

WEIGHT (lb) 53000 54000 55000 56000 57000 58000 59000 60000 61000 62000 63000 64000 65000 66000 67000 68000 69000 70000 71000 72000 73000 74000 75000 76000 77000 78000 79000 80000 81000 82000

STATIC AIR TEMPERATURE (°C) -40 -40 -40 -40

to to to to

38 35 31 27

39 36 32 28 -40 -40 -40

to to to to to to to

45 41 39 36 31 26 20

46 42 40 37 32 27 21 -40 -40

to to to to to to to to to

51 48 45 42 39 35 31 25 19

52 49 46 43 40 36 32 26 20 -40

to to to to to to to to to to ↓

52 50 48 46 44 42 40 38 33 34 28 29

to to ↓

36 34

↓

↓

↓

V1 VR V2

V1 VR V2

V1 VR V2

V1 VR V2

V1 VR V2

109 111 113 114 116 117 119 120 122 123 125 126 128 129 131 132 133 135 136 137 139 140 141 142 144 145 146 147 148 149

112 113 115 117 118 120 121 123 124 126 127 129 130 131 133 134 135 137 138 139 141 142 143 144 145 146 147 148 149 150

115 116 118 119 121 122 124 125 127 128 129 131 132 133 135 136 137 138 139 141 142 143 144 ---------------

117 118 120 121 123 124 126 127 129 130 131 133 134 135 136 -------------------------------

107 108 110 112 113 115 116 118 120 121 123 124 126 127 128 130 131 133 134 135 136 138 139 140 142 143 144 145 146 148

119 120 122 123 124 126 127 128 130 131 132 133 135 136 137 138 139 141 142 143 144 145 146 147 149 150 151 152 153 154

125 126 127 128 129 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148 149 150 151 152 153 154 155

120 121 123 124 125 127 128 129 130 132 133 134 135 137 138 139 140 141 143 144 145 146 147 148 149 150 151 152 153 154

125 126 127 128 129 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 147 148 148 149 150 151 152 153 154 155

121 122 124 125 126 128 129 130 131 133 134 135 136 138 139 140 141 142 143 144 145 147 148 149 150 151 152 153 154 155

125 126 127 128 129 131 132 133 134 135 136 137 138 139 140 141 142 143 145 146 147 148 149 150 150 151 152 153 154 155

122 123 125 126 127 129 130 131 132 134 135 136 137 138 139 141 142 143 144 145 146 147 148 ---------------

125 126 127 128 129 131 132 133 134 135 136 137 138 139 140 141 142 144 145 146 147 148 149 ---------------

123 124 125 127 128 129 131 132 133 134 135 137 138 139 140 -------------------------------

125 126 127 128 130 131 132 133 134 135 136 137 138 139 141 -------------------------------

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 66

Takeoff

REVISION 21

AOM-1502-003

ALTITUDE (ft) -1000 → SL → 1000 → 2000 → 3000 → 4000 → 5000 → 6000 → 7000 → 8000 →

PERFORMANCE

AIRPLANE OPERATIONS MANUAL V1/VR/V2 SPEEDS

EMBRAER 170 – CF34-8E5 – T/O-1 – FLAP 2 – V2/VS = 1.20 PRESSURE ALTITUDE (ft) -1000 → SL → 1000 → 2000 → 3000 → 4000 → 5000 → 6000 → 7000 → 8000 →

AOM-1502-003

WEIGHT (lb) 53000 54000 55000 56000 57000 58000 59000 60000 61000 62000 63000 64000 65000 66000 67000 68000 69000 70000 71000 72000 73000 74000 75000 76000 77000 78000 79000 80000 81000 82000

STATIC AIR TEMPERATURE (°C) -40 -40 -40 -40

to to to to

38 35 31 27

39 36 32 28 -40 -40 -40

to to to to to to to

43 40 37 34 29 24 20

44 41 38 35 30 25 21 -40 -40

to to to to to to to to to

48 46 43 40 36 33 28 22 16

↓

↓

↓

V1 VR V2

V1 VR V2

V1 VR V2

100 101 103 104 106 108 109 111 112 114 115 116 118 119 121 122 124 125 126 128 129 130 132 133 134 135 137 138 139 140

111 113 114 115 117 118 120 121 122 124 125 126 127 129 130 131 132 134 135 136 137 138 140 141 142 143 144 145 146 147

121 122 123 124 125 126 127 128 129 130 132 133 134 135 136 137 138 139 140 141 142 143 143 144 145 146 147 148 149 150

102 104 106 107 109 110 112 113 115 116 118 119 120 122 123 125 126 127 129 130 131 133 134 135 137 138 139 140 141 143

113 114 116 117 118 120 121 122 124 125 126 128 129 130 131 132 134 135 136 137 138 139 141 142 143 144 145 146 147 148

121 122 123 124 125 126 127 128 129 130 132 133 134 135 136 137 138 139 140 141 142 143 144 144 145 146 147 148 149 150

104 106 108 109 111 112 114 115 117 118 120 121 123 124 125 127 128 129 131 132 133 135 136 137 139 140 141 142 143 144

114 115 117 118 119 121 122 123 125 126 127 129 130 131 132 133 135 136 137 138 139 140 141 142 143 144 145 146 147 148

121 122 123 124 125 126 127 128 129 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 145 146 147 148 149 150

49 47 44 41 37 34 29 23 17 -40

to to to to to to to to to to ↓

52 50 48 46 43 40 36 32 27 21

V1 VR V2 107 108 110 111 113 114 116 117 119 120 122 123 125 126 128 129 130 131 133 134 136 137 138 139 140 -----------

115 116 118 119 120 122 123 124 126 127 128 129 131 132 133 134 135 136 138 139 140 141 142 143 144 -----------

121 122 123 124 125 126 127 128 129 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 -----------

44 41 37 33 28 22

to to to to to to ↓

44 42 40 38 36 34

V1 VR V2 109 111 112 114 115 117 118 120 122 123 124 126 127 128 130 131 132 133 135 -----------------------

116 118 119 121 122 123 124 126 127 128 129 131 132 133 134 135 136 137 138 -----------------------

121 122 123 124 125 126 127 128 130 131 132 133 134 135 136 137 138 139 140 -----------------------

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 67

PERFORMANCE

AIRPLANE OPERATIONS MANUAL V1/VR/V2 SPEEDS

EMBRAER 170 – CF34-8E5 – T/O-1 – FLAP 4 – V2/VS = 1.19 PRESSURE

WEIGHT (lb) 53000 54000 55000 56000 57000 58000 59000 60000 61000 62000 63000 64000 65000 66000 67000 68000 69000 70000 71000 72000 73000 74000 75000 76000 77000 78000 79000 80000 81000 82000

STATIC AIR TEMPERATURE (°C) -40 to -40 to -40 to

34 35 32 33 28 29 -40 -40

to to to to to

41 37 34 30 24

42 38 35 31 25 -40 -40

to to to to to to to

49 45 42 39 35 30 24

↓

↓

↓

V1 VR V2

V1 VR V2

V1 VR V2

91 91 91 92 93 95 96 98 99 100 102 103 104 106 107 108 110 111 112 114 115 116 117 118 119 121 122 123 124 125

97 96 96 97 99 100 101 102 104 105 106 107 108 110 111 112 113 114 115 116 117 119 120 121 122 123 124 125 126 127

108 107 106 107 108 109 110 111 112 112 113 114 115 116 117 118 119 119 120 121 122 123 124 124 125 126 127 128 129 129

90 91 93 94 95 97 98 100 101 102 104 105 106 108 109 110 112 113 114 115 117 118 119 120 122 123 123 124 125 127

95 96 97 99 100 101 103 104 105 106 107 109 110 111 112 113 114 115 116 118 119 119 121 121 122 123 124 125 126 127

105 105 106 107 108 109 110 111 112 112 113 114 115 116 117 118 119 120 120 121 122 123 124 125 125 126 127 128 129 129

92 93 95 96 98 99 101 102 103 105 106 107 109 110 111 113 114 115 116 118 119 120 121 122 123 124 ---------

96 98 99 100 101 103 104 105 106 107 109 110 111 112 113 114 115 116 118 119 120 121 121 122 123 124 ---------

104 105 106 107 108 109 110 111 112 112 113 114 115 116 117 118 119 120 120 121 122 123 124 125 125 126 ---------

50 46 43 40 36 31 25 -40 -40 -40

to to to to to to to to to to ↓

52 50 48 46 44 41 37 32 27 20

V1 VR V2 95 96 98 99 101 102 103 105 106 107 109 110 112 113 114 115 116 118 119 119 ---------------------

98 99 101 102 103 104 106 107 108 109 110 111 113 114 115 116 117 118 119 119 ---------------------

104 105 106 107 108 109 110 111 112 113 113 114 115 116 117 118 119 120 120 121 ---------------------

42 38 33 28 21

to to to to to ↓

42 40 38 36 34

V1 VR V2 98 99 101 102 103 105 106 108 109 110 111 113 114 -----------------------------------

100 101 102 104 105 106 107 108 109 110 112 113 114 -----------------------------------

104 105 106 107 108 109 110 111 112 113 113 114 115 -----------------------------------

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 68

Takeoff

REVISION 21

AOM-1502-003

ALTITUDE (ft) -1000 → SL → 1000 → 2000 → 3000 → 4000 → 5000 → 6000 → 7000 → 8000 →

PERFORMANCE

AIRPLANE OPERATIONS MANUAL V1/VR/V2 SPEEDS

EMBRAER 170 – CF34-8E5 – T/O-2 – FLAP 1 – V2/VS = 1.20 PRESSURE ALTITUDE (ft) -1000 → SL → 1000 → 2000 → 3000 → 4000 → 5000 → 6000 → 7000 → 8000 →

AOM-1502-003

WEIGHT (lb) 53000 54000 55000 56000 57000 58000 59000 60000 61000 62000 63000 64000 65000 66000 67000 68000 69000 70000 71000 72000 73000 74000 75000 76000 77000 78000 79000 80000 81000 82000

STATIC AIR TEMPERATURE (°C) -40 -40 -40 -40

to to to to

38 36 31 26

39 37 32 27 -40 -40 -40

to to to to to to to

45 43 38 33 28 23 20

46 44 39 34 29 24 21 -40 -40

to to to to to to to to to

52 50 48 44 40 35 30 25 20

45 41 36 31 26 21 -40

to to to to to to to ↓

46 44 42 40 38 33 34 29 30

to to ↓

36 34

↓

↓

↓

V1 VR V2

V1 VR V2

V1 VR V2

V1 VR V2

V1 VR V2

112 114 115 117 119 120 122 123 125 126 127 129 130 132 133 134 136 137 138 139 141 142 143 144 145 147 148 149 150 151

114 116 118 119 121 122 124 125 127 128 129 131 132 133 135 136 137 139 140 141 142 143 144 145 146 147 ---------

117 119 121 122 124 125 126 128 129 130 132 133 134 135 136 137 139 140 141 -----------------------

120 121 123 124 125 127 128 129 131 132 -----------------------------------------

110 111 113 115 116 118 119 121 122 124 125 127 128 130 131 132 134 135 136 138 139 140 142 143 144 145 146 148 149 150

120 121 123 124 125 127 128 129 131 132 133 134 136 137 138 139 140 141 143 144 145 146 147 148 149 150 151 152 153 154

125 126 127 128 129 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148 149 150 151 152 153 154 155

121 122 124 125 126 128 129 130 131 133 134 135 136 138 139 140 141 142 143 144 145 147 148 149 150 151 152 153 154 155

125 126 127 128 129 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 147 148 148 149 150 151 152 153 154 155

122 123 125 126 127 128 130 131 132 133 135 136 137 138 139 140 142 143 144 145 146 147 148 149 150 151 ---------

125 126 127 128 129 131 132 133 134 135 136 137 138 139 140 141 142 143 145 146 147 148 149 149 150 151 ---------

123 124 126 127 128 129 131 132 133 134 135 137 138 139 140 141 142 143 144 -----------------------

125 126 127 128 130 131 132 133 134 135 136 137 138 139 140 141 143 144 145 -----------------------

124 125 126 128 129 130 131 132 134 135 -----------------------------------------

125 126 127 128 130 131 132 133 134 135 -----------------------------------------

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 69

PERFORMANCE

AIRPLANE OPERATIONS MANUAL V1/VR/V2 SPEEDS

EMBRAER 170 – CF34-8E5 – T/O-2 – FLAP 2 – V2/VS = 1.20 PRESSURE

WEIGHT (lb) 53000 54000 55000 56000 57000 58000 59000 60000 61000 62000 63000 64000 65000 66000 67000 68000 69000 70000 71000 72000 73000 74000 75000 76000 77000 78000 79000 80000 81000 82000

STATIC AIR TEMPERATURE (°C) -40 -40 -40 -40

to to to to

37 35 30 26

38 36 31 27 -40 -40 -40

to to to to to to to

44 42 37 32 27 22 20

45 43 38 33 28 23 21 -40 -40

to to to to to to to to to

51 49 45 40 35 30 25 20 16

52 50 46 41 36 31 26 21 17 -40

to to to to to to to to to to ↓

52 50 48 46 44 40 36 31 26 21

41 37 32 27 22

to to to to to ↓

42 40 38 36 34

↓

↓

↓

V1 VR V2

V1 VR V2

V1 VR V2

V1 VR V2

V1 VR V2

105 107 109 110 112 113 115 116 118 119 121 122 123 125 126 128 129 131 132 133 134 135 137 138 139 140 142 143 144 145

107 109 110 112 113 115 116 118 119 121 122 124 125 127 128 129 131 132 133 135 136 137 139 140 141 142 ---------

110 111 113 114 116 117 119 120 122 123 125 126 127 129 130 132 133 134 135 136 ---------------------

112 114 116 117 119 120 122 123 125 126 127 128 130 131 ---------------------------------

103 104 106 108 109 111 112 114 115 117 118 120 121 122 124 125 127 128 129 130 132 133 134 136 137 138 140 141 142 143

113 114 116 117 119 120 121 123 124 125 126 128 129 130 131 133 134 135 136 137 138 140 141 142 143 144 145 146 147 148

121 122 123 124 125 126 127 128 129 130 132 133 134 135 136 137 138 139 140 141 142 143 143 144 145 146 147 148 149 150

114 116 117 119 120 121 123 124 125 126 128 129 130 131 133 134 135 136 137 138 139 140 141 143 143 145 145 146 147 148

121 122 123 124 125 126 127 128 129 131 132 133 134 135 136 137 138 139 140 141 142 143 144 144 145 146 147 148 149 150

115 117 118 119 121 122 123 125 126 127 128 130 131 132 133 134 136 137 138 139 140 141 142 143 144 145 ---------

121 122 123 124 125 126 127 128 129 131 132 133 134 135 136 137 138 139 140 141 142 143 144 144 145 146 ---------

116 118 119 121 122 123 124 126 127 128 129 130 132 133 134 135 136 137 138 139 ---------------------

121 122 123 124 125 126 127 128 129 131 132 133 134 135 136 137 138 139 140 141 ---------------------

118 119 121 122 123 124 126 127 128 129 130 131 132 133 ---------------------------------

121 122 123 124 125 126 127 128 130 131 132 133 134 135 ---------------------------------

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 70

Takeoff

REVISION 21

AOM-1502-003

ALTITUDE (ft) -1000 → SL → 1000 → 2000 → 3000 → 4000 → 5000 → 6000 → 7000 → 8000 →

PERFORMANCE

AIRPLANE OPERATIONS MANUAL V1/VR/V2 SPEEDS

EMBRAER 170 – CF34-8E5 – T/O-2 – FLAP 4 – V2/VS = 1.19 PRESSURE ALTITUDE (ft) -1000 → SL → 1000 → 2000 → 3000 → 4000 → 5000 → 6000 → 7000 → 8000 →

AOM-1502-003

WEIGHT (lb) 53000 54000 55000 56000 57000 58000 59000 60000 61000 62000 63000 64000 65000 66000 67000 68000 69000 70000 71000 72000 73000 74000 75000 76000 77000 78000 79000 80000 81000 82000

STATIC AIR TEMPERATURE (°C) -40 -40 -40 -40 -40 -40

to to to to to to

40 38 33 28 24 22

41 39 34 29 25 23 -40 -40 -40

to to to to to to to to to

49 47 42 37 32 27 22 18 16

↓

↓

V1 VR V2

V1 VR V2

92 94 95 97 98 100 101 102 104 105 106 108 109 110 112 113 115 115 117 118 119 120 121 122 123 124 125 -------

96 98 99 100 102 103 104 105 106 108 109 110 111 112 113 114 116 116 118 118 120 121 121 122 123 124 125 -------

104 105 106 107 108 109 110 111 112 112 113 114 115 116 117 118 119 120 120 121 122 123 124 124 125 126 127 -------

95 96 98 99 101 102 104 105 106 107 109 111 111 113 114 115 116 117 118 119 ---------------------

98 99 101 102 103 104 106 107 108 109 110 111 112 114 115 116 116 117 118 119 ---------------------

104 105 106 107 108 109 110 111 112 113 113 114 115 116 117 118 119 120 120 121 ---------------------

50 48 43 38 33 28 23 19 17 -40

to to to to to to to to to to ↓

52 50 48 46 42 36 32 26 21 14

V1 VR V2 97 99 100 101 103 104 105 107 108 110 111 112 113 114 ---------------------------------

99 101 102 103 104 106 107 108 109 110 111 112 113 114 ---------------------------------

104 105 106 107 108 109 110 111 112 113 113 114 115 116 ---------------------------------

43 37 33 27 22 15

to to to to to to ↓

44 42 40 36 37 31 32 26 27

V1 VR V2 99 101 102 104 105 106 107 109 110 111 -----------------------------------------

101 102 103 104 106 107 108 109 110 111 -----------------------------------------

104 105 106 107 108 109 110 111 112 113 -----------------------------------------

to to to ↓

38 36 34

V1 VR V2 101 103 104 105 -----------------------------------------------------

102 103 104 105 -----------------------------------------------------

104 105 106 107 -----------------------------------------------------

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 71

PERFORMANCE

AIRPLANE OPERATIONS MANUAL V1/VR/V2 SPEEDS

EMBRAER 175 – CF34-8E5 – T/O-1 – FLAP 1 – V2/VS = 1.20 PRESSURE

WEIGHT (lb) 57000 58000 59000 60000 61000 62000 63000 64000 65000 66000 67000 68000 69000 70000 71000 72000 73000 74000 75000 76000 77000 78000 79000 80000 81000 82000 83000 84000 85000 86000

STATIC AIR TEMPERATURE (°C) -40 -40 -40 -40 -40

to to to to to

38 35 32 28 24

39 36 33 29 25 -40 -40

to to to to to to to

44 41 38 35 30 25 20

45 42 39 36 31 26 21 -40 -40

to to to to to to to to to

50 47 44 41 38 34 29 24 16

51 48 45 42 39 35 30 25 17 -40

to to to to to to to to to to ↓

52 50 48 46 44 42 40 36 37 31 32 25 26

to to to ↓

38 36 34

↓

↓

↓

V1 VR V2

V1 VR V2

V1 VR V2

V1 VR V2

V1 VR V2

116 117 119 121 122 124 125 126 128 129 131 132 133 135 136 137 139 140 141 142 144 145 146 147 148 149 150 151 152 153

118 120 121 123 124 126 127 128 130 131 133 134 135 137 138 139 140 142 143 144 145 146 147 148 149 -----------

120 122 123 125 126 128 129 131 132 133 135 136 137 138 139 140 142 143 144 145 ---------------------

123 124 125 127 128 130 131 132 134 135 136 137 138 -----------------------------------

114 115 117 118 120 122 123 124 126 127 129 130 132 133 134 136 137 138 139 141 142 143 144 146 147 148 149 150 151 153

124 126 127 128 130 131 132 133 135 136 137 138 140 141 142 143 144 145 146 148 149 150 151 152 153 154 155 156 157 158

129 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148 149 150 151 152 153 154 155 156 157 158 159

125 127 128 129 130 132 133 134 135 137 138 139 140 141 143 144 145 146 147 148 149 150 151 152 153 154 155 156 157 158

129 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 147 148 148 149 150 151 152 153 154 155 156 157 158 159

126 127 129 130 131 133 134 135 136 137 139 140 141 142 143 144 145 147 148 149 150 151 152 153 154 -----------

129 131 132 133 134 135 136 137 138 139 140 141 142 143 145 146 147 148 149 150 150 151 152 153 154 -----------

127 128 130 131 132 133 135 136 137 138 139 140 142 143 144 145 146 147 148 149 ---------------------

129 131 132 133 134 135 136 137 138 139 140 141 142 144 145 146 147 148 149 150 ---------------------

128 129 131 132 133 134 135 136 138 139 140 141 142 -----------------------------------

130 131 132 133 134 135 136 137 138 139 141 142 143 -----------------------------------

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 72

Takeoff

REVISION 21

AOM-1502-003

ALTITUDE (ft) -1000 → SL → 1000 → 2000 → 3000 → 4000 → 5000 → 6000 → 7000 → 8000 →

PERFORMANCE

AIRPLANE OPERATIONS MANUAL V1/VR/V2 SPEEDS

EMBRAER 175 – CF34-8E5 – T/O-1 – FLAP 2 – V2/VS = 1.17 PRESSURE ALTITUDE (ft) -1000 → SL → 1000 → 2000 → 3000 → 4000 → 5000 → 6000 → 7000 → 8000 →

AOM-1502-003

WEIGHT (lb) 57000 58000 59000 60000 61000 62000 63000 64000 65000 66000 67000 68000 69000 70000 71000 72000 73000 74000 75000 76000 77000 78000 79000 80000 81000 82000 83000 84000 85000 86000

STATIC AIR TEMPERATURE (°C) -40 -40 -40 -40 -40

to to to to to

38 34 31 26 24

39 35 32 27 25 -40 -40

to to to to to to to

43 40 37 34 29 23 20

44 41 38 35 30 24 21 -40 -40

to to to to to to to to to

49 46 43 40 37 33 28 23 16

50 47 44 41 38 34 29 24 17 -40

to to to to to to to to to to ↓

52 50 48 46 44 42 38 34 29 24

39 35 30 25

to to to to ↓

40 38 36 34

↓

↓

↓

V1 VR V2

V1 VR V2

V1 VR V2

V1 VR V2

V1 VR V2

110 111 112 114 115 116 118 119 121 122 124 125 126 128 129 130 131 133 134 135 136 137 138 140 141 142 143 144 144 145

111 113 114 116 117 119 120 122 123 124 126 127 128 129 131 132 133 134 136 137 138 139 140 140 141 142 143 -------

114 115 117 118 120 121 122 124 125 126 128 129 130 131 132 133 135 136 136 137 ---------------------

116 118 119 121 122 123 124 126 127 128 129 130 131 -----------------------------------

108 109 111 112 114 115 116 117 119 120 122 123 124 126 127 129 130 131 132 134 135 136 137 138 139 141 142 143 144 145

116 118 119 120 121 122 123 125 126 127 128 129 130 131 132 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148

122 123 124 125 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 144 145 146 147 148 149 150

117 118 119 121 122 123 124 125 126 128 129 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148

122 123 124 125 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 145 146 147 148 149 150

118 119 120 121 122 124 125 126 127 128 129 130 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 -------

122 123 124 125 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 145 146 147 -------

118 120 121 122 123 124 126 127 128 129 130 131 132 133 134 135 136 137 138 140 ---------------------

122 123 124 125 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 141 ---------------------

119 121 122 123 124 125 126 128 129 130 131 132 133 -----------------------------------

122 123 124 125 126 127 128 129 130 131 132 133 134 -----------------------------------

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 73

PERFORMANCE

AIRPLANE OPERATIONS MANUAL V1/VR/V2 SPEEDS

EMBRAER 175 – CF34-8E5 – T/O-1 – FLAP 4 – V2/VS = 1.19 PRESSURE

WEIGHT (lb) 57000 58000 59000 60000 61000 62000 63000 64000 65000 66000 67000 68000 69000 70000 71000 72000 73000 74000 75000 76000 77000 78000 79000 80000 81000 82000 83000 84000 85000 86000

STATIC AIR TEMPERATURE (°C) -40 -40 -40 -40 -40

to to to to to

42 38 35 31 25

43 39 36 32 26 -40 -40 -40

to to to to to to to to

50 47 43 40 37 33 27 20

↓

↓

V1 VR V2

V1 VR V2

95 96 98 99 101 102 103 105 106 107 109 110 111 113 114 115 116 117 118 120 121 122 123 124 125 126 127 129 130 ---

100 101 102 103 105 106 107 108 109 111 112 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 128 129 130 ---

108 109 110 111 112 112 113 114 115 116 117 118 119 120 120 121 122 123 124 125 125 126 127 128 129 129 130 131 132 ---

98 100 101 102 104 105 106 108 109 110 112 113 115 116 117 118 119 120 121 123 123 -------------------

102 103 104 105 107 108 109 110 111 113 114 115 116 117 118 119 120 121 122 123 123 -------------------

108 109 110 111 112 113 113 114 115 116 117 118 119 120 120 121 122 123 124 125 125 -------------------

51 48 44 41 38 34 28 21 -40 -40

to to to to to to to to to to ↓

52 50 48 46 44 42 39 34 28 22

V1 VR V2 101 103 104 105 107 108 110 111 112 113 114 115 117 118 119 -------------------------------

104 105 106 107 108 109 111 112 113 114 115 116 117 118 119 -------------------------------

108 109 110 111 112 113 113 114 115 116 117 118 119 120 120 -------------------------------

40 35 29 23

to to to to ↓

40 38 35 36 30 31

V1 VR V2 103 105 106 108 109 110 112 113 ---------------------------------------------

105 106 107 108 110 111 112 113 ---------------------------------------------

108 109 110 111 112 113 113 114 ---------------------------------------------

to to ↓

36 34

V1 VR V2 104 106 108 109 -----------------------------------------------------

106 107 108 109 -----------------------------------------------------

108 109 110 111 -----------------------------------------------------

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 74

Takeoff

REVISION 21

AOM-1502-003

ALTITUDE (ft) -1000 → SL → 1000 → 2000 → 3000 → 4000 → 5000 → 6000 → 7000 → 8000 →

PERFORMANCE

AIRPLANE OPERATIONS MANUAL V1/VR/V2 SPEEDS

EMBRAER 175 – CF34-8E5 – T/O-2 – FLAP 1 – V2/VS = 1.20 PRESSURE ALTITUDE (ft) -1000 → SL → 1000 → 2000 → 3000 → 4000 → 5000 → 6000 → 7000 → 8000 →

AOM-1502-003

WEIGHT (lb) 57000 58000 59000 60000 61000 62000 63000 64000 65000 66000 67000 68000 69000 70000 71000 72000 73000 74000 75000 76000 77000 78000 79000 80000 81000 82000 83000 84000 85000 86000

STATIC AIR TEMPERATURE (°C) -40 -40 -40 -40

to to to to

38 36 31 26

39 37 32 27 -40 -40 -40

to to to to to to to

46 44 39 34 30 24 20

47 45 40 35 31 25 21 -40 -40 -40

to to to to to to to to to to ↓

52 50 48 43 38 34 29 24 19 14

44 39 35 30 25 20 15

to to to to to to to ↓

46 44 42 39 35 30 25

40 36 31 26

to to to to ↓

40 38 36 34

↓

↓

V1 VR V2

V1 VR V2

V1 VR V2

V1 VR V2

V1 VR V2

119 120 122 123 125 126 127 129 130 132 133 134 136 137 138 140 141 142 143 144 146 147 148 149 150 151 152 153 -----

121 122 124 125 127 128 130 131 132 134 135 136 137 139 140 141 142 143 144 145 146 -------------------

123 125 126 127 129 130 132 133 134 135 136 137 139 140 141 -------------------------------

125 126 128 129 130 131 133 134 ---------------------------------------------

116 118 119 121 123 124 125 127 128 130 131 132 134 135 136 138 139 140 142 143 144 145 146 148 149 150 151 152 153 154

125 127 128 129 131 132 133 134 136 137 138 139 140 141 143 144 145 146 147 148 149 150 151 152 153 154 155 156 157 158

129 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148 149 150 151 152 153 154 155 156 157 158 159

126 128 129 130 131 133 134 135 136 138 139 140 141 142 143 144 146 147 148 149 150 151 152 153 154 155 156 156 -----

129 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 147 148 148 149 150 151 152 153 154 155 156 157 -----

127 129 130 131 132 134 135 136 137 138 139 141 142 143 144 145 146 147 148 149 150 -------------------

129 131 132 133 134 135 136 137 138 139 140 141 142 144 145 146 147 148 149 149 150 -------------------

128 129 131 132 133 134 135 136 138 139 140 141 142 143 144 -------------------------------

130 131 132 133 134 135 136 137 138 139 140 141 143 144 145 -------------------------------

129 130 131 132 133 135 136 137 ---------------------------------------------

130 131 132 133 134 135 136 137 ---------------------------------------------

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 75

PERFORMANCE

AIRPLANE OPERATIONS MANUAL V1/VR/V2 SPEEDS

EMBRAER 175 – CF34-8E5 – T/O-2 – FLAP 2 – V2/VS = 1.17 PRESSURE

WEIGHT (lb) 57000 58000 59000 60000 61000 62000 63000 64000 65000 66000 67000 68000 69000 70000 71000 72000 73000 74000 75000 76000 77000 78000 79000 80000 81000 82000 83000 84000 85000 86000

STATIC AIR TEMPERATURE (°C) -40 -40 -40 -40 -40

to to to to to

37 35 31 26 24

38 36 32 27 25 -40

to to to to to to

44 42 37 33 28 22

45 43 38 34 29 23 -40 -40 -40

to to to to to to to to to

52 50 47 42 37 33 28 23 18

48 43 38 34 29 24 19 -40

to to to to to to to to ↓

48 46 44 42 40 36 37 32 33 27 28

↓

↓

↓

V1 VR V2

V1 VR V2

V1 VR V2

V1 VR V2

111 113 115 116 118 119 121 122 124 125 126 128 129 130 131 133 134 135 136 137 138 139 140 141 142 143 144 -------

114 116 117 119 120 121 123 124 125 127 128 129 130 132 133 134 135 136 137 138 139 -------------------

117 119 120 121 123 124 125 126 127 128 129 130 132 -----------------------------------

111 112 113 114 116 117 119 120 122 123 125 126 127 129 130 131 133 134 135 136 137 138 139 140 141 142 143 144 145 146

117 119 120 121 122 123 124 126 127 128 129 130 131 132 133 134 135 137 138 139 140 141 142 143 144 144 145 146 147 148

122 123 124 125 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 144 145 146 147 148 149 150

118 119 120 121 123 124 125 126 127 128 129 130 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 -------

122 123 124 125 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 144 145 146 147 -------

119 120 121 122 123 125 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 -------------------

122 123 124 125 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 141 142 -------------------

120 121 122 123 124 125 127 128 129 130 131 132 133 -----------------------------------

122 123 124 125 126 127 128 129 130 131 132 133 134 -----------------------------------

to to to ↓

38 36 34

V1 VR V2 119 121 122 123 124 ---------------------------------------------------

120 122 123 124 125 ---------------------------------------------------

122 123 124 125 126 ---------------------------------------------------

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 76

Takeoff

REVISION 21

AOM-1502-003

ALTITUDE (ft) -1000 → SL → 1000 → 2000 → 3000 → 4000 → 5000 → 6000 → 7000 → 8000 →

PERFORMANCE

AIRPLANE OPERATIONS MANUAL V1/VR/V2 SPEEDS

EMBRAER 175 – CF34-8E5 – T/O-2 – FLAP 4 – V2/VS = 1.19 PRESSURE ALTITUDE (ft) -1000 → SL → 1000 → 2000 → 3000 → 4000 → 5000 → 6000 → 7000 → 8000 →

AOM-1502-003

WEIGHT (lb) 57000 58000 59000 60000 61000 62000 63000 64000 65000 66000 67000 68000 69000 70000 71000 72000 73000 74000 75000 76000 77000 78000 79000 80000 81000 82000 83000 84000 85000 86000

STATIC AIR TEMPERATURE (°C) -40 to -40 to -40 to

35 36 33 34 28 29 -40 -40 -40 -40

to to to to to to to

43 42 37 32 26 22 20

44 43 38 33 27 23 21 -40 -40

to to to to to to to to to

52 50 48 44 39 34 29 23 18

↓

↓

↓

V1 VR V2

V1 VR V2

V1 VR V2

97 98 100 101 103 104 105 107 108 109 111 112 113 114 116 117 118 120 121 122 123 124 -----------------

101 102 103 105 106 107 108 109 111 112 113 114 115 116 117 118 119 120 121 122 123 124 -----------------

108 109 110 111 112 112 113 114 115 116 117 118 119 119 120 121 122 123 124 124 125 126 -----------------

99 101 102 103 105 106 107 109 110 112 113 114 115 116 117 118 119 121 122 123 ---------------------

102 103 105 106 107 108 109 111 112 113 114 115 116 117 118 119 120 121 122 123 ---------------------

108 109 110 111 112 112 113 114 115 116 117 118 119 120 120 121 122 123 124 124 ---------------------

102 103 104 106 107 109 110 111 112 113 114 115 117 118 ---------------------------------

104 105 106 107 108 110 111 112 113 114 115 116 117 118 ---------------------------------

108 109 110 111 112 113 113 114 115 116 117 118 119 120 ---------------------------------

45 40 35 30 24 19 -40

to to to to to to to ↓

46 44 40 35 30 25 19

V1 VR V2 104 106 107 108 109 111 112 -----------------------------------------------

105 106 107 109 110 111 112 -----------------------------------------------

108 109 110 111 112 113 113 -----------------------------------------------

41 36 31 26 20

to to to to to ↓

42 40 38 36 34

V1 VR V2 105 107 108 109 -----------------------------------------------------

106 107 108 109 -----------------------------------------------------

108 109 110 111 -----------------------------------------------------

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 77

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

FLAP RETRACTION SPEED SCHEDULE During flap retraction, the next flap setting should be selected when the F-Bug is reached.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 78

Takeoff

REVISION 21

AOM-1502-003

The F-Bug calculation algorithm is designed so as to meet minimum safe margins to VFE and Shaker speed. A minimum margin of 20% above the stall speed is set for the next flap.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

FINAL SEGMENT SPEED EMBRAER 170 WEIGHT (lb) 48000 50000 52000 54000 56000 58000 60000 62000 64000 66000 68000 70000 72000 74000 76000 78000 80000 82000

VFS (KIAS) 154 158 161 164 167 170 173 176 179 181 184 187 189 192 195 197 200 202 EMBRAER 175

AOM-1502-003

WEIGHT (lb) 50000 52000 54000 56000 58000 60000 62000

VFS (KIAS) 158 161 164 167 170 173 176

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 79

AIRPLANE OPERATIONS MANUAL

WEIGHT (lb) 64000 66000 68000 70000 72000 74000 76000 78000 80000 82000 84000 86000

VFS (KIAS) 179 181 184 187 189 192 195 197 200 202 205 207

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 80

Takeoff

REVISION 21

AOM-1502-003

PERFORMANCE

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

STAB TRIM SETTING FOR TAKEOFF EMBRAER 170/175 ALL WEIGHTS FLAP

CG POSITION (% MAC) 7

9

11

13

15

17

19

21

23

25

27

1

6.0 UP

6.0 UP

5.5 UP

5.0 UP

5.0 UP

4.5 UP

4.0 UP

3.5 UP

3.0 UP

3.0 UP

2.5 UP

2

6.0 UP

6.0 UP

5.5 UP

5.0 UP

4.5 UP

4.0 UP

3.5 UP

3.5 UP

3.0 UP

2.5 UP

2.0 UP

4

6.0 UP

5.5 UP

5.0 UP

4.5 UP

4.0 UP

3.5 UP

3.0 UP

2.5 UP

2.0 UP

1.5 UP

1.0 UP

!EMBRAER 175 Models with enhanced wing tip or POST-MOD SB-170-57-0058

EMBRAER 170/175 with enhanced wing tip ALL WEIGHTS

AOM-1502-003

FLAP

CG POSITION (% MAC) 11

13

15

17

19

21

23

25

27

29

31

1

5.5 UP

5.5 UP

4.5 UP

4.5 UP

4.0 UP

3.5 UP

3.0 UP

3.0 UP

2.5 UP

2.0 UP

1.5 UP

2

5.5 UP

5.0 UP

4.5 UP

4.0 UP

3.5 UP

3.5 UP

3.0 UP

2.5 UP

2.0 UP

2.0 UP

1.5 UP

4

5.5 UP

5.0 UP

4.5 UP

4.0 UP

3.5 UP

3.0 UP

2.5 UP

2.5 UP

2.0 UP

1.5 UP

1.0 UP "

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 81

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT - ALL ENGINES OPERATING !EMBRAER 170 Models

The climb gradient tables show the climb gradients in percentage and in ft/NM for several weights, temperatures and pressure altitudes. These tables are published in the following configurations:

GRADIENTS FOR TAKEOFF THRUST The gradients were obtained for: – A speed equal to V2 + 10 KIAS; – FLAP 2; – V2/VS ratio equal to the minimum of the range; – Anti-Ice OFF; – ECS ON; – Landing Gear Up; – Wings Leveled; – Temperatures in Celsius Degrees.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 82

Takeoff

REVISION 21

AOM-1502-003

Corrections in the climb gradient for Anti-Ice ON and Flaps 4 are also provided in the footer of each table.

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

GRADIENTS FOR CLIMB THRUST The gradients were obtained for: – A speed equal to VFS KIAS and 250 KIAS; – FLAP UP; – CLB-1 Thrust Rating; – Anti-Ice OFF; – ECS ON; – Landing Gear Up; – Wings Leveled; – Temperatures in ISA Deviation.

AOM-1502-003

Corrections in the climb gradient for Anti-Ice ON and CLB-2 thrust rating are also provided in the footer of each table.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 83

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.20 Altitude: Sea Level Grad % WEIGHT (lb) (ft/NM) SAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

30 and

39.2

33.5

29.0

25.4

22.4

19.9

17.8

16.0

below

(2383)

(2035)

(1761)

(1540)

(1359)

(1207)

(1079)

(973)

35.9

30.7

26.5

23.2

20.4

18.1

16.1

14.5

(2181)

(1864)

(1612)

(1408)

(1240)

(1099)

(980)

(882)

32.8

27.9

24.1

21.0

18.5

16.3

14.5

13.0

(1989)

(1697)

(1466)

(1278)

(1123)

(992)

(882)

(791)

35

40 29.6

25.2

21.8

18.9

16.6

14.6

12.9

11.5

(1799)

(1533)

(1322)

(1150)

(1007)

(886)

(784)

(701)

45 26.6

22.6

19.4

16.9

14.7

12.9

11.3

10.1

(1614)

(1374)

(1181)

(1023)

(892)

(781)

(688)

(613)

50 A-ICE CORRECTION SUBTRACT: 0.0 % OR 0. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 84

Takeoff

REVISION 21

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.1 % OR 64. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.20 Altitude: 2000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

25 and

36.8

31.5

27.3

23.9

21.1

18.8

16.8

15.1

below

(2236)

(1912)

(1657)

(1451)

(1282)

(1139)

(1018)

(919)

34.9

29.8

25.8

22.5

19.8

17.5

15.6

14.1

(2119)

(1811)

(1566)

(1367)

(1203)

(1064)

(949)

(854)

32.2

27.5

23.7

20.6

18.1

16.0

14.2

12.7

(1954)

(1668)

(1439)

(1254)

(1100)

(970)

(862)

(773)

30

35 29.2

24.9

21.4

18.6

16.3

14.3

12.7

11.3

(1772)

(1510)

(1300)

(1130)

(988)

(868)

(769)

(688)

40 26.4

22.5

19.3

16.7

14.5

12.7

11.2

9.9

(1605)

(1365)

(1172)

(1014)

(883)

(772)

(679)

(602)

23.8

20.2

17.3

14.9

12.9

11.2

9.8

8.6

(1445)

(1226)

(1048)

(903)

(782)

(679)

(593)

(522)

45

50 A-ICE CORRECTION SUBTRACT: 0.0 % OR 0. ft/NM

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.0 % OR 62. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 85

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.20 Altitude: 4000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

20 and

33.9

28.9

25.1

21.9

19.3

17.1

15.3

13.8

below

(2057)

(1758)

(1523)

(1333)

(1175)

(1041)

(929)

(837)

32.6

27.9

24.2

21.1

18.6

16.5

14.7

13.2

(1983)

(1694)

(1467)

(1282)

(1129)

(1000)

(891)

(801)

30.6

26.1

22.6

19.7

17.3

15.2

13.5

12.1

(1860)

(1588)

(1372)

(1195)

(1049)

(926)

(821)

(735)

25

30 28.4

24.1

20.8

18.1

15.8

13.9

12.3

10.9

(1722)

(1467)

(1264)

(1098)

(959)

(842)

(744)

(663)

35 26.0

22.1

19.0

16.4

14.3

12.5

10.9

9.7

(1582)

(1344)

(1153)

(996)

(866)

(756)

(664)

(588)

23.8

20.2

17.2

14.8

12.8

11.1

9.7

8.5

(1448)

(1226)

(1047)

(900)

(778)

(674)

(588)

(517)

21.7

18.3

15.6

13.3

11.4

9.8

8.5

7.4

(1319)

(1112)

(945)

(808)

(693)

(596)

(515)

(448)

40

45

50 A-ICE CORRECTION SUBTRACT: 0.0 % OR 1. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 86

Takeoff

REVISION 21

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.1 % OR 65. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.20 Altitude: 6000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

15 and

31.3

26.7

23.2

20.2

17.8

15.7

14.0

12.6

below

(1900)

(1625)

(1406)

(1228)

(1081)

(956)

(850)

(763)

30.5

26.1

22.6

19.7

17.3

15.3

13.6

12.2

(1854)

(1585)

(1371)

(1196)

(1052)

(929)

(826)

(741)

28.7

24.5

21.1

18.4

16.1

14.2

12.6

11.3

(1742)

(1487)

(1284)

(1118)

(980)

(864)

(766)

(686)

20

25 26.9

22.9

19.7

17.1

15.0

13.1

11.6

10.4

(1632)

(1390)

(1198)

(1041)

(909)

(798)

(706)

(629)

30 25.1

21.3

18.3

15.8

13.8

12.0

10.6

9.4

(1523)

(1295)

(1112)

(962)

(836)

(730)

(641)

(569)

23.3

19.7

16.9

14.5

12.6

10.9

9.5

8.4

(1415)

(1198)

(1024)

(882)

(763)

(662)

(577)

(508)

21.6

18.2

15.5

13.2

11.4

9.8

8.5

7.4

(1309)

(1104)

(939)

(803)

(690)

(595)

(515)

(450)

19.9

16.7

14.1

12.0

10.3

8.8

7.5

6.5

(1211)

(1016)

(859)

(730)

(623)

(532)

(456)

(395)

35

40

45

50 A-ICE CORRECTION SUBTRACT: 0.1 % OR 4. ft/NM

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.1 % OR 67. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 87

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.20 Altitude: 8000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10 and

28.9

24.7

21.4

18.6

16.4

14.4

12.8

11.5

below

(1759)

(1502)

(1298)

(1132)

(993)

(876)

(777)

(696)

28.6

24.4

21.1

18.4

16.1

14.2

12.6

11.3

(1736)

(1483)

(1281)

(1117)

(979)

(863)

(765)

(684)

26.9

22.9

19.8

17.2

15.0

13.2

11.7

10.4

(1633)

(1393)

(1201)

(1044)

(914)

(803)

(709)

(633)

15

20 25.2

21.5

18.5

16.0

14.0

12.2

10.8

9.6

(1532)

(1305)

(1122)

(973)

(848)

(742)

(654)

(581)

25 23.6

20.0

17.2

14.8

12.9

11.2

9.8

8.7

(1432)

(1217)

(1044)

(902)

(783)

(683)

(598)

(529)

22.0

18.6

15.9

13.7

11.8

10.3

8.9

7.9

(1333)

(1130)

(966)

(831)

(718)

(623)

(542)

(477)

20.4

17.2

14.6

12.5

10.8

9.3

8.0

7.0

(1239)

(1045)

(890)

(761)

(654)

(564)

(488)

(426)

18.9

15.9

13.5

11.5

9.8

8.4

7.2

6.2

(1149)

(965)

(817)

(696)

(594)

(508)

(435)

(376)

30

35

40

45 A-ICE CORRECTION SUBTRACT: 0.7 % OR 45. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 88

Takeoff

REVISION 21

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.1 % OR 69. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 170 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.20 Altitude: 10000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10 and

26.1

22.3

19.2

16.7

14.7

12.9

11.4

10.2

below

(1582)

(1352)

(1168)

(1016)

(890)

(783)

(693)

(619)

25.1

21.4

18.4

16.0

13.9

12.2

10.7

9.6

(1523)

(1297)

(1117)

(969)

(845)

(740)

(652)

(581)

23.5

20.0

17.2

14.9

13.0

11.3

9.9

8.8

(1428)

(1214)

(1043)

(903)

(787)

(688)

(603)

(535)

15

20 22.1

18.7

16.1

13.8

12.0

10.4

9.1

8.1

(1343)

(1138)

(975)

(841)

(729)

(634)

(554)

(489)

25 20.7

17.5

14.9

12.8

11.1

9.6

8.3

7.3

(1257)

(1062)

(907)

(779)

(671)

(580)

(504)

(443)

19.3

16.3

13.8

11.8

10.1

8.7

7.5

6.5

(1172)

(987)

(840)

(718)

(616)

(529)

(456)

(397)

17.9

15.0

12.7

10.8

9.2

7.9

6.7

5.8

(1087)

(913)

(773)

(657)

(561)

(478)

(409)

(353)

16.6

13.9

11.7

9.9

8.3

7.1

6.0

5.1

(1007)

(842)

(709)

(599)

(507)

(428)

(363)

(310)

30

35

40

45 A-ICE CORRECTION SUBTRACT: 1.4 % OR 84. ft/NM

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.2 % OR 74. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 89

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 170 – CF34-8E5 – T/O-2 FLAP 2 – V2/VS = 1.20 Altitude: Sea Level Grad % WEIGHT (lb) (ft/NM) SAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

30 and

35.0

29.9

25.9

22.7

20.0

17.7

15.8

14.2

below

(2124)

(1817)

(1574)

(1376)

(1213)

(1076)

(961)

(865)

32.6

27.8

24.1

21.1

18.5

16.4

14.6

13.1

(1980)

(1692)

(1464)

(1279)

(1125)

(995)

(886)

(797)

30.3

25.9

22.4

19.5

17.1

15.1

13.4

12.0

(1841)

(1572)

(1359)

(1185)

(1040)

(918)

(815)

(731)

35

40 28.1

24.0

20.7

18.0

15.8

13.9

12.3

11.0

(1708)

(1457)

(1258)

(1094)

(958)

(843)

(747)

(667)

45 26.0

22.1

19.1

16.5

14.4

12.7

11.2

9.9

(1578)

(1344)

(1158)

(1005)

(877)

(769)

(678)

(604)

50 A-ICE CORRECTION SUBTRACT: 0.0 % OR 0. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 90

Takeoff

REVISION 21

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.1 % OR 69. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 170 – CF34-8E5 – T/O-2 FLAP 2 – V2/VS = 1.20 Altitude: 2000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

25 and

32.2

27.5

23.8

20.8

18.3

16.2

14.4

12.9

below

(1956)

(1672)

(1446)

(1262)

(1111)

(982)

(874)

(785)

30.4

26.0

22.5

19.6

17.2

15.2

13.5

12.1

(1848)

(1578)

(1364)

(1189)

(1044)

(922)

(819)

(734)

28.3

24.1

20.8

18.1

15.9

14.0

12.4

11.0

(1718)

(1465)

(1264)

(1100)

(963)

(848)

(750)

(671)

30

35 26.3

22.4

19.3

16.7

14.6

12.8

11.3

10.1

(1595)

(1359)

(1171)

(1016)

(887)

(778)

(687)

(611)

40 24.3

20.7

17.8

15.4

13.4

11.7

10.3

9.1

(1475)

(1255)

(1078)

(933)

(812)

(709)

(623)

(553)

22.3

19.0

16.2

14.0

12.1

10.6

9.2

8.1

(1357)

(1151)

(986)

(850)

(737)

(641)

(560)

(494)

45

50 A-ICE CORRECTION SUBTRACT: 0.0 % OR 0. ft/NM

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.2 % OR 72. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 91

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 170 – CF34-8E5 – T/O-2 FLAP 2 – V2/VS = 1.20 Altitude: 4000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

20 and

29.5

25.2

21.7

19.0

16.6

14.7

13.0

11.6

below

(1791)

(1528)

(1321)

(1151)

(1010)

(891)

(790)

(707)

28.3

24.1

20.8

18.1

15.9

14.0

12.4

11.1

(1718)

(1465)

(1264)

(1100)

(964)

(848)

(751)

(671)

26.3

22.4

19.3

16.7

14.6

12.8

11.3

10.1

(1597)

(1361)

(1172)

(1017)

(888)

(779)

(687)

(612)

25

30 24.4

20.8

17.9

15.5

13.4

11.7

10.3

9.2

(1484)

(1262)

(1084)

(938)

(817)

(713)

(626)

(556)

35 22.6

19.2

16.4

14.2

12.3

10.7

9.3

8.2

(1374)

(1166)

(999)

(861)

(747)

(649)

(567)

(501)

20.8

17.6

15.0

12.9

11.2

9.6

8.4

7.3

(1263)

(1070)

(914)

(785)

(677)

(585)

(508)

(446)

19.0

16.1

13.7

11.7

10.0

8.6

7.4

6.5

(1157)

(976)

(829)

(709)

(608)

(522)

(450)

(392)

40

45

50 A-ICE CORRECTION SUBTRACT: 0.0 % OR 1. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 92

Takeoff

REVISION 21

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.2 % OR 75. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 170 – CF34-8E5 – T/O-2 FLAP 2 – V2/VS = 1.20 Altitude: 6000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

15 and

27.2

23.2

20.0

17.4

15.2

13.4

11.8

10.5

below

(1650)

(1407)

(1214)

(1055)

(923)

(811)

(717)

(639)

26.4

22.5

19.4

16.9

14.7

12.9

11.4

10.2

(1605)

(1368)

(1178)

(1023)

(894)

(785)

(692)

(617)

24.6

20.9

18.0

15.6

13.5

11.8

10.4

9.2

(1494)

(1270)

(1092)

(945)

(823)

(719)

(632)

(561)

20

25 22.8

19.4

16.6

14.3

12.4

10.8

9.4

8.3

(1386)

(1176)

(1008)

(869)

(754)

(656)

(574)

(507)

30 21.2

17.9

15.3

13.1

11.3

9.8

8.5

7.5

(1285)

(1087)

(929)

(798)

(689)

(596)

(518)

(454)

19.5

16.4

14.0

12.0

10.3

8.8

7.6

6.6

(1184)

(999)

(850)

(727)

(624)

(537)

(463)

(403)

17.9

15.0

12.7

10.8

9.2

7.9

6.7

5.8

(1085)

(911)

(772)

(656)

(560)

(478)

(409)

(354)

16.3

13.6

11.5

9.7

8.2

6.9

5.9

5.0

(990)

(828)

(697)

(589)

(498)

(421)

(357)

(305)

35

40

45

50 A-ICE CORRECTION SUBTRACT: 0.1 % OR 4. ft/NM

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.3 % OR 76. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 93

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 170 – CF34-8E5 – T/O-2 FLAP 2 – V2/VS = 1.20 Altitude: 8000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10 and

25.1

21.4

18.4

16.0

13.9

12.2

10.7

9.5

below

(1527)

(1301)

(1120)

(971)

(846)

(741)

(652)

(580)

24.8

21.1

18.2

15.7

13.7

12.0

10.6

9.4

(1507)

(1283)

(1103)

(956)

(833)

(729)

(641)

(569)

23.1

19.6

16.8

14.5

12.6

11.0

9.6

8.5

(1403)

(1192)

(1022)

(883)

(766)

(667)

(584)

(516)

15

20 21.4

18.1

15.5

13.3

11.5

10.0

8.7

7.6

(1302)

(1102)

(942)

(810)

(700)

(607)

(528)

(464)

25 19.9

16.8

14.3

12.2

10.5

9.1

7.8

6.8

(1207)

(1019)

(867)

(743)

(639)

(550)

(476)

(414)

18.3

15.4

13.1

11.1

9.5

8.1

7.0

6.0

(1112)

(936)

(793)

(675)

(577)

(493)

(423)

(367)

16.8

14.1

11.9

10.0

8.5

7.2

6.1

5.3

(1021)

(854)

(720)

(610)

(517)

(438)

(372)

(319)

15.4

12.8

10.7

9.0

7.6

6.3

5.3

4.5

(932)

(776)

(651)

(546)

(459)

(385)

(323)

(273)

30

35

40

45 A-ICE CORRECTION SUBTRACT: 0.7 % OR 45. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 94

Takeoff

REVISION 21

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.2 % OR 75. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 170 – CF34-8E5 – T/O-2 FLAP 2 – V2/VS = 1.20 Altitude: 10000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

47000

52000

57000

62000

67000

72000

77000

82000

10 and

23.1

19.6

16.8

14.5

12.6

11.0

9.6

8.5

below

(1400)

(1190)

(1021)

(882)

(766)

(668)

(585)

(517)

21.6

18.3

15.6

13.5

11.7

10.1

8.8

7.8

(1310)

(1111)

(950)

(818)

(708)

(614)

(535)

(471)

20.0

16.9

14.4

12.4

10.7

9.2

8.0

6.9

(1218)

(1029)

(877)

(752)

(647)

(558)

(483)

(422)

15

20 18.6

15.6

13.3

11.3

9.7

8.3

7.1

6.2

(1127)

(948)

(805)

(686)

(587)

(503)

(432)

(374)

25 17.1

14.3

12.1

10.2

8.7

7.4

6.3

5.4

(1038)

(868)

(733)

(621)

(527)

(448)

(381)

(327)

15.7

13.1

11.0

9.2

7.8

6.5

5.5

4.7

(951)

(794)

(666)

(561)

(472)

(397)

(334)

(283)

14.3

11.9

9.9

8.3

6.9

5.7

4.7

4.0

(869)

(720)

(600)

(501)

(418)

(347)

(287)

(240)

13.0

10.7

8.8

7.3

6.0

4.9

4.0

3.3

(787)

(647)

(535)

(441)

(363)

(297)

(241)

(197)

30

35

40

45 A-ICE CORRECTION SUBTRACT: 1.9 % OR 115. ft/NM

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.3 % OR 79. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 95

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 170 – CF34-8 ENGINES – CLB-1 VFS Altitude: Sea Level Grad % WEIGHT (lb) (ft/NM) ISA (°C)

47000

52000

57000

62000

67000

72000

77000

82000

38.9

33.3

28.9

25.5

22.7

20.3

18.2

16.5

(2364)

(2020)

(1757)

(1546)

(1378)

(1233)

(1106)

(1000)

38.8

33.2

28.9

25.4

22.6

20.3

18.2

16.4

(2360)

(2017)

(1754)

(1544)

(1376)

(1231)

(1104)

(998)

38.6

33.0

28.7

25.3

22.5

20.2

18.1

16.3

(2347)

(2005)

(1744)

(1535)

(1368)

(1225)

(1098)

(993)

-30

-20

-10 38.1

32.5

28.3

24.9

22.2

19.9

17.8

16.1

(2312)

(1977)

(1720)

(1514)

(1349)

(1206)

(1082)

(978)

0 37.8

32.3

28.1

24.8

22.1

19.7

17.7

16.0

(2299)

(1964)

(1708)

(1504)

(1340)

(1199)

(1075)

(971)

33.1

28.3

24.6

21.6

19.2

17.2

15.3

13.8

(2012)

(1718)

(1494)

(1313)

(1169)

(1042)

(932)

(840)

28.7

24.5

21.2

18.6

16.5

14.7

13.1

11.7

(1743)

(1486)

(1290)

(1132)

(1004)

(892)

(793)

(711)

10

20

30 A-ICE CORRECTION SUBTRACT: 0.9 % OR 56. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 96

Takeoff

REVISION 21

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 5.9 % OR 360. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 170 – CF34-8 ENGINES – CLB-1 VFS Altitude: 2000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

47000

52000

57000

62000

67000

72000

77000

82000

36.2

31.1

27.1

23.9

21.2

19.0

17.0

15.4

(2201)

(1886)

(1645)

(1453)

(1289)

(1151)

(1035)

(937)

36.2

31.0

27.0

23.9

21.2

18.9

17.0

15.4

(2196)

(1883)

(1643)

(1450)

(1287)

(1149)

(1033)

(936)

36.1

30.9

26.9

23.8

21.1

18.8

16.9

15.3

(2190)

(1876)

(1635)

(1444)

(1281)

(1144)

(1028)

(931)

-30

-20

-10 35.9

30.7

26.8

23.7

21.0

18.8

16.8

15.2

(2181)

(1867)

(1627)

(1437)

(1276)

(1139)

(1023)

(926)

0 35.4

30.3

26.4

23.3

20.7

18.5

16.6

15.0

(2152)

(1841)

(1603)

(1415)

(1256)

(1121)

(1007)

(911)

30.9

26.5

23.0

20.3

18.0

16.0

14.3

12.9

(1879)

(1609)

(1400)

(1234)

(1092)

(971)

(868)

(783)

26.8

22.9

19.9

17.5

15.4

13.7

12.2

10.9

(1626)

(1391)

(1208)

(1063)

(936)

(829)

(738)

(663)

10

20

30 A-ICE CORRECTION SUBTRACT: 0.8 % OR 47. ft/NM

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 5.4 % OR 331. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 97

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 170 – CF34-8 ENGINES – CLB-1 VFS Altitude: 4000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

47000

52000

57000

62000

67000

72000

77000

82000

33.8

29.0

25.4

22.3

19.8

17.7

15.9

14.3

(2051)

(1763)

(1541)

(1357)

(1201)

(1073)

(966)

(869)

33.7

29.0

25.3

22.3

19.7

17.6

15.9

14.3

(2047)

(1760)

(1538)

(1355)

(1199)

(1071)

(964)

(868)

33.6

28.9

25.2

22.2

19.6

17.5

15.8

14.2

(2042)

(1754)

(1531)

(1348)

(1193)

(1065)

(960)

(865)

-30

-20

-10 33.4

28.7

25.1

22.1

19.5

17.5

15.7

14.2

(2032)

(1745)

(1524)

(1342)

(1187)

(1060)

(955)

(860)

0 33.0

28.4

24.7

21.8

19.3

17.2

15.5

14.0

(2007)

(1723)

(1503)

(1324)

(1172)

(1046)

(942)

(848)

28.9

24.8

21.6

18.9

16.7

14.8

13.3

11.9

(1753)

(1505)

(1312)

(1150)

(1013)

(900)

(807)

(723)

25.0

21.4

18.6

16.3

14.3

12.6

11.3

10.0

(1518)

(1301)

(1132)

(989)

(868)

(768)

(685)

(610)

10

20

30 A-ICE CORRECTION SUBTRACT: 0.7 % OR 42. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 98

Takeoff

REVISION 21

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 4.9 % OR 295. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 170 – CF34-8 ENGINES – CLB-1 VFS Altitude: 6000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

47000

52000

57000

62000

67000

72000

77000

82000

31.4

27.1

23.6

20.7

18.3

16.4

14.7

13.2

(1908)

(1644)

(1433)

(1257)

(1114)

(995)

(892)

(804)

31.3

27.0

23.5

20.6

18.3

16.3

14.7

13.2

(1904)

(1640)

(1430)

(1254)

(1111)

(993)

(890)

(802)

31.3

26.9

23.5

20.6

18.3

16.3

14.6

13.2

(1900)

(1637)

(1427)

(1251)

(1109)

(990)

(888)

(800)

-30

-20

-10 31.2

26.9

23.4

20.5

18.2

16.3

14.6

13.1

(1894)

(1631)

(1422)

(1247)

(1105)

(987)

(884)

(796)

0 30.8

26.5

23.1

20.3

18.0

16.0

14.4

12.9

(1873)

(1613)

(1405)

(1232)

(1091)

(974)

(872)

(785)

26.9

23.1

20.1

17.6

15.5

13.8

12.3

11.0

(1635)

(1406)

(1221)

(1067)

(942)

(837)

(746)

(667)

23.3

20.0

17.3

15.0

13.2

11.7

10.3

9.2

(1414)

(1213)

(1049)

(912)

(801)

(709)

(627)

(556)

10

20

30 A-ICE CORRECTION SUBTRACT: 0.6 % OR 39. ft/NM

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 4.4 % OR 267. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 99

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 170 – CF34-8 ENGINES – CLB-1 VFS Altitude: 8000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

47000

52000

57000

62000

67000

72000

77000

82000

29.1

25.1

21.8

19.2

17.0

15.1

13.5

12.1

(1770)

(1527)

(1323)

(1163)

(1033)

(916)

(821)

(737)

29.1

25.1

21.7

19.1

17.0

15.1

13.5

12.1

(1766)

(1524)

(1320)

(1161)

(1031)

(914)

(819)

(735)

29.0

25.0

21.7

19.1

16.9

15.0

13.5

12.1

(1763)

(1521)

(1318)

(1159)

(1029)

(912)

(817)

(734)

-30

-20

-10 29.0

25.0

21.6

19.0

16.9

15.0

13.4

12.1

(1759)

(1518)

(1315)

(1156)

(1026)

(910)

(815)

(732)

0 28.7

24.7

21.4

18.8

16.7

14.8

13.3

11.9

(1742)

(1502)

(1301)

(1143)

(1015)

(899)

(805)

(723)

25.1

21.6

18.6

16.3

14.4

12.7

11.3

10.1

(1526)

(1313)

(1132)

(992)

(877)

(773)

(688)

(614)

21.7

18.6

16.0

13.9

12.2

10.7

9.5

8.4

(1131)

(972)

(846)

(743)

(649)

(574)

(509)

10

20

30 (1318)

A-ICE CORRECTION SUBTRACT: 2.1 % OR 129. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 100

Takeoff

REVISION 21

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 4.0 % OR 245. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 170 – CF34-8 ENGINES – CLB-1 VFS Altitude: 10000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

47000

52000

57000

62000

67000

72000

77000

82000

27.1

23.2

20.1

17.7

15.6

13.8

12.4

11.1

(1644)

(1409)

(1223)

(1077)

(948)

(839)

(751)

(672)

27.1

23.2

20.1

17.7

15.6

13.8

12.3

11.0

(1643)

(1407)

(1220)

(1074)

(946)

(838)

(750)

(671)

27.0

23.1

20.0

17.6

15.6

13.8

12.3

11.0

(1639)

(1404)

(1217)

(1072)

(944)

(837)

(749)

(670)

-30

-20

-10 26.9

23.0

20.0

17.6

15.5

13.8

12.3

11.0

(1634)

(1400)

(1214)

(1069)

(943)

(835)

(747)

(668)

0 26.6

22.8

19.8

17.4

15.4

13.6

12.2

10.9

(1619)

(1386)

(1202)

(1059)

(933)

(827)

(740)

(662)

23.4

20.0

17.3

15.2

13.3

11.7

10.4

9.3

(1423)

(1215)

(1050)

(921)

(807)

(711)

(633)

(562)

20.3

17.2

14.8

12.9

11.2

9.8

8.7

7.6

(1047)

(900)

(785)

(683)

(597)

(527)

(464)

10

20

30 (1233)

A-ICE CORRECTION SUBTRACT: 2.0 % OR 123. ft/NM

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 3.7 % OR 226. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 101

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 170 – CF34-8 ENGINES – CLB-1 250 KIAS Altitude: Sea Level Grad % WEIGHT (lb) (ft/NM) ISA (°C)

47000

52000

57000

62000

67000

72000

77000

82000

27.9

24.8

22.3

20.3

18.5

17.0

15.6

14.5

(1693)

(1506)

(1356)

(1231)

(1127)

(1033)

(950)

(878)

27.8

24.7

22.3

20.2

18.5

17.0

15.6

14.4

(1688)

(1503)

(1352)

(1228)

(1124)

(1030)

(948)

(876)

27.7

24.6

22.2

20.1

18.4

16.9

15.5

14.4

(1681)

(1496)

(1347)

(1223)

(1119)

(1026)

(944)

(872)

-30

-20

-10 27.2

24.2

21.8

19.8

18.1

16.6

15.3

14.1

(1655)

(1473)

(1326)

(1204)

(1102)

(1010)

(929)

(858)

0 27.0

24.1

21.7

19.7

18.0

16.5

15.2

14.0

(1642)

(1462)

(1316)

(1195)

(1093)

(1002)

(922)

(851)

23.3

20.7

18.7

16.9

15.5

14.2

13.0

12.0

(1413)

(1258)

(1133)

(1029)

(941)

(861)

(790)

(729)

19.6

17.4

15.7

14.2

13.0

11.9

10.9

10.0

(1190)

(1059)

(953)

(865)

(790)

(721)

(660)

(607)

10

20

30 A-ICE CORRECTION SUBTRACT: 0.7 % OR 41. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 102

Takeoff

REVISION 21

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 4.6 % OR 279. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 170 – CF34-8 ENGINES – CLB-1 250 KIAS Altitude: 2000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

47000

52000

57000

62000

67000

72000

77000

82000

26.0

23.2

20.9

19.0

17.4

15.9

14.6

13.5

(1582)

(1410)

(1271)

(1155)

(1054)

(966)

(889)

(822)

26.0

23.2

20.9

19.0

17.3

15.9

14.6

13.5

(1579)

(1407)

(1268)

(1153)

(1052)

(964)

(887)

(821)

25.8

23.0

20.8

18.9

17.2

15.8

14.5

13.4

(1569)

(1399)

(1261)

(1146)

(1046)

(958)

(882)

(816)

-30

-20

-10 25.7

22.9

20.6

18.8

17.1

15.7

14.4

13.4

(1560)

(1391)

(1253)

(1140)

(1040)

(952)

(877)

(811)

0 25.3

22.6

20.3

18.5

16.9

15.5

14.2

13.2

(1538)

(1371)

(1236)

(1124)

(1025)

(939)

(864)

(799)

21.6

19.2

17.3

15.8

14.4

13.1

12.1

11.1

(1310)

(1168)

(1053)

(957)

(872)

(797)

(732)

(676)

18.2

16.2

14.6

13.3

12.1

11.0

10.1

9.3

(985)

(888)

(806)

(733)

(668)

(612)

(563)

10

20

30 (1105)

A-ICE CORRECTION SUBTRACT: 0.6 % OR 39. ft/NM

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 4.5 % OR 274. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 103

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 170 – CF34-8 ENGINES – CLB-1 250 KIAS Altitude: 4000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

47000

52000

57000

62000

67000

72000

77000

82000

24.2

21.6

19.5

17.7

16.1

14.8

13.6

12.5

(1467)

(1310)

(1182)

(1072)

(977)

(896)

(826)

(761)

24.1

21.5

19.4

17.6

16.1

14.7

13.6

12.5

(1464)

(1307)

(1180)

(1070)

(975)

(894)

(824)

(759)

24.0

21.4

19.3

17.5

16.0

14.6

13.5

12.4

(1457)

(1300)

(1173)

(1065)

(970)

(890)

(820)

(755)

-30

-20

-10 23.9

21.3

19.2

17.4

15.9

14.6

13.4

12.4

(1449)

(1294)

(1167)

(1059)

(965)

(885)

(815)

(751)

0 23.5

21.0

19.0

17.2

15.7

14.4

13.2

12.2

(1429)

(1276)

(1151)

(1044)

(952)

(872)

(804)

(740)

20.0

17.9

16.1

14.6

13.3

12.2

11.2

10.3

(1216)

(1086)

(980)

(888)

(808)

(739)

(680)

(624)

16.8

15.0

13.5

12.2

11.1

10.1

9.3

8.5

(909)

(820)

(741)

(673)

(614)

(563)

(515)

10

20

30 (1018)

A-ICE CORRECTION SUBTRACT: 0.6 % OR 36. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 104

Takeoff

REVISION 21

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 4.3 % OR 259. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 170 – CF34-8 ENGINES – CLB-1 250 KIAS Altitude: 6000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

47000

52000

57000

62000

67000

72000

77000

82000

22.3

19.9

18.0

16.3

14.8

13.6

12.5

11.5

(1354)

(1211)

(1091)

(988)

(902)

(827)

(759)

(699)

22.2

19.9

17.9

16.2

14.8

13.6

12.5

11.5

(1350)

(1207)

(1088)

(985)

(899)

(825)

(757)

(697)

22.2

19.8

17.9

16.2

14.8

13.5

12.4

11.4

(1346)

(1204)

(1085)

(983)

(896)

(823)

(755)

(695)

-30

-20

-10 22.1

19.7

17.8

16.1

14.7

13.5

12.4

11.4

(1342)

(1199)

(1081)

(979)

(893)

(820)

(752)

(692)

0 21.8

19.5

17.5

15.9

14.5

13.3

12.2

11.2

(1322)

(1182)

(1065)

(965)

(880)

(808)

(741)

(682)

18.5

16.5

14.9

13.5

12.3

11.2

10.3

9.4

(1122)

(1003)

(903)

(817)

(744)

(681)

(623)

(572)

15.4

13.7

12.4

11.2

10.1

9.3

8.4

7.7

(834)

(750)

(677)

(615)

(562)

(512)

(467)

10

20

30 (933)

A-ICE CORRECTION SUBTRACT: 0.5 % OR 32. ft/NM

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 3.8 % OR 230. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 105

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 170 – CF34-8 ENGINES – CLB-1 250 KIAS Altitude: 8000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

47000

52000

57000

62000

67000

72000

77000

82000

20.6

18.4

16.6

15.0

13.7

12.5

11.5

10.6

(1253)

(1120)

(1007)

(913)

(834)

(762)

(699)

(644)

20.6

18.4

16.5

15.0

13.7

12.5

11.5

10.6

(1250)

(1117)

(1005)

(911)

(832)

(760)

(697)

(643)

20.5

18.4

16.5

15.0

13.7

12.5

11.5

10.6

(1247)

(1115)

(1002)

(909)

(830)

(758)

(696)

(641)

-30

-20

-10 20.4

18.3

16.4

14.9

13.6

12.4

11.4

10.5

(1242)

(1110)

(998)

(905)

(827)

(755)

(693)

(638)

0 20.2

18.0

16.2

14.7

13.4

12.3

11.2

10.4

(1225)

(1095)

(985)

(893)

(815)

(745)

(683)

(629)

17.0

15.2

13.7

12.4

11.3

10.3

9.4

8.6

(1035)

(925)

(831)

(753)

(686)

(625)

(571)

(524)

14.1

12.6

11.3

10.2

9.3

8.4

7.7

7.0

(765)

(686)

(620)

(563)

(511)

(465)

(425)

10

20

30 (857)

A-ICE CORRECTION SUBTRACT: 1.7 % OR 102. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 106

Takeoff

REVISION 21

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 3.5 % OR 211. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 170 – CF34-8 ENGINES – CLB-1 250 KIAS Altitude: 10000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

47000

52000

57000

62000

67000

72000

77000

82000

18.9

16.9

15.2

13.8

12.5

11.4

10.5

9.6

(1149)

(1024)

(922)

(837)

(761)

(695)

(638)

(586)

18.9

16.8

15.1

13.7

12.5

11.4

10.5

9.6

(1146)

(1021)

(919)

(835)

(759)

(693)

(636)

(584)

18.8

16.8

15.1

13.7

12.5

11.4

10.5

9.6

(1143)

(1019)

(917)

(832)

(757)

(691)

(635)

(582)

-30

-20

-10 18.8

16.7

15.1

13.7

12.4

11.4

10.4

9.6

(1140)

(1016)

(915)

(830)

(755)

(690)

(633)

(581)

0 18.5

16.5

14.9

13.5

12.3

11.2

10.3

9.4

(1126)

(1004)

(904)

(820)

(746)

(681)

(625)

(574)

15.7

14.0

12.6

11.4

10.3

9.4

8.6

7.9

(953)

(849)

(763)

(692)

(627)

(571)

(523)

(477)

12.9

11.5

10.3

9.3

8.4

7.6

6.9

6.3

(696)

(624)

(564)

(509)

(462)

(421)

(382)

10

20

30 (783)

A-ICE CORRECTION SUBTRACT: 1.6 % OR 99. ft/NM CLB-2 CORRECTION SUBTRACT: 3.0 % OR 181. ft/NM

AOM-1502-003

"

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 107

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT - ALL ENGINES OPERATING !EMBRAER 175 Models

The climb gradient tables show the climb gradients in percentage and in ft/NM for several weights, temperatures and pressure altitudes. These tables are published in the following configurations:

GRADIENTS FOR TAKEOFF THRUST The gradients were obtained for: – A speed equal to V2 + 10 KIAS; – FLAP 2; – V2/VS ratio equal to the minimum of the range; – Anti-Ice OFF; – ECS ON; – Landing Gear Up; – Wings Leveled; – Temperatures in Celsius Degrees.

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 108

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REVISION 21

AOM-1502-003

Corrections in the climb gradient for Anti-Ice ON and Flaps 4 are also provided in the footer of each table.

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

GRADIENTS FOR CLIMB THRUST The gradients were obtained for: – A speed equal to VFS KIAS and 250 KIAS; – FLAP UP; – CLB-1 Thrust Rating; – Anti-Ice OFF; – ECS ON; – Landing Gear Up; – Wings Leveled; – Temperatures in ISA Deviation.

AOM-1502-003

Corrections in the climb gradient for Anti-Ice ON and CLB-2 thrust rating are also provided in the footer of each table.

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 109

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.17 Altitude: Sea Level Grad % WEIGHT (lb) (ft/NM) SAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

30 and

34.6

29.9

26.1

23.0

20.4

18.2

16.3

14.7

below

(2104)

(1817)

(1585)

(1395)

(1237)

(1103)

(991)

(893)

31.7

27.4

23.9

21.0

18.5

16.5

14.8

13.3

(1926)

(1663)

(1449)

(1273)

(1126)

(1002)

(897)

(806)

28.9

24.9

21.7

19.0

16.7

14.8

13.2

11.9

(1755)

(1512)

(1315)

(1153)

(1016)

(901)

(804)

(720)

35

40 26.1

22.5

19.5

17.0

15.0

13.2

11.7

10.5

(1586)

(1364)

(1183)

(1034)

(908)

(801)

(712)

(635)

45 23.4

20.1

17.3

15.1

13.2

11.6

10.2

9.1

(1420)

(1218)

(1053)

(916)

(801)

(702)

(621)

(551)

50 A-ICE CORRECTION SUBTRACT: 0.0 % OR 0. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 110

Takeoff

REVISION 21

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.1 % OR 65. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.17 Altitude: 2000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

25 and

32.5

28.1

24.6

21.6

19.2

17.1

15.4

13.9

below

(1975)

(1707)

(1491)

(1314)

(1165)

(1039)

(933)

(841)

30.8

26.6

23.2

20.3

18.0

16.0

14.3

12.8

(1872)

(1616)

(1407)

(1236)

(1091)

(969)

(868)

(779)

28.4

24.5

21.3

18.6

16.4

14.5

12.9

11.6

(1724)

(1485)

(1291)

(1130)

(995)

(881)

(785)

(702)

30

35 25.7

22.1

19.2

16.7

14.7

12.9

11.5

10.2

(1561)

(1342)

(1163)

(1015)

(890)

(785)

(698)

(622)

40 23.2

19.9

17.2

15.0

13.0

11.4

10.1

8.9

(1412)

(1210)

(1045)

(908)

(792)

(694)

(612)

(540)

20.9

17.8

15.3

13.2

11.5

10.0

8.7

7.7

(1268)

(1083)

(931)

(804)

(697)

(606)

(530)

(464)

45

50 A-ICE CORRECTION SUBTRACT: 0.0 % OR 0. ft/NM

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.0 % OR 63. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 111

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.17 Altitude: 4000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

20 and

29.9

25.8

22.5

19.8

17.5

15.6

14.0

12.6

below

(1817)

(1568)

(1369)

(1204)

(1066)

(948)

(849)

(763)

28.8

24.9

21.7

19.1

16.8

15.0

13.4

12.0

(1750)

(1511)

(1317)

(1157)

(1023)

(909)

(813)

(730)

27.0

23.3

20.2

17.7

15.6

13.8

12.3

11.0

(1641)

(1414)

(1229)

(1076)

(948)

(839)

(747)

(667)

25

30 25.0

21.5

18.6

16.2

14.2

12.5

11.1

9.9

(1517)

(1303)

(1130)

(986)

(864)

(760)

(674)

(598)

35 22.9

19.6

16.9

14.7

12.8

11.2

9.9

8.7

(1391)

(1191)

(1027)

(891)

(777)

(679)

(598)

(527)

20.9

17.8

15.3

13.2

11.4

9.9

8.7

7.6

(1270)

(1083)

(929)

(801)

(694)

(602)

(526)

(460)

19.0

16.1

13.7

11.8

10.1

8.7

7.5

6.5

(1153)

(978)

(835)

(715)

(614)

(528)

(457)

(394)

40

45

50 A-ICE CORRECTION SUBTRACT: 0.0 % OR 1. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 112

Takeoff

REVISION 21

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.1 % OR 65. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.17 Altitude: 6000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

15 and

27.6

23.8

20.8

18.2

16.1

14.3

12.8

11.4

below

(1677)

(1448)

(1262)

(1107)

(978)

(867)

(775)

(694)

26.9

23.2

20.2

17.7

15.7

13.9

12.4

11.1

(1636)

(1411)

(1229)

(1078)

(950)

(842)

(752)

(673)

25.3

21.8

18.9

16.6

14.6

12.9

11.4

10.2

(1536)

(1322)

(1149)

(1005)

(884)

(781)

(695)

(621)

20

25 23.7

20.3

17.6

15.4

13.5

11.8

10.5

9.3

(1437)

(1234)

(1070)

(933)

(817)

(719)

(638)

(566)

30 22.0

18.9

16.3

14.2

12.3

10.8

9.5

8.4

(1338)

(1146)

(990)

(859)

(749)

(655)

(577)

(509)

20.4

17.4

15.0

12.9

11.2

9.7

8.5

7.4

(1240)

(1058)

(909)

(784)

(679)

(590)

(516)

(452)

18.8

16.0

13.7

11.7

10.1

8.7

7.5

6.5

(1145)

(971)

(829)

(711)

(612)

(527)

(457)

(396)

17.4

14.7

12.4

10.6

9.0

7.7

6.6

5.7

(1055)

(890)

(755)

(643)

(548)

(468)

(401)

(344)

35

40

45

50 A-ICE CORRECTION SUBTRACT: 0.1 % OR 4. ft/NM

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.1 % OR 68. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 113

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.17 Altitude: 8000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10 and

25.5

22.0

19.1

16.8

14.8

13.0

11.6

10.4

below

(1551)

(1336)

(1162)

(1018)

(896)

(792)

(705)

(629)

25.2

21.7

18.9

16.5

14.5

12.8

11.4

10.2

(1531)

(1319)

(1147)

(1004)

(883)

(780)

(694)

(619)

23.7

20.4

17.7

15.4

13.5

11.9

10.6

9.4

(1439)

(1237)

(1073)

(937)

(821)

(723)

(641)

(570)

15

20 22.2

19.0

16.5

14.3

12.5

11.0

9.7

8.6

(1347)

(1156)

(1000)

(870)

(760)

(667)

(588)

(520)

25 20.7

17.7

15.3

13.2

11.5

10.0

8.8

7.8

(1257)

(1076)

(927)

(804)

(699)

(610)

(536)

(471)

19.2

16.4

14.1

12.1

10.5

9.1

8.0

6.9

(1168)

(996)

(855)

(738)

(638)

(554)

(483)

(422)

17.8

15.1

12.9

11.1

9.5

8.2

7.1

6.2

(1082)

(918)

(784)

(673)

(578)

(498)

(431)

(373)

16.5

13.9

11.8

10.1

8.6

7.3

6.3

5.4

(1000)

(845)

(718)

(611)

(522)

(445)

(381)

(326)

30

35

40

45 A-ICE CORRECTION SUBTRACT: 0.7 % OR 40. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 114

Takeoff

REVISION 21

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.1 % OR 68. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 175 – CF34-8E5 – T/O-1 FLAP 2 – V2/VS = 1.17 Altitude: 10000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10 and

22.9

19.8

17.2

15.0

13.2

11.6

10.3

9.2

below

(1394)

(1200)

(1042)

(911)

(800)

(705)

(626)

(557)

22.1

18.9

16.4

14.3

12.5

10.9

9.7

8.6

(1340)

(1150)

(995)

(866)

(757)

(664)

(587)

(520)

20.6

17.7

15.3

13.3

11.6

10.1

8.9

7.9

(1254)

(1074)

(927)

(805)

(702)

(615)

(541)

(477)

15

20 19.4

16.5

14.2

12.3

10.7

9.3

8.1

7.1

(1177)

(1004)

(864)

(747)

(648)

(564)

(494)

(433)

25 18.1

15.4

13.2

11.4

9.8

8.5

7.4

6.4

(1099)

(935)

(801)

(689)

(594)

(514)

(447)

(389)

16.8

14.3

12.2

10.4

8.9

7.7

6.6

5.7

(1021)

(866)

(738)

(632)

(542)

(465)

(401)

(345)

15.6

13.1

11.1

9.5

8.1

6.9

5.9

5.0

(945)

(797)

(676)

(575)

(490)

(417)

(357)

(304)

14.4

12.1

10.2

8.6

7.2

6.1

5.2

4.3

(872)

(732)

(617)

(521)

(440)

(370)

(313)

(263)

30

35

40

45 A-ICE CORRECTION SUBTRACT: 1.3 % OR 76. ft/NM

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.2 % OR 72. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 115

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 175 – CF34-8E5 – T/O-2 FLAP 2 – V2/VS = 1.17 Altitude: Sea Level Grad % WEIGHT (lb) (ft/NM) SAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

30 and

30.9

26.7

23.3

20.5

18.1

16.1

14.5

13.0

below

(1876)

(1621)

(1414)

(1244)

(1101)

(981)

(879)

(790)

28.8

24.8

21.6

19.0

16.8

14.9

13.3

11.9

(1748)

(1508)

(1314)

(1154)

(1019)

(904)

(809)

(725)

26.7

23.0

20.0

17.6

15.5

13.7

12.2

10.9

(1624)

(1399)

(1217)

(1067)

(940)

(832)

(741)

(663)

35

40 24.8

21.3

18.5

16.2

14.2

12.5

11.1

9.9

(1505)

(1295)

(1124)

(983)

(863)

(761)

(676)

(602)

45 22.9

19.6

17.0

14.8

13.0

11.4

10.1

8.9

(1388)

(1192)

(1032)

(899)

(787)

(692)

(612)

(542)

50 A-ICE CORRECTION SUBTRACT: 0.0 % OR 0. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 116

Takeoff

REVISION 21

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.1 % OR 69. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 175 – CF34-8E5 – T/O-2 FLAP 2 – V2/VS = 1.17 Altitude: 2000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

25 and

28.4

24.5

21.4

18.7

16.6

14.7

13.1

11.8

below

(1727)

(1490)

(1298)

(1139)

(1005)

(892)

(797)

(714)

26.8

23.1

20.1

17.6

15.5

13.8

12.3

11.0

(1630)

(1405)

(1222)

(1071)

(943)

(835)

(745)

(666)

24.9

21.4

18.6

16.3

14.3

12.6

11.2

10.0

(1514)

(1302)

(1131)

(988)

(868)

(765)

(680)

(606)

30

35 23.1

19.9

17.2

15.0

13.1

11.5

10.2

9.0

(1404)

(1206)

(1044)

(910)

(797)

(700)

(620)

(549)

40 21.3

18.3

15.8

13.7

12.0

10.5

9.2

8.1

(1296)

(1110)

(959)

(833)

(726)

(635)

(559)

(493)

19.6

16.7

14.4

12.4

10.8

9.4

8.2

7.2

(1189)

(1016)

(874)

(756)

(656)

(570)

(499)

(437)

45

50 A-ICE CORRECTION SUBTRACT: 0.0 % OR 0. ft/NM

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.2 % OR 71. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 117

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 175 – CF34-8E5 – T/O-2 FLAP 2 – V2/VS = 1.17 Altitude: 4000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

20 and

26.0

22.4

19.5

17.0

15.0

13.3

11.8

10.5

below

(1579)

(1360)

(1183)

(1035)

(911)

(806)

(717)

(640)

24.9

21.4

18.6

16.3

14.3

12.6

11.2

10.0

(1514)

(1302)

(1131)

(988)

(868)

(766)

(681)

(606)

23.1

19.9

17.2

15.0

13.1

11.5

10.2

9.1

(1406)

(1207)

(1045)

(911)

(797)

(701)

(620)

(550)

25

30 21.5

18.4

15.9

13.8

12.0

10.5

9.3

8.2

(1304)

(1117)

(965)

(838)

(730)

(639)

(563)

(496)

35 19.8

16.9

14.6

12.6

10.9

9.5

8.3

7.3

(1204)

(1029)

(885)

(766)

(665)

(579)

(507)

(444)

18.2

15.5

13.3

11.4

9.9

8.5

7.4

6.5

(1105)

(941)

(807)

(695)

(599)

(518)

(451)

(392)

16.6

14.1

12.0

10.3

8.8

7.6

6.5

5.6

(1008)

(855)

(729)

(624)

(535)

(459)

(396)

(341)

40

45

50 A-ICE CORRECTION SUBTRACT: 0.0 % OR 1. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 118

Takeoff

REVISION 21

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.2 % OR 73. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 175 – CF34-8E5 – T/O-2 FLAP 2 – V2/VS = 1.17 Altitude: 6000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

15 and

23.9

20.6

17.9

15.6

13.7

12.0

10.7

9.5

below

(1453)

(1250)

(1084)

(946)

(830)

(731)

(648)

(576)

23.3

20.0

17.3

15.1

13.2

11.6

10.3

9.1

(1412)

(1214)

(1052)

(917)

(803)

(706)

(625)

(554)

21.6

18.5

16.0

13.9

12.1

10.6

9.4

8.3

(1312)

(1125)

(971)

(844)

(736)

(644)

(568)

(501)

20

25 20.0

17.1

14.7

12.7

11.1

9.6

8.4

7.4

(1216)

(1039)

(894)

(773)

(671)

(585)

(513)

(450)

30 18.5

15.8

13.5

11.6

10.1

8.7

7.6

6.6

(1124)

(957)

(821)

(707)

(610)

(528)

(460)

(400)

17.0

14.4

12.3

10.6

9.1

7.8

6.7

5.8

(1033)

(876)

(748)

(641)

(550)

(472)

(408)

(351)

15.5

13.1

11.1

9.5

8.1

6.9

5.9

5.0

(942)

(796)

(675)

(575)

(489)

(417)

(357)

(304)

14.1

11.8

10.0

8.4

7.1

6.0

5.1

4.3

(856)

(719)

(606)

(511)

(431)

(363)

(307)

(258)

35

40

45

50 A-ICE CORRECTION SUBTRACT: 0.1 % OR 4. ft/NM

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.2 % OR 74. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 119

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 175 – CF34-8E5 – T/O-2 FLAP 2 – V2/VS = 1.17 Altitude: 8000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10 and

22.1

19.0

16.4

14.3

12.5

11.0

9.7

8.6

below

(1343)

(1153)

(997)

(868)

(758)

(665)

(587)

(519)

21.8

18.7

16.2

14.1

12.3

10.8

9.5

8.4

(1325)

(1136)

(983)

(854)

(746)

(654)

(576)

(509)

20.3

17.3

14.9

12.9

11.2

9.8

8.6

7.6

(1231)

(1053)

(907)

(786)

(683)

(596)

(522)

(459)

15

20 18.8

16.0

13.7

11.8

10.2

8.9

7.7

6.7

(1139)

(971)

(833)

(718)

(621)

(538)

(469)

(409)

25 17.3

14.7

12.6

10.8

9.3

8.0

6.9

6.0

(1053)

(894)

(764)

(656)

(563)

(485)

(420)

(362)

15.9

13.5

11.4

9.8

8.3

7.1

6.1

5.2

(967)

(818)

(695)

(592)

(506)

(432)

(370)

(317)

14.6

12.2

10.3

8.8

7.4

6.3

5.3

4.5

(884)

(743)

(628)

(531)

(449)

(379)

(321)

(271)

13.2

11.1

9.3

7.8

6.5

5.4

4.5

3.8

(804)

(672)

(563)

(472)

(395)

(329)

(275)

(228)

30

35

40

45 A-ICE CORRECTION SUBTRACT: 0.7 % OR 40. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 120

Takeoff

REVISION 21

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.2 % OR 73. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING TAKEOFF THRUST EMBRAER 175 – CF34-8E5 – T/O-2 FLAP 2 – V2/VS = 1.17 Altitude: 10000 ft Grad % WEIGHT (lb) (ft/NM) SAT (°C)

51000

56000

61000

66000

71000

76000

81000

86000

10 and

20.2

17.3

14.9

12.9

11.3

9.8

8.6

7.6

below

(1229)

(1051)

(906)

(786)

(683)

(596)

(523)

(460)

18.9

16.1

13.8

12.0

10.4

9.0

7.9

6.9

(1147)

(979)

(841)

(726)

(628)

(546)

(476)

(416)

17.5

14.9

12.7

10.9

9.4

8.1

7.0

6.1

(1063)

(904)

(773)

(664)

(572)

(493)

(427)

(369)

15

20 16.2

13.7

11.6

9.9

8.5

7.3

6.2

5.3

(981)

(830)

(706)

(603)

(515)

(440)

(378)

(324)

25 14.8

12.5

10.5

8.9

7.6

6.4

5.4

4.6

(899)

(756)

(639)

(542)

(459)

(388)

(330)

(279)

13.5

11.3

9.5

8.0

6.7

5.6

4.7

3.9

(821)

(688)

(578)

(485)

(407)

(341)

(285)

(237)

12.3

10.2

8.5

7.1

5.9

4.8

4.0

3.2

(746)

(620)

(516)

(430)

(356)

(293)

(241)

(196)

11.1

9.1

7.5

6.2

5.0

4.1

3.3

2.6

(671)

(553)

(455)

(374)

(305)

(246)

(197)

(155)

30

35

40

45 A-ICE CORRECTION SUBTRACT: 1.7 % OR 104. ft/NM

AOM-1502-003

FLAP 4 CORRECTION SUBTRACT: 1.3 % OR 77. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 121

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 175 – CF34-8 ENGINES – CLB-1 VFS Altitude: Sea Level Grad % WEIGHT (lb) (ft/NM) ISA (°C)

51000

56000

61000

66000

71000

76000

81000

86000

34.2

29.6

26.0

23.1

20.7

18.5

16.7

15.2

(2079)

(1798)

(1581)

(1406)

(1256)

(1126)

(1015)

(921)

34.2

29.6

26.0

23.1

20.6

18.5

16.7

15.1

(2075)

(1795)

(1579)

(1404)

(1254)

(1124)

(1013)

(919)

34.0

29.4

25.8

23.0

20.5

18.4

16.6

15.1

(2063)

(1785)

(1570)

(1396)

(1247)

(1118)

(1008)

(915)

-30

-20

-10 33.5

29.0

25.5

22.7

20.2

18.1

16.3

14.8

(2034)

(1760)

(1548)

(1376)

(1228)

(1101)

(992)

(901)

0 33.3

28.8

25.3

22.5

20.1

18.0

16.2

14.7

(2021)

(1748)

(1537)

(1367)

(1221)

(1094)

(986)

(894)

29.1

25.2

22.1

19.6

17.5

15.6

14.0

12.7

(1768)

(1528)

(1343)

(1192)

(1061)

(949)

(852)

(771)

25.2

21.7

19.0

16.9

15.0

13.3

11.9

10.7

(1529)

(1320)

(1157)

(1025)

(908)

(808)

(721)

(649)

10

20

30 A-ICE CORRECTION SUBTRACT: 0.8 % OR 49. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 122

Takeoff

REVISION 21

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 5.2 % OR 318. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 175 – CF34-8 ENGINES – CLB-1 VFS Altitude: 2000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

51000

56000

61000

66000

71000

76000

81000

86000

31.9

27.7

24.4

21.7

19.3

17.3

15.7

14.2

(1939)

(1684)

(1485)

(1318)

(1172)

(1051)

(951)

(862)

31.9

27.7

24.4

21.7

19.3

17.3

15.6

14.2

(1935)

(1681)

(1482)

(1315)

(1170)

(1049)

(949)

(861)

31.7

27.6

24.3

21.6

19.2

17.2

15.5

14.1

(1928)

(1674)

(1475)

(1309)

(1164)

(1044)

(944)

(856)

-30

-20

-10 31.6

27.4

24.2

21.5

19.1

17.1

15.5

14.0

(1920)

(1666)

(1469)

(1303)

(1159)

(1039)

(939)

(851)

0 31.2

27.0

23.8

21.1

18.8

16.8

15.2

13.8

(1893)

(1642)

(1446)

(1283)

(1141)

(1023)

(924)

(838)

27.2

23.6

20.8

18.4

16.3

14.5

13.1

11.8

(1654)

(1433)

(1261)

(1115)

(989)

(883)

(794)

(715)

23.5

20.4

17.9

15.8

13.9

12.4

11.1

9.9

(1429)

(1237)

(1086)

(957)

(844)

(751)

(672)

(602)

10

20

30 A-ICE CORRECTION SUBTRACT: 0.7 % OR 43. ft/NM

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 4.8 % OR 292. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 123

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 175 – CF34-8 ENGINES – CLB-1 VFS Altitude: 4000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

51000

56000

61000

66000

71000

76000

81000

86000

29.8

26.0

22.9

20.2

18.0

16.1

14.5

13.1

(1810)

(1577)

(1389)

(1227)

(1093)

(981)

(883)

(796)

29.7

25.9

22.8

20.2

18.0

16.1

14.5

13.1

(1806)

(1574)

(1386)

(1224)

(1091)

(979)

(881)

(794)

29.6

25.8

22.7

20.1

17.9

16.0

14.5

13.0

(1800)

(1567)

(1380)

(1218)

(1086)

(974)

(878)

(792)

-30

-20

-10 29.5

25.7

22.6

20.0

17.8

16.0

14.4

13.0

(1791)

(1560)

(1373)

(1212)

(1080)

(969)

(873)

(788)

0 29.1

25.3

22.3

19.7

17.6

15.8

14.2

12.8

(1769)

(1539)

(1355)

(1196)

(1066)

(957)

(862)

(777)

25.4

22.1

19.4

17.0

15.1

13.5

12.1

10.8

(1545)

(1343)

(1178)

(1035)

(918)

(820)

(735)

(658)

22.0

19.1

16.7

14.6

12.9

11.5

10.2

9.1

(1335)

(1158)

(1012)

(886)

(783)

(696)

(620)

(551)

10

20

30 A-ICE CORRECTION SUBTRACT: 0.6 % OR 37. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 124

Takeoff

REVISION 21

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 4.3 % OR 261. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 175 – CF34-8 ENGINES – CLB-1 VFS Altitude: 6000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

51000

56000

61000

66000

71000

76000

81000

86000

27.7

24.2

21.1

18.7

16.7

14.9

13.4

12.1

(1686)

(1470)

(1284)

(1135)

(1014)

(906)

(816)

(737)

27.7

24.1

21.1

18.6

16.7

14.9

13.4

12.1

(1682)

(1466)

(1281)

(1133)

(1012)

(904)

(814)

(736)

27.6

24.1

21.0

18.6

16.6

14.9

13.4

12.1

(1678)

(1463)

(1278)

(1130)

(1009)

(902)

(812)

(734)

-30

-20

-10 27.5

24.0

21.0

18.5

16.6

14.8

13.3

12.0

(1673)

(1458)

(1274)

(1126)

(1006)

(898)

(807)

(729)

0 27.2

23.7

20.7

18.3

16.3

14.6

13.1

11.8

(1654)

(1441)

(1258)

(1112)

(992)

(886)

(796)

(719)

23.7

20.6

17.9

15.8

14.1

12.5

11.2

10.0

(1442)

(1253)

(1090)

(960)

(854)

(758)

(677)

(608)

20.5

17.7

15.4

13.5

11.9

10.5

9.3

8.3

(1245)

(1077)

(932)

(817)

(723)

(637)

(565)

(503)

10

20

30 A-ICE CORRECTION SUBTRACT: 0.6 % OR 34. ft/NM

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 3.9 % OR 239. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 125

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 175 – CF34-8 ENGINES – CLB-1 VFS Altitude: 8000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

51000

56000

61000

66000

71000

76000

81000

86000

25.8

22.3

19.5

17.3

15.4

13.7

12.3

11.1

(1566)

(1357)

(1187)

(1051)

(933)

(833)

(750)

(674)

25.7

22.3

19.5

17.3

15.3

13.7

12.3

11.1

(1563)

(1354)

(1185)

(1049)

(931)

(831)

(748)

(672)

25.7

22.2

19.5

17.2

15.3

13.7

12.3

11.0

(1560)

(1351)

(1182)

(1047)

(929)

(829)

(746)

(670)

-30

-20

-10 25.6

22.2

19.4

17.2

15.3

13.6

12.3

11.0

(1557)

(1348)

(1180)

(1045)

(927)

(827)

(745)

(669)

0 25.4

22.0

19.2

17.0

15.1

13.5

12.1

10.9

(1541)

(1334)

(1167)

(1033)

(916)

(817)

(735)

(660)

22.2

19.1

16.7

14.7

13.0

11.5

10.3

9.2

(1348)

(1161)

(1012)

(893)

(788)

(699)

(625)

(557)

19.1

16.4

14.2

12.5

10.9

9.6

8.5

7.5

(997)

(864)

(757)

(662)

(583)

(518)

(458)

10

20

30 (1162)

A-ICE CORRECTION SUBTRACT: 1.9 % OR 115. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 126

Takeoff

REVISION 21

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 3.6 % OR 220. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 175 – CF34-8 ENGINES – CLB-1 VFS Altitude: 10000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

51000

56000

61000

66000

71000

76000

81000

86000

23.8

20.6

18.1

15.9

14.1

12.6

11.2

10.1

(1446)

(1252)

(1098)

(966)

(855)

(763)

(683)

(612)

23.8

20.6

18.0

15.9

14.0

12.5

11.2

10.1

(1444)

(1249)

(1095)

(964)

(853)

(762)

(682)

(611)

23.7

20.5

18.0

15.8

14.0

12.5

11.2

10.0

(1440)

(1246)

(1093)

(962)

(852)

(761)

(680)

(610)

-30

-20

-10 23.6

20.5

17.9

15.8

14.0

12.5

11.2

10.0

(1436)

(1243)

(1090)

(960)

(851)

(760)

(679)

(609)

0 23.4

20.3

17.8

15.6

13.9

12.4

11.1

9.9

(1422)

(1230)

(1079)

(950)

(842)

(752)

(672)

(603)

20.5

17.7

15.5

13.5

11.9

10.6

9.4

8.4

(1247)

(1075)

(939)

(823)

(725)

(644)

(572)

(509)

17.7

15.2

13.2

11.5

10.0

8.8

7.8

6.8

(922)

(801)

(696)

(608)

(536)

(472)

(415)

10

20

30 (1075)

A-ICE CORRECTION SUBTRACT: 1.8 % OR 110. ft/NM

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 3.3 % OR 203. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 127

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 175 – CF34-8 ENGINES – CLB-1 250 KIAS Altitude: Sea Level Grad % WEIGHT (lb) (ft/NM) ISA (°C)

51000

56000

61000

66000

71000

76000

81000

86000

25.2

22.6

20.5

18.7

17.2

15.8

14.6

13.5

(1530)

(1374)

(1246)

(1139)

(1044)

(959)

(885)

(821)

25.1

22.6

20.5

18.7

17.1

15.8

14.5

13.5

(1526)

(1371)

(1243)

(1136)

(1041)

(957)

(883)

(819)

25.0

22.5

20.4

18.6

17.1

15.7

14.5

13.4

(1520)

(1365)

(1238)

(1131)

(1037)

(953)

(879)

(815)

-30

-20

-10 24.6

22.1

20.1

18.3

16.8

15.4

14.2

13.2

(1496)

(1344)

(1218)

(1113)

(1020)

(937)

(865)

(802)

0 24.4

22.0

19.9

18.2

16.7

15.3

14.1

13.1

(1484)

(1333)

(1209)

(1105)

(1012)

(930)

(858)

(795)

21.0

18.9

17.1

15.6

14.3

13.1

12.1

11.2

(1277)

(1147)

(1040)

(950)

(869)

(797)

(734)

(679)

17.7

15.9

14.4

13.1

12.0

11.0

10.1

9.3

(964)

(873)

(797)

(727)

(665)

(611)

(563)

10

20

30 (1074)

A-ICE CORRECTION SUBTRACT: 0.6 % OR 37. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 128

Takeoff

REVISION 21

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 4.2 % OR 253. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 175 – CF34-8 ENGINES – CLB-1 250 KIAS Altitude: 2000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

51000

56000

61000

66000

71000

76000

81000

86000

23.6

21.2

19.2

17.5

16.1

14.8

13.6

12.6

(1431)

(1287)

(1169)

(1066)

(975)

(897)

(829)

(767)

23.5

21.2

19.2

17.5

16.0

14.7

13.6

12.6

(1429)

(1285)

(1166)

(1064)

(973)

(895)

(827)

(766)

23.4

21.0

19.1

17.4

15.9

14.7

13.5

12.5

(1420)

(1277)

(1160)

(1058)

(968)

(890)

(822)

(761)

-30

-20

-10 23.2

20.9

19.0

17.3

15.8

14.6

13.5

12.5

(1412)

(1270)

(1153)

(1051)

(962)

(884)

(817)

(756)

0 22.9

20.6

18.7

17.1

15.6

14.4

13.3

12.3

(1392)

(1252)

(1136)

(1036)

(948)

(872)

(805)

(745)

19.5

17.5

15.9

14.5

13.2

12.2

11.2

10.3

(1184)

(1065)

(967)

(880)

(804)

(738)

(680)

(627)

16.4

14.8

13.4

12.2

11.1

10.2

9.3

8.6

(897)

(813)

(739)

(673)

(616)

(567)

(521)

10

20

30 (998)

A-ICE CORRECTION SUBTRACT: 0.6 % OR 36. ft/NM

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 4.1 % OR 249. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 129

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 175 – CF34-8 ENGINES – CLB-1 250 KIAS Altitude: 4000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

51000

56000

61000

66000

71000

76000

81000

86000

21.9

19.7

17.9

16.3

14.9

13.7

12.6

11.7

(1329)

(1197)

(1085)

(987)

(904)

(832)

(767)

(708)

21.8

19.7

17.8

16.2

14.9

13.7

12.6

11.6

(1326)

(1194)

(1083)

(986)

(903)

(831)

(766)

(706)

21.7

19.6

17.7

16.1

14.8

13.6

12.5

11.6

(1319)

(1188)

(1077)

(980)

(898)

(826)

(762)

(703)

-30

-20

-10 21.6

19.5

17.6

16.1

14.7

13.5

12.5

11.5

(1312)

(1182)

(1072)

(975)

(893)

(822)

(758)

(699)

0 21.3

19.2

17.4

15.8

14.5

13.3

12.3

11.3

(1294)

(1165)

(1057)

(962)

(880)

(810)

(746)

(688)

18.1

16.3

14.8

13.4

12.3

11.3

10.4

9.5

(1100)

(991)

(897)

(815)

(745)

(685)

(629)

(578)

15.1

13.6

12.3

11.2

10.2

9.3

8.5

7.8

(828)

(748)

(678)

(618)

(566)

(518)

(474)

10

20

30 (920)

A-ICE CORRECTION SUBTRACT: 0.5 % OR 33. ft/NM

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Page 130

Takeoff

REVISION 21

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 3.9 % OR 236. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 175 – CF34-8 ENGINES – CLB-1 250 KIAS Altitude: 6000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

51000

56000

61000

66000

71000

76000

81000

86000

20.2

18.2

16.5

15.0

13.7

12.6

11.6

10.7

(1227)

(1105)

(999)

(911)

(835)

(766)

(704)

(650)

20.1

18.1

16.4

14.9

13.7

12.6

11.6

10.7

(1224)

(1102)

(997)

(908)

(832)

(763)

(702)

(648)

20.1

18.1

16.4

14.9

13.7

12.5

11.5

10.6

(1220)

(1099)

(994)

(905)

(830)

(761)

(700)

(646)

-30

-20

-10 20.0

18.0

16.3

14.9

13.6

12.5

11.5

10.6

(1216)

(1095)

(990)

(902)

(827)

(759)

(698)

(644)

0 19.7

17.8

16.1

14.6

13.4

12.3

11.3

10.4

(1198)

(1079)

(976)

(889)

(814)

(747)

(687)

(634)

16.7

15.0

13.6

12.4

11.3

10.3

9.5

8.7

(1015)

(914)

(825)

(750)

(687)

(628)

(575)

(529)

13.9

12.5

11.2

10.2

9.3

8.5

7.7

7.1

(758)

(683)

(620)

(565)

(515)

(470)

(430)

10

20

30 (843)

A-ICE CORRECTION SUBTRACT: 0.5 % OR 29. ft/NM

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 3.5 % OR 210. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Takeoff

Page 131

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 175 – CF34-8 ENGINES – CLB-1 250 KIAS Altitude: 8000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

51000

56000

61000

66000

71000

76000

81000

86000

18.7

16.8

15.2

13.9

12.7

11.6

10.7

9.8

(1136)

(1019)

(923)

(842)

(769)

(705)

(649)

(598)

18.7

16.7

15.2

13.8

12.6

11.6

10.7

9.8

(1133)

(1017)

(921)

(840)

(767)

(703)

(647)

(596)

18.6

16.7

15.1

13.8

12.6

11.5

10.6

9.8

(1131)

(1015)

(919)

(838)

(765)

(701)

(645)

(595)

-30

-20

-10 18.5

16.6

15.1

13.7

12.5

11.5

10.6

9.8

(1126)

(1011)

(915)

(834)

(762)

(698)

(643)

(592)

0 18.3

16.4

14.9

13.5

12.4

11.3

10.4

9.6

(1110)

(997)

(902)

(823)

(751)

(688)

(633)

(583)

15.4

13.8

12.5

11.4

10.4

9.5

8.7

8.0

(937)

(840)

(760)

(691)

(630)

(575)

(527)

(484)

12.7

11.4

10.3

9.3

8.5

7.7

7.0

6.4

(692)

(624)

(567)

(514)

(467)

(427)

(389)

10

20

30 (774)

A-ICE CORRECTION SUBTRACT: 1.5 % OR 93. ft/NM

5-20 Copyright © by Embraer. Refer to cover page for details.

Page 132

Takeoff

REVISION 21

AOM-1502-003

CLB-2 CORRECTION SUBTRACT: 3.2 % OR 193. ft/NM

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CLIMB GRADIENT – ALL ENGINES OPERATING CLIMB THRUST EMBRAER 175 – CF34-8 ENGINES – CLB-1 250 KIAS Altitude: 10000 ft Grad % WEIGHT (lb) (ft/NM) ISA (°C)

51000

56000

61000

66000

71000

76000

81000

86000

17.1

15.4

13.9

12.6

11.5

10.6

9.7

8.9

(1037)

(932)

(845)

(768)

(701)

(643)

(590)

(542)

17.0

15.3

13.9

12.6

11.5

10.6

9.7

8.9

(1035)

(930)

(843)

(766)

(699)

(641)

(588)

(540)

17.0

15.3

13.8

12.6

11.5

10.5

9.7

8.9

(1032)

(927)

(840)

(764)

(697)

(639)

(587)

(539)

-30

-20

-10 17.0

15.2

13.8

12.5

11.5

10.5

9.6

8.9

(1030)

(925)

(838)

(762)

(695)

(638)

(585)

(538)

0 16.7

15.0

13.6

12.4

11.3

10.4

9.5

8.7

(1017)

(914)

(828)

(753)

(687)

(630)

(578)

(531)

14.1

12.7

11.5

10.4

9.5

8.7

7.9

7.2

(859)

(771)

(698)

(632)

(575)

(526)

(480)

(439)

11.6

10.4

9.4

8.4

7.7

7.0

6.3

5.7

(629)

(568)

(513)

(464)

(423)

(384)

(348)

10

20

30 (703)

A-ICE CORRECTION SUBTRACT: 1.5 % OR 90. ft/NM CLB-2 CORRECTION SUBTRACT: 2.7 % OR 165. ft/NM

AOM-1502-003

"

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REVISION 21

Takeoff

Page 133

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

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Page 134

Takeoff

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

SUPPLEMENTARY TAKEOFF INFORMATION TURN ANALYSIS The method below presents the criteria for transforming a takeoff flight path with turns into an equivalent straight flight path. This allows the use of runway analysis software to determine obstacle clearance. The method to be used herein converts an actual flight path with turns and wind effects into an equivalent straight flight path with still air. This straight flight path will be determined in terms of increments on the height of the existing obstacle, and is taken into account to ensure obstacle clearance. The performance calculation must be made with the equivalent straight flight path, as per the AFM. OPERATIONAL LIMITATIONS Maximum bank angle: Both Engines Operative: 25° at V2 + 10 One Engine Inoperative: 15° at V2 One Engine Inoperative: 20° at V2 + 5 (*) One Engine Inoperative: 25° at V2 + 10 (*)

AOM-1502-003

(*) According to FAR 121.189(f), the maximum bank angle with one engine inoperative is 15°. According to JAR OPS 1.495 (c), for bank angles greater than 15°, the airplane’s net path must clear all obstacles after the banked turn by 50 ft instead of 35 ft.

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REVISION 21

Supplementary Takeoff Information

Page 1

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

EQUIVALENT STRAIGHT FLIGHT PATH DETERMINATION The equivalent straight flight path (zero wind) to be used in the performance calculation should be determined as follows: 1 - OBSTACLE INCREMENT IN A STEADY TURN During a steady turn, the climb gradient deteriorates. To compensate for this, an increment of the actual obstacle height must be obtained as a function of the gradient loss due to a steady turn and the turning distance flown to the obstacle: ∆H = DT x GL + Aw where: ∆H = obstacle height increment. DT = distance flown along the turning flight to the obstacle. GL = gradient loss (obtained from the Turn performance calculation part in the ECAFM). Aw = allowance to compensate the lower wing tip height due to the bank angle. and Aw = [Wing span x sin (bank angle)]/2 The equivalent obstacle height to be used in an obstacle clearance calculation is: HE = HA + ∆H1 + ∆H2 + ......+ ∆Hn where: HE = equivalent obstacle height. HA = actual obstacle height. ∆H1,2,n = height increments for each distance portion flown in the turn to the obstacle. 2 - WIND EFFECT ON THE FLIGHT PATH

Considering the drift compensation, the straight portions of the

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Page 2

Supplementary Takeoff Information

REVISION 21

AOM-1502-003

2.1 - STRAIGHT FLIGHT PORTIONS

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

flight path may be corrected to a still air equivalent distance as follows: GD x TAS GS

SAD = where:

SAD = still air equivalent distance. GD = actual ground distance. TAS = airplane true airspeed (obtained from the radius of turns and speed conversion chart). GS = airplane ground speed. For straight flight: GS = TAS + (Vw x cosα) where: Vw = wind speed. α = angle between flight direction and wind direction. Remarks: Vw x cosα is negative for a head wind component. Vw x cosα is positive for a tailwind component. 2.2 - TURNING FLIGHT PORTIONS Two effects must be taken into account: 2.2.1 -

Distance Flown Compensation: The wind takes the same effect as mentioned in item 2.1.

SAD =

GD x TAS GS

AOM-1502-003

For turning flight:

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REVISION 21

Supplementary Takeoff Information

Page 3

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

GS =

Dm ∆t

where: Dm = distance flown along the actual trajectory. ∆t = elapsed time in turning flight. 2.2.2 -

Trajectory Displacement: The trajectory is displaced in the wind component direction proportionally to time. The displacement may be calculated by:

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Page 4

Supplementary Takeoff Information

REVISION 21

AOM-1502-003

∆D = ∆t x VW. ∆D = trajectory displacement in the wind component direction. ∆t = elapsed time in turning flight (obtained from the Horizontal Distance and Time to Complete chart). VW = wind speed.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

STILL AIR TRAJECTORY (WITHOUT WIND) D3

ACTUAL TRAJECTORY (WITH WIND)

D2

D1

AOM-1502-003

Vw EM170AOM050012A.DGN

t2

t3

t1

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REVISION 21

Supplementary Takeoff Information

Page 5

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

PERFORMANCE CHARTS PRESENTATION

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Page 6

Supplementary Takeoff Information

REVISION 21

AOM-1502-003

All necessary information is provided in the ECAFM.

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

AIRCRAFT CLASSIFICATION NUMBER - ACN The Pavement Classification Number (PCN) reported shall indicate that an airplane with ACN equal to or less than the reported PCN can operate on that pavement.

PCN - PAVEMENT CLASSIFICATION NUMBER Example: PCN 50 / F / A / X / T | | | | 1 2 3 4 1) Type of pavement: R = Rigid (concrete); F = Flexible (asphalt); 2) Pavement sub-grade strength category: A = High, B = Medium, C = Low, D = Ultra-low. 3)

4)

Maximum tire pressure authorized for the pavement: W = High, no limit; X = Medium (up to 217 psi); Y = Low (up to 145 psi); Z = Very low (up to 73 psi). Pavement evaluation method: T = Technical evaluation; U = By experience of airplane actually using the pavement.

OVERLOAD OPERATIONS

AOM-1502-003

Individual airport authorities are free to decide on their own criteria for permitting overload operations as long as pavements remain safe for use by airplanes.

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REVISION 21

Supplementary Takeoff Information

Page 7

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

!170 LR, units in lb

EMBRAER 170 LR − ACN RIGID PAVEMENT 25 24 23

D (K=20 MN/m³)

22

C (K=40 MN/m³)

21 B (K=80 MN/m³) AIRCRAFT CLASSIFICATION NUIMBER − ACN

20 19

A (K=150 MN/m³)

18 17 16 15 14 13 12 11 10 9

7 6 5 45000

50000

55000

60000

65000 70000 WEIGHT (lb)

75000

80000

85000

EM170AOM050013B.DGN

8

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Page 8

Supplementary Takeoff Information

REVISION 21

AOM-1502-003

"

PERFORMANCE

AIRPLANE OPERATIONS MANUAL !170 LR, units in lb

EMBRAER 170 LR − ACN FLEXIBLE PAVEMENT 25 24

D (CBR = 3 %)

23 22 21 C (CBR = 6 %)

AIRCRAFT CLASSIFICATION NUIMBER − ACN

20 19 B (CBR = 10 %)

18

A (CBR = 15 %)

17 16 15 14 13 12 11 10 9

7 6 5 45000

50000

55000

60000

65000 70000 WEIGHT (lb)

75000

80000

85000

EM170AOM050020B.DGN

8

AOM-1502-003

"

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REVISION 21

Supplementary Takeoff Information

Page 9

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

!EMBRAER 175 LR Model 30

29

EMBRAER 175 LR − ACN FLEXIBLE PAVEMENT 28

27

NOTES:

26

TIRE SIZE: H38 x 13−18 18PR TIRE PRESSURE: 9.56 kgf/cm² (136 psi)

25

24

AIRCRAFT CLASSIFICATION NUMBER − ACN

23

22

D (CBR = 3%)

21

B (CBR = 10%)

C (CBR = 6%) A (CBR = 15%) 20

19

18

17

16

15

14

13

12

11

10

8

22000

24000

26000

28000

30000

32000

34000

36000

38000

40000

WEIGHT − kg

47000

52000

57000

62000

67000

72000

77000

WEIGHT − lb

82000

87000

EM170AOM050039C.DGN

9

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Page 10

Supplementary Takeoff Information

REVISION 21

AOM-1502-003

"

PERFORMANCE

AIRPLANE OPERATIONS MANUAL !EMBRAER 175 LR Model 30

29

EMBRAER 175 LR − ACN RIGID PAVEMENT 28

27

TIRE SIZE: H38 x 13−18 18PR TIRE PRESSURE: 9.56 kgf/cm² (136 psi)

NOTES:

26

25

24

AIRCRAFT CLASSIFICATION NUMBER − ACN

23

22

D (K = 20 MN/m³) 21

C (K = 40 MN/m³) B ( K = 80 MN/m³)

20

A (K = 150 MN/m³)

19

18

17

16

15

14

13

12

11

10

8

22000

24000

26000

28000

30000

32000

34000

36000

38000

40000

WEIGHT − kg 22000

52000

57000

62000

67000

72000

77000

WEIGHT − lb

82000

87000

EM170AOM050040C.DGN

9

AOM-1502-003

"

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REVISION 21

Supplementary Takeoff Information

Page 11

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

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Page 12

Supplementary Takeoff Information

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

APPROACH AND LANDING SPEEDS EMBRAER 170 CF34-8 ENGINES

AOM-1502-003

Without Ice Accretion WEIGHT

VREF FLAP 5

VAC FLAP 2

(lb) 48000 50000 52000 54000 56000 58000 60000 62000 64000 66000 68000 70000 72000 74000 76000 78000 80000 82000

(KIAS) 107 109 112 114 116 118 120 122 124 126 128 130 131 133 135 137 139 140

(KIAS) 127 130 133 135 138 140 143 145 147 150 152 154 156 158 161 163 165 167

VREF FLAP FULL (KIAS) 101 103 105 107 109 111 113 115 116 118 120 122 123 125 126 127 128 129

VAC FLAP 4

VFS

(KIAS) 112 115 117 119 121 124 126 128 130 132 134 136 138 140 142 143 145 147

(KIAS) 154 158 161 164 167 170 173 176 179 181 184 187 189 192 195 197 200 202

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REVISION 21

Approach

Page 1

PERFORMANCE

AIRPLANE OPERATIONS MANUAL EMBRAER 170 CF34-8 ENGINES

WEIGHT

VREF FLAP 5

VAC FLAP 2

(lb) 48000 50000 52000 54000 56000 58000 60000 62000 64000 66000 68000 70000 72000 74000 76000 78000 80000 82000

(KIAS) 116 118 121 123 125 128 130 132 134 136 138 140 142 144 146 148 150 152

(KIAS) 127 130 133 135 138 140 143 145 147 150 152 154 156 158 161 163 165 167

VREF FLAP FULL (KIAS) 107 109 111 113 115 117 119 121 123 125 126 128 130 132 133 134 135 136

VAC FLAP 4

VFS

(KIAS) 112 115 117 119 121 124 126 128 130 132 134 136 138 140 142 143 145 147

(KIAS) 154 158 161 164 167 170 173 176 179 181 184 187 189 192 195 197 200 202

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Page 2

Approach

REVISION 21

AOM-1502-003

With Ice Accretion

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

EMBRAER 170 CF34-8 ENGINES CAT II OPERATION - With or Without Ice Accretion WEIGHT

AOM-1502-003

(lb) 48000 50000 52000 54000 56000 58000 60000 62000 64000 66000 68000 70000 72000 74000 76000 78000 80000 82000

VREF FLAP 5 (KIAS) 116 118 121 123 125 128 130 132 134 136 138 140 142 144 146 148 150 152

VAC FLAP 2 (KIAS) 127 130 133 135 138 140 143 145 147 150 152 154 156 158 161 163 165 167

VFS (KIAS) 154 158 161 164 167 170 173 176 179 181 184 187 189 192 195 197 200 202

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REVISION 21

Approach

Page 3

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

FLAPS MANEUVERING SPEEDS SPEED (KIAS) 210 180 160 150 140 140 130

FLAP UP 1 2 3 4 5 FULL

NOTE: These speeds allow an inadvertent 15° overshoot beyond the normal 25° bank and provide at least 1.3 g margin over stick shaker speed. They are valid for all weights up to the maximum structural landing weight, with or without ice accretion. The speeds above may be used as reference for flaps extension and maneuvering. For flaps retraction refer to the Flap Retraction Speed Schedule presented on section 5-20 (Takeoff). The green dot on the PFD provides at least 1.3 g margin over stick shaker speed adjusted for the current airplane weight, thus it can also be used as the Flap Maneuvering Speed. !170 models, MAU Load 21.2 up to Load 25.4 - Pentium M or Load 25.3 - Pentium II

For airplanes equipped with Load version previous than Load 25.5.0.1, the green dot does not account for ice accretion. Therefore when flying in icing conditions (EICAS message STALL PROT ICE SPEED displayed) it is recommended to add 10 kt to the green dot. " !170 models, MAU Load 25.5.0.1 and on

For airplanes equipped with Load version 25.5.0.1 and on, the green dot accounts for ice accretion.

5-30 Copyright © by Embraer. Refer to cover page for details.

Page 4

Approach

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

APPROACH CLIMB GRADIENT !EMBRAER 170 Models

The Approach Climb Gradient tables show the gradients as function of temperature (°C) and weight (lb). The associated conditions are: – Approach Flaps: 2 or 4; – Gear UP; – Anti-Ice OFF without Ice Accretion or Wing and Engine Anti-ice ON with Ice Accretion; – ECS OFF;

AOM-1502-003

– One Engine Inoperative.

5-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Approach

Page 5

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

APPROACH CLIMB GRADIENT (%) EMBRAER 170 – CF34-8 ENGINES LANDING FLAP 5 – APPROACH FLAP 2 Altitude: Sea Level ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 48 50

53000 12.93 12.91 12.89 12.86 12.84 12.81 12.79 12.76 12.74 12.72 12.69 12.67 12.65 12.62 12.58 12.56 12.03 11.51 10.98 10.44 9.95 9.55 9.15 8.75 8.36 7.96

55000 12.03 12.00 11.98 11.96 11.94 11.91 11.89 11.87 11.85 11.83 11.81 11.78 11.76 11.72 11.68 11.66 11.16 10.66 10.16 9.64 9.18 8.80 8.42 8.04 7.66 7.29

57000 11.19 11.17 11.15 11.13 11.11 11.09 11.07 11.04 11.02 11.00 10.98 10.96 10.94 10.90 10.86 10.83 10.36 9.88 9.40 8.90 8.47 8.11 7.74 7.38 7.02 6.66

WEIGHT (lb) 59000 61000 63000 65000 67000 69000 71000 73000 10.41 9.70 9.04 8.42 7.85 7.31 6.81 6.34 10.40 9.68 9.02 8.40 7.83 7.30 6.80 6.33 10.38 9.67 9.00 8.39 7.82 7.28 6.79 6.32 10.36 9.65 8.99 8.37 7.80 7.27 6.77 6.31 10.34 9.63 8.97 8.35 7.78 7.25 6.76 6.29 10.32 9.61 8.95 8.34 7.77 7.24 6.74 6.28 10.30 9.59 8.94 8.32 7.75 7.22 6.73 6.26 10.28 9.58 8.92 8.31 7.74 7.21 6.71 6.25 10.26 9.56 8.90 8.29 7.72 7.19 6.70 6.23 10.24 9.54 8.88 8.27 7.71 7.18 6.68 6.22 10.23 9.52 8.87 8.26 7.69 7.16 6.67 6.21 10.21 9.51 8.86 8.25 7.68 7.15 6.66 6.19 10.19 9.49 8.84 8.24 7.67 7.14 6.65 6.18 10.14 9.43 8.76 8.15 7.58 7.06 6.57 6.10 10.09 9.39 8.73 8.12 7.55 7.02 6.52 6.05 10.07 9.37 8.71 8.10 7.54 7.00 6.51 6.04 9.61 8.93 8.29 7.69 7.14 6.62 6.13 5.68 9.16 8.49 7.87 7.28 6.74 6.24 5.76 5.31 8.70 8.04 7.44 6.87 6.35 5.86 5.39 4.96 8.22 7.59 7.01 6.46 5.96 5.49 5.05 4.64 7.82 7.22 6.66 6.14 5.66 5.20 4.77 4.37 7.47 6.89 6.34 5.83 5.36 4.91 4.49 4.10 7.12 6.55 6.02 5.52 5.06 4.62 4.21 3.83 6.77 6.22 5.69 5.21 4.75 4.33 3.93 3.56 6.43 5.88 5.37 4.89 4.45 4.03 3.65 3.28 6.08 5.54 5.04 4.57 4.14 3.74 3.36 3.01

WING AND ENGINE ANTI-ICE ON

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 53000 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 10.66 9.76 8.93 8.17 7.47 6.81 6.20 5.63 5.10 4.61 4.14 10.68 9.78 8.95 8.19 7.48 6.83 6.22 5.65 5.12 4.62 4.16 10.67 9.78 8.95 8.18 7.48 6.83 6.22 5.65 5.12 4.62 4.16 10.65 9.76 8.93 8.16 7.46 6.81 6.20 5.63 5.10 4.61 4.14 10.63 9.73 8.91 8.14 7.45 6.79 6.18 5.62 5.09 4.59 4.13 10.60 9.71 8.89 8.13 7.43 6.78 6.17 5.60 5.07 4.58 4.11 10.58 9.69 8.87 8.11 7.41 6.76 6.15 5.59 5.06 4.56 4.10 10.55 9.67 8.84 8.09 7.39 6.74 6.13 5.57 5.04 4.55 4.09 10.53 9.64 8.82 8.07 7.37 6.72 6.12 5.55 5.03 4.53 4.07 10.50 9.62 8.80 8.05 7.35 6.70 6.10 5.54 5.01 4.52 4.06

5-30 Copyright © by Embraer. Refer to cover page for details.

Page 6

Approach

REVISION 21

AOM-1502-003

SAT

(°C)

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

APPROACH CLIMB GRADIENT (%) EMBRAER 170 – CF34-8 ENGINES LANDING FLAP 5 – APPROACH FLAP 2 Altitude: 1000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 48

53000 12.53 12.51 12.50 12.48 12.46 12.45 12.43 12.41 12.39 12.38 12.36 12.34 12.16 12.13 12.10 11.61 11.11 10.62 10.13 9.64 9.17 8.70 8.28 7.92 7.55

55000 11.65 11.64 11.62 11.60 11.59 11.57 11.56 11.54 11.52 11.51 11.49 11.48 11.29 11.26 11.24 10.77 10.29 9.82 9.34 8.87 8.43 7.99 7.60 7.25 6.90

57000 10.84 10.83 10.81 10.80 10.78 10.77 10.75 10.74 10.72 10.71 10.69 10.68 10.49 10.47 10.44 9.99 9.53 9.07 8.62 8.17 7.75 7.34 6.96 6.63 6.29

WEIGHT (lb) 59000 61000 63000 65000 67000 69000 71000 73000 10.09 9.40 8.76 8.16 7.60 7.08 6.60 6.14 10.08 9.39 8.75 8.15 7.59 7.07 6.58 6.13 10.06 9.37 8.73 8.13 7.58 7.06 6.57 6.12 10.05 9.36 8.72 8.12 7.57 7.05 6.56 6.10 10.04 9.35 8.71 8.11 7.56 7.04 6.55 6.09 10.02 9.34 8.70 8.10 7.54 7.02 6.54 6.08 10.01 9.32 8.68 8.08 7.53 7.01 6.52 6.07 9.99 9.31 8.67 8.07 7.51 7.00 6.51 6.05 9.98 9.29 8.65 8.06 7.50 6.99 6.50 6.04 9.97 9.28 8.64 8.04 7.49 6.97 6.49 6.03 9.95 9.26 8.62 8.03 7.47 6.96 6.48 6.02 9.94 9.25 8.61 8.01 7.46 6.95 6.46 6.01 9.76 9.09 8.46 7.87 7.33 6.82 6.34 5.88 9.72 9.04 8.40 7.80 7.25 6.73 6.25 5.80 9.70 9.01 8.37 7.78 7.23 6.71 6.23 5.78 9.26 8.60 7.98 7.40 6.86 6.36 5.89 5.44 8.82 8.17 7.57 7.00 6.48 5.99 5.53 5.10 8.38 7.74 7.15 6.60 6.08 5.61 5.17 4.75 7.95 7.33 6.75 6.21 5.71 5.25 4.82 4.41 7.52 6.91 6.35 5.83 5.35 4.89 4.47 4.07 7.12 6.54 6.00 5.50 5.03 4.59 4.18 3.79 6.73 6.17 5.65 5.16 4.71 4.29 3.89 3.52 6.38 5.83 5.33 4.86 4.42 4.00 3.62 3.25 6.06 5.53 5.03 4.57 4.14 3.74 3.36 3.01 5.74 5.22 4.74 4.29 3.87 3.48 3.11 2.76

WING AND ENGINE ANTI-ICE ON SAT

(°C)

AOM-1502-003

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 53000 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 10.29 9.43 8.62 7.88 7.20 6.57 5.98 5.43 4.91 4.43 3.98 10.29 9.43 8.62 7.88 7.21 6.57 5.98 5.43 4.92 4.43 3.98 10.28 9.41 8.61 7.87 7.19 6.56 5.97 5.42 4.90 4.42 3.97 10.26 9.39 8.59 7.85 7.17 6.54 5.95 5.40 4.89 4.41 3.95 10.24 9.37 8.57 7.84 7.16 6.53 5.94 5.39 4.87 4.39 3.94 10.22 9.36 8.56 7.82 7.14 6.51 5.92 5.37 4.86 4.38 3.93 10.20 9.34 8.54 7.80 7.13 6.50 5.91 5.36 4.85 4.36 3.91 10.18 9.32 8.52 7.79 7.11 6.48 5.89 5.35 4.83 4.35 3.90 10.17 9.30 8.51 7.77 7.10 6.47 5.88 5.33 4.82 4.34 3.88 10.15 9.29 8.49 7.76 7.08 6.45 5.86 5.32 4.80 4.32 3.87

5-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Approach

Page 7

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

APPROACH CLIMB GRADIENT (%) EMBRAER 170 – CF34-8 ENGINES LANDING FLAP 5 – APPROACH FLAP 2 Altitude: 2000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46

53000 11.90 11.89 11.87 11.86 11.85 11.83 11.81 11.80 11.78 11.76 11.74 11.64 11.62 11.61 11.20 10.78 10.33 9.85 9.37 8.87 8.38 7.92 7.50 7.08

55000 11.06 11.05 11.03 11.02 11.00 10.99 10.97 10.95 10.94 10.92 10.91 10.80 10.78 10.77 10.38 9.98 9.55 9.09 8.63 8.15 7.67 7.23 6.84 6.44

WEIGHT (lb) 57000 59000 61000 63000 65000 67000 69000 71000 73000 10.28 9.56 8.89 8.27 7.69 7.15 6.65 6.18 5.73 10.27 9.54 8.88 8.26 7.68 7.14 6.64 6.17 5.72 10.25 9.53 8.87 8.25 7.67 7.13 6.63 6.16 5.71 10.24 9.52 8.85 8.24 7.66 7.12 6.62 6.14 5.70 10.22 9.50 8.84 8.22 7.65 7.11 6.60 6.13 5.69 10.21 9.49 8.83 8.21 7.63 7.10 6.59 6.12 5.68 10.19 9.48 8.81 8.20 7.62 7.09 6.58 6.11 5.67 10.18 9.46 8.80 8.19 7.61 7.07 6.57 6.10 5.66 10.16 9.45 8.79 8.17 7.60 7.06 6.56 6.09 5.65 10.15 9.43 8.77 8.16 7.59 7.05 6.55 6.08 5.63 10.13 9.42 8.76 8.15 7.57 7.04 6.54 6.07 5.62 10.03 9.32 8.66 8.05 7.48 6.95 6.45 5.98 5.53 10.01 9.30 8.64 8.03 7.46 6.93 6.43 5.96 5.52 9.99 9.28 8.63 8.02 7.45 6.91 6.42 5.95 5.51 9.62 8.92 8.27 7.67 7.10 6.58 6.09 5.63 5.20 9.23 8.54 7.90 7.31 6.75 6.24 5.76 5.31 4.88 8.83 8.15 7.53 6.95 6.40 5.90 5.42 4.97 4.55 8.39 7.73 7.12 6.55 6.02 5.53 5.07 4.63 4.23 7.95 7.31 6.71 6.16 5.64 5.16 4.71 4.29 3.90 7.49 6.87 6.29 5.76 5.26 4.79 4.36 3.95 3.57 7.02 6.42 5.87 5.35 4.87 4.42 4.00 3.61 3.23 6.60 6.02 5.49 4.99 4.52 4.09 3.68 3.30 2.94 6.23 5.67 5.15 4.67 4.22 3.80 3.40 3.03 2.68 5.86 5.31 4.81 4.34 3.91 3.50 3.12 2.76 2.43

WING AND ENGINE ANTI-ICE ON

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 53000 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 9.70 8.86 8.09 7.38 6.72 6.10 5.52 4.99 4.49 4.02 3.58 9.68 8.85 8.08 7.36 6.70 6.08 5.51 4.97 4.48 4.01 3.57 9.66 8.83 8.06 7.35 6.69 6.07 5.49 4.96 4.46 4.00 3.56 9.65 8.82 8.05 7.33 6.67 6.06 5.48 4.95 4.45 3.99 3.55 9.63 8.80 8.03 7.32 6.66 6.04 5.47 4.93 4.44 3.97 3.54 9.61 8.78 8.02 7.30 6.64 6.03 5.45 4.92 4.43 3.96 3.53 9.59 8.77 8.00 7.29 6.63 6.01 5.44 4.91 4.41 3.95 3.51 9.58 8.75 7.98 7.27 6.61 6.00 5.43 4.90 4.40 3.94 3.50 9.56 8.73 7.97 7.26 6.60 5.99 5.41 4.88 4.39 3.93 3.49 9.54 8.72 7.95 7.24 6.59 5.97 5.40 4.87 4.38 3.91 3.48

5-30 Copyright © by Embraer. Refer to cover page for details.

Page 8

Approach

REVISION 21

AOM-1502-003

SAT

(°C)

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

APPROACH CLIMB GRADIENT (%) EMBRAER 170 – CF34-8 ENGINES LANDING FLAP 5 – APPROACH FLAP 2 Altitude: 3000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44

53000 11.26 11.24 11.22 11.20 11.19 11.17 11.16 11.14 11.13 11.12 11.04 11.03 11.01 10.64 10.25 9.86 9.44 9.01 8.57 8.12 7.68 7.24 6.80

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 10.44 9.68 8.99 8.35 7.75 7.19 6.67 6.19 5.73 5.30 10.42 9.67 8.97 8.33 7.74 7.18 6.66 6.17 5.72 5.29 10.41 9.65 8.96 8.32 7.72 7.17 6.65 6.16 5.70 5.28 10.39 9.64 8.95 8.31 7.71 7.16 6.64 6.15 5.69 5.26 10.37 9.62 8.93 8.29 7.70 7.14 6.63 6.14 5.68 5.25 10.36 9.61 8.92 8.28 7.69 7.13 6.61 6.13 5.67 5.24 10.34 9.60 8.90 8.27 7.67 7.12 6.60 6.12 5.66 5.23 10.33 9.58 8.89 8.25 7.66 7.11 6.59 6.11 5.65 5.23 10.32 9.57 8.88 8.24 7.65 7.09 6.58 6.09 5.64 5.22 10.31 9.55 8.86 8.23 7.63 7.08 6.57 6.08 5.63 5.21 10.23 9.48 8.79 8.16 7.57 7.01 6.50 6.02 5.57 5.14 10.22 9.47 8.77 8.14 7.55 7.00 6.48 6.00 5.55 5.12 10.21 9.46 8.77 8.13 7.54 6.98 6.47 5.99 5.54 5.11 9.85 9.11 8.44 7.82 7.23 6.69 6.18 5.71 5.27 4.85 9.47 8.75 8.09 7.49 6.92 6.39 5.89 5.43 4.99 4.59 9.10 8.39 7.74 7.14 6.58 6.06 5.57 5.12 4.70 4.30 8.68 7.99 7.35 6.76 6.22 5.71 5.23 4.79 4.37 3.98 8.27 7.59 6.96 6.39 5.85 5.36 4.89 4.46 4.06 3.67 7.85 7.18 6.57 6.01 5.49 5.01 4.55 4.13 3.74 3.36 7.43 6.78 6.19 5.64 5.13 4.66 4.22 3.80 3.42 3.05 7.00 6.38 5.80 5.27 4.77 4.31 3.88 3.48 3.10 2.74 6.58 5.98 5.42 4.90 4.41 3.96 3.54 3.15 2.78 2.44 6.16 5.58 5.03 4.53 4.06 3.61 3.21 2.82 2.47 2.13

WING AND ENGINE ANTI-ICE ON SAT

(°C)

AOM-1502-003

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 53000 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 9.06 8.25 7.50 6.81 6.18 5.58 5.03 4.52 4.03 3.58 3.15 9.04 8.23 7.48 6.79 6.16 5.57 5.02 4.50 4.02 3.57 3.14 9.02 8.21 7.47 6.78 6.15 5.56 5.01 4.49 4.01 3.55 3.13 9.00 8.20 7.45 6.77 6.13 5.54 4.99 4.48 4.00 3.54 3.12 8.98 8.18 7.44 6.75 6.12 5.53 4.98 4.47 3.98 3.53 3.11 8.97 8.16 7.42 6.74 6.11 5.52 4.97 4.45 3.97 3.52 3.09 8.95 8.15 7.41 6.72 6.09 5.50 4.95 4.44 3.96 3.51 3.08 8.93 8.13 7.39 6.71 6.08 5.49 4.94 4.43 3.95 3.50 3.07 8.91 8.12 7.38 6.69 6.06 5.48 4.93 4.42 3.94 3.48 3.06 8.90 8.10 7.36 6.68 6.05 5.46 4.91 4.40 3.92 3.47 3.05

5-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Approach

Page 9

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

APPROACH CLIMB GRADIENT (%) EMBRAER 170 – CF34-8 ENGINES LANDING FLAP 5 – APPROACH FLAP 2 Altitude: 4000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42

WEIGHT (lb) 53000 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 10.62 9.84 9.12 8.44 7.82 7.24 6.70 6.19 5.72 5.28 4.87 10.60 9.82 9.10 8.43 7.80 7.22 6.68 6.18 5.71 5.27 4.86 10.58 9.80 9.08 8.41 7.79 7.21 6.67 6.17 5.70 5.26 4.85 10.56 9.78 9.06 8.39 7.77 7.20 6.66 6.16 5.69 5.25 4.84 10.55 9.76 9.04 8.37 7.76 7.18 6.65 6.15 5.68 5.24 4.83 10.53 9.75 9.03 8.36 7.74 7.17 6.63 6.13 5.67 5.23 4.81 10.52 9.74 9.02 8.35 7.73 7.16 6.62 6.12 5.65 5.21 4.80 10.50 9.72 9.00 8.34 7.72 7.14 6.61 6.11 5.64 5.20 4.79 10.49 9.71 8.99 8.32 7.70 7.13 6.59 6.10 5.63 5.19 4.78 10.47 9.69 8.97 8.30 7.69 7.12 6.58 6.08 5.62 5.18 4.77 10.45 9.67 8.95 8.29 7.67 7.10 6.57 6.07 5.60 5.17 4.76 10.40 9.63 8.92 8.26 7.66 7.09 6.55 6.06 5.59 5.16 4.75 10.10 9.34 8.64 7.98 7.38 6.82 6.30 5.81 5.36 4.93 4.52 9.75 9.01 8.32 7.69 7.10 6.55 6.04 5.56 5.11 4.69 4.29 9.40 8.68 8.01 7.38 6.80 6.26 5.75 5.28 4.84 4.42 4.03 9.04 8.32 7.66 7.04 6.47 5.93 5.43 4.96 4.53 4.12 3.74 8.67 7.97 7.31 6.70 6.13 5.60 5.11 4.65 4.22 3.82 3.44 8.26 7.57 6.92 6.33 5.78 5.26 4.78 4.33 3.91 3.52 3.15 7.85 7.16 6.53 5.95 5.42 4.92 4.45 4.02 3.61 3.22 2.86 7.44 6.77 6.15 5.58 5.06 4.57 4.12 3.70 3.30 2.92 2.57 7.04 6.39 5.78 5.23 4.71 4.23 3.78 3.37 2.98 2.62 2.28 6.64 6.00 5.40 4.86 4.36 3.89 3.45 3.04 2.67 2.31 1.98

WING AND ENGINE ANTI-ICE ON

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 53000 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 8.41 7.64 6.92 6.26 5.64 5.07 4.53 4.03 3.57 3.13 2.72 8.40 7.63 6.92 6.25 5.63 5.06 4.52 4.03 3.56 3.12 2.71 8.39 7.62 6.91 6.24 5.63 5.06 4.52 4.02 3.55 3.12 2.71 8.37 7.61 6.90 6.23 5.62 5.05 4.51 4.01 3.55 3.11 2.70 8.36 7.59 6.88 6.22 5.60 5.03 4.50 4.00 3.53 3.10 2.69 8.34 7.57 6.86 6.20 5.59 5.02 4.48 3.99 3.52 3.09 2.68 8.32 7.55 6.84 6.18 5.57 5.00 4.47 3.97 3.51 3.08 2.67 8.30 7.53 6.82 6.16 5.55 4.98 4.45 3.96 3.50 3.06 2.66 8.28 7.51 6.80 6.14 5.54 4.97 4.44 3.95 3.49 3.05 2.65 8.22 7.46 6.76 6.11 5.50 4.94 4.42 3.93 3.47 3.04 2.64

5-30 Copyright © by Embraer. Refer to cover page for details.

Page 10

Approach

REVISION 21

AOM-1502-003

SAT

(°C)

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

APPROACH CLIMB GRADIENT (%) EMBRAER 170 – CF34-8 ENGINES LANDING FLAP 5 – APPROACH FLAP 2 Altitude: 5000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40

WEIGHT (lb) 53000 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 10.06 9.29 8.58 7.93 7.33 6.77 6.25 5.77 5.32 4.89 4.49 10.04 9.27 8.57 7.92 7.32 6.76 6.24 5.76 5.30 4.88 4.48 10.02 9.26 8.55 7.90 7.30 6.75 6.23 5.74 5.29 4.87 4.47 10.01 9.24 8.54 7.89 7.29 6.73 6.22 5.73 5.28 4.86 4.46 9.99 9.23 8.52 7.88 7.28 6.72 6.20 5.72 5.27 4.85 4.45 9.97 9.21 8.51 7.86 7.27 6.71 6.19 5.71 5.26 4.84 4.44 9.95 9.20 8.50 7.85 7.25 6.70 6.18 5.70 5.25 4.83 4.43 9.94 9.18 8.48 7.84 7.24 6.69 6.17 5.69 5.24 4.82 4.42 9.93 9.17 8.47 7.82 7.23 6.67 6.16 5.68 5.23 4.80 4.41 9.85 9.10 8.41 7.78 7.19 6.64 6.13 5.65 5.21 4.79 4.40 9.75 9.01 8.33 7.70 7.12 6.57 6.06 5.59 5.15 4.73 4.34 9.57 8.84 8.16 7.54 6.95 6.41 5.90 5.43 4.99 4.57 4.18 9.27 8.55 7.88 7.26 6.69 6.16 5.66 5.20 4.76 4.35 3.96 8.94 8.23 7.57 6.97 6.41 5.89 5.40 4.94 4.51 4.11 3.73 8.59 7.89 7.24 6.65 6.10 5.58 5.10 4.65 4.23 3.84 3.46 8.25 7.55 6.91 6.32 5.78 5.28 4.81 4.37 3.95 3.57 3.20 7.89 7.21 6.58 6.00 5.47 4.98 4.52 4.08 3.68 3.30 2.94 7.53 6.86 6.25 5.68 5.16 4.68 4.22 3.80 3.40 3.03 2.68 7.16 6.51 5.91 5.36 4.85 4.37 3.92 3.51 3.12 2.76 2.41 6.80 6.16 5.57 5.03 4.53 4.06 3.63 3.22 2.84 2.49 2.15 6.43 5.81 5.23 4.70 4.21 3.75 3.33 2.93 2.56 2.21 1.89

WING AND ENGINE ANTI-ICE ON SAT

(°C)

AOM-1502-003

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 53000 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 7.83 7.09 6.39 5.75 5.16 4.61 4.10 3.62 3.17 2.74 2.35 7.82 7.08 6.38 5.74 5.15 4.60 4.09 3.61 3.17 2.75 2.35 7.81 7.06 6.37 5.73 5.14 4.59 4.08 3.60 3.16 2.74 2.35 7.78 7.04 6.35 5.71 5.12 4.58 4.06 3.59 3.14 2.73 2.33 7.76 7.02 6.33 5.69 5.11 4.56 4.05 3.57 3.13 2.71 2.32 7.74 7.00 6.31 5.68 5.09 4.54 4.03 3.56 3.12 2.70 2.31 7.72 6.98 6.29 5.66 5.07 4.53 4.02 3.55 3.10 2.69 2.29 7.69 6.96 6.27 5.64 5.06 4.51 4.00 3.53 3.09 2.67 2.28 7.61 6.87 6.19 5.57 4.99 4.45 3.94 3.47 3.03 2.62 2.23 7.51 6.78 6.11 5.49 4.91 4.37 3.87 3.41 2.97 2.56 2.17

5-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Approach

Page 11

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

APPROACH CLIMB GRADIENT (%) EMBRAER 170 – CF34-8 ENGINES LANDING FLAP FULL – APPROACH FLAP 4 Altitude: Sea Level ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 48 50

53000 12.12 12.10 12.07 12.05 12.02 12.00 11.98 11.95 11.93 11.90 11.88 11.86 11.83 11.81 11.77 11.75 11.26 10.70 10.17 9.63 9.10 8.69 8.28 7.87 7.46 7.06

55000 11.22 11.19 11.17 11.14 11.12 11.09 11.07 11.05 11.02 11.00 10.97 10.95 10.93 10.90 10.88 10.85 10.38 9.85 9.34 8.83 8.32 7.93 7.54 7.15 6.76 6.37

WEIGHT (lb) 57000 59000 61000 63000 65000 67000 69000 71000 73000 10.38 9.61 8.89 8.22 7.60 7.01 6.46 5.94 5.46 10.36 9.59 8.87 8.20 7.58 6.99 6.44 5.93 5.44 10.33 9.56 8.85 8.18 7.56 6.97 6.43 5.91 5.43 10.31 9.54 8.83 8.16 7.54 6.95 6.41 5.89 5.41 10.29 9.52 8.81 8.14 7.52 6.94 6.39 5.88 5.40 10.27 9.50 8.79 8.12 7.50 6.92 6.37 5.86 5.38 10.24 9.48 8.77 8.10 7.48 6.90 6.36 5.85 5.37 10.22 9.45 8.74 8.08 7.46 6.88 6.34 5.83 5.35 10.20 9.43 8.72 8.06 7.44 6.86 6.32 5.81 5.34 10.17 9.41 8.70 8.04 7.42 6.84 6.30 5.80 5.32 10.15 9.39 8.68 8.02 7.40 6.83 6.29 5.78 5.31 10.13 9.37 8.66 8.00 7.38 6.81 6.27 5.77 5.29 10.10 9.34 8.64 7.98 7.37 6.79 6.26 5.75 5.28 10.08 9.32 8.62 7.96 7.35 6.77 6.23 5.72 5.24 10.06 9.30 8.60 7.94 7.33 6.75 6.20 5.69 5.21 10.04 9.28 8.58 7.92 7.31 6.73 6.18 5.67 5.19 9.58 8.83 8.14 7.49 6.89 6.33 5.80 5.30 4.83 9.07 8.35 7.68 7.06 6.47 5.93 5.41 4.93 4.48 8.58 7.88 7.23 6.62 6.06 5.52 5.02 4.55 4.11 8.09 7.41 6.78 6.19 5.64 5.12 4.62 4.16 3.73 7.61 6.95 6.33 5.76 5.23 4.73 4.26 3.82 3.40 7.23 6.59 5.99 5.43 4.91 4.42 3.96 3.53 3.12 6.86 6.23 5.65 5.10 4.59 4.12 3.67 3.24 2.85 6.49 5.87 5.30 4.77 4.28 3.81 3.37 2.96 2.57 6.11 5.52 4.96 4.45 3.96 3.50 3.08 2.67 2.29 5.74 5.16 4.62 4.12 3.65 3.20 2.78 2.39 2.02

WING AND ENGINE ANTI-ICE ON

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 53000 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 10.33 9.44 8.61 7.84 7.13 6.47 5.85 5.27 4.73 4.21 3.73 10.36 9.46 8.63 7.86 7.15 6.49 5.87 5.29 4.74 4.23 3.74 10.36 9.46 8.63 7.86 7.15 6.49 5.87 5.29 4.74 4.22 3.74 10.33 9.44 8.61 7.84 7.13 6.47 5.85 5.27 4.72 4.21 3.73 10.31 9.41 8.59 7.82 7.11 6.45 5.83 5.25 4.70 4.19 3.71 10.29 9.39 8.56 7.80 7.09 6.43 5.81 5.23 4.69 4.17 3.70 10.27 9.37 8.54 7.78 7.07 6.40 5.79 5.21 4.67 4.16 3.68 10.24 9.35 8.52 7.75 7.04 6.38 5.77 5.19 4.65 4.14 3.66 10.22 9.32 8.50 7.73 7.02 6.36 5.75 5.17 4.63 4.12 3.65 10.20 9.30 8.47 7.71 7.00 6.34 5.73 5.15 4.61 4.11 3.63

5-30 Copyright © by Embraer. Refer to cover page for details.

Page 12

Approach

REVISION 21

AOM-1502-003

SAT

(°C)

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

APPROACH CLIMB GRADIENT (%) EMBRAER 170 – CF34-8 ENGINES LANDING FLAP FULL – APPROACH FLAP 4 Altitude: 1000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 48

53000 11.70 11.68 11.66 11.65 11.63 11.61 11.59 11.57 11.55 11.54 11.52 11.51 11.32 11.30 11.27 10.79 10.29 9.80 9.30 8.81 8.32 7.83 7.40 7.03 6.66

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 10.81 9.99 9.24 8.53 7.88 7.27 6.70 6.17 5.67 5.20 10.79 9.98 9.22 8.52 7.86 7.26 6.69 6.16 5.66 5.19 10.78 9.96 9.20 8.50 7.85 7.24 6.68 6.14 5.65 5.18 10.76 9.94 9.19 8.49 7.84 7.23 6.66 6.13 5.63 5.17 10.74 9.93 9.17 8.47 7.82 7.22 6.65 6.12 5.62 5.15 10.72 9.91 9.16 8.46 7.81 7.20 6.64 6.11 5.61 5.14 10.70 9.89 9.14 8.44 7.79 7.19 6.62 6.10 5.60 5.13 10.69 9.87 9.12 8.43 7.78 7.17 6.61 6.08 5.59 5.12 10.67 9.86 9.11 8.41 7.76 7.16 6.60 6.07 5.58 5.11 10.65 9.84 9.09 8.40 7.75 7.15 6.59 6.06 5.56 5.10 10.64 9.83 9.08 8.38 7.74 7.13 6.57 6.05 5.55 5.09 10.63 9.82 9.07 8.37 7.72 7.12 6.56 6.03 5.54 5.08 10.45 9.65 8.91 8.22 7.58 6.98 6.42 5.89 5.40 4.94 10.43 9.63 8.89 8.20 7.56 6.96 6.40 5.87 5.38 4.92 10.41 9.61 8.87 8.18 7.54 6.94 6.38 5.86 5.36 4.90 9.93 9.15 8.43 7.76 7.14 6.55 6.01 5.49 5.01 4.55 9.46 8.70 8.00 7.34 6.73 6.16 5.63 5.12 4.65 4.21 8.99 8.25 7.56 6.92 6.33 5.77 5.25 4.76 4.30 3.86 8.52 7.79 7.13 6.51 5.93 5.39 4.87 4.39 3.94 3.52 8.05 7.34 6.69 6.09 5.53 5.00 4.50 4.03 3.59 3.17 7.58 6.89 6.26 5.67 5.13 4.61 4.13 3.68 3.26 2.86 7.11 6.45 5.83 5.26 4.73 4.23 3.77 3.33 2.92 2.54 6.70 6.05 5.45 4.89 4.37 3.89 3.44 3.02 2.63 2.25 6.34 5.71 5.12 4.58 4.07 3.60 3.16 2.75 2.36 2.00 5.99 5.37 4.80 4.27 3.77 3.31 2.88 2.48 2.10 1.74

WING AND ENGINE ANTI-ICE ON SAT

(°C)

AOM-1502-003

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 53000 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 9.96 9.07 8.26 7.51 6.81 6.16 5.56 4.99 4.46 3.96 3.50 9.96 9.07 8.26 7.51 6.81 6.16 5.56 4.99 4.46 3.97 3.50 9.94 9.06 8.24 7.49 6.80 6.15 5.54 4.98 4.45 3.95 3.49 9.92 9.04 8.23 7.48 6.78 6.13 5.53 4.97 4.44 3.94 3.47 9.90 9.02 8.21 7.46 6.77 6.12 5.52 4.95 4.42 3.93 3.46 9.88 9.00 8.19 7.44 6.75 6.10 5.50 4.94 4.41 3.91 3.45 9.86 8.98 8.17 7.43 6.73 6.09 5.49 4.92 4.40 3.90 3.44 9.84 8.96 8.15 7.41 6.72 6.07 5.47 4.91 4.38 3.89 3.42 9.82 8.94 8.14 7.39 6.70 6.06 5.46 4.90 4.37 3.87 3.41 9.80 8.92 8.12 7.38 6.69 6.04 5.44 4.88 4.36 3.86 3.40

5-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Approach

Page 13

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

APPROACH CLIMB GRADIENT (%) EMBRAER 170 – CF34-8 ENGINES LANDING FLAP FULL – APPROACH FLAP 4 Altitude: 2000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46

53000 11.05 11.03 11.02 11.00 10.99 10.97 10.96 10.94 10.93 10.92 10.90 10.79 10.76 10.74 10.35 9.96 9.52 9.05 8.59 8.08 7.57 7.09 6.62 6.16

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 10.19 9.40 8.67 7.99 7.36 6.77 6.22 5.71 5.23 4.78 10.17 9.38 8.65 7.98 7.35 6.76 6.21 5.70 5.22 4.77 10.16 9.37 8.64 7.96 7.33 6.75 6.20 5.69 5.21 4.76 10.15 9.36 8.63 7.95 7.32 6.74 6.19 5.68 5.20 4.75 10.13 9.35 8.62 7.94 7.31 6.73 6.18 5.67 5.19 4.73 10.12 9.33 8.61 7.93 7.30 6.72 6.17 5.66 5.18 4.72 10.10 9.32 8.59 7.92 7.29 6.70 6.16 5.65 5.16 4.71 10.09 9.31 8.58 7.90 7.27 6.69 6.14 5.63 5.15 4.70 10.08 9.29 8.56 7.89 7.26 6.68 6.13 5.62 5.14 4.69 10.06 9.28 8.55 7.87 7.25 6.66 6.12 5.61 5.13 4.68 10.05 9.26 8.53 7.86 7.23 6.65 6.10 5.60 5.12 4.67 9.94 9.16 8.44 7.77 7.14 6.56 6.02 5.52 5.04 4.59 9.92 9.14 8.42 7.75 7.13 6.55 6.01 5.50 5.02 4.58 9.90 9.13 8.41 7.75 7.13 6.55 6.00 5.49 5.01 4.56 9.53 8.76 8.06 7.41 6.80 6.23 5.69 5.19 4.72 4.28 9.15 8.40 7.70 7.06 6.46 5.90 5.37 4.88 4.42 3.99 8.73 7.99 7.31 6.68 6.09 5.54 5.03 4.55 4.10 3.68 8.28 7.56 6.89 6.27 5.69 5.15 4.66 4.19 3.76 3.34 7.83 7.12 6.47 5.86 5.29 4.77 4.29 3.83 3.41 3.01 7.35 6.66 6.03 5.44 4.89 4.38 3.91 3.46 3.05 2.66 6.86 6.20 5.59 5.02 4.49 3.99 3.53 3.09 2.68 2.30 6.40 5.76 5.17 4.62 4.10 3.62 3.17 2.75 2.35 1.98 5.96 5.34 4.77 4.24 3.74 3.28 2.84 2.44 2.05 1.69 5.51 4.92 4.37 3.86 3.38 2.93 2.52 2.12 1.75 1.41

WING AND ENGINE ANTI-ICE ON

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 53000 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 9.33 8.48 7.69 6.97 6.29 5.66 5.08 4.54 4.03 3.55 3.10 9.32 8.46 7.68 6.95 6.28 5.65 5.06 4.52 4.01 3.54 3.09 9.30 8.45 7.66 6.94 6.26 5.63 5.05 4.51 4.00 3.52 3.08 9.28 8.43 7.65 6.92 6.25 5.62 5.04 4.50 3.99 3.51 3.06 9.27 8.41 7.63 6.91 6.23 5.61 5.03 4.48 3.98 3.50 3.05 9.25 8.40 7.62 6.89 6.22 5.59 5.01 4.47 3.96 3.49 3.04 9.23 8.38 7.60 6.88 6.21 5.58 5.00 4.46 3.95 3.48 3.03 9.21 8.37 7.58 6.86 6.19 5.57 4.99 4.45 3.94 3.46 3.02 9.20 8.35 7.57 6.85 6.18 5.55 4.97 4.43 3.93 3.45 3.01 9.18 8.33 7.55 6.83 6.16 5.54 4.96 4.42 3.92 3.44 2.99

5-30 Copyright © by Embraer. Refer to cover page for details.

Page 14

Approach

REVISION 21

AOM-1502-003

SAT

(°C)

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

APPROACH CLIMB GRADIENT (%) EMBRAER 170 – CF34-8 ENGINES LANDING FLAP FULL – APPROACH FLAP 4 Altitude: 3000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44

WEIGHT (lb) 53000 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 10.39 9.56 8.80 8.09 7.44 6.83 6.26 5.73 5.24 4.77 4.33 10.37 9.54 8.78 8.08 7.43 6.82 6.25 5.72 5.22 4.76 4.32 10.36 9.53 8.77 8.07 7.41 6.80 6.24 5.71 5.21 4.75 4.31 10.34 9.51 8.75 8.05 7.40 6.79 6.22 5.69 5.20 4.73 4.30 10.33 9.50 8.74 8.04 7.38 6.78 6.21 5.68 5.19 4.72 4.28 10.31 9.48 8.73 8.02 7.37 6.76 6.20 5.67 5.17 4.71 4.27 10.30 9.47 8.71 8.01 7.36 6.75 6.19 5.66 5.16 4.70 4.26 10.28 9.46 8.70 8.00 7.35 6.74 6.18 5.65 5.16 4.69 4.25 10.27 9.44 8.69 7.99 7.34 6.74 6.17 5.64 5.15 4.68 4.24 10.25 9.43 8.67 7.98 7.33 6.72 6.16 5.63 5.14 4.67 4.23 10.18 9.36 8.61 7.91 7.27 6.67 6.10 5.58 5.08 4.62 4.18 10.15 9.34 8.59 7.89 7.25 6.65 6.09 5.56 5.07 4.61 4.17 10.14 9.32 8.57 7.88 7.23 6.63 6.07 5.55 5.06 4.60 4.16 9.77 8.97 8.24 7.55 6.92 6.33 5.78 5.26 4.78 4.33 3.90 9.40 8.61 7.89 7.22 6.60 6.02 5.47 4.97 4.49 4.05 3.63 9.00 8.23 7.52 6.87 6.27 5.70 5.17 4.67 4.20 3.76 3.35 8.60 7.84 7.15 6.51 5.92 5.36 4.84 4.35 3.89 3.45 3.04 8.19 7.46 6.78 6.15 5.57 5.02 4.51 4.02 3.57 3.14 2.74 7.75 7.03 6.37 5.75 5.18 4.65 4.15 3.68 3.24 2.82 2.43 7.31 6.60 5.96 5.36 4.80 4.28 3.79 3.33 2.90 2.50 2.12 6.86 6.18 5.55 4.96 4.42 3.91 3.44 2.99 2.57 2.18 1.81 6.42 5.75 5.14 4.57 4.04 3.54 3.08 2.65 2.24 1.86 1.50 5.98 5.33 4.73 4.17 3.65 3.17 2.72 2.30 1.91 1.54 1.19

WING AND ENGINE ANTI-ICE ON SAT

(°C)

AOM-1502-003

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 53000 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 8.66 7.83 7.08 6.39 5.74 5.14 4.58 4.05 3.55 3.09 2.65 8.64 7.82 7.07 6.37 5.73 5.12 4.56 4.04 3.54 3.07 2.64 8.63 7.81 7.05 6.36 5.71 5.11 4.55 4.02 3.53 3.06 2.63 8.61 7.79 7.04 6.34 5.70 5.09 4.53 4.01 3.51 3.05 2.61 8.59 7.78 7.02 6.33 5.68 5.08 4.52 3.99 3.50 3.04 2.60 8.58 7.76 7.01 6.31 5.67 5.07 4.50 3.98 3.49 3.03 2.59 8.56 7.75 6.99 6.30 5.65 5.05 4.49 3.97 3.48 3.01 2.58 8.54 7.73 6.98 6.28 5.64 5.04 4.48 3.95 3.46 3.00 2.57 8.53 7.72 6.96 6.27 5.62 5.02 4.46 3.94 3.45 2.99 2.56 8.51 7.70 6.95 6.25 5.61 5.01 4.45 3.93 3.44 2.98 2.55

5-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Approach

Page 15

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

APPROACH CLIMB GRADIENT (%) EMBRAER 170 – CF34-8 ENGINES LANDING FLAP FULL – APPROACH FLAP 4 Altitude: 4000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42

WEIGHT (lb) 53000 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 9.76 8.96 8.22 7.53 6.89 6.30 5.75 5.24 4.77 4.32 3.90 9.74 8.94 8.20 7.52 6.88 6.29 5.74 5.23 4.75 4.31 3.89 9.72 8.92 8.18 7.50 6.87 6.27 5.73 5.22 4.74 4.29 3.87 9.70 8.90 8.17 7.48 6.85 6.26 5.71 5.21 4.73 4.28 3.86 9.68 8.88 8.15 7.47 6.84 6.25 5.70 5.19 4.72 4.27 3.85 9.66 8.87 8.13 7.45 6.82 6.24 5.69 5.18 4.70 4.26 3.84 9.64 8.85 8.12 7.44 6.81 6.22 5.68 5.17 4.70 4.25 3.83 9.63 8.84 8.11 7.43 6.80 6.21 5.67 5.16 4.68 4.24 3.82 9.62 8.83 8.10 7.42 6.79 6.20 5.65 5.15 4.67 4.22 3.80 9.61 8.82 8.08 7.41 6.78 6.19 5.64 5.14 4.66 4.21 3.79 9.55 8.77 8.05 7.38 6.75 6.17 5.63 5.12 4.65 4.20 3.78 9.47 8.69 7.97 7.31 6.69 6.11 5.58 5.08 4.61 4.17 3.75 9.23 8.46 7.74 7.07 6.46 5.88 5.35 4.85 4.39 3.95 3.54 8.88 8.12 7.42 6.76 6.15 5.59 5.07 4.58 4.13 3.71 3.30 8.53 7.79 7.09 6.45 5.85 5.30 4.78 4.31 3.87 3.45 3.06 8.18 7.45 6.77 6.14 5.55 5.01 4.50 4.03 3.59 3.18 2.79 7.83 7.11 6.45 5.83 5.25 4.72 4.22 3.76 3.32 2.91 2.53 7.43 6.73 6.08 5.47 4.91 4.39 3.90 3.44 3.01 2.61 2.23 7.03 6.35 5.71 5.12 4.56 4.05 3.57 3.12 2.70 2.30 1.93 6.63 5.97 5.34 4.76 4.22 3.72 3.25 2.80 2.39 2.00 1.64 6.24 5.58 4.97 4.40 3.87 3.38 2.92 2.49 2.09 1.71 1.36 5.84 5.20 4.60 4.05 3.53 3.05 2.60 2.18 1.79 1.42 1.06

WING AND ENGINE ANTI-ICE ON

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 53000 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 8.00 7.22 6.49 5.82 5.19 4.60 4.06 3.55 3.08 2.63 2.21 7.99 7.20 6.47 5.80 5.17 4.59 4.05 3.55 3.07 2.63 2.21 7.97 7.18 6.45 5.78 5.16 4.58 4.04 3.54 3.07 2.62 2.20 7.95 7.16 6.44 5.77 5.15 4.56 4.03 3.52 3.05 2.61 2.19 7.93 7.14 6.42 5.75 5.13 4.55 4.01 3.51 3.04 2.60 2.18 7.91 7.13 6.40 5.74 5.12 4.54 4.00 3.50 3.03 2.58 2.17 7.89 7.11 6.39 5.72 5.10 4.52 3.99 3.48 3.01 2.57 2.15 7.87 7.09 6.37 5.70 5.09 4.51 3.97 3.47 3.00 2.55 2.14 7.85 7.07 6.35 5.69 5.07 4.49 3.96 3.46 2.98 2.54 2.12 7.78 7.00 6.29 5.62 5.01 4.44 3.90 3.41 2.94 2.50 2.09

5-30 Copyright © by Embraer. Refer to cover page for details.

Page 16

Approach

REVISION 21

AOM-1502-003

SAT

(°C)

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

APPROACH CLIMB GRADIENT (%) EMBRAER 170 – CF34-8 ENGINES LANDING FLAP FULL – APPROACH FLAP 4 Altitude: 5000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40

WEIGHT (lb) 53000 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 9.17 8.40 7.69 7.03 6.42 5.86 5.32 4.82 4.35 3.91 3.50 9.16 8.38 7.68 7.02 6.41 5.84 5.31 4.81 4.34 3.90 3.49 9.14 8.37 7.66 7.00 6.39 5.83 5.29 4.80 4.33 3.89 3.48 9.13 8.36 7.65 6.99 6.38 5.81 5.28 4.78 4.32 3.88 3.46 9.11 8.34 7.63 6.98 6.37 5.80 5.27 4.77 4.30 3.87 3.45 9.10 8.33 7.62 6.96 6.35 5.78 5.25 4.76 4.29 3.85 3.44 9.08 8.31 7.60 6.95 6.34 5.77 5.24 4.74 4.28 3.84 3.43 9.07 8.30 7.59 6.93 6.32 5.76 5.23 4.73 4.27 3.83 3.42 9.02 8.26 7.56 6.91 6.31 5.74 5.22 4.72 4.26 3.82 3.41 8.92 8.16 7.47 6.82 6.22 5.66 5.14 4.66 4.20 3.77 3.37 8.82 8.07 7.38 6.73 6.14 5.58 5.07 4.58 4.13 3.71 3.31 8.65 7.91 7.22 6.58 5.99 5.44 4.93 4.45 4.00 3.58 3.18 8.38 7.65 6.96 6.33 5.74 5.20 4.69 4.21 3.77 3.35 2.96 8.06 7.33 6.66 6.04 5.46 4.92 4.42 3.96 3.52 3.12 2.73 7.73 7.02 6.36 5.75 5.18 4.65 4.16 3.70 3.26 2.86 2.48 7.40 6.71 6.06 5.46 4.90 4.38 3.89 3.43 3.01 2.60 2.23 7.04 6.36 5.72 5.13 4.59 4.08 3.60 3.16 2.74 2.34 1.97 6.68 6.01 5.39 4.81 4.27 3.78 3.31 2.87 2.46 2.08 1.72 6.31 5.66 5.05 4.49 3.96 3.48 3.02 2.59 2.19 1.81 1.46 5.95 5.31 4.71 4.16 3.65 3.17 2.73 2.31 1.91 1.54 1.19 5.59 4.96 4.38 3.84 3.34 2.87 2.44 2.02 1.64 1.27 0.93

WING AND ENGINE ANTI-ICE ON SAT

(°C) -8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 53000 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 7.40 6.64 5.94 5.29 4.69 4.13 3.60 3.11 2.65 2.22 1.81 7.38 6.62 5.92 5.28 4.68 4.12 3.60 3.10 2.64 2.21 1.80 7.36 6.60 5.91 5.26 4.66 4.10 3.58 3.09 2.63 2.20 1.79 7.34 6.58 5.89 5.24 4.64 4.08 3.56 3.07 2.62 2.18 1.78 7.31 6.56 5.87 5.22 4.62 4.06 3.55 3.06 2.60 2.17 1.76 7.29 6.54 5.85 5.20 4.60 4.05 3.53 3.04 2.58 2.15 1.75 7.27 6.52 5.83 5.18 4.58 4.03 3.51 3.02 2.57 2.14 1.74 7.25 6.50 5.81 5.16 4.56 4.01 3.49 3.00 2.55 2.12 1.72 7.15 6.40 5.72 5.08 4.48 3.93 3.42 2.93 2.48 2.06 1.66 7.05 6.31 5.62 4.99 4.40 3.85 3.34 2.86 2.41 1.99 1.60

AOM-1502-003

"

5-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Approach

Page 17

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

APPROACH AND LANDING SPEEDS EMBRAER 175 CF34-8 ENGINES

WEIGHT

VREF FLAP 5

VAC FLAP 2

(lb) 50000 52000 54000 56000 58000 60000 62000 64000 66000 68000 70000 72000 74000 76000 78000 80000 82000 84000 86000

(KIAS) 109 112 114 116 118 120 122 124 126 128 130 131 133 135 137 139 140 142 144

(KIAS) 130 133 135 138 140 143 145 147 150 152 154 156 158 161 163 165 167 169 171

VREF FLAP FULL (KIAS) 103 105 107 109 111 113 115 116 118 120 122 123 125 126 127 128 129 130 132

VAC FLAP 4

VFS

(KIAS) 115 117 119 121 124 126 128 130 132 134 136 138 140 142 143 145 147 149 151

(KIAS) 158 161 164 167 170 173 176 179 181 184 187 189 192 195 197 200 202 205 207

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Page 18

Approach

REVISION 21

AOM-1502-003

Without Ice Accretion

PERFORMANCE

AIRPLANE OPERATIONS MANUAL EMBRAER 175 CF34-8 ENGINES

AOM-1502-003

With Ice Accretion WEIGHT

VREF FLAP 5

VAC FLAP 2

(lb) 50000 52000 54000 56000 58000 60000 62000 64000 66000 68000 70000 72000 74000 76000 78000 80000 82000 84000 86000

(KIAS) 118 121 123 125 128 130 132 134 136 138 140 142 144 146 148 150 152 154 156

(KIAS) 130 133 135 138 140 143 145 147 150 152 154 156 158 161 163 165 167 169 171

VREF FLAP FULL (KIAS) 109 111 113 115 117 119 121 123 125 126 128 130 132 133 134 135 136 136 137

VAC FLAP 4

VFS

(KIAS) 115 117 119 121 124 126 128 130 132 134 136 138 140 142 143 145 147 149 151

(KIAS) 158 161 164 167 170 173 176 179 181 184 187 189 192 195 197 200 202 205 207

5-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Approach

Page 19

PERFORMANCE

AIRPLANE OPERATIONS MANUAL EMBRAER 175 CF34-8 ENGINES

CAT II OPERATION - With or Without Ice Accretion

(lb) 50000 52000 54000 56000 58000 60000 62000 64000 66000 68000 70000 72000 74000 76000 78000 80000 82000 84000 86000

VREF FLAP 5 (KIAS) 118 121 123 125 128 130 132 134 136 138 140 142 144 146 148 150 152 154 156

VAC FLAP 2 (KIAS) 130 133 135 138 140 143 145 147 150 152 154 156 158 161 163 165 167 169 171

VFS (KIAS) 158 161 164 167 170 173 176 179 181 184 187 189 192 195 197 200 202 205 207

5-30 Copyright © by Embraer. Refer to cover page for details.

Page 20

Approach

REVISION 21

AOM-1502-003

WEIGHT

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

FLAPS MANEUVERING SPEEDS SPEED (KIAS) 210 180 160 150 140 140 130

FLAP UP 1 2 3 4 5 FULL

NOTE: These speeds allow an inadvertent 15° overshoot beyond the normal 25° bank and provide at least 1.3 g margin over stick shaker speed. They are valid for all weights up to the maximum structural landing weight, with or without ice accretion. The speeds above may be used as reference for flaps extension and maneuvering. For flaps retraction refer to the Flap Retraction Speed Schedule presented on section 5-20 (Takeoff). The green dot on the PFD provides at least 1.3 g margin over stick shaker speed adjusted for the current airplane weight, thus it can also be used as the Flap Maneuvering Speed. !175 models, MAU Load 21.2 up to Load 25.4 - Pentium M or Load 25.3 - Pentium II

For airplanes equipped with Load version previous than Load 25.5.0.1, the green dot does not account for ice accretion. Therefore when flying in icing conditions (EICAS message STALL PROT ICE SPEED displayed) it is recommended to add 10 kt to the green dot. " !175 models, MAU Load 25.5.0.1 and on

For airplanes equipped with Load version 25.5.0.1 and on, the green dot accounts for ice accretion.

AOM-1502-003

"

5-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Approach

Page 21

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

APPROACH CLIMB GRADIENT !EMBRAER 175 Models

The Approach Climb Gradient tables show the gradients as function of temperature (°C) and weight (lb). The associated conditions are: – Approach Flaps: 2 or 4; – Gear UP; – Anti-Ice OFF without Ice Accretion or Wing and Engine Anti-ice ON with Ice Accretion; – ECS OFF;

5-30 Copyright © by Embraer. Refer to cover page for details.

Page 22

Approach

REVISION 21

AOM-1502-003

– One Engine Inoperative.

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

APPROACH CLIMB GRADIENT (%) EMBRAER 175 – CF34-8 ENGINES LANDING FLAP 5 – APPROACH FLAP 2 Altitude: Sea Level ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 48 50

55000 11.98 11.96 11.94 11.92 11.90 11.87 11.85 11.83 11.81 11.79 11.76 11.74 11.72 11.68 11.64 11.62 11.12 10.62 10.12 9.60 9.14 8.76 8.38 8.00 7.62 7.25

57000 11.15 11.13 11.11 11.09 11.07 11.05 11.02 11.00 10.98 10.96 10.94 10.92 10.90 10.86 10.82 10.79 10.32 9.84 9.36 8.86 8.43 8.07 7.70 7.34 6.98 6.62

WEIGHT (lb) 59000 61000 63000 65000 67000 69000 71000 73000 75000 10.37 9.66 9.00 8.38 7.81 7.27 6.77 6.30 5.85 10.35 9.64 8.98 8.36 7.79 7.26 6.76 6.29 5.85 10.34 9.63 8.96 8.35 7.78 7.24 6.75 6.28 5.84 10.32 9.61 8.95 8.33 7.76 7.23 6.73 6.27 5.83 10.30 9.59 8.93 8.32 7.74 7.22 6.72 6.25 5.81 10.28 9.57 8.91 8.30 7.73 7.20 6.70 6.24 5.80 10.26 9.55 8.90 8.28 7.71 7.18 6.69 6.22 5.78 10.24 9.54 8.88 8.27 7.70 7.17 6.67 6.21 5.77 10.22 9.52 8.86 8.25 7.68 7.15 6.66 6.19 5.76 10.20 9.50 8.84 8.23 7.67 7.14 6.64 6.18 5.74 10.18 9.48 8.83 8.22 7.65 7.13 6.63 6.17 5.73 10.17 9.47 8.82 8.21 7.64 7.11 6.62 6.15 5.71 10.15 9.45 8.80 8.20 7.63 7.10 6.61 6.14 5.70 10.10 9.39 8.72 8.11 7.54 7.02 6.53 6.07 5.63 10.05 9.35 8.69 8.08 7.51 6.98 6.48 6.01 5.57 10.03 9.33 8.67 8.06 7.50 6.96 6.47 6.00 5.56 9.57 8.89 8.25 7.65 7.10 6.58 6.09 5.64 5.21 9.12 8.45 7.83 7.25 6.70 6.20 5.72 5.27 4.85 8.66 8.00 7.40 6.83 6.31 5.82 5.36 4.92 4.52 8.18 7.55 6.97 6.42 5.92 5.45 5.01 4.60 4.21 7.78 7.18 6.62 6.10 5.62 5.16 4.73 4.33 3.95 7.43 6.85 6.30 5.79 5.32 4.87 4.45 4.06 3.69 7.08 6.51 5.98 5.48 5.02 4.58 4.17 3.79 3.43 6.73 6.18 5.65 5.17 4.72 4.29 3.89 3.52 3.17 6.39 5.84 5.33 4.85 4.41 3.99 3.61 3.24 2.90 6.04 5.50 5.00 4.53 4.10 3.70 3.32 2.97 2.64

WING AND ENGINE ANTI-ICE ON SAT

(°C)

AOM-1502-003

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 9.72 8.89 8.13 7.43 6.77 6.16 5.59 5.06 4.57 4.10 3.66 9.74 8.91 8.15 7.44 6.79 6.18 5.61 5.08 4.58 4.12 3.68 9.74 8.91 8.14 7.44 6.79 6.18 5.61 5.08 4.58 4.12 3.68 9.71 8.89 8.12 7.42 6.77 6.16 5.60 5.07 4.57 4.10 3.66 9.69 8.87 8.11 7.41 6.75 6.14 5.58 5.05 4.55 4.09 3.65 9.67 8.85 8.09 7.39 6.74 6.13 5.56 5.03 4.54 4.07 3.64 9.65 8.83 8.07 7.37 6.72 6.11 5.55 5.02 4.52 4.06 3.62 9.62 8.80 8.05 7.35 6.70 6.09 5.53 5.00 4.51 4.05 3.61 9.60 8.78 8.03 7.33 6.68 6.08 5.51 4.99 4.49 4.03 3.60 9.58 8.76 8.01 7.31 6.66 6.06 5.50 4.97 4.48 4.02 3.58

5-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Approach

Page 23

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

APPROACH CLIMB GRADIENT (%) EMBRAER 175 – CF34-8 ENGINES LANDING FLAP 5 – APPROACH FLAP 2 Altitude: 1000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 48

55000 11.61 11.59 11.58 11.56 11.55 11.53 11.52 11.50 11.48 11.47 11.45 11.44 11.25 11.22 11.20 10.72 10.25 9.78 9.30 8.83 8.39 7.95 7.56 7.21 6.86

57000 10.80 10.78 10.77 10.76 10.74 10.73 10.71 10.70 10.68 10.67 10.65 10.64 10.45 10.42 10.40 9.95 9.49 9.03 8.58 8.13 7.71 7.30 6.92 6.59 6.25

WEIGHT (lb) 59000 61000 63000 65000 67000 69000 71000 73000 75000 10.05 9.36 8.72 8.12 7.56 7.04 6.56 6.10 5.67 10.04 9.35 8.71 8.11 7.55 7.03 6.55 6.09 5.66 10.02 9.33 8.69 8.09 7.54 7.02 6.53 6.08 5.65 10.01 9.32 8.68 8.08 7.53 7.01 6.52 6.06 5.63 10.00 9.31 8.67 8.07 7.52 7.00 6.51 6.05 5.62 9.98 9.30 8.66 8.06 7.50 6.98 6.50 6.04 5.61 9.97 9.28 8.64 8.04 7.49 6.97 6.48 6.03 5.59 9.95 9.27 8.63 8.03 7.47 6.96 6.47 6.01 5.58 9.94 9.25 8.61 8.02 7.46 6.95 6.46 6.00 5.57 9.93 9.24 8.60 8.00 7.45 6.93 6.45 5.99 5.56 9.91 9.22 8.59 7.99 7.43 6.92 6.44 5.98 5.56 9.90 9.21 8.57 7.97 7.42 6.91 6.42 5.97 5.54 9.72 9.05 8.42 7.83 7.29 6.78 6.30 5.85 5.42 9.68 9.00 8.36 7.76 7.21 6.69 6.21 5.76 5.33 9.66 8.97 8.34 7.74 7.19 6.67 6.19 5.74 5.31 9.22 8.56 7.94 7.36 6.82 6.32 5.85 5.40 4.98 8.78 8.13 7.53 6.96 6.44 5.95 5.49 5.06 4.65 8.34 7.71 7.11 6.56 6.04 5.57 5.13 4.71 4.32 7.91 7.29 6.71 6.17 5.68 5.21 4.78 4.37 3.99 7.48 6.87 6.31 5.79 5.31 4.85 4.43 4.03 3.65 7.08 6.50 5.96 5.46 4.99 4.55 4.14 3.75 3.39 6.69 6.13 5.61 5.12 4.67 4.25 3.85 3.48 3.12 6.34 5.79 5.29 4.82 4.38 3.96 3.58 3.21 2.87 6.02 5.49 4.99 4.53 4.10 3.70 3.32 2.97 2.64 5.70 5.18 4.70 4.25 3.83 3.44 3.07 2.72 2.39

WING AND ENGINE ANTI-ICE ON

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 9.38 8.58 7.84 7.16 6.53 5.94 5.39 4.88 4.39 3.94 3.51 9.39 8.58 7.84 7.17 6.53 5.94 5.39 4.88 4.39 3.94 3.51 9.37 8.57 7.83 7.15 6.52 5.93 5.38 4.86 4.38 3.93 3.50 9.35 8.55 7.81 7.13 6.50 5.91 5.36 4.85 4.37 3.91 3.49 9.33 8.53 7.80 7.12 6.49 5.90 5.35 4.83 4.35 3.90 3.47 9.32 8.52 7.78 7.10 6.47 5.88 5.34 4.82 4.34 3.89 3.46 9.30 8.50 7.76 7.09 6.46 5.87 5.32 4.81 4.32 3.87 3.45 9.28 8.48 7.75 7.07 6.44 5.85 5.31 4.79 4.31 3.86 3.43 9.26 8.47 7.73 7.06 6.43 5.84 5.29 4.78 4.30 3.84 3.42 9.25 8.45 7.72 7.04 6.41 5.83 5.28 4.76 4.28 3.83 3.40

5-30 Copyright © by Embraer. Refer to cover page for details.

Page 24

Approach

REVISION 21

AOM-1502-003

SAT

(°C)

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

APPROACH CLIMB GRADIENT (%) EMBRAER 175 – CF34-8 ENGINES LANDING FLAP 5 – APPROACH FLAP 2 Altitude: 2000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46

55000 11.02 11.01 10.99 10.98 10.96 10.95 10.93 10.91 10.90 10.88 10.87 10.76 10.74 10.73 10.34 9.94 9.51 9.05 8.59 8.11 7.63 7.19 6.80 6.40

WEIGHT (lb) 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 10.24 9.52 8.85 8.23 7.65 7.11 6.61 6.14 5.70 5.28 10.23 9.50 8.84 8.22 7.64 7.10 6.60 6.13 5.68 5.27 10.21 9.49 8.83 8.21 7.63 7.09 6.59 6.12 5.67 5.26 10.20 9.48 8.81 8.20 7.62 7.08 6.58 6.10 5.66 5.24 10.18 9.46 8.80 8.18 7.61 7.07 6.57 6.09 5.65 5.23 10.17 9.45 8.79 8.17 7.59 7.06 6.55 6.08 5.64 5.22 10.15 9.44 8.77 8.16 7.58 7.05 6.54 6.07 5.63 5.21 10.14 9.42 8.76 8.15 7.57 7.03 6.53 6.06 5.62 5.20 10.12 9.41 8.75 8.13 7.56 7.02 6.52 6.05 5.61 5.19 10.11 9.39 8.73 8.12 7.55 7.01 6.51 6.04 5.60 5.18 10.09 9.38 8.72 8.11 7.54 7.00 6.50 6.03 5.58 5.17 9.99 9.28 8.62 8.01 7.44 6.91 6.41 5.94 5.49 5.08 9.97 9.26 8.60 7.99 7.42 6.89 6.39 5.92 5.48 5.07 9.95 9.24 8.59 7.98 7.41 6.88 6.38 5.91 5.48 5.06 9.58 8.88 8.23 7.63 7.06 6.54 6.05 5.59 5.16 4.75 9.19 8.50 7.86 7.27 6.71 6.20 5.72 5.27 4.84 4.44 8.79 8.11 7.49 6.91 6.36 5.86 5.38 4.93 4.51 4.12 8.35 7.69 7.08 6.51 5.98 5.49 5.03 4.59 4.19 3.80 7.91 7.27 6.68 6.12 5.60 5.12 4.67 4.25 3.86 3.49 7.45 6.83 6.25 5.72 5.22 4.75 4.32 3.91 3.53 3.17 6.98 6.38 5.83 5.31 4.83 4.38 3.96 3.57 3.19 2.84 6.56 5.98 5.45 4.95 4.49 4.05 3.64 3.26 2.90 2.56 6.19 5.63 5.11 4.63 4.18 3.76 3.36 2.99 2.64 2.32 5.82 5.27 4.77 4.30 3.87 3.46 3.08 2.72 2.39 2.07

WING AND ENGINE ANTI-ICE ON SAT

(°C)

AOM-1502-003

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 8.82 8.05 7.34 6.68 6.06 5.48 4.95 4.45 3.98 3.55 3.13 8.81 8.04 7.32 6.66 6.04 5.47 4.93 4.44 3.97 3.53 3.12 8.79 8.02 7.31 6.65 6.03 5.45 4.92 4.42 3.96 3.52 3.11 8.78 8.01 7.29 6.63 6.02 5.44 4.91 4.41 3.95 3.51 3.10 8.76 7.99 7.28 6.62 6.00 5.43 4.90 4.40 3.93 3.50 3.09 8.74 7.98 7.26 6.60 5.99 5.41 4.88 4.39 3.92 3.49 3.07 8.73 7.96 7.25 6.59 5.98 5.40 4.87 4.37 3.91 3.47 3.06 8.71 7.94 7.23 6.58 5.96 5.39 4.86 4.36 3.90 3.46 3.05 8.69 7.93 7.22 6.56 5.95 5.37 4.84 4.35 3.89 3.45 3.04 8.68 7.91 7.20 6.55 5.93 5.36 4.83 4.34 3.87 3.44 3.03

5-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Approach

Page 25

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

APPROACH CLIMB GRADIENT (%) EMBRAER 175 – CF34-8 ENGINES LANDING FLAP 5 – APPROACH FLAP 2 Altitude: 3000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 10.40 9.64 8.95 8.31 7.71 7.15 6.63 6.15 5.69 5.26 4.85 10.38 9.63 8.93 8.29 7.70 7.14 6.62 6.13 5.68 5.25 4.84 10.37 9.61 8.92 8.28 7.68 7.13 6.61 6.12 5.67 5.24 4.83 10.35 9.60 8.91 8.27 7.67 7.12 6.60 6.11 5.65 5.23 4.82 10.33 9.58 8.89 8.25 7.66 7.10 6.59 6.10 5.64 5.21 4.81 10.32 9.57 8.88 8.24 7.65 7.09 6.57 6.09 5.63 5.20 4.80 10.30 9.56 8.86 8.23 7.63 7.08 6.56 6.08 5.62 5.20 4.79 10.29 9.54 8.85 8.21 7.62 7.07 6.55 6.07 5.61 5.19 4.79 10.28 9.53 8.84 8.20 7.61 7.05 6.54 6.06 5.60 5.18 4.78 10.27 9.51 8.82 8.19 7.59 7.04 6.53 6.04 5.59 5.17 4.77 10.19 9.44 8.75 8.12 7.53 6.97 6.46 5.98 5.53 5.10 4.70 10.18 9.43 8.73 8.10 7.51 6.96 6.44 5.96 5.51 5.09 4.69 10.17 9.42 8.73 8.10 7.50 6.94 6.43 5.95 5.50 5.07 4.67 9.81 9.07 8.40 7.78 7.19 6.65 6.14 5.67 5.23 4.81 4.42 9.43 8.71 8.05 7.45 6.88 6.35 5.85 5.39 4.96 4.55 4.16 9.06 8.35 7.70 7.10 6.54 6.02 5.54 5.08 4.66 4.26 3.89 8.64 7.95 7.31 6.72 6.18 5.67 5.19 4.75 4.33 3.94 3.57 8.23 7.55 6.92 6.35 5.82 5.32 4.85 4.42 4.02 3.63 3.27 7.81 7.14 6.53 5.97 5.45 4.97 4.51 4.09 3.70 3.32 2.97 7.39 6.74 6.15 5.60 5.09 4.62 4.18 3.77 3.38 3.01 2.67 6.96 6.34 5.76 5.23 4.73 4.27 3.84 3.44 3.06 2.71 2.37 6.54 5.94 5.38 4.86 4.37 3.92 3.50 3.11 2.74 2.40 2.07 6.13 5.54 4.99 4.49 4.02 3.58 3.17 2.79 2.43 2.09 1.78

WING AND ENGINE ANTI-ICE ON

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 8.21 7.46 6.77 6.14 5.54 4.99 4.48 3.99 3.54 3.11 2.71 8.19 7.44 6.75 6.12 5.53 4.98 4.47 3.98 3.53 3.10 2.70 8.17 7.43 6.74 6.11 5.52 4.97 4.45 3.97 3.52 3.09 2.69 8.16 7.41 6.73 6.09 5.50 4.95 4.44 3.96 3.50 3.08 2.68 8.14 7.40 6.71 6.08 5.49 4.94 4.43 3.94 3.49 3.07 2.67 8.12 7.38 6.70 6.07 5.48 4.93 4.42 3.93 3.48 3.06 2.65 8.11 7.37 6.68 6.05 5.46 4.91 4.40 3.92 3.47 3.04 2.64 8.09 7.35 6.67 6.04 5.45 4.90 4.39 3.91 3.46 3.03 2.63 8.08 7.34 6.65 6.02 5.44 4.89 4.38 3.90 3.45 3.02 2.62 8.06 7.32 6.64 6.01 5.42 4.88 4.36 3.88 3.43 3.01 2.61

5-30 Copyright © by Embraer. Refer to cover page for details.

Page 26

Approach

REVISION 21

AOM-1502-003

SAT

(°C)

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

APPROACH CLIMB GRADIENT (%) EMBRAER 175 – CF34-8 ENGINES LANDING FLAP 5 – APPROACH FLAP 2 Altitude: 4000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 9.80 9.08 8.40 7.78 7.20 6.66 6.15 5.68 5.24 4.83 4.44 9.78 9.06 8.39 7.76 7.18 6.64 6.14 5.67 5.23 4.82 4.43 9.76 9.04 8.37 7.75 7.17 6.63 6.13 5.66 5.22 4.81 4.42 9.74 9.02 8.35 7.73 7.16 6.62 6.12 5.65 5.21 4.80 4.41 9.72 9.00 8.34 7.72 7.14 6.61 6.11 5.64 5.20 4.79 4.40 9.71 8.99 8.32 7.71 7.13 6.60 6.09 5.63 5.19 4.78 4.39 9.70 8.98 8.31 7.69 7.12 6.58 6.08 5.61 5.18 4.76 4.38 9.68 8.96 8.30 7.68 7.10 6.57 6.07 5.60 5.16 4.75 4.36 9.67 8.95 8.28 7.66 7.09 6.55 6.06 5.59 5.15 4.74 4.35 9.65 8.93 8.26 7.65 7.08 6.54 6.04 5.58 5.14 4.73 4.34 9.63 8.91 8.25 7.63 7.06 6.53 6.03 5.56 5.13 4.72 4.33 9.59 8.88 8.22 7.62 7.05 6.51 6.02 5.55 5.12 4.71 4.32 9.30 8.60 7.94 7.34 6.78 6.26 5.77 5.32 4.89 4.48 4.10 8.98 8.28 7.65 7.06 6.51 6.00 5.52 5.07 4.65 4.25 3.88 8.64 7.97 7.34 6.76 6.22 5.71 5.24 4.80 4.38 3.99 3.62 8.28 7.62 7.00 6.43 5.89 5.39 4.93 4.49 4.08 3.70 3.34 7.93 7.27 6.66 6.09 5.56 5.07 4.61 4.18 3.78 3.40 3.05 7.53 6.88 6.29 5.74 5.22 4.74 4.29 3.87 3.48 3.11 2.77 7.12 6.49 5.91 5.38 4.88 4.41 3.98 3.57 3.18 2.82 2.48 6.73 6.11 5.54 5.02 4.53 4.08 3.66 3.26 2.88 2.53 2.20 6.35 5.74 5.19 4.67 4.19 3.75 3.33 2.94 2.58 2.24 1.91 5.96 5.36 4.82 4.33 3.85 3.41 3.00 2.63 2.27 1.94 1.63

WING AND ENGINE ANTI-ICE ON SAT

(°C)

AOM-1502-003

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 7.60 6.88 6.22 5.60 5.03 4.49 3.99 3.53 3.09 2.68 2.30 7.59 6.88 6.21 5.60 5.02 4.48 3.99 3.52 3.09 2.68 2.29 7.58 6.87 6.21 5.59 5.02 4.48 3.98 3.52 3.08 2.67 2.28 7.57 6.86 6.19 5.58 5.01 4.47 3.97 3.51 3.07 2.66 2.27 7.55 6.84 6.18 5.56 4.99 4.46 3.96 3.49 3.06 2.65 2.26 7.53 6.82 6.16 5.55 4.98 4.44 3.95 3.48 3.05 2.64 2.25 7.51 6.80 6.14 5.53 4.96 4.43 3.93 3.47 3.04 2.63 2.24 7.49 6.78 6.12 5.51 4.95 4.41 3.92 3.46 3.03 2.62 2.23 7.47 6.76 6.10 5.50 4.93 4.40 3.91 3.45 3.01 2.61 2.22 7.42 6.72 6.07 5.46 4.90 4.38 3.89 3.43 3.00 2.60 2.21

5-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Approach

Page 27

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

APPROACH CLIMB GRADIENT (%) EMBRAER 175 – CF34-8 ENGINES LANDING FLAP 5 – APPROACH FLAP 2 Altitude: 5000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 9.25 8.54 7.89 7.29 6.73 6.21 5.73 5.28 4.85 4.46 4.08 9.23 8.53 7.88 7.28 6.72 6.20 5.72 5.26 4.84 4.44 4.07 9.22 8.51 7.86 7.26 6.71 6.19 5.70 5.25 4.83 4.43 4.05 9.20 8.50 7.85 7.25 6.70 6.18 5.69 5.24 4.82 4.42 4.04 9.19 8.48 7.84 7.24 6.68 6.16 5.68 5.23 4.81 4.41 4.04 9.17 8.47 7.82 7.23 6.67 6.15 5.67 5.22 4.80 4.40 4.03 9.16 8.46 7.81 7.21 6.66 6.14 5.66 5.21 4.79 4.39 4.02 9.14 8.44 7.80 7.20 6.65 6.13 5.65 5.20 4.78 4.38 4.01 9.13 8.43 7.78 7.19 6.63 6.12 5.64 5.19 4.77 4.37 3.99 9.06 8.37 7.74 7.15 6.60 6.09 5.61 5.17 4.75 4.36 3.98 8.97 8.29 7.66 7.08 6.53 6.02 5.55 5.11 4.69 4.30 3.93 8.80 8.12 7.50 6.91 6.37 5.86 5.39 4.95 4.53 4.14 3.77 8.51 7.84 7.22 6.65 6.12 5.62 5.16 4.72 4.31 3.92 3.56 8.19 7.53 6.93 6.37 5.85 5.36 4.90 4.47 4.07 3.69 3.33 7.85 7.20 6.61 6.06 5.54 5.07 4.62 4.19 3.80 3.42 3.07 7.52 6.87 6.28 5.75 5.24 4.77 4.33 3.91 3.53 3.16 2.82 7.17 6.54 5.96 5.43 4.94 4.48 4.04 3.64 3.26 2.90 2.56 6.82 6.21 5.64 5.12 4.64 4.18 3.76 3.36 2.99 2.64 2.31 6.47 5.87 5.32 4.81 4.33 3.89 3.47 3.08 2.72 2.38 2.05 6.12 5.53 4.99 4.49 4.02 3.59 3.18 2.80 2.45 2.11 1.80 5.77 5.19 4.66 4.17 3.71 3.29 2.89 2.52 2.18 1.85 1.54

WING AND ENGINE ANTI-ICE ON

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 7.05 6.35 5.71 5.12 4.57 4.06 3.58 3.13 2.70 2.31 1.93 7.04 6.34 5.70 5.11 4.57 4.05 3.58 3.13 2.71 2.31 1.94 7.02 6.33 5.69 5.10 4.55 4.04 3.56 3.12 2.70 2.31 1.94 7.00 6.31 5.67 5.08 4.54 4.02 3.55 3.10 2.69 2.29 1.92 6.98 6.29 5.65 5.07 4.52 4.01 3.53 3.09 2.67 2.28 1.91 6.96 6.27 5.64 5.05 4.51 3.99 3.52 3.08 2.66 2.27 1.89 6.94 6.25 5.62 5.03 4.49 3.98 3.51 3.06 2.65 2.25 1.88 6.92 6.23 5.60 5.02 4.47 3.97 3.49 3.05 2.63 2.24 1.87 6.83 6.15 5.53 4.95 4.41 3.90 3.43 2.99 2.58 2.19 1.82 6.75 6.07 5.45 4.87 4.34 3.83 3.37 2.93 2.52 2.13 1.77

5-30 Copyright © by Embraer. Refer to cover page for details.

Page 28

Approach

REVISION 21

AOM-1502-003

SAT

(°C)

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

APPROACH CLIMB GRADIENT (%) EMBRAER 175 – CF34-8 ENGINES LANDING FLAP FULL – APPROACH FLAP 4 Altitude: Sea Level ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 48 50

55000 11.19 11.16 11.14 11.11 11.09 11.06 11.04 11.02 10.99 10.97 10.94 10.92 10.90 10.87 10.85 10.82 10.35 9.82 9.31 8.80 8.29 7.90 7.51 7.12 6.73 6.34

WEIGHT (lb) 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 10.35 9.58 8.86 8.19 7.57 6.98 6.43 5.91 5.43 4.97 10.33 9.56 8.84 8.17 7.55 6.96 6.41 5.90 5.41 4.96 10.30 9.53 8.82 8.15 7.53 6.94 6.40 5.88 5.40 4.94 10.28 9.51 8.80 8.13 7.51 6.93 6.38 5.87 5.38 4.93 10.26 9.49 8.78 8.11 7.49 6.91 6.36 5.85 5.37 4.92 10.24 9.47 8.76 8.09 7.47 6.89 6.34 5.83 5.35 4.90 10.21 9.45 8.74 8.07 7.45 6.87 6.33 5.82 5.34 4.89 10.19 9.42 8.71 8.05 7.43 6.85 6.31 5.80 5.32 4.87 10.17 9.40 8.69 8.03 7.41 6.83 6.29 5.78 5.31 4.86 10.14 9.38 8.67 8.01 7.39 6.81 6.27 5.77 5.29 4.84 10.12 9.36 8.65 7.99 7.37 6.80 6.26 5.75 5.28 4.83 10.10 9.34 8.63 7.97 7.35 6.78 6.24 5.74 5.26 4.82 10.07 9.31 8.61 7.95 7.34 6.76 6.23 5.72 5.25 4.80 10.05 9.29 8.59 7.93 7.32 6.74 6.20 5.69 5.22 4.76 10.03 9.27 8.57 7.91 7.30 6.72 6.17 5.66 5.18 4.73 10.01 9.25 8.55 7.89 7.28 6.70 6.15 5.64 5.16 4.71 9.55 8.80 8.11 7.46 6.86 6.30 5.77 5.27 4.81 4.37 9.04 8.32 7.65 7.03 6.45 5.90 5.38 4.90 4.45 4.02 8.55 7.85 7.20 6.60 6.03 5.49 4.99 4.52 4.08 3.66 8.06 7.38 6.75 6.16 5.61 5.09 4.60 4.13 3.70 3.29 7.58 6.92 6.31 5.73 5.20 4.70 4.23 3.79 3.37 2.99 7.20 6.56 5.96 5.40 4.88 4.39 3.93 3.50 3.10 2.72 6.83 6.20 5.62 5.07 4.57 4.09 3.64 3.22 2.82 2.45 6.46 5.84 5.28 4.75 4.25 3.78 3.34 2.93 2.54 2.18 6.08 5.49 4.93 4.42 3.93 3.48 3.05 2.64 2.26 1.91 5.71 5.13 4.59 4.09 3.62 3.17 2.75 2.36 1.99 1.64

WING AND ENGINE ANTI-ICE ON SAT

(°C)

AOM-1502-003

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 9.41 8.58 7.81 7.10 6.44 5.82 5.24 4.70 4.18 3.70 3.25 9.43 8.60 7.84 7.12 6.46 5.84 5.26 4.71 4.20 3.71 3.26 9.43 8.60 7.83 7.12 6.46 5.84 5.26 4.71 4.19 3.71 3.26 9.41 8.58 7.81 7.10 6.44 5.82 5.24 4.69 4.18 3.70 3.25 9.38 8.56 7.79 7.08 6.42 5.80 5.22 4.67 4.16 3.68 3.23 9.36 8.53 7.77 7.06 6.40 5.78 5.20 4.66 4.15 3.67 3.22 9.34 8.51 7.75 7.04 6.38 5.76 5.18 4.64 4.13 3.65 3.20 9.32 8.49 7.73 7.02 6.35 5.74 5.16 4.62 4.11 3.64 3.19 9.29 8.47 7.70 6.99 6.33 5.72 5.14 4.60 4.10 3.62 3.17 9.27 8.45 7.68 6.97 6.31 5.70 5.12 4.59 4.08 3.60 3.16

5-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Approach

Page 29

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

APPROACH CLIMB GRADIENT (%) EMBRAER 175 – CF34-8 ENGINES LANDING FLAP FULL – APPROACH FLAP 4 Altitude: 1000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 48

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 10.78 9.96 9.21 8.50 7.85 7.24 6.67 6.14 5.64 5.17 4.73 10.76 9.95 9.19 8.49 7.84 7.23 6.66 6.13 5.63 5.16 4.72 10.75 9.93 9.17 8.47 7.82 7.21 6.65 6.12 5.62 5.15 4.71 10.73 9.91 9.16 8.46 7.81 7.20 6.63 6.10 5.60 5.14 4.70 10.71 9.90 9.14 8.44 7.79 7.19 6.62 6.09 5.59 5.13 4.69 10.69 9.88 9.13 8.43 7.78 7.17 6.61 6.08 5.58 5.11 4.67 10.67 9.86 9.11 8.41 7.76 7.16 6.60 6.07 5.57 5.10 4.66 10.66 9.84 9.09 8.40 7.75 7.15 6.58 6.05 5.56 5.09 4.65 10.64 9.83 9.08 8.38 7.73 7.13 6.57 6.04 5.55 5.08 4.64 10.62 9.81 9.06 8.37 7.72 7.12 6.56 6.03 5.54 5.07 4.63 10.61 9.80 9.05 8.36 7.71 7.10 6.54 6.02 5.52 5.06 4.62 10.60 9.79 9.04 8.34 7.69 7.09 6.53 6.01 5.51 5.05 4.61 10.42 9.62 8.88 8.19 7.55 6.95 6.39 5.87 5.37 4.91 4.48 10.40 9.60 8.86 8.17 7.53 6.93 6.37 5.85 5.35 4.89 4.45 10.38 9.58 8.84 8.15 7.51 6.91 6.35 5.83 5.33 4.87 4.43 9.90 9.12 8.40 7.73 7.11 6.53 5.98 5.46 4.98 4.53 4.10 9.43 8.67 7.97 7.31 6.70 6.13 5.60 5.10 4.62 4.18 3.76 8.96 8.22 7.53 6.89 6.30 5.74 5.22 4.73 4.27 3.83 3.43 8.49 7.77 7.10 6.48 5.90 5.36 4.84 4.36 3.91 3.49 3.09 8.02 7.31 6.66 6.06 5.50 4.97 4.47 4.00 3.56 3.15 2.76 7.55 6.87 6.23 5.64 5.10 4.58 4.10 3.65 3.23 2.83 2.45 7.08 6.42 5.80 5.23 4.70 4.20 3.74 3.30 2.90 2.51 2.15 6.67 6.02 5.42 4.86 4.35 3.86 3.41 2.99 2.60 2.23 1.87 6.31 5.68 5.10 4.55 4.04 3.57 3.13 2.72 2.33 1.97 1.63 5.96 5.34 4.77 4.24 3.74 3.28 2.85 2.45 2.07 1.71 1.38

WING AND ENGINE ANTI-ICE ON

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 9.04 8.23 7.48 6.78 6.13 5.53 4.96 4.43 3.94 3.47 3.03 9.05 8.23 7.48 6.78 6.13 5.53 4.97 4.44 3.94 3.47 3.03 9.03 8.21 7.46 6.77 6.12 5.52 4.95 4.42 3.92 3.46 3.02 9.01 8.20 7.45 6.75 6.10 5.50 4.94 4.41 3.91 3.44 3.01 8.99 8.18 7.43 6.74 6.09 5.49 4.92 4.40 3.90 3.43 2.99 8.97 8.16 7.41 6.72 6.07 5.47 4.91 4.38 3.88 3.42 2.98 8.95 8.14 7.40 6.70 6.06 5.46 4.90 4.37 3.87 3.41 2.97 8.93 8.12 7.38 6.69 6.04 5.44 4.88 4.35 3.86 3.39 2.96 8.91 8.11 7.36 6.67 6.03 5.43 4.87 4.34 3.85 3.38 2.95 8.89 8.09 7.35 6.66 6.01 5.42 4.85 4.33 3.83 3.37 2.93

5-30 Copyright © by Embraer. Refer to cover page for details.

Page 30

Approach

REVISION 21

AOM-1502-003

SAT

(°C)

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

APPROACH CLIMB GRADIENT (%) EMBRAER 175 – CF34-8 ENGINES LANDING FLAP FULL – APPROACH FLAP 4 Altitude: 2000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 10.16 9.37 8.64 7.96 7.33 6.74 6.20 5.68 5.20 4.75 4.32 10.14 9.35 8.62 7.95 7.32 6.73 6.18 5.67 5.19 4.74 4.31 10.13 9.34 8.61 7.94 7.31 6.72 6.17 5.66 5.18 4.73 4.30 10.12 9.33 8.60 7.92 7.29 6.71 6.16 5.65 5.17 4.72 4.29 10.10 9.32 8.59 7.91 7.28 6.70 6.15 5.64 5.16 4.71 4.28 10.09 9.30 8.58 7.90 7.27 6.69 6.14 5.63 5.15 4.69 4.27 10.07 9.29 8.56 7.89 7.26 6.67 6.13 5.62 5.14 4.68 4.26 10.06 9.28 8.55 7.87 7.24 6.66 6.12 5.60 5.12 4.67 4.25 10.05 9.26 8.53 7.86 7.23 6.65 6.10 5.59 5.11 4.66 4.24 10.03 9.25 8.52 7.84 7.22 6.63 6.09 5.58 5.10 4.65 4.23 10.02 9.23 8.50 7.83 7.20 6.62 6.08 5.57 5.09 4.64 4.22 9.91 9.13 8.41 7.74 7.12 6.53 5.99 5.49 5.01 4.56 4.14 9.89 9.11 8.39 7.72 7.10 6.52 5.98 5.47 5.00 4.55 4.13 9.87 9.10 8.38 7.72 7.10 6.52 5.98 5.46 4.99 4.53 4.11 9.50 8.74 8.03 7.38 6.77 6.20 5.66 5.16 4.69 4.25 3.83 9.12 8.37 7.67 7.03 6.43 5.87 5.35 4.85 4.39 3.96 3.55 8.70 7.97 7.28 6.65 6.06 5.51 5.00 4.52 4.07 3.65 3.25 8.25 7.53 6.86 6.24 5.66 5.13 4.63 4.16 3.73 3.32 2.93 7.80 7.09 6.44 5.83 5.26 4.74 4.26 3.81 3.38 2.98 2.60 7.32 6.63 6.00 5.41 4.86 4.35 3.88 3.43 3.02 2.63 2.26 6.83 6.17 5.56 4.99 4.46 3.96 3.50 3.06 2.66 2.27 1.91 6.37 5.73 5.14 4.59 4.07 3.59 3.14 2.72 2.32 1.95 1.60 5.93 5.31 4.74 4.21 3.71 3.25 2.81 2.41 2.02 1.66 1.33 5.48 4.89 4.34 3.83 3.35 2.91 2.49 2.09 1.72 1.38 1.05

WING AND ENGINE ANTI-ICE ON SAT

(°C)

AOM-1502-003

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 8.45 7.66 6.94 6.26 5.63 5.05 4.51 4.00 3.52 3.07 2.65 8.43 7.65 6.92 6.25 5.62 5.04 4.49 3.99 3.51 3.06 2.63 8.42 7.63 6.91 6.23 5.60 5.02 4.48 3.97 3.49 3.05 2.62 8.40 7.62 6.89 6.22 5.59 5.01 4.47 3.96 3.48 3.03 2.61 8.38 7.60 6.88 6.20 5.58 5.00 4.46 3.95 3.47 3.02 2.60 8.37 7.59 6.86 6.19 5.56 4.98 4.44 3.94 3.46 3.01 2.59 8.35 7.57 6.85 6.18 5.55 4.97 4.43 3.92 3.45 3.00 2.58 8.34 7.56 6.83 6.16 5.54 4.96 4.42 3.91 3.43 2.99 2.57 8.32 7.54 6.82 6.15 5.52 4.94 4.40 3.90 3.42 2.98 2.56 8.30 7.53 6.80 6.13 5.51 4.93 4.39 3.89 3.41 2.96 2.54

5-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Approach

Page 31

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

APPROACH CLIMB GRADIENT (%) EMBRAER 175 – CF34-8 ENGINES LANDING FLAP FULL – APPROACH FLAP 4 Altitude: 3000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 9.53 8.77 8.07 7.41 6.80 6.24 5.70 5.21 4.74 4.30 3.89 9.51 8.75 8.05 7.40 6.79 6.22 5.69 5.19 4.73 4.29 3.88 9.50 8.74 8.04 7.38 6.78 6.21 5.68 5.18 4.72 4.28 3.87 9.49 8.73 8.02 7.37 6.76 6.19 5.67 5.17 4.70 4.27 3.86 9.47 8.71 8.01 7.35 6.75 6.18 5.65 5.16 4.69 4.26 3.84 9.46 8.70 7.99 7.34 6.73 6.17 5.64 5.15 4.68 4.24 3.83 9.44 8.68 7.98 7.33 6.72 6.16 5.63 5.14 4.67 4.23 3.82 9.43 8.67 7.97 7.32 6.71 6.15 5.62 5.13 4.66 4.22 3.81 9.41 8.66 7.96 7.31 6.71 6.14 5.61 5.12 4.65 4.21 3.80 9.40 8.64 7.95 7.30 6.70 6.13 5.60 5.11 4.64 4.20 3.79 9.33 8.58 7.88 7.24 6.64 6.07 5.55 5.05 4.59 4.15 3.74 9.31 8.56 7.86 7.22 6.62 6.06 5.53 5.04 4.58 4.14 3.73 9.29 8.54 7.85 7.20 6.60 6.04 5.52 5.03 4.57 4.14 3.73 8.94 8.21 7.53 6.89 6.30 5.75 5.23 4.75 4.30 3.87 3.47 8.58 7.86 7.19 6.57 5.99 5.45 4.94 4.46 4.02 3.60 3.20 8.20 7.49 6.84 6.24 5.67 5.14 4.64 4.18 3.73 3.32 2.93 7.81 7.12 6.48 5.89 5.33 4.81 4.32 3.86 3.42 3.01 2.63 7.43 6.75 6.12 5.54 4.99 4.48 4.00 3.54 3.11 2.71 2.33 7.00 6.34 5.73 5.16 4.62 4.12 3.65 3.21 2.79 2.40 2.03 6.57 5.93 5.33 4.77 4.25 3.77 3.31 2.88 2.47 2.09 1.73 6.15 5.52 4.93 4.39 3.88 3.41 2.96 2.54 2.15 1.78 1.43 5.72 5.11 4.54 4.01 3.51 3.05 2.62 2.21 1.83 1.47 1.14 5.30 4.70 4.14 3.63 3.14 2.69 2.28 1.88 1.51 1.17 0.84

WING AND ENGINE ANTI-ICE ON

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 7.81 7.05 6.36 5.71 5.11 4.55 4.02 3.52 3.06 2.62 2.21 7.79 7.04 6.34 5.70 5.10 4.53 4.01 3.51 3.05 2.61 2.20 7.78 7.02 6.33 5.68 5.08 4.52 3.99 3.50 3.03 2.60 2.19 7.76 7.01 6.31 5.67 5.07 4.51 3.98 3.49 3.02 2.59 2.18 7.75 6.99 6.30 5.65 5.05 4.49 3.97 3.47 3.01 2.57 2.17 7.73 6.98 6.28 5.64 5.04 4.48 3.95 3.46 3.00 2.56 2.15 7.72 6.97 6.27 5.62 5.02 4.46 3.94 3.45 2.98 2.55 2.14 7.70 6.95 6.25 5.61 5.01 4.45 3.92 3.43 2.97 2.54 2.13 7.69 6.94 6.24 5.59 4.99 4.43 3.91 3.42 2.96 2.53 2.12 7.67 6.92 6.23 5.58 4.98 4.42 3.90 3.41 2.95 2.52 2.11

5-30 Copyright © by Embraer. Refer to cover page for details.

Page 32

Approach

REVISION 21

AOM-1502-003

SAT

(°C)

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

APPROACH CLIMB GRADIENT (%) EMBRAER 175 – CF34-8 ENGINES LANDING FLAP FULL – APPROACH FLAP 4 Altitude: 4000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 8.93 8.19 7.50 6.86 6.27 5.72 5.22 4.74 4.29 3.87 3.47 8.91 8.17 7.49 6.85 6.26 5.71 5.20 4.73 4.28 3.86 3.46 8.89 8.15 7.47 6.84 6.25 5.70 5.19 4.71 4.27 3.84 3.45 8.87 8.14 7.46 6.82 6.23 5.69 5.18 4.70 4.25 3.83 3.43 8.85 8.12 7.44 6.81 6.22 5.67 5.16 4.69 4.24 3.82 3.42 8.84 8.10 7.42 6.79 6.21 5.66 5.15 4.68 4.23 3.81 3.41 8.82 8.09 7.41 6.78 6.19 5.65 5.14 4.67 4.22 3.80 3.40 8.81 8.08 7.40 6.77 6.18 5.64 5.13 4.66 4.21 3.79 3.39 8.80 8.07 7.39 6.76 6.17 5.63 5.12 4.64 4.20 3.78 3.38 8.79 8.05 7.38 6.75 6.16 5.61 5.11 4.63 4.18 3.76 3.37 8.74 8.02 7.35 6.73 6.14 5.60 5.09 4.62 4.17 3.75 3.35 8.66 7.95 7.28 6.66 6.09 5.55 5.05 4.58 4.14 3.72 3.33 8.43 7.71 7.04 6.43 5.85 5.32 4.82 4.36 3.92 3.51 3.12 8.09 7.39 6.73 6.13 5.56 5.04 4.55 4.10 3.68 3.27 2.89 7.76 7.06 6.42 5.82 5.27 4.76 4.28 3.84 3.42 3.03 2.66 7.42 6.74 6.11 5.52 4.98 4.47 4.01 3.57 3.15 2.76 2.40 7.09 6.42 5.80 5.22 4.69 4.19 3.73 3.29 2.89 2.50 2.14 6.70 6.05 5.44 4.88 4.36 3.87 3.41 2.98 2.58 2.20 1.85 6.32 5.68 5.09 4.54 4.02 3.54 3.09 2.67 2.27 1.90 1.55 5.94 5.31 4.73 4.19 3.69 3.22 2.78 2.36 1.97 1.61 1.27 5.56 4.94 4.37 3.85 3.35 2.89 2.46 2.06 1.68 1.33 0.99 5.17 4.57 4.02 3.50 3.02 2.57 2.15 1.76 1.39 1.03 0.71

WING AND ENGINE ANTI-ICE ON SAT

(°C)

AOM-1502-003

-8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 7.19 6.46 5.79 5.16 4.57 4.03 3.52 3.05 2.60 2.18 1.79 7.17 6.44 5.77 5.15 4.56 4.02 3.52 3.04 2.60 2.18 1.78 7.15 6.43 5.75 5.13 4.55 4.01 3.51 3.04 2.59 2.17 1.78 7.13 6.41 5.74 5.12 4.54 4.00 3.50 3.02 2.58 2.17 1.77 7.11 6.39 5.72 5.10 4.52 3.98 3.48 3.01 2.57 2.15 1.76 7.10 6.38 5.71 5.09 4.51 3.97 3.47 3.00 2.55 2.14 1.74 7.08 6.36 5.69 5.07 4.49 3.96 3.45 2.98 2.54 2.12 1.73 7.06 6.34 5.68 5.06 4.48 3.94 3.44 2.97 2.52 2.11 1.71 7.04 6.32 5.66 5.04 4.47 3.93 3.43 2.95 2.51 2.09 1.70 6.97 6.26 5.60 4.98 4.41 3.88 3.38 2.91 2.47 2.06 1.67

5-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Approach

Page 33

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

APPROACH CLIMB GRADIENT (%) EMBRAER 175 – CF34-8 ENGINES LANDING FLAP FULL – APPROACH FLAP 4 Altitude: 5000 ft ANTI-ICE OFF SAT

(°C) 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 8.37 7.66 7.00 6.39 5.83 5.29 4.79 4.32 3.88 3.47 3.08 8.35 7.65 6.99 6.38 5.81 5.28 4.78 4.31 3.87 3.46 3.07 8.34 7.63 6.98 6.37 5.80 5.27 4.77 4.30 3.86 3.45 3.06 8.33 7.62 6.96 6.35 5.78 5.25 4.75 4.29 3.85 3.44 3.05 8.31 7.60 6.95 6.34 5.77 5.24 4.74 4.27 3.84 3.43 3.04 8.30 7.59 6.93 6.32 5.75 5.22 4.73 4.26 3.83 3.42 3.03 8.29 7.58 6.92 6.31 5.74 5.21 4.71 4.25 3.81 3.40 3.02 8.27 7.56 6.91 6.30 5.73 5.20 4.70 4.24 3.80 3.39 3.01 8.23 7.53 6.88 6.28 5.72 5.19 4.69 4.23 3.79 3.38 3.00 8.13 7.44 6.79 6.19 5.64 5.11 4.63 4.17 3.74 3.34 2.96 8.04 7.35 6.71 6.11 5.55 5.04 4.56 4.10 3.68 3.28 2.90 7.88 7.19 6.55 5.96 5.41 4.90 4.42 3.97 3.55 3.15 2.78 7.62 6.93 6.30 5.71 5.17 4.66 4.19 3.74 3.33 2.93 2.57 7.30 6.63 6.01 5.43 4.89 4.39 3.93 3.50 3.09 2.70 2.34 6.99 6.33 5.72 5.15 4.62 4.13 3.67 3.24 2.83 2.45 2.09 6.68 6.03 5.43 4.87 4.35 3.86 3.41 2.98 2.57 2.20 1.84 6.33 5.69 5.10 4.56 4.05 3.57 3.13 2.71 2.31 1.94 1.59 5.98 5.36 4.78 4.25 3.75 3.28 2.85 2.44 2.05 1.69 1.35 5.63 5.02 4.46 3.93 3.45 2.99 2.56 2.16 1.78 1.43 1.09 5.28 4.69 4.14 3.62 3.15 2.70 2.28 1.88 1.51 1.17 0.84 4.93 4.35 3.81 3.31 2.85 2.41 2.00 1.61 1.25 0.90 0.58

WING AND ENGINE ANTI-ICE ON SAT

(°C) -8 -6 -4 -2 0 2 4 6 8 10

WEIGHT (lb) 55000 57000 59000 61000 63000 65000 67000 69000 71000 73000 75000 6.61 5.91 5.26 4.66 4.10 3.57 3.08 2.62 2.19 1.78 1.40 6.59 5.89 5.25 4.65 4.09 3.57 3.08 2.62 2.18 1.78 1.39 6.57 5.88 5.23 4.63 4.08 3.55 3.06 2.60 2.17 1.76 1.38 6.55 5.86 5.21 4.61 4.06 3.54 3.05 2.59 2.15 1.75 1.37 6.53 5.84 5.19 4.59 4.04 3.52 3.03 2.57 2.14 1.74 1.36 6.51 5.82 5.17 4.57 4.02 3.50 3.01 2.55 2.12 1.72 1.34 6.49 5.80 5.15 4.56 4.00 3.48 2.99 2.54 2.11 1.71 1.33 6.47 5.78 5.13 4.54 3.98 3.46 2.98 2.52 2.09 1.69 1.32 6.38 5.69 5.05 4.46 3.90 3.39 2.91 2.45 2.03 1.63 1.26 6.28 5.59 4.96 4.37 3.82 3.31 2.83 2.39 1.96 1.57 1.20

5-30 Copyright © by Embraer. Refer to cover page for details.

Page 34

Approach

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

UNFACTORED LANDING DISTANCE !EMBRAER 170 Models

Unfactored landing distance is the actual distance to land the airplane on a zero slope, ISA temperature, dry runway, from a point 50 ft above runway threshold at Vref, using only the brakes and spoilers as deceleration devices (i.e., no engine reverse thrust is used). The unfactored landing distances provided are valid for anti-ice ON and OFF.

NORMAL OPERATION The required landing distance for dispatch is the unfactored landing distance increased by 66.7% for dry runway, or 91.7% for wet runway. For obtaining the DRY runway factored distance, multiply unfactored landing distance by 1.667. For obtaining the WET runway factored distance, multiply unfactored landing distance by 1.917. The unfactored landing distance corrections are valid for overspeeds up to Vref + 20 and no failure.

EMERGENCY/ABNORMAL OPERATION LANDING DISTANCE CORRECTION FACTOR - DRY RUNWAYS The Actual Landing Distance is equal to the Unfactored Landing Distance for flaps FULL multiplied by the associated landing distance factor for DRY runways.

AOM-1502-003

The DRY + OVSP corresponds to the factor associated to a 10 kt overspeed (above the non-normal VREF) on a dry runway.

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 1

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

LANDING DISTANCE CORRECTION FACTOR - WET RUNWAYS The WET + OVSP corresponds to the factor associated to a 10 kt overspeed (above the non-normal VREF) on a wet runway. To calculate the actual landing distance on a WET runway, the pilot must do the steps below: 1. Recognize the system malfunction; 2. Find the Unfactored Landing Distance (ULD) for Flaps Full in Quick Reference Handbook (QRH), considering the airplane type, altitude, landing weight and ice accretion condition; 3.

Find the multiplier factor value (K) on the table with Landing Distance Correction Factors and multiply the obtained values of (ULD) and (K). 4. In the same line of table with Landing Distance Correction Factors, find the value (B). 5.

Subtract (B) from the result of step (3). This is the actual landing distance (ALD) to safely land the airplane on wet runways condition.

ALD = (ULD x K) – B

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 2

Landing

REVISION 21

AOM-1502-003

NOTE: The calculated value is the actual distance to safely land the airplane, but no distance margins are included. The distance margin available is the difference between the runway length and the calculated value.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP 5 – WITHOUT ICE ACCRETION PRESSURE ALTITUDE (ft) 0

WEIGHT (lb)

1000 WIND (kt)

-10

0

10

20

-10

0

10

20

52000

2502

2089

1960

1835

2544

2128

1998

1872

56000

2615

2193

2061

1933

2660

2234

2101

1972

60000

2731

2298

2163

2032

2779

2343

2206

2074

64000

2849

2405

2266

2132

2901

2453

2313

2177

68000

2969

2512

2369

2232

3028

2563

2419

2280

72000

3104

2622

2476

2335

3167

2677

2529

2387

76000

3242

2738

2583

2438

3311

2800

2643

2494

80000

3386

2863

2702

2547

3471

2938

2775

2618

Per 5 kt above Vref (and no failure) add 221 ft. PRESSURE ALTITUDE (ft) 2000

WEIGHT (lb)

3000 WIND (kt)

-10

0

10

20

-10

0

10

20

52000

2587

2168

2037

1910

2632

2210

2077

1949

56000

2707

2277

2143

2013

2756

2322

2187

2056

60000

2829

2389

2251

2118

2882

2438

2299

2164

64000

2955

2503

2361

2225

3012

2555

2412

2274

68000

3089

2616

2471

2331

3154

2672

2526

2384

72000

3234

2735

2585

2441

3304

2798

2643

2497

76000

3388

2869

2709

2556

3475

2946

2784

2627

80000

3560

3017

2851

2691

3653

3101

2931

2768

AOM-1502-003

Per 5 kt above Vref (and no failure) add 237 ft.

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 3

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP 5 – WITHOUT ICE ACCRETION PRESSURE ALTITUDE (ft) 4000

WEIGHT (lb)

5000 WIND (kt)

-10

0

10

20

-10

0

10

20

52000

2679

2253

2120

1991

2726

2297

2163

2032

56000

2806

2369

2232

2100

2858

2417

2279

2145

60000

2937

2488

2348

2212

2993

2540

2398

2260

64000

3073

2609

2465

2325

3136

2665

2519

2378

68000

3221

2731

2582

2439

3290

2790

2640

2495

72000

3383

2869

2711

2561

3469

2946

2785

2631

76000

3565

3027

2861

2702

3658

3110

2941

2779

80000

3751

3187

3014

2848

3852

3277

3100

2931

Per 5 kt above Vref (and no failure) add 256 ft. PRESSURE ALTITUDE (ft) 6000

WEIGHT (lb)

7000 WIND (kt)

-10

0

10

20

-10

0

10

20

2775

2343

2207

2076

2827

2391

2254

2121

56000

2911

2466

2327

2192

2968

2518

2378

2241

60000

3051

2593

2450

2311

3112

2649

2504

2364

64000

3202

2722

2575

2432

3272

2783

2634

2489

68000

3369

2861

2707

2560

3456

2939

2780

2630

72000

3559

3026

2862

2704

3653

3111

2944

2783

76000

3755

3197

3025

2860

3858

3288

3113

2944

80000

3957

3370

3190

3018

4068

3469

3285

3109

52000

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 4

Landing

REVISION 21

AOM-1502-003

Per 5 kt above Vref (and no failure) add 277 ft.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP 5 – WITHOUT ICE ACCRETION PRESSURE ALTITUDE (ft) 8000

WEIGHT (lb)

WIND (kt) -10

0

10

20

52000

2881

2441

2303

2169

56000

3026

2573

2430

2293

60000

3177

2708

2561

2419

64000

3352

2853

2702

2555

68000

3546

3020

2858

2704

72000

3752

3199

3029

2865

76000

3965

3383

3205

3033

80000

4185

3572

3384

3204

AOM-1502-003

Per 5 kt above Vref (and no failure) add 289 ft.

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 5

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP FULL – WITHOUT ICE ACCRETION PRESSURE ALTITUDE (ft) 0

WEIGHT (lb)

1000 WIND (kt)

-10

0

10

20

-10

0

10

20

52000

2357

1954

1828

1706

2395

1989

1862

1739

56000

2456

2045

1916

1792

2497

2083

1953

1827

60000

2558

2137

2006

1879

2601

2178

2045

1917

64000

2658

2228

2094

1964

2704

2271

2136

2005

68000

2760

2321

2184

2051

2809

2366

2228

2094

72000

2862

2414

2273

2138

2915

2461

2320

2183

76000

2967

2501

2358

2219

3024

2551

2407

2267

80000

3036

2555

2410

2269

3096

2607

2460

2318

Per 5 kt above Vref (and no failure) add 171 ft. PRESSURE ALTITUDE (ft) 2000

WEIGHT (lb)

3000 WIND (kt)

-10

0

10

20

-10

0

10

20

52000

2434

2026

1898

1774

2475

2064

1935

1810

56000

2539

2121

1991

1864

2583

2162

2030

1903

60000

2646

2219

2085

1956

2693

2262

2128

1997

64000

2752

2315

2179

2046

2802

2361

2223

2090

68000

2860

2413

2274

2138

2913

2462

2321

2185

72000

2972

2511

2368

2230

3031

2563

2419

2279

76000

3085

2604

2457

2316

3148

2658

2511

2368

80000

3159

2663

2513

2369

3225

2722

2568

2423

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 6

Landing

REVISION 21

AOM-1502-003

Per 5 kt above Vref (and no failure) add 188 ft.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP FULL – WITHOUT ICE ACCRETION PRESSURE ALTITUDE (ft) 4000

WEIGHT (lb)

5000 WIND (kt)

-10

0

10

20

-10

0

10

20

52000

2518

2103

1973

1847

2561

2143

2012

1885

56000

2628

2204

2071

1943

2674

2247

2113

1983

60000

2742

2307

2171

2040

2791

2353

2216

2083

64000

2854

2409

2270

2135

2907

2458

2317

2181

68000

2969

2513

2370

2232

3026

2565

2421

2281

72000

3092

2617

2471

2330

3155

2672

2524

2381

76000

3214

2715

2566

2421

3281

2776

2622

2476

80000

3294

2784

2626

2478

3365

2847

2687

2535

Per 5 kt above Vref (and no failure) add 206 ft. PRESSURE ALTITUDE (ft) 6000

WEIGHT (lb)

7000 WIND (kt)

-10

0

10

20

-10

0

10

20

52000

2605

2184

2052

1924

2652

2227

2094

1965

56000

2722

2291

2156

2025

2772

2337

2201

2069

60000

2842

2400

2262

2128

2896

2449

2310

2174

64000

2961

2508

2366

2229

3018

2561

2417

2279

68000

3086

2618

2473

2332

3150

2674

2527

2385

72000

3221

2729

2580

2435

3290

2788

2638

2491

76000

3351

2839

2681

2533

3425

2905

2744

2592

80000

3438

2912

2750

2595

3516

2982

2817

2659

AOM-1502-003

Per 5 kt above Vref (and no failure) add 225 ft.

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 7

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP FULL – WITHOUT ICE ACCRETION PRESSURE ALTITUDE (ft) 8000

WEIGHT (lb)

WIND (kt) -10

0

10

20

52000

2700

2272

2138

2008

56000

2824

2385

2247

2114

60000

2951

2501

2360

2223

64000

3078

2615

2471

2330

68000

3217

2733

2584

2440

72000

3361

2852

2698

2550

76000

3502

2974

2811

2654

80000

3597

3054

2886

2726

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 8

Landing

REVISION 21

AOM-1502-003

Per 5 kt above Vref (and no failure) add 236 ft.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP 5 – WITH ICE ACCRETION PRESSURE ALTITUDE (ft) 0

WEIGHT (lb)

1000 WIND (kt)

-10

0

10

20

-10

0

10

20

52000

2728

2299

2165

2035

2776

2343

2208

2077

56000

2859

2418

2280

2147

2911

2466

2327

2192

60000

2994

2541

2399

2262

3050

2593

2450

2311

64000

3136

2664

2518

2377

3200

2720

2572

2430

68000

3292

2792

2642

2497

3372

2864

2709

2562

72000

3472

2949

2788

2633

3558

3026

2862

2705

76000

3662

3114

2946

2784

3756

3198

3027

2862

80000

3857

3282

3106

2937

3959

3373

3193

3020

Per 5 kt above Vref (and no failure) add 240 ft. PRESSURE ALTITUDE (ft) 2000

WEIGHT (lb)

3000 WIND (kt)

-10

0

10

20

-10

0

10

20

52000

2825

2389

2252

2120

2877

2437

2299

2166

56000

2965

2516

2375

2239

3021

2568

2426

2289

60000

3108

2646

2502

2362

3171

2702

2556

2415

64000

3266

2777

2629

2485

3346

2847

2697

2551

68000

3455

2939

2779

2630

3542

3017

2855

2701

72000

3648

3107

2940

2780

3743

3192

3022

2859

76000

3854

3285

3111

2943

3957

3377

3199

3028

80000

4065

3467

3284

3108

4177

3566

3379

3199

AOM-1502-003

Per 5 kt above Vref (and no failure) add 260 ft.

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 9

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP 5 – WITH ICE ACCRETION PRESSURE ALTITUDE (ft) 4000

WEIGHT (lb)

5000 WIND (kt)

-10

0

10

20

-10

0

10

20

52000

2931

2487

2348

2213

2986

2538

2397

2261

56000

3080

2622

2478

2340

3139

2677

2532

2392

60000

3238

2761

2613

2470

3314

2828

2679

2534

64000

3430

2920

2767

2619

3515

2998

2840

2690

68000

3633

3099

2934

2775

3727

3183

3015

2853

72000

3842

3280

3107

2941

3944

3371

3195

3026

76000

4065

3473

3291

3117

4176

3572

3387

3209

80000

4294

3670

3479

3295

4416

3778

3582

3395

Per 5 kt above Vref (and no failure) add 282 ft. PRESSURE ALTITUDE (ft) 6000

WEIGHT (lb)

7000 WIND (kt)

-10

0

10

20

-10

0

10

20

52000

3043

2590

2448

2311

3103

2646

2502

2363

56000

3201

2734

2588

2446

3272

2799

2651

2507

60000

3396

2900

2749

2602

3482

2976

2822

2673

64000

3605

3078

2916

2763

3699

3163

2997

2839

68000

3824

3270

3099

2935

3927

3363

3189

3021

72000

4050

3467

3287

3114

4162

3567

3384

3207

76000

4292

3676

3486

3305

4415

3785

3592

3406

80000

4543

3890

3690

3499

4678

4009

3805

3609

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 10

Landing

REVISION 21

AOM-1502-003

Per 5 kt above Vref (and no failure) add 307 ft.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP 5 – WITH ICE ACCRETION PRESSURE ALTITUDE (ft) 8000

WEIGHT (lb)

WIND (kt) -10

0

10

20

52000

3165

2703

2558

2418

56000

3353

2872

2721

2576

60000

3572

3054

2898

2747

64000

3797

3252

3083

2920

68000

4034

3459

3281

3111

72000

4280

3672

3485

3305

76000

4544

3899

3702

3512

80000

4819

4134

3924

3724

AOM-1502-003

Per 5 kt above Vref (and no failure) add 321 ft.

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 11

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP FULL – WITH ICE ACCRETION PRESSURE ALTITUDE (ft) 0

WEIGHT (lb)

1000 WIND (kt)

-10

0

10

20

-10

0

10

20

52000

2495

2081

1952

1827

2536

2120

1989

1863

56000

2604

2182

2049

1921

2648

2223

2089

1960

60000

2713

2281

2146

2015

2760

2324

2188

2056

64000

2823

2381

2243

2109

2874

2427

2288

2153

68000

2936

2483

2341

2204

2989

2532

2389

2251

72000

3054

2583

2438

2298

3114

2636

2489

2348

76000

3172

2679

2531

2388

3236

2736

2585

2440

80000

3245

2740

2584

2439

3312

2800

2642

2493

Per 5 kt above Vref (and no failure) add 186 ft. PRESSURE ALTITUDE (ft) 2000

WEIGHT (lb)

3000 WIND (kt)

-10

0

10

20

-10

0

10

20

52000

2578

2159

2028

1901

2623

2200

2068

1940

56000

2694

2265

2131

2000

2742

2309

2174

2042

60000

2809

2370

2232

2099

2860

2417

2278

2144

64000

2926

2476

2335

2198

2981

2526

2384

2246

68000

3047

2583

2439

2299

3108

2637

2491

2350

72000

3176

2690

2542

2399

3242

2747

2597

2452

76000

3303

2796

2641

2494

3373

2859

2700

2551

80000

3382

2862

2702

2549

3455

2928

2765

2609

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 12

Landing

REVISION 21

AOM-1502-003

Per 5 kt above Vref (and no failure) add 204 ft.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP FULL – WITH ICE ACCRETION PRESSURE ALTITUDE (ft) 4000

WEIGHT (lb)

5000 WIND (kt)

-10

0

10

20

-10

0

10

20

52000

2669

2243

2110

1981

2716

2286

2152

2022

56000

2792

2355

2218

2086

2842

2402

2264

2130

60000

2914

2466

2326

2190

2967

2516

2374

2237

64000

3037

2578

2434

2295

3095

2631

2486

2346

68000

3172

2693

2545

2402

3236

2749

2600

2456

72000

3310

2806

2655

2508

3380

2869

2713

2565

76000

3447

2924

2763

2610

3522

2992

2828

2671

80000

3532

2996

2831

2672

3610

3066

2899

2737

Per 5 kt above Vref (and no failure) add 224 ft. PRESSURE ALTITUDE (ft) 6000

WEIGHT (lb)

7000 WIND (kt)

-10

0

10

20

-10

0

10

20

52000

2764

2331

2196

2064

2815

2378

2242

2109

56000

2894

2450

2311

2176

2949

2500

2360

2224

60000

3023

2567

2424

2286

3082

2621

2477

2337

64000

3156

2686

2540

2398

3222

2744

2596

2452

68000

3304

2808

2657

2512

3375

2870

2717

2570

72000

3453

2934

2774

2624

3529

3003

2841

2686

76000

3600

3062

2896

2736

3682

3135

2967

2804

80000

3693

3139

2969

2805

3780

3216

3043

2877

AOM-1502-003

Per 5 kt above Vref (and no failure) add 245 ft.

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 13

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP FULL – WITH ICE ACCRETION PRESSURE ALTITUDE (ft) 8000

WEIGHT (lb)

WIND (kt) -10

0

10

20

52000

2868

2427

2289

2155

56000

3005

2553

2411

2273

60000

3143

2677

2532

2390

64000

3290

2804

2654

2509

68000

3449

2935

2780

2630

72000

3609

3075

2910

2751

76000

3771

3214

3043

2878

80000

3880

3306

3129

2960

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 14

Landing

REVISION 21

AOM-1502-003

Per 5 kt above Vref (and no failure) add 254 ft.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

LANDING DISTANCE CORRECTION FACTOR EMBRAER 170 - DRY RUNWAYS Emerg/Abnormal Procedure

Factor Flaps – Speed

DUAL ENGINE FAILURE

Slat/Flap 3 – VREF or 130 KIAS

JAMMED CONTROL COLUMN (PITCH)

DRY + OVSP

2.10

2.60

FULL

+ 20

Slat/Flap 5 – VREF

FULL

+ 15

1.40

1.55

JAMMED CONTROL WHEEL (ROLL)

Slat/Flap 5 – VREF

FULL

+ 15

1.40

1.55

LOSS OF HYDRAULIC SYSTEM 1

Slat/Flap Full – VREF

FULL

1.90

2.20

LOSS OF HYDRAULIC SYSTEM 2

Slat/Flap Full – VREF

FULL

1.80

2.10

LOSS OF HYDRAULIC SYSTEM 1 AND 2

Slat/Flap 5 – VREF

FULL

+ 10

2.70

3.25

LOSS OF HYDRAULIC SYSTEM 1 AND 3

Slat/Flap 5 – VREF

FULL

+ 10

2.30

2.65

LOSS OF HYDRAULIC SYSTEM 2 AND 3

Slat/Flap 5 – VREF

FULL

+ 10

2.20

2.50

FULL

+ 20

1.40

1.70

FULL

+ 15

1.40

1.55

1.22

1.38

2.10

2.60

ONE ENGINE INOPERATIVE APPROACH Slat/Flap 5 – VREF AND LANDING Slat/Flap 5 – VREF STALL PROT FAIL

AOM-1502-003

DRY

Slat/Flap Full – VREF 10

FULL

+

ELEC EMERGENCY

Slat/Flap 3 – VREF or 130 KIAS

DC BUS 1 OFF

Slat/Flap Full – VREF

FULL

1.15

1.30

DC BUS 2 OFF

Slat/Flap Full – VREF

FULL

1.20

1.40

DC ESS BUS 1 OFF

Slat/Flap Full – VREF

FULL

1.70

2.00

DC ESS BUS 2 OFF

Slat/Flap Full – VREF

FULL

1.80

2.10

GROUND SPOILERS FAIL

Slat/Flap Full – VREF

FULL

1.30

1.40

SPOILER NML MODE FAIL

Slat/Flap Full – VREF

FULL

1.45

1.75

ELEVATOR LH (RH) FAIL

Slat/Flap 5 – VREF

1.40

1.65

FULL

FULL

+ 20

+ 15

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 15

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

PITCH TRIM FAIL SPOILER FAULT

Factor Flaps – Speed

DRY

DRY + OVSP 1.55

Slat/Flap 5 – VREF

FULL

+ 15

1.40

Slat/Flap 5 – VREF

FULL

+ 15

1.78

2.11

1.45

1.75

Slat/Flap Full – VREF

AILERON LH (RH) FAIL

Slat/Flap 5 – VREF

AVNX MAU 1A FAIL

Slat/Flap Full – VREF

AVNX MAU 1B FAIL

FULL

1.30

1.45

FULL

1.70

2.00

Slat/Flap Full – VREF

FULL

1.15

1.30

AVNX MAU 2B FAIL

Slat/Flap Full – VREF

FULL

1.65

1.85

AVNX MAU 3A FAIL

Slat/Flap Full – VREF

FULL

1.20

1.75

AVNX MAU 3B FAIL

Slat/Flap Full – VREF

FULL

FULL

+ 10

1.20

1.40

A-I WING FAIL or A-I WING Slat/Flap 5 – VREF FLAP 5 ICE 1 (2) LEAK

1.30

1.50

BRK LH (RH) FAIL

Slat/Flap Full – VREF

FULL

1.65

1.85

LG WOW SYS FAIL

Slat/Flap Full – VREF

FULL

1.30

1.75

BRK LH (RH) FAULT

Slat/Flap Full – VREF

FULL

1.65

1.85

DC BUS 1 OFF and DC Slat/Flap 3 – VREF Essential BUS 1 OFF SMOKE/ FIRE/ FUMES

FULL

+ 20

2.30

2.60

DC Essential BUS 2 and DC BUS 2 OFF

Slat/Flap 3 – VREF

FULL

+ 20

2.50

2.90

DC Essential BUS 3 OFF

Slat/Flap 3 – VREF

FULL

+ 20

2.10

2.60

TRU ESS and TRU BUS AUTO

Slat/Flap 3 – VREF

FULL

+ 20

2.10

2.60

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 16

Landing

REVISION 21

AOM-1502-003

Emerg/Abnormal Procedure

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

LANDING DISTANCE CORRECTION FACTOR EMBRAER 170 - WET RUNWAYS - DISTANCE IN FEET !!EMBRAER 170 models, length in British units

Emerg/Abnormal Procedure

Flaps – Speed

WET + OVSP

WET K

B

K

B

DUAL ENGINE FAILURE

FULL

Slat/Flap 3 – VREF + 20 or 130 KIAS

4.10

2638

5.39

4193

JAMMED CONTROL COLUMN (PITCH)

Slat/Flap 5 – VREF FULL + 15

2.01

1148

2.30

1421

JAMMED CONTROL WHEEL (ROLL)

Slat/Flap 5 – VREF FULL + 15

2.01

1148

2.30

1421

2.82

1808

3.16

1926

2.57

1621

2.87

1742

LOSS OF HYDRAULIC SYSTEM 1 LOSS OF HYDRAULIC SYSTEM 2

Slat/Flap Full – VREF FULL

Slat/Flap Full – VREF FULL

LOSS OF HYDRAULIC SYSTEM 1 AND 2

Slat/Flap 5 – VREF FULL + 10

5.16

3307

5.92

3048

LOSS OF HYDRAULIC SYSTEM 1 AND 3

Slat/Flap 5 – VREF FULL + 10

3.42

2428

3.89

2779

LOSS OF HYDRAULIC SYSTEM 2 AND 3

Slat/Flap 5 – VREF FULL + 10

3.12

2152

3.53

2470

ONE ENGINE INOPERATIVE APPROACH AND LANDING

Slat/Flap 5 – VREF FULL + 20

2.30

1453

2.63

1772

Slat/Flap 5 – VREF FULL + 15

2.01

1148

2.30

1421

Slat/Flap Full – VREF + 10

1.98

1102

2.23

1240

STALL PROT FAIL AOM-1502-003

Factor ALD = (ULD x K) – B

FULL

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 17

PERFORMANCE

Emerg/Abnormal Procedure

AIRPLANE OPERATIONS MANUAL Factor ALD = (ULD x K) – B Flaps – Speed

WET + OVSP

WET K

B

K

B

4.10

2638

5.39

4193

2.27

1424

2.54

1552

2.47

1588

2.77

1716

2.62

1611

2.93

1722

2.88

1788

3.23

1877

GROUND SPOILERS Slat/Flap Full – VREF FAIL FULL

1.83

994

2.07

1093

SPOILER NML MODE FAIL

2.53

1493

2.95

1975

FULL

ELEVATOR LH (RH) FAIL

Slat/Flap 5 – VREF FULL + 15

2.11

1066

2.40

1325

Slat/Flap 5 – VREF + 15

2.01

1148

2.30

1421

Slat/Flap 5 – VREF FULL + 15

3.01

2001

3.56

2490

2.53

1493

2.90

1722

1.88

1037

2.15

1276

2.58

1667

2.83

1778

1.69

869

1.90

965

2.44

1529

2.67

1631

2.53

1493

2.90

1722

ELEC EMERGENCY

DC BUS 1 OFF

Slat/Flap 3 – VREF + 20 or 130 KIAS FULL

Slat/Flap Full – VREF FULL

DC BUS 2 OFF

Slat/Flap Full – VREF FULL

DC ESS BUS 1 OFF

Slat/Flap Full – VREF FULL

DC ESS BUS 2 OFF

Slat/Flap Full – VREF FULL

PITCH TRIM FAIL

Slat/Flap Full – VREF

FULL

SPOILER FAULT

Slat/Flap Full – VREF FULL

AILERON LH (RH) FAIL AVNX MAU 1A FAIL

Slat/Flap 5 – VREF FULL + 10 Slat/Flap Full – VREF FULL

AVNX MAU 1B FAIL

Slat/Flap Full – VREF FULL

AVNX MAU 2B FAIL

Slat/Flap Full – VREF FULL

AVNX MAU 3A FAIL

Slat/Flap Full – VREF

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 18

Landing

REVISION 21

AOM-1502-003

FULL

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

Emerg/Abnormal Procedure

Factor ALD = (ULD x K) – B Flaps – Speed

WET + OVSP

WET K

B

K

B

1.83

994

2.07

1093

2.24

1588

2.53

1870

2.44

1529

2.67

1631

3.33

1549

3.83

1345

2.16

1302

2.38

1404

3.30

2024

3.88

2792

Slat/Flap 3 – VREF FULL + 20

3.65

2293

4.33

3179

DC Slat/Flap 3 – VREF Essential FULL + 20 BUS 3 OFF

4.10

2638

5.39

4193

TRU ESS and TRU BUS AUTO

4.10

2638

5.39

4193

AVNX MAU 3B FAIL

Slat/Flap Full – VREF FULL

A-I WING FAIL or A-I WING 1 (2) LEAK BRK LH (RH) FAIL

Slat/Flap 5 – VREF FLAP 5 ICE

Slat/Flap Full – VREF FULL

LG WOW SYS FAIL

Slat/Flap Full – VREF FULL

BRK LH (RH) FAULT

Slat/Flap Full – VREF FULL

DC BUS 1 OFF and Slat/Flap 3 – VREF DC FULL + 20 Essential BUS 1 OFF DC Essential SMOKE/ BUS 2 and FIRE/ DC BUS 2 FUMES OFF

Slat/Flap 3 – VREF FULL + 20

AOM-1502-003

""

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 19

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

FLAP (SLAT) FAIL - EMBRAER 170 - DRY RUNWAYS The Actual Landing Distance is equal to the Unfactored Landing Distance for flaps FULL multiplied by the associated landing distance factor for DRY runways. Refer to the following tables for reference speed and factor to be applied to the unfactored landing distance, for a flap/slat fail or a flap/slat fail with shaker anticipated: FLAP/SLAT FAIL WITHOUT SHAKER ANTICIPATED LANDING CONFIGURATION TABLE - DRY RUNWAY !!170 models, EASA/FAA certification

SLAT → FLAP ↓

0

VREF (KIAS) Factor

0

VREF

VREF (KIAS) Factor

1

VREF

VREF (KIAS) Factor

2

VREF

VREF (KIAS) Factor

3 (4) (5)

VREF (KIAS) FULL Factor

FULL

+ 60

2.41 FULL

+ 35

1.46 FULL

+ 30

1.38

NOT USABLE

1 (2) (3)

4 (5) (FULL)

VREF FULL + 50 1.75 VREF FULL + 35 2.00 VREF FULL + 25 1.55 VREF FULL + 15 1.31 VREF FULL + 5 1.06

VREF FULL + 50 1.80 VREF FULL + 35 2.00 VREF FULL + 20 1.28 VREF FULL + 10 1.29 VREF FULL 1.00

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 20

Landing

REVISION 21

AOM-1502-003

""

PERFORMANCE

AIRPLANE OPERATIONS MANUAL FLAP/SLAT

FAIL WITH SHAKER ANTICIPATED CONFIGURATION TABLE - DRY RUNWAY SLAT → FLAP ↓

0

VREF (KIAS) Factor

0

VREF

VREF (KIAS) Factor

1

VREF

VREF (KIAS) Factor

2

VREF

VREF (KIAS) Factor

3 (4) (5)

VREF (KIAS) FULL Factor

FULL

+ 60

2.41 FULL

+ 40

1.55 FULL

+ 30

1.38

NOT USABLE

LANDING

1 (2) (3)

4 (5) (FULL)

VREF FULL + 60 2.00 VREF FULL + 40 1.60 VREF FULL + 25 1.55 VREF FULL + 15 1.31 VREF FULL + 5 1.06

VREF FULL + 60 2.00 VREF FULL + 40 1.60 VREF FULL + 25 1.57 VREF FULL + 10 1.29 VREF FULL 1.00

FLAP/SLAT FAIL WITHOUT SHAKER ANTICIPATED LANDING CONFIGURATION TABLE - DRY RUNWAY + 10 kt OVERSPEED SLAT → FLAP ↓

0

1 (2) (3)

AOM-1502-003

VREF FULL + 60 VREF (KIAS) 0 Factor 2.10 VREF FULL + 35 VREF (KIAS) 1 Factor 1.74 VREF FULL + 30 VREF (KIAS) 2 Factor 1.54 VREF (KIAS) 3 (4) Factor (5) NOT USABLE VREF (KIAS) FULL Factor

VREF

FULL

4 (5) (FULL)

+ 50 VREF

1.97 VREF

FULL

+ 35 VREF

1.72 VREF

FULL

FULL

+ 50

FULL

+ 35

1.71 + 25 VREF

1.74 VREF

FULL

1.96

FULL

+ 20

1.48 + 15 VREF

FULL

+ 10

1.50

1.44

VREF FULL + 5 1.12

VREF FULL 1.24

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 21

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

FLAP/SLAT FAIL WITH SHAKER ANTICIPATED LANDING CONFIGURATION TABLE - DRY RUNWAY + 10 kt OVERSPEED

0

1 (2) (3)

VREF FULL + 60 VREF (KIAS) 0 Factor 2.18 VREF FULL + 40 VREF (KIAS) 1 Factor 1.82 VREF FULL + 30 VREF (KIAS) 2 Factor 1.54 VREF (KIAS) 3 (4) Factor (5) NOT USABLE VREF (KIAS) FULL Factor

VREF

FULL

4 (5) (FULL)

+ 60 VREF

2.15 VREF

FULL

+ 40 VREF

1.78 VREF

FULL

FULL

+ 60

FULL

+ 40

1.80 + 25 VREF

1.72 VREF

FULL

2.12

FULL

+ 25

1.73 + 15 VREF

FULL

+ 10

1.50

1.47

VREF FULL + 5 1.12

VREF FULL 1.24

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 22

Landing

REVISION 21

AOM-1502-003

SLAT → FLAP ↓

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

FLAP (SLAT) FAIL - LANDING CONFIGURATION TABLE - WET RUNWAYS The WET + OVSP corresponds to the factor associated to a 10 kt overspeed (above the non-normal VREF) on a wet runway. To calculate the actual landing distance on a WET runway, the pilot must do the steps below: 1. Recognize the FLAP/SLAT position; 2. Find the Unfactored Landing Distance (ULD) for Flaps Full in Quick Reference Handbook (QRH), considering the airplane type, altitude, landing weight and ice accretion condition; 3.

Find the multiplier factor value (K) on the table with FLAP/SLAT Fail - Landing Configuration and multiply the obtained values of (ULD) and (K). 4. In the same line of table with FLAP/SLAT Fail - Landing Configuration, find the value (B). 5.

Subtract (B) from the result of step (3). This is the actual landing distance (ALD) to safely land the airplane on wet runways condition.

ALD = (ULD x K) – B

AOM-1502-003

NOTE: The calculated value is the actual distance to safely land the airplane, but no distance margins are included. The distance margin available is the difference between the runway length and the calculated value.

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 23

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

FLAP (SLAT) FAIL - EMBRAER 170 - WET RUNWAYS !!EMBRAER 170 models, length in British units

FLAP/SLAT FAIL WITHOUT SHAKER ANTICIPATED LANDING CONFIGURATION TABLE - WET RUNWAY ALD = (ULD x K) – B SLAT → FLAP ↓ 0

Factor VREF (KIAS)

1

Factor VREF (KIAS)

2

Factor VREF (KIAS)

0

1 (2) (3)

4 (5) (FULL)

VREF FULL + 60 K B 3.63 2805 VREF FULL + 35 K B 2.77 2008 VREF FULL + 30 K B 2.52 1732

VREF FULL + 50 K B 3.29 2487 VREF FULL + 35 K B 2.77 1982 VREF FULL + 25 K B 2.36 1545 VREF FULL + 15 K B 1.88 1050 VREF FULL + 15 K B 2.00 1155

VREF FULL + 50 K B 3.29 2457 VREF FULL + 35 K B 2.77 1965 VREF FULL + 20 K B 2.21 1378 VREF FULL + 10 K B 1.76 938 VREF FULL + 10 K B 1.88 1037

3

Factor VREF (KIAS)

4 (5)

Factor VREF (KIAS)

NOT USABLE

VREF FULL

K 1.66

Factor

FULL

+5

B 807

VREF FULL K 1.57

B 722

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 24

Landing

REVISION 21

AOM-1502-003

Distance in feet VREF (KIAS)

PERFORMANCE

AIRPLANE OPERATIONS MANUAL FLAP/SLAT

FAIL WITH SHAKER ANTICIPATED CONFIGURATION TABLE - WET RUNWAY

LANDING

ALD = (ULD x K) – B Distance in feet VREF (KIAS)

SLAT → FLAP ↓ 0

Factor VREF (KIAS)

1

Factor VREF (KIAS)

2

Factor VREF (KIAS)

0

1 (2) (3)

4 (5) (FULL)

VREF FULL + 60 K B 3.63 2805 VREF FULL + 40 K B 2.94 2185 VREF FULL + 30 K B 2.52 1732

VREF FULL + 50 K B 3.62 2759 VREF FULL + 40 K B 2.95 2156 VREF FULL + 25 K B 2.36 1545 VREF FULL + 15 K B 1.88 1050 VREF FULL + 15 K B 2.00 1155

VREF FULL + 50 K B 3.62 2723 VREF FULL + 40 K B 2.95 2136 VREF FULL + 20 K B 2.36 1535 VREF FULL + 10 K B 1.76 938 VREF FULL + 10 K B 1.88 1037

3

Factor VREF (KIAS)

4 (5)

Factor VREF (KIAS)

NOT USABLE

VREF FULL

K 1.66

AOM-1502-003

Factor

FULL

+5

B 807

VREF FULL K 1.57

B 722

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 25

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

FLAP/SLAT FAIL WITHOUT SHAKER ANTICIPATED LANDING CONFIGURATION TABLE - WET RUNWAY + 10 kt OVERSPEED ALD = (ULD x K) – B SLAT → FLAP ↓ 0

Factor VREF (KIAS)

1

Factor VREF (KIAS)

2

Factor VREF (KIAS)

0

1 (2) (3)

4 (5) (FULL)

VREF FULL + 60 K B 3.96 3064 VREF FULL + 35 K B 3.12 2352 VREF FULL + 30 K B 2.86 2073

VREF FULL + 50 K B 3.62 2759 VREF FULL + 35 K B 3.12 2320 VREF FULL + 25 K B 2.69 1886 VREF FULL + 15 K B 2.15 1322 VREF FULL + 15 K B 2.29 1430

VREF FULL + 50 K B 3.62 2723 VREF FULL + 35 K B 3.12 2293 VREF FULL + 20 K B 2.53 1703 VREF FULL + 10 K B 2.01 1171 VREF FULL + 10 K B 2.15 1276

3

Factor VREF (KIAS)

4 (5)

Factor VREF (KIAS)

NOT USABLE

VREF FULL

K 1.85

Factor

FULL

+5

B 906

VREF FULL K 1.76

B 787

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 26

Landing

REVISION 21

AOM-1502-003

Distance in feet VREF (KIAS)

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

FLAP/SLAT FAIL WITH SHAKER ANTICIPATED LANDING CONFIGURATION TABLE - WET RUNWAY + 10 kt OVERSPEED ALD = (ULD x K) – B Distance in feet VREF (KIAS)

SLAT → FLAP ↓ 0

Factor VREF (KIAS)

1

Factor VREF (KIAS)

2

Factor VREF (KIAS)

0

1 (2) (3)

4 (5) (FULL)

VREF FULL + 60 K B 3.96 3064 VREF FULL + 40 K B 3.29 2507 VREF FULL + 30 K B 2.86 2073

VREF FULL + 60 K B 3.95 3005 VREF FULL + 40 K B 3.29 2467 VREF FULL + 25 K B 2.69 1886 VREF FULL + 15 K B 2.15 1322 VREF FULL + 15 K B 2.29 1430

VREF FULL + 60 K B 3.95 2963 VREF FULL + 40 K B 3.29 2441 VREF FULL + 25 K B 2.69 1867 VREF FULL + 10 K B 2.01 1171 VREF FULL + 10 K B 2.15 1276

3

Factor VREF (KIAS)

4 (5)

Factor VREF (KIAS)

NOT USABLE

VREF FULL

K 1.85

Factor

FULL

+5

B 906

VREF FULL K 1.76

B 787

AOM-1502-003

"" "

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 27

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE !EMBRAER 175 Models

Unfactored landing distance is the actual distance to land the airplane on a zero slope, ISA temperature, dry runway, from a point 50 ft above runway threshold at Vref, using only the brakes and spoilers as deceleration devices (i.e., no engine reverse thrust is used). The unfactored landing distances provided are valid for anti-ice ON and OFF.

NORMAL OPERATION The required landing distance for dispatch is the unfactored landing distance increased by 66.7% for dry runway, or 91.7% for wet runway. For obtaining the DRY runway factored distance, multiply unfactored landing distance by 1.667. For obtaining the WET runway factored distance, multiply unfactored landing distance by 1.917. The unfactored landing distance corrections are valid for overspeeds up to Vref + 20 and no failure.

EMERGENCY/ABNORMAL OPERATION LANDING DISTANCE CORRECTION FACTOR - DRY RUNWAYS The Actual Landing Distance is equal to the Unfactored Landing Distance for flaps FULL multiplied by the associated landing distance factor for DRY runways.

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 28

Landing

REVISION 21

AOM-1502-003

The DRY + OVSP corresponds to the factor associated to a 10 kt overspeed (above the non-normal VREF) on a dry runway.

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

LANDING DISTANCE CORRECTION FACTOR - WET RUNWAYS The WET + OVSP corresponds to the factor associated to a 10 kt overspeed (above the non-normal VREF) on a wet runway. To calculate the actual landing distance on a WET runway, the pilot must do the steps below: 1. Recognize the system malfunction; 2. Find the Unfactored Landing Distance (ULD) for Flaps Full in Quick Reference Handbook (QRH), considering the airplane type, altitude, landing weight and ice accretion condition; 3.

Find the multiplier factor value (K) on the table with Landing Distance Correction Factors and multiply the obtained values of (ULD) and (K). 4. In the same line of table with Landing Distance Correction Factors, find the value (B). 5.

Subtract (B) from the result of step (3). This is the actual landing distance (ALD) to safely land the airplane on wet runways condition.

ALD = (ULD x K) – B

AOM-1502-003

NOTE: The calculated value is the actual distance to safely land the airplane, but no distance margins are included. The distance margin available is the difference between the runway length and the calculated value.

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 29

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP 5 – WITHOUT ICE ACCRETION PRESSURE ALTITUDE (ft) 0

WEIGHT (lb)

1000 WIND (kt)

-10

0

10

20

-10

0

10

20

50000

2444

2036

1909

1786

2484

2073

1945

1821

55000

2587

2167

2036

1909

2631

2208

2076

1948

60000

2730

2298

2163

2032

2779

2343

2206

2074

65000

2876

2430

2291

2156

2929

2479

2338

2202

70000

3034

2565

2421

2282

3095

2618

2473

2332

75000

3206

2708

2556

2412

3274

2768

2613

2467

80000

3385

2863

2702

2548

3471

2938

2775

2618

85000

3596

3043

2874

2712

3689

3126

2954

2788

Per 5 kt above Vref (and no failure) add 236 ft. PRESSURE ALTITUDE (ft) 2000

WEIGHT (lb)

3000 WIND (kt)

-10

0

10

20

-10

0

10

20

50000

2525

2112

1982

1857

2568

2152

2022

1895

55000

2677

2250

2117

1988

2725

2295

2160

2030

60000

2829

2389

2251

2118

2882

2438

2299

2164

65000

2984

2530

2388

2250

3044

2583

2439

2300

70000

3159

2674

2527

2385

3226

2732

2583

2439

75000

3344

2832

2674

2524

3429

2908

2747

2592

80000

3559

3017

2851

2691

3653

3101

2931

2768

85000

3787

3213

3037

2868

3890

3304

3124

2952

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 30

Landing

REVISION 21

AOM-1502-003

Per 5 kt above Vref (and no failure) add 255 ft.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP 5 – WITHOUT ICE ACCRETION PRESSURE ALTITUDE (ft) 4000

WEIGHT (lb)

5000 WIND (kt)

-10

0

10

20

-10

0

10

20

50000

2613

2193

2062

1935

2659

2236

2103

1975

55000

2774

2341

2205

2074

2825

2387

2251

2118

60000

2937

2488

2348

2212

2992

2540

2398

2261

65000

3107

2638

2493

2352

3172

2694

2548

2406

70000

3296

2793

2641

2496

3374

2864

2707

2560

75000

3518

2987

2823

2666

3609

3068

2902

2741

80000

3750

3187

3014

2848

3851

3277

3101

2931

85000

3998

3399

3216

3040

4109

3497

3310

3131

Per 5 kt above Vref (and no failure) add 276 ft. PRESSURE ALTITUDE (ft) 6000

WEIGHT (lb)

7000 WIND (kt)

-10

0

10

20

-10

0

10

20

50000

2706

2279

2146

2017

2756

2326

2191

2060

55000

2877

2436

2298

2164

2933

2487

2348

2212

60000

3050

2593

2450

2311

3112

2649

2505

2364

65000

3239

2753

2605

2461

3312

2816

2666

2521

70000

3460

2941

2781

2630

3551

3022

2859

2703

75000

3704

3153

2984

2820

3804

3243

3070

2904

80000

3956

3370

3191

3018

4067

3469

3285

3109

85000

4226

3600

3409

3226

4349

3709

3513

3326

AOM-1502-003

Per 5 kt above Vref (and no failure) add 301 ft.

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 31

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP 5 – WITHOUT ICE ACCRETION PRESSURE ALTITUDE (ft) 8000

WEIGHT (lb)

WIND (kt) -10

0

10

20

50000

2807

2373

2238

2106

55000

2990

2540

2399

2263

60000

3176

2708

2561

2420

65000

3397

2891

2738

2591

70000

3645

3107

2941

2781

75000

3909

3336

3160

2990

80000

4184

3572

3384

3205

85000

4479

3823

3623

3431

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 32

Landing

REVISION 21

AOM-1502-003

Per 5 kt above Vref (and no failure) add 314 ft.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP FULL – WITHOUT ICE ACCRETION PRESSURE ALTITUDE (ft) 0

WEIGHT (lb)

1000 WIND (kt)

-10

0

10

20

-10

0

10

20

50000

2306

1907

1782

1662

2342

1941

1815

1694

55000

2432

2023

1895

1771

2472

2060

1931

1806

60000

2557

2137

2006

1879

2601

2178

2045

1917

65000

2683

2252

2117

1987

2730

2295

2159

2028

70000

2811

2367

2229

2095

2861

2414

2274

2139

75000

2943

2482

2340

2202

3000

2532

2388

2249

80000

3035

2555

2410

2269

3096

2607

2461

2319

85000

3155

2655

2501

2357

3225

2718

2562

2414

Per 5 kt above Vref (and no failure) add 203 ft. PRESSURE ALTITUDE (ft) 2000

WEIGHT (lb)

3000 WIND (kt)

-10

0

10

20

-10

0

10

20

50000

2380

1976

1850

1727

2419

2013

1885

1762

55000

2513

2098

1968

1843

2556

2138

2007

1881

60000

2645

2219

2086

1956

2692

2262

2128

1997

65000

2779

2340

2203

2070

2830

2387

2248

2114

70000

2914

2462

2321

2184

2970

2513

2370

2232

75000

3059

2584

2439

2298

3122

2638

2491

2349

80000

3159

2663

2513

2370

3233

2730

2575

2430

85000

3302

2786

2628

2475

3382

2858

2697

2542

AOM-1502-003

Per 5 kt above Vref (and no failure) add 217 ft.

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 33

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP FULL – WITHOUT ICE ACCRETION PRESSURE ALTITUDE (ft) 4000

WEIGHT (lb)

5000 WIND (kt)

-10

0

10

20

-10

0

10

20

50000

2460

2051

1922

1798

2502

2089

1960

1835

55000

2601

2179

2048

1920

2646

2221

2088

1960

60000

2741

2307

2171

2040

2790

2353

2216

2083

65000

2882

2435

2296

2160

2936

2485

2344

2207

70000

3029

2565

2421

2281

3090

2618

2473

2332

75000

3193

2700

2551

2407

3268

2766

2615

2469

80000

3311

2799

2642

2493

3391

2871

2711

2558

85000

3466

2932

2768

2611

3552

3009

2842

2682

Per 5 kt above Vref (and no failure) add 232 ft. PRESSURE ALTITUDE (ft) 6000

WEIGHT (lb)

7000 WIND (kt)

-10

0

10

20

-10

0

10

20

50000

2544

2129

1999

1873

2589

2170

2039

1912

55000

2693

2265

2131

2001

2742

2310

2175

2044

60000

2841

2400

2262

2128

2895

2449

2310

2175

65000

2991

2536

2393

2255

3050

2589

2445

2306

70000

3157

2677

2530

2387

3232

2743

2594

2450

75000

3347

2837

2681

2533

3429

2911

2751

2600

80000

3474

2946

2783

2626

3562

3024

2858

2699

85000

3641

3089

2919

2756

3736

3173

3000

2833

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 34

Landing

REVISION 21

AOM-1502-003

Per 5 kt above Vref (and no failure) add 249 ft.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP FULL – WITHOUT ICE ACCRETION PRESSURE ALTITUDE (ft) 8000

WEIGHT (lb)

WIND (kt) -10

0

10

20

50000

2636

2213

2081

1953

55000

2793

2357

2221

2089

60000

2951

2501

2360

2223

65000

3111

2646

2500

2359

70000

3311

2812

2661

2514

75000

3515

2988

2825

2670

80000

3653

3105

2937

2774

85000

3834

3260

3084

2914

AOM-1502-003

Per 5 kt above Vref (and no failure) add 259 ft.

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 35

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP 5 – WITH ICE ACCRETION PRESSURE ALTITUDE (ft) 0

WEIGHT (lb)

1000 WIND (kt)

-10

0

10

20

-10

0

10

20

50000

2663

2239

2107

1979

2708

2282

2148

2019

55000

2826

2389

2252

2120

2877

2436

2298

2164

60000

2994

2541

2399

2262

3050

2593

2450

2311

65000

3175

2696

2550

2408

3240

2753

2605

2461

70000

3380

2869

2712

2565

3463

2944

2784

2632

75000

3613

3072

2906

2746

3705

3154

2985

2822

80000

3856

3282

3106

2937

3958

3373

3193

3021

85000

4116

3504

3317

3138

4228

3603

3413

3230

Per 5 kt above Vref (and no failure) add 260 ft. PRESSURE ALTITUDE (ft) 2000

WEIGHT (lb)

3000 WIND (kt)

-10

0

10

20

-10

0

10

20

50000

2755

2325

2191

2061

2805

2372

2236

2104

55000

2930

2484

2345

2210

2985

2535

2395

2258

60000

3108

2646

2502

2362

3171

2702

2557

2415

65000

3313

2817

2667

2522

3395

2889

2736

2589

70000

3549

3022

2859

2702

3640

3103

2937

2778

75000

3800

3240

3067

2902

3901

3330

3154

2985

80000

4064

3467

3284

3108

4176

3566

3379

3200

85000

4347

3708

3513

3326

4471

3817

3618

3427

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 36

Landing

REVISION 21

AOM-1502-003

Per 5 kt above Vref (and no failure) add 282 ft.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP 5 – WITH ICE ACCRETION PRESSURE ALTITUDE (ft) 4000

WEIGHT (lb)

5000 WIND (kt)

-10

0

10

20

-10

0

10

20

50000

2857

2419

2282

2150

2909

2468

2330

2196

55000

3042

2588

2446

2309

3101

2642

2499

2360

60000

3237

2761

2613

2470

3314

2828

2679

2534

65000

3480

2966

2808

2659

3568

3045

2883

2731

70000

3735

3188

3019

2857

3833

3276

3104

2939

75000

4007

3424

3244

3072

4116

3521

3338

3162

80000

4294

3670

3479

3296

4415

3778

3582

3395

85000

4602

3932

3728

3533

4738

4052

3843

3643

Per 5 kt above Vref (and no failure) add 308 ft. PRESSURE ALTITUDE (ft) 6000

WEIGHT (lb)

7000 WIND (kt)

-10

0

10

20

-10

0

10

20

50000

2964

2518

2379

2244

3021

2571

2431

2294

55000

3161

2698

2553

2413

3225

2757

2611

2469

60000

3395

2900

2749

2602

3482

2976

2822

2673

65000

3659

3127

2962

2805

3755

3214

3046

2884

70000

3934

3367

3192

3024

4042

3463

3285

3113

75000

4229

3622

3436

3256

4350

3729

3539

3356

80000

4542

3890

3691

3499

4677

4009

3805

3609

85000

4881

4177

3963

3758

5033

4310

4090

3880

AOM-1502-003

Per 5 kt above Vref (and no failure) add 338 ft.

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 37

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP 5 – WITH ICE ACCRETION PRESSURE ALTITUDE (ft) 8000

WEIGHT (lb)

WIND (kt) -10

0

10

20

50000

3081

2627

2484

2346

55000

3302

2828

2679

2535

60000

3571

3054

2898

2747

65000

3856

3304

3133

2969

70000

4154

3564

3382

3207

75000

4476

3841

3646

3459

80000

4819

4134

3925

3724

85000

5192

4449

4223

4008

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 38

Landing

REVISION 21

AOM-1502-003

Per 5 kt above Vref (and no failure) add 354 ft.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP FULL – WITH ICE ACCRETION PRESSURE ALTITUDE (ft) 0

WEIGHT (lb)

1000 WIND (kt)

-10

0

10

20

-10

0

10

20

50000

2438

2030

1902

1778

2478

2067

1938

1814

55000

2576

2157

2025

1898

2620

2197

2065

1936

60000

2712

2281

2146

2015

2760

2324

2188

2056

65000

2852

2408

2269

2134

2903

2455

2315

2179

70000

2994

2534

2391

2252

3052

2585

2440

2300

75000

3149

2662

2514

2372

3222

2725

2575

2431

80000

3257

2751

2595

2450

3333

2820

2661

2511

85000

3358

2836

2676

2522

3438

2908

2745

2588

Per 5 kt above Vref (and no failure) add 211 ft. PRESSURE ALTITUDE (ft) 2000

WEIGHT (lb)

3000 WIND (kt)

-10

0

10

20

-10

0

10

20

50000

2519

2105

1975

1850

2562

2145

2014

1888

55000

2665

2238

2105

1976

2712

2282

2147

2017

60000

2809

2370

2232

2099

2860

2417

2278

2144

65000

2957

2504

2362

2225

3012

2555

2412

2274

70000

3112

2638

2492

2350

3184

2701

2553

2410

75000

3296

2792

2639

2492

3375

2862

2705

2556

80000

3412

2890

2730

2575

3495

2965

2801

2644

85000

3521

2982

2816

2657

3609

3060

2891

2729

AOM-1502-003

Per 5 kt above Vref (and no failure) add 225 ft.

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 39

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP FULL – WITH ICE ACCRETION PRESSURE ALTITUDE (ft) 4000

WEIGHT (lb)

5000 WIND (kt)

-10

0

10

20

-10

0

10

20

50000

2606

2186

2054

1927

2651

2228

2095

1966

55000

2761

2327

2191

2060

2810

2373

2236

2103

60000

2913

2466

2326

2190

2967

2516

2374

2238

65000

3070

2608

2464

2324

3136

2667

2521

2379

70000

3259

2767

2617

2472

3336

2834

2682

2535

75000

3457

2936

2775

2623

3541

3011

2847

2691

80000

3582

3042

2876

2716

3671

3121

2952

2790

85000

3700

3141

2969

2805

3794

3225

3050

2882

Per 5 kt above Vref (and no failure) add 242 ft. PRESSURE ALTITUDE (ft) 6000

WEIGHT (lb)

7000 WIND (kt)

-10

0

10

20

-10

0

10

20

50000

2697

2271

2137

2007

2746

2316

2181

2051

55000

2861

2420

2282

2148

2915

2470

2330

2195

60000

3023

2567

2425

2286

3081

2621

2477

2338

65000

3209

2731

2583

2440

3285

2799

2649

2504

70000

3416

2904

2749

2601

3499

2980

2820

2669

75000

3628

3089

2923

2763

3719

3172

3002

2840

80000

3763

3204

3032

2867

3861

3291

3116

2947

85000

3892

3312

3134

2963

3995

3404

3222

3048

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 40

Landing

REVISION 21

AOM-1502-003

Per 5 kt above Vref (and no failure) add 260 ft.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

UNFACTORED LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES MAXIMUM MANUAL BRAKING FLAP FULL – WITH ICE ACCRETION PRESSURE ALTITUDE (ft) 8000

WEIGHT (lb)

WIND (kt) -10

0

10

20

50000

2797

2363

2227

2095

55000

2970

2521

2380

2244

60000

3151

2685

2539

2398

65000

3364

2869

2717

2570

70000

3587

3058

2895

2741

75000

3815

3257

3085

2919

80000

3962

3382

3203

3031

85000

4103

3499

3314

3136

AOM-1502-003

Per 5 kt above Vref (and no failure) add 270 ft.

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 41

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

LANDING DISTANCE CORRECTION FACTOR EMBRAER 175 - DRY RUNWAYS Factor Flaps – Speed

DUAL ENGINE FAILURE

Slat/Flap 3 – VREF or 130 KIAS

JAMMED CONTROL COLUMN (PITCH)

DRY

DRY + OVSP

2.10

2.60

FULL

+ 20

Slat/Flap 5 – VREF

FULL

+ 15

1.40

1.55

JAMMED CONTROL WHEEL (ROLL)

Slat/Flap 5 – VREF

FULL

+ 15

1.40

1.55

LOSS OF HYDRAULIC SYSTEM 1

Slat/Flap Full – VREF

FULL

1.90

2.20

LOSS OF HYDRAULIC SYSTEM 2

Slat/Flap Full – VREF

FULL

1.80

2.10

LOSS OF HYDRAULIC SYSTEM 1 AND 2

Slat/Flap 5 – VREF

FULL

+ 10

2.70

3.25

LOSS OF HYDRAULIC SYSTEM 1 AND 3

Slat/Flap 5 – VREF

FULL

+ 10

2.30

2.65

LOSS OF HYDRAULIC SYSTEM 2 AND 3

Slat/Flap 5 – VREF

FULL

+ 10

2.20

2.50

FULL

+ 20

1.40

1.70

FULL

+ 15

1.40

1.55

1.22

1.38

2.10

2.60

ONE ENGINE INOPERATIVE APPROACH Slat/Flap 5 – VREF AND LANDING Slat/Flap 5 – VREF STALL PROT FAIL

Slat/Flap Full – VREF 10

FULL

+

ELEC EMERGENCY

Slat/Flap 3 – VREF or 130 KIAS

DC BUS 1 OFF

Slat/Flap Full – VREF

FULL

1.15

1.30

DC BUS 2 OFF

Slat/Flap Full – VREF

FULL

1.20

1.40

DC ESS BUS 1 OFF

Slat/Flap Full – VREF

FULL

1.70

2.00

DC ESS BUS 2 OFF

Slat/Flap Full – VREF

FULL

1.80

2.10

GROUND SPOILERS FAIL

Slat/Flap Full – VREF

FULL

1.30

1.40

FULL

1.45

1.75

1.40

1.65

FULL

SPOILER NML MODE FAIL Slat/Flap Full – VREF ELEVATOR LH (RH) FAIL

Slat/Flap 5 – VREF

FULL

+ 20

+ 15

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 42

Landing

REVISION 21

AOM-1502-003

Emerg/Abnormal Procedure

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

Emerg/Abnormal Procedure PITCH TRIM FAIL SPOILER FAULT

DRY

DRY + OVSP 1.55

Slat/Flap 5 – VREF

FULL

+ 15

1.40

Slat/Flap 5 – VREF

FULL

+ 15

1.78

2.11

1.45

1.75

Slat/Flap Full – VREF

AILERON LH (RH) FAIL

Slat/Flap 5 – VREF

AVNX MAU 1A FAIL

Slat/Flap Full – VREF

AVNX MAU 1B FAIL

FULL

1.30

1.45

FULL

1.70

2.00

Slat/Flap Full – VREF

FULL

1.15

1.30

AVNX MAU 2B FAIL

Slat/Flap Full – VREF

FULL

1.65

1.85

AVNX MAU 3A FAIL

Slat/Flap Full – VREF

FULL

1.20

1.75

AVNX MAU 3B FAIL

Slat/Flap Full – VREF

FULL

FULL

+ 10

1.20

1.40

A-I WING FAIL or A-I WING Slat/Flap 5 – VREF FLAP 5 ICE 1 (2) LEAK

1.30

1.50

BRK LH (RH) FAIL

Slat/Flap Full – VREF

FULL

1.65

1.85

LG WOW SYS FAIL

Slat/Flap Full – VREF

FULL

1.30

1.75

BRK LH (RH) FAULT

Slat/Flap Full – VREF

FULL

1.65

1.85

DC BUS 1 OFF and DC Essential BUS 1 OFF SMOKE/ FIRE/ FUMES

AOM-1502-003

Factor Flaps – Speed

Slat/Flap 3 – VREF

DC Essential BUS 2 and DC Slat/Flap 3 – VREF BUS 2 OFF

FULL

+ 20

2.30

2.60

FULL

+ 20

2.50

2.90

DC Essential BUS 3 OFF

Slat/Flap 3 – VREF

FULL

+ 20

2.10

2.60

TRU ESS and TRU BUS AUTO

Slat/Flap 3 – VREF

FULL

+ 20

2.10

2.60

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 43

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

LANDING DISTANCE CORRECTION FACTOR EMBRAER 175 - WET RUNWAYS - DISTANCE IN FEET !!EMBRAER 175 models, length in British units

Flaps – Speed

WET + OVSP

WET K

B

K

B

DUAL ENGINE FAILURE

FULL

Slat/Flap 3 – VREF + 20 or 130 KIAS

4.10

2638

5.39

4193

JAMMED CONTROL COLUMN (PITCH)

Slat/Flap 5 – VREF FULL + 15

2.01

1148

2.30

1421

JAMMED CONTROL WHEEL (ROLL)

Slat/Flap 5 – VREF FULL + 15

2.01

1148

2.30

1421

2.82

1808

3.16

1926

2.57

1621

2.87

1742

LOSS OF HYDRAULIC SYSTEM 1 LOSS OF HYDRAULIC SYSTEM 2

Slat/Flap Full – VREF FULL

Slat/Flap Full – VREF FULL

LOSS OF HYDRAULIC SYSTEM 1 AND 2

Slat/Flap 5 – VREF FULL + 10

5.16

3307

5.92

3048

LOSS OF HYDRAULIC SYSTEM 1 AND 3

Slat/Flap 5 – VREF FULL + 10

3.42

2428

3.89

2779

LOSS OF HYDRAULIC SYSTEM 2 AND 3

Slat/Flap 5 – VREF FULL + 10

3.12

2152

3.53

2470

ONE ENGINE INOPERATIVE APPROACH AND LANDING

Slat/Flap 5 – VREF FULL + 20

2.30

1453

2.63

1772

Slat/Flap 5 – VREF FULL + 15

2.01

1148

2.30

1421

Slat/Flap Full – VREF + 10

1.98

1102

2.23

1240

STALL PROT FAIL

FULL

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 44

Landing

REVISION 21

AOM-1502-003

Emerg/Abnormal Procedure

Factor ALD = (ULD x K) – B

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

Emerg/Abnormal Procedure

Factor ALD = (ULD x K) – B Flaps – Speed

WET + OVSP

WET K

B

K

B

4.10

2638

5.39

4193

2.27

1424

2.54

1552

2.47

1588

2.77

1716

2.62

1611

2.93

1722

2.88

1788

3.23

1877

GROUND SPOILERS Slat/Flap Full – VREF FAIL FULL

1.83

994

2.07

1093

SPOILER NML MODE FAIL

2.53

1493

2.95

1975

FULL

ELEVATOR LH (RH) FAIL

Slat/Flap 5 – VREF FULL + 15

2.11

1066

2.40

1325

Slat/Flap 5 – VREF + 15

2.01

1148

2.30

1421

Slat/Flap 5 – VREF FULL + 15

3.01

2001

3.56

2490

2.53

1493

2.90

1722

1.88

1037

2.15

1276

2.58

1667

2.83

1778

1.69

869

1.90

965

2.44

1529

2.67

1631

2.53

1493

2.90

1722

ELEC EMERGENCY

DC BUS 1 OFF

Slat/Flap 3 – VREF + 20 or 130 KIAS FULL

Slat/Flap Full – VREF FULL

DC BUS 2 OFF

Slat/Flap Full – VREF FULL

DC ESS BUS 1 OFF

Slat/Flap Full – VREF FULL

DC ESS BUS 2 OFF

Slat/Flap Full – VREF FULL

PITCH TRIM FAIL

Slat/Flap Full – VREF

FULL

SPOILER FAULT

Slat/Flap Full – VREF FULL

AILERON LH (RH) FAIL AVNX MAU 1A FAIL

Slat/Flap 5 – VREF FULL + 10 Slat/Flap Full – VREF FULL

AVNX MAU 1B FAIL

Slat/Flap Full – VREF FULL

AVNX MAU 2B FAIL

Slat/Flap Full – VREF FULL

AVNX MAU 3A FAIL

Slat/Flap Full – VREF

AOM-1502-003

FULL

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 45

PERFORMANCE

Emerg/Abnormal Procedure

AIRPLANE OPERATIONS MANUAL Factor ALD = (ULD x K) – B Flaps – Speed

WET + OVSP

WET K

B

K

B

1.83

994

2.07

1093

2.24

1588

2.53

1870

2.44

1529

2.67

1631

3.33

1549

3.83

1345

2.16

1302

2.38

1404

3.30

2024

3.88

2792

Slat/Flap 3 – VREF FULL + 20

3.65

2293

4.33

3179

DC Slat/Flap 3 – VREF Essential FULL + 20 BUS 3 OFF

4.10

2638

5.39

4193

TRU ESS and TRU BUS AUTO

4.10

2638

5.39

4193

AVNX MAU 3B FAIL

Slat/Flap Full – VREF FULL

A-I WING FAIL or A-I WING 1 (2) LEAK BRK LH (RH) FAIL

Slat/Flap 5 – VREF FLAP 5 ICE

Slat/Flap Full – VREF FULL

LG WOW SYS FAIL

Slat/Flap Full – VREF FULL

BRK LH (RH) FAULT

Slat/Flap Full – VREF FULL

DC BUS 1 OFF and Slat/Flap 3 – VREF DC FULL + 20 Essential BUS 1 OFF DC Essential SMOKE/ BUS 2 and FIRE/ DC BUS 2 FUMES OFF

Slat/Flap 3 – VREF FULL + 20

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 46

Landing

REVISION 21

AOM-1502-003

""

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

FLAP (SLAT) FAIL - EMBRAER 175 - DRY RUNWAYS The Actual Landing Distance is equal to the Unfactored Landing Distance for flaps FULL multiplied by the associated landing distance factor for DRY runways. Refer to the following tables for reference speed and factor to be applied to the unfactored landing distance, for a flap/slat fail or a flap/slat fail with shaker anticipated: FLAP/SLAT FAIL WITHOUT SHAKER ANTICIPATED LANDING CONFIGURATION TABLE - DRY RUNWAY !!175 models, EASA/FAA certification

SLAT → FLAP ↓

0

1 (2) (3)

VREF FULL + 60 VREF (KIAS) 0 Factor 2.41 VREF FULL + 35 VREF (KIAS) 1 Factor 1.46 VREF FULL + 30 VREF (KIAS) 2 Factor 1.38 VREF (KIAS) 3 (4) Factor (5) NOT USABLE VREF (KIAS) FULL Factor

VREF

FULL

4 (5) (FULL)

+ 50 VREF

1.75 VREF

FULL

+ 35 VREF

2.00 VREF

FULL

FULL

+ 50

FULL

+ 35

2.00 + 25 VREF

1.55 VREF

FULL

1.80

FULL

+ 20

1.28 + 15 VREF

FULL

+ 10

1.31

1.29

VREF FULL + 5 1.06

VREF FULL 1.00

AOM-1502-003

""

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 47

PERFORMANCE

FLAP/SLAT

AIRPLANE OPERATIONS MANUAL

FAIL WITH SHAKER ANTICIPATED CONFIGURATION TABLE - DRY RUNWAY SLAT → FLAP ↓

0

1 (2) (3)

VREF FULL + 60 VREF (KIAS) 0 Factor 2.41 VREF FULL + 40 VREF (KIAS) 1 Factor 1.55 VREF FULL + 30 VREF (KIAS) 2 Factor 1.38 VREF (KIAS) 3 (4) Factor (5) NOT USABLE VREF (KIAS) FULL Factor

VREF

FULL

LANDING

4 (5) (FULL)

+ 60 VREF

2.00 VREF

FULL

+ 40 VREF

1.60 VREF

FULL

FULL

+ 60

FULL

+ 40

1.60 + 25 VREF

1.55 VREF

FULL

2.00

FULL

+ 25

1.57 + 15 VREF

FULL

+ 10

1.31

1.29

VREF FULL + 5 1.06

VREF FULL 1.00

FLAP/SLAT FAIL WITHOUT SHAKER ANTICIPATED LANDING CONFIGURATION TABLE - DRY RUNWAY + 10 kt OVERSPEED

0

1 (2) (3)

VREF FULL + 60 VREF (KIAS) 0 Factor 2.10 VREF FULL + 35 VREF (KIAS) 1 Factor 1.74 VREF FULL + 30 VREF (KIAS) 2 Factor 1.54 VREF (KIAS) 3 (4) Factor (5) NOT USABLE VREF (KIAS) FULL Factor

VREF

FULL

4 (5) (FULL)

+ 50 VREF

1.97 VREF

FULL

+ 35 VREF

1.72 VREF

FULL

FULL

+ 50

FULL

+ 35

1.71 + 25 VREF

1.74 VREF

FULL

1.96

FULL

+ 20

1.48 + 15 VREF

FULL

+ 10

1.50

1.44

VREF FULL + 5 1.12

VREF FULL 1.24

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 48

Landing

REVISION 21

AOM-1502-003

SLAT → FLAP ↓

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

FLAP/SLAT FAIL WITH SHAKER ANTICIPATED LANDING CONFIGURATION TABLE - DRY RUNWAY + 10 kt OVERSPEED SLAT → FLAP ↓

0

1 (2) (3)

AOM-1502-003

VREF FULL + 60 VREF FULL + 60 VREF (KIAS) 0 Factor 2.18 2.15 VREF FULL + 40 VREF FULL + 40 VREF (KIAS) 1 Factor 1.82 1.78 VREF FULL + 30 VREF FULL + 25 VREF (KIAS) 2 Factor 1.54 1.72 VREF FULL + 15 VREF (KIAS) 3 (4) Factor (5) 1.50 NOT USABLE VREF FULL + 5 VREF (KIAS) FULL Factor 1.12

4 (5) (FULL) VREF

FULL

+ 60

2.12 VREF

FULL

+ 40

1.80 VREF

FULL

+ 25

1.73 VREF

FULL

+ 10

1.47 VREF FULL 1.24

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 49

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

FLAP (SLAT) FAIL - LANDING CONFIGURATION TABLE - WET RUNWAYS The WET + OVSP corresponds to the factor associated to a 10 kt overspeed (above the non-normal VREF) on a wet runway. To calculate the actual landing distance on a WET runway, the pilot must do the steps below: 1. Recognize the FLAP/SLAT position; 2. Find the Unfactored Landing Distance (ULD) for Flaps Full in Quick Reference Handbook (QRH), considering the airplane type, altitude, landing weight and ice accretion condition; 3.

Find the multiplier factor value (K) on the table with FLAP/SLAT Fail - Landing Configuration and multiply the obtained values of (ULD) and (K). 4. In the same line of table with FLAP/SLAT Fail - Landing Configuration, find the value (B). 5.

Subtract (B) from the result of step (3). This is the actual landing distance (ALD) to safely land the airplane on wet runways condition.

ALD = (ULD x K) – B

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 50

Landing

REVISION 21

AOM-1502-003

NOTE: The calculated value is the actual distance to safely land the airplane, but no distance margins are included. The distance margin available is the difference between the runway length and the calculated value.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

FLAP (SLAT) FAIL - EMBRAER 175 - WET RUNWAYS !!EMBRAER 175 models, length in British units

FLAP/SLAT FAIL WITHOUT SHAKER ANTICIPATED LANDING CONFIGURATION TABLE - WET RUNWAY ALD = (ULD x K) – B Distance in feet VREF (KIAS)

SLAT → FLAP ↓ 0

Factor VREF (KIAS)

1

Factor VREF (KIAS)

2

Factor VREF (KIAS)

0

1 (2) (3)

4 (5) (FULL)

VREF FULL + 60 K B 3.63 2805 VREF FULL + 35 K B 2.77 2008 VREF FULL + 30 K B 2.52 1732

VREF FULL + 50 K B 3.29 2487 VREF FULL + 35 K B 2.77 1982 VREF FULL + 25 K B 2.36 1545 VREF FULL + 15 K B 1.88 1050 VREF FULL + 15 K B 2.00 1155

VREF FULL + 50 K B 3.29 2457 VREF FULL + 35 K B 2.77 1965 VREF FULL + 20 K B 2.21 1378 VREF FULL + 10 K B 1.76 938 VREF FULL + 10 K B 1.88 1037

3

Factor VREF (KIAS)

4 (5)

Factor VREF (KIAS)

NOT USABLE

VREF FULL

K 1.66

AOM-1502-003

Factor

FULL

+5

B 807

VREF FULL K 1.57

B 722

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 51

PERFORMANCE

FLAP/SLAT

AIRPLANE OPERATIONS MANUAL

FAIL WITH SHAKER ANTICIPATED CONFIGURATION TABLE - WET RUNWAY

LANDING

ALD = (ULD x K) – B SLAT → FLAP ↓ 0

Factor VREF (KIAS)

1

Factor VREF (KIAS)

2

Factor VREF (KIAS)

0

1 (2) (3)

4 (5) (FULL)

VREF FULL + 60 K B 3.63 2805 VREF FULL + 40 K B 2.94 2185 VREF FULL + 30 K B 2.52 1732

VREF FULL + 50 K B 3.62 2759 VREF FULL + 40 K B 2.95 2156 VREF FULL + 25 K B 2.36 1545 VREF FULL + 15 K B 1.88 1050 VREF FULL + 15 K B 2.00 1155

VREF FULL + 50 K B 3.62 2723 VREF FULL + 40 K B 2.95 2136 VREF FULL + 20 K B 2.36 1535 VREF FULL + 10 K B 1.76 938 VREF FULL + 10 K B 1.88 1037

3

Factor VREF (KIAS)

4 (5)

Factor VREF (KIAS)

NOT USABLE

VREF FULL

K 1.66

Factor

FULL

+5

B 807

VREF FULL K 1.57

B 722

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 52

Landing

REVISION 21

AOM-1502-003

Distance in feet VREF (KIAS)

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

FLAP/SLAT FAIL WITHOUT SHAKER ANTICIPATED LANDING CONFIGURATION TABLE - WET RUNWAY + 10 kt OVERSPEED ALD = (ULD x K) – B Distance in feet VREF (KIAS)

SLAT → FLAP ↓ 0

Factor VREF (KIAS)

1

Factor VREF (KIAS)

2

Factor VREF (KIAS)

0

1 (2) (3)

4 (5) (FULL)

VREF FULL + 60 K B 3.96 3064 VREF FULL + 35 K B 3.12 2352 VREF FULL + 30 K B 2.86 2073

VREF FULL + 50 K B 3.62 2759 VREF FULL + 35 K B 3.12 2320 VREF FULL + 25 K B 2.69 1886 VREF FULL + 15 K B 2.15 1322 VREF FULL + 15 K B 2.29 1430

VREF FULL + 50 K B 3.62 2723 VREF FULL + 35 K B 3.12 2293 VREF FULL + 20 K B 2.53 1703 VREF FULL + 10 K B 2.01 1171 VREF FULL + 10 K B 2.15 1276

3

Factor VREF (KIAS)

4 (5)

Factor VREF (KIAS)

NOT USABLE

VREF FULL

K 1.85

AOM-1502-003

Factor

FULL

+5

B 906

VREF FULL K 1.76

B 787

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 53

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

FLAP/SLAT FAIL WITH SHAKER ANTICIPATED LANDING CONFIGURATION TABLE - WET RUNWAY + 10 kt OVERSPEED ALD = (ULD x K) – B Distance in feet VREF (KIAS)

SLAT → FLAP ↓ 0

Factor VREF (KIAS)

1

Factor VREF (KIAS)

2

Factor VREF (KIAS)

0

1 (2) (3)

4 (5) (FULL)

VREF FULL + 60 K B 3.96 3064 VREF FULL + 40 K B 3.29 2507 VREF FULL + 30 K B 2.86 2073

VREF FULL + 60 K B 3.95 3005 VREF FULL + 40 K B 3.29 2467 VREF FULL + 25 K B 2.69 1886 VREF FULL + 15 K B 2.15 1322 VREF FULL + 15 K B 2.29 1430

VREF FULL + 60 K B 3.95 2963 VREF FULL + 40 K B 3.29 2441 VREF FULL + 25 K B 2.69 1867 VREF FULL + 10 K B 2.01 1171 VREF FULL + 10 K B 2.15 1276

3

Factor VREF (KIAS)

4 (5)

Factor VREF (KIAS)

NOT USABLE

VREF FULL

K 1.85

Factor

FULL

+5

B 906

VREF FULL K 1.76

B 787 "" "

OPERATIONAL LANDING DISTANCE

The operational landing distance for contaminated runways contained

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 54

Landing

REVISION 21

AOM-1502-003

NOTE: The operational landing tables are intended for in-flight assessment, not for dispatch.

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

herein are the greater between the distance for contaminated runway as per EASA CS 25.1591 and the distance for WET runway as per FAA AC 25-32. The data do not include any multiplication factor or additional safety margin. The distances are obtained from 50 ft above threshold until full airplane stop. NOTE: Local operational regulations may require an additional factor to these distances. Emergency/abnormal multiplication factors were not analyzed for contaminated runways. For Emergency/Abnormal Operation refer to the Unfactored Landing Distance chapter. !Airplanes equipped with Autobrake, except J-Air, Operational Landing Runway Condition

In order to find the operational landing distance, enter the table with the current contaminant, flaps and autobrakes configuration, ice condition, and current landing weight. Then obtain a reference operational landing distance (OPLDREF). For autobrakes set to manual, data are provided for maximum manual braking effort. " !Airplanes not equipped with Autobrake, Operational Landing Runway Condition, except J-Air

In order to find the operational landing distance, enter the table with the current contaminant, flaps configuration, ice condition, and current landing weight. Then obtain a reference operational landing distance (OPLDREF). Data are provided for maximum manual braking effort. "

Apply corrections to the reference operational landing distance according to the formula below: Final altitude correction (%) = Altitude correction from the table x (Current Altitude in ft/1000 ft)

AOM-1502-003

Final tailwind correction (%) = Wind correction from the table x (Current tailwind component in kt/5 kt) Final overspeed correction (%) = Overspeed correction from the table x (Current overspeed in kt/5 kt)

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 55

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

Final reverse correction (%) = Reverse correction from the table. The operational landing distance on contaminated runways (OPLD) becomes: Additional Distance = OPLDREF x (Final Altitude Correction + Final Tailwind Correction + Final overspeed Correction + Final reverse correction) OPLD= OPLDREF + Additional distance Suppose that, for the following condition: – Airport pressure altitude: 4000 ft – Wind: 10 kt headwind – Overspeed: VREF + 5 kt – Reverses: All reverses operating For a certain contaminant, weight, flaps and autobrakes configuration (if applicable) and ice condition, the results from the table are: – OPLDREF: 1000 m – Altitude correction: 3% – Wind correction: 8% – Overspeed correction: 7% – Reverse correction: -3% Calculations: – Final Altitude Correction = 3% x (4000 ft/1000 ft) = 12% – Final Tailwind Correction = 8% x (0 kt/5 kt) = 0% – Final Overspeed Correction = 7% x (5 kt/5 kt) = 7% – Final reverse correction = -3%

– Additional Distance = 2000 ft x (12% + 0%+ 7% - 3%) = 2000 ft x 16% = 320 ft OPLD= 2000 ft + 320 ft = 2320 ft

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 56

Landing

REVISION 21

AOM-1502-003

Operational landing distance on contaminated runway:

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

OPERATIONAL LANDING DISTANCE

AOM-1502-003

!EMBRAER 170 Models, except J-Air, except Operational Landing Braking Action

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 57

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES STANDING WATER 1/8 in FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

61000

4619

5321

4054

4391

62000

4702

5415

4109

4464

63000

4785

5509

4164

4534

64000

4869

5599

4216

4605

65000

4948

5696

4273

4682

66000

5034

5788

4330

4754

67000

5115

5886

4384

4827

68000

5202

5981

4463

4901

69000

5286

6075

4531

4975

70000

5369

6170

4600

5050

71000

5456

6266

4670

5123

72000

5545

6363

4738

5195

73000

5631

6460

4806

5272

74000

5717

6558

4874

5349

75000

5804

6658

4943

5421

76000

5889

6755

4998

5479

77000

5964

6842

5037

5515

78000

6045

6934

5075

5555

79000

6127

7023

5109

5591

80000

6205

7115

5145

5630

81000

6286

7207

5181

5669

82000

6370

7296

5216

5706

83000

6446

7387

5276

5741

ALTITUDE

LANDING DISTANCE + 5% per 1000 ft above SL

WIND

LANDING DISTANCE +18% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 9% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 58

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

AOM-1502-003

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

OVERSPEED

LANDING DISTANCE + 9% per 5 kt above Vref

REVERSER

LANDING DISTANCE -5% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 59

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES STANDING WATER 1/2 in FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

61000

4146

4724

3702

3986

62000

4215

4805

3751

4049

63000

4285

4888

3800

4108

64000

4356

4966

3847

4169

65000

4423

5052

3898

4236

66000

4496

5133

3949

4298

67000

4565

5220

3997

4361

68000

4639

5304

4062

4425

69000

4711

5388

4120

4490

70000

4783

5474

4179

4555

71000

4858

5560

4239

4619

72000

4935

5647

4297

4682

73000

5009

5736

4355

4750

74000

5085

5825

4414

4818

75000

5161

5916

4474

4881

76000

5237

6006

4522

4934

77000

5304

6087

4557

4967

78000

5376

6174

4592

5004

79000

5450

6258

4622

5038

80000

5521

6345

4655

5074

81000

5594

6432

4688

5110

82000

5671

6517

4720

5145

83000

5741

6605

4774

5177

ALTITUDE

LANDING DISTANCE + 5% per 1000 ft above SL

WIND

LANDING DISTANCE +15% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 7% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 60

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

AOM-1502-003

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

OVERSPEED

LANDING DISTANCE + 8% per 5 kt above Vref

REVERSER

LANDING DISTANCE -3% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 61

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES SLUSH 1/8 in FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

61000

4646

5356

4073

4413

62000

4730

5451

4129

4487

63000

4814

5545

4185

4558

64000

4899

5636

4237

4629

65000

4978

5734

4294

4707

66000

5065

5826

4352

4780

67000

5147

5925

4406

4854

68000

5234

6020

4486

4928

69000

5320

6115

4554

5003

70000

5403

6210

4624

5078

71000

5491

6307

4695

5152

72000

5581

6404

4763

5224

73000

5667

6502

4831

5302

74000

5753

6601

4900

5379

75000

5841

6700

4970

5451

76000

5927

6799

5025

5510

77000

6002

6885

5064

5546

78000

6083

6978

5103

5586

79000

6166

7067

5136

5623

80000

6245

7159

5173

5662

81000

6325

7251

5209

5701

82000

6410

7340

5244

5738

83000

6487

7432

5305

5773

ALTITUDE

LANDING DISTANCE + 5% per 1000 ft above SL

WIND

LANDING DISTANCE +18% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 9% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 62

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

AOM-1502-003

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

OVERSPEED

LANDING DISTANCE + 9% per 5 kt above Vref

REVERSER

LANDING DISTANCE -5% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 63

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES SLUSH 1/2 in FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

61000

4224

4822

3761

4054

62000

4295

4905

3811

4118

63000

4368

4989

3862

4179

64000

4441

5070

3909

4242

65000

4509

5158

3961

4310

66000

4584

5241

4013

4374

67000

4656

5330

4062

4439

68000

4732

5416

4130

4505

69000

4806

5502

4189

4571

70000

4880

5589

4250

4638

71000

4957

5677

4311

4703

72000

5036

5766

4371

4768

73000

5112

5856

4431

4838

74000

5189

5947

4492

4907

75000

5268

6040

4553

4972

76000

5345

6131

4602

5025

77000

5413

6213

4638

5059

78000

5487

6301

4673

5096

79000

5563

6386

4704

5131

80000

5635

6474

4738

5168

81000

5710

6562

4772

5205

82000

5788

6648

4803

5240

83000

5859

6737

4859

5273

ALTITUDE

LANDING DISTANCE + 5% per 1000 ft above SL

WIND

LANDING DISTANCE +16% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 7% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 64

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

AOM-1502-003

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

OVERSPEED

LANDING DISTANCE + 8% per 5 kt above Vref

REVERSER

LANDING DISTANCE -4% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 65

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES WET SNOW 1/4 in FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

61000

4606

5091

4167

4449

62000

4660

5153

4214

4500

63000

4715

5215

4261

4549

64000

4771

5273

4304

4599

65000

4822

5337

4352

4653

66000

4878

5397

4401

4703

67000

4931

5460

4446

4754

68000

4987

5522

4494

4804

69000

5042

5582

4541

4855

70000

5095

5643

4588

4907

71000

5150

5704

4636

4957

72000

5207

5766

4682

5006

73000

5262

5828

4729

5058

74000

5316

5891

4775

5110

75000

5371

5953

4821

5158

76000

5425

6014

4857

5196

77000

5467

6064

4880

5215

78000

5514

6119

4902

5238

79000

5562

6170

4920

5257

80000

5607

6224

4941

5279

81000

5653

6277

4961

5300

82000

5702

6327

4980

5320

83000

5745

6380

5017

5338

ALTITUDE

LANDING DISTANCE + 4% per 1000 ft above SL

WIND

LANDING DISTANCE +12% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 2% per 5°C above ISA

SLOPE

LANDING DISTANCE + 7% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 66

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

AOM-1502-003

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

OVERSPEED

LANDING DISTANCE + 6% per 5 kt above Vref

REVERSER

LANDING DISTANCE -3% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 67

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES WET SNOW 1 in FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

61000

4189

4620

3823

4069

62000

4240

4679

3867

4118

63000

4292

4738

3911

4164

64000

4343

4795

3951

4211

65000

4392

4856

3996

4261

66000

4445

4913

4041

4309

67000

4495

4975

4083

4356

68000

4548

5034

4128

4404

69000

4599

5093

4172

4453

70000

4650

5152

4216

4502

71000

4703

5212

4262

4549

72000

4757

5272

4305

4596

73000

4809

5333

4348

4646

74000

4862

5394

4392

4696

75000

4915

5456

4436

4742

76000

4966

5517

4471

4779

77000

5009

5568

4494

4800

78000

5056

5623

4517

4823

79000

5104

5676

4537

4845

80000

5149

5731

4558

4868

81000

5196

5786

4580

4890

82000

5244

5838

4600

4912

83000

5288

5892

4636

4931

ALTITUDE

LANDING DISTANCE + 4% per 1000 ft above SL

WIND

LANDING DISTANCE +12% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 8% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 68

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

AOM-1502-003

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

OVERSPEED

LANDING DISTANCE + 8% per 5 kt above Vref

REVERSER

LANDING DISTANCE -2% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 69

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES DRY SNOW 1 in FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

61000

4594

5081

4148

4433

62000

4650

5145

4196

4486

63000

4707

5208

4245

4537

64000

4764

5268

4290

4588

65000

4817

5333

4340

4644

66000

4874

5393

4390

4696

67000

4929

5458

4437

4747

68000

4986

5520

4486

4799

69000

5042

5581

4534

4852

70000

5096

5643

4584

4904

71000

5153

5705

4633

4955

72000

5211

5767

4680

5005

73000

5266

5829

4727

5059

74000

5322

5892

4775

5112

75000

5377

5955

4823

5161

76000

5431

6016

4860

5199

77000

5475

6067

4883

5219

78000

5522

6121

4906

5243

79000

5571

6173

4926

5263

80000

5616

6226

4947

5285

81000

5663

6279

4968

5308

82000

5712

6330

4987

5328

83000

5755

6382

5025

5347

ALTITUDE

LANDING DISTANCE + 4% per 1000 ft above SL

WIND

LANDING DISTANCE +13% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 2% per 5°C above ISA

SLOPE

LANDING DISTANCE + 7% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 70

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

AOM-1502-003

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

OVERSPEED

LANDING DISTANCE + 6% per 5 kt above Vref

REVERSER

LANDING DISTANCE -3% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 71

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES DRY SNOW 2 in FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

61000

4431

4900

4008

4283

62000

4487

4963

4057

4336

63000

4544

5026

4105

4387

64000

4601

5086

4151

4438

65000

4654

5150

4201

4494

66000

4711

5211

4251

4545

67000

4765

5275

4297

4597

68000

4822

5337

4347

4649

69000

4878

5397

4394

4701

70000

4932

5459

4443

4753

71000

4988

5520

4493

4804

72000

5046

5582

4540

4854

73000

5101

5644

4587

4907

74000

5156

5707

4634

4960

75000

5212

5769

4682

5009

76000

5266

5830

4719

5048

77000

5310

5881

4744

5069

78000

5358

5936

4768

5093

79000

5406

5988

4788

5115

80000

5452

6042

4810

5138

81000

5499

6095

4833

5161

82000

5548

6146

4853

5183

83000

5592

6198

4891

5203

ALTITUDE

LANDING DISTANCE + 4% per 1000 ft above SL

WIND

LANDING DISTANCE +12% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 8% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 72

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

AOM-1502-003

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

OVERSPEED

LANDING DISTANCE + 7% per 5 kt above Vref

REVERSER

LANDING DISTANCE -3% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 73

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES COMPACTED SNOW FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

61000

4350

4822

3937

4214

62000

4402

4880

3982

4263

63000

4454

4938

4027

4310

64000

4506

4993

4068

4357

65000

4555

5053

4114

4408

66000

4608

5109

4160

4455

67000

4657

5168

4203

4503

68000

4710

5225

4248

4551

69000

4761

5281

4292

4599

70000

4811

5338

4338

4648

71000

4863

5395

4383

4694

72000

4916

5452

4426

4740

73000

4967

5510

4470

4789

74000

5018

5568

4513

4838

75000

5069

5626

4557

4883

76000

5118

5682

4590

4918

77000

5158

5728

4611

4935

78000

5201

5777

4630

4955

79000

5245

5824

4647

4972

80000

5286

5873

4666

4991

81000

5329

5921

4684

5011

82000

5373

5967

4701

5028

83000

5413

6015

4735

5044

ALTITUDE

LANDING DISTANCE + 4% per 1000 ft above SL

WIND

LANDING DISTANCE +12% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 8% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 74

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

AOM-1502-003

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

OVERSPEED

LANDING DISTANCE + 7% per 5 kt above Vref

REVERSER

LANDING DISTANCE -3% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 75

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 170 – CF34-8 ENGINES ICE FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

61000

18100

18689

13625

13822

62000

18100

18689

13625

13822

63000

18100

18689

13625

13822

64000

18100

18689

13625

13822

65000

18100

18689

13625

13822

66000

18100

18689

13625

13822

67000

18100

18689

13625

13822

68000

18100

18689

13625

13822

69000

18100

18689

13625

13822

70000

18100

18689

13625

13822

71000

18100

18689

13625

13822

72000

18100

18689

13625

13822

73000

18100

18689

13625

13822

74000

18100

18689

13625

13822

75000

18100

18689

13625

13822

76000

18100

18689

13625

13822

77000

18100

18689

13625

13822

78000

18100

18689

13625

13822

79000

18100

18689

13625

13822

80000

18100

18689

13625

13822

81000

18100

18689

13625

13822

82000

18100

18689

13625

13822

83000

18100

18689

13625

13822

ALTITUDE

LANDING DISTANCE + 1% per 1000 ft above SL

WIND

LANDING DISTANCE +43% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 2% per 5°C above ISA

SLOPE

LANDING DISTANCE +51% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 76

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

OVERSPEED

LANDING DISTANCE + 4% per 5 kt above Vref

REVERSER

LANDING DISTANCE -3% for ALL REV OP

AOM-1502-003

"

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 77

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 78

Landing

REVISION 21

AOM-1502-003

!EMBRAER 175 Models, except Operational Landing Braking Action

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES STANDING WATER 1/8 in WEIGHT (lb)

64000

68000

72000

76000

80000

84000

AOM-1502-003

88000

AUTO BRAKE

FLAP 5

FLAP FULL

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

MAN

4801

5530

4189

4548 5052

HI

5215

5913

4696

MED

5215

5913

4696

5052

LO

6616

7522

5986

6514

MAN

5129

5907

4412

4840

HI

5477

6284

4923

5299

MED

5477

6284

4923

5300

LO

6947

7910

6279

6835

MAN

5468

6284

4674

5131 5563

HI

5797

6653

5150

MED

5797

6653

5150

5563

LO

7282

8288

6567

7147

MAN

5807

6671

4930

5410

HI

6128

7032

5360

5839

MED

6128

7032

5360

5839

LO

7612

8674

6833

7439

MAN

6134

7043

5087

5572

HI

6446

7396

5483

5991

MED

6446

7396

5483

5991 7588

LO

7934

9049

6985

MAN

6471

7424

5290

5734

HI

6774

7768

5676

6144

MED

6774

7768

5676

6145

LO

8262

9429

7189

7735

MAN

6802

7803

5566

5966

HI

7095

8137

5949

6370

MED

7095

8138

5949

6370

LO

8577

9800

7475

7965

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 79

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

ALTITUDE

LANDING DISTANCE + 5% per 1000 ft above SL

WIND

LANDING DISTANCE +18% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 9% per 1% slope downhill

OVERSPEED

LANDING DISTANCE + 8% per 5 kt above Vref

REVERSER

LANDING DISTANCE -5% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 80

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES STANDING WATER 1/2 in WEIGHT (lb)

64000

68000

72000

76000

80000

84000

AOM-1502-003

88000

AUTO BRAKE

FLAP 5

FLAP FULL

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

MAN

4317

4929

3830

4136 4702

HI

4824

5414

4391

MED

4824

5414

4392

4706

LO

6616

7522

5986

6514

MAN

4597

5263

4031

4389

HI

5061

5736

4597

4927

MED

5061

5736

4597

4927

LO

6947

7910

6279

6835

MAN

4891

5603

4258

4644 5162

HI

5336

6061

4802

MED

5336

6061

4802

5162

LO

7282

8288

6567

7147

MAN

5188

5958

4480

4891

HI

5620

6399

4994

5404

MED

5620

6399

4994

5404

LO

7612

8674

6833

7439

MAN

5482

6305

4621

5040

HI

5899

6730

5110

5542

MED

5899

6730

5110

5542 7588

LO

7934

9049

6985

MAN

5788

6667

4802

5189

HI

6189

7073

5281

5682

MED

6189

7073

5281

5682

LO

8262

9429

7189

7735

MAN

6092

7031

5047

5402

HI

6477

7417

5521

5885

MED

6477

7417

5521

5885

LO

8577

9800

7475

7965

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 81

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

ALTITUDE

LANDING DISTANCE + 5% per 1000 ft above SL

WIND

LANDING DISTANCE +15% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 8% per 1% slope downhill

OVERSPEED

LANDING DISTANCE + 8% per 5 kt above Vref

REVERSER

LANDING DISTANCE -3% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 82

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES SLUSH 1/8 in WEIGHT (lb)

64000

68000

72000

76000

80000

84000

AOM-1502-003

88000

AUTO BRAKE

FLAP 5

FLAP FULL

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

MAN

4828

5564

4208

4571 5071

HI

5237

5941

4713

MED

5237

5941

4713

5071

LO

6616

7522

5986

6514

MAN

5160

5944

4433

4866

HI

5501

6315

4942

5320

MED

5501

6315

4942

5320

LO

6947

7910

6279

6835

MAN

5501

6323

4698

5159 5586

HI

5823

6687

5169

MED

5823

6687

5169

5586

LO

7282

8288

6567

7147

MAN

5842

6711

4955

5439

HI

6157

7068

5380

5863

MED

6157

7068

5380

5864

LO

7612

8674

6833

7439

MAN

6171

7085

5113

5602

HI

6478

7434

5504

6017

MED

6478

7434

5504

6017 7588

LO

7934

9049

6985

MAN

6510

7467

5318

5765

HI

6808

7808

5698

6170

MED

6808

7808

5698

6170

LO

8262

9429

7189

7735

MAN

6842

7847

5595

5998

HI

7131

8178

5973

6398

MED

7131

8178

5973

6398

LO

8577

9800

7475

7965

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 83

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

ALTITUDE

LANDING DISTANCE + 5% per 1000 ft above SL

WIND

LANDING DISTANCE +18% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 9% per 1% slope downhill

OVERSPEED

LANDING DISTANCE + 8% per 5 kt above Vref

REVERSER

LANDING DISTANCE -6% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 84

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES SLUSH 1/2 in WEIGHT (lb)

64000

68000

72000

76000

80000

84000

AOM-1502-003

88000

AUTO BRAKE

FLAP 5

FLAP FULL

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

MAN

4397

5028

3891

4205 4761

HI

4889

5496

4443

MED

4889

5496

4443

4761

LO

6616

7522

5986

6514

MAN

4685

5370

4095

4465

HI

5130

5827

4652

4990

MED

5130

5827

4652

4990

LO

6947

7910

6279

6835

MAN

4987

5717

4328

4726 5230

HI

5413

6160

4861

MED

5413

6160

4861

5230

LO

7282

8288

6567

7147

MAN

5291

6077

4556

4979

HI

5705

6505

5056

5478

MED

5705

6505

5056

5478

LO

7612

8674

6833

7439

MAN

5591

6430

4700

5130

HI

5990

6842

5174

5619

MED

5990

6842

5174

5619 7588

LO

7934

9049

6985

MAN

5903

6795

4885

5282

HI

6287

7190

5349

5760

MED

6287

7190

5349

5760

LO

8262

9429

7189

7735

MAN

6212

7162

5136

5498

HI

6581

7539

5594

5967

MED

6581

7539

5594

5967

LO

8577

9800

7475

7965

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 85

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

ALTITUDE

LANDING DISTANCE + 5% per 1000 ft above SL

WIND

LANDING DISTANCE +16% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 7% per 1% slope downhill

OVERSPEED

LANDING DISTANCE + 8% per 5 kt above Vref

REVERSER

LANDING DISTANCE -4% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 86

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES WET SNOW 1/4 in WEIGHT (lb)

64000

68000

72000

76000

80000

84000

AOM-1502-003

88000

AUTO BRAKE

FLAP 5

FLAP FULL

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

MAN

4734

5234

4272

4565 5143

HI

5278

5818

4823

MED

5278

5818

4823

5143

LO

6616

7522

5986

6514

MAN

4948

5480

4460

4769

HI

5500

6072

5020

5356

MED

5500

6072

5020

5356

LO

6947

7910

6279

6835

MAN

5167

5722

4647

4969 5564

HI

5725

6320

5215

MED

5725

6320

5215

5564

LO

7282

8288

6567

7147

MAN

5380

5967

4819

5156

HI

5945

6571

5394

5758

MED

5945

6571

5394

5758

LO

7612

8674

6833

7439

MAN

5579

6193

4917

5253

HI

6149

6803

5494

5857

MED

6149

6803

5494

5857 7588

LO

7934

9049

6985

MAN

5780

6422

5044

5350

HI

6355

7037

5625

5954

MED

6355

7037

5625

5954

LO

8262

9429

7189

7735

MAN

5975

6646

5218

5493

HI

6555

7266

5807

6102

MED

6555

7267

5807

6102

LO

8577

9800

7475

7965

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 87

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

ALTITUDE

LANDING DISTANCE + 4% per 1000 ft above SL

WIND

LANDING DISTANCE +12% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 7% per 1% slope downhill

OVERSPEED

LANDING DISTANCE + 8% per 5 kt above Vref

REVERSER

LANDING DISTANCE -3% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 88

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES WET SNOW 1 in WEIGHT (lb)

64000

68000

72000

76000

80000

84000

AOM-1502-003

88000

AUTO BRAKE

FLAP 5

FLAP FULL

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

MAN

4319

4769

3929

4188 4807

HI

4913

5397

4521

MED

4969

5502

4562

4876

LO

6616

7522

5986

6514

MAN

4521

5006

4105

4380

HI

5121

5638

4706

5007

MED

5176

5740

4749

5079

LO

6947

7910

6279

6835

MAN

4729

5242

4280

4570 5204

HI

5333

5877

4889

MED

5386

5973

4932

5275

LO

7282

8288

6567

7147

MAN

4935

5483

4444

4750

HI

5542

6120

5059

5389

MED

5591

6208

5101

5457

LO

7612

8674

6833

7439

MAN

5130

5710

4542

4850

HI

5740

6349

5158

5489

MED

5784

6429

5195

5548 7588

LO

7934

9049

6985

MAN

5330

5942

4667

4949

HI

5942

6582

5287

5588

MED

5980

6653

5319

5639

LO

8262

9429

7189

7735

MAN

5524

6171

4837

5092

HI

6138

6811

5461

5733

MED

6169

6871

5492

5778

LO

8577

9800

7475

7965

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 89

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

ALTITUDE

LANDING DISTANCE + 4% per 1000 ft above SL

WIND

LANDING DISTANCE +12% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 8% per 1% slope downhill

OVERSPEED

LANDING DISTANCE + 8% per 5 kt above Vref

REVERSER

LANDING DISTANCE -2% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 90

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES DRY SNOW 1 in WEIGHT (lb)

64000

68000

72000

76000

80000

84000

AOM-1502-003

88000

AUTO BRAKE

FLAP 5

FLAP FULL

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

MAN

4726

5228

4258

4554 5128

HI

5267

5811

4803

MED

5267

5811

4803

5128

LO

6616

7522

5986

6514

MAN

4947

5477

4453

4764

HI

5495

6070

5007

5348

MED

5495

6070

5007

5348

LO

6947

7910

6279

6835

MAN

5170

5723

4644

4968 5561

HI

5726

6323

5208

MED

5726

6323

5208

5561

LO

7282

8288

6567

7147

MAN

5387

5968

4821

5158

HI

5950

6577

5392

5759

MED

5950

6577

5392

5759

LO

7612

8674

6833

7439

MAN

5587

6195

4922

5259

HI

6158

6811

5496

5862

MED

6158

6811

5496

5862 7588

LO

7934

9049

6985

MAN

5790

6423

5052

5359

HI

6367

7046

5631

5962

MED

6367

7048

5631

5962

LO

8262

9429

7189

7735

MAN

5986

6647

5229

5503

HI

6569

7276

5816

6112

MED

6569

7278

5816

6112

LO

8577

9800

7475

7965

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 91

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

ALTITUDE

LANDING DISTANCE + 4% per 1000 ft above SL

WIND

LANDING DISTANCE +12% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 8% per 1% slope downhill

OVERSPEED

LANDING DISTANCE + 8% per 5 kt above Vref

REVERSER

LANDING DISTANCE -3% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 92

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES DRY SNOW 2 in WEIGHT (lb)

64000

68000

72000

76000

80000

84000

AOM-1502-003

88000

AUTO BRAKE

FLAP 5

FLAP FULL

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

MAN

4569

5052

4123

4409 4995

HI

5124

5652

4680

MED

5124

5658

4680

4996

LO

6616

7522

5986

6514

MAN

4788

5300

4317

4618

HI

5352

5910

4884

5214

MED

5352

5917

4884

5215

LO

6947

7910

6279

6835

MAN

5011

5544

4509

4822 5427

HI

5582

6162

5085

MED

5582

6170

5085

5428

LO

7282

8288

6567

7147

MAN

5226

5788

4685

5012

HI

5806

6414

5269

5626

MED

5806

6423

5269

5627

LO

7612

8674

6833

7439

MAN

5427

6014

4789

5116

HI

6014

6648

5375

5731

MED

6014

6659

5375

5732 7588

LO

7934

9049

6985

MAN

5630

6242

4921

5218

HI

6224

6884

5512

5835

MED

6224

6897

5512

5835

LO

8262

9429

7189

7735

MAN

5825

6465

5098

5364

HI

6426

7113

5697

5986

MED

6426

7128

5697

5986

LO

8577

9800

7475

7965

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 93

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

ALTITUDE

LANDING DISTANCE + 4% per 1000 ft above SL

WIND

LANDING DISTANCE +12% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 8% per 1% slope downhill

OVERSPEED

LANDING DISTANCE + 8% per 5 kt above Vref

REVERSER

LANDING DISTANCE -3% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 94

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES COMPACTED SNOW WEIGHT (lb)

64000

68000

72000

76000

80000

84000

AOM-1502-003

88000

AUTO BRAKE

FLAP 5

FLAP FULL

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

MAN

4467

4951

4034

4320 4906

HI

5023

5550

4591

MED

5023

5557

4591

4907

LO

6616

7522

5986

6514

MAN

4669

5181

4213

4513

HI

5235

5790

4781

5110

MED

5235

5799

4781

5111

LO

6947

7910

6279

6835

MAN

4874

5406

4389

4701 5308

HI

5448

6025

4967

MED

5448

6035

4967

5310

LO

7282

8288

6567

7147

MAN

5072

5632

4550

4875

HI

5655

6259

5137

5491

MED

5655

6272

5137

5494

LO

7612

8674

6833

7439

MAN

5255

5839

4639

4964

HI

5847

6476

5229

5582

MED

5847

6492

5229

5584 7588

LO

7934

9049

6985

MAN

5441

6048

4756

5050

HI

6041

6694

5353

5671

MED

6041

6714

5352

5673

LO

8262

9429

7189

7735

MAN

5619

6253

4918

5181

HI

6226

6906

5524

5809

MED

6227

6930

5524

5810

LO

8577

9800

7475

7965

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 95

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

ALTITUDE

LANDING DISTANCE + 4% per 1000 ft above SL

WIND

LANDING DISTANCE +12% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 8% per 1% slope downhill

OVERSPEED

LANDING DISTANCE + 8% per 5 kt above Vref

REVERSER

LANDING DISTANCE -3% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 96

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES ICE WEIGHT (lb)

64000

68000

72000

76000

80000

84000

AOM-1502-003

88000

AUTO BRAKE

FLAP 5

FLAP FULL

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

MAN

14683

15291

11510

11860 12234

HI

14971

15629

11852

MED

14971

15629

11852

12234

LO

14971

15633

11852

12237

MAN

14683

15291

11510

11860

HI

14971

15629

11852

12234

MED

14971

15629

11852

12234

LO

14971

15633

11852

12237

MAN

14683

15291

11510

11860 12234

HI

14971

15629

11852

MED

14971

15629

11852

12234

LO

14971

15633

11852

12237

MAN

14683

15291

11510

11860

HI

14971

15629

11852

12234

MED

14971

15629

11852

12234

LO

14971

15633

11852

12237

MAN

14683

15291

11510

11860

HI

14971

15629

11852

12234

MED

14971

15629

11852

12234 12237

LO

14971

15633

11852

MAN

14683

15291

11510

11860

HI

14971

15629

11852

12234

MED

14971

15629

11852

12234

LO

14971

15633

11852

12237

MAN

14683

15291

11510

11860

HI

14971

15629

11852

12234

MED

14971

15629

11852

12234

LO

14971

15633

11852

12237

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 97

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

ALTITUDE

LANDING DISTANCE + 3% per 1000 ft above SL

WIND

LANDING DISTANCE +31% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 2% per 5°C above ISA

SLOPE

LANDING DISTANCE +45% per 1% slope downhill

OVERSPEED

LANDING DISTANCE + 5% per 5 kt above Vref

REVERSER

LANDING DISTANCE -4% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 98

Landing

REVISION 21

AOM-1502-003

CORRECTIONS

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES STANDING WATER 1/8 in FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

66000

4964

5717

4302

4696

67000

5044

5813

4355

4768

68000

5129

5907

4412

4840

69000

5213

6000

4467

4914

70000

5295

6094

4524

4988

71000

5380

6189

4608

5060

72000

5468

6284

4674

5131

73000

5553

6381

4742

5207

74000

5638

6478

4809

5283

75000

5724

6576

4877

5354

76000

5807

6671

4930

5410

77000

5884

6760

4971

5448

78000

5968

6856

5012

5491

79000

6053

6948

5048

5530

80000

6134

7043

5087

5572

81000

6217

7138

5126

5614

82000

6305

7230

5163

5653

83000

6384

7325

5226

5691

84000

6471

7424

5290

5734

85000

6553

7518

5359

5773

86000

6635

7613

5423

5812

87000

6718

7701

5494

5892

88000

6802

7803

5566

5966

AOM-1502-003

CORRECTIONS ALTITUDE

LANDING DISTANCE + 5% per 1000 ft above SL

WIND

LANDING DISTANCE +18% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 9% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 99

AIRPLANE OPERATIONS MANUAL

OVERSPEED

LANDING DISTANCE + 8% per 5 kt above Vref

REVERSER

LANDING DISTANCE -6% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 100

Landing

REVISION 21

AOM-1502-003

PERFORMANCE

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES STANDING WATER 1/2 in FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

66000

4456

5094

3932

4263

67000

4524

5180

3980

4326

68000

4597

5263

4031

4389

69000

4669

5347

4080

4453

70000

4740

5431

4131

4518

71000

4814

5517

4200

4581

72000

4891

5603

4258

4644

73000

4964

5691

4316

4711

74000

5039

5780

4374

4778

75000

5114

5869

4433

4841

76000

5188

5958

4480

4891

77000

5257

6041

4517

4927

78000

5332

6130

4553

4966

79000

5408

6216

4586

5001

80000

5482

6305

4621

5040

81000

5557

6395

4656

5078

82000

5636

6482

4689

5115

83000

5709

6572

4745

5149

84000

5788

6667

4802

5189

85000

5863

6756

4863

5225

86000

5939

6847

4920

5262

87000

6015

6932

4983

5334

88000

6092

7031

5047

5402

AOM-1502-003

CORRECTIONS ALTITUDE

LANDING DISTANCE + 5% per 1000 ft above SL

WIND

LANDING DISTANCE +15% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 8% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 101

AIRPLANE OPERATIONS MANUAL

OVERSPEED

LANDING DISTANCE + 8% per 5 kt above Vref

REVERSER

LANDING DISTANCE -4% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 102

Landing

REVISION 21

AOM-1502-003

PERFORMANCE

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES SLUSH 1/8 in FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

66000

4992

5752

4323

4720

67000

5073

5850

4376

4792

68000

5160

5944

4433

4866

69000

5244

6037

4489

4940

70000

5326

6132

4545

5014

71000

5413

6227

4631

5087

72000

5501

6323

4698

5159

73000

5586

6420

4765

5235

74000

5672

6518

4834

5312

75000

5759

6616

4902

5383

76000

5842

6711

4955

5439

77000

5920

6801

4997

5477

78000

6004

6897

5038

5520

79000

6090

6989

5074

5560

80000

6171

7085

5113

5602

81000

6255

7180

5152

5644

82000

6343

7272

5189

5684

83000

6423

7368

5253

5721

84000

6510

7467

5318

5765

85000

6592

7561

5387

5804

86000

6675

7656

5451

5843

87000

6758

7744

5523

5923

88000

6842

7847

5595

5998

AOM-1502-003

CORRECTIONS ALTITUDE

LANDING DISTANCE + 5% per 1000 ft above SL

WIND

LANDING DISTANCE +18% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 9% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 103

AIRPLANE OPERATIONS MANUAL

OVERSPEED

LANDING DISTANCE + 9% per 5 kt above Vref

REVERSER

LANDING DISTANCE -6% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 104

Landing

REVISION 21

AOM-1502-003

PERFORMANCE

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES SLUSH 1/2 in FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

66000

4540

5197

3994

4336

67000

4610

5285

4043

4400

68000

4685

5370

4095

4465

69000

4759

5455

4146

4530

70000

4832

5541

4198

4597

71000

4908

5629

4269

4662

72000

4987

5717

4328

4726

73000

5062

5806

4388

4795

74000

5139

5897

4448

4863

75000

5216

5988

4508

4928

76000

5291

6077

4556

4979

77000

5362

6161

4593

5015

78000

5438

6252

4631

5054

79000

5516

6339

4664

5091

80000

5591

6430

4700

5130

81000

5668

6520

4735

5169

82000

5748

6609

4769

5206

83000

5822

6700

4827

5241

84000

5903

6795

4885

5282

85000

5979

6886

4947

5318

86000

6056

6977

5006

5355

87000

6134

7063

5070

5429

88000

6212

7162

5136

5498

AOM-1502-003

CORRECTIONS ALTITUDE

LANDING DISTANCE + 5% per 1000 ft above SL

WIND

LANDING DISTANCE +16% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 7% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 105

AIRPLANE OPERATIONS MANUAL

OVERSPEED

LANDING DISTANCE + 8% per 5 kt above Vref

REVERSER

LANDING DISTANCE -4% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 106

Landing

REVISION 21

AOM-1502-003

PERFORMANCE

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES WET SNOW 1/4 in FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

66000

4840

5356

4368

4668

67000

4893

5419

4413

4719

68000

4948

5480

4460

4769

69000

5003

5540

4506

4820

70000

5055

5601

4554

4871

71000

5110

5661

4602

4920

72000

5167

5722

4647

4969

73000

5221

5784

4693

5021

74000

5275

5846

4739

5072

75000

5329

5908

4785

5120

76000

5380

5967

4819

5156

77000

5427

6021

4845

5178

78000

5478

6079

4870

5205

79000

5530

6135

4893

5228

80000

5579

6193

4917

5253

81000

5629

6250

4941

5279

82000

5681

6305

4963

5302

83000

5728

6362

5003

5324

84000

5780

6422

5044

5350

85000

5828

6477

5088

5372

86000

5877

6534

5128

5395

87000

5926

6585

5173

5446

88000

5975

6646

5218

5493

AOM-1502-003

CORRECTIONS ALTITUDE

LANDING DISTANCE + 4% per 1000 ft above SL

WIND

LANDING DISTANCE +12% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 7% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 107

AIRPLANE OPERATIONS MANUAL

OVERSPEED

LANDING DISTANCE + 6% per 5 kt above Vref

REVERSER

LANDING DISTANCE -3% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 108

Landing

REVISION 21

AOM-1502-003

PERFORMANCE

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES WET SNOW 1 in FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

66000

4419

4886

4018

4285

67000

4469

4947

4060

4332

68000

4521

5006

4105

4380

69000

4573

5064

4148

4428

70000

4623

5123

4192

4476

71000

4675

5182

4237

4523

72000

4729

5242

4280

4570

73000

4781

5302

4323

4620

74000

4833

5363

4367

4669

75000

4885

5424

4410

4715

76000

4935

5483

4444

4750

77000

4981

5537

4470

4774

78000

5031

5596

4495

4800

79000

5082

5652

4518

4824

80000

5130

5710

4542

4850

81000

5179

5768

4566

4876

82000

5231

5824

4589

4900

83000

5278

5881

4628

4923

84000

5330

5942

4667

4949

85000

5378

5999

4710

4973

86000

5426

6056

4749

4996

87000

5475

6109

4793

5046

88000

5524

6171

4837

5092

AOM-1502-003

CORRECTIONS ALTITUDE

LANDING DISTANCE + 4% per 1000 ft above SL

WIND

LANDING DISTANCE +12% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 8% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 109

AIRPLANE OPERATIONS MANUAL

OVERSPEED

LANDING DISTANCE + 7% per 5 kt above Vref

REVERSER

LANDING DISTANCE -2% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 110

Landing

REVISION 21

AOM-1502-003

PERFORMANCE

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES DRY SNOW 1 in FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

66000

4836

5352

4357

4661

67000

4890

5416

4403

4712

68000

4947

5477

4453

4764

69000

5002

5538

4500

4816

70000

5056

5599

4549

4868

71000

5112

5661

4598

4918

72000

5170

5723

4644

4968

73000

5224

5785

4691

5021

74000

5280

5847

4739

5073

75000

5335

5909

4785

5122

76000

5387

5968

4821

5158

77000

5434

6023

4848

5182

78000

5485

6081

4874

5209

79000

5538

6137

4897

5233

80000

5587

6195

4922

5259

81000

5638

6252

4947

5285

82000

5690

6307

4970

5309

83000

5738

6364

5011

5332

84000

5790

6423

5052

5359

85000

5839

6479

5097

5382

86000

5887

6535

5138

5405

87000

5937

6586

5183

5456

88000

5986

6647

5229

5503

AOM-1502-003

CORRECTIONS ALTITUDE

LANDING DISTANCE + 4% per 1000 ft above SL

WIND

LANDING DISTANCE +12% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 8% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 111

AIRPLANE OPERATIONS MANUAL

OVERSPEED

LANDING DISTANCE + 6% per 5 kt above Vref

REVERSER

LANDING DISTANCE -3% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 112

Landing

REVISION 21

AOM-1502-003

PERFORMANCE

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES DRY SNOW 2 in FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

66000

4678

5175

4222

4515

67000

4732

5239

4268

4566

68000

4788

5300

4317

4618

69000

4844

5361

4365

4670

70000

4897

5422

4413

4722

71000

4953

5483

4462

4772

72000

5011

5544

4509

4822

73000

5065

5606

4556

4874

74000

5120

5667

4603

4927

75000

5175

5729

4650

4975

76000

5226

5788

4685

5012

77000

5274

5843

4713

5037

78000

5326

5901

4740

5064

79000

5378

5957

4764

5089

80000

5427

6014

4789

5116

81000

5478

6071

4814

5142

82000

5530

6127

4838

5168

83000

5578

6183

4880

5191

84000

5630

6242

4921

5218

85000

5679

6298

4966

5242

86000

5727

6354

5006

5266

87000

5776

6405

5052

5317

88000

5825

6465

5098

5364

AOM-1502-003

CORRECTIONS ALTITUDE

LANDING DISTANCE + 4% per 1000 ft above SL

WIND

LANDING DISTANCE +12% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 8% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 113

AIRPLANE OPERATIONS MANUAL

OVERSPEED

LANDING DISTANCE + 7% per 5 kt above Vref

REVERSER

LANDING DISTANCE -3% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 114

Landing

REVISION 21

AOM-1502-003

PERFORMANCE

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES COMPACTED SNOW FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

66000

4568

5065

4125

4418

67000

4617

5124

4168

4466

68000

4669

5181

4213

4513

69000

4720

5237

4256

4561

70000

4769

5293

4301

4609

71000

4821

5349

4346

4655

72000

4874

5406

4389

4701

73000

4924

5463

4432

4750

74000

4974

5520

4475

4798

75000

5025

5578

4518

4842

76000

5072

5632

4550

4875

77000

5115

5681

4574

4896

78000

5162

5735

4597

4920

79000

5210

5786

4617

4941

80000

5255

5839

4639

4964

81000

5301

5891

4661

4986

82000

5350

5942

4681

5007

83000

5393

5994

4718

5027

84000

5441

6048

4756

5050

85000

5485

6099

4797

5070

86000

5529

6150

4834

5091

87000

5574

6197

4876

5138

88000

5619

6253

4918

5181

AOM-1502-003

CORRECTIONS ALTITUDE

LANDING DISTANCE + 4% per 1000 ft above SL

WIND

LANDING DISTANCE +12% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 3% per 5°C above ISA

SLOPE

LANDING DISTANCE + 8% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 115

AIRPLANE OPERATIONS MANUAL

OVERSPEED

LANDING DISTANCE + 7% per 5 kt above Vref

REVERSER

LANDING DISTANCE -3% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 116

Landing

REVISION 21

AOM-1502-003

PERFORMANCE

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OPERATIONAL LANDING DISTANCE (ft) EMBRAER 175 – CF34-8 ENGINES ICE FLAP 5

FLAP FULL

WEIGHT (lb)

NO ICE ACC

ICE ACC

NO ICE ACC

ICE ACC

66000

14683

15291

11510

11860

67000

14683

15291

11510

11860

68000

14683

15291

11510

11860

69000

14683

15291

11510

11860

70000

14683

15291

11510

11860

71000

14683

15291

11510

11860

72000

14683

15291

11510

11860

73000

14683

15291

11510

11860

74000

14683

15291

11510

11860

75000

14683

15291

11510

11860

76000

14683

15291

11510

11860

77000

14683

15291

11510

11860

78000

14683

15291

11510

11860

79000

14683

15291

11510

11860

80000

14683

15291

11510

11860

81000

14683

15291

11510

11860

82000

14683

15291

11510

11860

83000

14683

15291

11510

11860

84000

14683

15291

11510

11860

85000

14683

15291

11510

11860

86000

14683

15291

11510

11860

87000

14683

15291

11510

11860

88000

14683

15291

11510

11860

AOM-1502-003

CORRECTIONS ALTITUDE

LANDING DISTANCE + 3% per 1000 ft above SL

WIND

LANDING DISTANCE +31% per 5 kt tailwind

TEMPERATURE

LANDING DISTANCE + 2% per 5°C above ISA

SLOPE

LANDING DISTANCE +43% per 1% slope downhill

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 117

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

OVERSPEED

LANDING DISTANCE + 4% per 5 kt above Vref

REVERSER

LANDING DISTANCE -4% for ALL REV OP

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 118

Landing

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

PERFORMANCE

QUICK TURN AROUND WEIGHT !EMBRAER 170 Models

For normal operation, the brake temperature can be monitored through the brake temperature indication in the MFD. The Quick Turn Around Weight Table must be used only when the brake temperature indication is not working properly (according to the MMEL). In this case, if the landing weight exceeds the Quick Turn Around Weight, a subsequent takeoff must not be performed before 25 minutes after chocks on. At the end of this time interval, check that the wheel thermal plugs have not melted. The tables in the following pages are provided for the maximum manual braking setting and no runway slope.

AOM-1502-003

NOTE: If the tires are not flat after 25 minutes, this is a positive indication that the wheel thermal plugs have not melted.

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 119

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 170 – CF34-8 ENGINES FLAP 5 – WITHOUT ICE ACCRETION ALTITUDE 0 ft

Temp

1000 ft

(°C) -10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

80299

85097

85097

85097

78916

85097

85097

85097

-15

79505

85097

85097

85097

78166

85097

85097

85097

-10

78759

85097

85097

85097

77436

85097

85097

85097

-5

78037

85097

85097

85097

76704

84464

85097

85097

0

77335

85097

85097

85097

75982

83648

85097

85097

5

76625

84385

85097

85097

75305

82885

85097

85097

10

75931

83602

85097

85097

74644

82095

84730

85097

15

75278

82865

85097

85097

73999

81363

83938

85097

20

74641

82101

84740

85097

73370

80653

83194

85097

25

74017

81392

83973

85097

72755

79936

82457

85042

30

73408

80706

83251

85097

72153

79233

81720

84275

35

72812

80015

82545

85097

71569

78572

81033

83538

40

72231

79329

81822

84390

71019

77926

80356

82841

45

71660

78689

81156

83668

70477

77293

79667

82114

50

71128

78063

80506

82994

69927

76653

79011

81441

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 120

Landing

REVISION 21

AOM-1502-003

WIND

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 170 – CF34-8 ENGINES FLAP 5 – WITHOUT ICE ACCRETION ALTITUDE 2000 ft

Temp

AOM-1502-003

(°C)

3000 ft WIND

-10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

77584

85097

85097

85097

76196

83873

85097

85097

-15

76829

84594

85097

85097

75460

83045

85097

85097

-10

76075

83742

85097

85097

74750

82206

84838

85097

-5

75371

82950

85097

85097

74057

81410

83986

85097

0

74686

82135

84768

85097

73383

80651

83186

85097

5

74018

81373

83947

85097

72723

79881

82393

84973

10

73367

80640

83176

85097

72081

79134

81612

84152

15

72730

79896

82410

84992

71462

78429

80879

83374

20

72108

79172

81653

84200

70874

77740

80148

82628

25

71508

78489

80944

83443

70289

77062

79415

81853

30

70938

77822

80239

82724

69706

76374

78730

81145

35

70375

77170

79528

81967

69134

75717

78064

80453

40

69808

76502

78859

81281

68574

75089

77412

79743

45

69253

75859

78212

80610

---

---

---

---

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 121

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 170 – CF34-8 ENGINES FLAP 5 – WITHOUT ICE ACCRETION ALTITUDE 4000 ft

Temp

(°C)

5000 ft

-10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

74854

82329

84961

85097

73555

80830

83368

85097

-15

74135

81493

84075

85097

72844

80008

82524

85097

-10

73434

80703

83240

85097

72152

79198

81673

84216

-5

72751

79909

82422

84999

71485

78440

80886

83376

0

72086

79134

81609

84150

70855

77700

80100

82572

5

71445

78403

80851

83344

70227

76971

79317

81750

10

70839

77691

80094

82568

69601

76234

78587

80993

15

70232

76988

79337

81773

68990

75539

77875

80243

20

69629

76277

78632

81043

68394

74870

77180

79486

25

69040

75604

77945

80322

67833

74216

76469

78776

30

68464

74957

77273

79590

67288

73578

75788

78089

35

67919

74326

76590

78899

66733

72955

75140

77418

40

67390

73707

75923

78234

66189

72344

74506

76741

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 122

Landing

REVISION 21

AOM-1502-003

WIND

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

QUICK TURN AROUND WEIGHT (lb) EMBRAER 170 – CF34-8 ENGINES FLAP FULL – WITHOUT ICE ACCRETION ALTITUDE 0 ft

Temp

1000 ft

AOM-1502-003

(°C)

WIND -10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

85097

85097

85097

85097

85097

85097

85097

85097

-15

85097

85097

85097

85097

85097

85097

85097

85097

-10

85097

85097

85097

85097

85097

85097

85097

85097

-5

85097

85097

85097

85097

85097

85097

85097

85097

0

85097

85097

85097

85097

84414

85097

85097

85097

5

85092

85097

85097

85097

83680

85097

85097

85097

10

84362

85097

85097

85097

82935

85097

85097

85097

15

83653

85097

85097

85097

82213

85097

85097

85097

20

82932

85097

85097

85097

81389

85097

85097

85097

25

82235

85097

85097

85097

80536

85097

85097

85097

30

81446

85097

85097

85097

79735

85097

85097

85097

35

80618

85097

85097

85097

78931

85097

85097

85097

40

79840

85097

85097

85097

78133

85097

85097

85097

45

79068

85097

85097

85097

77390

85097

85097

85097

50

78286

85097

85097

85097

76665

85097

85097

85097

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 123

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

QUICK TURN AROUND WEIGHT (lb) EMBRAER 170 – CF34-8 ENGINES FLAP FULL – WITHOUT ICE ACCRETION ALTITUDE 2000 ft

Temp

(°C)

3000 ft

-10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

85097

85097

85097

85097

84633

85097

85097

85097

-15

85097

85097

85097

85097

83847

85097

85097

85097

-10

84510

85097

85097

85097

83047

85097

85097

85097

-5

83753

85097

85097

85097

82271

85097

85097

85097

0

82978

85097

85097

85097

81398

85097

85097

85097

5

82231

85097

85097

85097

80484

85097

85097

85097

10

81379

85097

85097

85097

79632

85097

85097

85097

15

80497

85097

85097

85097

78766

85097

85097

85097

20

79672

85097

85097

85097

77928

85097

85097

85097

25

78836

85097

85097

85097

77138

85097

85097

85097

30

78019

85097

85097

85097

76368

85097

85097

85097

35

77255

85097

85097

85097

75662

84798

85097

85097

40

76506

85097

85097

85097

75001

84117

85097

85097

45

75804

84957

85097

85097

---

---

---

---

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 124

Landing

REVISION 21

AOM-1502-003

WIND

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

QUICK TURN AROUND WEIGHT (lb) EMBRAER 170 – CF34-8 ENGINES FLAP FULL – WITHOUT ICE ACCRETION ALTITUDE 4000 ft

Temp

AOM-1502-003

(°C)

5000 ft WIND

-10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

83163

85097

85097

85097

81633

85097

85097

85097

-15

82355

85097

85097

85097

80646

85097

85097

85097

-10

81467

85097

85097

85097

79721

85097

85097

85097

-5

80520

85097

85097

85097

78795

85097

85097

85097

0

79635

85097

85097

85097

77896

85097

85097

85097

5

78740

85097

85097

85097

77050

85097

85097

85097

10

77876

85097

85097

85097

76226

85097

85097

85097

15

77060

85097

85097

85097

75488

84599

85097

85097

20

76266

85097

85097

85097

74800

83874

85097

85097

25

75548

84672

85097

85097

74176

83132

85097

85097

30

74876

83972

85097

85097

73566

82407

85097

85097

35

74273

83259

85097

85097

72969

81626

84384

85097

40

73682

82555

85097

85097

72386

80760

83691

85097

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 125

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 170 – CF34-8 ENGINES FLAP 5 – WITH ICE ACCRETION ALTITUDE 0 ft

Temp

1000 ft

(°C) -10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

74975

82471

85069

-15

74257

81627

84192

85097

73711

80974

83521

85097

85097

73002

80155

82693

-10

73558

80805

85097

83356

85097

72310

79380

81852

84371

-5

72877

0

72213

80024

82555

85097

71639

78590

81032

83530

79274

81745

84261

70984

77840

80242

82736 81931

5

71564

78514

80955

83457

70344

77120

79498

10

70932

77793

80197

82691

69721

76390

78744

81142

15

70315

77097

79478

81911

69111

75692

78014

80378

20

69713

76392

78750

81150

68517

75026

77322

79659

25

69126

75717

78043

80410

67935

74374

76623

78940

30

68550

75072

77374

79716

67368

73739

75939

78226

35

67988

74442

76701

79022

66829

73116

75295

77559

40

67439

73825

76033

78328

66306

72507

74663

76892

45

66913

73222

75407

77677

65782

71913

74047

76223

50

66407

72633

74796

77038

65263

71333

73444

75592

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 126

Landing

REVISION 21

AOM-1502-003

WIND

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 170 – CF34-8 ENGINES FLAP 5 – WITH ICE ACCRETION ALTITUDE 2000 ft

Temp

AOM-1502-003

(°C)

3000 ft WIND

-10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

72454

79530

82013

-15

71755

78716

81160

84536

71186

78054

80460

82958

83654

70496

77279

79655

-10

71073

77932

80335

82831

82098

69825

76496

78850

81249

-5

70410

77186

79561

0

69762

76429

78782

81997

69171

75743

78063

80424

81180

68532

75029

77320

79653

5

69132

75706

78025

80386

67912

74331

76572

78882

10

68516

75015

77309

79643

67303

73650

75844

78124

15

67915

74341

76584

78898

66732

72986

75156

77410

20

67328

73683

75880

78162

66174

72339

74485

76693

25

66774

73041

75215

77472

65611

71707

73827

75985

30

66234

72413

74564

76781

65059

71087

73186

75322

35

65690

71801

73926

76091

64538

70484

72559

74672

40

65153

71200

73305

75445

64030

69894

71947

74038

45

64645

70614

72697

74816

---

---

---

---

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 127

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 170 – CF34-8 ENGINES FLAP 5 – WITH ICE ACCRETION ALTITUDE 4000 ft

Temp

(°C)

5000 ft

-10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

69926

76611

78968

81370

68702

75202

77498

79833

-15

69245

75824

78145

80511

68031

74449

76697

79006

-10

68584

75082

77375

79709

67377

73717

75910

78187

-5

67939

74358

76600

78910

66759

73003

75169

77418

0

67311

73653

75845

78123

66160

72307

74447

76649

5

66718

72966

75133

77384

65557

71628

73743

75895

10

66143

72296

74438

76641

64969

70969

73058

75183

15

65560

71642

73760

75913

64413

70324

72389

74490

20

64992

71004

73097

75227

63869

69694

71735

73813

25

64455

70380

72452

74558

63319

69078

71098

73153

30

63931

69771

71820

73903

62784

68478

70475

72507

35

63400

69178

71203

73265

62278

67891

69867

71878

40

62880

68596

70601

72641

61783

67317

69273

71263

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 128

Landing

REVISION 21

AOM-1502-003

WIND

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 170 – CF34-8 ENGINES FLAP FULL – WITH ICE ACCRETION ALTITUDE 0 ft

Temp

1000 ft

AOM-1502-003

(°C)

WIND -10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

85097

85097

85097

85097

84486

85097

85097

85097

-15

85097

85097

85097

85097

83463

85097

85097

85097

-10

84268

85097

85097

85097

82491

85097

85097

85097

-5

83296

85097

85097

85097

81496

85097

85097

85097

0

82346

85097

85097

85097

80556

85097

85097

85097

5

81395

85097

85097

85097

79672

85097

85097

85097

10

80488

85097

85097

85097

78785

85097

85097

85097

15

79638

85097

85097

85097

77920

85097

85097

85097

20

78778

85097

85097

85097

77103

85097

85097

85097

25

77943

85097

85097

85097

76267

85097

85097

85097

30

77156

85097

85097

85097

75538

85097

85097

85097

35

76345

85097

85097

85097

74864

84686

85097

85097

40

75626

85097

85097

85097

74254

83766

85097

85097

45

74964

84852

85097

85097

73667

82923

85097

85097

50

74373

83961

85097

85097

73110

82037

85097

85097

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 129

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 170 – CF34-8 ENGINES FLAP FULL – WITH ICE ACCRETION ALTITUDE 2000 ft

Temp

(°C)

3000 ft

-10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

82701

85097

85097

85097

80837

85097

85097

85097

-15

81658

85097

85097

85097

79874

85097

85097

85097

-10

80680

85097

85097

85097

78926

85097

85097

85097

-5

79759

85097

85097

85097

77994

85097

85097

85097

0

78841

85097

85097

85097

77120

85097

85097

85097

5

77945

85097

85097

85097

76221

85097

85097

85097

10

77099

85097

85097

85097

75452

85097

85097

85097

15

76232

85097

85097

85097

74744

84478

85097

85097

20

75484

85097

85097

85097

74096

83515

85097

85097

25

74796

84566

85097

85097

73478

82612

85097

85097

30

74167

83626

85097

85097

72884

81663

85097

85097

35

73565

82757

85097

85097

72305

80774

84181

85097

40

72990

81835

85097

85097

71739

79930

83281

85097

45

72427

80970

84395

85097

---

---

---

---

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 130

Landing

REVISION 21

AOM-1502-003

WIND

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 170 – CF34-8 ENGINES FLAP FULL – WITH ICE ACCRETION ALTITUDE 4000 ft

Temp

(°C)

5000 ft WIND

-10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

79069

85097

85097

85097

77345

85097

85097

85097

-15

78095

85097

85097

85097

76387

85097

85097

85097

-10

77189

85097

85097

85097

75535

85097

85097

85097

-5

76261

85097

85097

85097

74769

84490

85097

85097

0

75458

85097

85097

85097

74074

83460

85097

85097

5

74727

84440

85097

85097

73414

82480

85097

85097

10

74055

83449

85097

85097

72779

81476

84929

85097

15

73420

82506

85097

85097

72160

80526

83908

85097

20

72808

81535

84998

85097

71551

79638

82967

85097

25

72210

80618

84010

85097

70934

78738

81991

85097

30

71624

79755

83095

85097

70342

77869

81066

84438

35

71028

78892

82162

85097

69778

77042

80176

83489

40

70450

78040

81258

84648

69226

76194

79333

82596

AOM-1502-003

"

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 131

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

QUICK TURN AROUND WEIGHT !EMBRAER 175 Models

For normal operation, the brake temperature can be monitored through the brake temperature indication in the MFD The Quick Turn Around Weight Table must be used only when the brake temperature indication is not working properly (according to the MMEL). In this case, if the landing weight exceeds the Quick Turn Around Weight, a subsequent takeoff must not be performed before 25 minutes after chocks on. At the end of this time interval, check that the wheel thermal plugs have not melted. The tables in the following pages are provided for the maximum manual braking setting and no runway slope.

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 132

Landing

REVISION 21

AOM-1502-003

NOTE: If the tires are not flat after 25 minutes, this is a positive indication that the wheel thermal plugs have not melted.

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 175 – CF34-8 ENGINES FLAP 5 – WITHOUT ICE ACCRETION ALTITUDE 0 ft

Temp

1000 ft

AOM-1502-003

(°C)

WIND -10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

80310

88665

89000

89000

78926

87062

89000

89000

-15

79515

87763

89000

89000

78176

86172

89000

89000

-10

78768

86885

89000

89000

77445

85307

88106

89000

-5

78046

86030

88862

89000

76714

84464

87229

89000

0

77344

85197

87995

89000

75991

83648

86374

89000

5

76634

84384

87149

89000

75313

82885

85540

88294

10

75940

83601

86326

89000

74653

82096

84727

87448

15

75287

82865

85522

88277

74008

81362

83934

86624

20

74649

82101

84736

87461

73379

80653

83190

85820

25

74026

81392

83970

86663

72764

79936

82454

85034

30

73417

80706

83249

85885

72162

79233

81716

84268

35

72822

80015

82541

85126

71578

78572

81029

83531

40

72239

79329

81818

84383

71027

77926

80353

82834

45

71669

78689

81154

83662

70486

77293

79663

82108

50

71135

78063

80503

82989

---

---

---

---

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 133

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 175 – CF34-8 ENGINES FLAP 5 – WITHOUT ICE ACCRETION ALTITUDE 2000 ft

Temp

(°C)

3000 ft

-10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

77593

85471

88275

89000

76206

83873

86610

89000

-15

76839

84594

87362

89000

75469

83044

85711

88466

-10

76084

83742

86473

89000

74758

82206

84835

87556

-5

75380

82949

85608

88361

74067

81410

83983

86670

0

74695

82135

84765

87484

73391

80650

83183

85807

5

74027

81374

83944

86631

72732

79882

82390

84967

10

73376

80639

83172

85798

72090

79134

81608

84146

15

72740

79896

82407

84985

71470

78429

80876

83368

20

72119

79173

81650

84193

70882

77739

80145

82621

25

71516

78490

80941

83437

70298

77063

79411

81847

30

70948

77823

80237

82717

69714

76374

78727

81140

35

70385

77170

79526

81962

69142

75716

78062

80447

40

69817

76502

78858

81275

68583

75089

77409

79736

45

69261

75858

78210

80604

---

---

---

---

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 134

Landing

REVISION 21

AOM-1502-003

WIND

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 175 – CF34-8 ENGINES FLAP 5 – WITHOUT ICE ACCRETION ALTITUDE 4000 ft

Temp

AOM-1502-003

(°C)

5000 ft WIND

-10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

74862

82329

84957

87682

73564

80829

83364

86000

-15

74143

81494

84071

86761

72854

80008

82521

85093

-10

73442

80704

83237

85865

72161

79198

81671

84209

-5

72760

79909

82418

84993

71492

78440

80882

83370

0

72094

79134

81607

84143

70862

77700

80097

82565

5

71453

78404

80849

83338

70235

76970

79314

81744

10

70846

77691

80090

82561

69609

76233

78584

80987

15

70242

76988

79334

81767

68999

75540

77872

80236

20

69638

76277

78631

81036

68402

74870

77177

79479

25

69047

75604

77942

80316

67841

74216

76466

78770

30

68471

74957

77270

79583

67295

73579

75785

78082

35

67927

74325

76587

78892

66741

72954

75137

77411

40

67398

73707

75920

78226

66196

72344

74503

76734

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 135

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

QUICK TURN AROUND WEIGHT (lb) EMBRAER 175 – CF34-8 ENGINES FLAP FULL – WITHOUT ICE ACCRETION ALTITUDE 0 ft

Temp

1000 ft

(°C) -10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

89000

89000

89000

89000

87583

89000

89000

89000

-15

88214

89000

89000

89000

86777

89000

89000

89000

-10

87417

89000

89000

89000

85991

89000

89000

89000

-5

86640

89000

89000

89000

85186

89000

89000

89000

0

85879

89000

89000

89000

84424

89000

89000

89000

5

85103

89000

89000

89000

83692

89000

89000

89000

10

84372

89000

89000

89000

82945

89000

89000

89000

15

83665

89000

89000

89000

82223

89000

89000

89000

20

82944

89000

89000

89000

81402

89000

89000

89000

25

82247

89000

89000

89000

80549

89000

89000

89000

30

81458

89000

89000

89000

79747

88640

89000

89000

35

80632

89000

89000

89000

78945

87900

89000

89000

40

79854

88752

89000

89000

78144

87199

89000

89000

45

79081

88029

89000

89000

77402

86513

89000

89000

50

78299

87351

89000

89000

---

---

---

---

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 136

Landing

REVISION 21

AOM-1502-003

WIND

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

QUICK TURN AROUND WEIGHT (lb) EMBRAER 175 – CF34-8 ENGINES FLAP FULL – WITHOUT ICE ACCRETION ALTITUDE 2000 ft

Temp

AOM-1502-003

(°C)

3000 ft WIND

-10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

86147

89000

89000

89000

84644

89000

89000

89000

-15

85318

89000

89000

89000

83858

89000

89000

89000

-10

84521

89000

89000

89000

83058

89000

89000

89000

-5

83764

89000

89000

89000

82282

89000

89000

89000

0

82989

89000

89000

89000

81411

89000

89000

89000 89000

5

82242

89000

89000

89000

80498

89000

89000

10

81393

89000

89000

89000

79644

88520

89000

89000

15

80511

89000

89000

89000

78779

87738

89000

89000

20

79685

88566

89000

89000

77939

86991

89000

89000

25

78850

87807

89000

89000

77151

86262

89000

89000

30

78032

87083

89000

89000

76379

85526

88294

89000

35

77267

86377

89000

89000

75671

84797

87564

89000

40

76517

85670

88445

89000

75012

84117

86856

89000

45

75814

84957

87728

89000

---

---

---

---

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 137

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

QUICK TURN AROUND WEIGHT (lb) EMBRAER 175 – CF34-8 ENGINES FLAP FULL – WITHOUT ICE ACCRETION ALTITUDE 4000 ft

Temp

(°C)

5000 ft

-10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

83174

89000

89000

89000

81646

89000

89000

89000

-15

82365

89000

89000

89000

80660

89000

89000

89000

-10

81480

89000

89000

89000

79734

88587

89000

89000

-5

80533

89000

89000

89000

78808

87744

89000

89000

0

79648

88517

89000

89000

77907

86942

89000

89000

5

78753

87708

89000

89000

77062

86161

88961

89000

10

77887

86937

89000

89000

76238

85368

88127

89000

15

77072

86183

88988

89000

75498

84600

87353

89000

20

76276

85419

88180

89000

74810

83874

86599

89000

25

75558

84672

87433

89000

74185

83132

85855

88575

30

74886

83972

86703

89000

73576

82408

85096

87806

35

74281

83259

85991

88720

72978

81626

84381

87074

40

73691

82556

85255

87965

72395

80760

83689

86360

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 138

Landing

REVISION 21

AOM-1502-003

WIND

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 175 – CF34-8 ENGINES FLAP 5 – WITH ICE ACCRETION ALTITUDE 0 ft

Temp

1000 ft

AOM-1502-003

(°C)

WIND -10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

74984

82470

85066

87780

73718

80974

83520

86147

-15

74265

81626

84188

86891

73009

80155

82690

85239

-10

73567

80804

83354

85961

72319

79379

81848

84364

-5

72884

80024

82552

85097

71647

78591

81029

83525

0

72221

79274

81742

84256

70992

77840

80240

82730 81924

5

71573

78513

80952

83450

70352

77120

79494

10

70941

77794

80194

82685

69729

76390

78741

81136

15

70323

77097

79474

81906

69120

75692

78012

80371

20

69722

76391

78745

81144

68524

75026

77319

79654

25

69134

75718

78040

80404

67944

74374

76621

78934

30

68557

75073

77372

79710

67376

73739

75936

78220

35

67996

74443

76696

79016

66837

73116

75291

77553

40

67445

73825

76030

78323

66314

72507

74661

76886

45

66919

73222

75404

77672

65789

71914

74043

76218

50

66414

72634

74794

77033

---

---

---

---

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 139

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 175 – CF34-8 ENGINES FLAP 5 – WITH ICE ACCRETION ALTITUDE 2000 ft

Temp

(°C)

3000 ft

-10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

72462

79531

82010

-15

71763

78717

81157

84529

71193

78054

80458

82953

83648

70504

77279

79653

-10

71082

77933

80334

82824

82092

69833

76497

78847

81242

-5

70417

77187

79559

81991

69178

75743

78061

80418

0

69770

76430

78780

81173

68540

75029

77318

79648 78876

5

69140

75705

78024

80380

67918

74331

76569

10

68524

75015

77306

79637

67311

73650

75841

78119

15

67923

74341

76582

78892

66740

72987

75153

77403

20

67336

73683

75877

78157

66182

72338

74481

76686

25

66780

73040

75211

77466

65618

71706

73825

75979

30

66241

72413

74561

76774

65067

71087

73183

75315

35

65697

71800

73923

76085

64545

70483

72558

74666

40

65162

71201

73302

75440

64038

69894

71945

74032

45

64652

70613

72694

74810

---

---

---

---

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 140

Landing

REVISION 21

AOM-1502-003

WIND

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 175 – CF34-8 ENGINES FLAP 5 – WITH ICE ACCRETION ALTITUDE 4000 ft

Temp

(°C) -10 kt

AOM-1502-003

5000 ft WIND

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

69934

76611

78965

81364

68710

75204

77494

79828

-15

69254

75825

78142

80505

68039

74450

76692

79000

-10

68592

75081

77372

79703

67385

73716

75906

78180

-5

67947

74357

76597

78903

66766

73002

75166

77414

0

67319

73652

75842

78118

66168

72307

74444

76642

5

66726

72966

75130

77379

65564

71629

73741

75889

10

66150

72296

74434

76636

64976

70967

73054

75178

15

65567

71641

73757

75908

64421

70323

72386

74486

20

64999

71004

73094

75222

63876

69693

71732

73809

25

64463

70381

72448

74553

63326

69079

71096

73148

30

63938

69772

71818

73898

62791

68478

70473

72502

35

63407

69178

71201

73259

62285

67891

69864

71873

40

62888

68597

70598

72635

61789

67317

69269

71256

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 141

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 175 – CF34-8 ENGINES FLAP FULL – WITH ICE ACCRETION ALTITUDE 0 ft

Temp

1000 ft

(°C) -10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

86266

89000

89000

89000

84500

89000

89000

89000

-15

85313

89000

89000

89000

83476

89000

89000

89000

-10

84281

89000

89000

89000

82505

89000

89000

89000

-5

83308

89000

89000

89000

81509

89000

89000

89000

0

82360

89000

89000

89000

80569

89000

89000

89000

5

81408

89000

89000

89000

79685

89000

89000

89000

10

80501

89000

89000

89000

78797

88676

89000

89000

15

79650

89000

89000

89000

77934

87896

89000

89000

20

78792

88683

89000

89000

77117

87133

89000

89000

25

77955

87928

89000

89000

76279

86422

89000

89000

30

77169

87191

89000

89000

75547

85629

88458

89000

35

76358

86500

89000

89000

74874

84686

87719

89000

40

75636

85768

88569

89000

74264

83766

86998

89000

45

74975

84852

87852

89000

73676

82922

86325

89000

50

74383

83961

87152

89000

---

---

---

---

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 142

Landing

REVISION 21

AOM-1502-003

WIND

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 175 – CF34-8 ENGINES FLAP FULL – WITH ICE ACCRETION ALTITUDE 2000 ft

Temp

AOM-1502-003

(°C)

3000 ft WIND

-10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

82713

89000

89000

89000

80850

89000

89000

89000

-15

81672

89000

89000

89000

79887

89000

89000

89000

-10

80694

89000

89000

89000

78940

88784

89000

89000

-5

79771

89000

89000

89000

78006

87944

89000

89000

0

78854

88714

89000

89000

77132

87127

89000

89000

5

77957

87905

89000

89000

76235

86365

89000

89000

10

77112

87117

89000

89000

75462

85483

88339

89000

15

76244

86381

89000

89000

74754

84478

87549

89000

20

75495

85540

88385

89000

74106

83516

86793

89000

25

74806

84566

87621

89000

73487

82612

86078

88777

30

74176

83627

86883

89000

72894

81664

85133

88012

35

73574

82757

86189

88902

72314

80774

84177

87265

40

72998

81835

85321

88161

71747

79930

83277

86562

45

72435

80971

84391

87435

---

---

---

---

5-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing

Page 143

PERFORMANCE

AIRPLANE OPERATIONS MANUAL QUICK TURN AROUND WEIGHT (lb) EMBRAER 175 – CF34-8 ENGINES FLAP FULL – WITH ICE ACCRETION ALTITUDE 4000 ft

Temp

(°C)

5000 ft WIND

-10 kt

0 kt

10 kt

20 kt

-10 kt

0 kt

10 kt

20 kt

-20

79082

88905

89000

89000

77358

87317

89000

89000

-15

78106

88032

89000

89000

76400

86486

89000

89000

-10

77200

87184

89000

89000

75545

85571

88402

89000

-5

76272

86390

89000

89000

74779

84491

87554

89000

0

75468

85482

88336

89000

74083

83459

86744

89000

5

74735

84440

87519

89000

73423

82480

85973

88661

10

74065

83451

86739

89000

72788

81477

84924

87844

15

73429

82507

86000

88691

72169

80527

83904

87049

20

72816

81536

84993

87901

71561

79639

82963

86308

25

72219

80617

84006

87130

70944

78739

81986

85423

30

71633

79754

83089

86412

70351

77870

81061

84429

35

71037

78891

82158

85602

69786

77043

80173

83481

40

70458

78041

81253

84639

69234

76194

79329

82587

5-35 Copyright © by Embraer. Refer to cover page for details.

Page 144

Landing

REVISION 21

AOM-1502-003

"

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

CAT II OPERATION The performance data required for Category II operations are presented by basic CAFM output tables and must be calculated previously.

APPROACH CLIMB LANDING CLIMB LANDING

ENGINES

TLA

FLAPS

GEAR

AIRSPEED APPROACH CLMB SPEED [1]

1

TO/GA

2

UP

2

TO/GA

5

DOWN

VREF5

[2]

2

IDLE

5

DOWN

VREF5

[2]

AOM-1502-003

1. Approach climb speed is equal to VREF5. 2. The Landing Reference Speed (VREF5) for Category II operations is the appropriate speed obtained from the CAFM.

5-40 Copyright © by Embraer. Refer to cover page for details.

REVISION 14

Supplementary Operations

Page 1

PERFORMANCE

AIRPLANE OPERATIONS MANUAL

5-40 Copyright © by Embraer. Refer to cover page for details.

Page 2

Supplementary Operations

REVISION 14

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

SECTION 6 FLIGHT PLANNING TABLE OF CONTENTS Block

Page

Simplified Flight Planning................................... 6-05 ...........

1

EMBRAER 170 Models

SIMPLIFIED FLIGHT PLANNING.......................... 6-05 ...........

1

EMBRAER 175 Models

SIMPLIFIED FLIGHT PLANNING.......................... 6-05 ...........

6

EMBRAER 170 Models

CRUISE - FLIGHT LEVEL TABLE......................... 6-05 ........... 11 EMBRAER 175 Models

CRUISE - FLIGHT LEVEL TABLE......................... 6-05 ........... 14 EMBRAER 170 Models

CRUISE - ALTITUDE CAPABILITY TABLE........... 6-05 ........... 17 EMBRAER 175 Models

CRUISE - ALTITUDE CAPABILITY TABLE........... 6-05 ........... 20 EMBRAER 170 Models

CRUISE - WIND ALTITUDE TRADE..................... 6-05 ........... 23 EMBRAER 175 Models

CRUISE - WIND ALTITUDE TRADE..................... 6-05 ........... 26 EMBRAER 170 Models

FLIGHT PLANNING - FUEL TANKERING............. 6-05 ........... 29 EMBRAER 175 Models

FLIGHT PLANNING - FUEL TANKERING............. 6-05 ........... 32 Engine and APU Fuel Consumption.................. 6-07 ........... ENGINE FUEL CONSUMPTION........................... 6-07 ........... APU FUEL CONSUMPTION.................................. 6-07 ...........

1 1 2

Climb..................................................................... 6-10 ...........

1

EMBRAER 170 Models

CLIMB SPEEDS..................................................... 6-10 ...........

1

EMBRAER 175 Models AOM-1502-003

CLIMB SPEEDS..................................................... 6-10 ...........

3

EMBRAER 170 Models

6-TOC Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Table of Contents

Page 1

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

Block Page CLIMB TABLES...................................................... 6-10 ........... 4 EMBRAER 175 Models

CLIMB TABLES...................................................... 6-10 ........... 43 Cruise.................................................................... 6-15 ...........

1

EMBRAER 170 Models

BUFFET ONSET.................................................... 6-15 ...........

1

EMBRAER 175 Models

BUFFET ONSET.................................................... 6-15 ...........

5

EMBRAER 170 Models

LONG RANGE CRUISE........................................ 6-15 ...........

9

EMBRAER 175 Models

LONG RANGE CRUISE........................................ 6-15 ........... 26 EMBRAER 170 Models

FIXED SPEED CRUISE......................................... 6-15 ........... 43 EMBRAER 175 Models

FIXED SPEED CRUISE......................................... 6-15 ........... 63 EMBRAER 170 Models

COST INDEX AND ECONOMIC CRUISE SPEED.. 6-15 ........... 71 EMBRAER 175 Models

COST INDEX AND ECONOMIC CRUISE SPEED.. 6-15 ........... 77 Descent................................................................. 6-20 ...........

1

EMBRAER 170 Models

DESCENT.............................................................. 6-20 ...........

1

EMBRAER 175 Models

DESCENT.............................................................. 6-20 ...........

5

EMBRAER 170 Models

IDLE DESCENT - CONSTANT FLIGHT PATH ANGLE............................................................. 6-20 ...........

9

EMBRAER 175 Models

IDLE DESCENT - CONSTANT FLIGHT PATH ANGLE............................................................. 6-20 ........... 13 Holding.................................................................. 6-25 ...........

1

EMBRAER 170 Models

HOLDING............................................................... 6-25 ...........

1

EMBRAER 175 Models

6-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 21

AOM-1502-003

HOLDING............................................................... 6-25 ........... 11

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

Block Page One Engine Inoperative Performance................ 6-30 ........... 1 EMBRAER 170 Models

ONE ENGINE INOPERATIVE - LONG RANGE CRUISE............................................................ 6-30 ...........

1

EMBRAER 175 Models

ONE ENGINE INOPERATIVE - LONG RANGE CRUISE............................................................ 6-30 ........... 10 EMBRAER 170 Models

ONE ENGINE INOPERATIVE - DRIFTDOWN...... 6-30 ........... 18 EMBRAER 175 Models

ONE ENGINE INOPERATIVE - DRIFTDOWN...... 6-30 ........... 21 EMBRAER 170 Models

ONE ENGINE INOPERATIVE - ALTITUDE CAPABILITY..................................................... 6-30 ........... 24 EMBRAER 175 Models

ONE ENGINE INOPERATIVE - ALTITUDE CAPABILITY..................................................... 6-30 ........... 26 EMBRAER 170 Models

ONE ENGINE INOPERATIVE - HOLDING........... 6-30 ........... 28 EMBRAER 175 Models

ONE ENGINE INOPERATIVE - HOLDING........... 6-30 ........... 38 MAXIMUM DISTANCE FROM AN ADEQUATE AERODROME.................................................. 6-30 ........... 48 INFLIGHT DIVERSION.......................................... 6-30 ........... 51 Inflight Diversion.................................................. 6-35 ...........

1

EMBRAER 170 Models

INFLIGHT DIVERSION.......................................... 6-35 ...........

1

EMBRAER 175 Models

AOM-1502-003

INFLIGHT DIVERSION.......................................... 6-35 ........... FLIGHT OVER MOUNTAINOUS AREA................. 6-35 ...........

4 7

6-TOC Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Table of Contents

Page 3

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

6-TOC Copyright © by Embraer. Refer to cover page for details.

Page 4

Table of Contents

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

SIMPLIFIED FLIGHT PLANNING !EMBRAER 170 Models

Simplified flight planning charts allow quick determination of estimated trip fuel and time from brake release to landing. The following phases are included: takeoff, climb, cruise, descent, approach and landing. Alternate fuel, holding, reserve fuel and other allowances (APU usage and taxi) should be added to the trip fuel in order to obtain the total fuel required. To determine trip fuel enter trip ground distance, correct for wind condition and estimated landing weight, move as far as the line indicating cruise pressure altitude, and read the trip fuel. To determine trip time, enter trip ground distance, correct for wind condition, move as far as the referring cruise pressure altitude, and read the trip time. For winds greater than those shown, enter in the chart, directly, corrected ground distance, ignore wind correction reference line, to obtain the corrected ground distance, apply the following equation. CGD

=

GD

x

( TAS ) ( TAS + WIND )

Where: CGD: Corrected ground distance; GD: Ground distance; Head wind is negative; Tail wind is positive. The alternate fuel is determined by entering the Simplified Flight Planning chart with the alternate distance and wind.

AOM-1502-003

The holding fuel is determined from the holding table in this section. Depending upon national regulations, the holding fuel is normally calculated so that the aircraft can hold for 30 min, at 1500 ft above the alternate airport.

6-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Simplified Flight Planning

Page 1

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

EMBRAER 170 SIMPLIFIED FLIGHT PLANNING TRIP FUEL ALL ENGINE TYPES LONG RANGE CRUISE ISA CONDITION 16000 FL 200 FL 250 BASED ON: 240 / 290 / M 0.70 CLIMB M 0.77 / 290 / 250 DESCENT

14000

FL 150 FL 300

FUEL REQUIRED − lb

12000 FL 350 10000

8000 FL370 AND ABOVE 6000

4000

REF. LINE

30 REF. LINE

30 60 0

200

400

600

800

1000

1200

1400

TRIP DISTANCE − NM

1600

1800

2000

6-05 Copyright © by Embraer. Refer to cover page for details.

Page 2

Simplified Flight Planning

REVISION 21

AOM-1502-003

0

EM170AOM060006D.DGN

HEAD

73000 71000 69000 67000 65000 63000 60

TAIL

WIND − kt

LANDING WEIGHT − lb

2000

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

EMBRAER 170 SIMPLIFIED FLIGHT PLANNING TRIP TIME ALL ENGINE TYPES LONG RANGE CRUISE ISA CONDITION FL 250 BASED ON: 240 / 290 / M 0.70 CLIMB M 0.77 / 290 / 250 DESCENT

250

FL 150

FL 200

FL 300 FL 350

FLIGHT TIME − min

200

FL370 AND ABOVE

150

100

50

WIND − kt LANDING WEIGHT − lb TAIL HEAD

0 73000 71000 69000

REF. LINE

67000 65000 63000 60

0

REF. LINE

30 60 0

200

400

600

800

1000

1200

1400

AOM-1502-003

TRIP DISTANCE − NM

1600

1800

2000

EM170AOM060002E.DGN

30

6-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Simplified Flight Planning

Page 3

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

EMBRAER 170 SIMPLIFIED FLIGHT PLANNING TRIP FUEL ALL ENGINE TYPES MACH 0.78 CRUISE ISA CONDITION 16000 FL 300

BASED ON: 240 / 290 / M 0.70 CLIMB M 0.77 / 290 / 250 DESCENT

14000

FUEL REQUIRED − lb

12000

FL370 AND ABOVE

10000

8000

6000

4000

REF. LINE

30 REF. LINE

30 60 0

200

400

600

800

1000

1200

1400

TRIP DISTANCE − NM

1600

1800

2000

6-05 Copyright © by Embraer. Refer to cover page for details.

Page 4

Simplified Flight Planning

REVISION 21

AOM-1502-003

0

EM170AOM060004D.DGN

HEAD

WIND − kt

73000 71000 69000 67000 65000 63000 60

TAIL

LANDING WEIGHT − lb

2000

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

EMBRAER 170 SIMPLIFIED FLIGHT PLANNING TRIP TIME ALL ENGINE TYPES MACH 0.78 CRUISE ISA CONDITION 250 FL 350

BASED ON: 240 / 290 / M 0.70 CLIMB M 0.77 / 290 / 250 DESCENT

225

FLIGHT TIME − min

200 FL 300

175 150 FL370 AND ABOVE 125 100 75 50 25

30 0

REF. LINE

30 60 0

200

400

600

800

1000

1200

1400

AOM-1502-003

TRIP DISTANCE − NM

1600

1800 2000

EM170AOM060007C.DGN

WIND − kt TAIL HEAD

60

"

6-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Simplified Flight Planning

Page 5

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

SIMPLIFIED FLIGHT PLANNING !EMBRAER 175 Models

Simplified flight planning charts allow quick determination of estimated trip fuel and time from brake release to landing. The following phases are included: takeoff, climb, cruise, descent, approach and landing. Alternate fuel, holding, reserve fuel and other allowances (APU usage and taxi) should be added to the trip fuel in order to obtain the total fuel required. To determine trip fuel enter trip ground distance, correct for wind condition and estimated landing weight, move as far as the line indicating cruise pressure altitude, and read the trip fuel. To determine trip time, enter trip ground distance, correct for wind condition, move as far as the referring cruise pressure altitude, and read the trip time. For winds greater than those shown, enter in the chart, directly, corrected ground distance, ignore wind correction reference line, to obtain the corrected ground distance, apply the following equation. CGD

=

GD

x

( TAS ) ( TAS + WIND )

Where: CGD: Corrected ground distance; GD: Ground distance; Head wind is negative; Tail wind is positive. The alternate fuel is determined by entering the Simplified Flight Planning chart with the alternate distance and wind.

6-05 Copyright © by Embraer. Refer to cover page for details.

Page 6

Simplified Flight Planning

REVISION 21

AOM-1502-003

The holding fuel is determined from the holding table in this section. Depending upon national regulations, the holding fuel is normally calculated so that the aircraft can hold for 30 min, at 1500 ft above the alternate airport.

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

EMBRAER 175 SIMPLIFIED FLIGHT PLANNING TRIP FUEL ALL ENGINE TYPES LONG RANGE CRUISE

LANDING WEIGHT − lb

FUEL REQUIRED − lb

ISA CONDITION 23000 22000 21000 20000 19000 18000 17000 16000 15000 14000 13000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000

BASED ON: 240 / 290 / M 0.70 CLIMB M 0.77 / 290 / 250 DESCENT

FL 150

FL 200 FL 250 FL 300 FL 350

FL 370 AND ABOVE

74000 70000 66000 62000 58000 54000

REF. LINE

HEAD

30

0 REF. LINE

60

0

200 400 600 800 1000 1200 1400 1600 1800 2000 2200 2400 2600

AOM-1502-003

TRIP DISTANCE − NM

EM170AOM060024D.DGN

WIND − kt

30

TAIL

60

6-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Simplified Flight Planning

Page 7

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

EMBRAER 175 SIMPLIFIED FLIGHT PLANNING TRIP TIME ALL ENGINE TYPES LONG RANGE CRUISE ISA CONDITION BASED ON: 240 / 290 / M 0.70 CLIMB M 0.77 / 290 / 250 DESCENT

FL 200 FL 250 FL 150 FL 300 FL 350

FL 370 AND ABOVE

74000 70000 66000 62000 58000 54000

REF. LINE

60

REF. LINE

0 30 60 0

200 400 600 800 1000 1200 1400 1600 1800 2000 2200 2400 2600

TRIP DISTANCE − NM

6-05 Copyright © by Embraer. Refer to cover page for details.

Page 8

Simplified Flight Planning

REVISION 21

AOM-1502-003

30

EM170AOM060063C.DGN

WIND − kt TAIL HEAD

LANDING WEIGHT − lb

FLIGHT TIME − min

450 430 410 390 370 350 330 310 290 270 250 230 210 190 170 150 130 110 90 70 50 30 10

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

EMBRAER 175 SIMPLIFIED FLIGHT PLANNING TRIP FUEL ALL ENGINE TYPES MACH 0.78 CRUISE

LANDING WEIGHT − lb

FUEL REQUIRED − lb

ISA CONDITION 23000 22000 21000 20000 19000 18000 17000 16000 15000 14000 13000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000

FL 300

BASED ON: 240 / 290 / M 0.70 CLIMB M 0.77 / 290 / 250 DESCENT

FL 350 AND ABOVE

74000 70000 66000 62000 58000 54000

REF. LINE

30

0

REF. LINE

60

0

200

400

600

800

1000 1200 1400 1600 1800 2000 2200

AOM-1502-003

TRIP DISTANCE − NM

EM170AOM060062B.DGN

HEAD

30

TAIL

60

6-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Simplified Flight Planning

Page 9

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

EMBRAER 175 SIMPLIFIED FLIGHT PLANNING TRIP TIME ALL ENGINE TYPES MACH 0.78 CRUISE ISA CONDITION 330

BASED ON: 240 / 290 / M 0.70 CLIMB M 0.77 / 290 / 250 DESCENT

310 290

FL 300

FLIGHT TIME − min

270 250

FL 370 AND ABOVE

230 210 190 170 150 130 110 90 70 50 30 10

30

REF. LINE

0 30 60 0

200

400

600

800 1000 1200 1400 1600 1800 2000 2200 2400 2600

TRIP DISTANCE − NM

EM170AOM060064C.DGN

WIND − kt TAIL HEAD

60

6-05 Copyright © by Embraer. Refer to cover page for details.

Page 10

Simplified Flight Planning

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

CRUISE - FLIGHT LEVEL TABLE !EMBRAER 170 Models

The following tables permit quick determination of the cruise flight level for minimum fuel consumption, based on the trip distance and takeoff weight. The flight level was calculated based on a combination of minimum fuel consumption and at least 5 minutes in cruise.

CLIMB UP

DESCENT

AT LEAST 5 MINUTES OF CRUISE

EM170AOM060008B.DGN

CRUISE

AOM-1502-003

The table data are presented for ISA condition and all engines operating. A minimum remaining rate of climb equal to 300 ft/min is considered.

6-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Simplified Flight Planning

Page 11

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

FLIGHT LEVEL - ALL ENGINES OPERATING ALL ENGINES, LONG RANGE CRUISE AND ISA CONDITIONS TRIP DISTANCE (NM) 1000

TOW

(lb)

100

150

200

250

300

400

500

600

700

800

900

and above

82000 [1]

80000 [1]

78000 [1]

76000 [1]

74000 [1]

72000 70000 68000 66000 64000 62000 60000 [2]

-

-

-

-

-

-

-

-

-

-

-

350

-

-

-

-

-

-

-

-

-

-

360

360

-

-

-

-

-

-

-

-

360

360

360

360

-

-

-

-

-

-

360

370

370

370

370

370

-

-

300

310

310

370

370

370

370

370

370

370

160

220

300

310

320

380

380

380

380

380

380

380

160

220

300

320

320

380

380

380

380

380

380

380

160

210

300

330

330

380

380

380

380

380

380

380

160

210

300

330

340

340

390

390

390

390

390

390

160

210

300

340

340

350

400

400

400

400

400

400

170

210

300

350

350

360

400

400

400

400

400

400

170

210

310

350

360

360

410

410

410

410

410

-

6-05 Copyright © by Embraer. Refer to cover page for details.

Page 12

Simplified Flight Planning

REVISION 21

AOM-1502-003

1. The Blank spaces means that the landing weight is beyond the Maximum Landing Weight. 2. The Blank spaces means that the TOW does not allow enough fuel quantity to accomplish the specified trip distance.

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

FLIGHT LEVEL - ALL ENGINES OPERATING ALL ENGINES, MACH 0.78 AND ISA CONDITIONS TRIP DISTANCE (NM) 1000

TOW

(lb)

200

300

400

500

600

700

800

900

and above

82000 [1]

80000 [1]

78000 [1]

76000 [1]

74000 72000 70000 68000 66000 64000 62000 60000 [2]

-

-

-

-

-

-

-

-

340

-

-

-

-

-

-

-

340

340

-

-

-

-

-

350

350

350

350

-

-

350

350

350

350

350

350

350

310

360

360

360

360

360

360

360

360

320

360

360

360

360

360

360

360

360

320

370

370

370

370

370

370

370

370

330

370

370

370

370

370

370

370

370

330

380

380

380

380

380

380

380

380

340

380

380

380

380

380

380

380

380

340

390

390

390

390

390

390

390

390

350

400

400

400

400

400

400

400

-

1. The Blank spaces means that the landing weight is beyond the Maximum Landing Weight. 2. The Blank spaces means that the TOW does not allow enough fuel quantity to accomplish the specified trip distance.

AOM-1502-003

"

6-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Simplified Flight Planning

Page 13

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CRUISE - FLIGHT LEVEL TABLE !EMBRAER 175 Models

The following tables permit quick determination of the cruise flight level for minimum fuel consumption, based on the trip distance and takeoff weight. The flight level was calculated based on a combination of minimum fuel consumption and at least 5 minutes in cruise.

CLIMB UP

DESCENT

AT LEAST 5 MINUTES OF CRUISE

EM170AOM060008B.DGN

CRUISE

6-05 Copyright © by Embraer. Refer to cover page for details.

Page 14

Simplified Flight Planning

REVISION 21

AOM-1502-003

The table data are presented for ISA condition and all engines operating. A minimum remaining rate of climb equal to 300 ft/min is considered.

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

FLIGHT LEVEL - ALL ENGINES OPERATING ALL ENGINES, LONG RANGE CRUISE AND ISA CONDITIONS TRIP DISTANCE (NM) 1000

TOW

(lb)

100

150

200

250

300

400

500

600

700

800

900

and above

85000 [1]

83000 [1]

81000 [1]

79000 [1]

77000 [1]

75000 73000 71000 69000 67000 65000 63000 [2]

61000 [2]

-

-

-

-

-

-

-

-

-

-

-

340

-

-

-

-

-

-

-

-

-

340

340

340

-

-

-

-

-

-

-

350

350

350

350

350

-

-

-

-

-

350

350

350

350

350

350

350

-

220

290

300

300

360

360

360

360

360

360

360

150

220

300

300

310

360

360

360

360

360

360

360

150

220

300

310

310

370

370

370

370

370

370

370

160

220

300

310

320

370

370

370

370

370

370

370

160

220

310

320

330

380

380

380

380

380

380

380

160

220

310

330

330

380

380

380

380

380

380

380

160

220

310

340

340

340

390

390

390

390

390

390

160

220

310

340

350

350

360

360

360

-

-

-

170

220

310

350

360

360

360

-

-

-

-

-

AOM-1502-003

1. The Blank spaces means that the landing weight is beyond the Maximum Landing Weight. 2. The Blank spaces means that the TOW does not allow enough fuel quantity to accomplish the specified trip distance.

6-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Simplified Flight Planning

Page 15

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

FLIGHT LEVEL - ALL ENGINES OPERATING ALL ENGINES, MACH 0.78 AND ISA CONDITIONS TRIP DISTANCE (NM) 1000

TOW

(lb)

200

300

400

500

600

700

800

900

and above

85000 [1]

83000 [1]

81000 [1]

79000 [1]

77000 75000 73000 71000 69000 67000 65000 [2]

63000 [2]

61000 [2]

-

-

-

-

-

-

-

-

320

-

-

-

-

-

-

320

320

320

-

-

-

-

330

330

330

330

330

-

-

340

340

340

340

340

340

340

300

350

350

350

350

350

350

350

350

310

350

350

350

350

350

350

350

350

310

360

360

360

360

360

360

360

360

320

360

360

360

360

360

360

360

360

320

370

370

370

370

370

370

370

370

330

370

370

370

370

370

370

370

370

330

380

380

380

380

380

380

380

-

340

380

380

380

380

380

-

-

-

350

390

390

-

-

-

-

-

-

1. The Blank spaces means that the landing weight is beyond the Maximum Landing Weight. 2. The Blank spaces means that the TOW does not allow enough fuel quantity to accomplish the specified trip distance.

6-05 Copyright © by Embraer. Refer to cover page for details.

Page 16

Simplified Flight Planning

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

CRUISE - ALTITUDE CAPABILITY TABLE !EMBRAER 170 Models

The tables below permit quick determination of the altitude capability, based on the initial cruise weight. Tables are presented for various ISA conditions and all engines operating. The established associated conditions are:

AOM-1502-003

Flaps.......................................................................... UP Gears......................................................................... UP Bleeds........................................................................ OPEN Center of gravity........................................................ 18% Minimum Remaining Rate of Climb.......................... 300 ft/min Minimum Buffet Margin............................................. 1.3 g Thrust Setting............................................................ MAX CRUISE THRUST

6-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Simplified Flight Planning

Page 17

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CRUISE ALTITUDE CAPABILITY - ALL ENGINES OPERATING ALL ENGINES, LONG RANGE CRUISE

-10

-5

0

5

10

15

20

25

30

35

82000

340

340

340

340

340

330

320

310

300

300

80000

350

350

350

350

350

340

320

310

310

310

78000

350

360

360

360

360

350

330

320

320

320

76000

350

360

360

360

360

350

340

330

320

320

74000

350

370

370

370

370

360

350

330

330

330

72000

350

370

370

370

370

360

350

340

340

340

70000

350

380

380

380

380

370

360

350

340

340

68000

350

380

380

380

380

370

360

350

350

350

66000

350

390

380

390

390

380

370

360

360

360

64000

350

390

390

390

390

380

370

360

360

360

62000

350

400

400

390

390

390

380

370

360

360

60000

350

400

400

400

400

390

380

370

360

360

58000

350

410

410

410

410

400

390

380

370

360

56000

350

410

410

410

410

400

390

390

380

370

54000

350

410

410

410

410

410

400

390

380

380

52000

350

410

410

410

410

410

410

400

390

380

50000

350

410

410

410

410

410

410

410

400

390

48000

350

410

410

410

410

410

410

410

400

400

6-05 Copyright © by Embraer. Refer to cover page for details.

Page 18

Simplified Flight Planning

REVISION 21

AOM-1502-003

ISA + ºC

Weight (lb)

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CRUISE ALTITUDE CAPABILITY - ALL ENGINES OPERATING ALL ENGINES, MACH 0.78 ISA + ºC

Weight (lb)

-10

-5

0

5

10

15

20

25

30

35

82000

320

330

330

330

330

300

-

-

-

-

80000

330

330

330

330

330

310

-

-

-

-

78000

340

340

340

340

340

320

-

-

-

-

76000

340

350

350

350

350

330

-

-

-

-

74000

340

350

350

350

350

340

-

-

-

-

72000

340

360

360

360

360

350

320

-

-

-

70000

340

360

360

360

360

360

330

-

-

-

68000

340

370

370

370

370

360

340

-

-

-

66000

340

370

370

370

370

370

350

-

-

-

64000

340

380

380

380

380

370

360

-

-

-

62000

340

380

380

380

380

380

360

340

-

-

60000

340

390

390

390

390

380

370

350

-

-

58000

340

400

400

400

400

390

370

360

-

-

56000

340

400

400

400

400

390

380

360

-

-

54000

340

410

410

410

410

400

380

370

-

-

52000

340

410

410

410

410

400

390

370

-

-

50000

340

410

410

410

410

410

390

380

360

-

48000

340

410

410

410

410

410

400

380

360

-

AOM-1502-003

"

6-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Simplified Flight Planning

Page 19

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CRUISE - ALTITUDE CAPABILITY TABLE !EMBRAER 175 Models

The tables below permit quick determination of the altitude capability, based on the initial cruise weight. Tables are presented for various ISA conditions and all engines operating.

6-05 Copyright © by Embraer. Refer to cover page for details.

Page 20

Simplified Flight Planning

REVISION 21

AOM-1502-003

The established associated conditions are: Flaps.......................................................................... UP Gears......................................................................... UP Bleeds........................................................................ OPEN Center of gravity........................................................ 18% Minimum Remaining Rate of Climb.......................... 300 ft/min Minimum Buffet Margin............................................. 1.3 g Thrust Setting............................................................ MAX CRUISE THRUST

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

AOM-1502-003

CRUISE ALTITUDE CAPABILITY - ALL ENGINES OPERATING ALL ENGINES, LONG RANGE CRUISE ISA + ºC

Weight (lb)

-10

-5

0

5

10

15

20

25

30

35

82000

340

340

340

340

340

330

310

300

300

300

80000

340

350

350

350

350

330

320

310

300

300

78000

340

350

350

350

350

340

330

320

310

310

76000

340

360

360

360

360

350

330

320

320

320

74000

340

360

360

360

360

360

340

330

330

330

72000

340

370

370

370

370

360

350

340

330

330

70000

340

370

370

370

370

370

360

340

340

340

68000

340

380

380

380

380

370

360

350

350

350

66000

340

380

380

380

380

370

370

360

360

360

64000

340

390

390

390

390

380

370

360

360

360

62000

340

390

390

390

390

380

370

370

360

360

60000

340

400

400

400

400

390

380

370

360

360

58000

340

400

400

400

400

390

390

380

370

360

56000

340

410

410

410

410

400

390

380

380

370

54000

340

410

410

410

410

410

400

390

380

370

52000

340

410

410

410

410

410

410

400

390

380

50000

340

410

410

410

410

410

410

410

400

390

6-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Simplified Flight Planning

Page 21

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CRUISE ALTITUDE CAPABILITY - ALL ENGINES OPERATING ALL ENGINES, MACH 0.78 Weight (lb)

ISA + ºC -10

-5

0

5

10

15

20

25

30

35

82000

320

320

320

320

320

-

-

-

-

-

80000

330

330

330

330

330

300

-

-

-

-

78000

330

330

340

340

340

310

-

-

-

-

76000

340

340

340

340

340

320

-

-

-

-

74000

340

350

350

350

350

330

-

-

-

-

72000

340

360

360

360

360

340

-

-

-

-

70000

340

360

360

360

360

350

320

-

-

-

68000

340

360

360

360

360

360

330

-

-

-

66000

340

370

370

370

370

360

340

-

-

-

64000

340

380

380

380

380

370

350

-

-

-

62000

340

380

380

380

380

370

360

-

-

-

60000

340

390

390

390

390

380

360

-

-

-

58000

340

390

390

390

390

380

370

350

-

-

56000

340

400

400

400

400

390

380

360

-

-

54000

340

400

400

400

400

390

380

360

-

-

52000

340

410

410

410

410

400

380

370

-

-

50000

340

410

410

410

410

400

390

370

-

-

6-05 Copyright © by Embraer. Refer to cover page for details.

Page 22

Simplified Flight Planning

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

CRUISE - WIND ALTITUDE TRADE !EMBRAER 170 Models

The following tables allow the determination of the break- even wind in order to maintain the same ground specific range at another altitude than the one planned initially.

AOM-1502-003

These tables are based on the comparison between ground specific range at the new and actual altitudes. They do not consider climb/descent time, fuel and distances. The tables may be used in-flight, where the wind information is available and more accurate.

6-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Simplified Flight Planning

Page 23

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CRUISE – WIND ALTITUDE TRADE TABLES ALL ENGINES, LONG RANGE CRUISE Pressure

Weight (lb)

Altitude (ft) 39000 38000 37000 36000 35000 34000 33000 32000 31000 30000 29000 28000 27000

60000 62000 64000 66000 68000 70000 72000 74000 76000 78000 5 6 7 8 9 12 19 25 29 33 42 50 58

4 6 7 8 9 10 17 23 27 31 38 47 55

0 3 7 8 9 10 12 19 23 28 34 41 49

0 6 8 10 10 11 16 21 25 31 37 45

0 5 10 12 13 14 14 20 25 31 36 43

0 2 7 11 13 13 13 15 21 27 33 38

0 2 8 11 12 12 12 16 22 28 34

1 0 6 11 13 14 14 14 20 26 32

0 5 10 13 15 15 15 18 24 30

0 1 5 11 14 14 14 14 20 26

Evaluation Method 1 - Check the wind factors for actual and new altitudes on table above. 2 - Calculate the difference between new and actual wind factors. This number may be negative or positive. 3 - The BREAK EVEN WIND at the new altitude is the wind component at actual altitude plus the difference calculated on step (2). Example: 66000 lb of actual cruise weight, LRC: Actual Flight Level: FL 280, -10 kt (headwind) New Flight Level: FL 350, -20 kt (headwind) 1 - Wind factor FL280 = 37, Wind factor FL350 = 10 2 - Difference = 10 (new FL) - 37 (actual FL) = -27 3 - Break Even Wind = -10 (wind actual FL) -27 (difference) = -37 kt

6-05 Copyright © by Embraer. Refer to cover page for details.

Page 24

Simplified Flight Planning

REVISION 21

AOM-1502-003

Wind on FL350 (20 kt headwind) is more favorable than Break Even Wind (37 kt headwind). Therefore, climb to FL350.

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL ALL ENGINES, MACH 0.78 Pressure

Weight (lb)

Altitude (ft) 39000 38000 37000 36000 35000 34000 33000 32000 31000 30000 29000 28000 27000

60000 62000 64000 66000 68000 70000 72000 74000 76000 78000 0 8 20 30 45 60 76 93 112 130 150 170 193

0 11 20 34 47 63 79 97 114 135 154 175

0 7 16 30 42 57 72 90 106 126 145 166

0 9 21 33 47 61 78 95 114 132 152

0 5 16 28 41 55 71 87 105 123 143

0 9 20 32 45 60 76 93 111 130

0 5 16 27 40 54 69 86 103 122

0 7 19 31 44 58 74 91 109

0 4 15 26 39 52 67 84 101

0 7 18 31 43 57 73 90

Evaluation Method 1 - Check the wind factors for actual and new altitudes on table above. 2 - Calculate the difference between new and actual wind factors. This number may be negative or positive. 3 - The BREAK EVEN WIND at the new altitude is the wind component at actual altitude plus the difference calculated on step (2). Example: 68000 lb of actual cruise weight, Mach 0.78: Actual Flight Level: FL 360, -10 kt (headwind) New Flight Level: FL 310, 15 kt (tailwind) 1 - Wind factor FL360 = 5, Wind factor FL310 = 71 2 - Difference = 71 (new FL) - 5 (actual FL) = 66 3 - Break Even Wind = -10 (wind actual FL) + 66 (difference) = 76 kt Wind on FL310 (15 kt tailwind) is less favorable than Break Even Wind (76 kt tailwind). Therefore, maintain FL360.

AOM-1502-003

"

6-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Simplified Flight Planning

Page 25

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CRUISE - WIND ALTITUDE TRADE !EMBRAER 175 Models

The following tables allow the determination of the break-even wind in order to maintain the same specific range at another altitude than the one planned initially.

6-05 Copyright © by Embraer. Refer to cover page for details.

Page 26

Simplified Flight Planning

REVISION 21

AOM-1502-003

These tables are based on the comparison between ground specific range at the new and actual altitudes. They do not consider climb/descent time, fuel and distances. The tables may be used in flight, where the wind information is available and more accurate.

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CRUISE – WIND ALTITUDE TRADE TABLES ALL ENGINES, LONG RANGE CRUISE Pressure

Weight (lb)

Altitude (ft) 39000 38000 37000 36000 35000 34000 33000 32000 31000 30000 29000 28000 27000

62000 64000 66000 68000 70000 72000 74000 76000 78000 80000 0 3 5 5 5 6 12 19 23 27 33 42 50

0 3 7 8 9 9 12 19 23 28 33 40 49

0 6 8 10 10 10 15 20 25 31 36 44

0 6 10 12 13 13 13 19 25 30 35 41

0 4 9 11 11 10 16 19 25 30 36

0 1 8 11 12 12 15 16 22 28 33

0 7 12 14 15 15 16 21 27 32

0 4 9 12 14 15 15 17 23 29

0 3 9 12 13 13 15 18 24

0 2 8 11 13 14 15 15 21

Evaluation Method 1 - Check the wind factors for actual and new altitudes on table above. 2 - Calculate the difference between new and actual wind factors. This number may be negative or positive. 3 - The BREAK EVEN WIND at the new altitude is the wind component at actual altitude plus the difference calculated on step (2). Example: 70000 lb of actual cruise weight, LRC: Actual Flight Level: FL 280, -10 kt (headwind) New Flight Level: FL 350, -20 kt (headwind) 1 - Wind factor FL280 = 30, Wind factor FL350 = 9 2 - Difference = 9 (new FL) - 30 (actual FL) = -21 3 - Break Even Wind = -10 (wind actual FL) + (-21) (difference) = -31 kt

AOM-1502-003

Wind on FL350 (20 kt headwind) is more favorable than Break Even Wind (31 kt headwind). Therefore, climb to FL350.

6-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Simplified Flight Planning

Page 27

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL ALL ENGINES, MACH 0.78

Pressure

Weight (lb)

Altitude (ft) 39000 38000 37000 36000 35000 34000 33000 32000 31000 30000 29000 28000 27000

62000 64000 66000 68000 70000 72000 74000 76000 78000 80000 0 10 20 34 47 63 79 97 114 134 154 175

0 6 17 29 42 57 72 90 107 126 146 166

0 9 21 33 46 61 78 95 113 132 152

0 11 23 36 49 65 82 99 117 137

0 9 20 32 45 60 76 93 111 130

0 5 15 28 40 54 69 86 103 122

0 7 19 31 44 58 74 90 109

0 11 22 35 48 63 79 96

0 7 18 31 43 57 73 90

0 10 21 34 47 61 78

Evaluation Method 1 - Check the wind factors for actual and new altitudes on table above. 2 - Calculate the difference between new and actual wind factors. This number may be negative or positive. 3 - The BREAK EVEN WIND at the new altitude is the wind component at actual altitude plus the difference calculated on step (2). Example: 68000 lb of actual cruise weight, Mach 0.78 Actual Flight Level: FL 340, -10 kt (headwind) New Flight Level: FL 310, 15 kt (tailwind) 1 - Wind factor FL340 = 23, Wind factor FL310 = 65 2 - Difference = 65 (new FL) - 23 (actual FL) = 42 3 - Break Even Wind = -10 (wind actual FL) + 42 (difference) = 32 kt Wind on FL310 (15 kt tailwind) is less favorable than Break Even Wind (32 kt tailwind). Therefore, maintain FL340.

6-05 Copyright © by Embraer. Refer to cover page for details.

Page 28

Simplified Flight Planning

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

FLIGHT PLANNING - FUEL TANKERING !EMBRAER 170 Models

Fuel price variations at different airports may require carrying more fuel than the minimum required on a flight leg. The procedure of loading this extra amount of fuel (or surplus fuel) in order to minimize fuel costs is known as Fuel Tankering. Since the surplus fuel tankered results in additional fuel burnoff (due to the weight increase) it is important to analyze the costs of the extra fuel transportation operation. The following tables are designed to determine the break-even fuel price on departure airport and it may be used whenever there is difference on fuel price comparing to destination. Enter the trip distance on the table and read the fuel surplus ratio according to cruise altitude. The break-even fuel price is the price at departure multiplied by the fuel surplus ratio. If break-even fuel price is lower than destination price, it is economically feasible to execute fuel tankering. The additional maintenance costs involved with increased weight operations (additional brakes and tires wearing) are not considered. It is important to remind that whenever fuel tankering is considered, the estimated landing weight at destination should be lower than the Maximum Landing Weight.

Example Analyze the possibility to proceed with fuel tankering between two airports distant 600 NM from each other, using LRC speed schedule cruising on FL350. Consider the following fuel prices: Departure Airport: 1.80 US$/Gal.

AOM-1502-003

Destination Airport: 2.00 US$/Gal.

•

Enter the LONG RANGE CRUISE table for 600 NM trip distance and FL350, the FUEL SURPLUS RATIO is 1.05.

•

The BREAK-EVEN PRICE is 1.80 (price at departure) multiplied by 1.05 = 1.89 US$/Gal.

6-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Simplified Flight Planning

Page 29

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

Since fuel price on destination airport (2.00 US$/Gal) is greater than break-even fuel price (1.89 US$/Gal), it is economically feasible the fuel tankering operation between these two airports.

6-05 Copyright © by Embraer. Refer to cover page for details.

Page 30

Simplified Flight Planning

REVISION 21

AOM-1502-003

FUEL TANKERING EMBRAER 170 / ALL ENGINES LONG RANGE CRUISE FUEL SURPLUS RATIO TRIP DISTANCE 31000 ft and 32000 ft (NM) below above 200 1.02 1.02 400 1.03 1.03 600 1.04 1.05 800 1.06 1.07 1000 1.07 1.09 1200 1.08 1.11 1400 1.10 1.12 1600 1.11 1.14 1800 1.13 1.18 2000 1.14 1.19

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

FUEL TANKERING EMBRAER 170 / ALL ENGINES MACH 0.78 FUEL SURPLUS RATIO TRIP DISTANCE 31000 ft and 32000 ft (NM) below above 200 1.01 1.01 400 1.02 1.02 600 1.03 1.03 800 1.04 1.04 1000 1.04 1.05 1200 1.05 1.06 1400 1.06 1.07 1600 1.07 1.09 1800 1.08 1.09 2000 1.08 1.11

AOM-1502-003

"

6-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Simplified Flight Planning

Page 31

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING - FUEL TANKERING !EMBRAER 175 Models

Fuel price variations at different airports may require carrying more fuel than the minimum required on a flight leg. The procedure of loading this extra amount of fuel (or surplus fuel) in order to minimize fuel costs is known as Fuel Tankering. Since the surplus fuel tankered results in additional fuel burnoff (due to the weight increase) it is important to analyze the costs of the extra fuel transportation operation. The following tables are designed to determine the break-even fuel price on departure airport and it may be used whenever there is difference on fuel price comparing to destination. Enter the trip distance on the table and read the fuel surplus ratio according to cruise altitude. The break-even fuel price is the price at departure multiplied by the fuel surplus ratio. If break-even fuel price is lower than destination price, it is economically feasible to execute fuel tankering. The additional maintenance costs involved with increased weight operations (additional brakes and tires wearing) are not considered. It is important to remind that whenever fuel tankering is considered, the estimated landing weight at destination should be lower than the Maximum Landing Weight.

Example Analyze the possibility to proceed with fuel tankering between two airports distant 600 NM from each other, using LRC speed schedule cruising on FL350. Consider the following fuel prices: Departure Airport: 1.80 US$/Gal.

•

Enter the LONG RANGE CRUISE table for 600 NM trip distance and FL350, the FUEL SURPLUS RATIO is 1.05.

•

The BREAK-EVEN PRICE is 1.80 (price at departure) multiplied by 1.05 = 1.89 US$/Gal.

6-05 Copyright © by Embraer. Refer to cover page for details.

Page 32

Simplified Flight Planning

REVISION 21

AOM-1502-003

Destination Airport: 2.00 US$/Gal.

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

Since fuel price on destination airport (2.00 US$/Gal) is greater than break-even fuel price (1.89 US$/Gal), it is economically feasible the fuel tankering operation between these two airports.

AOM-1502-003

FUEL TANKERING EMBRAER 175 / ALL ENGINES LONG RANGE CRUISE FUEL SURPLUS RATIO TRIP DISTANCE 31000 ft and 32000 ft (NM) below above 200 1.02 1.02 400 1.03 1.03 600 1.04 1.05 800 1.06 1.07 1000 1.07 1.08 1200 1.08 1.10 1400 1.10 1.12 1600 1.11 1.13 1800 1.13 1.16 2000 1.14 1.17

6-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Simplified Flight Planning

Page 33

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

FUEL TANKERING EMBRAER 175 / ALL ENGINES MACH 0.78 FUEL SURPLUS RATIO TRIP DISTANCE 31000 ft and 32000 ft (NM) below above 200 1.01 1.01 400 1.02 1.02 600 1.03 1.03 800 1.04 1.04 1000 1.04 1.06 1200 1.05 1.07 1400 1.06 1.08 1600 1.07 1.10 1800 1.08 1.10 2000 1.09 1.11

6-05 Copyright © by Embraer. Refer to cover page for details.

Page 34

Simplified Flight Planning

REVISION 21

AOM-1502-003

"

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ENGINE FUEL CONSUMPTION The following values established for taxi, take-off, approach and go around fuel consumption should be considered when calculating detailed flight plans. FUEL CONSUMPTION ENGINE

PHASE OF FLIGHT

TAXI ALL TAKE-OFF ENGINE APPROACH AND LANDING TYPES GO AROUND

FUEL CONSUMPTION lb/min 18 160 39 160

A typical average value to be used during the flight planning calculation should be considered: TAKE-OFF =320 lb (2 minutes used); APPROACH AND LANDING = 156 lb (4 minutes used);

AOM-1502-003

GO AROUND = 160 lb (1 minute used).

6-07 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Engine and APU Fuel Consumption

Page 1

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

APU FUEL CONSUMPTION The table below shows the APU fuel consumption on the ground and during level flight at 5000 ft, 15000 ft, and 33000 ft altitudes. The data is calculated for different airspeeds, APU air bleeds and electrical loads. AIRSPEED (KIAS)

APU AIR BLEED 0

0

0 Max. 0 170 Max.

5000 0 300 Max. 0 170 Max. 15000 0 320 Max. 170

0

300

0

33000

APU GEN. LOAD (kVA) 0 40 0 40 0 40 0 40 0 40 0 40 0 40 0 40 0 40 0 40 0 40 0 40

APU FUEL FLOW (lb/min) 3.3 3.8 4.7 5.2 2.8 3.3 4.0 4.5 2.8 3.2 3.9 4.5 2.2 2.6 3.1 3.7 2.1 2.6 3.1 3.7 1.5 2.1 1.4 2.0

6-07 Copyright © by Embraer. Refer to cover page for details.

Page 2

Engine and APU Fuel Consumption

REVISION 21

AOM-1502-003

ALTITUDE (ft)

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB SPEEDS !EMBRAER 170 Models

MAXIMUM ANGLE SPEED This speed is recommended for obstacle clearance in order to reach an altitude on minimum ground distance. The recommended maximum angle speed is related to flaps up, all engines operating and is approximately VFS for all gross weights and altitudes.

MAXIMUM RATE OF CLIMB SPEED This speed is recommended when maximum rate of climb is desired in order to reach an altitude on minimum climb time. The recommended maximum rate of climb speed is related to flaps up, all engines operating and is function of gross weights and altitudes as shown in the tables below: Weight (lb)

Altitude (ft)

58000

60000

62000

64000

66000

68000

5000

241

241

241

241

242

242

10000

233

234

235

236

237

238

15000

223

224

224

228

232

236

20000

220

221

223

223

224

224

25000

215

216

217

219

220

221

Weight (lb)

Altitude (ft)

70000

72000

74000

76000

78000

80000

5000

244

246

250

250

250

249

10000

240

242

246

246

246

245

15000

237

239

241

241

241

241

20000

227

231

237

237

236

235

25000

225

228

234

232

231

230

AOM-1502-003

Maintain the speeds above until intercepting Mach 0.60 or green dot speed, whichever is higher, following this until level off.

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 1

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

!!170 models, MAU Load 21.2 up to Load 25.4 - Pentium M or Load 25.3 Pentium II

The green dot does not account for ice accretion. Therefore when flying in icing conditions (EICAS message STALL PROT ICE SPEED displayed) it is recommended to add 10 kt to the green dot. "" !!170 models, MAU Load 25.5.0.1 and on

The green dot accounts for ice accretion.

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 2

Climb

REVISION 21

AOM-1502-003

"" "

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB SPEEDS !EMBRAER 175 Models

MAXIMUM ANGLE SPEED This speed is recommended for obstacle clearance in order to reach an altitude on minimum ground distance. The recommended maximum angle speed is related to flaps up, all engines operating and is approximately VFS for all gross weights and altitudes.

MAXIMUM RATE OF CLIMB SPEED This speed is recommended when maximum rate of climb is desired in order to reach an altitude on minimum climb time. The recommended maximum rate of climb speed is related to flaps up, all engines operating and is function of gross weights and altitudes as shown in the tables below: Weight (lb)

Altitude (ft)

49000

55000

61000

67000

73000

79000

85000

5000

235

237

240

242

245

248

250

10000

226

232

235

237

240

244

247

15000

216

219

223

232

236

237

241

20000

212

217

221

223

229

234

239

25000

210

212

218

222

226

229

233

Maintain the speeds above until intercepting Mach 0.63 or green dot speed, whichever is higher, following this until level off. !!175 models, MAU Load 21.2 up to Load 25.4 - Pentium M or Load 25.3 Pentium II

The green dot does not account for ice accretion. Therefore when flying in icing conditions (EICAS message STALL PROT ICE SPEED displayed) it is recommended to add 10 kt to the green dot.

AOM-1502-003

""

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 3

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

!!175 models, MAU Load 25.5.0.1 and on

The green dot accounts for ice accretion. "" "

CLIMB TABLES !EMBRAER 170 Models

The climb planning tables show fuel consumption, distance, and time elapsed from the Sea Level to the top of climb. Data are shown for various weights, ISA deviations and cruise altitudes. The takeoff fuel consumption is not considered in the following tables. Tables present the scheduled climb speed according to the autopilot climb mode, i.e.: – 240 KIAS for altitudes up to 10000 ft, increasing linearly to 290 KIAS at 12000 ft, maintaining 290 KIAS up to 25400 ft and 0.7 Mach above 25400 ft. The associated conditions are:

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 4

Climb

REVISION 21

AOM-1502-003

Thrust Mode.............................................................. CLB1 Flaps.......................................................................... UP Gear........................................................................... UP Bleeds........................................................................ OPEN Anti-Ice...................................................................... OFF CG............................................................................. 18% Minimum Remaining Rate of Climb.......................... 300 ft/min

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

EXAMPLE: Given: Departure Airport Elevation....................................... 3500 ft Takeoff weight............................................................ 70000 lb ISA Condition Cruise Altitude.................................... 33000 ft

RESULTS: Data for 5000 ft (3500 ft + 1500 ft above departure airport) obtained from the climb table: Fuel: 189 lb Distance: 5 NM Time: 1 min Data provided from the Sea Level to 33000 ft (Top of Climb) table: Fuel: 1604 lb Distance: 90 NM Time: 15 min The fuel, distance and time spent during the climb phase (from 5000 ft to 33000 ft) are: Fuel: 1604 – 189 = 1415 lb Distance: 90 – 5 = 85 NM Time: 15 – 1 = 14 min

AOM-1502-003

The fuel consumption related to the takeoff phase is provided on the Section 1-06-07.

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 5

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 5000 AND 6000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

5000 ft ISA + °C -10 0

10

20

-20

6000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

217 6 1 210 6 1 203 5 1 197 5 1 191 5 1 185 5 1 179 5 1 173 5 1 167 4 1 161 4 1

227 6 1 220 6 1 213 6 1 206 5 1 200 5 1 193 5 1 187 5 1 181 5 1 174 5 1 168 4 1

237 6 2 230 6 1 223 6 1 216 6 1 209 6 1 202 5 1 196 5 1 189 5 1 183 5 1 176 5 1

250 7 2 242 6 2 234 6 1 227 6 1 220 6 1 213 6 1 206 5 1 199 5 1 192 5 1 185 5 1

274 8 2 265 8 2 257 8 2 249 7 2 240 7 2 232 7 2 225 7 2 217 6 1 209 6 1 202 6 1

260 7 2 252 7 2 244 7 2 237 6 2 229 6 2 222 6 2 214 6 1 207 6 1 200 5 1 193 5 1

272 7 2 264 7 2 256 7 2 247 7 2 240 6 2 232 6 2 224 6 1 217 6 1 209 6 1 202 5 1

285 8 2 276 7 2 267 7 2 259 7 2 251 7 2 243 7 2 235 6 2 227 6 1 219 6 1 211 6 1

300 8 2 291 8 2 282 8 2 273 7 2 264 7 2 255 7 2 247 7 2 239 6 2 231 6 1 223 6 1

330 10 2 319 10 2 309 9 2 299 9 2 289 9 2 279 8 2 270 8 2 260 8 2 251 7 2 242 7 2

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 1 1

3 2 2

2 1 1

0 0 0

0 0 0

3 1 1

3 2 2

2 1 1

0 0 0

0 0 0

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 6

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 5000 AND 6000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

5000 ft ISA + °C -10 0

10

20

-20

6000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

155 4 1 150 4 1 144 4 1 139 4 1 134 4 1 129 3 1 124 3 1 118 3 1 113 3 1

162 4 1 157 4 1 151 4 1 145 4 1 140 4 1 135 4 1 129 3 1 124 3 1 118 3 1

170 4 1 164 4 1 158 4 1 152 4 1 147 4 1 141 4 1 135 4 1 130 3 1 124 3 1

179 5 1 173 5 1 166 4 1 160 4 1 154 4 1 148 4 1 142 4 1 136 4 1 130 3 1

194 6 1 187 5 1 180 5 1 174 5 1 167 5 1 160 5 1 154 4 1 147 4 1 141 4 1

186 5 1 180 5 1 173 5 1 167 4 1 161 4 1 154 4 1 148 4 1 142 4 1 136 4 1

195 5 1 188 5 1 181 5 1 174 5 1 168 4 1 161 4 1 155 4 1 148 4 1 142 4 1

204 5 1 197 5 1 190 5 1 183 5 1 176 5 1 169 4 1 162 4 1 155 4 1 149 4 1

215 6 1 207 6 1 199 5 1 192 5 1 185 5 1 178 5 1 170 4 1 163 4 1 156 4 1

233 7 2 225 7 2 217 6 2 208 6 1 200 6 1 192 6 1 185 5 1 177 5 1 169 5 1

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 1 1

3 1 1

2 1 1

0 0 0

0 0 0

3 1 1

3 1 1

2 1 1

0 0 0

0 0 0

64000

62000

60000

58000

56000

54000

52000

50000

AOM-1502-003

48000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 7

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 7000 AND 8000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

7000 ft ISA + °C -10 0

10

20

-20

8000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

304 8 2 295 8 2 285 8 2 276 8 2 267 7 2 259 7 2 250 7 2 242 7 2 234 6 2 226 6 2

318 9 2 308 8 2 298 8 2 289 8 2 280 8 2 271 7 2 262 7 2 253 7 2 244 7 2 236 6 2

333 9 2 322 9 2 312 9 2 302 8 2 293 8 2 283 8 2 274 7 2 265 7 2 256 7 2 247 7 2

350 10 2 340 9 2 329 9 2 318 9 2 308 8 2 298 8 2 288 8 2 279 8 2 269 7 2 260 7 2

386 12 3 373 11 3 361 11 3 349 11 2 337 10 2 326 10 2 315 10 2 304 9 2 293 9 2 283 9 2

348 10 2 337 9 2 326 9 2 316 9 2 306 9 2 296 8 2 286 8 2 276 8 2 267 7 2 258 7 2

364 10 2 352 10 2 341 10 2 330 9 2 320 9 2 309 9 2 299 8 2 289 8 2 279 8 2 270 8 2

381 11 3 369 10 2 357 10 2 346 10 2 334 9 2 324 9 2 313 9 2 302 8 2 292 8 2 282 8 2

401 11 3 388 11 3 376 10 2 364 10 2 352 10 2 341 9 2 329 9 2 318 9 2 307 9 2 297 8 2

442 14 3 427 13 3 413 13 3 399 12 3 386 12 3 373 12 3 360 11 3 348 11 2 335 10 2 324 10 2

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 2

3 2 1

2 1 1

0 0 0

0 0 0

3 2 2

3 1 1

2 1 1

0 1 1

0 0 0

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 8

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 7000 AND 8000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

7000 ft ISA + °C -10 0

10

20

-20

8000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

218 6 1 210 6 1 202 6 1 195 5 1 187 5 1 180 5 1 173 5 1 165 4 1 158 4 1

227 6 2 219 6 1 211 6 1 203 6 1 196 5 1 188 5 1 181 5 1 173 5 1 166 4 1

238 6 2 229 6 2 221 6 1 213 6 1 205 6 1 197 5 1 189 5 1 181 5 1 173 5 1

250 7 2 241 7 2 233 6 1 224 6 1 215 6 1 207 6 1 199 5 1 190 5 1 182 5 1

273 8 2 263 8 2 253 8 2 243 7 2 234 7 2 224 7 2 215 6 2 206 6 1 197 6 1

249 7 2 240 7 2 231 6 2 222 6 2 214 6 1 205 6 1 197 5 1 189 5 1 181 5 1

260 7 2 251 7 2 242 7 2 232 6 2 224 6 2 215 6 1 206 6 1 198 5 1 189 5 1

272 8 2 262 7 2 253 7 2 243 7 2 234 6 2 225 6 1 216 6 1 207 6 1 198 5 1

286 8 2 276 8 2 266 7 2 256 7 2 246 7 2 236 6 2 227 6 1 218 6 1 208 6 1

312 10 2 300 9 2 289 9 2 278 9 2 267 8 2 257 8 2 246 8 2 236 7 2 226 7 2

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 1 1

3 1 1

2 1 1

0 0 0

0 0 0

3 2 1

3 1 1

2 1 1

0 1 1

0 0 0

64000

62000

60000

58000

56000

54000

52000

50000

AOM-1502-003

48000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 9

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 9000 AND 10000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

9000 ft ISA + °C -10 0

10

20

-20

10000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

392 11 3 380 11 3 368 11 3 356 10 2 344 10 2 333 10 2 322 9 2 311 9 2 300 9 2 290 8 2

410 12 3 397 11 3 385 11 3 372 11 3 360 10 2 348 10 2 337 10 2 325 9 2 314 9 2 303 9 2

429 12 3 415 12 3 402 11 3 389 11 3 377 11 3 364 10 2 352 10 2 340 10 2 329 9 2 317 9 2

452 13 3 438 12 3 424 12 3 410 12 3 397 11 3 384 11 3 371 11 2 358 10 2 346 10 2 334 9 2

498 16 4 482 15 3 466 15 3 450 14 3 435 14 3 420 13 3 406 13 3 392 12 3 378 12 3 364 11 3

436 13 3 422 12 3 409 12 3 396 12 3 383 11 3 371 11 3 358 10 3 346 10 2 334 10 2 322 9 2

456 13 3 442 13 3 428 12 3 414 12 3 401 12 3 388 11 3 375 11 3 362 11 3 350 10 2 337 10 2

477 14 3 462 13 3 447 13 3 433 13 3 419 12 3 405 12 3 392 11 3 378 11 3 365 11 2 353 10 2

503 15 3 487 14 3 471 14 3 456 13 3 441 13 3 427 12 3 413 12 3 399 12 3 385 11 3 371 11 2

555 18 4 537 17 4 519 17 4 501 16 4 485 16 4 468 15 3 452 15 3 436 14 3 420 13 3 405 13 3

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 2

3 1 1

3 1 1

1 2 2

0 0 0

3 2 2

3 1 1

3 1 1

1 3 3

0 0 0

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 10

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 9000 AND 10000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

9000 ft ISA + °C -10 0

10

20

-20

10000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

280 8 2 270 8 2 260 7 2 250 7 2 241 7 2 231 7 2 222 6 2 213 6 1 203 6 1

293 8 2 282 8 2 272 8 2 262 7 2 252 7 2 242 7 2 232 7 2 222 6 2 213 6 1

306 9 2 295 8 2 284 8 2 273 8 2 263 7 2 253 7 2 242 7 2 232 7 2 222 6 1

322 9 2 311 9 2 299 8 2 288 8 2 277 8 2 266 7 2 255 7 2 245 7 2 234 7 2

351 11 3 338 11 2 326 10 2 313 10 2 301 9 2 289 9 2 277 9 2 265 8 2 254 8 2

311 9 2 300 9 2 289 8 2 278 8 2 267 8 2 257 7 2 246 7 2 236 7 2 226 6 2

325 9 2 314 9 2 302 9 2 291 8 2 280 8 2 269 8 2 258 7 2 247 7 2 236 7 2

340 10 2 328 9 2 316 9 2 304 9 2 292 8 2 281 8 2 269 8 2 258 7 2 247 7 2

358 10 2 345 10 2 333 10 2 320 9 2 308 9 2 296 8 2 284 8 2 272 8 2 260 7 2

391 13 3 376 12 3 362 12 3 348 11 3 335 11 2 321 10 2 308 10 2 295 9 2 282 9 2

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 2

3 1 1

2 1 1

1 2 2

0 0 0

3 2 2

3 1 1

3 1 1

1 3 2

0 0 0

64000

62000

60000

58000

56000

54000

52000

50000

AOM-1502-003

48000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 11

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 11000 AND 12000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

11000 ft ISA + °C -10 0

10

20

-20

12000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

512 16 4 495 15 4 479 15 3 464 14 3 449 14 3 434 13 3 420 13 3 405 12 3 391 12 3 378 11 3

535 16 4 518 16 4 502 15 4 486 15 3 470 14 3 454 14 3 439 13 3 424 13 3 410 12 3 395 12 3

560 17 4 542 16 4 524 16 4 507 15 4 491 15 3 475 14 3 459 14 3 443 13 3 428 13 3 413 12 3

590 18 4 571 17 4 553 17 4 535 16 4 517 16 3 500 15 3 483 15 3 467 14 3 451 14 3 435 13 3

653 22 5 631 21 5 610 20 4 589 20 4 569 19 4 550 18 4 531 18 4 512 17 4 494 17 4 476 16 4

594 19 4 575 18 4 557 18 4 539 17 4 521 17 4 504 16 4 487 16 4 471 15 3 455 15 3 439 14 3

622 20 4 602 19 4 583 19 4 564 18 4 546 17 4 528 17 4 510 16 4 493 16 4 476 15 3 459 15 3

650 21 5 629 20 4 609 19 4 589 19 4 570 18 4 551 18 4 533 17 4 515 16 4 497 16 3 480 15 3

684 22 5 663 21 5 641 20 4 621 20 4 600 19 4 581 18 4 561 18 4 542 17 4 524 17 4 505 16 3

763 27 6 737 26 6 713 25 5 689 24 5 665 24 5 642 23 5 620 22 5 599 21 4 577 20 4 557 20 4

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 2

3 1 1

3 1 1

2 4 4

0 0 0

4 2 2

3 2 1

3 2 1

3 6 5

0 0 0

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 12

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 11000 AND 12000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

11000 ft ISA + °C -10 0

10

20

-20

12000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

364 11 3 351 11 3 338 10 2 326 10 2 313 9 2 301 9 2 289 9 2 276 8 2 265 8 2

381 11 3 367 11 3 354 11 2 341 10 2 328 10 2 315 9 2 302 9 2 289 9 2 277 8 2

398 12 3 384 12 3 370 11 3 356 11 2 342 10 2 329 10 2 315 9 2 302 9 2 289 9 2

419 13 3 404 12 3 389 12 3 375 11 3 360 11 2 346 10 2 332 10 2 318 9 2 304 9 2

459 15 3 442 15 3 425 14 3 409 14 3 393 13 3 377 13 3 361 12 3 346 11 3 331 11 2

423 14 3 408 13 3 393 13 3 378 12 3 364 12 3 350 11 3 335 11 2 321 10 2 308 10 2

443 14 3 427 14 3 411 13 3 396 13 3 381 12 3 366 12 3 351 11 3 336 11 2 322 10 2

463 15 3 446 14 3 430 14 3 414 13 3 398 13 3 382 12 3 367 12 3 351 11 2 336 11 2

487 15 3 470 15 3 452 14 3 435 14 3 419 13 3 402 13 3 386 12 3 370 12 3 354 11 2

536 19 4 516 18 4 497 17 4 478 17 4 459 16 3 441 15 3 423 15 3 405 14 3 387 14 3

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 2

3 1 1

3 1 1

2 4 4

0 0 0

3 2 2

3 1 1

3 1 1

3 6 5

0 0 0

64000

62000

60000

58000

56000

54000

52000

50000

AOM-1502-003

48000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 13

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 13000 AND 14000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

13000 ft ISA + °C -10 0

10

20

-20

14000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

644 21 5 624 21 5 604 20 4 585 19 4 566 19 4 547 18 4 529 17 4 511 17 4 493 16 4 476 16 4

675 22 5 653 22 5 632 21 5 612 20 4 592 20 4 573 19 4 554 18 4 535 18 4 517 17 4 499 16 4

705 23 5 682 22 5 661 22 5 639 21 5 619 20 4 598 20 4 578 19 4 559 18 4 540 18 4 521 17 4

742 24 5 718 24 5 695 23 5 673 22 5 651 21 5 629 21 4 608 20 4 588 19 4 568 19 4 548 18 4

832 30 6 804 29 6 777 28 6 751 27 6 725 26 5 700 26 5 676 25 5 653 24 5 629 23 5 607 22 5

696 24 5 674 23 5 652 22 5 631 22 5 610 21 5 590 20 4 571 19 4 551 19 4 533 18 4 514 18 4

729 25 5 705 24 5 683 23 5 661 22 5 639 22 5 618 21 5 598 20 4 577 20 4 558 19 4 538 18 4

762 26 5 737 25 5 713 24 5 690 23 5 668 23 5 646 22 5 624 21 4 603 20 4 583 20 4 562 19 4

801 27 6 775 26 5 750 25 5 726 24 5 702 24 5 679 23 5 657 22 5 634 21 4 613 21 4 591 20 4

903 34 7 872 33 7 842 32 6 814 31 6 786 30 6 759 29 6 733 28 6 708 27 5 682 26 5 658 25 5

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 2 2

3 2 2

3 2 2

4 7 6

1 1 1

4 3 2

4 2 2

3 2 2

4 8 7

2 3 2

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 14

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 13000 AND 14000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

13000 ft ISA + °C -10 0

10

20

-20

14000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

459 15 3 443 15 3 427 14 3 411 14 3 395 13 3 379 12 3 364 12 3 349 11 3 334 11 2

481 16 3 464 15 3 447 15 3 430 14 3 413 14 3 397 13 3 381 12 3 365 12 3 350 11 3

502 16 4 484 16 3 466 15 3 449 15 3 432 14 3 415 14 3 398 13 3 382 12 3 365 12 3

528 17 4 509 17 4 491 16 3 472 15 3 454 15 3 436 14 3 419 14 3 401 13 3 384 12 3

585 21 4 563 20 4 542 20 4 521 19 4 501 18 4 481 17 4 461 17 3 442 16 3 422 15 3

496 17 4 478 16 4 460 16 3 443 15 3 426 14 3 410 14 3 393 13 3 377 13 3 361 12 3

519 18 4 500 17 4 482 16 4 464 16 3 446 15 3 429 14 3 412 14 3 394 13 3 378 13 3

542 18 4 523 18 4 504 17 4 485 16 3 466 16 3 448 15 3 430 14 3 412 14 3 394 13 3

570 19 4 550 18 4 530 18 4 510 17 4 490 16 3 471 16 3 452 15 3 433 14 3 415 14 3

634 24 5 611 23 5 588 22 4 565 21 4 543 20 4 521 20 4 500 19 4 479 18 4 458 17 3

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 2

3 2 1

3 2 1

3 6 6

0 1 1

4 2 2

3 2 2

3 2 2

4 7 6

1 3 2

64000

62000

60000

58000

56000

54000

52000

50000

AOM-1502-003

48000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 15

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 15000 AND 16000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

15000 ft ISA + °C -10 0

10

20

-20

16000 ft ISA + °C -10 0

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

750 26 6 725 26 5 701 25 5 678 24 5 656 23 5 634 22 5 613 22 5 593 21 4 572 20 4 552 19 4

785 28 6 759 27 6 734 26 5 710 25 5 687 24 5 664 23 5 642 22 5 621 22 5 599 21 4 578 20 4

820 29 6 793 28 6 767 27 6 742 26 5 718 25 5 694 24 5 671 23 5 648 23 5 626 22 5 604 21 4

863 30 6 834 29 6 807 28 6 780 27 6 755 26 5 730 25 5 706 24 5 682 24 5 658 23 5 635 22 4

978 38 8 943 37 7 911 35 7 879 34 7 849 33 7 820 32 6 791 31 6 764 30 6 737 29 6 710 28 5

804 29 6 778 28 6 752 27 6 727 26 6 703 25 5 679 25 5 657 24 5 634 23 5 613 22 5 591 21 5

842 30 6 815 29 6 788 28 6 761 27 6 736 26 5 711 26 5 688 25 5 664 24 5 642 23 5 619 22 5

880 32 6 851 31 6 823 30 6 796 29 6 769 28 6 743 27 5 719 26 5 694 25 5 670 24 5 647 23 5

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 2 2

3 2 2

5 9 8

3 5 4

4 3 3

4 2 2

3 2 2

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

10

20

926 1055 33 42 7 8 895 1017 32 41 6 8 865 981 31 39 6 8 836 947 30 38 6 7 808 913 29 37 6 7 781 881 28 35 6 7 755 851 27 34 5 7 730 821 26 33 5 6 705 792 25 32 5 6 680 763 24 30 5 6 5 9 8

4 6 5

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 16

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 15000 AND 16000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

15000 ft ISA + °C -10 0

10

20

-20

16000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

533 19 4 514 18 4 495 17 4 476 17 4 458 16 3 440 15 3 422 15 3 405 14 3 388 13 3

558 19 4 538 19 4 518 18 4 499 17 4 480 17 4 461 16 3 442 15 3 424 15 3 406 14 3

583 20 4 562 20 4 541 19 4 521 18 4 501 17 4 482 17 3 462 16 3 443 15 3 424 15 3

613 21 4 591 20 4 569 20 4 548 19 4 527 18 4 506 17 4 486 17 3 466 16 3 446 15 3

684 27 5 659 26 5 634 25 5 610 24 5 586 23 5 563 22 4 540 21 4 517 20 4 495 19 4

570 21 4 550 20 4 530 19 4 510 18 4 490 18 4 471 17 4 452 16 3 433 16 3 415 15 3

597 21 4 576 21 4 555 20 4 534 19 4 514 18 4 493 18 4 474 17 4 454 16 3 435 15 3

624 22 5 602 22 4 580 21 4 558 20 4 537 19 4 516 18 4 495 18 4 474 17 3 454 16 3

656 23 5 632 23 5 609 22 4 586 21 4 564 20 4 542 19 4 520 18 4 498 18 4 477 17 3

736 29 6 708 28 6 682 27 5 656 26 5 630 25 5 605 24 5 580 23 5 556 22 4 532 21 4

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 2

3 2 2

3 2 2

4 8 7

2 4 3

4 3 3

4 2 2

3 2 2

5 9 8

3 6 5

64000

62000

60000

58000

56000

54000

52000

50000

AOM-1502-003

48000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 17

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 17000 AND 18000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

17000 ft ISA + °C -10 0

10

20

-20

18000 ft ISA + °C -10 0

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

860 32 7 832 31 6 804 30 6 777 29 6 751 28 6 725 27 6 701 26 5 677 25 5 654 24 5 631 23 5

901 33 7 871 32 7 842 31 6 814 30 6 787 29 6 760 28 6 734 27 6 709 26 5 685 25 5 661 24 5

942 35 7 911 34 7 880 33 6 851 31 6 822 30 6 794 29 6 767 28 6 741 27 5 716 26 5 691 25 5

990 37 7 957 35 7 925 34 7 894 33 6 864 32 6 835 31 6 806 30 6 779 29 6 752 28 5 726 27 5

1134 47 9 1093 45 9 1054 43 8 1017 42 8 980 40 8 945 39 7 912 37 7 879 36 7 848 35 7 818 34 6

918 35 7 888 34 7 858 33 7 829 32 6 801 31 6 773 30 6 747 29 6 721 28 6 696 27 5 671 26 5

962 1005 1056 1215 37 38 40 52 7 7 8 10 930 971 1021 1172 35 37 39 50 7 7 7 9 899 939 987 1129 34 36 37 48 7 7 7 9 868 907 953 1089 33 34 36 46 7 7 7 9 839 876 921 1049 32 33 35 44 6 7 7 8 810 846 889 1012 31 32 34 43 6 6 6 8 782 817 859 975 30 31 32 41 6 6 6 8 755 789 829 940 29 30 31 40 6 6 6 7 729 761 800 906 28 29 30 38 6 6 6 7 703 735 772 873 27 28 29 37 5 5 6 7

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 2 2

4 2 2

6 10 9

5 8 7

4 3 3

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

4 2 2

4 2 2

10

6 11 10

20

5 9 8

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 18

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 17000 AND 18000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

17000 ft ISA + °C -10 0

10

20

-20

18000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

609 23 5 587 22 5 565 21 4 544 20 4 523 19 4 503 19 4 482 18 4 462 17 4 443 16 3

638 24 5 615 23 5 592 22 4 570 21 4 548 20 4 527 19 4 505 19 4 484 18 4 464 17 3

666 25 5 642 24 5 619 23 5 595 22 4 573 21 4 550 20 4 528 19 4 506 19 4 484 18 4

700 26 5 675 25 5 650 24 5 626 23 5 602 22 4 578 21 4 555 20 4 532 19 4 509 19 4

788 32 6 759 31 6 730 30 6 702 29 6 675 28 5 648 27 5 621 25 5 595 24 5 569 23 4

648 25 5 624 24 5 601 23 5 579 22 5 557 21 4 535 20 4 513 19 4 492 19 4 471 18 4

678 26 5 654 25 5 630 24 5 606 23 5 583 22 4 560 21 4 538 20 4 515 19 4 493 19 4

709 27 5 683 26 5 658 25 5 633 24 5 609 23 5 585 22 4 562 21 4 538 20 4 515 19 4

745 28 5 718 27 5 691 26 5 665 25 5 640 24 5 615 23 4 590 22 4 566 21 4 541 20 4

841 35 7 810 34 6 779 33 6 749 32 6 720 30 6 691 29 5 663 28 5 635 27 5 608 26 5

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 2 2

3 2 2

5 9 8

4 7 6

4 3 3

4 2 2

3 2 2

5 10 9

4 8 7

64000

62000

60000

58000

56000

54000

52000

50000

AOM-1502-003

48000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 19

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 19000 AND 20000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

-20 lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

978 39 8 945 37 7 913 36 7 882 35 7 852 34 7 822 32 6 794 31 6 766 30 6 739 29 6 713 28 6

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

19000 ft ISA + °C -10 0

10

20

1024 1070 1124 1299 40 42 44 57 8 8 8 10 990 1034 1086 1252 39 40 42 55 8 8 8 10 956 999 1050 1207 37 39 41 53 7 8 8 10 924 965 1014 1163 36 38 39 51 7 7 7 9 892 932 979 1121 35 36 38 49 7 7 7 9 862 900 946 1080 34 35 37 47 7 7 7 9 832 869 913 1040 32 34 35 45 6 7 7 8 803 838 881 1002 31 33 34 43 6 6 6 8 774 809 850 965 30 31 33 42 6 6 6 8 747 780 819 929 29 30 32 40 6 6 6 7 4 2 2

4 2 2

7 12 10

6 11 9

-20

20000 ft ISA + °C -10 0

10

20

1039 1089 1137 1194 1385 42 44 46 48 62 8 8 9 9 11 1004 1052 1099 1154 1335 41 42 44 46 60 8 8 8 9 11 970 1016 1061 1115 1286 39 41 43 45 58 8 8 8 8 10 937 981 1025 1077 1239 38 40 41 43 55 7 8 8 8 10 905 948 990 1040 1194 37 38 40 41 53 7 7 8 8 10 873 915 956 1003 1150 35 37 38 40 51 7 7 7 7 9 843 883 922 968 1107 34 35 37 39 49 7 7 7 7 9 813 852 890 934 1066 33 34 36 37 47 6 7 7 7 9 784 821 858 901 1027 32 33 34 36 46 6 6 7 7 8 756 792 827 868 988 30 32 33 34 44 6 6 6 6 8 4 3 3

4 2 2

4 2 2

7 12 11

7 12 10

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 20

Climb

REVISION 21

AOM-1502-003

WEIGHT (lb)

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 19000 AND 20000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

19000 ft ISA + °C -10 0

10

20

-20

20000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

687 27 5 663 26 5 638 25 5 614 24 5 591 23 5 568 22 4 545 21 4 522 20 4 500 19 4

720 28 6 694 27 5 669 26 5 644 25 5 619 24 5 595 23 5 571 22 4 547 21 4 524 20 4

752 29 6 725 28 5 698 27 5 672 26 5 647 25 5 621 24 5 596 23 4 571 22 4 547 21 4

790 31 6 762 29 6 734 28 5 706 27 5 679 26 5 652 25 5 626 24 5 600 23 4 574 22 4

895 39 7 862 37 7 829 36 7 798 34 6 766 33 6 736 32 6 706 30 6 676 29 5 647 28 5

728 29 6 702 28 6 676 27 5 651 26 5 626 25 5 601 24 5 577 23 5 553 22 4 529 21 4

763 31 6 735 29 6 708 28 6 682 27 5 655 26 5 630 25 5 604 24 5 579 23 5 554 22 4

797 32 6 768 31 6 740 29 6 712 28 5 685 27 5 658 26 5 631 25 5 605 24 5 579 23 4

837 33 6 807 32 6 777 31 6 748 30 6 719 28 5 691 27 5 663 26 5 635 25 5 608 24 5

951 42 8 915 41 7 881 39 7 847 38 7 814 36 7 781 35 6 749 33 6 717 32 6 686 30 6

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 2 2

3 2 2

6 10 9

5 9 8

4 3 3

4 2 2

4 2 2

6 11 10

6 10 9

64000

62000

60000

58000

56000

54000

52000

50000

AOM-1502-003

48000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 21

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 21000 AND 22000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

-20

21000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1102 46 9 1065 44 9 1028 43 8 993 41 8 958 40 8 925 38 7 892 37 7 861 36 7 830 34 7 800 33 6

1154 48 9 1115 46 9 1077 45 8 1040 43 8 1004 42 8 969 40 8 935 39 7 902 37 7 869 36 7 838 35 7

1206 50 9 1165 48 9 1125 46 9 1086 45 8 1049 43 8 1012 42 8 976 40 8 942 39 7 908 37 7 875 36 7

1266 52 10 1223 50 9 1181 49 9 1140 47 9 1101 45 8 1062 44 8 1025 42 8 989 40 7 953 39 7 918 37 7

1474 68 12 1420 65 12 1368 63 11 1318 61 11 1269 58 10 1222 56 10 1176 54 10 1132 52 9 1089 50 9 1048 48 9

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 2 2

4 2 2

8 13 12

8 13 12

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

-20

22000 ft ISA + °C -10 0

10

20

1168 1223 1277 1341 1568 50 52 54 57 74 10 10 10 10 13 1128 1181 1234 1295 1510 49 51 53 55 72 9 9 10 10 13 1089 1141 1191 1250 1454 47 49 51 53 69 9 9 9 10 12 1051 1101 1150 1207 1400 45 47 49 51 66 9 9 9 9 12 1014 1063 1110 1165 1348 44 45 47 49 64 8 8 9 9 11 979 1025 1071 1124 1297 42 44 45 47 61 8 8 8 9 11 944 989 1033 1084 1248 40 42 44 46 59 8 8 8 8 10 910 953 996 1045 1201 39 41 42 44 57 7 8 8 8 10 877 919 960 1007 1155 37 39 41 42 54 7 7 7 8 10 845 885 925 970 1111 36 38 39 41 52 7 7 7 7 9 4 3 3

4 2 2

4 2 2

8 13 12

9 15 13

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 22

Climb

REVISION 21

AOM-1502-003

WEIGHT (lb)

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 21000 AND 22000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

21000 ft ISA + °C -10 0

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

770 32 6 742 31 6 714 30 6 687 28 6 661 27 5 635 26 5 609 25 5 584 24 5 559 23 5

807 33 6 777 32 6 748 31 6 720 30 6 692 28 5 665 27 5 638 26 5 612 25 5 586 24 5

843 35 6 812 33 6 781 32 6 752 31 6 723 30 6 695 28 5 667 27 5 639 26 5 612 25 5

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 2 2

4 2 2

64000

62000

60000

58000

56000

54000

52000

50000

AOM-1502-003

48000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

20

-20

22000 ft ISA + °C -10 0

885 1008 36 46 7 8 852 970 35 44 6 8 820 932 33 42 6 8 789 896 32 41 6 7 759 861 31 39 6 7 729 827 30 38 5 7 700 793 28 36 5 6 671 759 27 34 5 6 642 726 26 33 5 6

814 35 7 783 33 6 754 32 6 725 31 6 697 30 6 670 28 5 642 27 5 616 26 5 589 25 5

853 36 7 821 35 7 790 33 6 760 32 6 730 31 6 701 30 6 673 28 5 645 27 5 617 26 5

890 38 7 857 36 7 825 35 6 793 33 6 763 32 6 733 31 6 703 30 5 674 28 5 645 27 5

4 3 3

4 2 2

4 2 2

10

6 11 10

6 11 9

10

20

935 1068 39 50 7 9 900 1027 38 48 7 9 866 987 36 46 7 8 833 948 35 44 6 8 801 911 33 43 6 8 769 874 32 41 6 7 738 838 31 39 6 7 707 803 29 37 5 7 677 768 28 36 5 6 7 12 11

7 12 11

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 23

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 23000 AND 24000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

23000 ft ISA + °C -10 0

24000 ft ISA + °C -10 0

10

20

-20

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1236 55 10 1194 53 10 1152 51 10 1112 49 9 1073 47 9 1035 46 9 998 44 8 962 42 8 927 41 8 892 39 7

1295 57 11 1251 55 10 1207 53 10 1165 51 9 1124 49 9 1084 48 9 1045 46 8 1008 44 8 971 42 8 935 41 8

1352 59 11 1306 57 10 1261 55 10 1217 53 10 1174 51 9 1132 49 9 1092 48 9 1052 46 8 1014 44 8 977 42 8

1419 62 11 1370 60 11 1323 58 10 1277 56 10 1232 54 10 1188 52 9 1146 50 9 1104 48 9 1064 46 8 1025 44 8

1668 82 14 1606 78 14 1545 75 13 1487 72 13 1431 70 12 1377 67 12 1325 64 11 1274 62 11 1225 59 10 1177 57 10

1310 60 11 1264 58 11 1219 56 10 1176 54 10 1135 52 10 1094 50 9 1054 48 9 1016 46 9 978 44 8 942 43 8

1372 62 11 1324 60 11 1277 58 11 1232 56 10 1189 54 10 1146 52 9 1105 50 9 1064 48 9 1025 46 8 987 44 8

1433 65 12 1382 63 11 1334 60 11 1287 58 10 1241 56 10 1197 54 10 1154 52 9 1112 50 9 1071 48 9 1031 46 8

1503 68 12 1450 65 11 1399 63 11 1350 61 11 1302 58 10 1256 56 10 1210 54 9 1166 52 9 1123 50 9 1081 48 8

1776 90 15 1708 86 15 1643 83 14 1581 79 14 1520 76 13 1462 73 12 1406 70 12 1351 67 12 1299 65 11 1248 62 11

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 3 2

4 2 2

9 14 13

10 17 15

5 3 3

4 3 3

4 3 2

9 15 14

12 19 17

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 24

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 23000 AND 24000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

23000 ft ISA + °C -10 0

10

20

-20

24000 ft ISA + °C -10 0

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

859 38 7 827 36 7 795 35 7 764 33 6 734 32 6 705 31 6 677 30 6 649 28 5 621 27 5

900 39 7 866 38 7 833 36 7 801 35 6 770 33 6 739 32 6 709 31 6 680 29 5 650 28 5

940 41 7 905 39 7 870 38 7 836 36 7 804 35 6 772 33 6 741 32 6 710 31 6 679 29 5

986 43 8 949 41 7 913 39 7 878 38 7 843 36 6 810 35 6 777 33 6 745 32 6 713 31 5

1132 55 10 1087 52 9 1044 50 9 1002 48 8 962 46 8 923 44 8 885 42 7 848 41 7 811 39 7

906 41 8 872 39 7 838 38 7 805 36 7 773 35 7 742 33 6 712 32 6 682 31 6 653 29 5

950 43 8 914 41 7 878 39 7 844 38 7 810 36 7 778 35 6 746 33 6 715 32 6 684 30 6

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 2 2

4 2 2

7 13 11

8 14 12

4 3 3

4 2 2

64000

62000

60000

58000

56000

54000

52000

50000

AOM-1502-003

48000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

10

20

992 1041 1198 44 46 60 8 8 10 954 1001 1151 43 44 57 8 8 10 917 962 1104 41 43 55 7 8 9 882 925 1060 39 41 52 7 7 9 847 888 1016 38 39 50 7 7 9 813 853 975 36 38 48 7 7 8 780 818 934 35 36 46 6 6 8 747 784 895 33 35 44 6 6 8 715 750 856 32 33 42 6 6 7 4 2 2

8 13 12

9 15 13

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 25

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 25000 AND 26000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -19

25000 ft ISA + °C -10 0

26000 ft ISA + °C -10 0

10

20

-18

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1395 66 12 1345 63 12 1297 61 11 1250 59 11 1205 57 10 1162 54 10 1119 52 10 1078 50 9 1038 48 9 999 47 9

1454 68 12 1403 66 12 1352 63 11 1304 61 11 1257 59 11 1212 57 10 1167 54 10 1124 52 9 1082 50 9 1042 48 9

1519 71 12 1465 68 12 1412 66 12 1362 63 11 1313 61 11 1265 59 10 1219 57 10 1174 54 10 1131 52 9 1088 50 9

1593 74 13 1536 71 12 1481 69 12 1428 66 11 1377 64 11 1327 61 11 1279 59 10 1232 57 10 1186 54 9 1141 52 9

1896 99 17 1822 95 16 1750 91 15 1682 87 15 1617 84 14 1554 80 13 1493 77 13 1434 74 12 1378 71 12 1323 68 11

1474 72 13 1420 69 12 1368 66 12 1319 64 11 1270 61 11 1224 59 11 1178 57 10 1135 54 10 1092 52 9 1050 50 9

1529 74 13 1474 71 13 1420 68 12 1369 66 12 1319 63 11 1270 61 11 1223 59 10 1178 56 10 1133 54 10 1090 52 9

1597 77 13 1539 74 13 1484 71 12 1430 68 12 1377 66 11 1327 63 11 1278 61 11 1230 59 10 1184 56 10 1139 54 9

1675 80 14 1614 77 13 1555 74 13 1499 71 12 1444 69 12 1391 66 11 1340 63 11 1290 61 10 1242 59 10 1194 56 10

2008 108 18 1928 103 17 1850 99 16 1776 95 16 1706 91 15 1638 87 14 1573 83 14 1510 80 13 1450 77 13 1391 73 12

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

5 4 3

4 3 3

4 3 3

10 17 15

14 22 19

5 4 3

4 3 3

4 3 3

11 18 17

16 26 23

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 26

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 25000 AND 26000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -19 lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

961 45 8 923 43 8 887 41 8 852 40 7 818 38 7 785 36 7 752 35 6 721 33 6 690 32 6

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

64000

62000

60000

58000

56000

54000

52000

50000

AOM-1502-003

48000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

25000 ft ISA + °C -10 0

10

20

1002 1047 1098 1270 46 48 50 65 8 9 9 11 963 1006 1055 1218 45 46 48 62 8 8 8 11 926 967 1014 1169 43 44 46 60 8 8 8 10 889 929 974 1121 41 43 44 57 7 8 8 10 853 892 935 1074 39 41 43 55 7 7 7 9 819 855 897 1029 38 39 41 52 7 7 7 9 785 820 860 986 36 38 39 50 7 7 7 8 752 786 824 944 35 36 37 48 6 6 7 8 720 752 789 902 33 34 36 46 6 6 6 8 4 2 2

4 2 2

8 14 13

10 17 15

-18

26000 ft ISA + °C -10 0

10

20

1010 1048 1095 1148 1334 48 50 52 54 70 9 9 9 9 12 970 1007 1053 1104 1280 46 48 50 52 67 8 9 9 9 11 932 968 1011 1060 1227 44 46 48 50 64 8 8 8 9 11 895 929 971 1018 1176 43 44 46 48 62 8 8 8 8 10 859 891 931 977 1126 41 42 44 46 59 7 8 8 8 10 823 855 893 937 1078 39 40 42 44 56 7 7 7 8 9 789 819 856 898 1032 37 39 40 42 54 7 7 7 7 9 755 784 820 860 987 36 37 38 40 51 6 7 7 7 9 723 750 784 822 944 34 35 37 38 49 6 6 6 7 8 4 3 3

4 3 2

4 3 2

9 15 14

11 19 17

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 27

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 27000 AND 28000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -17

27000 ft ISA + °C -10 0

28000 ft ISA + °C -10 0

10

20

-16

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1546 77 14 1489 74 13 1434 71 13 1381 68 12 1330 66 12 1280 63 11 1232 61 11 1186 58 10 1141 56 10 1097 54 10

1597 79 14 1539 76 13 1482 73 13 1427 70 12 1374 68 12 1323 65 11 1273 62 11 1226 60 10 1179 58 10 1134 55 10

1669 82 14 1607 79 14 1548 76 13 1491 73 13 1436 70 12 1382 68 12 1331 65 11 1280 62 11 1232 60 10 1185 58 10

1749 86 14 1685 82 14 1623 79 13 1563 76 13 1505 73 12 1449 70 12 1395 68 11 1342 65 11 1291 62 11 1242 60 10

2110 116 19 2023 111 18 1941 106 17 1861 102 17 1786 97 16 1714 93 15 1644 89 15 1578 86 14 1513 82 13 1452 78 13

1621 83 14 1560 79 14 1502 76 13 1445 73 13 1391 70 12 1339 67 12 1288 65 11 1239 62 11 1191 60 10 1145 57 10

1667 85 15 1605 81 14 1545 78 13 1487 75 13 1431 72 12 1377 69 12 1324 66 12 1274 64 11 1225 61 11 1177 59 10

1741 88 15 1676 85 14 1614 81 14 1553 78 13 1495 75 13 1439 72 12 1384 69 12 1331 66 11 1280 64 11 1230 61 10

1825 92 15 1757 88 15 1691 85 14 1628 81 14 1567 78 13 1508 75 12 1451 72 12 1395 69 12 1342 66 11 1290 64 11

2214 125 20 2120 120 19 2032 114 18 1947 109 18 1867 104 17 1790 100 16 1716 95 15 1645 91 15 1577 87 14 1512 84 14

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

5 4 3

5 3 3

4 3 3

12 20 18

18 29 26

5 4 4

5 3 3

5 3 3

13 21 19

20 33 29

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 28

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 27000 AND 28000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -17 lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1054 52 9 1013 49 9 973 47 8 933 45 8 895 43 8 858 42 7 822 40 7 787 38 7 752 36 7

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

64000

62000

60000

58000

56000

54000

52000

50000

AOM-1502-003

48000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

27000 ft ISA + °C -10 0

10

20

1090 1139 1194 1392 53 55 57 75 9 10 10 12 1047 1094 1147 1334 51 53 55 72 9 9 9 12 1005 1050 1101 1278 49 51 53 69 9 9 9 11 965 1008 1057 1224 47 49 51 66 8 8 9 11 925 967 1014 1172 45 47 48 63 8 8 8 10 887 927 972 1122 43 45 46 60 8 8 8 10 850 888 931 1073 41 43 44 57 7 7 8 9 813 850 891 1026 39 41 42 55 7 7 7 9 778 813 852 980 37 39 41 52 7 7 7 9 4 3 3

4 3 2

10 16 15

12 21 18

-16

28000 ft ISA + °C -10 0

10

20

1100 1131 1182 1239 1449 55 56 59 61 80 10 10 10 10 13 1056 1086 1135 1190 1388 53 54 56 59 76 9 9 10 10 12 1014 1043 1090 1143 1329 50 52 54 56 73 9 9 9 9 12 973 1000 1046 1096 1273 48 50 52 54 70 9 9 9 9 11 932 959 1003 1051 1218 46 47 49 51 67 8 8 8 9 11 893 919 961 1007 1165 44 45 47 49 64 8 8 8 8 10 855 880 920 964 1114 42 43 45 47 61 7 8 8 8 10 819 842 880 923 1064 40 41 43 45 58 7 7 7 8 10 782 805 841 882 1016 39 40 41 43 55 7 7 7 7 9 4 3 3

4 3 3

4 3 2

10 17 16

13 23 20

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 29

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 29000 AND 30000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -15

29000 ft ISA + °C -10 0

30000 ft ISA + °C -10 0

10

20

-14

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1700 89 15 1634 85 15 1572 82 14 1512 78 14 1454 75 13 1398 72 13 1345 69 12 1293 66 12 1242 64 11 1193 61 11

1740 91 15 1673 87 15 1609 83 14 1547 80 14 1488 77 13 1431 74 13 1376 71 12 1323 68 12 1272 65 11 1222 62 11

1818 94 16 1748 90 15 1681 87 15 1617 83 14 1556 80 13 1496 77 13 1439 74 12 1383 71 12 1329 68 11 1277 65 11

1905 98 16 1831 94 15 1762 90 15 1695 87 14 1630 83 14 1568 80 13 1508 77 13 1449 73 12 1393 70 12 1338 68 11

2322 135 21 2220 128 20 2125 122 20 2035 117 19 1949 112 18 1867 107 17 1789 102 16 1714 97 16 1642 93 15 1572 89 14

1784 95 16 1713 91 16 1645 87 15 1581 84 14 1519 80 14 1460 77 13 1403 74 13 1348 71 12 1295 68 12 1243 65 11

1818 97 16 1745 93 16 1676 89 15 1610 85 14 1548 82 14 1488 78 13 1430 75 13 1373 72 12 1319 69 12 1267 66 11

1899 101 17 1824 97 16 1752 93 15 1683 89 15 1618 85 14 1555 82 14 1494 78 13 1436 75 13 1379 72 12 1324 69 12

1989 105 17 1910 101 16 1835 96 16 1763 92 15 1695 89 14 1629 85 14 1566 81 13 1505 78 13 1445 75 12 1388 72 12

2439 145 23 2327 138 22 2223 131 21 2125 125 20 2033 119 19 1946 114 18 1863 109 17 1784 104 17 1707 99 16 1634 94 15

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

5 4 4

5 4 3

5 3 3

14 23 21

23 37 33

5 4 4

5 4 4

5 3 3

16 26 23

25 40 35

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 30

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 29000 AND 30000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -15 lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1146 59 10 1100 56 10 1056 54 9 1012 51 9 970 49 9 929 47 8 889 45 8 851 43 8 813 41 7

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

5 3 3

64000

62000

60000

58000

56000

54000

52000

50000

AOM-1502-003

48000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

29000 ft ISA + °C -10 0

10

20

1173 1226 1286 1506 60 62 65 85 10 11 11 14 1126 1177 1234 1442 57 60 62 81 10 10 10 13 1081 1130 1184 1380 55 57 59 77 9 10 10 13 1036 1083 1136 1321 52 55 57 74 9 9 9 12 993 1038 1089 1263 50 52 54 71 9 9 9 11 951 995 1043 1208 48 50 52 67 8 8 9 11 911 952 998 1154 46 48 50 64 8 8 8 10 871 911 955 1102 44 46 47 61 8 8 8 10 832 870 912 1052 42 43 45 58 7 7 8 10 4 3 3

4 3 3

11 18 17

15 25 22

-14

30000 ft ISA + °C -10 0

10

20

1193 1216 1271 1332 1564 62 63 66 69 90 11 11 11 11 14 1145 1167 1220 1279 1497 60 61 63 66 86 10 10 11 11 14 1098 1119 1170 1226 1432 57 58 60 63 82 10 10 10 10 13 1053 1073 1122 1176 1370 55 55 58 60 78 9 10 10 10 13 1009 1028 1075 1126 1309 52 53 55 58 75 9 9 9 10 12 966 984 1029 1079 1251 50 51 53 55 71 9 9 9 9 11 924 941 984 1032 1195 48 48 50 53 68 8 8 9 9 11 883 900 941 987 1141 45 46 48 50 65 8 8 8 8 10 844 860 899 942 1088 43 44 46 48 62 8 8 8 8 10 5 3 3

5 3 3

4 3 3

11 19 18

16 27 24

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 31

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 31000 AND 32000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -13

31000 ft ISA + °C -10 0

32000 ft ISA + °C -10 0

10

20

-12

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1875 103 17 1797 98 17 1723 94 16 1653 90 15 1587 86 15 1524 82 14 1463 79 13 1405 76 13 1349 72 12 1294 69 12

1901 104 17 1822 100 17 1748 95 16 1677 91 15 1609 87 15 1545 83 14 1484 80 14 1425 76 13 1368 73 12 1313 70 12

1987 109 18 1905 104 17 1827 99 16 1753 95 16 1683 91 15 1616 87 14 1552 83 14 1490 80 13 1430 76 13 1373 73 12

2081 113 18 1995 108 17 1913 103 17 1836 99 16 1763 94 15 1693 90 15 1626 87 14 1561 83 13 1499 79 13 1439 76 12

2567 157 25 2443 149 23 2328 141 22 2221 134 21 2121 127 20 2028 121 19 1939 116 18 1855 110 17 1774 105 17 1697 100 16

1974 112 19 1888 106 18 1808 101 17 1732 97 16 1660 92 16 1591 88 15 1526 84 14 1464 81 14 1405 77 13 1347 74 12

1993 112 19 1906 107 18 1825 102 17 1748 97 16 1675 93 16 1606 89 15 1541 85 14 1478 81 14 1418 78 13 1360 74 13

2083 117 19 1992 111 18 1908 106 17 1827 101 17 1752 97 16 1680 92 15 1611 88 15 1546 85 14 1483 81 13 1422 77 13

2181 122 19 2086 116 19 1998 111 18 1914 105 17 1835 101 16 1760 96 16 1688 92 15 1620 88 14 1554 84 14 1491 81 13

2710 171 27 2570 161 25 2443 152 24 2325 144 22 2216 136 21 2114 130 20 2018 123 19 1929 117 18 1843 112 18 1762 106 17

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

5 4 4

5 4 4

5 4 3

17 28 26

25 40 36

5 4 4

5 4 4

5 3 3

16 26 24

23 37 34

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 32

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 31000 AND 32000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -13

32000 ft ISA + °C -10 0

10

20

-12

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1242 66 11 1191 63 11 1142 61 10 1094 58 10 1048 55 10 1003 53 9 959 50 9 916 48 8 875 46 8

1259 67 11 1208 64 11 1158 61 10 1109 59 10 1063 56 10 1017 54 9 973 51 9 929 49 8 887 46 8

1317 70 12 1263 67 11 1211 64 11 1160 61 10 1111 58 10 1064 56 9 1017 53 9 972 51 9 928 48 8

1380 73 12 1324 70 11 1269 67 11 1216 64 10 1165 61 10 1115 58 10 1066 55 9 1019 53 9 973 50 8

1623 96 15 1552 91 15 1484 87 14 1419 83 13 1356 79 13 1295 75 12 1236 72 11 1179 68 11 1125 65 10

1292 70 12 1238 67 11 1186 64 11 1136 61 10 1087 59 10 1040 56 10 995 53 9 950 51 9 907 49 8

1304 71 12 1250 68 11 1198 65 11 1147 62 11 1098 59 10 1050 57 10 1004 54 9 959 51 9 915 49 8

1364 74 12 1307 71 12 1253 68 11 1200 65 11 1148 62 10 1099 59 10 1050 56 9 1003 54 9 958 51 9

1429 77 13 1370 74 12 1313 70 11 1257 67 11 1204 64 10 1151 61 10 1101 59 10 1052 56 9 1004 53 9

1684 101 16 1609 97 15 1537 92 15 1468 88 14 1402 84 13 1339 80 13 1277 76 12 1218 72 11 1161 68 11

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

5 3 3

5 3 3

4 3 3

12 21 19

17 29 26

4 3 3

4 3 3

4 3 3

12 19 18

17 28 25

64000

62000

60000

58000

56000

54000

52000

50000

48000

AOM-1502-003

31000 ft ISA + °C -10 0

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 33

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 33000 AND 34000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -11

33000 ft ISA + °C -10 0

34000 ft ISA + °C -5 0

10

20

-10

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

2083 121 20 1989 115 19 1900 109 18 1816 104 17 1738 99 17 1664 94 16 1593 90 15 1527 86 14 1463 82 14 1402 78 13

2093 122 20 1998 116 19 1909 110 18 1825 104 17 1746 99 17 1671 95 16 1601 90 15 1534 86 14 1470 82 14 1409 79 13

2188 127 21 2089 120 20 1996 114 19 1908 109 18 1826 104 17 1748 99 16 1674 94 15 1604 90 15 1538 86 14 1474 82 13

2291 132 21 2187 125 20 2090 119 19 1999 113 18 1913 108 17 1831 103 16 1754 98 16 1681 94 15 1611 90 14 1544 86 14

2872 187 29 2715 175 27 2571 165 25 2440 155 24 2319 147 23 2207 139 22 2103 132 21 2006 125 20 1914 119 19 1828 113 18

2204 132 22 2099 125 21 2001 119 20 1909 112 19 1823 107 18 1742 102 17 1666 97 16 1593 92 15 1525 88 15 1459 84 14

2255 135 22 2147 128 21 2047 121 20 1953 115 19 1865 109 18 1782 104 17 1704 99 16 1630 94 15 1560 90 15 1493 85 14

2305 138 22 2196 130 21 2094 124 20 1998 117 19 1907 111 18 1823 106 17 1743 101 16 1667 96 16 1595 91 15 1527 87 14

2414 144 23 2300 136 21 2193 129 20 2093 122 19 1998 116 18 1910 110 18 1826 105 17 1747 100 16 1672 95 15 1600 91 15

3058 206 31 2878 192 29 2716 180 28 2568 168 26 2433 158 24 2310 149 23 2196 141 22 2089 134 21 1990 127 20 1897 120 19

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

5 4 3

5 3 3

4 3 3

15 24 22

22 34 31

4 3 3

4 3 3

4 3 3

15 22 20

21 31 29

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 34

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 33000 AND 34000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -11

34000 ft ISA + °C -5 0

10

20

-10

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1344 75 13 1287 72 12 1232 68 12 1179 65 11 1128 62 11 1079 59 10 1031 57 10 984 54 9 939 51 9

1350 75 13 1293 72 12 1238 69 12 1185 66 11 1134 63 11 1084 60 10 1036 57 10 989 54 9 944 52 9

1412 78 13 1353 75 12 1295 72 12 1240 68 11 1186 65 11 1134 62 10 1084 59 10 1035 56 9 987 54 9

1480 82 13 1418 78 13 1358 75 12 1299 71 12 1243 68 11 1189 65 11 1136 62 10 1085 59 10 1035 56 9

1746 108 17 1667 102 16 1591 97 15 1519 93 15 1450 88 14 1383 84 13 1319 80 13 1257 76 12 1198 72 11

1397 80 13 1337 76 13 1280 73 12 1224 69 12 1171 66 11 1119 63 11 1068 60 10 1020 57 10 972 54 9

1429 81 13 1368 78 13 1309 74 12 1253 71 12 1198 67 11 1145 64 11 1093 61 10 1043 58 10 995 55 9

1462 83 14 1400 79 13 1339 76 12 1281 72 12 1225 69 11 1171 66 11 1118 63 10 1067 60 10 1018 57 9

1532 87 14 1467 83 13 1404 79 13 1343 75 12 1284 72 12 1227 68 11 1172 65 11 1119 62 10 1067 59 10

1810 114 18 1727 109 17 1647 103 16 1571 98 15 1498 93 15 1428 89 14 1361 84 13 1297 80 13 1235 76 12

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 3 3

4 3 2

11 18 17

16 26 24

4 3 3

4 2 2

4 2 2

11 17 16

15 24 22

64000

62000

60000

58000

56000

54000

52000

50000

48000

AOM-1502-003

33000 ft ISA + °C -10 0

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 35

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 35000 AND 36000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -9

35000 ft ISA + °C -5 0

36000 ft ISA + °C -5 0

10

20

-8

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

2344 146 24 2222 137 22 2112 129 21 2011 122 20 1916 116 19 1827 110 18 1744 104 17 1665 99 16 1591 94 16 1520 89 15

2387 148 24 2264 139 23 2152 131 21 2048 124 20 1952 118 19 1861 111 18 1776 106 17 1696 100 16 1620 96 16 1549 91 15

2442 151 24 2316 142 23 2201 134 22 2095 127 20 1997 120 19 1904 114 18 1817 108 17 1735 103 17 1658 98 16 1584 93 15

2558 158 25 2426 148 23 2306 140 22 2196 132 21 2093 125 20 1995 119 19 1904 113 18 1819 107 17 1737 102 16 1661 97 15

3066 212 32 2879 197 30 2713 184 28 2562 172 26 2423 161 25 2297 152 23 2180 143 22 2072 135 21 1971 128 20

2371 152 25 2241 142 23 2124 133 22 2019 126 20 1921 119 19 1829 112 18 1743 106 17 1662 101 17 1586 96 16

2404 154 25 2272 144 23 2154 135 22 2047 127 21 1948 120 19 1855 114 18 1768 108 18 1686 102 17 1608 97 16

2460 157 25 2325 147 23 2204 138 22 2095 130 21 1993 123 20 1898 116 19 1809 110 18 1725 104 17 1645 99 16

2747 177 28 2579 164 26 2438 153 24 2311 144 23 2196 136 21 2090 128 20 1990 121 19 1896 115 18 1808 109 17 1725 103 16

3075 219 33 2877 202 31 2705 188 29 2551 176 27 2410 164 25 2280 154 24 2161 145 22 2051 137 21

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 3 2

4 2 2

14 20 18

20 28 26

4 2 2

4 2 2

4 2 2

12 17 16

18 25 24

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 36

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 35000 AND 36000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -9

36000 ft ISA + °C -5 0

10

20

-8

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1454 85 14 1390 81 13 1329 77 13 1270 74 12 1214 70 12 1159 67 11 1107 63 11 1056 60 10 1006 57 10

1480 87 14 1416 82 14 1354 79 13 1294 75 12 1236 71 12 1181 68 11 1127 65 11 1075 61 10 1025 58 10

1514 88 14 1448 84 14 1385 80 13 1324 76 12 1265 73 12 1208 69 11 1153 66 11 1100 63 10 1048 60 10

1588 92 15 1518 88 14 1452 84 13 1388 80 13 1326 76 12 1267 72 12 1209 69 11 1153 65 11 1099 62 10

1877 121 19 1788 115 18 1704 109 17 1624 104 16 1548 98 15 1475 93 15 1404 89 14 1337 84 13 1272 80 13

1514 91 15 1445 86 14 1380 82 14 1318 78 13 1259 74 12 1202 71 12 1146 67 11 1093 64 11 1041 61 10

1535 92 15 1466 88 14 1400 83 14 1337 79 13 1276 75 12 1218 72 12 1162 68 11 1108 65 11 1055 61 10

1571 94 15 1500 89 14 1432 85 14 1368 81 13 1306 77 13 1246 73 12 1189 70 11 1133 66 11 1080 63 10

1647 98 16 1572 93 15 1502 89 14 1434 84 13 1369 80 13 1307 76 12 1247 73 12 1189 69 11 1132 66 11

1949 129 20 1854 122 19 1764 116 18 1679 110 17 1599 104 16 1522 99 15 1448 94 15 1378 89 14 1310 84 13

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 2 2

4 2 2

4 2 2

10 16 15

15 23 21

4 2 2

4 2 2

4 2 2

10 15 14

14 21 20

64000

62000

60000

58000

56000

54000

52000

50000

48000

AOM-1502-003

35000 ft ISA + °C -5 0

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 37

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 37000 AND 38000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -8

37000 ft ISA + °C -5 0

38000 ft ISA + °C -5 0

10

20

-8

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

2262 148 24 2137 138 22 2024 130 21 1922 122 20 1827 115 19 1739 109 18 1655 103 17

2295 150 24 2167 140 23 2053 132 21 1949 124 20 1853 117 19 1763 110 18 1678 104 17

2349 153 24 2218 143 23 2101 134 21 1995 127 20 1897 120 19 1804 113 18 1717 107 17

2464 160 25 2327 150 23 2204 141 22 2093 132 21 1989 125 20 1892 118 19 1801 112 18

2712 194 29 2551 181 28 2405 169 26 2271 158 24 2148 148 23

2155 144 23 2034 135 22 1925 126 20 1826 119 19 1734 112 18

2186 146 23 2063 137 22 1953 128 21 1852 120 19 1759 113 18

2238 150 24 2112 140 22 1999 131 21 1896 123 20 1800 116 19

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 2 2

4 2 2

3 2 2

11 14 14

15 21 20

3 2 2

3 2 2

3 2 2

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

10

20

2348 157 24 2216 146 23 2097 2563 137 188 21 29 1989 2407 129 174 20 27 1888 2267 121 163 19 25 9 13 12

13 18 17

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 38

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 37000 AND 38000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -8

38000 ft ISA + °C -5 0

10

20

-8

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1577 98 16 1502 92 15 1432 88 14 1366 83 14 1303 79 13 1242 75 12 1184 71 12 1128 68 11 1074 64 11

1599 99 16 1524 94 15 1452 89 14 1385 84 14 1321 80 13 1260 76 12 1201 72 12 1144 69 11 1089 65 11

1636 101 16 1559 96 15 1486 91 15 1417 86 14 1352 82 13 1289 78 13 1229 74 12 1170 70 11 1114 66 11

1716 106 17 1635 100 16 1559 95 15 1486 90 14 1418 85 14 1352 81 13 1289 77 12 1228 73 12 1168 69 11

2035 139 21 1930 131 20 1833 124 19 1741 117 18 1656 111 17 1575 105 16 1497 99 15 1423 94 15 1352 89 14

1647 105 17 1566 100 16 1490 94 15 1418 89 15 1350 84 14 1286 80 13 1224 76 12 1165 72 12 1109 68 11

1671 107 17 1589 101 16 1511 95 15 1438 90 15 1369 85 14 1304 81 13 1242 77 13 1182 73 12 1124 69 11

1710 109 17 1626 103 17 1547 98 16 1472 92 15 1401 87 14 1334 83 13 1271 79 13 1209 74 12 1150 71 11

1794 114 18 1705 108 17 1622 102 16 1544 96 15 1470 91 14 1400 87 14 1333 82 13 1269 78 12 1207 74 12

2139 152 23 2021 142 22 1913 134 20 1813 126 19 1719 118 18 1632 112 17 1550 106 16 1472 100 15 1397 94 15

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 2 2

4 2 2

3 2 2

9 14 13

13 19 18

3 2 2

3 2 2

3 2 2

9 13 12

13 18 16

64000

62000

60000

58000

56000

54000

52000

50000

48000

AOM-1502-003

37000 ft ISA + °C -5 0

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 39

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 39000 AND 40000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -8 lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

2047 141 23 1930 131 21 1825 123 20

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 2

84000

82000

80000

78000

76000

74000

72000

70000

68000

66000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

39000 ft ISA + °C -5 0

10

20

2077 2127 2233 143 146 153 23 23 24 1958 2004 2104 133 136 142 21 22 22 1851 1895 1989 2422 124 127 133 183 20 20 21 28 3 2 2

3 1 1

9 11 11

-

-8

40000 ft ISA + °C -5 0

10

20

1938 1967 2016 2118 137 139 142 149 22 22 22 23

-

-

-

-

-

-

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 40

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 39000 AND 40000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -8

40000 ft ISA + °C -5 0

10

20

-8

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1729 115 19 1639 108 18 1555 102 17 1477 96 16 1403 91 15 1333 86 14 1267 81 13 1205 76 13 1145 72 12

1753 117 19 1662 110 18 1577 103 17 1498 97 16 1423 92 15 1352 87 14 1285 82 13 1222 78 13 1161 73 12

1795 119 19 1702 112 18 1614 106 17 1533 99 16 1456 94 15 1384 89 14 1315 84 13 1251 79 13 1188 75 12

1884 125 19 1786 117 18 1694 110 17 1608 104 16 1528 98 15 1452 93 15 1380 88 14 1312 83 13 1247 78 12

2270 169 26 2134 157 24 2010 146 22 1897 137 21 1793 128 20 1697 120 18 1608 113 17 1524 107 16 1445 101 15

1825 127 20 1724 119 19 1630 111 18 1543 104 17 1462 98 16 1386 92 15 1315 87 14 1247 82 13 1184 77 13

1852 129 21 1749 120 19 1654 113 18 1565 106 17 1483 99 16 1406 93 15 1333 88 14 1265 83 13 1201 78 13

1897 132 21 1791 123 20 1694 115 18 1603 108 17 1518 102 16 1439 96 15 1365 90 14 1295 85 14 1229 80 13

1993 139 21 1881 129 20 1778 121 19 1683 113 18 1594 106 17 1510 100 16 1432 94 15 1359 89 14 1290 84 13

2283 177 27 2135 163 25 2002 151 23 1883 140 21 1774 131 20 1675 122 19 1583 115 18 1498 108 17

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 2

3 2 2

3 2 2

8 11 11

12 15 14

3 2 2

3 2 2

3 1 1

8 10 10

10 14 13

64000

62000

60000

58000

56000

54000

52000

50000

48000

AOM-1502-003

39000 ft ISA + °C -5 0

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 41

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 41000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -8

41000 ft ISA + °C -5 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1951 144 23 1827 132 21 1718 123 20 1620 114 18 1530 107 17 1445 100 16 1367 94 15 1294 88 14 1225 83 13

1980 146 23 1854 134 21 1743 125 20 1644 116 19 1552 108 17 1466 101 16 1387 95 15 1313 89 14 1243 84 14

2031 150 24 1900 138 22 1786 128 20 1684 119 19 1590 111 18 1502 104 16 1420 97 15 1344 91 15 1273 86 14

2137 158 24 1998 145 22 1878 134 21 1770 125 19 1670 116 18 1577 109 17 1491 102 16 1411 96 15 1336 90 14

2137 170 26 1994 156 24 1867 144 22 1754 134 20 1651 125 19 1557 116 18

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 1

3 1 1

3 1 1

7 10 9

9 12 11

64000

62000

60000

58000

56000

54000

52000

50000

48000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 42

Climb

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

CLIMB TABLES !EMBRAER 175 Models

The climb planning tables show fuel consumption, distance, and time elapsed from the Sea Level to the top of climb. Data are shown for various weights, ISA deviations and cruise altitudes. The takeoff fuel consumption is not considered in the following tables. Tables present the scheduled climb speed according to the autopilot climb mode, i.e.: – 240 KIAS for altitudes up to 10000 ft, increasing linearly to 290 KIAS at 12000 ft, maintaining 290 KIAS up to 25400 ft and 0.7 Mach above 25400 ft. The associated conditions are: Thrust Mode.............................................................. CLB1 Flaps.......................................................................... UP Gear........................................................................... UP Bleeds........................................................................ OPEN Anti-Ice...................................................................... OFF CG............................................................................. 18% Minimum Remaining Rate of Climb.......................... 300 ft/min

EXAMPLE:

AOM-1502-003

Given: Departure Airport Elevation....................................... 3500 ft Takeoff weight............................................................ 78000 lb ISA Condition Cruise Altitude.................................... 33000 ft

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 43

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

RESULTS: Data for 5000 ft (3500 ft + 1500 ft above departure airport) obtained from the climb table: Fuel: 217 lb Distance: 6 NM Time: 1 min Data provided from the Sea Level to 33000 ft (Top of Climb) table: Fuel: 1948 lb Distance: 112 NM Time: 18 min The fuel, distance and time spent during the climb phase (from 5000 ft to 33000 ft) are: Fuel: 1948 – 217 = 1731 lb Distance: 112 – 6 = 106 NM Time: 18 – 1 = 17 min

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 44

Climb

REVISION 21

AOM-1502-003

The fuel consumption related to the takeoff phase is provided on the Section 1-06-07.

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 5000 AND 6000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

5000 ft ISA + °C -10 0

10

20

-20

6000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

222 6 1 215 6 1 208 6 1 202 5 1 195 5 1 189 5 1 183 5 1 177 5 1 171 5 1 165 4 1

232 6 2 225 6 1 218 6 1 211 6 1 204 5 1 198 5 1 191 5 1 185 5 1 179 5 1 172 5 1

243 6 2 235 6 2 228 6 1 221 6 1 214 6 1 207 5 1 200 5 1 194 5 1 187 5 1 181 5 1

256 7 2 248 7 2 240 6 2 232 6 1 225 6 1 218 6 1 211 6 1 204 5 1 197 5 1 190 5 1

281 8 2 272 8 2 263 8 2 255 7 2 246 7 2 238 7 2 230 7 2 222 6 2 215 6 1 207 6 1

266 7 2 258 7 2 250 7 2 242 7 2 234 6 2 227 6 2 220 6 1 212 6 1 205 6 1 198 5 1

278 8 2 270 7 2 261 7 2 253 7 2 245 7 2 237 6 2 230 6 2 222 6 1 214 6 1 207 6 1

292 8 2 283 8 2 274 7 2 265 7 2 257 7 2 248 7 2 240 6 2 232 6 2 224 6 1 217 6 1

307 8 2 297 8 2 288 8 2 279 7 2 270 7 2 261 7 2 253 7 2 244 7 2 236 6 2 228 6 1

338 10 2 327 10 2 317 9 2 306 9 2 296 9 2 286 9 2 276 8 2 267 8 2 258 8 2 249 7 2

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 1 1

3 2 2

2 1 1

0 0 0

0 0 0

3 1 1

3 2 2

2 1 1

0 0 0

0 0 0

85000

83000

81000

79000

77000

75000

73000

71000

69000

AOM-1502-003

67000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 45

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 5000 AND 6000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

5000 ft ISA + °C -10 0

10

20

-20

6000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

159 4 1 154 4 1 148 4 1 143 4 1 137 4 1 132 3 1 127 3 1 122 3 1 117 3 1

166 4 1 161 4 1 155 4 1 149 4 1 144 4 1 138 4 1 133 3 1 127 3 1 122 3 1

174 5 1 168 4 1 162 4 1 156 4 1 150 4 1 145 4 1 139 4 1 133 3 1 128 3 1

183 5 1 177 5 1 170 4 1 164 4 1 158 4 1 152 4 1 146 4 1 140 4 1 134 3 1

200 6 1 192 6 1 185 5 1 178 5 1 172 5 1 165 5 1 158 5 1 152 4 1 145 4 1

191 5 1 184 5 1 178 5 1 171 5 1 165 4 1 158 4 1 152 4 1 146 4 1 140 4 1

200 5 1 193 5 1 186 5 1 179 5 1 172 5 1 166 4 1 159 4 1 153 4 1 146 4 1

209 6 1 202 5 1 194 5 1 187 5 1 180 5 1 173 5 1 166 4 1 160 4 1 153 4 1

220 6 1 212 6 1 204 5 1 197 5 1 190 5 1 182 5 1 175 5 1 168 4 1 161 4 1

240 7 2 231 7 2 222 7 2 214 6 1 206 6 1 198 6 1 190 6 1 182 5 1 174 5 1

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 1 1

3 1 1

2 1 1

0 0 0

0 0 0

3 1 1

3 1 1

2 1 1

0 0 0

0 0 0

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 46

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 7000 AND 8000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

7000 ft ISA + °C -10 0

10

20

-20

8000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

311 9 2 301 8 2 292 8 2 283 8 2 274 8 2 265 7 2 256 7 2 248 7 2 239 7 2 231 6 2

325 9 2 315 9 2 305 8 2 296 8 2 286 8 2 277 8 2 268 7 2 259 7 2 250 7 2 242 7 2

340 9 2 330 9 2 319 9 2 309 8 2 299 8 2 290 8 2 280 8 2 271 7 2 262 7 2 253 7 2

359 10 2 347 10 2 337 9 2 326 9 2 315 9 2 305 8 2 295 8 2 285 8 2 276 8 2 266 7 2

395 12 3 383 12 3 370 11 3 358 11 3 346 10 2 334 10 2 323 10 2 312 9 2 301 9 2 290 9 2

356 10 2 345 10 2 334 9 2 323 9 2 313 9 2 303 9 2 293 8 2 283 8 2 274 8 2 264 7 2

372 10 3 361 10 2 349 10 2 338 9 2 327 9 2 317 9 2 306 9 2 296 8 2 286 8 2 276 8 2

389 11 3 377 11 3 365 10 2 354 10 2 342 10 2 331 9 2 320 9 2 310 9 2 299 8 2 289 8 2

410 11 3 398 11 3 385 11 3 373 10 2 361 10 2 349 10 2 337 9 2 326 9 2 315 9 2 304 8 2

453 14 3 438 14 3 424 13 3 410 13 3 396 12 3 383 12 3 370 11 3 357 11 3 344 11 2 332 10 2

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 2

3 2 1

2 1 1

0 0 0

0 0 0

3 2 2

3 2 1

2 1 1

0 1 1

0 0 0

85000

83000

81000

79000

77000

75000

73000

71000

69000

AOM-1502-003

67000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 47

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 7000 AND 8000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

7000 ft ISA + °C -10 0

10

20

-20

8000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

223 6 2 215 6 1 207 6 1 200 5 1 192 5 1 185 5 1 177 5 1 170 5 1 163 4 1

233 6 2 225 6 2 217 6 1 209 6 1 201 5 1 193 5 1 185 5 1 178 5 1 170 5 1

244 7 2 235 6 2 227 6 1 218 6 1 210 6 1 202 5 1 194 5 1 186 5 1 178 5 1

257 7 2 248 7 2 239 6 2 230 6 1 221 6 1 213 6 1 204 5 1 196 5 1 187 5 1

280 8 2 270 8 2 260 8 2 250 8 2 240 7 2 231 7 2 222 7 2 212 6 1 203 6 1

255 7 2 246 7 2 237 7 2 228 6 2 219 6 2 211 6 1 203 6 1 194 5 1 186 5 1

267 7 2 257 7 2 248 7 2 239 7 2 230 6 2 221 6 1 212 6 1 203 6 1 195 5 1

279 8 2 269 7 2 259 7 2 249 7 2 240 7 2 231 6 2 222 6 1 212 6 1 203 6 1

293 8 2 283 8 2 273 8 2 263 7 2 253 7 2 243 7 2 233 6 2 224 6 1 214 6 1

320 10 2 308 9 2 297 9 2 286 9 2 275 8 2 264 8 2 253 8 2 243 7 2 232 7 2

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 1 1

3 1 1

2 1 1

0 0 0

0 0 0

3 2 1

3 1 1

2 1 1

0 1 1

0 0 0

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 48

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 9000 AND 10000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

9000 ft ISA + °C -10 0

10

20

-20

10000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

401 12 3 389 11 3 376 11 3 364 10 3 353 10 2 341 10 2 330 9 2 319 9 2 308 9 2 297 8 2

420 12 3 406 12 3 394 11 3 381 11 3 369 11 3 357 10 2 345 10 2 333 9 2 322 9 2 311 9 2

439 13 3 425 12 3 412 12 3 399 11 3 386 11 3 373 11 3 361 10 2 349 10 2 337 10 2 325 9 2

463 13 3 448 13 3 434 12 3 420 12 3 406 12 3 393 11 3 380 11 2 367 10 2 355 10 2 342 10 2

511 16 4 494 16 4 478 15 3 462 15 3 446 14 3 431 14 3 417 13 3 402 13 3 388 12 3 374 12 3

447 13 3 433 13 3 419 12 3 405 12 3 392 11 3 379 11 3 367 11 3 355 10 3 342 10 2 331 10 2

467 14 3 453 13 3 438 13 3 424 12 3 410 12 3 397 12 3 384 11 3 371 11 3 358 10 2 346 10 2

489 14 3 473 14 3 458 13 3 443 13 3 429 12 3 415 12 3 401 12 3 388 11 3 374 11 3 361 10 2

515 15 3 499 14 3 483 14 3 467 14 3 452 13 3 437 13 3 423 12 3 408 12 3 394 11 3 381 11 3

570 18 4 551 18 4 532 17 4 515 17 4 497 16 4 480 15 3 464 15 3 448 14 3 432 14 3 416 13 3

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 2

3 1 1

3 1 1

1 2 2

0 0 0

3 2 2

3 1 1

3 1 1

1 3 3

0 0 0

85000

83000

81000

79000

77000

75000

73000

71000

69000

AOM-1502-003

67000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 49

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 9000 AND 10000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

9000 ft ISA + °C -10 0

10

20

-20

10000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

287 8 2 277 8 2 267 8 2 257 7 2 247 7 2 237 7 2 228 6 2 219 6 2 209 6 1

300 9 2 289 8 2 279 8 2 268 8 2 258 7 2 248 7 2 238 7 2 229 6 2 219 6 2

314 9 2 302 9 2 291 8 2 281 8 2 270 8 2 259 7 2 249 7 2 239 7 2 229 6 2

330 9 2 319 9 2 307 9 2 296 8 2 284 8 2 273 8 2 262 7 2 252 7 2 241 7 2

361 11 3 347 11 2 334 10 2 322 10 2 309 10 2 297 9 2 285 9 2 273 9 2 261 8 2

319 9 2 307 9 2 296 9 2 285 8 2 274 8 2 264 8 2 253 7 2 243 7 2 233 7 2

334 10 2 322 9 2 310 9 2 298 9 2 287 8 2 276 8 2 265 8 2 254 7 2 243 7 2

349 10 2 336 10 2 324 9 2 312 9 2 300 9 2 288 8 2 277 8 2 265 8 2 254 7 2

367 11 2 354 10 2 341 10 2 329 9 2 316 9 2 304 9 2 292 8 2 280 8 2 268 8 2

401 13 3 386 12 3 372 12 3 358 11 3 344 11 2 330 11 2 317 10 2 304 10 2 291 9 2

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 2

3 1 1

2 1 1

1 2 2

0 0 0

3 2 2

3 1 1

3 1 1

1 3 2

0 0 0

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 50

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 11000 AND 12000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

11000 ft ISA + °C -10 0

10

20

-20

12000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

524 16 4 507 15 4 491 15 4 475 14 3 460 14 3 445 14 3 430 13 3 416 13 3 401 12 3 387 12 3

548 17 4 531 16 4 514 16 4 497 15 4 481 15 3 465 14 3 450 14 3 435 13 3 420 13 3 405 12 3

573 17 4 555 17 4 537 16 4 520 16 4 503 15 3 487 15 3 470 14 3 455 14 3 439 13 3 424 13 3

604 18 4 585 18 4 566 17 4 548 17 4 530 16 4 513 15 3 495 15 3 479 14 3 462 14 3 446 13 3

670 22 5 648 22 5 626 21 5 605 20 4 584 20 4 565 19 4 545 18 4 526 18 4 507 17 4 489 16 4

609 20 4 590 19 4 571 18 4 553 18 4 535 17 4 517 17 4 500 16 4 483 15 4 467 15 3 451 14 3

638 20 5 617 20 4 598 19 4 579 18 4 560 18 4 541 17 4 523 17 4 506 16 4 489 16 4 472 15 3

666 21 5 645 21 5 625 20 4 604 19 4 585 19 4 566 18 4 547 17 4 529 17 4 510 16 4 493 16 3

702 22 5 679 22 5 658 21 5 636 20 4 616 20 4 595 19 4 576 18 4 556 18 4 537 17 4 519 16 4

784 28 6 758 27 6 733 26 5 708 25 5 684 24 5 661 23 5 638 23 5 616 22 5 594 21 4 573 20 4

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 2

3 1 1

3 1 1

2 4 4

0 0 0

4 2 2

3 2 2

3 2 1

3 6 5

0 0 0

85000

83000

81000

79000

77000

75000

73000

71000

69000

AOM-1502-003

67000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 51

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 11000 AND 12000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

11000 ft ISA + °C -10 0

10

20

-20

12000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

374 11 3 360 11 3 347 11 3 334 10 2 322 10 2 309 9 2 297 9 2 284 9 2 272 8 2

391 12 3 377 11 3 363 11 3 350 11 2 336 10 2 323 10 2 310 9 2 298 9 2 285 9 2

409 12 3 394 12 3 380 11 3 365 11 3 352 11 2 338 10 2 324 10 2 311 9 2 298 9 2

430 13 3 415 12 3 400 12 3 385 12 3 370 11 3 356 11 2 341 10 2 327 10 2 313 9 2

471 16 3 454 15 3 437 15 3 420 14 3 404 13 3 388 13 3 372 12 3 357 12 3 341 11 3

435 14 3 419 13 3 404 13 3 389 12 3 374 12 3 360 11 3 345 11 3 331 11 2 317 10 2

455 14 3 439 14 3 423 13 3 407 13 3 392 12 3 376 12 3 361 11 3 346 11 2 332 10 2

475 15 3 458 15 3 442 14 3 425 13 3 409 13 3 393 12 3 377 12 3 362 11 3 347 11 2

500 16 3 482 15 3 465 15 3 447 14 3 430 14 3 414 13 3 397 12 3 381 12 3 365 11 3

552 19 4 531 19 4 512 18 4 492 17 4 473 17 4 454 16 3 436 15 3 418 15 3 400 14 3

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 2

3 1 1

3 1 1

2 4 4

0 0 0

3 2 2

3 1 1

3 1 1

3 6 5

0 0 0

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 52

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 13000 AND 14000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

13000 ft ISA + °C -10 0

10

20

-20

14000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

661 22 5 640 21 5 620 21 5 600 20 4 580 19 4 561 19 4 543 18 4 524 17 4 507 17 4 489 16 4

692 23 5 670 22 5 649 21 5 628 21 5 608 20 4 588 19 4 568 19 4 549 18 4 530 17 4 512 17 4

723 24 5 700 23 5 678 22 5 656 22 5 635 21 4 614 20 4 594 20 4 574 19 4 554 18 4 535 18 4

762 25 5 737 24 5 713 23 5 690 23 5 668 22 5 646 21 4 625 20 4 604 20 4 583 19 4 563 18 4

856 31 6 827 30 6 799 29 6 772 28 6 746 27 6 721 26 5 696 25 5 672 25 5 648 24 5 625 23 5

715 24 5 692 24 5 669 23 5 648 22 5 627 21 5 606 21 5 586 20 4 566 19 4 547 19 4 528 18 4

749 26 5 724 25 5 701 24 5 678 23 5 656 22 5 635 22 5 614 21 4 593 20 4 573 19 4 553 19 4

783 27 6 757 26 5 732 25 5 709 24 5 686 23 5 663 22 5 641 22 5 620 21 4 599 20 4 578 20 4

823 28 6 797 27 6 771 26 5 745 25 5 721 24 5 698 24 5 674 23 5 652 22 5 629 21 4 608 20 4

931 35 7 899 34 7 868 33 7 838 32 6 810 31 6 782 29 6 755 28 6 729 27 6 703 26 5 678 26 5

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 2 2

3 2 2

3 2 2

4 7 6

1 1 1

4 3 2

4 2 2

3 2 2

4 8 7

2 3 3

85000

83000

81000

79000

77000

75000

73000

71000

69000

AOM-1502-003

67000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 53

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 13000 AND 14000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

13000 ft ISA + °C -10 0

10

20

-20

14000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

472 16 3 455 15 3 438 14 3 422 14 3 406 13 3 390 13 3 375 12 3 359 12 3 344 11 3

494 16 4 476 16 3 459 15 3 442 14 3 425 14 3 409 13 3 392 13 3 376 12 3 360 12 3

516 17 4 498 16 4 479 16 3 462 15 3 444 15 3 427 14 3 410 13 3 393 13 3 377 12 3

543 18 4 523 17 4 504 16 3 486 16 3 467 15 3 449 15 3 431 14 3 413 13 3 396 13 3

602 22 5 580 21 4 558 20 4 537 20 4 516 19 4 496 18 4 476 17 4 456 17 3 436 16 3

510 17 4 491 17 4 474 16 4 456 16 3 439 15 3 422 14 3 405 14 3 388 13 3 372 13 3

534 18 4 515 17 4 496 17 4 477 16 3 459 16 3 442 15 3 424 14 3 407 14 3 389 13 3

558 19 4 538 18 4 518 17 4 499 17 4 480 16 3 461 16 3 443 15 3 425 14 3 407 14 3

586 20 4 565 19 4 545 18 4 524 18 4 505 17 4 485 16 3 466 16 3 447 15 3 428 14 3

653 25 5 629 24 5 606 23 5 583 22 4 560 21 4 538 20 4 516 19 4 495 19 4 474 18 4

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 2

3 2 1

3 2 1

3 7 6

1 1 1

4 2 2

3 2 2

3 2 2

4 7 7

1 3 2

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 54

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 15000 AND 16000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

15000 ft ISA + °C -10 0

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

771 27 6 745 26 6 721 25 5 697 25 5 674 24 5 652 23 5 630 22 5 609 21 5 588 21 4 568 20 4

807 28 6 781 27 6 755 26 6 730 26 5 706 25 5 683 24 5 660 23 5 638 22 5 616 22 5 595 21 4

844 30 6 816 29 6 789 28 6 763 27 6 738 26 5 713 25 5 690 24 5 666 23 5 644 22 5 621 22 4

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 2 2

3 2 2

85000

83000

81000

79000

77000

75000

73000

71000

69000

AOM-1502-003

67000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

20

-20

16000 ft ISA + °C -10 0

887 1009 31 39 6 8 858 974 30 38 6 8 830 939 29 37 6 7 802 907 28 35 6 7 776 875 27 34 5 7 750 845 26 33 5 7 725 816 25 32 5 6 701 787 24 31 5 6 677 760 24 30 5 6 653 732 23 28 5 6

828 30 6 800 29 6 774 28 6 748 27 6 723 26 6 698 25 5 675 24 5 652 24 5 630 23 5 608 22 5

867 31 6 838 30 6 810 29 6 783 28 6 757 27 6 732 26 5 707 25 5 683 25 5 660 24 5 637 23 5

906 33 7 876 32 6 847 31 6 818 29 6 791 28 6 764 27 6 739 27 5 714 26 5 690 25 5 666 24 5

4 3 3

4 2 2

3 2 2

10

5 9 8

3 5 4

10

20

953 1090 34 44 7 9 921 1051 33 42 7 8 890 1014 32 41 6 8 861 978 31 39 6 8 832 943 30 38 6 7 804 910 29 36 6 7 777 878 28 35 6 7 751 847 27 34 5 7 725 817 26 33 5 6 700 788 25 32 5 6 6 10 9

4 7 6

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 55

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 15000 AND 16000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

15000 ft ISA + °C -10 0

10

20

-20

16000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

548 19 4 528 19 4 509 18 4 490 17 4 472 17 4 453 16 3 435 15 3 418 15 3 400 14 3

574 20 4 553 19 4 533 19 4 513 18 4 494 17 4 475 17 4 456 16 3 437 15 3 419 15 3

600 21 4 578 20 4 557 19 4 536 19 4 516 18 4 496 17 4 476 17 3 457 16 3 438 15 3

630 22 4 608 21 4 586 20 4 564 20 4 543 19 4 521 18 4 501 17 4 480 17 3 460 16 3

706 27 5 680 26 5 655 25 5 630 24 5 605 23 5 581 23 4 558 22 4 535 21 4 512 20 4

587 21 4 566 20 4 545 20 4 525 19 4 505 18 4 486 17 4 466 17 4 447 16 3 428 15 3

615 22 5 593 21 4 571 21 4 550 20 4 529 19 4 509 18 4 488 17 4 468 17 3 449 16 3

642 23 5 619 22 5 597 21 4 575 21 4 553 20 4 531 19 4 510 18 4 489 17 4 469 17 3

675 24 5 651 23 5 627 22 4 604 22 4 581 21 4 559 20 4 536 19 4 514 18 4 493 17 4

759 30 6 731 29 6 704 28 5 677 27 5 651 26 5 625 25 5 600 24 5 575 23 4 551 22 4

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 2

3 2 2

3 2 2

4 8 7

2 4 4

4 3 3

4 2 2

3 2 2

5 9 8

3 6 5

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 56

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 17000 AND 18000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

17000 ft ISA + °C -10 0

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

886 33 7 857 32 7 828 31 6 800 30 6 773 29 6 747 28 6 721 27 6 697 26 5 673 25 5 649 24 5

928 35 7 897 33 7 867 32 7 838 31 6 810 30 6 782 29 6 755 28 6 730 27 5 705 26 5 680 25 5

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 2 2

85000

83000

81000

79000

77000

75000

73000

71000

69000

AOM-1502-003

67000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

20

-20

18000 ft ISA + °C -10 0

970 1020 1173 36 38 49 7 7 9 938 986 1131 35 36 47 7 7 9 906 953 1091 34 35 45 7 7 9 876 921 1051 32 34 43 6 7 8 846 889 1013 31 33 42 6 6 8 817 859 977 30 32 40 6 6 8 789 830 942 29 31 39 6 6 7 763 801 908 28 29 37 6 6 7 736 774 876 27 28 36 5 6 7 711 747 845 26 27 35 5 5 7

946 36 7 915 35 7 884 34 7 854 33 7 825 32 6 797 31 6 769 29 6 742 28 6 717 27 6 691 26 5

991 1036 1089 1259 38 40 41 54 8 8 8 10 958 1001 1052 1213 37 38 40 52 7 7 8 10 926 967 1017 1169 35 37 39 50 7 7 7 9 894 935 982 1127 34 36 37 48 7 7 7 9 864 903 949 1086 33 34 36 46 7 7 7 9 834 872 916 1047 32 33 35 44 6 6 7 8 806 842 885 1008 31 32 33 43 6 6 6 8 778 813 854 972 30 31 32 41 6 6 6 8 751 784 824 936 29 30 31 40 6 6 6 7 724 757 795 902 28 29 30 38 6 6 6 7

4 2 2

10

6 11 9

5 8 7

4 3 3

4 2 2

4 2 2

10

7 11 10

20

6 10 8

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 57

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 17000 AND 18000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

17000 ft ISA + °C -10 0

10

20

-20

18000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

627 23 5 604 22 5 582 22 4 561 21 4 539 20 4 518 19 4 498 18 4 477 18 4 457 17 4

656 24 5 633 23 5 610 23 5 587 22 4 565 21 4 543 20 4 521 19 4 500 18 4 479 18 4

686 25 5 661 24 5 637 23 5 614 23 5 590 22 4 567 21 4 545 20 4 523 19 4 501 18 4

721 26 5 695 25 5 670 25 5 645 24 5 620 23 4 596 22 4 573 21 4 549 20 4 526 19 4

814 33 6 784 32 6 755 31 6 726 30 6 698 29 5 670 27 5 643 26 5 616 25 5 590 24 5

667 25 5 643 25 5 620 24 5 597 23 5 574 22 4 552 21 4 530 20 4 508 19 4 487 18 4

699 27 5 674 26 5 649 25 5 625 24 5 601 23 5 578 22 4 555 21 4 532 20 4 510 19 4

730 28 5 704 27 5 678 26 5 653 25 5 628 24 5 604 23 4 580 22 4 556 21 4 533 20 4

767 29 6 740 28 5 713 27 5 686 26 5 660 25 5 635 24 5 609 23 4 584 22 4 560 21 4

870 37 7 837 35 7 806 34 6 775 33 6 745 31 6 716 30 6 687 29 5 658 28 5 630 27 5

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 2 2

3 2 2

5 10 9

4 7 6

4 3 3

4 2 2

3 2 2

6 10 9

5 8 7

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 58

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 19000 AND 20000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20 lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1008 40 8 975 39 8 942 37 7 909 36 7 878 35 7 848 33 7 818 32 6 790 31 6 762 30 6 735 29 6

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

85000

83000

81000

79000

77000

75000

73000

71000

69000

AOM-1502-003

67000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

19000 ft ISA + °C -10 0

10

20

1056 1104 1160 1347 42 43 45 59 8 8 9 11 1021 1066 1121 1298 40 42 44 57 8 8 8 10 986 1030 1083 1251 39 40 42 55 8 8 8 10 953 995 1046 1205 37 39 41 53 7 7 8 10 920 961 1010 1161 36 38 39 51 7 7 7 9 888 928 975 1118 35 36 38 49 7 7 7 9 857 896 941 1077 34 35 37 47 7 7 7 9 827 864 908 1037 32 34 35 45 6 7 7 8 798 834 876 999 31 32 34 43 6 6 6 8 770 804 845 962 30 31 33 42 6 6 6 8 4 2 2

4 2 2

7 12 11

7 11 10

-20

20000 ft ISA + °C -10 0

10

20

1073 1124 1174 1233 1438 44 45 47 49 65 9 9 9 9 12 1037 1086 1134 1191 1386 42 44 46 48 62 8 8 9 9 11 1001 1049 1095 1151 1335 41 42 44 46 60 8 8 8 9 11 967 1013 1058 1111 1286 39 41 43 44 58 8 8 8 8 10 934 978 1021 1073 1238 38 39 41 43 55 7 8 8 8 10 901 944 986 1035 1192 36 38 40 41 53 7 7 8 8 10 870 911 951 999 1148 35 37 38 40 51 7 7 7 7 9 839 879 918 964 1105 34 35 37 38 49 7 7 7 7 9 809 847 885 930 1064 33 34 35 37 47 6 7 7 7 9 780 817 853 896 1024 31 33 34 36 46 6 6 6 7 8 4 3 3

4 2 2

4 2 2

8 13 11

8 13 11

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 59

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 19000 AND 20000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

19000 ft ISA + °C -10 0

10

20

-20

20000 ft ISA + °C -10 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

709 28 6 683 27 5 658 26 5 634 25 5 610 24 5 586 23 5 563 22 4 540 21 4 517 20 4

742 29 6 716 28 6 690 27 5 664 26 5 639 25 5 614 24 5 590 23 5 565 22 4 542 21 4

776 30 6 748 29 6 720 28 5 694 27 5 667 26 5 641 25 5 616 24 5 591 23 4 566 22 4

815 32 6 785 30 6 757 29 6 728 28 5 701 27 5 674 26 5 647 25 5 620 24 5 594 23 4

926 40 7 892 39 7 859 37 7 826 36 7 794 34 6 762 33 6 731 32 6 701 30 6 671 29 5

752 30 6 724 29 6 698 28 6 672 27 5 646 26 5 621 25 5 596 24 5 572 23 5 548 22 4

787 32 6 759 30 6 731 29 6 704 28 5 677 27 5 651 26 5 625 25 5 599 24 5 574 23 4

822 33 6 792 32 6 763 30 6 735 29 6 707 28 5 680 27 5 652 26 5 626 25 5 599 24 5

864 34 6 832 33 6 802 32 6 772 31 6 742 29 6 714 28 5 685 27 5 657 26 5 629 25 5

985 44 8 948 42 8 912 41 7 877 39 7 843 37 7 810 36 7 777 34 6 745 33 6 713 32 6

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 2 2

4 2 2

6 11 10

5 9 8

4 3 3

4 2 2

4 2 2

6 11 10

6 10 9

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 60

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 21000 AND 22000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

22000 ft ISA + °C -10 0

10

20

-20

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1139 48 9 1100 46 9 1062 44 9 1025 43 8 990 41 8 955 40 8 922 38 7 889 37 7 857 36 7 826 34 7

1193 50 9 1152 48 9 1113 46 9 1074 45 8 1037 43 8 1001 41 8 965 40 8 931 39 7 898 37 7 865 36 7

1245 52 10 1203 50 9 1162 48 9 1122 46 9 1083 45 8 1045 43 8 1008 42 8 972 40 7 937 39 7 903 37 7

1308 54 10 1263 52 10 1220 50 9 1178 48 9 1137 47 9 1097 45 8 1058 43 8 1021 42 8 984 40 7 949 39 7

1532 71 13 1476 68 12 1421 66 12 1368 63 11 1317 61 11 1268 58 10 1221 56 10 1175 54 10 1130 52 9 1087 50 9

1207 52 10 1166 50 10 1126 49 9 1087 47 9 1049 45 9 1012 43 8 976 42 8 941 40 8 907 39 7 873 37 7

1265 54 10 1221 52 10 1179 51 9 1138 49 9 1098 47 9 1060 45 8 1022 44 8 985 42 8 950 40 8 915 39 7

1321 56 10 1275 54 10 1231 53 10 1189 51 9 1147 49 9 1107 47 9 1067 45 8 1029 44 8 992 42 8 956 40 7

1386 59 11 1339 57 10 1293 55 10 1248 53 10 1204 51 9 1162 49 9 1120 47 9 1080 46 8 1041 44 8 1003 42 8

1632 78 14 1571 75 13 1512 72 13 1456 69 12 1401 66 12 1348 64 11 1297 61 11 1248 59 10 1200 57 10 1154 54 10

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 2 2

4 2 2

8 13 12

9 14 12

4 3 3

4 3 2

4 2 2

9 14 13

10 16 14

85000

83000

81000

79000

77000

75000

73000

71000

69000

67000

AOM-1502-003

21000 ft ISA + °C -10 0

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 61

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 21000 AND 22000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

21000 ft ISA + °C -10 0

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

796 33 6 766 32 6 738 31 6 710 29 6 683 28 6 656 27 5 630 26 5 604 25 5 579 24 5

833 34 7 803 33 6 773 32 6 744 31 6 715 29 6 688 28 5 660 27 5 633 26 5 606 25 5

870 36 7 838 34 6 807 33 6 777 32 6 747 31 6 718 29 6 689 28 5 661 27 5 633 26 5

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 2 2

4 2 2

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

20

-20

22000 ft ISA + °C -10 0

914 1046 37 48 7 9 880 1005 36 46 7 8 847 967 35 44 6 8 815 930 33 42 6 8 784 893 32 41 6 7 754 858 31 39 6 7 724 823 29 37 5 7 694 789 28 36 5 6 665 755 27 34 5 6

841 36 7 810 35 7 779 33 6 749 32 6 721 31 6 693 29 6 665 28 5 638 27 5 611 26 5

881 37 7 848 36 7 816 35 7 785 33 6 755 32 6 726 31 6 697 29 6 668 28 5 640 27 5

920 39 7 886 37 7 853 36 7 820 35 6 789 33 6 758 32 6 728 31 6 698 29 5 668 28 5

4 3 3

4 2 2

4 2 2

10

7 12 11

7 12 10

10

20

966 1109 41 52 7 9 930 1066 39 50 7 9 895 1024 38 48 7 9 861 984 36 46 7 8 828 945 35 44 6 8 795 908 33 43 6 8 764 871 32 41 6 7 732 834 31 39 6 7 701 798 29 37 5 7 7 12 11

7 13 11

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 62

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 23000 AND 24000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -20

24000 ft ISA + °C -10 0

10

20

-20

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1280 57 11 1236 55 10 1193 53 10 1151 51 10 1110 49 9 1071 47 9 1032 46 9 995 44 8 959 42 8 923 41 8

1341 59 11 1294 57 11 1249 55 10 1206 53 10 1163 51 9 1122 49 9 1082 48 9 1042 46 8 1004 44 8 967 42 8

1400 62 11 1352 59 11 1305 57 10 1259 55 10 1215 53 10 1171 51 9 1129 49 9 1089 48 9 1049 46 8 1010 44 8

1469 64 11 1418 62 11 1369 60 11 1321 58 10 1274 56 10 1229 54 10 1185 52 9 1142 50 9 1101 48 9 1060 46 8

1739 85 15 1673 82 14 1610 79 14 1549 76 13 1490 73 13 1433 70 12 1378 67 12 1325 64 11 1274 62 11 1224 59 10

1358 62 12 1310 60 11 1264 58 11 1219 56 10 1175 54 10 1133 52 10 1092 50 9 1052 48 9 1013 46 9 975 44 8

1422 65 12 1372 63 11 1324 60 11 1277 58 11 1231 56 10 1187 54 10 1144 52 9 1102 50 9 1062 48 9 1022 46 8

1485 68 12 1433 65 12 1382 63 11 1333 60 11 1286 58 10 1240 56 10 1195 54 10 1151 52 9 1109 50 9 1067 48 9

1558 70 12 1503 68 12 1450 65 11 1398 63 11 1349 61 11 1300 58 10 1253 56 10 1208 54 9 1163 52 9 1120 50 9

1856 94 16 1784 90 15 1715 87 15 1649 83 14 1585 80 14 1524 77 13 1465 74 13 1408 71 12 1353 68 12 1299 65 11

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

5 4 3

4 3 3

4 3 2

9 15 14

11 18 16

5 4 3

4 3 3

4 3 3

10 16 15

13 21 18

85000

83000

81000

79000

77000

75000

73000

71000

69000

67000

AOM-1502-003

23000 ft ISA + °C -10 0

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 63

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 23000 AND 24000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -20

23000 ft ISA + °C -10 0

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

889 39 7 855 38 7 823 36 7 791 35 7 760 33 6 730 32 6 701 31 6 672 29 6 644 28 5

931 41 8 896 39 7 862 38 7 829 36 7 796 35 6 765 33 6 734 32 6 704 31 6 674 29 5

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 2 2

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

20

-20

24000 ft ISA + °C -10 0

973 1020 1176 42 44 57 8 8 10 936 982 1130 41 42 55 7 8 10 900 945 1085 39 41 52 7 7 9 866 908 1042 38 39 50 7 7 9 832 873 1000 36 38 48 7 7 8 799 838 959 35 36 46 6 6 8 767 805 920 33 35 44 6 6 8 735 772 882 32 33 42 6 6 7 704 739 844 30 32 41 6 6 7

939 43 8 903 41 8 868 39 7 834 38 7 801 36 7 769 35 6 738 33 6 708 32 6 678 30 6

984 1027 1078 1248 44 46 48 62 8 8 8 11 946 988 1037 1198 43 44 46 60 8 8 8 10 910 950 997 1150 41 43 44 57 7 8 8 10 874 913 958 1103 39 41 43 55 7 7 7 9 840 877 920 1058 38 39 41 53 7 7 7 9 806 842 883 1014 36 38 39 50 7 7 7 9 773 808 847 972 35 36 38 48 6 6 7 8 741 775 812 931 33 35 36 46 6 6 6 8 710 742 778 891 32 33 34 44 6 6 6 8

4 2 2

10

8 13 12

8 14 12

4 3 3

4 2 2

4 2 2

10

8 14 13

20

9 16 14

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 64

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 25000 AND 26000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -19

26000 ft ISA + °C -10 0

10

20

-18

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1449 69 12 1396 66 12 1346 64 12 1297 61 11 1250 59 11 1205 57 10 1161 55 10 1118 52 10 1076 50 9 1035 48 9

1510 71 13 1456 69 12 1403 66 12 1353 64 11 1304 61 11 1256 59 11 1210 57 10 1166 54 10 1122 52 9 1080 50 9

1577 74 13 1520 71 12 1466 69 12 1413 66 12 1362 64 11 1312 61 11 1264 59 10 1218 57 10 1172 54 10 1128 52 9

1654 77 13 1594 74 13 1537 71 12 1481 69 12 1428 66 11 1376 64 11 1326 61 11 1277 59 10 1229 57 10 1183 54 9

1986 104 17 1907 100 17 1831 96 16 1758 92 15 1689 88 15 1623 84 14 1559 81 14 1497 77 13 1437 74 12 1380 71 12

1533 75 13 1476 72 13 1422 69 12 1370 66 12 1319 64 11 1271 61 11 1223 59 11 1178 57 10 1133 55 10 1090 52 9

1591 77 14 1532 74 13 1476 71 13 1422 69 12 1369 66 12 1319 63 11 1270 61 11 1223 59 10 1176 56 10 1132 54 10

1661 80 14 1600 77 13 1542 74 13 1485 71 12 1430 69 12 1378 66 11 1327 63 11 1277 61 11 1229 59 10 1182 56 10

1741 84 14 1678 80 14 1616 77 13 1557 74 13 1500 71 12 1444 69 12 1391 66 11 1339 64 11 1289 61 10 1239 59 10

2109 114 19 2023 109 18 1940 104 17 1861 100 16 1786 96 16 1714 92 15 1645 88 14 1579 84 14 1515 81 13 1453 77 13

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

5 4 3

4 3 3

4 3 3

11 18 16

15 24 21

5 4 4

5 3 3

4 3 3

12 19 18

18 28 25

85000

83000

81000

79000

77000

75000

73000

71000

69000

67000

AOM-1502-003

25000 ft ISA + °C -10 0

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 65

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 25000 AND 26000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

-19 lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

996 47 9 958 45 8 920 43 8 884 41 8 848 39 7 814 38 7 781 36 7 748 35 6 716 33 6

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

25000 ft ISA + °C -10 0

10

20

1039 1085 1138 1324 48 50 52 68 9 9 9 11 999 1043 1094 1270 46 48 50 65 8 8 9 11 960 1003 1051 1218 44 46 48 63 8 8 8 11 922 963 1010 1168 43 44 46 60 8 8 8 10 885 925 970 1120 41 43 44 57 7 8 8 10 849 887 930 1073 39 41 42 55 7 7 7 9 814 851 892 1027 38 39 41 52 7 7 7 9 780 815 855 983 36 37 39 50 6 7 7 8 747 781 819 941 34 36 37 48 6 6 6 8 4 3 2

4 3 2

9 15 14

11 18 16

-18

26000 ft ISA + °C -10 0

10

20

1048 1088 1137 1192 1394 50 52 54 56 74 9 9 9 10 12 1007 1046 1092 1145 1336 48 50 52 54 71 9 9 9 9 12 967 1004 1049 1100 1281 46 48 50 52 68 8 8 9 9 11 929 964 1007 1056 1227 44 46 48 50 65 8 8 8 8 11 891 925 967 1014 1175 42 44 46 48 62 8 8 8 8 10 855 887 927 972 1125 41 42 44 46 59 7 7 8 8 10 819 851 889 932 1077 39 40 42 44 56 7 7 7 7 9 785 815 851 893 1030 37 38 40 42 54 7 7 7 7 9 751 780 815 854 985 36 37 38 40 51 6 7 7 7 9 4 3 3

4 3 3

4 3 2

10 16 15

12 20 18

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 66

Climb

REVISION 21

AOM-1502-003

WEIGHT (lb)

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 27000 AND 28000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -17

28000 ft ISA + °C -10 0

10

20

-16

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1610 80 14 1550 77 14 1492 74 13 1437 71 13 1383 69 12 1331 66 12 1281 63 11 1232 61 11 1185 58 10 1140 56 10

1664 83 14 1602 80 14 1542 76 13 1484 73 13 1429 71 12 1375 68 12 1323 65 11 1273 63 11 1225 60 11 1178 58 10

1737 86 15 1673 83 14 1610 79 14 1550 76 13 1492 73 13 1437 71 12 1383 68 12 1330 65 11 1280 62 11 1230 60 10

1821 90 15 1753 86 14 1688 83 14 1625 80 13 1564 76 13 1506 73 12 1449 71 12 1395 68 11 1342 65 11 1290 62 11

2222 123 20 2128 118 19 2039 113 18 1954 108 17 1873 103 17 1796 98 16 1722 94 15 1652 90 15 1584 86 14 1518 82 14

1691 87 15 1626 83 14 1565 80 14 1505 77 13 1448 74 13 1393 71 12 1340 68 12 1288 65 11 1238 62 11 1190 60 11

1738 89 15 1672 85 15 1609 82 14 1548 78 14 1489 75 13 1432 72 12 1378 69 12 1325 67 12 1274 64 11 1224 61 11

1816 92 16 1747 89 15 1681 85 14 1617 82 14 1556 78 13 1497 75 13 1440 72 12 1384 69 12 1331 67 11 1279 64 11

1903 96 16 1831 92 15 1761 88 15 1695 85 14 1631 82 14 1569 78 13 1509 75 13 1451 72 12 1395 69 12 1341 66 11

2335 133 21 2234 127 20 2139 121 19 2048 116 19 1961 110 18 1879 105 17 1800 101 16 1725 96 16 1653 92 15 1583 88 14

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

5 4 4

5 3 3

5 3 3

13 21 19

20 32 29

5 4 4

5 4 3

5 3 3

14 23 21

23 37 33

85000

83000

81000

79000

77000

75000

73000

71000

69000

67000

AOM-1502-003

27000 ft ISA + °C -10 0

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 67

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 27000 AND 28000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

-17 lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1095 54 10 1052 52 9 1010 49 9 970 47 8 930 45 8 892 43 8 854 41 7 818 40 7 782 38 7

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

27000 ft ISA + °C -10 0

10

20

1132 1183 1240 1455 55 58 60 79 10 10 10 13 1087 1136 1191 1395 53 55 57 75 9 9 10 12 1044 1091 1144 1336 51 53 55 72 9 9 9 12 1002 1047 1098 1279 49 51 53 69 9 9 9 11 961 1004 1053 1225 47 49 51 66 8 8 9 11 921 963 1010 1172 45 46 48 63 8 8 8 10 883 923 967 1121 43 44 46 60 8 8 8 10 845 883 926 1072 41 42 44 57 7 7 8 9 809 845 886 1024 39 41 42 55 7 7 7 9 4 3 3

4 3 2

10 17 16

13 22 20

-16

28000 ft ISA + °C -10 0

10

20

1143 1176 1229 1288 1517 57 59 61 64 84 10 10 10 11 14 1098 1129 1180 1237 1453 55 56 59 61 80 10 10 10 10 13 1054 1084 1133 1188 1391 53 54 56 59 77 9 9 10 10 13 1011 1040 1087 1139 1331 50 52 54 56 73 9 9 9 9 12 969 997 1042 1093 1274 48 49 52 54 70 9 9 9 9 11 929 956 999 1047 1218 46 47 49 51 67 8 8 8 9 11 890 915 956 1003 1164 44 45 47 49 64 8 8 8 8 10 851 876 915 960 1113 42 43 45 47 61 7 8 8 8 10 814 837 875 918 1063 40 41 43 45 58 7 7 7 8 10 5 3 3

4 3 3

4 3 3

11 18 17

15 24 22

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 68

Climb

REVISION 21

AOM-1502-003

WEIGHT (lb)

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 29000 AND 30000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -15

30000 ft ISA + °C -10 0

10

20

-14

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1776 93 16 1706 89 15 1639 86 15 1576 82 14 1515 79 14 1457 76 13 1400 72 13 1346 69 12 1293 67 12 1242 64 11

1818 95 16 1746 91 16 1678 87 15 1613 84 14 1551 80 14 1491 77 13 1433 74 13 1377 71 12 1323 68 12 1271 65 11

1899 99 17 1824 95 16 1753 91 15 1686 87 15 1621 84 14 1558 80 13 1498 77 13 1440 74 12 1383 71 12 1329 68 11

1989 103 17 1911 99 16 1837 95 16 1766 91 15 1698 87 14 1633 83 14 1570 80 13 1509 77 13 1450 74 12 1393 71 12

2456 144 23 2344 136 22 2241 130 21 2143 124 20 2051 118 19 1963 113 18 1879 108 17 1799 103 16 1722 98 16 1649 94 15

1868 101 17 1791 96 16 1719 92 16 1650 88 15 1585 84 14 1522 81 14 1462 77 13 1405 74 13 1349 71 12 1295 68 12

1903 102 17 1825 98 17 1751 93 16 1681 89 15 1614 86 15 1551 82 14 1490 79 13 1431 75 13 1374 72 12 1319 69 12

1988 106 18 1907 102 17 1830 97 16 1757 93 15 1687 89 15 1621 85 14 1557 82 14 1496 78 13 1437 75 13 1379 72 12

2082 111 18 1997 106 17 1916 101 16 1840 97 16 1768 93 15 1699 89 15 1632 85 14 1568 82 13 1505 78 13 1445 75 12

2588 155 24 2464 147 23 2349 140 22 2242 133 21 2143 127 20 2049 121 19 1960 115 18 1875 110 17 1793 105 17 1716 100 16

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

5 4 4

5 4 4

5 3 3

16 25 23

27 43 38

5 4 4

5 4 4

5 3 3

17 28 25

26 42 38

85000

83000

81000

79000

77000

75000

73000

71000

69000

67000

AOM-1502-003

29000 ft ISA + °C -10 0

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 69

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 29000 AND 30000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -15

29000 ft ISA + °C -10 0

30000 ft ISA + °C -10 0

10

20

-14

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1192 61 11 1145 59 10 1098 56 10 1053 54 9 1009 51 9 967 49 9 925 47 8 885 45 8 846 43 7

1221 62 11 1172 60 10 1124 57 10 1078 55 9 1033 52 9 990 50 9 948 48 8 906 46 8 866 44 8

1276 65 11 1225 62 11 1175 60 10 1127 57 10 1080 55 9 1035 52 9 991 50 8 948 48 8 906 45 8

1337 68 11 1284 65 11 1232 62 10 1181 59 10 1132 57 9 1085 54 9 1038 52 9 993 50 8 950 47 8

1578 89 14 1511 85 14 1446 82 13 1383 78 13 1323 74 12 1264 71 11 1208 68 11 1154 64 10 1101 61 10

1243 65 11 1192 62 11 1143 60 10 1096 57 10 1050 55 9 1005 52 9 962 50 9 920 48 8 879 45 8

1266 66 11 1215 63 11 1165 61 10 1117 58 10 1070 55 10 1024 53 9 980 51 9 937 48 8 896 46 8

1324 69 12 1270 66 11 1218 63 11 1168 60 10 1119 58 10 1071 55 9 1025 53 9 980 50 8 936 48 8

1387 72 12 1331 69 11 1276 66 11 1224 63 10 1172 60 10 1123 58 9 1074 55 9 1027 52 9 982 50 8

1641 95 15 1570 91 15 1501 87 14 1435 83 13 1372 79 13 1311 75 12 1252 71 12 1195 68 11 1140 65 10

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

5 3 3

5 3 3

4 3 3

11 19 18

16 27 24

5 4 3

5 3 3

4 3 3

12 21 19

17 29 26

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 70

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 31000 AND 32000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -13

32000 ft ISA + °C -10 0

10

20

-12

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1967 109 18 1883 104 17 1804 99 17 1729 95 16 1658 90 15 1591 86 15 1527 83 14 1466 79 13 1406 76 13 1349 73 12

1995 110 18 1909 105 18 1829 100 17 1753 96 16 1681 91 15 1613 87 15 1548 84 14 1486 80 14 1426 77 13 1368 73 12

2084 115 19 1995 109 18 1912 104 17 1832 100 16 1758 95 16 1686 91 15 1619 87 14 1554 83 14 1491 80 13 1431 76 13

2182 119 19 2089 114 18 2002 109 18 1919 104 17 1841 99 16 1767 95 15 1696 91 15 1628 87 14 1563 83 14 1499 80 13

2734 169 26 2595 159 25 2467 151 24 2349 143 22 2240 136 21 2138 129 20 2043 123 19 1952 117 18 1866 111 18 1784 106 17

2077 118 20 1983 112 19 1896 107 18 1814 102 17 1737 97 16 1664 93 16 1595 88 15 1529 85 14 1466 81 14 1406 77 13

2096 119 20 2002 113 19 1914 108 18 1831 103 17 1753 98 16 1679 93 16 1610 89 15 1543 85 14 1480 82 14 1419 78 13

2190 124 20 2092 118 19 2000 112 18 1914 107 17 1833 102 17 1756 97 16 1683 93 15 1614 89 15 1548 85 14 1484 81 13

2292 129 21 2190 123 20 2094 117 19 2004 111 18 1919 106 17 1839 101 16 1763 97 16 1691 92 15 1621 88 14 1555 85 14

2899 185 29 2741 174 27 2597 163 25 2466 154 24 2345 146 23 2234 138 22 2130 131 21 2032 125 20 1941 119 19 1853 113 18

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

6 5 4

5 4 4

5 4 4

19 31 28

26 43 38

5 4 4

5 4 4

5 3 3

18 29 26

25 39 36

85000

83000

81000

79000

77000

75000

73000

71000

69000

67000

AOM-1502-003

31000 ft ISA + °C -10 0

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 71

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 31000 AND 32000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -13

31000 ft ISA + °C -10 0

32000 ft ISA + °C -10 0

10

20

-12

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1294 69 12 1241 66 11 1189 63 11 1140 61 10 1091 58 10 1044 55 9 999 53 9 955 50 9 912 48 8

1312 70 12 1258 67 11 1206 64 11 1156 61 10 1107 59 10 1059 56 10 1013 53 9 968 51 9 925 49 8

1372 73 12 1316 70 12 1261 67 11 1209 64 11 1157 61 10 1108 58 10 1060 56 9 1013 53 9 967 51 8

1438 76 12 1379 73 12 1322 70 11 1267 67 11 1213 64 10 1161 61 10 1111 58 10 1062 55 9 1014 53 9

1705 101 16 1629 96 15 1557 92 15 1488 87 14 1421 83 13 1357 79 13 1295 76 12 1236 72 12 1179 68 11

1347 74 12 1291 71 12 1237 67 11 1184 64 11 1134 62 10 1084 59 10 1037 56 10 991 53 9 946 51 9

1360 74 13 1303 71 12 1248 68 11 1195 65 11 1144 62 10 1095 59 10 1047 56 10 1000 54 9 955 51 9

1422 78 13 1363 74 12 1306 71 12 1250 68 11 1197 65 11 1145 62 10 1095 59 10 1046 56 9 999 53 9

1490 81 13 1428 77 13 1368 74 12 1310 71 11 1254 67 11 1200 64 10 1147 61 10 1096 58 10 1047 56 9

1770 107 17 1690 102 16 1614 97 15 1541 93 15 1471 88 14 1404 84 13 1340 80 13 1277 76 12 1217 72 11

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

5 4 3

5 3 3

4 3 3

13 22 20

19 32 29

5 3 3

5 3 3

4 3 3

12 20 19

19 30 27

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 72

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 33000 AND 34000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -11

34000 ft ISA + °C -5 0

10

20

-10

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

2197 129 21 2094 122 20 1997 116 19 1907 110 18 1822 105 17 1742 100 17 1667 95 16 1596 90 15 1528 86 14 1464 82 14

2208 130 21 2104 123 20 2006 116 19 1915 110 18 1830 105 17 1750 100 17 1675 95 16 1604 91 15 1536 87 14 1471 83 14

2308 135 22 2199 128 21 2098 121 20 2003 115 19 1914 109 18 1831 104 17 1752 99 16 1677 95 15 1606 90 15 1539 86 14

2415 140 22 2302 133 21 2196 126 20 2097 120 19 2005 114 18 1917 108 17 1835 103 17 1757 99 16 1683 94 15 1612 90 14

3089 204 31 2908 190 29 2744 178 27 2596 167 26 2462 157 24 2338 148 23 2224 140 22 2118 133 21 2019 126 20 1926 120 19

2333 142 23 2217 134 22 2109 126 21 2009 119 20 1916 113 19 1828 107 18 1746 102 17 1668 97 16 1595 92 15 1526 88 15

2386 145 23 2267 136 22 2158 129 21 2055 122 20 1960 116 19 1870 110 18 1786 104 17 1707 99 16 1632 94 15 1561 90 15

2440 148 24 2318 139 22 2206 131 21 2102 124 20 2004 118 19 1912 112 18 1826 106 17 1746 101 16 1669 96 16 1596 92 15

2554 154 24 2428 145 23 2311 137 22 2201 130 20 2099 123 19 2003 117 18 1914 111 18 1829 105 17 1749 100 16 1673 96 15

3310 227 34 3099 210 32 2912 195 30 2744 182 28 2592 171 26 2454 160 25 2327 151 23 2211 143 22 2102 135 21 2002 128 20

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

5 4 4

5 4 3

5 3 3

17 26 24

24 36 33

5 3 3

4 3 3

4 3 3

16 24 22

22 33 30

85000

83000

81000

79000

77000

75000

73000

71000

69000

67000

AOM-1502-003

33000 ft ISA + °C -10 0

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 73

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 33000 AND 34000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -11

33000 ft ISA + °C -10 0

34000 ft ISA + °C -5 0

10

20

-10

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1402 79 13 1343 75 13 1286 72 12 1230 68 12 1177 65 11 1125 62 11 1075 59 10 1027 57 10 980 54 9

1409 79 13 1349 75 13 1292 72 12 1236 69 12 1183 66 11 1131 63 11 1080 60 10 1032 57 10 985 54 9

1474 82 14 1412 79 13 1351 75 12 1293 72 12 1237 68 11 1183 65 11 1130 62 10 1080 59 10 1030 56 9

1544 86 14 1479 82 13 1416 78 13 1355 75 12 1297 71 12 1240 68 11 1185 65 10 1132 62 10 1080 59 10

1837 114 18 1753 108 17 1673 103 16 1596 98 15 1522 93 15 1452 89 14 1384 84 13 1319 80 13 1257 76 12

1460 84 14 1397 80 13 1336 76 13 1278 73 12 1222 69 12 1168 66 11 1115 63 11 1064 60 10 1015 57 10

1494 86 14 1429 82 13 1367 78 13 1308 74 12 1250 71 12 1195 67 11 1141 64 11 1089 61 10 1039 58 10

1528 87 14 1462 83 14 1398 80 13 1337 76 12 1279 72 12 1222 69 11 1167 66 11 1114 62 10 1062 59 10

1601 91 15 1532 87 14 1466 83 13 1402 79 13 1340 75 12 1281 72 12 1223 68 11 1168 65 10 1114 62 10

1907 121 19 1818 115 18 1733 109 17 1652 104 16 1575 99 15 1501 94 15 1430 89 14 1362 84 13 1296 80 13

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 3 3

4 3 3

12 19 18

18 28 26

4 3 3

4 3 2

4 2 2

11 18 17

17 27 24

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 74

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 35000 AND 36000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -9

36000 ft ISA + °C -5 0

10

20

-8

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

2494 157 25 2357 147 24 2234 138 22 2122 130 21 2018 123 20 1922 116 19 1831 110 18 1747 104 17 1667 99 16 1592 94 16

2540 160 26 2400 149 24 2275 140 23 2161 132 21 2056 125 20 1957 118 19 1865 112 18 1779 106 17 1698 101 16 1621 96 16

2599 163 26 2455 153 24 2327 143 23 2211 135 22 2103 128 20 2002 121 19 1908 114 18 1820 108 18 1737 103 17 1658 98 16

2722 170 27 2572 159 25 2438 150 23 2316 141 22 2204 133 21 2098 126 20 2000 119 19 1907 113 18 1820 107 17 1738 102 16

3105 216 33 2912 200 30 2740 186 28 2584 174 27 2442 163 25 2313 153 24 2194 145 22 2084 136 21

2534 165 27 2381 153 25 2250 143 23 2132 134 22 2025 126 21 1926 119 19 1833 113 18 1745 107 17 1663 101 17

2570 167 27 2415 155 25 2282 145 23 2162 136 22 2054 128 21 1953 121 20 1858 114 19 1770 108 18 1686 102 17

2630 170 27 2471 158 25 2335 148 24 2213 139 22 2101 131 21 1998 124 20 1901 117 19 1811 110 18 1725 105 17

2757 178 28 2591 165 26 2448 154 24 2320 145 23 2203 137 21 2095 129 20 1993 122 19 1898 115 18 1809 109 17

3109 222 34 2907 205 31 2730 190 29 2571 177 27 2426 166 25 2294 156 24 2173 146 22

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 3

4 3 3

4 2 2

15 21 20

21 30 28

4 2 2

4 2 2

4 2 2

13 18 17

19 27 25

85000

83000

81000

79000

77000

75000

73000

71000

69000

67000

AOM-1502-003

35000 ft ISA + °C -5 0

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 75

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 35000 AND 36000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -9

35000 ft ISA + °C -5 0

36000 ft ISA + °C -5 0

10

20

-8

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1521 90 15 1453 85 14 1389 81 13 1327 77 13 1268 74 12 1211 70 12 1156 67 11 1102 63 11 1051 60 10

1549 91 15 1480 87 14 1415 83 14 1352 79 13 1292 75 12 1233 71 12 1177 68 11 1123 64 11 1070 61 10

1584 93 15 1514 89 14 1447 84 14 1383 80 13 1321 76 12 1262 73 12 1204 69 11 1149 66 11 1095 63 10

1661 97 15 1587 92 15 1517 88 14 1450 84 13 1385 80 13 1323 76 12 1263 72 12 1204 69 11 1148 65 10

1981 129 20 1885 122 19 1795 116 18 1710 110 17 1628 104 16 1551 99 15 1476 94 15 1405 89 14 1337 84 13

1586 96 16 1513 91 15 1444 86 14 1379 82 14 1316 78 13 1256 74 12 1198 71 12 1142 67 11 1088 64 11

1608 97 16 1534 92 15 1464 88 14 1398 83 14 1334 79 13 1273 75 12 1215 72 12 1158 68 11 1103 65 11

1645 99 16 1570 94 15 1498 90 14 1430 85 14 1365 81 13 1303 77 13 1243 73 12 1185 70 11 1128 66 11

1725 104 16 1646 98 16 1571 93 15 1499 89 14 1431 84 13 1366 80 13 1303 76 12 1242 73 12 1183 69 11

2061 138 21 1957 130 20 1860 123 19 1769 116 18 1683 110 17 1602 105 16 1524 99 15 1449 94 15 1377 89 14

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 3 2

4 2 2

4 2 2

11 17 16

16 25 23

4 2 2

4 2 2

4 2 2

10 16 15

16 23 21

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 76

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 37000 AND 38000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -8

10

20

-8

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

2269 149 24 2143 139 22 2029 130 21 1926 123 20 1830 116 19 1739 109 18

2302 151 24 2173 141 23 2058 132 21 1953 124 20 1855 117 19 1764 111 18

2356 154 24 2224 144 23 2107 135 22 1999 127 20 1899 120 19 1805 113 18

2471 161 25 2333 151 23 2210 141 22 2097 133 21 1992 125 20 1893 118 19

2735 196 30 2570 182 28 2420 170 26 2283 159 24

2159 145 23 2037 135 22 1927 127 20 1827 119 19

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 2 2

4 2 2

3 2 2

11 15 14

16 22 21

3 2 2

85000

83000

81000

79000

77000

75000

73000

71000

69000

67000

AOM-1502-003

37000 ft ISA + °C -5 0

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

38000 ft ISA + °C -5 0

10

20

2190 2242 2353 147 150 157 24 24 24 2066 2115 2219 137 140 147 22 22 23 1955 2001 2100 2580 128 131 137 190 21 21 21 29 1853 1897 1990 2421 121 123 129 176 19 20 20 27 3 2 2

3 2 2

10 13 13

14 19 18

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 77

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 37000 AND 38000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -8

37000 ft ISA + °C -5 0

38000 ft ISA + °C -5 0

10

20

-8

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1655 103 17 1576 98 16 1501 93 15 1430 88 14 1363 83 14 1300 79 13 1239 75 12 1180 71 12 1123 68 11

1678 105 17 1598 99 16 1522 94 15 1450 89 14 1382 84 14 1318 80 13 1256 76 12 1196 72 12 1139 68 11

1717 107 17 1635 101 16 1557 96 15 1484 91 15 1414 86 14 1348 82 13 1285 78 13 1224 74 12 1165 70 11

1801 112 18 1715 106 17 1633 100 16 1556 95 15 1483 90 14 1414 85 14 1348 81 13 1284 77 12 1222 73 12

2158 149 23 2043 140 21 1937 132 20 1838 124 19 1745 117 18 1659 111 17 1576 105 16 1498 99 15 1422 94 15

1734 112 18 1646 106 17 1564 100 16 1488 94 15 1415 89 15 1347 84 14 1282 80 13 1220 76 12 1160 72 12

1758 114 18 1669 107 17 1586 101 16 1509 95 15 1435 90 15 1366 85 14 1300 81 13 1237 77 13 1177 73 12

1800 116 19 1709 109 17 1624 103 17 1544 98 16 1469 92 15 1398 87 14 1330 83 13 1266 78 13 1204 74 12

1888 121 19 1792 114 18 1703 108 17 1619 102 16 1540 96 15 1466 91 14 1395 86 14 1328 82 13 1263 78 12

2277 164 25 2147 153 23 2027 143 22 1918 134 21 1816 126 19 1722 119 18 1634 112 17 1550 106 16 1471 100 15

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

4 2 2

4 2 2

3 2 2

10 14 14

15 21 19

3 2 2

3 2 2

3 2 2

9 13 12

14 19 17

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 78

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 39000 AND 40000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -8 lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

2048 141 23 1930 131 21

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 2

85000

83000

81000

79000

77000

75000

73000

71000

69000

AOM-1502-003

67000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

39000 ft ISA + °C -5 0

10

20

2078 2128 2234 143 146 153 23 23 24 1958 2005 2105 133 136 143 21 22 22

-

3 2 2

3 1 1

9 12 11

-

-8

40000 ft ISA + °C -5 0

2067 2098 2150 148 150 154 24 24 24 -

-

-

10

20

-

-

-

-

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 79

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 39000 AND 40000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION ALL ENGINE TYPES

WEIGHT (lb) -8

39000 ft ISA + °C -5 0

40000 ft ISA + °C -5 0

10

20

-8

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1825 123 20 1727 115 19 1637 108 18 1552 102 17 1473 96 16 1398 90 15 1329 85 14 1262 81 13 1199 76 12

1851 125 20 1752 117 19 1660 110 18 1574 103 17 1494 97 16 1418 92 15 1347 87 14 1280 82 13 1216 77 13

1895 127 20 1794 119 19 1699 112 18 1611 106 17 1529 99 16 1452 94 15 1379 88 14 1310 84 13 1245 79 13

1989 133 21 1882 125 19 1783 117 18 1690 110 17 1604 104 16 1523 98 15 1447 93 15 1375 87 14 1306 83 13

2434 184 28 2279 170 26 2140 158 24 2014 147 22 1900 137 21 1795 128 20 1698 120 18 1608 113 17 1524 107 16

1937 137 22 1824 127 20 1721 119 19 1627 111 18 1539 104 17 1457 98 16 1381 92 15 1309 86 14 1241 82 13

1966 139 22 1850 129 21 1746 120 19 1650 113 18 1561 106 17 1478 99 16 1400 93 15 1328 88 14 1259 83 13

2014 142 22 1895 132 21 1789 123 20 1690 115 18 1598 108 17 1513 101 16 1434 95 15 1359 90 14 1289 85 14

2117 149 23 1991 139 21 1879 129 20 1774 121 19 1678 113 18 1588 106 17 1505 100 16 1426 94 15 1353 89 14

2290 178 27 2139 164 25 2004 151 23 1884 140 21 1775 131 20 1675 122 19 1582 115 18

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 2

3 2 2

3 2 2

9 12 11

12 16 15

3 2 2

3 2 2

3 2 1

8 11 10

11 14 13

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 80

Climb

REVISION 21

AOM-1502-003

BLEED: OPEN

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CLIMB PLANNING - ALL ENGINES OPERATING ALTITUDE: SEA LEVEL TO 41000 FT SPEED SCHEDULE

240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 25400 FT AND MACH 0.70 ABOVE 25400 FT.

CRUISE CONFIGURATION BLEED: OPEN

ALL ENGINE TYPES

WEIGHT (lb) -8

41000 ft ISA + °C -5 0

10

20

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

1947 143 23 1823 132 21 1714 123 20 1615 114 18 1524 106 17 1439 100 16 1361 93 15 1287 88 14

1976 146 23 1850 134 21 1740 124 20 1639 116 19 1546 108 17 1460 101 16 1380 95 15 1306 89 14

2026 149 23 1896 138 22 1783 128 20 1679 119 19 1584 111 18 1495 103 16 1414 97 15 1337 91 14

2133 157 24 1994 145 22 1874 134 21 1764 125 19 1663 116 18 1570 108 17 1484 102 16 1404 95 15

2140 171 26 1994 156 24 1867 144 22 1753 134 20 1649 125 19

For Anti- Fuel (%) ice ON, Distance (%) increase Time (%)

3 2 2

3 1 1

3 1 1

7 10 9

10 13 12

65000

63000

61000

59000

57000

55000

53000

51000

49000

Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

AOM-1502-003

"

6-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Climb

Page 81

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

6-10 Copyright © by Embraer. Refer to cover page for details.

Page 82

Climb

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

BUFFET ONSET !EMBRAER 170 Models

AOM-1502-003

This chart provides the buffet margin (maneuver capability) and associated bank angles for a variety of cruise altitudes and weights as function of Mach number.

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 1

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 2

Cruise

REVISION 18

AOM-1502-003

INTENTIONALLY BLANK

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

MANEUVER CAPABILITY ISA CONDITIONS

80500 lb 21000 ft 76000 lb 23000 ft

71500 lb 25000 ft 27000 ft

67000 lb

62500 lb

58000 lb

29000 ft

33000 ft

37000 ft

0.30

0.35

0.40

0.45

0.50

0.55

0.60 MACH

0.65

0.70

0.75

0.80

0.85

1.00 0°

1.25 37°

1.50 48°

1.75 55°

2.00 60°

2.25 64°

2.50 66°

LOAD FACTOR BANK ANGLE

EM170AOM060014A.DGN

41000 ft

AOM-1502-003

"

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 3

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 4

Cruise

REVISION 18

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

BUFFET ONSET !EMBRAER 175 Models

AOM-1502-003

This chart provides the buffet margin (maneuver capability) and associated bank angles for a variety of cruise altitudes and weights as function of Mach number.

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 5

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 6

Cruise

REVISION 18

AOM-1502-003

INTENTIONALLY BLANK

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

MANEUVER CAPABILITY EMBRAER 175

80000 lb

21000 ft 23000 ft

76000 lb 72000 lb 25000 ft 68000 lb

64000 lb 27000 ft

60000 lb

29000 ft 31000 ft

33000 ft 35000 ft 37000 ft 39000 ft

0.30

0.35

0.40

0.45

0.50

0.55

0.60

0.65 MACH

0.70

0.75

0.80

0.85

1.00 0°

1.25 37°

1.50 48°

1.75 55°

2.00 60°

2.25 64°

2.50 66°

LOAD FACTOR BANK ANGLE

EM170AOM060065B.DGN

41000 ft

AOM-1502-003

"

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 7

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 8

Cruise

REVISION 18

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE !EMBRAER 170 Models

These tables show N1, fuel flow, indicated airspeed, true airspeed, indicated Mach number, buffet margin and specific range. Data are presented for various weights and altitudes. Correction for ISA deviation and anti-ice are also presented. In the long range cruise schedule (LRC), the airplane is flown at a speed corresponding to a specific range equal to 99% of maximum specific range. It is used when range is the main factor. The associated conditions are:

AOM-1502-003

Flaps.......................................................................... UP Gear........................................................................... UP Bleeds........................................................................ OPEN Anti-ice....................................................................... OFF Center of gravity........................................................ 18% Minimum Remaining Rate of Climb.......................... 300 ft/min

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 9

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

N1 % 65.5 68.4 69.2 69.9 70.6 71.4 72.6 73.8 Fuel Flow lb/h/Eng 1865 1800 1793 1782 1782 1785 1818 1846 IAS kt 269 266 266 265 263 261 264 267 84000 TAS kt 289 307 311 315 317 320 329 337 Ind. MACH 0.44 0.48 0.49 0.50 0.50 0.51 0.52 0.54 Buffet Marg G 2.22 2.15 2.14 2.12 2.09 2.06 2.10 2.14 SR NM/lb 0.077 0.085 0.087 0.088 0.089 0.090 0.090 0.091 N1 % 64.8 67.7 68.5 69.4 69.9 70.7 71.7 72.9 Fuel Flow lb/h/Eng 1819 1755 1750 1744 1736 1738 1757 1787 IAS kt 266 263 262 262 261 259 260 263 82000 TAS kt 285 303 307 312 315 317 323 332 Ind. MACH 0.44 0.47 0.48 0.49 0.50 0.50 0.52 0.53 Buffet Marg G 2.22 2.15 2.14 2.14 2.11 2.08 2.08 2.12 SR NM/lb 0.078 0.086 0.088 0.089 0.091 0.091 0.092 0.093 N1 % 64.3 67.0 67.8 68.7 69.3 70.2 71.0 71.8 Fuel Flow lb/h/Eng 1787 1709 1706 1703 1693 1696 1703 1714 IAS kt 264 259 259 259 259 258 257 257 80000 TAS kt 283 299 304 308 312 316 319 324 Ind. MACH 0.44 0.47 0.48 0.49 0.49 0.50 0.51 0.52 Buffet Marg G 2.25 2.14 2.14 2.14 2.12 2.10 2.08 2.08 SR NM/lb 0.079 0.087 0.089 0.091 0.092 0.093 0.094 0.095 N1 % 63.5 66.2 67.1 67.9 68.7 69.5 70.2 70.8 Fuel Flow lb/h/Eng 1739 1663 1662 1659 1655 1649 1655 1649 IAS kt 260 256 256 256 256 255 254 252 78000 TAS kt 279 295 300 304 309 313 316 318 Ind. MACH 0.43 0.46 0.47 0.48 0.49 0.50 0.50 0.51 Buffet Marg G 2.24 2.14 2.14 2.14 2.13 2.12 2.09 2.05 SR NM/lb 0.080 0.089 0.090 0.092 0.093 0.095 0.096 0.096 N1 % 62.8 65.6 66.4 67.1 68.1 68.8 69.5 70.1 Fuel Flow lb/h/Eng 1697 1623 1617 1612 1614 1610 1606 1597 IAS kt 257 253 252 252 253 253 252 249 76000 TAS kt 276 292 296 300 305 310 313 314 Ind. MACH 0.42 0.46 0.47 0.47 0.48 0.49 0.50 0.50 Buffet Marg G 2.25 2.15 2.14 2.13 2.14 2.14 2.11 2.05 SR NM/lb 0.081 0.090 0.091 0.093 0.095 0.096 0.098 0.098 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 3% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 1.0% AND FUEL FLOW BY 7.4%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 6.2%.

74.8 1857 269 344 0.55 2.15 0.093 74.1 1806 265 340 0.55 2.15 0.094 73.2 1749 261 334 0.54 2.14 0.096 72.3 1691 256 329 0.53 2.12 0.097 71.3 1624 251 322 0.52 2.08 0.099

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Page 10

Cruise

REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

AOM-1502-003

N1 % 62.1 65.0 65.6 66.4 67.3 68.2 68.7 69.5 Fuel Flow lb/h/Eng 1659 1587 1572 1566 1571 1574 1558 1558 IAS kt 255 250 249 249 249 250 249 247 74000 TAS kt 273 288 292 296 301 307 310 313 Ind. MACH 0.42 0.45 0.46 0.47 0.48 0.49 0.49 0.50 Buffet Marg G 2.26 2.16 2.14 2.13 2.14 2.15 2.12 2.09 SR NM/lb 0.082 0.091 0.093 0.094 0.096 0.098 0.099 0.100 N1 % 61.5 64.5 65.1 65.8 66.6 67.5 68.1 68.7 Fuel Flow lb/h/Eng 1624 1551 1537 1525 1529 1533 1521 1509 IAS kt 252 247 246 246 246 247 246 245 72000 TAS kt 270 285 289 292 297 303 306 310 Ind. MACH 0.42 0.45 0.45 0.46 0.47 0.48 0.49 0.50 Buffet Marg G 2.27 2.17 2.15 2.13 2.14 2.15 2.13 2.10 SR NM/lb 0.083 0.092 0.094 0.096 0.097 0.099 0.101 0.103 N1 % 61.0 63.9 64.6 65.2 66.0 66.8 67.5 68.2 Fuel Flow lb/h/Eng 1590 1515 1505 1491 1489 1490 1482 1470 IAS kt 249 245 244 243 243 244 243 242 70000 TAS kt 267 283 286 289 294 299 303 306 Ind. MACH 0.41 0.44 0.45 0.46 0.47 0.48 0.48 0.49 Buffet Marg G 2.29 2.19 2.17 2.15 2.15 2.16 2.14 2.12 SR NM/lb 0.084 0.093 0.095 0.097 0.099 0.100 0.102 0.104 N1 % 60.3 63.4 64.1 64.7 65.3 66.0 66.8 67.6 Fuel Flow lb/h/Eng 1554 1479 1470 1459 1453 1451 1442 1433 IAS kt 246 242 241 241 241 241 240 239 68000 TAS kt 264 279 283 287 291 296 299 303 Ind. MACH 0.41 0.44 0.45 0.45 0.46 0.47 0.48 0.49 Buffet Marg G 2.30 2.20 2.19 2.18 2.17 2.17 2.15 2.13 SR NM/lb 0.085 0.095 0.096 0.098 0.100 0.102 0.104 0.106 N1 % 59.7 62.8 63.5 64.2 64.8 65.4 66.2 67.0 Fuel Flow lb/h/Eng 1517 1441 1433 1424 1420 1415 1404 1393 IAS kt 243 239 239 238 238 238 237 236 66000 TAS kt 261 276 280 284 288 293 296 299 Ind. MACH 0.40 0.43 0.44 0.45 0.46 0.47 0.47 0.48 Buffet Marg G 2.31 2.22 2.21 2.20 2.19 2.19 2.16 2.14 SR NM/lb 0.086 0.096 0.098 0.100 0.101 0.103 0.105 0.107 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 3% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 7 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 1.1% AND FUEL FLOW BY 8.9%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 7.3%.

70.4 1565 247 316 0.51 2.07 0.101 69.6 1516 244 313 0.50 2.08 0.103 68.8 1467 241 310 0.50 2.10 0.106 68.2 1429 239 308 0.49 2.13 0.108 67.6 1390 236 304 0.49 2.14 0.109

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 11

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

N1 % 59.0 62.2 62.9 63.6 64.2 64.9 65.6 66.4 Fuel Flow lb/h/Eng 1477 1404 1397 1388 1389 1387 1371 1360 IAS kt 240 236 236 235 236 237 235 234 64000 TAS kt 258 273 277 280 285 290 293 296 Ind. MACH 0.40 0.43 0.44 0.44 0.45 0.46 0.47 0.47 Buffet Marg G 2.32 2.24 2.23 2.21 2.22 2.22 2.19 2.17 SR NM/lb 0.087 0.097 0.099 0.101 0.103 0.105 0.107 0.109 N1 % 58.3 61.6 62.3 62.9 63.7 64.4 65.1 65.9 Fuel Flow lb/h/Eng 1438 1373 1363 1351 1358 1360 1344 1331 IAS kt 237 235 234 233 234 235 234 233 62000 TAS kt 254 271 274 277 283 288 291 294 Ind. MACH 0.39 0.42 0.43 0.44 0.45 0.46 0.46 0.47 Buffet Marg G 2.33 2.27 2.25 2.23 2.25 2.26 2.23 2.21 SR NM/lb 0.088 0.099 0.101 0.103 0.104 0.106 0.108 0.111 N1 % 57.6 61.3 61.7 62.2 63.1 63.9 64.7 65.5 Fuel Flow lb/h/Eng 1400 1356 1328 1310 1325 1333 1321 1307 IAS kt 234 234 231 229 232 233 232 232 60000 TAS kt 251 270 271 273 280 286 290 293 Ind. MACH 0.39 0.42 0.43 0.43 0.44 0.46 0.46 0.47 Buffet Marg G 2.35 2.34 2.28 2.24 2.28 2.30 2.29 2.26 SR NM/lb 0.090 0.100 0.102 0.104 0.106 0.107 0.110 0.112 N1 % 57.1 60.9 61.2 61.6 62.6 63.5 64.3 65.2 Fuel Flow lb/h/Eng 1370 1331 1305 1279 1296 1312 1298 1286 IAS kt 232 232 230 227 230 232 231 230 58000 TAS kt 249 268 270 271 278 285 288 292 Ind. MACH 0.38 0.42 0.42 0.43 0.44 0.45 0.46 0.47 Buffet Marg G 2.39 2.38 2.33 2.27 2.32 2.37 2.34 2.32 SR NM/lb 0.091 0.101 0.103 0.106 0.107 0.109 0.111 0.113 N1 % 56.5 60.5 60.9 61.1 62.1 63.0 63.8 64.5 Fuel Flow lb/h/Eng 1336 1311 1289 1256 1274 1284 1274 1258 IAS kt 229 231 229 226 229 230 230 228 56000 TAS kt 246 267 269 269 277 283 286 289 Ind. MACH 0.38 0.42 0.42 0.42 0.44 0.45 0.46 0.46 Buffet Marg G 2.42 2.44 2.40 2.33 2.38 2.41 2.39 2.36 SR NM/lb 0.092 0.102 0.104 0.107 0.109 0.110 0.112 0.115 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 6% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 12 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 1.2% AND FUEL FLOW BY10.0%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 8.4%.

67.0 1354 234 300 0.48 2.16 0.111 66.4 1319 231 297 0.48 2.18 0.113 65.9 1288 229 295 0.47 2.21 0.114 65.4 1261 228 293 0.47 2.26 0.116 64.9 1237 226 291 0.47 2.31 0.117

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 12

Cruise

REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

AOM-1502-003

N1 % 56.1 60.1 60.4 60.8 61.6 62.4 63.2 63.8 Fuel Flow lb/h/Eng 1315 1287 1263 1242 1245 1255 1243 1226 IAS kt 228 230 227 226 227 229 227 225 54000 TAS kt 245 265 267 269 274 281 283 285 Ind. MACH 0.38 0.42 0.42 0.42 0.43 0.45 0.45 0.46 Buffet Marg G 2.48 2.50 2.45 2.41 2.43 2.46 2.43 2.38 SR NM/lb 0.093 0.103 0.106 0.108 0.110 0.112 0.114 0.116 N1 % 55.8 59.3 59.8 60.4 61.0 61.6 62.2 62.9 Fuel Flow lb/h/Eng 1296 1256 1237 1220 1219 1214 1200 1189 IAS kt 227 227 225 224 225 224 223 222 52000 TAS kt 243 262 264 267 272 276 278 281 Ind. MACH 0.37 0.41 0.42 0.42 0.43 0.44 0.44 0.45 Buffet Marg G 2.50 2.50 2.50 2.47 2.47 2.47 2.43 2.40 SR NM/lb 0.094 0.104 0.107 0.109 0.111 0.114 0.116 0.118 N1 % 55.5 58.5 59.1 59.8 60.4 60.7 61.2 61.8 Fuel Flow lb/h/Eng 1278 1221 1209 1195 1188 1171 1153 1144 IAS kt 225 223 223 222 222 219 218 217 50000 TAS kt 242 258 261 265 268 270 272 275 Ind. MACH 0.37 0.40 0.41 0.42 0.42 0.43 0.43 0.44 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.46 2.41 2.39 SR NM/lb 0.095 0.106 0.108 0.111 0.113 0.115 0.118 0.120 N1 % 55.1 57.4 58.4 59.1 59.4 59.4 60.0 60.6 Fuel Flow lb/h/Eng 1260 1178 1176 1166 1148 1119 1108 1096 IAS kt 224 219 220 220 217 213 212 211 48000 TAS kt 241 253 258 262 263 262 265 268 Ind. MACH 0.37 0.40 0.41 0.41 0.42 0.42 0.42 0.43 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.41 2.38 2.36 SR NM/lb 0.096 0.107 0.110 0.112 0.114 0.117 0.119 0.122 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 6% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 11 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.6% AND FUEL FLOW BY10.6%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 8.6%.

64.3 1211 224 288 0.46 2.35 0.119 63.7 1181 222 285 0.46 2.39 0.121 62.7 1143 218 280 0.45 2.40 0.123 61.6 1097 212 274 0.44 2.39 0.125

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 13

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

N1 % 75.6 76.1 76.6 77.2 77.7 78.5 79.2 79.7 Fuel Flow lb/h/Eng 1856 1845 1828 1782 1767 1765 1767 1746 IAS kt 269 268 267 266 265 264 264 260 84000 TAS kt 350 354 357 362 366 371 376 378 Ind. MACH 0.56 0.57 0.58 0.59 0.60 0.61 0.62 0.63 Buffet Marg G 2.13 2.10 2.05 2.02 1.97 1.94 1.90 1.84 SR NM/lb 0.094 0.096 0.098 0.102 0.104 0.105 0.106 0.108 N1 % 75.1 75.7 76.2 76.8 77.3 77.9 78.6 79.2 Fuel Flow lb/h/Eng 1815 1806 1790 1747 1731 1723 1727 1709 IAS kt 267 266 264 263 262 261 261 259 82000 TAS kt 347 351 355 359 363 367 373 375 Ind. MACH 0.56 0.57 0.58 0.59 0.60 0.61 0.62 0.62 Buffet Marg G 2.15 2.12 2.08 2.04 2.00 1.96 1.93 1.87 SR NM/lb 0.095 0.097 0.099 0.103 0.105 0.107 0.108 0.110 N1 % 74.4 75.1 75.7 76.3 76.8 77.3 78.0 78.6 Fuel Flow lb/h/Eng 1767 1764 1754 1712 1696 1684 1684 1670 IAS kt 263 263 262 261 260 259 259 256 80000 TAS kt 342 347 352 356 360 364 370 372 Ind. MACH 0.55 0.56 0.57 0.58 0.59 0.60 0.61 0.62 Buffet Marg G 2.16 2.14 2.10 2.07 2.03 1.99 1.95 1.89 SR NM/lb 0.097 0.098 0.100 0.104 0.106 0.108 0.110 0.111 N1 % 73.5 74.5 75.3 75.8 76.3 76.9 77.4 78.0 Fuel Flow lb/h/Eng 1714 1719 1715 1674 1657 1652 1642 1629 IAS kt 259 260 260 259 257 257 256 254 78000 TAS kt 337 343 349 353 356 362 366 369 Ind. MACH 0.54 0.56 0.57 0.58 0.58 0.60 0.61 0.61 Buffet Marg G 2.16 2.15 2.13 2.09 2.05 2.02 1.97 1.92 SR NM/lb 0.098 0.100 0.102 0.105 0.107 0.109 0.111 0.113 N1 % 72.7 73.7 74.6 75.3 75.9 76.4 76.8 77.5 Fuel Flow lb/h/Eng 1659 1669 1671 1633 1622 1616 1605 1594 IAS kt 255 256 257 256 255 255 254 252 76000 TAS kt 332 339 345 349 353 358 363 366 Ind. MACH 0.54 0.55 0.56 0.57 0.58 0.59 0.60 0.61 Buffet Marg G 2.14 2.16 2.14 2.11 2.07 2.04 2.00 1.95 SR NM/lb 0.100 0.101 0.103 0.107 0.109 0.111 0.113 0.115 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 3% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 7 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.8% AND FUEL FLOW BY 7.1%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 6.0%.

80.3 1733 258 381 0.64 1.79 0.110 79.9 1697 257 379 0.63 1.82 0.112 79.3 1658 254 375 0.63 1.85 0.113 78.8 1620 252 373 0.62 1.87 0.115 78.2 1578 250 369 0.62 1.90 0.117

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 14

Cruise

REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

AOM-1502-003

N1 % 71.7 72.8 73.8 74.6 75.4 75.8 76.2 76.9 Fuel Flow lb/h/Eng 1600 1614 1620 1591 1585 1578 1570 1552 IAS kt 250 252 253 253 252 252 251 250 74000 TAS kt 326 333 339 345 350 355 359 363 Ind. MACH 0.53 0.54 0.55 0.56 0.57 0.58 0.59 0.60 Buffet Marg G 2.12 2.14 2.15 2.13 2.10 2.07 2.03 1.98 SR NM/lb 0.102 0.103 0.105 0.108 0.110 0.112 0.114 0.117 N1 % 70.6 71.9 72.9 73.9 74.8 75.3 75.6 76.3 Fuel Flow lb/h/Eng 1527 1557 1566 1546 1546 1541 1532 1517 IAS kt 244 247 248 249 250 249 248 247 72000 TAS kt 318 327 334 341 346 351 355 359 Ind. MACH 0.51 0.53 0.54 0.56 0.57 0.58 0.59 0.60 Buffet Marg G 2.07 2.13 2.14 2.14 2.12 2.09 2.05 2.01 SR NM/lb 0.104 0.105 0.106 0.110 0.112 0.114 0.116 0.118 N1 % 69.7 70.8 72.1 73.1 74.1 74.6 75.1 75.8 Fuel Flow lb/h/Eng 1475 1489 1511 1496 1503 1500 1494 1481 IAS kt 240 241 244 245 247 246 246 245 70000 TAS kt 314 319 328 335 342 347 352 356 Ind. MACH 0.51 0.52 0.53 0.55 0.56 0.57 0.58 0.59 Buffet Marg G 2.08 2.08 2.12 2.15 2.14 2.11 2.08 2.04 SR NM/lb 0.106 0.107 0.108 0.112 0.114 0.116 0.118 0.120 N1 % 68.9 70.0 71.2 72.3 73.4 73.9 74.4 75.2 Fuel Flow lb/h/Eng 1424 1437 1457 1445 1457 1457 1452 1443 IAS kt 237 238 239 241 243 243 242 242 68000 TAS kt 310 315 322 330 337 342 347 352 Ind. MACH 0.50 0.51 0.52 0.54 0.55 0.56 0.57 0.58 Buffet Marg G 2.09 2.09 2.11 2.14 2.15 2.13 2.10 2.06 SR NM/lb 0.109 0.110 0.111 0.114 0.116 0.118 0.120 0.122 N1 % 68.1 69.4 70.6 71.6 72.5 73.2 73.8 74.7 Fuel Flow lb/h/Eng 1376 1402 1416 1400 1407 1412 1411 1411 IAS kt 235 237 237 238 239 239 239 240 66000 TAS kt 306 314 319 325 332 338 343 349 Ind. MACH 0.49 0.51 0.52 0.53 0.54 0.56 0.57 0.58 Buffet Marg G 2.11 2.13 2.13 2.14 2.15 2.14 2.12 2.10 SR NM/lb 0.111 0.112 0.113 0.116 0.118 0.120 0.121 0.124 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 3% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 8 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 1.0% AND FUEL FLOW BY 7.9%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 7.0%.

77.6 1538 247 366 0.61 1.93 0.119 77.0 1495 245 362 0.60 1.95 0.121 76.5 1467 244 360 0.60 2.00 0.123 76.0 1433 241 357 0.60 2.03 0.125 75.7 1407 240 355 0.59 2.08 0.126

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 15

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

N1 % 67.4 68.7 70.0 70.9 71.7 72.4 73.1 74.2 Fuel Flow lb/h/Eng 1336 1359 1382 1354 1356 1364 1366 1375 IAS kt 232 235 236 235 234 235 235 237 64000 TAS kt 302 311 318 321 326 332 338 346 Ind. MACH 0.49 0.50 0.52 0.52 0.53 0.55 0.56 0.57 Buffet Marg G 2.11 2.16 2.19 2.15 2.14 2.15 2.13 2.13 SR NM/lb 0.113 0.114 0.115 0.118 0.120 0.122 0.124 0.126 N1 % 66.9 68.0 69.3 70.1 70.9 71.7 72.4 73.5 Fuel Flow lb/h/Eng 1305 1321 1343 1313 1311 1317 1320 1335 IAS kt 229 232 234 232 231 231 232 234 62000 TAS kt 300 308 316 318 321 327 333 341 Ind. MACH 0.48 0.50 0.51 0.52 0.53 0.54 0.55 0.57 Buffet Marg G 2.14 2.19 2.22 2.18 2.15 2.15 2.15 2.16 SR NM/lb 0.115 0.116 0.118 0.121 0.123 0.124 0.126 0.128 N1 % 66.3 67.4 68.5 69.4 70.4 71.0 71.6 72.6 Fuel Flow lb/h/Eng 1270 1285 1302 1278 1278 1275 1271 1292 IAS kt 227 229 232 231 230 228 227 230 60000 TAS kt 296 304 312 316 320 323 327 336 Ind. MACH 0.48 0.49 0.51 0.52 0.52 0.53 0.54 0.56 Buffet Marg G 2.17 2.20 2.25 2.23 2.20 2.17 2.15 2.18 SR NM/lb 0.117 0.118 0.120 0.124 0.125 0.127 0.129 0.130 N1 % 65.8 66.8 67.8 68.6 69.7 70.2 70.9 71.7 Fuel Flow lb/h/Eng 1244 1256 1268 1238 1242 1232 1228 1250 IAS kt 226 227 229 229 228 225 224 227 58000 TAS kt 295 301 308 313 318 319 323 331 Ind. MACH 0.48 0.49 0.50 0.51 0.52 0.53 0.53 0.55 Buffet Marg G 2.22 2.24 2.27 2.26 2.25 2.19 2.16 2.20 SR NM/lb 0.118 0.120 0.122 0.127 0.128 0.129 0.131 0.133 N1 % 65.4 66.2 67.0 67.8 68.6 69.5 70.4 70.9 Fuel Flow lb/h/Eng 1219 1226 1232 1204 1198 1197 1195 1212 IAS kt 224 225 225 225 225 224 223 224 56000 TAS kt 293 299 304 309 314 317 320 327 Ind. MACH 0.47 0.48 0.49 0.50 0.51 0.52 0.53 0.54 Buffet Marg G 2.27 2.28 2.28 2.28 2.27 2.24 2.21 2.23 SR NM/lb 0.120 0.122 0.123 0.128 0.131 0.132 0.134 0.135 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 6% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 13 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.7% AND FUEL FLOW BY 9.8%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 8.2%.

75.3 1381 239 353 0.59 2.12 0.128 74.6 1348 236 350 0.58 2.16 0.130 73.7 1311 233 346 0.58 2.19 0.132 72.7 1270 230 341 0.57 2.21 0.134 71.6 1228 226 335 0.56 2.24 0.136

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 16

Cruise

REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

AOM-1502-003

N1 % 65.0 65.5 66.1 67.0 67.8 68.7 69.8 70.0 Fuel Flow lb/h/Eng 1197 1189 1188 1165 1162 1159 1166 1171 IAS kt 223 222 221 221 222 222 222 221 54000 TAS kt 292 294 298 304 309 314 319 323 Ind. MACH 0.47 0.48 0.49 0.50 0.51 0.52 0.53 0.54 Buffet Marg G 2.33 2.30 2.28 2.28 2.29 2.28 2.28 2.25 SR NM/lb 0.122 0.124 0.125 0.130 0.133 0.136 0.137 0.138 N1 % 64.4 64.7 65.1 66.0 66.9 67.8 68.8 68.7 Fuel Flow lb/h/Eng 1172 1156 1141 1124 1124 1122 1124 1118 IAS kt 221 218 216 217 218 219 219 216 52000 TAS kt 289 290 291 298 304 310 315 316 Ind. MACH 0.47 0.47 0.47 0.49 0.50 0.51 0.52 0.53 Buffet Marg G 2.38 2.32 2.26 2.28 2.29 2.30 2.31 2.24 SR NM/lb 0.123 0.126 0.128 0.133 0.135 0.138 0.140 0.141 N1 % 63.6 63.8 64.1 64.9 65.7 66.9 67.8 67.4 Fuel Flow lb/h/Eng 1138 1121 1104 1078 1073 1085 1085 1068 IAS kt 218 215 212 212 212 215 216 212 50000 TAS kt 285 286 287 291 296 304 311 310 Ind. MACH 0.46 0.46 0.47 0.48 0.49 0.50 0.51 0.52 Buffet Marg G 2.40 2.33 2.27 2.27 2.26 2.31 2.33 2.24 SR NM/lb 0.125 0.127 0.130 0.135 0.138 0.140 0.143 0.145 N1 % 62.6 62.9 63.2 64.0 64.5 65.6 66.9 66.3 Fuel Flow lb/h/Eng 1101 1084 1069 1041 1025 1034 1047 1021 IAS kt 214 211 209 208 206 209 212 207 48000 TAS kt 280 281 282 286 288 296 305 304 Ind. MACH 0.45 0.46 0.46 0.47 0.47 0.49 0.50 0.50 Buffet Marg G 2.42 2.35 2.29 2.28 2.23 2.27 2.33 2.24 SR NM/lb 0.127 0.129 0.132 0.137 0.141 0.143 0.146 0.149 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 4% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 8 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.8% AND FUEL FLOW BY10.0%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 8.5%.

70.2 1172 220 327 0.55 2.22 0.139 68.7 1112 213 318 0.53 2.18 0.143 67.3 1054 208 309 0.52 2.15 0.147 66.3 1006 204 304 0.51 2.16 0.151

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REVISION 18

Cruise

Page 17

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

N1 % 80.8 81.7 82.9 84.1 85.0 85.8 86.6 87.0 Fuel Flow lb/h/Eng 1718 1733 1782 1826 1844 1845 1829 1777 IAS kt 256 255 258 261 261 260 256 246 84000 TAS kt 384 389 399 410 417 421 422 414 Ind. MACH 0.64 0.65 0.67 0.70 0.71 0.72 0.73 0.71 Buffet Marg G 1.74 1.70 1.69 1.67 1.63 1.58 1.52 1.42 SR NM/lb 0.112 0.112 0.112 0.112 0.113 0.114 0.115 0.116 N1 % 80.3 80.9 82.1 83.2 84.4 85.4 86.1 86.4 Fuel Flow lb/h/Eng 1680 1669 1713 1756 1794 1817 1798 1745 IAS kt 254 252 254 256 259 260 256 247 82000 TAS kt 381 384 393 403 413 422 422 416 Ind. MACH 0.64 0.65 0.66 0.68 0.70 0.72 0.73 0.72 Buffet Marg G 1.76 1.71 1.69 1.68 1.65 1.62 1.55 1.47 SR NM/lb 0.113 0.115 0.115 0.115 0.115 0.116 0.117 0.119 N1 % 79.9 80.5 81.3 82.4 83.6 84.7 85.5 85.9 Fuel Flow lb/h/Eng 1645 1634 1647 1686 1730 1766 1760 1722 IAS kt 252 250 250 252 255 257 254 249 80000 TAS kt 378 382 387 396 407 418 420 418 Ind. MACH 0.63 0.64 0.65 0.67 0.69 0.72 0.72 0.72 Buffet Marg G 1.79 1.74 1.71 1.68 1.67 1.64 1.59 1.51 SR NM/lb 0.115 0.117 0.118 0.118 0.118 0.118 0.119 0.121 N1 % 79.4 80.1 80.5 81.6 82.8 83.9 84.9 85.6 Fuel Flow lb/h/Eng 1610 1602 1587 1618 1660 1699 1718 1704 IAS kt 251 249 247 247 250 253 253 250 78000 TAS kt 376 380 383 390 400 411 418 420 Ind. MACH 0.63 0.64 0.65 0.66 0.68 0.70 0.72 0.73 Buffet Marg G 1.82 1.78 1.72 1.70 1.67 1.65 1.62 1.56 SR NM/lb 0.117 0.119 0.121 0.120 0.120 0.121 0.122 0.123 N1 % 78.9 79.5 80.0 80.8 81.9 83.1 84.2 85.2 Fuel Flow lb/h/Eng 1572 1565 1551 1553 1593 1631 1668 1688 IAS kt 248 247 245 244 245 248 251 252 76000 TAS kt 373 377 380 384 393 403 414 423 Ind. MACH 0.62 0.63 0.64 0.65 0.67 0.69 0.71 0.73 Buffet Marg G 1.85 1.81 1.75 1.71 1.69 1.67 1.64 1.61 SR NM/lb 0.119 0.120 0.122 0.124 0.123 0.124 0.124 0.125 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 3% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 7 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.7% AND FUEL FLOW BY 7.2%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 6.5%.

86.8 1703 242 414 0.72 1.44 0.122 86.3 1681 244 419 0.73 1.49 0.125 85.8 1657 246 420 0.73 1.53 0.127

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Page 18

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REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

AOM-1502-003

N1 % 78.3 78.9 79.5 80.2 81.2 82.3 83.4 84.6 Fuel Flow lb/h/Eng 1533 1525 1516 1508 1531 1565 1604 1638 IAS kt 246 245 243 242 242 243 246 249 74000 TAS kt 370 374 377 381 388 397 407 419 Ind. MACH 0.62 0.63 0.64 0.65 0.66 0.68 0.70 0.72 Buffet Marg G 1.88 1.83 1.78 1.74 1.71 1.68 1.66 1.64 SR NM/lb 0.121 0.122 0.124 0.126 0.127 0.127 0.127 0.128 N1 % 77.7 78.3 79.0 79.7 80.3 81.4 82.6 83.7 Fuel Flow lb/h/Eng 1493 1486 1479 1473 1467 1497 1535 1572 IAS kt 244 242 241 240 238 239 241 244 72000 TAS kt 366 370 374 379 382 389 400 411 Ind. MACH 0.61 0.62 0.63 0.64 0.65 0.67 0.69 0.71 Buffet Marg G 1.91 1.86 1.82 1.77 1.72 1.69 1.67 1.65 SR NM/lb 0.123 0.125 0.126 0.129 0.130 0.130 0.130 0.131 N1 % 77.1 77.7 78.4 79.0 79.7 80.6 81.7 82.9 Fuel Flow lb/h/Eng 1451 1445 1439 1433 1428 1442 1470 1506 IAS kt 241 240 238 237 236 236 237 239 70000 TAS kt 363 367 370 375 379 385 393 403 Ind. MACH 0.61 0.62 0.63 0.64 0.65 0.66 0.68 0.70 Buffet Marg G 1.94 1.89 1.84 1.80 1.75 1.72 1.68 1.66 SR NM/lb 0.125 0.127 0.129 0.131 0.133 0.134 0.134 0.134 N1 % 76.6 77.1 77.7 78.4 79.2 80.0 80.9 81.9 Fuel Flow lb/h/Eng 1421 1405 1400 1394 1397 1397 1415 1437 IAS kt 240 237 236 235 235 234 234 234 68000 TAS kt 361 363 367 371 377 383 388 395 Ind. MACH 0.60 0.61 0.62 0.63 0.64 0.66 0.67 0.68 Buffet Marg G 1.98 1.92 1.87 1.83 1.79 1.75 1.71 1.67 SR NM/lb 0.127 0.129 0.131 0.133 0.135 0.137 0.137 0.137 N1 % 76.1 76.4 77.1 77.7 78.5 79.3 80.0 81.0 Fuel Flow lb/h/Eng 1392 1365 1361 1353 1359 1364 1355 1371 IAS kt 238 235 233 232 232 232 230 229 66000 TAS kt 359 359 363 367 373 380 382 388 Ind. MACH 0.60 0.60 0.61 0.62 0.64 0.65 0.66 0.67 Buffet Marg G 2.02 1.95 1.91 1.86 1.82 1.79 1.73 1.69 SR NM/lb 0.129 0.132 0.134 0.136 0.137 0.139 0.141 0.141 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 4% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 9 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.5% AND FUEL FLOW BY 8.2%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 7.0%.

85.2 1616 244 418 0.72 1.56 0.129 84.8 1591 244 419 0.73 1.61 0.132 84.0 1539 242 414 0.72 1.64 0.134 83.1 1473 236 406 0.70 1.65 0.138 82.2 1406 231 398 0.69 1.67 0.142

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REVISION 18

Cruise

Page 19

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

N1 % 75.6 76.1 76.5 77.1 77.8 78.6 79.3 80.3 Fuel Flow lb/h/Eng 1362 1341 1325 1314 1320 1328 1316 1328 IAS kt 236 234 232 229 229 230 228 228 64000 TAS kt 356 358 360 363 369 376 380 386 Ind. MACH 0.60 0.60 0.61 0.62 0.63 0.64 0.65 0.67 Buffet Marg G 2.06 2.01 1.94 1.89 1.85 1.82 1.77 1.73 SR NM/lb 0.131 0.134 0.136 0.138 0.140 0.142 0.144 0.145 N1 % 75.0 75.6 76.0 76.4 77.2 77.9 78.6 79.4 Fuel Flow lb/h/Eng 1330 1313 1290 1273 1282 1291 1284 1276 IAS kt 234 232 230 227 227 227 226 225 62000 TAS kt 353 356 358 359 366 372 377 381 Ind. MACH 0.59 0.60 0.60 0.61 0.62 0.64 0.65 0.66 Buffet Marg G 2.11 2.05 1.99 1.92 1.89 1.86 1.81 1.76 SR NM/lb 0.133 0.136 0.139 0.141 0.143 0.144 0.147 0.149 N1 % 74.4 75.2 75.6 75.9 76.6 77.2 77.9 78.6 Fuel Flow lb/h/Eng 1298 1288 1269 1243 1251 1253 1247 1240 IAS kt 232 231 229 225 225 225 223 222 60000 TAS kt 349 354 357 357 363 368 373 377 Ind. MACH 0.59 0.60 0.60 0.61 0.62 0.63 0.64 0.65 Buffet Marg G 2.15 2.10 2.04 1.97 1.93 1.89 1.84 1.80 SR NM/lb 0.135 0.138 0.140 0.144 0.145 0.147 0.149 0.152 N1 % 73.7 74.6 75.0 75.6 75.9 76.4 77.1 77.9 Fuel Flow lb/h/Eng 1265 1256 1239 1223 1216 1215 1210 1204 IAS kt 229 229 227 225 223 222 221 220 58000 TAS kt 346 351 353 357 360 364 369 373 Ind. MACH 0.58 0.59 0.60 0.61 0.61 0.62 0.63 0.64 Buffet Marg G 2.19 2.15 2.09 2.03 1.98 1.93 1.88 1.83 SR NM/lb 0.137 0.140 0.143 0.146 0.148 0.150 0.152 0.155 N1 % 72.7 73.7 74.3 75.1 75.4 75.6 76.4 77.1 Fuel Flow lb/h/Eng 1225 1220 1208 1197 1193 1177 1172 1167 IAS kt 226 226 225 224 223 219 218 217 56000 TAS kt 341 346 350 355 359 360 364 369 Ind. MACH 0.57 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G 2.21 2.18 2.14 2.09 2.04 1.97 1.92 1.87 SR NM/lb 0.139 0.142 0.145 0.148 0.151 0.153 0.155 0.158 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 5% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 13 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.6% AND FUEL FLOW BY 8.6%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 7.3%.

81.3 1347 228 392 0.68 1.69 0.145 80.4 1290 224 386 0.67 1.71 0.150 79.5 1239 221 382 0.66 1.75 0.154 78.7 1200 219 378 0.66 1.79 0.158 77.9 1165 217 374 0.65 1.83 0.161

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Page 20

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REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

AOM-1502-003

N1 % 71.6 72.7 73.6 74.4 74.7 74.8 75.6 76.3 Fuel Flow lb/h/Eng 1182 1179 1176 1168 1161 1138 1135 1131 IAS kt 222 222 222 222 220 216 216 214 54000 TAS kt 335 341 346 352 355 355 360 365 Ind. MACH 0.56 0.57 0.59 0.60 0.61 0.61 0.62 0.63 Buffet Marg G 2.23 2.21 2.18 2.14 2.09 2.01 1.96 1.91 SR NM/lb 0.142 0.144 0.147 0.150 0.153 0.156 0.159 0.161 N1 % 70.2 71.6 72.7 73.6 74.0 74.2 74.8 75.6 Fuel Flow lb/h/Eng 1127 1137 1140 1138 1129 1107 1097 1096 IAS kt 216 218 219 219 217 214 213 212 52000 TAS kt 326 335 342 348 351 351 356 361 Ind. MACH 0.55 0.56 0.58 0.59 0.60 0.60 0.61 0.62 Buffet Marg G 2.22 2.23 2.22 2.19 2.13 2.05 2.00 1.96 SR NM/lb 0.145 0.147 0.150 0.153 0.156 0.159 0.162 0.165 N1 % 68.8 70.3 71.7 72.7 73.2 73.5 74.1 74.8 Fuel Flow lb/h/Eng 1069 1084 1099 1102 1094 1074 1067 1059 IAS kt 210 212 215 216 214 211 210 209 50000 TAS kt 317 326 336 343 347 347 352 357 Ind. MACH 0.53 0.55 0.57 0.58 0.59 0.59 0.61 0.62 Buffet Marg G 2.18 2.23 2.25 2.23 2.18 2.10 2.05 2.00 SR NM/lb 0.148 0.151 0.153 0.156 0.158 0.162 0.165 0.168 N1 % 67.6 69.1 70.4 71.7 72.3 72.8 73.5 74.1 Fuel Flow lb/h/Eng 1014 1031 1050 1063 1056 1037 1034 1029 IAS kt 204 207 210 212 211 207 208 207 48000 TAS kt 309 318 328 338 341 342 348 353 Ind. MACH 0.52 0.54 0.55 0.57 0.58 0.58 0.60 0.61 Buffet Marg G 2.16 2.20 2.25 2.27 2.21 2.13 2.10 2.06 SR NM/lb 0.153 0.154 0.156 0.159 0.161 0.165 0.168 0.172 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 4% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 9 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.6% AND FUEL FLOW BY 8.9%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 7.3%.

77.1 1130 214 370 0.64 1.87 0.164 76.3 1093 211 366 0.63 1.91 0.167 75.5 1054 208 361 0.63 1.95 0.171 74.7 1016 205 356 0.62 2.00 0.175

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REVISION 18

Cruise

Page 21

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 36000 37000 38000 39000 40000 41000

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Page 22

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REVISION 18

AOM-1502-003

N1 % Fuel Flow lb/h/Eng IAS kt 84000 TAS kt Ind. MACH Buffet Marg G SR NM/lb N1 % Fuel Flow lb/h/Eng IAS kt 82000 TAS kt Ind. MACH Buffet Marg G SR NM/lb N1 % Fuel Flow lb/h/Eng IAS kt 80000 TAS kt Ind. MACH Buffet Marg G SR NM/lb N1 % 87.0 Fuel Flow lb/h/Eng 1641 IAS kt 234 78000 TAS kt 410 Ind. MACH 0.71 Buffet Marg G 1.39 SR NM/lb 0.125 N1 % 86.2 Fuel Flow lb/h/Eng 1599 IAS kt 235 76000 TAS kt 410 Ind. MACH 0.71 Buffet Marg G 1.43 SR NM/lb 0.128 INCREASE/DECREASE N1(%) BY 1% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.3% AND FUEL FLOW BY 5.5%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 5.8%.

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 36000 37000 38000 39000 40000 41000

AOM-1502-003

N1 % 85.8 87.1 Fuel Flow lb/h/Eng 1590 1575 IAS kt 239 231 74000 TAS kt 417 412 Ind. MACH 0.73 0.72 Buffet Marg G 1.49 1.41 SR NM/lb 0.131 0.131 N1 % 85.3 86.5 Fuel Flow lb/h/Eng 1568 1549 IAS kt 240 233 72000 TAS kt 419 416 Ind. MACH 0.73 0.72 Buffet Marg G 1.54 1.46 SR NM/lb 0.134 0.134 N1 % 84.9 85.8 86.7 Fuel Flow lb/h/Eng 1548 1517 1486 IAS kt 242 234 224 70000 TAS kt 421 417 410 Ind. MACH 0.73 0.73 0.72 Buffet Marg G 1.60 1.51 1.41 SR NM/lb 0.136 0.138 0.138 N1 % 84.3 85.3 86.0 Fuel Flow lb/h/Eng 1504 1490 1458 IAS kt 239 234 226 68000 TAS kt 417 418 414 Ind. MACH 0.73 0.73 0.72 Buffet Marg G 1.63 1.55 1.47 SR NM/lb 0.139 0.140 0.142 N1 % 83.4 84.7 85.6 Fuel Flow lb/h/Eng 1439 1456 1446 IAS kt 234 233 230 66000 TAS kt 409 417 419 Ind. MACH 0.71 0.73 0.73 Buffet Marg G 1.64 1.60 1.53 SR NM/lb 0.142 0.143 0.145 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 3% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 10 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.7% AND FUEL FLOW BY 7.6%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 6.5%.

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REVISION 18

Cruise

Page 23

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 36000 37000 38000 39000 40000 41000

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Page 24

Cruise

REVISION 18

AOM-1502-003

N1 % 82.5 84.0 85.2 86.3 Fuel Flow lb/h/Eng 1373 1419 1434 1421 IAS kt 229 232 232 227 64000 TAS kt 401 415 423 423 Ind. MACH 0.70 0.72 0.74 0.74 Buffet Marg G 1.66 1.64 1.60 1.52 SR NM/lb 0.146 0.146 0.148 0.149 N1 % 81.4 83.1 84.7 85.7 86.4 Fuel Flow lb/h/Eng 1306 1357 1410 1395 1362 IAS kt 224 228 233 227 218 62000 TAS kt 392 407 424 424 418 Ind. MACH 0.68 0.71 0.74 0.74 0.73 Buffet Marg G 1.67 1.66 1.65 1.57 1.48 SR NM/lb 0.150 0.150 0.150 0.152 0.153 N1 % 80.6 82.1 83.6 85.0 86.0 Fuel Flow lb/h/Eng 1253 1294 1342 1363 1353 IAS kt 221 223 226 227 222 60000 TAS kt 388 399 414 423 425 Ind. MACH 0.68 0.70 0.72 0.74 0.74 Buffet Marg G 1.71 1.68 1.66 1.62 1.55 SR NM/lb 0.155 0.154 0.154 0.155 0.157 N1 % 79.8 81.2 82.5 84.3 85.6 86.3 Fuel Flow lb/h/Eng 1214 1245 1276 1322 1340 1308 IAS kt 220 220 221 225 225 217 58000 TAS kt 386 394 404 420 429 424 Ind. MACH 0.67 0.69 0.70 0.73 0.75 0.74 Buffet Marg G 1.76 1.72 1.68 1.66 1.62 1.52 SR NM/lb 0.159 0.158 0.158 0.159 0.160 0.162 N1 % 78.7 80.1 81.5 83.1 84.9 85.5 Fuel Flow lb/h/Eng 1164 1185 1212 1254 1308 1270 IAS kt 216 215 215 219 225 215 56000 TAS kt 380 387 395 409 429 421 Ind. MACH 0.66 0.67 0.69 0.71 0.75 0.73 Buffet Marg G 1.79 1.74 1.70 1.68 1.68 1.57 SR NM/lb 0.163 0.163 0.163 0.163 0.164 0.166 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 6% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 16 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.7% AND FUEL FLOW BY 8.2%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 7.0%.

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 36000 37000 38000 39000 40000 41000

N1 % 77.9 78.8 80.4 81.9 83.4 84.8 Fuel Flow lb/h/Eng 1127 1121 1153 1186 1222 1242 IAS kt 213 210 211 212 215 215 54000 TAS kt 376 378 388 399 412 421 Ind. MACH 0.65 0.66 0.68 0.70 0.72 0.73 Buffet Marg G 1.83 1.76 1.72 1.69 1.67 1.63 SR NM/lb 0.167 0.169 0.168 0.168 0.169 0.170 N1 % 77.1 78.0 79.0 80.6 82.0 83.7 Fuel Flow lb/h/Eng 1089 1086 1083 1112 1138 1185 IAS kt 210 208 205 206 206 211 52000 TAS kt 371 374 378 387 397 413 Ind. MACH 0.65 0.65 0.66 0.68 0.69 0.72 Buffet Marg G 1.87 1.80 1.74 1.70 1.67 1.66 SR NM/lb 0.170 0.172 0.174 0.174 0.174 0.174 N1 % 76.2 77.2 78.0 79.3 80.8 82.4 Fuel Flow lb/h/Eng 1046 1046 1036 1050 1074 1109 IAS kt 206 205 201 201 201 204 50000 TAS kt 364 369 371 379 388 401 Ind. MACH 0.63 0.64 0.65 0.66 0.68 0.70 Buffet Marg G 1.90 1.84 1.77 1.73 1.69 1.67 SR NM/lb 0.174 0.176 0.179 0.181 0.181 0.181 N1 % 75.3 76.4 77.2 78.2 79.7 81.2 Fuel Flow lb/h/Eng 1008 1007 997 1000 1022 1048 IAS kt 203 202 198 197 198 199 48000 TAS kt 359 364 366 373 383 392 Ind. MACH 0.63 0.63 0.64 0.65 0.67 0.68 Buffet Marg G 1.94 1.88 1.81 1.76 1.73 1.70 SR NM/lb 0.178 0.181 0.184 0.186 0.187 0.187 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 3% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 9 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.6% AND FUEL FLOW BY 8.4%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 7.2%.

AOM-1502-003

"

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REVISION 18

Cruise

Page 25

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE !EMBRAER 175 Models

These tables show N1, fuel flow, indicated airspeed, true airspeed, indicated Mach number, buffet margin and specific range. Data are presented for various weights and altitudes. Correction for ISA deviation and anti-ice are also presented. In the long range cruise schedule (LRC), the airplane is flown at a speed corresponding to a specific range equal to 99% of maximum specific range. It is used when range is the main factor.

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Page 26

Cruise

REVISION 18

AOM-1502-003

The associated conditions are: Flaps.......................................................................... UP Gear........................................................................... UP Bleeds........................................................................ OPEN Anti-ice....................................................................... OFF Center of gravity........................................................ 18% Minimum Remaining Rate of Climb.......................... 300 ft/min

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

AOM-1502-003

N1 % 65.8 69.0 69.7 70.5 71.2 72.0 73.3 74.5 Fuel Flow lb/h/Eng 1892 1838 1828 1819 1822 1833 1866 1894 IAS kt 269 267 266 265 263 262 266 269 85000 TAS kt 288 308 311 314 317 321 330 339 Ind. MACH 0.44 0.48 0.49 0.50 0.50 0.51 0.53 0.54 Buffet Marg G 2.19 2.13 2.12 2.09 2.06 2.05 2.10 2.14 SR NM/lb 0.076 0.084 0.085 0.086 0.087 0.088 0.088 0.090 N1 % 65.3 68.3 69.1 69.9 70.5 71.3 72.4 73.7 Fuel Flow lb/h/Eng 1854 1793 1787 1777 1774 1778 1805 1835 IAS kt 266 263 263 263 261 259 261 265 83000 TAS kt 286 304 308 312 315 318 325 334 Ind. MACH 0.44 0.48 0.48 0.49 0.50 0.51 0.52 0.53 Buffet Marg G 2.20 2.13 2.13 2.11 2.08 2.05 2.08 2.12 SR NM/lb 0.077 0.085 0.086 0.088 0.089 0.089 0.090 0.091 N1 % 64.7 67.6 68.5 69.3 69.8 70.7 71.5 72.7 Fuel Flow lb/h/Eng 1816 1748 1744 1739 1727 1732 1735 1773 IAS kt 264 260 260 260 259 257 256 260 81000 TAS kt 283 300 304 309 312 315 318 328 Ind. MACH 0.44 0.47 0.48 0.49 0.49 0.50 0.51 0.53 Buffet Marg G 2.21 2.13 2.13 2.12 2.10 2.07 2.04 2.10 SR NM/lb 0.078 0.086 0.087 0.089 0.090 0.091 0.092 0.092 N1 % 64.1 66.9 67.7 68.6 69.3 70.1 70.8 71.6 Fuel Flow lb/h/Eng 1774 1701 1699 1697 1689 1689 1686 1696 IAS kt 261 256 257 257 256 256 254 253 79000 TAS kt 280 296 301 305 310 313 315 320 Ind. MACH 0.43 0.46 0.47 0.48 0.49 0.50 0.50 0.51 Buffet Marg G 2.22 2.13 2.13 2.13 2.12 2.10 2.06 2.05 SR NM/lb 0.079 0.087 0.088 0.090 0.092 0.093 0.094 0.094 N1 % 63.4 66.1 67.0 67.8 68.7 69.4 70.1 70.7 Fuel Flow lb/h/Eng 1733 1656 1655 1651 1651 1644 1645 1636 IAS kt 258 253 253 253 254 254 252 249 77000 TAS kt 277 292 297 301 306 311 314 315 Ind. MACH 0.43 0.46 0.47 0.48 0.49 0.49 0.50 0.50 Buffet Marg G 2.23 2.13 2.13 2.12 2.12 2.12 2.09 2.03 SR NM/lb 0.080 0.088 0.090 0.091 0.093 0.095 0.095 0.096 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 3% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 7 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.9% AND FUEL FLOW BY 6.7%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 5.9%.

75.3 1898 269 345 0.55 2.13 0.091 74.7 1848 266 341 0.55 2.14 0.092 73.9 1794 262 336 0.54 2.13 0.094 73.1 1738 258 331 0.53 2.12 0.095 72.1 1677 253 325 0.52 2.10 0.097

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REVISION 18

Cruise

Page 27

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

N1 % 62.7 65.5 66.2 67.0 68.0 68.9 69.4 70.0 Fuel Flow lb/h/Eng 1691 1618 1608 1605 1608 1608 1597 1588 IAS kt 255 250 250 250 250 251 250 247 75000 TAS kt 274 289 293 297 302 308 311 312 Ind. MACH 0.42 0.45 0.46 0.47 0.48 0.49 0.50 0.50 Buffet Marg G 2.24 2.13 2.12 2.12 2.13 2.13 2.10 2.05 SR NM/lb 0.081 0.089 0.091 0.093 0.094 0.096 0.097 0.098 N1 % 62.1 65.0 65.6 66.3 67.2 68.2 68.7 69.4 Fuel Flow lb/h/Eng 1655 1581 1568 1560 1563 1568 1555 1551 IAS kt 252 248 247 246 247 248 247 246 73000 TAS kt 271 286 289 293 298 304 307 310 Ind. MACH 0.42 0.45 0.45 0.46 0.47 0.48 0.49 0.50 Buffet Marg G 2.25 2.15 2.13 2.12 2.13 2.14 2.11 2.09 SR NM/lb 0.082 0.090 0.092 0.094 0.095 0.097 0.099 0.100 N1 % 61.5 64.5 65.1 65.7 66.6 67.4 68.1 68.7 Fuel Flow lb/h/Eng 1620 1546 1534 1519 1523 1525 1516 1504 IAS kt 250 245 244 243 244 245 244 243 71000 TAS kt 268 283 286 290 295 300 304 307 Ind. MACH 0.41 0.44 0.45 0.46 0.47 0.48 0.49 0.49 Buffet Marg G 2.27 2.16 2.15 2.13 2.14 2.14 2.13 2.10 SR NM/lb 0.083 0.092 0.093 0.095 0.097 0.098 0.100 0.102 N1 % 60.9 63.9 64.6 65.3 65.9 66.6 67.4 68.1 Fuel Flow lb/h/Eng 1584 1510 1500 1488 1483 1483 1476 1466 IAS kt 247 242 242 241 241 241 241 240 69000 TAS kt 265 280 284 287 291 296 300 304 Ind. MACH 0.41 0.44 0.45 0.45 0.46 0.47 0.48 0.49 Buffet Marg G 2.28 2.18 2.17 2.15 2.15 2.15 2.13 2.12 SR NM/lb 0.084 0.093 0.095 0.097 0.098 0.100 0.102 0.104 N1 % 60.2 63.3 64.1 64.7 65.3 65.9 66.7 67.5 Fuel Flow lb/h/Eng 1548 1472 1465 1455 1448 1444 1435 1427 IAS kt 244 240 239 239 239 239 238 237 67000 TAS kt 262 277 281 284 288 293 296 300 Ind. MACH 0.40 0.43 0.44 0.45 0.46 0.47 0.47 0.48 Buffet Marg G 2.29 2.20 2.19 2.17 2.16 2.16 2.14 2.13 SR NM/lb 0.085 0.094 0.096 0.098 0.100 0.101 0.103 0.105 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 3% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 7 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 1.0% AND FUEL FLOW BY 8.4%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 7.1%.

71.1 1606 247 317 0.51 2.05 0.099 70.3 1555 244 314 0.50 2.06 0.101 69.5 1505 242 310 0.50 2.08 0.103 68.7 1457 239 307 0.49 2.09 0.105 68.0 1415 236 303 0.49 2.10 0.107

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Page 28

Cruise

REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

AOM-1502-003

N1 % 59.6 62.7 63.4 64.1 64.7 65.3 66.1 66.9 Fuel Flow lb/h/Eng 1510 1434 1428 1419 1415 1411 1398 1386 IAS kt 241 237 237 236 236 236 235 234 65000 TAS kt 259 274 278 281 286 290 293 296 Ind. MACH 0.40 0.43 0.44 0.44 0.45 0.46 0.47 0.47 Buffet Marg G 2.30 2.21 2.20 2.19 2.19 2.19 2.16 2.14 SR NM/lb 0.086 0.095 0.097 0.099 0.101 0.103 0.105 0.107 N1 % 58.9 62.1 62.8 63.5 64.2 64.8 65.5 66.3 Fuel Flow lb/h/Eng 1471 1397 1390 1382 1384 1382 1366 1354 IAS kt 238 234 234 233 234 234 233 232 63000 TAS kt 255 271 274 278 283 288 291 294 Ind. MACH 0.39 0.42 0.43 0.44 0.45 0.46 0.46 0.47 Buffet Marg G 2.32 2.23 2.22 2.21 2.22 2.22 2.19 2.17 SR NM/lb 0.087 0.097 0.099 0.101 0.102 0.104 0.106 0.108 N1 % 58.1 61.6 62.2 62.8 63.6 64.4 65.1 65.9 Fuel Flow lb/h/Eng 1428 1369 1355 1343 1352 1358 1340 1325 IAS kt 234 233 231 230 232 233 232 231 61000 TAS kt 251 269 272 274 280 286 289 292 Ind. MACH 0.39 0.42 0.43 0.43 0.44 0.46 0.46 0.47 Buffet Marg G 2.32 2.27 2.25 2.22 2.25 2.27 2.23 2.21 SR NM/lb 0.088 0.098 0.100 0.102 0.104 0.105 0.108 0.110 N1 % 57.5 61.2 61.6 62.0 63.0 63.8 64.7 65.5 Fuel Flow lb/h/Eng 1392 1346 1322 1300 1320 1330 1318 1304 IAS kt 231 231 229 227 230 231 231 230 59000 TAS kt 249 267 269 270 278 284 287 291 Ind. MACH 0.38 0.42 0.42 0.43 0.44 0.45 0.46 0.47 Buffet Marg G 2.34 2.32 2.28 2.22 2.28 2.31 2.29 2.27 SR NM/lb 0.089 0.099 0.102 0.104 0.105 0.107 0.109 0.111 N1 % 56.9 60.9 61.1 61.4 62.4 63.4 64.2 65.1 Fuel Flow lb/h/Eng 1356 1328 1300 1272 1290 1309 1294 1280 IAS kt 229 230 228 225 228 231 229 228 57000 TAS kt 246 266 267 268 275 283 286 289 Ind. MACH 0.38 0.42 0.42 0.42 0.44 0.45 0.46 0.46 Buffet Marg G 2.37 2.39 2.33 2.27 2.32 2.37 2.34 2.32 SR NM/lb 0.091 0.100 0.103 0.105 0.107 0.108 0.110 0.113 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 6% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 12 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 1.2% AND FUEL FLOW BY 9.8%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 8.3%.

67.5 1384 234 301 0.48 2.13 0.109 66.9 1347 231 297 0.48 2.15 0.110 66.3 1312 229 294 0.47 2.17 0.112 65.8 1281 227 292 0.47 2.21 0.114 65.3 1257 226 290 0.47 2.26 0.115

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REVISION 18

Cruise

Page 29

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

N1 % 56.5 60.4 60.7 61.1 61.9 62.9 63.7 64.4 Fuel Flow lb/h/Eng 1332 1306 1277 1253 1262 1280 1267 1250 IAS kt 227 229 226 224 226 229 227 226 55000 TAS kt 244 265 265 267 273 281 284 286 Ind. MACH 0.38 0.41 0.42 0.42 0.43 0.45 0.45 0.46 Buffet Marg G 2.43 2.45 2.38 2.33 2.37 2.42 2.39 2.35 SR NM/lb 0.092 0.101 0.104 0.107 0.108 0.110 0.112 0.114 N1 % 56.0 59.9 60.3 60.7 61.4 62.1 62.9 63.5 Fuel Flow lb/h/Eng 1309 1281 1258 1234 1239 1240 1230 1216 IAS kt 226 227 225 223 224 225 224 223 53000 TAS kt 242 263 264 266 271 277 280 282 Ind. MACH 0.37 0.41 0.42 0.42 0.43 0.44 0.45 0.45 Buffet Marg G 2.48 2.50 2.45 2.40 2.42 2.44 2.41 2.37 SR NM/lb 0.093 0.103 0.105 0.108 0.110 0.112 0.114 0.116 N1 % 55.7 59.1 59.7 60.2 60.8 61.4 61.9 62.6 Fuel Flow lb/h/Eng 1292 1248 1231 1214 1210 1201 1184 1177 IAS kt 224 224 223 222 222 221 219 219 51000 TAS kt 241 259 262 265 268 272 274 277 Ind. MACH 0.37 0.41 0.41 0.42 0.43 0.43 0.44 0.44 Buffet Marg G 2.50 2.50 2.50 2.47 2.46 2.44 2.40 2.38 SR NM/lb 0.093 0.104 0.106 0.109 0.111 0.113 0.116 0.118 N1 % 55.4 58.3 59.0 59.7 60.1 60.2 60.8 61.5 Fuel Flow lb/h/Eng 1274 1212 1201 1189 1175 1151 1139 1130 IAS kt 224 221 220 220 218 215 214 214 49000 TAS kt 240 255 259 262 264 264 267 271 Ind. MACH 0.37 0.40 0.41 0.41 0.42 0.42 0.43 0.43 Buffet Marg G 2.50 2.50 2.50 2.50 2.48 2.40 2.38 2.37 SR NM/lb 0.094 0.105 0.108 0.110 0.112 0.115 0.117 0.120 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 7% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 13 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.7% AND FUEL FLOW BY10.6%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 8.7%.

64.8 1231 224 288 0.46 2.31 0.117 64.2 1204 222 285 0.46 2.35 0.119 63.5 1172 219 282 0.45 2.38 0.120 62.4 1130 215 276 0.44 2.38 0.122

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Page 30

Cruise

REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

AOM-1502-003

N1 % 76.0 76.6 77.1 77.7 78.3 79.1 79.7 80.2 Fuel Flow lb/h/Eng 1891 1882 1866 1820 1805 1806 1798 1780 IAS kt 269 268 267 266 265 264 263 260 85000 TAS kt 350 354 358 362 366 372 375 377 Ind. MACH 0.56 0.57 0.58 0.59 0.60 0.61 0.62 0.63 Buffet Marg G 2.11 2.07 2.03 2.00 1.96 1.92 1.87 1.82 SR NM/lb 0.092 0.094 0.096 0.100 0.102 0.103 0.104 0.106 N1 % 75.5 76.1 76.6 77.2 77.8 78.5 79.1 79.7 Fuel Flow lb/h/Eng 1852 1842 1826 1782 1768 1763 1758 1745 IAS kt 267 266 265 264 263 262 261 259 83000 TAS kt 347 351 355 359 363 368 372 375 Ind. MACH 0.56 0.57 0.58 0.59 0.60 0.61 0.62 0.62 Buffet Marg G 2.13 2.09 2.05 2.02 1.98 1.94 1.90 1.85 SR NM/lb 0.094 0.095 0.097 0.101 0.103 0.104 0.106 0.108 N1 % 75.0 75.6 76.2 76.8 77.3 77.9 78.6 79.2 Fuel Flow lb/h/Eng 1807 1800 1787 1746 1732 1720 1724 1707 IAS kt 264 263 262 262 260 260 259 257 81000 TAS kt 343 348 352 356 360 365 370 373 Ind. MACH 0.55 0.56 0.57 0.58 0.59 0.60 0.61 0.62 Buffet Marg G 2.15 2.11 2.08 2.04 2.01 1.97 1.93 1.87 SR NM/lb 0.095 0.097 0.098 0.102 0.104 0.106 0.107 0.109 N1 % 74.2 75.0 75.7 76.3 76.8 77.4 78.0 78.6 Fuel Flow lb/h/Eng 1757 1758 1750 1709 1695 1686 1682 1667 IAS kt 260 261 260 259 258 257 257 254 79000 TAS kt 339 344 349 353 357 362 367 370 Ind. MACH 0.55 0.56 0.57 0.58 0.59 0.60 0.61 0.61 Buffet Marg G 2.15 2.13 2.10 2.07 2.03 1.99 1.96 1.90 SR NM/lb 0.096 0.098 0.100 0.103 0.105 0.107 0.109 0.111 N1 % 73.4 74.4 75.2 75.8 76.3 76.9 77.4 78.0 Fuel Flow lb/h/Eng 1703 1710 1710 1669 1657 1650 1640 1623 IAS kt 256 257 257 257 255 255 254 252 77000 TAS kt 333 340 346 350 354 359 364 366 Ind. MACH 0.54 0.55 0.56 0.57 0.58 0.59 0.60 0.61 Buffet Marg G 2.14 2.15 2.13 2.09 2.05 2.02 1.98 1.92 SR NM/lb 0.098 0.099 0.101 0.105 0.107 0.109 0.111 0.113 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 3% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 8 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.6% AND FUEL FLOW BY 6.6%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 5.8%.

80.7 1764 258 380 0.63 1.76 0.108 80.3 1729 256 378 0.63 1.79 0.109 79.9 1695 255 376 0.63 1.83 0.111 79.3 1655 253 373 0.62 1.85 0.113 78.8 1617 251 370 0.62 1.88 0.114

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 31

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

N1 % 72.5 73.6 74.5 75.2 75.9 76.4 76.8 77.4 Fuel Flow lb/h/Eng 1646 1658 1663 1628 1619 1613 1604 1582 IAS kt 252 253 254 254 253 252 252 249 75000 TAS kt 328 335 341 346 350 355 360 362 Ind. MACH 0.53 0.54 0.56 0.57 0.58 0.59 0.60 0.60 Buffet Marg G 2.12 2.14 2.14 2.11 2.08 2.04 2.01 1.95 SR NM/lb 0.100 0.101 0.103 0.106 0.108 0.110 0.112 0.115 N1 % 71.4 72.7 73.6 74.6 75.3 75.8 76.2 76.9 Fuel Flow lb/h/Eng 1575 1602 1609 1584 1580 1577 1567 1552 IAS kt 246 249 250 250 250 250 249 248 73000 TAS kt 320 329 336 342 347 352 356 360 Ind. MACH 0.52 0.53 0.55 0.56 0.57 0.58 0.59 0.60 Buffet Marg G 2.08 2.13 2.13 2.13 2.10 2.07 2.03 1.99 SR NM/lb 0.102 0.103 0.104 0.108 0.110 0.112 0.114 0.116 N1 % 70.3 71.6 72.8 73.8 74.8 75.2 75.6 76.4 Fuel Flow lb/h/Eng 1511 1534 1555 1538 1540 1536 1529 1516 IAS kt 241 243 245 247 247 247 246 245 71000 TAS kt 314 322 330 337 343 348 353 357 Ind. MACH 0.51 0.52 0.54 0.55 0.56 0.57 0.58 0.59 Buffet Marg G 2.05 2.08 2.12 2.14 2.12 2.09 2.06 2.02 SR NM/lb 0.104 0.105 0.106 0.110 0.111 0.113 0.115 0.118 N1 % 69.5 70.6 71.9 73.0 74.0 74.6 75.0 75.8 Fuel Flow lb/h/Eng 1460 1471 1500 1487 1496 1494 1490 1479 IAS kt 238 238 241 243 244 244 243 243 69000 TAS kt 310 315 324 332 339 344 349 353 Ind. MACH 0.50 0.51 0.53 0.54 0.56 0.57 0.58 0.59 Buffet Marg G 2.06 2.06 2.11 2.13 2.14 2.11 2.08 2.05 SR NM/lb 0.106 0.107 0.108 0.112 0.113 0.115 0.117 0.119 N1 % 68.7 69.9 71.1 72.2 73.3 73.9 74.4 75.2 Fuel Flow lb/h/Eng 1412 1427 1445 1436 1448 1450 1448 1441 IAS kt 235 236 237 239 240 241 240 240 67000 TAS kt 307 312 319 326 334 339 344 349 Ind. MACH 0.50 0.51 0.52 0.53 0.55 0.56 0.57 0.58 Buffet Marg G 2.08 2.08 2.10 2.13 2.15 2.13 2.10 2.07 SR NM/lb 0.109 0.109 0.110 0.114 0.115 0.117 0.119 0.121 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 3% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 7 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.9% AND FUEL FLOW BY 8.6%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 7.0%.

78.2 1576 248 367 0.61 1.91 0.116 77.6 1533 245 363 0.61 1.93 0.118 76.9 1491 243 359 0.60 1.96 0.120 76.6 1466 242 358 0.60 2.00 0.122 76.0 1430 239 354 0.59 2.04 0.124

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 32

Cruise

REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

AOM-1502-003

N1 % 67.9 69.3 70.5 71.4 72.3 73.1 73.7 74.7 Fuel Flow lb/h/Eng 1368 1394 1409 1388 1387 1404 1404 1406 IAS kt 232 235 235 235 235 237 237 238 65000 TAS kt 303 311 317 322 326 334 340 346 Ind. MACH 0.49 0.50 0.52 0.53 0.54 0.55 0.56 0.57 Buffet Marg G 2.10 2.14 2.14 2.13 2.12 2.14 2.12 2.10 SR NM/lb 0.111 0.112 0.113 0.116 0.118 0.119 0.121 0.123 N1 % 67.3 68.6 69.9 70.7 71.5 72.3 72.9 74.1 Fuel Flow lb/h/Eng 1329 1350 1374 1344 1344 1353 1350 1369 IAS kt 229 233 234 232 232 232 232 235 63000 TAS kt 299 309 316 318 322 328 333 343 Ind. MACH 0.48 0.50 0.51 0.52 0.53 0.54 0.55 0.57 Buffet Marg G 2.10 2.16 2.19 2.15 2.13 2.14 2.12 2.14 SR NM/lb 0.113 0.114 0.115 0.118 0.120 0.121 0.123 0.125 N1 % 66.8 67.9 69.1 70.0 70.8 71.6 72.2 73.3 Fuel Flow lb/h/Eng 1299 1314 1332 1305 1301 1308 1310 1328 IAS kt 227 230 232 230 229 229 229 232 61000 TAS kt 297 305 313 315 318 324 329 338 Ind. MACH 0.48 0.49 0.51 0.52 0.52 0.53 0.54 0.56 Buffet Marg G 2.14 2.18 2.22 2.18 2.15 2.15 2.14 2.16 SR NM/lb 0.114 0.116 0.117 0.121 0.122 0.124 0.126 0.127 N1 % 66.2 67.3 68.4 69.3 70.2 70.8 71.5 72.5 Fuel Flow lb/h/Eng 1263 1279 1296 1269 1269 1263 1261 1283 IAS kt 225 227 229 229 228 226 225 228 59000 TAS kt 294 301 309 314 317 319 323 333 Ind. MACH 0.47 0.49 0.50 0.51 0.52 0.53 0.54 0.55 Buffet Marg G 2.16 2.20 2.24 2.23 2.20 2.16 2.14 2.18 SR NM/lb 0.116 0.118 0.119 0.124 0.125 0.126 0.128 0.130 N1 % 65.7 66.7 67.7 68.5 69.4 70.0 70.8 71.6 Fuel Flow lb/h/Eng 1236 1249 1260 1230 1231 1223 1218 1240 IAS kt 223 225 226 226 226 223 222 224 57000 TAS kt 292 298 305 310 315 316 319 328 Ind. MACH 0.47 0.48 0.50 0.51 0.52 0.52 0.53 0.54 Buffet Marg G 2.21 2.24 2.26 2.25 2.25 2.19 2.15 2.19 SR NM/lb 0.118 0.119 0.121 0.126 0.128 0.129 0.131 0.132 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 6% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 13 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.7% AND FUEL FLOW BY 9.1%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 8.0%.

75.6 1404 238 352 0.59 2.08 0.125 75.2 1376 236 350 0.58 2.13 0.127 74.5 1342 234 347 0.58 2.17 0.129 73.5 1302 231 342 0.57 2.19 0.131 72.5 1261 227 337 0.56 2.22 0.134

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 33

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

N1 % 65.3 66.1 66.9 67.7 68.4 69.3 70.2 70.8 Fuel Flow lb/h/Eng 1214 1217 1223 1195 1188 1188 1188 1202 IAS kt 222 223 223 223 223 222 221 222 55000 TAS kt 291 295 301 305 310 314 318 324 Ind. MACH 0.47 0.48 0.49 0.50 0.51 0.52 0.53 0.54 Buffet Marg G 2.28 2.27 2.27 2.27 2.26 2.24 2.22 2.22 SR NM/lb 0.120 0.121 0.123 0.128 0.131 0.132 0.134 0.135 N1 % 64.9 65.3 65.9 66.8 67.6 68.5 69.6 69.7 Fuel Flow lb/h/Eng 1192 1183 1176 1156 1154 1150 1157 1154 IAS kt 221 220 218 219 220 220 220 218 53000 TAS kt 289 292 294 300 306 311 317 318 Ind. MACH 0.47 0.47 0.48 0.49 0.50 0.51 0.52 0.53 Buffet Marg G 2.33 2.30 2.26 2.27 2.28 2.28 2.28 2.22 SR NM/lb 0.121 0.123 0.125 0.130 0.132 0.135 0.137 0.138 N1 % 64.2 64.5 64.9 65.8 66.6 67.6 68.5 68.4 Fuel Flow lb/h/Eng 1163 1148 1132 1113 1108 1115 1113 1104 IAS kt 219 216 213 214 214 216 217 213 51000 TAS kt 286 287 288 294 299 306 313 312 Ind. MACH 0.46 0.47 0.47 0.48 0.49 0.50 0.52 0.52 Buffet Marg G 2.37 2.31 2.25 2.27 2.26 2.30 2.31 2.23 SR NM/lb 0.123 0.125 0.127 0.132 0.135 0.137 0.140 0.142 N1 % 63.3 63.6 64.0 64.5 65.4 66.6 67.6 67.1 Fuel Flow lb/h/Eng 1129 1112 1097 1063 1058 1070 1078 1052 IAS kt 215 212 210 209 209 211 214 209 49000 TAS kt 282 282 284 286 291 299 307 306 Ind. MACH 0.45 0.46 0.46 0.47 0.48 0.49 0.51 0.51 Buffet Marg G 2.40 2.33 2.27 2.24 2.23 2.28 2.33 2.23 SR NM/lb 0.125 0.127 0.129 0.135 0.137 0.140 0.143 0.146 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 4% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 8 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.8% AND FUEL FLOW BY10.0%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 8.5%.

71.2 1209 222 329 0.55 2.22 0.136 69.8 1153 216 321 0.54 2.19 0.139 68.1 1087 209 311 0.52 2.13 0.143 67.1 1038 205 305 0.51 2.14 0.147

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Cruise

REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

AOM-1502-003

N1 % 81.3 82.4 83.6 84.7 85.7 86.3 87.2 Fuel Flow lb/h/Eng 1753 1791 1838 1881 1889 1868 1866 IAS kt 256 257 260 263 261 257 255 85000 TAS kt 384 392 402 413 417 417 421 Ind. MACH 0.64 0.66 0.68 0.70 0.71 0.71 0.72 Buffet Marg G 1.72 1.69 1.68 1.66 1.61 1.55 1.49 SR NM/lb 0.109 0.109 0.109 0.110 0.110 0.112 0.113 N1 % 80.8 81.6 82.8 83.9 85.0 85.9 86.7 87.1 Fuel Flow lb/h/Eng 1716 1721 1769 1811 1834 1844 1831 1785 IAS kt 254 253 256 258 258 258 254 246 83000 TAS kt 381 386 396 406 413 418 420 414 Ind. MACH 0.64 0.65 0.67 0.69 0.70 0.72 0.72 0.71 Buffet Marg G 1.74 1.70 1.69 1.67 1.63 1.59 1.53 1.44 SR NM/lb 0.111 0.112 0.112 0.112 0.113 0.113 0.115 0.116 N1 % 80.4 80.9 82.0 83.1 84.3 85.3 86.2 86.5 Fuel Flow lb/h/Eng 1679 1664 1698 1742 1781 1806 1801 1752 IAS kt 252 250 251 254 256 257 254 247 81000 TAS kt 378 381 389 399 409 417 420 416 Ind. MACH 0.63 0.64 0.66 0.68 0.70 0.71 0.72 0.72 Buffet Marg G 1.77 1.72 1.70 1.68 1.65 1.62 1.57 1.48 SR NM/lb 0.113 0.115 0.115 0.115 0.115 0.116 0.117 0.119 N1 % 79.9 80.5 81.2 82.3 83.5 84.6 85.6 86.0 Fuel Flow lb/h/Eng 1642 1632 1635 1673 1714 1752 1760 1725 IAS kt 250 249 248 249 251 254 253 247 79000 TAS kt 376 379 384 392 402 413 418 416 Ind. MACH 0.63 0.64 0.65 0.67 0.69 0.71 0.72 0.72 Buffet Marg G 1.80 1.75 1.71 1.69 1.67 1.64 1.60 1.52 SR NM/lb 0.114 0.116 0.117 0.117 0.117 0.118 0.119 0.121 N1 % 79.4 80.1 80.5 81.5 82.7 83.8 84.9 85.6 Fuel Flow lb/h/Eng 1606 1599 1585 1604 1646 1685 1706 1704 IAS kt 249 247 245 245 247 250 250 249 77000 TAS kt 373 377 380 386 396 406 413 418 Ind. MACH 0.63 0.63 0.64 0.66 0.67 0.70 0.71 0.72 Buffet Marg G 1.83 1.79 1.73 1.70 1.68 1.66 1.62 1.57 SR NM/lb 0.116 0.118 0.120 0.120 0.120 0.121 0.121 0.123 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 3% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 8 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.7% AND FUEL FLOW BY 7.7%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 6.5%.

86.9 1709 242 414 0.72 1.45 0.121 86.4 1686 244 418 0.73 1.50 0.124

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REVISION 18

Cruise

Page 35

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

N1 % 78.9 79.5 80.0 80.7 81.8 83.0 84.2 85.2 Fuel Flow lb/h/Eng 1569 1561 1548 1541 1580 1617 1656 1682 IAS kt 247 245 243 241 243 245 248 250 75000 TAS kt 371 374 377 381 390 399 410 420 Ind. MACH 0.62 0.63 0.64 0.65 0.66 0.68 0.71 0.72 Buffet Marg G 1.86 1.81 1.76 1.72 1.69 1.67 1.65 1.62 SR NM/lb 0.118 0.120 0.122 0.124 0.123 0.123 0.124 0.125 N1 % 78.2 78.9 79.5 80.2 81.0 82.1 83.3 84.5 Fuel Flow lb/h/Eng 1528 1522 1513 1504 1516 1551 1590 1625 IAS kt 244 243 241 240 239 241 243 246 73000 TAS kt 367 371 375 379 384 392 403 414 Ind. MACH 0.61 0.62 0.63 0.64 0.65 0.67 0.69 0.71 Buffet Marg G 1.89 1.84 1.79 1.75 1.71 1.68 1.66 1.64 SR NM/lb 0.120 0.122 0.124 0.126 0.127 0.127 0.127 0.127 N1 % 77.6 78.3 79.0 79.7 80.2 81.2 82.4 83.6 Fuel Flow lb/h/Eng 1486 1481 1474 1469 1457 1482 1521 1558 IAS kt 242 240 239 238 236 236 238 241 71000 TAS kt 363 367 371 376 379 386 395 406 Ind. MACH 0.61 0.62 0.63 0.64 0.65 0.66 0.68 0.70 Buffet Marg G 1.91 1.87 1.82 1.78 1.73 1.69 1.67 1.65 SR NM/lb 0.122 0.124 0.126 0.128 0.130 0.130 0.130 0.130 N1 % 77.0 77.6 78.3 79.0 79.7 80.5 81.6 82.7 Fuel Flow lb/h/Eng 1446 1440 1435 1428 1424 1429 1456 1489 IAS kt 239 238 237 235 234 234 234 236 69000 TAS kt 360 364 368 372 376 382 389 398 Ind. MACH 0.60 0.61 0.62 0.63 0.64 0.65 0.67 0.69 Buffet Marg G 1.94 1.90 1.85 1.81 1.76 1.72 1.69 1.66 SR NM/lb 0.124 0.126 0.128 0.130 0.132 0.134 0.134 0.134 N1 % 76.5 77.0 77.7 78.4 79.2 80.0 80.8 81.7 Fuel Flow lb/h/Eng 1413 1397 1394 1389 1392 1395 1401 1413 IAS kt 237 235 234 233 233 233 231 230 67000 TAS kt 357 360 364 368 374 381 385 389 Ind. MACH 0.60 0.61 0.62 0.62 0.64 0.65 0.66 0.67 Buffet Marg G 1.98 1.93 1.88 1.84 1.80 1.77 1.72 1.67 SR NM/lb 0.126 0.129 0.131 0.133 0.134 0.136 0.137 0.138 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 3% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 10 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.6% AND FUEL FLOW BY 8.2%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 6.9%.

85.9 1659 244 418 0.73 1.55 0.126 85.3 1618 243 416 0.72 1.58 0.129 84.7 1578 241 414 0.72 1.62 0.131 83.9 1524 238 409 0.71 1.64 0.134 83.0 1458 234 401 0.70 1.66 0.138

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Page 36

Cruise

REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

AOM-1502-003

N1 % 76.1 76.4 77.1 77.7 78.5 79.3 79.8 80.9 Fuel Flow lb/h/Eng 1390 1359 1354 1348 1353 1359 1342 1359 IAS kt 237 233 231 230 230 230 228 227 65000 TAS kt 356 357 360 364 370 377 379 385 Ind. MACH 0.60 0.60 0.61 0.62 0.63 0.65 0.65 0.66 Buffet Marg G 2.03 1.96 1.91 1.87 1.83 1.80 1.74 1.70 SR NM/lb 0.128 0.131 0.133 0.135 0.137 0.139 0.141 0.142 N1 % 75.6 76.1 76.5 77.0 77.8 78.6 79.2 80.2 Fuel Flow lb/h/Eng 1358 1340 1319 1307 1315 1321 1312 1315 IAS kt 234 232 230 227 228 228 226 226 63000 TAS kt 353 356 358 360 367 373 377 382 Ind. MACH 0.59 0.60 0.60 0.61 0.62 0.64 0.65 0.66 Buffet Marg G 2.07 2.02 1.95 1.90 1.87 1.83 1.78 1.74 SR NM/lb 0.130 0.133 0.136 0.138 0.139 0.141 0.144 0.145 N1 % 75.0 75.6 76.0 76.3 77.1 77.8 78.6 79.3 Fuel Flow lb/h/Eng 1326 1309 1288 1267 1276 1284 1278 1271 IAS kt 232 231 228 225 225 225 224 223 61000 TAS kt 350 353 355 356 363 369 374 378 Ind. MACH 0.59 0.59 0.60 0.60 0.62 0.63 0.64 0.65 Buffet Marg G 2.11 2.06 2.00 1.93 1.90 1.87 1.82 1.77 SR NM/lb 0.132 0.135 0.138 0.141 0.142 0.144 0.146 0.149 N1 % 74.3 75.2 75.6 76.0 76.5 77.1 77.8 78.6 Fuel Flow lb/h/Eng 1293 1283 1266 1249 1245 1247 1240 1235 IAS kt 230 229 227 225 224 223 221 221 59000 TAS kt 347 351 354 357 361 365 369 374 Ind. MACH 0.58 0.59 0.60 0.61 0.61 0.63 0.64 0.65 Buffet Marg G 2.15 2.12 2.06 2.00 1.95 1.90 1.86 1.81 SR NM/lb 0.134 0.137 0.140 0.143 0.145 0.146 0.149 0.152 N1 % 73.5 74.4 74.9 75.5 75.9 76.3 77.0 77.8 Fuel Flow lb/h/Eng 1257 1250 1234 1220 1211 1208 1202 1198 IAS kt 227 227 225 223 222 220 219 218 57000 TAS kt 342 347 351 354 358 361 365 370 Ind. MACH 0.57 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G 2.19 2.16 2.10 2.05 2.00 1.94 1.89 1.85 SR NM/lb 0.136 0.139 0.142 0.145 0.148 0.149 0.152 0.155 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 6% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 14 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.6% AND FUEL FLOW BY 8.5%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 7.2%.

82.1 1390 229 393 0.68 1.67 0.141 81.2 1334 225 388 0.67 1.70 0.146 80.2 1273 221 382 0.66 1.72 0.150 79.3 1228 219 379 0.66 1.76 0.154 78.6 1195 217 376 0.65 1.80 0.157

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REVISION 18

Cruise

Page 37

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

N1 % 72.5 73.5 74.3 75.0 75.4 75.5 76.2 77.0 Fuel Flow lb/h/Eng 1216 1211 1203 1193 1189 1168 1165 1160 IAS kt 223 223 223 222 221 217 216 215 55000 TAS kt 337 343 347 352 356 357 361 366 Ind. MACH 0.56 0.58 0.59 0.60 0.61 0.61 0.62 0.63 Buffet Marg G 2.21 2.19 2.15 2.11 2.06 1.98 1.93 1.88 SR NM/lb 0.139 0.141 0.144 0.147 0.150 0.153 0.155 0.158 N1 % 71.2 72.5 73.5 74.4 74.7 74.8 75.4 76.2 Fuel Flow lb/h/Eng 1163 1170 1170 1166 1158 1133 1126 1124 IAS kt 218 219 220 220 218 214 213 213 53000 TAS kt 329 337 343 349 353 352 357 362 Ind. MACH 0.55 0.57 0.58 0.59 0.60 0.60 0.61 0.62 Buffet Marg G 2.21 2.21 2.19 2.16 2.11 2.02 1.97 1.93 SR NM/lb 0.142 0.144 0.147 0.150 0.152 0.155 0.158 0.161 N1 % 69.8 71.2 72.5 73.5 73.9 74.1 74.7 75.4 Fuel Flow lb/h/Eng 1109 1118 1132 1132 1124 1102 1090 1087 IAS kt 212 214 217 217 216 212 211 210 51000 TAS kt 321 329 338 345 348 349 352 358 Ind. MACH 0.54 0.55 0.57 0.59 0.59 0.60 0.61 0.62 Buffet Marg G 2.19 2.21 2.22 2.21 2.15 2.07 2.02 1.97 SR NM/lb 0.145 0.147 0.149 0.152 0.155 0.158 0.162 0.164 N1 % 68.4 70.0 71.5 72.6 73.1 73.4 74.1 74.7 Fuel Flow lb/h/Eng 1047 1067 1090 1096 1087 1066 1061 1052 IAS kt 205 209 213 214 212 209 208 207 49000 TAS kt 311 321 332 340 343 343 349 353 Ind. MACH 0.52 0.54 0.56 0.58 0.58 0.59 0.60 0.61 Buffet Marg G 2.14 2.20 2.25 2.25 2.19 2.11 2.07 2.02 SR NM/lb 0.149 0.150 0.152 0.155 0.158 0.161 0.164 0.168 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 4% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 9 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.7% AND FUEL FLOW BY 8.6%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 7.2%.

77.8 1161 215 372 0.65 1.85 0.160 77.0 1122 212 367 0.64 1.88 0.164 76.2 1084 209 362 0.63 1.93 0.167 75.3 1044 206 357 0.62 1.97 0.171

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Page 38

Cruise

REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 36000 37000 38000 39000 40000 41000

AOM-1502-003

N1 % Fuel Flow lb/h/Eng IAS kt 85000 TAS kt Ind. MACH Buffet Marg G SR NM/lb N1 % Fuel Flow lb/h/Eng IAS kt 83000 TAS kt Ind. MACH Buffet Marg G SR NM/lb N1 % Fuel Flow lb/h/Eng IAS kt 81000 TAS kt Ind. MACH Buffet Marg G SR NM/lb N1 % Fuel Flow lb/h/Eng IAS kt 79000 TAS kt Ind. MACH Buffet Marg G SR NM/lb N1 % 87.1 Fuel Flow lb/h/Eng 1644 IAS kt 234 77000 TAS kt 409 Ind. MACH 0.71 Buffet Marg G 1.41 SR NM/lb 0.124 INCREASE/DECREASE N1(%) BY 1% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.3% AND FUEL FLOW BY 5.6%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 5.7%.

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REVISION 18

Cruise

Page 39

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 36000 37000 38000 39000 40000 41000

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Page 40

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REVISION 18

AOM-1502-003

N1 % 86.3 Fuel Flow lb/h/Eng 1603 IAS kt 235 75000 TAS kt 410 Ind. MACH 0.71 Buffet Marg G 1.45 SR NM/lb 0.128 N1 % 85.9 87.1 Fuel Flow lb/h/Eng 1589 1576 IAS kt 238 230 73000 TAS kt 415 412 Ind. MACH 0.72 0.72 Buffet Marg G 1.51 1.43 SR NM/lb 0.131 0.131 N1 % 85.4 86.5 Fuel Flow lb/h/Eng 1567 1552 IAS kt 239 233 71000 TAS kt 417 416 Ind. MACH 0.73 0.72 Buffet Marg G 1.56 1.48 SR NM/lb 0.133 0.134 N1 % 85.0 85.9 86.7 Fuel Flow lb/h/Eng 1548 1520 1486 IAS kt 240 233 224 69000 TAS kt 419 416 410 Ind. MACH 0.73 0.73 0.71 Buffet Marg G 1.61 1.53 1.43 SR NM/lb 0.135 0.137 0.138 N1 % 84.2 85.4 86.0 Fuel Flow lb/h/Eng 1491 1490 1456 IAS kt 236 233 226 67000 TAS kt 412 416 413 Ind. MACH 0.72 0.73 0.72 Buffet Marg G 1.63 1.57 1.49 SR NM/lb 0.138 0.140 0.142 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 3% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 9 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.6% AND FUEL FLOW BY 7.6%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 6.4%.

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 36000 37000 38000 39000 40000 41000

AOM-1502-003

N1 % 83.3 84.7 85.6 Fuel Flow lb/h/Eng 1425 1450 1445 IAS kt 231 231 229 65000 TAS kt 404 413 417 Ind. MACH 0.70 0.72 0.73 Buffet Marg G 1.65 1.61 1.55 SR NM/lb 0.142 0.143 0.144 N1 % 82.3 83.9 85.3 86.5 Fuel Flow lb/h/Eng 1358 1406 1434 1429 IAS kt 226 230 231 227 63000 TAS kt 396 411 422 423 Ind. MACH 0.69 0.72 0.74 0.74 Buffet Marg G 1.66 1.65 1.61 1.54 SR NM/lb 0.146 0.146 0.147 0.148 N1 % 81.2 82.9 84.5 85.8 86.4 Fuel Flow lb/h/Eng 1290 1340 1392 1395 1365 IAS kt 221 225 229 226 219 61000 TAS kt 388 402 418 422 419 Ind. MACH 0.68 0.70 0.73 0.74 0.73 Buffet Marg G 1.68 1.66 1.65 1.59 1.50 SR NM/lb 0.150 0.150 0.150 0.151 0.153 N1 % 80.4 81.9 83.4 85.0 86.0 Fuel Flow lb/h/Eng 1244 1280 1325 1357 1354 IAS kt 219 220 223 225 222 59000 TAS kt 385 395 408 420 423 Ind. MACH 0.67 0.69 0.71 0.73 0.74 Buffet Marg G 1.72 1.69 1.67 1.64 1.57 SR NM/lb 0.155 0.154 0.154 0.155 0.156 N1 % 79.6 81.0 82.3 84.0 85.5 86.3 Fuel Flow lb/h/Eng 1201 1230 1260 1305 1336 1307 IAS kt 218 217 218 221 223 216 57000 TAS kt 383 390 399 414 427 422 Ind. MACH 0.67 0.68 0.70 0.72 0.74 0.74 Buffet Marg G 1.77 1.72 1.69 1.67 1.64 1.55 SR NM/lb 0.159 0.159 0.158 0.159 0.160 0.162 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 6% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 16 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.7% AND FUEL FLOW BY 8.1%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 7.0%.

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REVISION 18

Cruise

Page 41

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 36000 37000 38000 39000 40000 41000

N1 % 78.6 79.8 81.1 82.8 84.5 85.5 Fuel Flow lb/h/Eng 1158 1169 1185 1235 1280 1267 IAS kt 215 213 211 215 219 214 55000 TAS kt 377 383 388 403 419 419 Ind. MACH 0.66 0.67 0.68 0.70 0.73 0.73 Buffet Marg G 1.80 1.75 1.69 1.68 1.67 1.59 SR NM/lb 0.163 0.164 0.164 0.163 0.164 0.165 N1 % 77.8 78.6 80.0 81.5 82.9 84.6 Fuel Flow lb/h/Eng 1122 1110 1128 1158 1189 1225 IAS kt 212 208 207 208 209 212 53000 TAS kt 373 374 382 391 402 416 Ind. MACH 0.65 0.65 0.67 0.68 0.70 0.72 Buffet Marg G 1.85 1.77 1.72 1.69 1.66 1.64 SR NM/lb 0.166 0.169 0.169 0.169 0.169 0.170 N1 % 76.9 77.8 78.7 80.2 81.6 83.3 Fuel Flow lb/h/Eng 1080 1071 1066 1091 1115 1157 IAS kt 208 205 202 203 203 206 51000 TAS kt 367 369 373 382 390 405 Ind. MACH 0.64 0.64 0.65 0.67 0.68 0.71 Buffet Marg G 1.88 1.80 1.74 1.71 1.67 1.66 SR NM/lb 0.170 0.172 0.175 0.175 0.175 0.175 N1 % 76.0 77.0 77.9 78.9 80.5 82.0 Fuel Flow lb/h/Eng 1036 1036 1028 1028 1058 1089 IAS kt 204 202 199 198 199 200 49000 TAS kt 360 365 368 374 384 395 Ind. MACH 0.63 0.64 0.64 0.65 0.67 0.69 Buffet Marg G 1.91 1.85 1.78 1.73 1.71 1.68 SR NM/lb 0.174 0.176 0.179 0.182 0.181 0.181 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 4% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 11 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.5% AND FUEL FLOW BY 7.8%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 7.0%.

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Page 42

Cruise

REVISION 18

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

FIXED SPEED CRUISE !EMBRAER 170 Models

These tables show N1, fuel flow, indicated airspeed, true airspeed, indicated Mach number, buffet margin and specific range. Data are presented for various weights and altitudes. Correction for ISA deviation and anti-ice are also presented.

AOM-1502-003

The associated conditions are: Flaps.......................................................................... UP Gear........................................................................... UP Bleeds........................................................................ OPEN Anti-ice....................................................................... OFF Center of gravity........................................................ 18% Minimum Remaining Rate of Climb.......................... 300 ft/min

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REVISION 18

Cruise

Page 43

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

320 KIAS CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

N1 % - 75.1 75.9 76.6 77.5 78.3 79.0 79.8 Fuel Flow lb/h/Eng - 2398 2390 2383 2398 2410 2411 2411 IAS kt 320 320 320 320 320 320 320 84000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.077 0.078 0.079 0.080 0.081 0.082 0.083 N1 % - 75.0 75.8 76.5 77.2 78.1 78.9 79.6 Fuel Flow lb/h/Eng - 2388 2381 2373 2375 2388 2395 2395 IAS kt 320 320 320 320 320 320 320 82000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.077 0.078 0.080 0.081 0.082 0.083 0.084 N1 % - 74.9 75.7 76.4 77.0 77.8 78.7 79.4 Fuel Flow lb/h/Eng - 2378 2371 2364 2356 2366 2376 2380 IAS kt 320 320 320 320 320 320 320 80000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.077 0.079 0.080 0.082 0.082 0.083 0.084 N1 % - 74.8 75.6 76.3 76.9 77.6 78.4 79.3 Fuel Flow lb/h/Eng - 2368 2362 2355 2348 2344 2356 2364 IAS kt 320 320 320 320 320 320 320 78000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.078 0.079 0.080 0.082 0.083 0.084 0.085 N1 % - 74.8 75.5 76.2 76.9 77.5 78.2 79.0 Fuel Flow lb/h/Eng - 2360 2352 2346 2340 2332 2335 2344 IAS kt 320 320 320 320 320 320 320 76000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.078 0.079 0.081 0.082 0.084 0.085 0.086 INCREASE/DECREASE N1(%) BY 1% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 5 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.2% AND FUEL FLOW BY 4.1%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 3.9%.

80.4 2412 320 407 0.65 2.50 0.084 80.3 2397 320 407 0.65 2.50 0.085 80.1 2381 320 407 0.65 2.50 0.085 80.0 2366 320 407 0.65 2.50 0.086 79.8 2350 320 407 0.65 2.50 0.087

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 44

Cruise

REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

320 KIAS CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

AOM-1502-003

N1 % - 74.7 75.4 76.1 76.8 77.4 78.0 78.8 Fuel Flow lb/h/Eng - 2353 2344 2337 2331 2324 2316 2325 IAS kt 320 320 320 320 320 320 320 74000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.078 0.080 0.081 0.082 0.084 0.085 0.086 N1 % - 74.6 75.3 76.0 76.7 77.3 77.9 78.6 Fuel Flow lb/h/Eng - 2347 2337 2328 2323 2317 2310 2305 IAS kt 320 320 320 320 320 320 320 72000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.078 0.080 0.081 0.083 0.084 0.086 0.087 N1 % - 74.6 75.3 76.0 76.6 77.2 77.9 78.5 Fuel Flow lb/h/Eng - 2340 2331 2322 2315 2309 2303 2295 IAS kt 320 320 320 320 320 320 320 70000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.079 0.080 0.082 0.083 0.084 0.086 0.087 N1 % - 74.5 75.2 75.9 76.5 77.1 77.8 78.4 Fuel Flow lb/h/Eng - 2333 2325 2316 2308 2302 2296 2288 IAS kt 320 320 320 320 320 320 320 68000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.079 0.080 0.082 0.083 0.085 0.086 0.088 N1 % - 74.4 75.1 75.9 76.5 77.1 77.7 78.3 Fuel Flow lb/h/Eng - 2327 2319 2311 2303 2294 2289 2282 IAS kt 320 320 320 320 320 320 320 66000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.079 0.080 0.082 0.083 0.085 0.086 0.088 INCREASE/DECREASE N1(%) BY 1% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 5 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.2% AND FUEL FLOW BY 4.2%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 4.0%.

79.6 2333 320 407 0.65 2.50 0.087 79.4 2314 320 407 0.65 2.50 0.088 79.2 2295 320 407 0.65 2.50 0.089 79.1 2281 320 407 0.65 2.50 0.089 79.0 2275 320 407 0.65 2.50 0.089

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 45

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

320 KIAS CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

N1 % - 74.3 75.1 75.8 76.4 77.0 77.6 78.3 Fuel Flow lb/h/Eng - 2320 2313 2305 2298 2290 2282 2276 IAS kt 320 320 320 320 320 320 320 64000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.079 0.081 0.082 0.084 0.085 0.087 0.088 N1 % - 74.3 75.0 75.8 76.4 77.0 77.6 78.2 Fuel Flow lb/h/Eng - 2313 2307 2300 2293 2285 2277 2269 IAS kt 320 320 320 320 320 320 320 62000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.080 0.081 0.082 0.084 0.085 0.087 0.088 N1 % - 74.2 74.9 75.7 76.3 76.9 77.5 78.1 Fuel Flow lb/h/Eng - 2310 2301 2294 2288 2280 2273 2264 IAS kt 320 320 320 320 320 320 320 60000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.080 0.081 0.083 0.084 0.085 0.087 0.089 N1 % - 74.2 74.9 75.6 76.3 76.9 77.5 78.1 Fuel Flow lb/h/Eng - 2307 2297 2289 2282 2276 2269 2261 IAS kt 320 320 320 320 320 320 320 58000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.080 0.081 0.083 0.084 0.086 0.087 0.089 N1 % - 74.2 74.9 75.6 76.2 76.8 77.5 78.1 Fuel Flow lb/h/Eng - 2304 2295 2285 2277 2271 2265 2257 IAS kt 320 320 320 320 320 320 320 56000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.080 0.081 0.083 0.084 0.086 0.087 0.089 INCREASE/DECREASE N1(%) BY 1% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 5 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.2% AND FUEL FLOW BY 4.2%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 4.0%.

78.9 2269 320 407 0.65 2.50 0.090 78.9 2263 320 407 0.65 2.50 0.090 78.8 2257 320 407 0.65 2.50 0.090 78.7 2252 320 407 0.65 2.50 0.090 78.7 2249 320 407 0.65 2.50 0.090

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 46

Cruise

REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

320 KIAS CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

AOM-1502-003

N1 % - 74.1 74.9 75.6 76.2 76.8 77.4 78.0 Fuel Flow lb/h/Eng - 2301 2292 2283 2274 2267 2261 2254 IAS kt 320 320 320 320 320 320 320 54000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.080 0.081 0.083 0.084 0.086 0.087 0.089 N1 % - 74.1 74.8 75.6 76.2 76.7 77.4 78.0 Fuel Flow lb/h/Eng - 2298 2290 2281 2272 2263 2256 2250 IAS kt 320 320 320 320 320 320 320 52000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.080 0.081 0.083 0.085 0.086 0.088 0.089 N1 % - 74.1 74.8 75.5 76.1 76.7 77.3 78.0 Fuel Flow lb/h/Eng - 2295 2287 2278 2270 2262 2254 2247 IAS kt 320 320 320 320 320 320 320 50000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.080 0.082 0.083 0.085 0.086 0.088 0.089 N1 % - 74.0 74.8 75.5 76.1 76.7 77.3 77.9 Fuel Flow lb/h/Eng - 2292 2284 2276 2269 2261 2253 2244 IAS kt 320 320 320 320 320 320 320 48000 TAS kt 368 373 379 384 390 395 401 Ind. MACH - 0.58 0.59 0.60 0.61 0.62 0.63 0.64 Buffet Marg G - 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb - 0.080 0.082 0.083 0.085 0.086 0.088 0.089 INCREASE/DECREASE N1(%) BY 1% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 5 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.2% AND FUEL FLOW BY 4.2%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 4.0%.

78.7 2246 320 407 0.65 2.50 0.091 78.6 2243 320 407 0.65 2.50 0.091 78.6 2240 320 407 0.65 2.50 0.091 78.6 2237 320 407 0.65 2.50 0.091

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 47

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

320 KIAS CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

N1 % 81.1 81.8 82.4 83.2 83.9 84.7 85.4 86.2 Fuel Flow lb/h/Eng 2414 2417 2422 2384 2392 2407 2422 2441 IAS kt 320 320 320 320 320 320 320 320 84000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.45 2.40 2.34 2.22 SR NM/lb 0.086 0.087 0.088 0.091 0.092 0.092 0.093 0.094 N1 % 80.9 81.6 82.3 83.0 83.7 84.5 85.3 86.0 Fuel Flow lb/h/Eng 2398 2402 2406 2369 2376 2388 2403 2422 IAS kt 320 320 320 320 320 320 320 320 82000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.45 2.40 2.27 SR NM/lb 0.086 0.087 0.088 0.091 0.092 0.093 0.094 0.095 N1 % 80.8 81.5 82.1 82.8 83.6 84.3 85.1 85.9 Fuel Flow lb/h/Eng 2383 2386 2390 2353 2361 2371 2384 2404 IAS kt 320 320 320 320 320 320 320 320 80000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.45 2.33 SR NM/lb 0.087 0.088 0.089 0.092 0.093 0.094 0.095 0.095 N1 % 80.6 81.3 82.0 82.7 83.4 84.2 84.9 85.7 Fuel Flow lb/h/Eng 2367 2370 2374 2337 2345 2354 2366 2386 IAS kt 320 320 320 320 320 320 320 320 78000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.39 SR NM/lb 0.087 0.088 0.090 0.092 0.093 0.094 0.095 0.096 N1 % 80.5 81.2 81.8 82.5 83.2 84.0 84.7 85.5 Fuel Flow lb/h/Eng 2351 2355 2359 2322 2329 2338 2349 2368 IAS kt 320 320 320 320 320 320 320 320 76000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.45 SR NM/lb 0.088 0.089 0.090 0.093 0.094 0.095 0.096 0.097 INCREASE/DECREASE N1(%) BY 1% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 5 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.4% AND FUEL FLOW BY 4.0%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 3.9%.

86.9 2456 320 465 0.78 2.07 0.095 86.7 2438 320 465 0.78 2.12 0.095 86.6 2419 320 465 0.78 2.18 0.096 86.4 2400 320 465 0.78 2.23 0.097 86.2 2381 320 465 0.78 2.29 0.098

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 48

Cruise

REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

320 KIAS CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

AOM-1502-003

N1 % 80.4 81.0 81.7 82.4 83.1 83.8 84.6 85.3 Fuel Flow lb/h/Eng 2336 2339 2343 2306 2313 2322 2332 2350 IAS kt 320 320 320 320 320 320 320 320 74000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb 0.088 0.090 0.091 0.094 0.095 0.096 0.097 0.097 N1 % 80.2 80.9 81.5 82.2 82.9 83.6 84.4 85.1 Fuel Flow lb/h/Eng 2320 2323 2327 2291 2297 2305 2316 2332 IAS kt 320 320 320 320 320 320 320 320 72000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb 0.089 0.090 0.091 0.094 0.095 0.096 0.097 0.098 N1 % 80.0 80.7 81.4 82.0 82.7 83.5 84.2 85.0 Fuel Flow lb/h/Eng 2302 2308 2311 2275 2281 2289 2299 2314 IAS kt 320 320 320 320 320 320 320 320 70000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb 0.090 0.091 0.092 0.095 0.096 0.097 0.098 0.099 N1 % 79.8 80.5 81.2 81.9 82.6 83.3 84.0 84.8 Fuel Flow lb/h/Eng 2285 2292 2296 2259 2265 2273 2282 2295 IAS kt 320 320 320 320 320 320 320 320 68000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb 0.090 0.091 0.093 0.096 0.097 0.098 0.099 0.100 N1 % 79.6 80.4 81.0 81.7 82.4 83.1 83.8 84.6 Fuel Flow lb/h/Eng 2267 2275 2280 2244 2250 2256 2265 2277 IAS kt 320 320 320 320 320 320 320 320 66000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb 0.091 0.092 0.093 0.096 0.097 0.099 0.100 0.101 INCREASE/DECREASE N1(%) BY 1% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 5 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.4% AND FUEL FLOW BY 4.1%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 4.0%.

86.0 2362 320 465 0.78 2.35 0.098 85.8 2343 320 465 0.78 2.42 0.099 85.7 2324 320 465 0.78 2.49 0.100 85.5 2305 320 465 0.78 2.50 0.101 85.3 2286 320 465 0.78 2.50 0.102

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 49

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

320 KIAS CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

N1 % 79.6 80.2 80.9 81.6 82.2 82.9 83.7 84.4 Fuel Flow lb/h/Eng 2261 2259 2265 2228 2234 2240 2248 2259 IAS kt 320 320 320 320 320 320 320 320 64000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb 0.091 0.093 0.094 0.097 0.098 0.099 0.100 0.101 N1 % 79.5 80.1 80.7 81.4 82.1 82.8 83.5 84.2 Fuel Flow lb/h/Eng 2256 2249 2249 2214 2218 2224 2231 2241 IAS kt 320 320 320 320 320 320 320 320 62000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb 0.092 0.093 0.095 0.098 0.099 0.100 0.101 0.102 N1 % 79.4 80.0 80.6 81.3 81.9 82.6 83.3 84.0 Fuel Flow lb/h/Eng 2250 2245 2237 2200 2203 2208 2215 2223 IAS kt 320 320 320 320 320 320 320 320 60000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb 0.092 0.093 0.095 0.098 0.099 0.101 0.102 0.103 N1 % 79.4 80.0 80.6 81.1 81.8 82.4 83.1 83.8 Fuel Flow lb/h/Eng 2245 2240 2233 2188 2191 2192 2198 2206 IAS kt 320 320 320 320 320 320 320 320 58000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb 0.092 0.094 0.095 0.099 0.100 0.101 0.103 0.104 N1 % 79.3 79.9 80.5 81.1 81.7 82.3 82.9 83.6 Fuel Flow lb/h/Eng 2240 2235 2229 2184 2179 2181 2181 2188 IAS kt 320 320 320 320 320 320 320 320 56000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb 0.092 0.094 0.095 0.099 0.101 0.102 0.103 0.105 INCREASE/DECREASE N1(%) BY 1% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 5 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.4% AND FUEL FLOW BY 4.2%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 4.0%.

85.1 2266 320 465 0.78 2.50 0.103 84.9 2248 320 465 0.78 2.50 0.103 84.7 2231 320 465 0.78 2.50 0.104 84.5 2213 320 465 0.78 2.50 0.105 84.3 2196 320 465 0.78 2.50 0.106

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 50

Cruise

REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

320 KIAS CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

AOM-1502-003

N1 % 79.3 79.9 80.5 81.1 81.6 82.2 82.8 83.4 Fuel Flow lb/h/Eng 2238 2230 2225 2180 2175 2171 2171 2171 IAS kt 320 320 320 320 320 320 320 320 54000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb 0.092 0.094 0.096 0.099 0.101 0.102 0.104 0.106 N1 % 79.3 79.9 80.5 81.0 81.6 82.1 82.7 83.3 Fuel Flow lb/h/Eng 2235 2228 2220 2176 2171 2166 2163 2161 IAS kt 320 320 320 320 320 320 320 320 52000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb 0.092 0.094 0.096 0.099 0.101 0.103 0.104 0.106 N1 % 79.2 79.8 80.4 81.0 81.6 82.1 82.7 83.2 Fuel Flow lb/h/Eng 2233 2226 2218 2172 2168 2163 2158 2154 IAS kt 320 320 320 320 320 320 320 320 50000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb 0.093 0.094 0.096 0.099 0.101 0.103 0.105 0.106 N1 % 79.2 79.8 80.4 81.0 81.5 82.1 82.6 83.2 Fuel Flow lb/h/Eng 2230 2224 2216 2170 2165 2161 2156 2150 IAS kt 320 320 320 320 320 320 320 320 48000 TAS kt 413 419 425 432 438 445 451 458 Ind. MACH 0.67 0.68 0.69 0.71 0.72 0.73 0.75 0.76 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb 0.093 0.094 0.096 0.099 0.101 0.103 0.105 0.107 INCREASE/DECREASE N1(%) BY 1% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 5 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.4% AND FUEL FLOW BY 4.2%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 4.0%.

84.1 2179 320 465 0.78 2.50 0.107 83.9 2161 320 465 0.78 2.50 0.108 83.8 2150 320 465 0.78 2.50 0.108 83.8 2146 320 465 0.78 2.50 0.108

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 51

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

320 KIAS CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

N1 % 87.9 Fuel Flow lb/h/Eng 2487 IAS kt 320 84000 TAS kt 472 Ind. MACH 0.79 Buffet Marg G 1.93 SR NM/lb 0.095 N1 % 87.7 Fuel Flow lb/h/Eng 2469 IAS kt 320 82000 TAS kt 472 Ind. MACH 0.79 Buffet Marg G 1.98 SR NM/lb 0.096 N1 % 87.5 Fuel Flow lb/h/Eng 2452 IAS kt 320 80000 TAS kt 472 Ind. MACH 0.79 Buffet Marg G 2.02 SR NM/lb 0.096 N1 % 87.3 Fuel Flow lb/h/Eng 2434 IAS kt 320 78000 TAS kt 472 Ind. MACH 0.79 Buffet Marg G 2.08 SR NM/lb 0.097 N1 % 87.2 Fuel Flow lb/h/Eng 2417 IAS kt 320 76000 TAS kt 472 Ind. MACH 0.79 Buffet Marg G 2.13 SR NM/lb 0.098 INCREASE/DECREASE N1(%) BY 1% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.4% AND FUEL FLOW BY 3.7%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 3.6%.

-

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REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

320 KIAS CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

AOM-1502-003

N1 % 87.0 88.6 Fuel Flow lb/h/Eng 2399 2496 IAS kt 320 320 74000 TAS kt 472 479 Ind. MACH 0.79 0.81 Buffet Marg G 2.19 2.01 SR NM/lb 0.098 0.096 N1 % 86.8 88.5 Fuel Flow lb/h/Eng 2382 2485 IAS kt 320 320 72000 TAS kt 472 479 Ind. MACH 0.79 0.81 Buffet Marg G 2.25 2.06 SR NM/lb 0.099 0.096 N1 % 86.6 88.3 Fuel Flow lb/h/Eng 2364 2466 IAS kt 320 320 70000 TAS kt 472 479 Ind. MACH 0.79 0.81 Buffet Marg G 2.31 2.12 SR NM/lb 0.100 0.097 N1 % 86.5 88.1 Fuel Flow lb/h/Eng 2346 2446 IAS kt 320 320 68000 TAS kt 472 479 Ind. MACH 0.79 0.81 Buffet Marg G 2.38 2.19 SR NM/lb 0.101 0.098 N1 % 86.2 87.9 Fuel Flow lb/h/Eng 2324 2427 IAS kt 320 320 66000 TAS kt 472 479 Ind. MACH 0.79 0.81 Buffet Marg G 2.45 2.25 SR NM/lb 0.102 0.099 INCREASE/DECREASE N1(%) BY 1% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.4% AND FUEL FLOW BY 3.8%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 3.7%.

-

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 53

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

320 KIAS CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

N1 % 86.0 87.6 Fuel Flow lb/h/Eng 2302 2401 IAS kt 320 320 64000 TAS kt 472 479 Ind. MACH 0.79 0.81 Buffet Marg G 2.50 2.32 SR NM/lb 0.103 0.100 N1 % 85.8 87.3 Fuel Flow lb/h/Eng 2280 2369 IAS kt 320 320 62000 TAS kt 472 479 Ind. MACH 0.79 0.81 Buffet Marg G 2.50 2.40 SR NM/lb 0.104 0.101 N1 % 85.6 87.0 Fuel Flow lb/h/Eng 2258 2337 IAS kt 320 320 60000 TAS kt 472 479 Ind. MACH 0.79 0.81 Buffet Marg G 2.50 2.48 SR NM/lb 0.105 0.103 N1 % 85.4 86.6 Fuel Flow lb/h/Eng 2237 2305 IAS kt 320 320 58000 TAS kt 472 479 Ind. MACH 0.79 0.81 Buffet Marg G 2.50 2.50 SR NM/lb 0.106 0.104 N1 % 85.1 86.3 Fuel Flow lb/h/Eng 2216 2274 IAS kt 320 320 56000 TAS kt 472 479 Ind. MACH 0.79 0.81 Buffet Marg G 2.50 2.50 SR NM/lb 0.107 0.105 INCREASE/DECREASE N1(%) BY 1% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.4% AND FUEL FLOW BY 3.9%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 3.7%.

-

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Cruise

REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

320 KIAS CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

AOM-1502-003

N1 % 84.9 86.0 Fuel Flow lb/h/Eng 2195 2242 IAS kt 320 320 54000 TAS kt 472 479 Ind. MACH 0.79 0.81 Buffet Marg G 2.50 2.50 SR NM/lb 0.108 0.107 N1 % 84.7 85.7 Fuel Flow lb/h/Eng 2173 2210 IAS kt 320 320 52000 TAS kt 472 479 Ind. MACH 0.79 0.81 Buffet Marg G 2.50 2.50 SR NM/lb 0.109 0.108 N1 % 84.5 85.3 Fuel Flow lb/h/Eng 2152 2178 IAS kt 320 320 50000 TAS kt 472 479 Ind. MACH 0.79 0.81 Buffet Marg G 2.50 2.50 SR NM/lb 0.110 0.110 N1 % 84.3 85.0 Fuel Flow lb/h/Eng 2139 2147 IAS kt 320 320 48000 TAS kt 472 479 Ind. MACH 0.79 0.81 Buffet Marg G 2.50 2.50 SR NM/lb 0.110 0.112 INCREASE/DECREASE N1(%) BY 1% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.4% AND FUEL FLOW BY 4.0%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 3.8%.

-

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 55

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

MACH 0.78 CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

N1 % 87.2 87.2 87.4 87.6 87.8 88.1 Fuel Flow lb/h/Eng 2403 2327 2259 2193 2131 2079 IAS kt 315 309 302 296 289 283 84000 TAS kt 466 464 462 460 458 456 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 1.97 1.88 1.80 1.72 1.64 1.57 SR NM/lb 0.097 0.100 0.102 0.105 0.107 0.110 N1 % 87.0 87.0 87.2 87.3 87.5 87.7 88.3 Fuel Flow lb/h/Eng 2384 2305 2237 2170 2108 2049 2012 IAS kt 315 309 302 296 289 283 277 82000 TAS kt 466 464 462 460 458 456 454 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.02 1.93 1.84 1.76 1.68 1.61 1.53 SR NM/lb 0.098 0.101 0.103 0.106 0.109 0.111 0.113 N1 % 86.8 86.8 86.9 87.0 87.2 87.4 87.8 Fuel Flow lb/h/Eng 2365 2286 2214 2148 2085 2026 1975 IAS kt 315 309 302 296 289 283 277 80000 TAS kt 466 464 462 460 458 456 454 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.07 1.98 1.89 1.81 1.73 1.65 1.57 SR NM/lb 0.098 0.101 0.104 0.107 0.110 0.112 0.115 N1 % 86.6 86.6 86.7 86.8 86.9 87.1 87.4 87.9 Fuel Flow lb/h/Eng 2347 2267 2192 2125 2063 2003 1947 1908 IAS kt 315 309 302 296 289 283 277 271 78000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.12 2.03 1.94 1.85 1.77 1.69 1.61 1.54 SR NM/lb 0.099 0.102 0.105 0.108 0.111 0.114 0.117 0.118 N1 % 86.4 86.4 86.5 86.5 86.7 86.8 87.0 87.3 Fuel Flow lb/h/Eng 2328 2248 2173 2103 2040 1980 1923 1872 IAS kt 315 309 302 296 289 283 277 271 76000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.18 2.08 1.99 1.90 1.82 1.74 1.66 1.58 SR NM/lb 0.100 0.103 0.106 0.109 0.112 0.115 0.118 0.121 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.7% AND FUEL FLOW BY 5.6%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 5.3%.

88.1 1847 264 450 0.78 1.51 0.122

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REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

MACH 0.78 CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

AOM-1502-003

N1 % 86.2 86.2 86.2 86.2 86.4 86.5 86.7 86.9 Fuel Flow lb/h/Eng 2309 2229 2154 2081 2017 1957 1900 1845 IAS kt 315 309 302 296 289 283 277 271 74000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.24 2.14 2.04 1.95 1.87 1.78 1.70 1.62 SR NM/lb 0.101 0.104 0.107 0.110 0.113 0.116 0.119 0.122 N1 % 86.1 86.0 86.0 86.0 86.1 86.2 86.4 86.5 Fuel Flow lb/h/Eng 2291 2210 2135 2062 1994 1934 1877 1822 IAS kt 315 309 302 296 289 283 277 271 72000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.30 2.20 2.10 2.01 1.92 1.83 1.75 1.67 SR NM/lb 0.102 0.105 0.108 0.111 0.115 0.118 0.121 0.124 N1 % 85.9 85.8 85.8 85.8 85.8 85.9 86.0 86.2 Fuel Flow lb/h/Eng 2272 2192 2116 2043 1975 1911 1854 1799 IAS kt 315 309 302 296 289 283 277 271 70000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.36 2.26 2.16 2.06 1.97 1.88 1.80 1.72 SR NM/lb 0.102 0.106 0.109 0.113 0.116 0.119 0.122 0.126 N1 % 85.7 85.6 85.6 85.5 85.6 85.6 85.7 85.8 Fuel Flow lb/h/Eng 2253 2173 2098 2023 1956 1889 1832 1776 IAS kt 315 309 302 296 289 283 277 271 68000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.43 2.33 2.22 2.13 2.03 1.94 1.85 1.77 SR NM/lb 0.103 0.107 0.110 0.114 0.117 0.121 0.124 0.127 N1 % 85.5 85.4 85.4 85.3 85.3 85.3 85.4 85.5 Fuel Flow lb/h/Eng 2234 2154 2080 2004 1938 1869 1810 1753 IAS kt 315 309 302 296 289 283 277 271 66000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.40 2.29 2.19 2.09 2.00 1.91 1.82 SR NM/lb 0.104 0.108 0.111 0.115 0.118 0.122 0.125 0.129 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.9% AND FUEL FLOW BY 6.3%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 5.9%.

87.5 1809 264 450 0.78 1.55 0.124 86.8 1772 264 450 0.78 1.59 0.127 86.5 1748 264 450 0.78 1.64 0.129 86.1 1724 264 450 0.78 1.68 0.130 85.7 1702 264 450 0.78 1.74 0.132

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 57

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

MACH 0.78 CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

N1 % 85.3 85.2 85.2 85.1 85.1 85.0 85.1 85.1 Fuel Flow lb/h/Eng 2216 2134 2062 1985 1920 1850 1791 1729 IAS kt 315 309 302 296 289 283 277 271 64000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.47 2.36 2.26 2.16 2.06 1.97 1.88 SR NM/lb 0.105 0.109 0.112 0.116 0.119 0.123 0.127 0.131 N1 % 85.1 85.0 85.0 84.9 84.9 84.8 84.9 84.8 Fuel Flow lb/h/Eng 2197 2115 2044 1967 1902 1833 1772 1709 IAS kt 315 309 302 296 289 283 277 271 62000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.50 2.44 2.33 2.23 2.13 2.03 1.94 SR NM/lb 0.106 0.110 0.113 0.117 0.120 0.124 0.128 0.132 N1 % 84.9 84.8 84.7 84.7 84.6 84.6 84.6 84.6 Fuel Flow lb/h/Eng 2178 2097 2025 1951 1884 1816 1754 1692 IAS kt 315 309 302 296 289 283 277 271 60000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.50 2.50 2.41 2.30 2.20 2.10 2.00 SR NM/lb 0.107 0.111 0.114 0.118 0.121 0.125 0.129 0.133 N1 % 84.7 84.6 84.5 84.4 84.4 84.3 84.3 84.3 Fuel Flow lb/h/Eng 2159 2079 2006 1933 1866 1799 1736 1675 IAS kt 315 309 302 296 289 283 277 271 58000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.50 2.50 2.49 2.38 2.27 2.17 2.07 SR NM/lb 0.108 0.111 0.115 0.119 0.123 0.127 0.131 0.135 N1 % 84.5 84.4 84.3 84.2 84.2 84.1 84.1 84.1 Fuel Flow lb/h/Eng 2141 2062 1987 1916 1848 1782 1719 1658 IAS kt 315 309 302 296 289 283 277 271 56000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.50 2.50 2.50 2.47 2.35 2.25 2.14 SR NM/lb 0.109 0.112 0.116 0.120 0.124 0.128 0.132 0.136 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.9% AND FUEL FLOW BY 6.6%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 6.2%.

85.4 1680 264 450 0.78 1.79 0.134 85.0 1658 264 450 0.78 1.85 0.136 84.6 1636 264 450 0.78 1.91 0.137 84.3 1616 264 450 0.78 1.97 0.139 84.1 1599 264 450 0.78 2.05 0.141

6-15 Copyright © by Embraer. Refer to cover page for details.

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Cruise

REVISION 18

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

MACH 0.78 CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

AOM-1502-003

N1 % 84.3 84.2 84.1 84.0 83.9 83.9 83.8 83.8 Fuel Flow lb/h/Eng 2122 2044 1970 1898 1831 1765 1702 1641 IAS kt 315 309 302 296 289 283 277 271 54000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.44 2.33 2.22 SR NM/lb 0.110 0.113 0.117 0.121 0.125 0.129 0.133 0.138 N1 % 84.1 83.9 83.8 83.8 83.7 83.6 83.6 83.6 Fuel Flow lb/h/Eng 2104 2026 1952 1880 1813 1748 1685 1625 IAS kt 315 309 302 296 289 283 277 271 52000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.42 2.31 SR NM/lb 0.111 0.114 0.118 0.122 0.126 0.130 0.135 0.139 N1 % 83.9 83.7 83.6 83.5 83.5 83.4 83.4 83.3 Fuel Flow lb/h/Eng 2087 2009 1934 1863 1795 1730 1667 1608 IAS kt 315 309 302 296 289 283 277 271 50000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.40 SR NM/lb 0.112 0.115 0.119 0.123 0.127 0.132 0.136 0.140 N1 % 83.7 83.5 83.4 83.3 83.2 83.2 83.1 83.1 Fuel Flow lb/h/Eng 2075 1991 1917 1845 1778 1712 1650 1590 IAS kt 315 309 302 296 289 283 277 271 48000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 SR NM/lb 0.112 0.116 0.120 0.125 0.129 0.133 0.137 0.142 INCREASE/DECREASE N1(%) BY 1% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.8% AND FUEL FLOW BY 6.7%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 6.3%.

83.8 1582 264 450 0.78 2.12 0.142 83.6 1565 264 450 0.78 2.20 0.144 83.3 1548 264 450 0.78 2.29 0.145 83.0 1532 264 450 0.78 2.39 0.147

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REVISION 18

Cruise

Page 59

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

MACH 0.78 CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 36000 37000 38000 39000 40000 41000

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REVISION 18

AOM-1502-003

N1 % Fuel Flow lb/h/Eng IAS kt 74000 TAS kt Ind. MACH Buffet Marg G SR NM/lb N1 % 87.5 Fuel Flow lb/h/Eng 1746 IAS kt 258 72000 TAS kt 448 Ind. MACH 0.78 Buffet Marg G 1.52 SR NM/lb 0.128 N1 % 86.9 Fuel Flow lb/h/Eng 1707 IAS kt 258 70000 TAS kt 448 Ind. MACH 0.78 Buffet Marg G 1.56 SR NM/lb 0.131 N1 % 86.3 87.3 Fuel Flow lb/h/Eng 1674 1656 IAS kt 258 252 68000 TAS kt 448 447 Ind. MACH 0.78 0.78 Buffet Marg G 1.61 1.53 SR NM/lb 0.134 0.135 N1 % 85.8 86.6 Fuel Flow lb/h/Eng 1650 1618 IAS kt 258 252 66000 TAS kt 448 447 Ind. MACH 0.78 0.78 Buffet Marg G 1.65 1.58 SR NM/lb 0.136 0.138 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.5% AND FUEL FLOW BY 6.4%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 6.0%.

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

MACH 0.78 CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 36000 37000 38000 39000 40000 41000

AOM-1502-003

N1 % 85.4 86.2 87.0 Fuel Flow lb/h/Eng 1626 1592 1568 IAS kt 258 252 247 64000 TAS kt 448 447 447 Ind. MACH 0.78 0.78 0.78 Buffet Marg G 1.71 1.63 1.55 SR NM/lb 0.138 0.140 0.143 N1 % 85.0 85.8 86.4 Fuel Flow lb/h/Eng 1602 1570 1533 IAS kt 258 252 247 62000 TAS kt 448 447 447 Ind. MACH 0.78 0.78 0.78 Buffet Marg G 1.76 1.68 1.60 SR NM/lb 0.140 0.142 0.146 N1 % 84.7 85.4 85.9 86.7 Fuel Flow lb/h/Eng 1582 1548 1509 1480 IAS kt 258 252 247 241 60000 TAS kt 448 447 447 447 Ind. MACH 0.78 0.78 0.78 0.78 Buffet Marg G 1.82 1.73 1.65 1.58 SR NM/lb 0.141 0.144 0.148 0.151 N1 % 84.4 85.0 85.4 86.2 87.0 Fuel Flow lb/h/Eng 1562 1527 1485 1455 1432 IAS kt 258 252 247 241 235 58000 TAS kt 448 447 447 447 447 Ind. MACH 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 1.88 1.79 1.71 1.63 1.55 SR NM/lb 0.143 0.147 0.151 0.154 0.156 N1 % 84.1 84.6 85.0 85.8 86.3 Fuel Flow lb/h/Eng 1543 1505 1461 1433 1399 IAS kt 258 252 247 241 235 56000 TAS kt 448 447 447 447 447 Ind. MACH 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 1.95 1.86 1.77 1.69 1.61 SR NM/lb 0.145 0.149 0.153 0.156 0.160 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.5% AND FUEL FLOW BY 7.1%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 6.6%.

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REVISION 18

Cruise

Page 61

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

MACH 0.78 CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 36000 37000 38000 39000 40000 41000

N1 % 83.8 84.3 84.6 85.3 85.8 86.5 Fuel Flow lb/h/Eng 1526 1483 1441 1411 1375 1348 IAS kt 258 252 247 241 235 230 54000 TAS kt 448 447 447 447 447 447 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.02 1.93 1.84 1.75 1.67 1.59 SR NM/lb 0.147 0.151 0.155 0.159 0.163 0.166 N1 % 83.6 83.9 84.3 84.9 85.3 86.0 Fuel Flow lb/h/Eng 1509 1464 1421 1389 1350 1327 IAS kt 258 252 247 241 235 230 52000 TAS kt 448 447 447 447 447 447 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.10 2.00 1.91 1.82 1.73 1.65 SR NM/lb 0.148 0.153 0.157 0.161 0.166 0.169 N1 % 83.3 83.6 84.0 84.5 84.8 85.6 Fuel Flow lb/h/Eng 1492 1447 1404 1368 1329 1307 IAS kt 258 252 247 241 235 230 50000 TAS kt 448 447 447 447 447 447 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.18 2.08 1.98 1.89 1.80 1.72 SR NM/lb 0.150 0.155 0.159 0.164 0.168 0.171 N1 % 83.0 83.4 83.7 84.1 84.4 85.1 Fuel Flow lb/h/Eng 1475 1430 1387 1347 1310 1286 IAS kt 258 252 247 241 235 230 48000 TAS kt 448 447 447 447 447 447 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.27 2.17 2.07 1.97 1.88 1.79 SR NM/lb 0.152 0.156 0.161 0.166 0.171 0.174 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.6% AND FUEL FLOW BY 7.4%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 6.9%.

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AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

FIXED SPEED CRUISE !EMBRAER 175 Models

These tables show N1, fuel flow, indicated airspeed, true airspeed, indicated Mach number, buffet margin and specific range. Data are presented for various weights and altitudes. Correction for ISA deviation and anti-ice are also presented.

AOM-1502-003

The associated conditions are: Flaps.......................................................................... UP Gear........................................................................... UP Bleeds........................................................................ OPEN Anti-ice....................................................................... OFF Center of gravity........................................................ 18% Minimum Remaining Rate of Climb.......................... 300 ft/min

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REVISION 18

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FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

MACH 0.78 CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

N1 % 87.7 87.8 88.0 88.2 88.4 Fuel Flow lb/h/Eng 2454 2379 2309 2242 2178 IAS kt 315 309 302 296 289 85000 TAS kt 466 464 462 460 458 Ind. MACH 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 1.95 1.86 1.78 1.70 1.62 SR NM/lb 0.095 0.097 0.100 0.103 0.105 N1 % 87.5 87.6 87.7 87.9 88.1 88.4 Fuel Flow lb/h/Eng 2435 2356 2287 2219 2156 2096 IAS kt 315 309 302 296 289 283 83000 TAS kt 466 464 462 460 458 456 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 1.99 1.91 1.82 1.74 1.66 1.59 SR NM/lb 0.096 0.098 0.101 0.104 0.106 0.109 N1 % 87.3 87.3 87.5 87.6 87.8 88.1 Fuel Flow lb/h/Eng 2416 2336 2265 2197 2133 2072 IAS kt 315 309 302 296 289 283 81000 TAS kt 466 464 462 460 458 456 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.04 1.95 1.87 1.78 1.70 1.63 SR NM/lb 0.096 0.099 0.102 0.105 0.107 0.110 N1 % 87.1 87.1 87.2 87.4 87.6 87.7 88.0 Fuel Flow lb/h/Eng 2398 2317 2242 2174 2110 2049 1992 IAS kt 315 309 302 296 289 283 277 79000 TAS kt 466 464 462 460 458 456 454 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.09 2.00 1.91 1.83 1.75 1.67 1.59 SR NM/lb 0.097 0.100 0.103 0.106 0.108 0.111 0.114 N1 % 86.9 86.9 87.0 87.1 87.3 87.4 87.7 88.1 Fuel Flow lb/h/Eng 2379 2298 2222 2151 2087 2027 1969 1923 IAS kt 315 309 302 296 289 283 277 271 77000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.15 2.05 1.96 1.88 1.79 1.71 1.63 1.56 SR NM/lb 0.098 0.101 0.104 0.107 0.110 0.112 0.115 0.117 INCREASE/DECREASE N1(%) BY 1% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.6% AND FUEL FLOW BY 4.7%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 4.5%.

-

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AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

MACH 0.78 CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

AOM-1502-003

N1 % 86.8 86.7 86.8 86.8 87.0 87.1 87.4 87.6 Fuel Flow lb/h/Eng 2360 2279 2202 2129 2065 2004 1946 1889 IAS kt 315 309 302 296 289 283 277 271 75000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.21 2.11 2.02 1.93 1.84 1.76 1.68 1.60 SR NM/lb 0.099 0.102 0.105 0.108 0.111 0.114 0.117 0.120 N1 % 86.6 86.5 86.6 86.6 86.7 86.8 87.0 87.2 Fuel Flow lb/h/Eng 2341 2260 2183 2109 2042 1981 1922 1866 IAS kt 315 309 302 296 289 283 277 271 73000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.27 2.17 2.07 1.98 1.89 1.81 1.72 1.65 SR NM/lb 0.099 0.103 0.106 0.109 0.112 0.115 0.118 0.121 N1 % 86.4 86.3 86.4 86.3 86.4 86.5 86.7 86.9 Fuel Flow lb/h/Eng 2323 2241 2164 2090 2020 1958 1899 1843 IAS kt 315 309 302 296 289 283 277 271 71000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.33 2.23 2.13 2.04 1.94 1.86 1.77 1.69 SR NM/lb 0.100 0.103 0.107 0.110 0.113 0.116 0.119 0.123 N1 % 86.2 86.1 86.1 86.1 86.1 86.2 86.3 86.5 Fuel Flow lb/h/Eng 2304 2222 2145 2070 2000 1935 1876 1820 IAS kt 315 309 302 296 289 283 277 271 69000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.40 2.29 2.19 2.09 2.00 1.91 1.82 1.74 SR NM/lb 0.101 0.104 0.108 0.111 0.114 0.118 0.121 0.124 N1 % 86.0 85.9 85.9 85.9 85.9 85.9 86.0 86.1 Fuel Flow lb/h/Eng 2285 2203 2126 2051 1981 1914 1853 1796 IAS kt 315 309 302 296 289 283 277 271 67000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.47 2.36 2.26 2.16 2.06 1.97 1.88 1.79 SR NM/lb 0.102 0.105 0.109 0.112 0.116 0.119 0.122 0.126 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.8% AND FUEL FLOW BY 6.2%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 5.8%.

88.3 1860 264 450 0.78 1.53 0.121 87.7 1822 264 450 0.78 1.57 0.123 87.2 1791 264 450 0.78 1.61 0.125 86.8 1768 264 450 0.78 1.66 0.127 86.4 1744 264 450 0.78 1.71 0.129

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REVISION 18

Cruise

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FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

MACH 0.78 CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

N1 % 85.8 85.7 85.7 85.6 85.7 85.6 85.7 85.8 Fuel Flow lb/h/Eng 2265 2184 2107 2032 1963 1894 1831 1773 IAS kt 315 309 302 296 289 283 277 271 65000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.43 2.33 2.22 2.12 2.03 1.94 1.85 SR NM/lb 0.103 0.106 0.110 0.113 0.117 0.120 0.124 0.127 N1 % 85.6 85.5 85.5 85.4 85.4 85.4 85.4 85.4 Fuel Flow lb/h/Eng 2245 2164 2089 2013 1945 1874 1813 1750 IAS kt 315 309 302 296 289 283 277 271 63000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.50 2.40 2.29 2.19 2.09 2.00 1.91 SR NM/lb 0.104 0.107 0.110 0.114 0.118 0.122 0.125 0.129 N1 % 85.4 85.3 85.3 85.2 85.2 85.1 85.2 85.1 Fuel Flow lb/h/Eng 2227 2144 2071 1993 1927 1855 1794 1728 IAS kt 315 309 302 296 289 283 277 271 61000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.50 2.48 2.37 2.26 2.16 2.06 1.97 SR NM/lb 0.105 0.108 0.111 0.115 0.119 0.123 0.126 0.131 N1 % 85.2 85.1 85.0 85.0 85.0 84.9 84.9 84.8 Fuel Flow lb/h/Eng 2208 2124 2052 1974 1908 1837 1776 1711 IAS kt 315 309 302 296 289 283 277 271 59000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.50 2.50 2.45 2.34 2.23 2.13 2.04 SR NM/lb 0.105 0.109 0.113 0.116 0.120 0.124 0.128 0.132 N1 % 85.0 84.9 84.8 84.7 84.7 84.6 84.6 84.6 Fuel Flow lb/h/Eng 2189 2106 2033 1957 1890 1820 1757 1694 IAS kt 315 309 302 296 289 283 277 271 57000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.50 2.50 2.50 2.42 2.31 2.21 2.11 SR NM/lb 0.106 0.110 0.114 0.117 0.121 0.125 0.129 0.133 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.9% AND FUEL FLOW BY 6.6%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 6.2%.

86.0 1720 264 450 0.78 1.76 0.131 85.6 1698 264 450 0.78 1.82 0.132 85.3 1676 264 450 0.78 1.88 0.134 84.9 1655 264 450 0.78 1.94 0.136 84.6 1636 264 450 0.78 2.01 0.137

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AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

MACH 0.78 CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

AOM-1502-003

N1 % 84.8 84.7 84.6 84.5 84.5 84.4 84.4 84.3 Fuel Flow lb/h/Eng 2170 2088 2014 1939 1871 1803 1739 1677 IAS kt 315 309 302 296 289 283 277 271 55000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.40 2.29 2.18 SR NM/lb 0.107 0.111 0.115 0.119 0.122 0.126 0.130 0.135 N1 % 84.6 84.5 84.4 84.3 84.2 84.2 84.1 84.1 Fuel Flow lb/h/Eng 2152 2070 1995 1921 1853 1786 1722 1660 IAS kt 315 309 302 296 289 283 277 271 53000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.49 2.37 2.27 SR NM/lb 0.108 0.112 0.116 0.120 0.124 0.128 0.132 0.136 N1 % 84.4 84.3 84.2 84.1 84.0 83.9 83.9 83.9 Fuel Flow lb/h/Eng 2133 2053 1977 1904 1835 1768 1705 1643 IAS kt 315 309 302 296 289 283 277 271 51000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.47 2.35 SR NM/lb 0.109 0.113 0.117 0.121 0.125 0.129 0.133 0.137 N1 % 84.2 84.1 83.9 83.8 83.8 83.7 83.6 83.6 Fuel Flow lb/h/Eng 2115 2035 1959 1886 1817 1751 1687 1626 IAS kt 315 309 302 296 289 283 277 271 49000 TAS kt 466 464 462 460 458 456 454 452 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.45 SR NM/lb 0.110 0.114 0.118 0.122 0.126 0.130 0.134 0.139 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.9% AND FUEL FLOW BY 6.7%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 6.3%.

84.3 1617 264 450 0.78 2.08 0.139 84.1 1600 264 450 0.78 2.16 0.141 83.8 1583 264 450 0.78 2.25 0.142 83.6 1566 264 450 0.78 2.34 0.144

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REVISION 18

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FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

MACH 0.78 CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 36000 37000 38000 39000 40000 41000

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AOM-1502-003

N1 % Fuel Flow lb/h/Eng IAS kt 75000 TAS kt Ind. MACH Buffet Marg G SR NM/lb N1 % Fuel Flow lb/h/Eng IAS kt 73000 TAS kt Ind. MACH Buffet Marg G SR NM/lb N1 % 87.7 Fuel Flow lb/h/Eng 1758 IAS kt 258 71000 TAS kt 448 Ind. MACH 0.78 Buffet Marg G 1.54 SR NM/lb 0.127 N1 % 87.1 Fuel Flow lb/h/Eng 1720 IAS kt 258 69000 TAS kt 448 Ind. MACH 0.78 Buffet Marg G 1.58 SR NM/lb 0.130 N1 % 86.6 87.5 Fuel Flow lb/h/Eng 1692 1667 IAS kt 258 252 67000 TAS kt 448 447 Ind. MACH 0.78 0.78 Buffet Marg G 1.63 1.55 SR NM/lb 0.132 0.134 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.5% AND FUEL FLOW BY 6.2%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 5.9%.

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

MACH 0.78 CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 36000 37000 38000 39000 40000 41000

AOM-1502-003

N1 % 86.2 86.9 Fuel Flow lb/h/Eng 1668 1631 IAS kt 258 252 65000 TAS kt 448 447 Ind. MACH 0.78 0.78 Buffet Marg G 1.68 1.60 SR NM/lb 0.134 0.137 N1 % 85.7 86.4 87.2 Fuel Flow lb/h/Eng 1644 1608 1578 IAS kt 258 252 247 63000 TAS kt 448 447 447 Ind. MACH 0.78 0.78 0.78 Buffet Marg G 1.73 1.65 1.57 SR NM/lb 0.136 0.139 0.142 N1 % 85.3 86.1 86.7 Fuel Flow lb/h/Eng 1620 1586 1549 IAS kt 258 252 247 61000 TAS kt 448 447 447 Ind. MACH 0.78 0.78 0.78 Buffet Marg G 1.79 1.71 1.63 SR NM/lb 0.138 0.141 0.144 N1 % 84.9 85.7 86.2 86.9 Fuel Flow lb/h/Eng 1597 1564 1524 1491 IAS kt 258 252 247 241 59000 TAS kt 448 447 447 447 Ind. MACH 0.78 0.78 0.78 0.78 Buffet Marg G 1.85 1.76 1.68 1.60 SR NM/lb 0.140 0.143 0.147 0.150 N1 % 84.6 85.3 85.7 86.4 87.2 Fuel Flow lb/h/Eng 1577 1542 1500 1467 1439 IAS kt 258 252 247 241 235 57000 TAS kt 448 447 447 447 447 Ind. MACH 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 1.92 1.83 1.74 1.66 1.58 SR NM/lb 0.142 0.145 0.149 0.152 0.155 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.5% AND FUEL FLOW BY 6.8%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 6.4%.

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REVISION 18

Cruise

Page 69

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

MACH 0.78 CRUISE - ALL ENGINES OPERATING ALL ENGINES ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 36000 37000 38000 39000 40000 41000

N1 % 84.3 84.9 85.3 86.0 86.6 Fuel Flow lb/h/Eng 1559 1520 1476 1446 1412 IAS kt 258 252 247 241 235 55000 TAS kt 448 447 447 447 447 Ind. MACH 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 1.99 1.89 1.80 1.72 1.64 SR NM/lb 0.144 0.147 0.152 0.155 0.158 N1 % 84.1 84.5 84.8 85.6 86.1 86.8 Fuel Flow lb/h/Eng 1542 1499 1454 1424 1388 1359 IAS kt 258 252 247 241 235 230 53000 TAS kt 448 447 447 447 447 447 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.06 1.96 1.87 1.78 1.70 1.62 SR NM/lb 0.145 0.149 0.154 0.157 0.161 0.165 N1 % 83.8 84.2 84.5 85.1 85.6 86.3 Fuel Flow lb/h/Eng 1525 1481 1434 1402 1363 1338 IAS kt 258 252 247 241 235 230 51000 TAS kt 448 447 447 447 447 447 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.14 2.04 1.94 1.85 1.77 1.68 SR NM/lb 0.147 0.151 0.156 0.160 0.164 0.167 N1 % 83.5 83.9 84.2 84.7 85.1 85.8 Fuel Flow lb/h/Eng 1508 1462 1418 1380 1339 1317 IAS kt 258 252 247 241 235 230 49000 TAS kt 448 447 447 447 447 447 Ind. MACH 0.78 0.78 0.78 0.78 0.78 0.78 Buffet Marg G 2.23 2.12 2.02 1.93 1.84 1.75 SR NM/lb 0.148 0.153 0.158 0.162 0.167 0.170 INCREASE/DECREASE N1(%) BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5°C ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 6 KT PER 5°C ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1(%) BY 0.5% AND FUEL FLOW BY 7.4%. 31000 FT AND ANTI-ICE ON • DECREASE SR(%) by 6.9%.

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REVISION 18

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"

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

COST INDEX AND ECONOMIC CRUISE SPEED !EMBRAER 170 Models

The cost index represents the ratio between time related costs per fuel related costs and is a way to express the direct operational costs of an operator. Flying on an economic cruise speed will minimize the direct operational cost of the cruise phase for a given cost index. There are two types of tables: – Correction to cost index. – Corrected cost index. In order to find the economic speed for a given flight condition and cost index the following procedure should be applied: 1. Enter in the Correction to cost index table. Inputs: Route cost index and Wind speed (negative values for headwind and positive values for tailwind). Outputs: Cost index wind correction for the route cost index. 2. Add the cost index wind correction found in (1) to the route cost index. This new value is the corrected cost index. 3. Enter in Corrected cost index table for the current altitude. Inputs: Corrected cost index and Airplane current weight. Outputs: Mach number for the economic speed.

AOM-1502-003

NOTE: The values were calculated for ISA conditions and all engines operating. The ISA deviations corrections are negligible.

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REVISION 18

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FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ECONOMIC CRUISE - ALL ENGINES OPERATING EMBRAER 170 WIND CORRECTION

CRUISE MACH NUMBER

Wind Corrections CORRECTION TO COST INDEX (100lb/h) Wind 90 100 110

120 &

0

5

10

15

20

25

30

35

40

45

50

60

70

80

-200

33

38

42

45

49

52

56

59

63

66

70

78

85

93 101 109 116

124

-160

21

24

27

30

33

35

38

41

43

46

48

54

59

64

70

75

80

86

-130

15

17

20

22

24

26

28

30

32

34

36

39

43

47

51

55

59

63

-100

10

12

14

15

17

18

19

21

22

24

25

28

31

33

36

39

42

45

-80

8

9

10

11

12

14

15

16

17

18

19

21

23

25

27

30

32

34

-60

5

6

7

8

9

10

10

11

12

13

13

15

17

18

20

21

23

24

-40

3

4

4

5

6

6

7

7

8

8

9

10

10

11

12

13

14

15

-20

2

2

2

2

3

3

3

3

4

4

4

5

5

5

6

6

7

7

20

0

-2

-2

-2

-2

-3

-3

-3

-3

-4

-4

-4

-5

-5

-5

-6

-6

-7

40

0

-3

-4

-4

-5

-5

-5

-6

-6

-7

-7

-8

-9

-10 -10 -11 -12

-13

60

0

-5

-5

-6

-7

-7

-8

-8

-9

-10 -10 -11 -13 -14 -15 -16 -17

-18

80

0

-5

-7

-8

-8

-9

-10 -11 -12 -12 -13 -15 -16 -18 -19 -21 -22

-24

100

0

-5

-8

-9

-10 -11 -12 -13 -14 -15 -16 -18 -20 -21 -23 -25 -27

-29

130

0

-5

-10 -11 -12 -14 -15 -16 -17 -18 -20 -22 -24 -26 -29 -31 -33

-35

160

0

-5

-10 -13 -14 -16 -17 -19 -20 -22 -23 -26 -28 -31 -33 -36 -39

-41

200

0

-5

-10 -15 -17 -19 -20 -22 -24 -25 -27 -30 -33 -36 -39 -42 -45

-48

Above

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 72

Cruise

REVISION 18

AOM-1502-003

(kt)

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ECONOMIC CRUISE - ALL ENGINES OPERATING EMBRAER 170 CRUISE MACH NUMBER

Altitude: 27000 ft CORRECTED COST INDEX (100lb/h) Weight (lb)

0

5

10

15

20

25

30

35

40

45

50

60

70

80

90 100 110

120 & Above

60000

0.55 0.57 0.60 0.62 0.64 0.67 0.69 0.71 0.73 0.75 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79

62000

0.55 0.58 0.60 0.62 0.65 0.67 0.69 0.71 0.73 0.75 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79

64000

0.56 0.58 0.60 0.62 0.65 0.67 0.69 0.71 0.73 0.75 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79

66000

0.56 0.58 0.60 0.63 0.65 0.67 0.69 0.71 0.73 0.75 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79

68000

0.57 0.59 0.61 0.63 0.65 0.67 0.69 0.71 0.73 0.75 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79

70000

0.57 0.59 0.61 0.64 0.65 0.67 0.69 0.71 0.73 0.75 0.75 0.78 0.78 0.78 0.79 0.79 0.79 0.79

72000

0.57 0.60 0.62 0.64 0.66 0.67 0.70 0.72 0.73 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79

74000

0.58 0.60 0.62 0.64 0.66 0.68 0.70 0.72 0.74 0.75 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.79

76000

0.59 0.61 0.63 0.64 0.66 0.68 0.70 0.72 0.74 0.74 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.79

78000

0.59 0.61 0.63 0.65 0.67 0.69 0.71 0.72 0.74 0.75 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.79

80000

0.60 0.61 0.63 0.65 0.67 0.69 0.71 0.73 0.73 0.75 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.79

Altitude: 29000 ft CORRECTED COST INDEX (100lb/h) Weight

AOM-1502-003

(lb)

0

5

10

15

20

25

30

35

40

45

50

60

70

80

90 100 110

120 & Above

60000

0.56 0.59 0.61 0.63 0.66 0.68 0.70 0.72 0.75 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.80 0.80

62000

0.57 0.59 0.61 0.64 0.66 0.68 0.70 0.72 0.75 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80

64000

0.57 0.59 0.62 0.64 0.66 0.68 0.70 0.72 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80

66000

0.58 0.60 0.62 0.65 0.67 0.69 0.70 0.73 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80

68000

0.58 0.60 0.63 0.65 0.67 0.69 0.71 0.73 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80

70000

0.59 0.61 0.63 0.65 0.67 0.69 0.72 0.74 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80

72000

0.59 0.62 0.64 0.66 0.67 0.70 0.72 0.74 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.80 0.80

74000

0.60 0.62 0.64 0.66 0.68 0.70 0.72 0.74 0.75 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80

76000

0.60 0.62 0.64 0.66 0.68 0.71 0.73 0.74 0.75 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80

78000

0.61 0.62 0.65 0.66 0.69 0.71 0.73 0.74 0.76 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80

80000

0.61 0.63 0.65 0.67 0.70 0.72 0.73 0.74 0.76 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.80

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 73

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ECONOMIC CRUISE - ALL ENGINES OPERATING EMBRAER 170 CRUISE MACH NUMBER

Altitude: 31000 ft CORRECTED COST INDEX (100lb/h) Weight (lb)

0

5

10

15

20

25

30

35

40

45

50

60

70

80

90 100 110

120 & Above

60000

0.58 0.60 0.63 0.66 0.67 0.70 0.72 0.74 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80

62000

0.58 0.61 0.64 0.66 0.68 0.70 0.72 0.75 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80

64000

0.59 0.62 0.64 0.66 0.68 0.70 0.73 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80

66000

0.60 0.62 0.65 0.66 0.68 0.71 0.73 0.76 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80

68000

0.60 0.62 0.65 0.67 0.69 0.71 0.73 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.80 0.80 0.80

70000

0.61 0.63 0.65 0.67 0.69 0.72 0.74 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.80 0.80 0.80

72000

0.61 0.63 0.65 0.67 0.70 0.72 0.74 0.75 0.77 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80 0.80

74000

0.62 0.64 0.66 0.69 0.71 0.73 0.74 0.76 0.77 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.80 0.80

76000

0.63 0.65 0.67 0.70 0.72 0.73 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.80

78000

0.64 0.66 0.68 0.71 0.72 0.73 0.76 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79

80000

0.65 0.67 0.70 0.71 0.72 0.75 0.76 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79

Altitude: 33000 ft CORRECTED COST INDEX (100lb/h) Weight 0

5

10

15

20

25

30

35

40

45

50

60

70

80

90 100 110

120 & Above

60000

0.60 0.63 0.66 0.67 0.70 0.72 0.74 0.77 0.78 0.78 0.78 0.79 0.79 0.79 0.80 0.80 0.80 0.80

62000

0.61 0.63 0.66 0.68 0.70 0.72 0.75 0.77 0.78 0.78 0.78 0.79 0.79 0.79 0.80 0.80 0.80 0.80

64000

0.61 0.64 0.66 0.68 0.70 0.73 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.80 0.80 0.80 0.80

66000

0.62 0.64 0.66 0.68 0.71 0.73 0.76 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80 0.80

68000

0.62 0.65 0.67 0.69 0.72 0.74 0.75 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.80 0.80

70000

0.64 0.65 0.68 0.71 0.73 0.74 0.76 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.80

72000

0.64 0.67 0.69 0.72 0.73 0.75 0.77 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79

74000

0.65 0.68 0.70 0.72 0.74 0.76 0.77 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79

76000

0.67 0.69 0.71 0.72 0.75 0.76 0.78 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79

78000

0.68 0.70 0.71 0.74 0.75 0.77 0.78 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79

80000

0.68 0.70 0.72 0.74 0.75 0.77 0.78 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 74

Cruise

REVISION 18

AOM-1502-003

(lb)

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ECONOMIC CRUISE - ALL ENGINES OPERATING EMBRAER 170 CRUISE MACH NUMBER

Altitude: 35000 ft CORRECTED COST INDEX (100lb/h) Weight (lb)

0

5

10

15

20

25

30

35

40

45

50

60

70

80

90 100 110

120 & Above

60000

0.63 0.65 0.67 0.69 0.72 0.75 0.77 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80 0.80 0.80

62000

0.63 0.65 0.68 0.70 0.73 0.76 0.77 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.80 0.80 0.80

64000

0.64 0.66 0.69 0.71 0.74 0.76 0.77 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.80 0.80

66000

0.65 0.67 0.70 0.73 0.75 0.76 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.80

68000

0.66 0.68 0.71 0.73 0.75 0.77 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.79

70000

0.67 0.70 0.72 0.74 0.76 0.77 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.79

72000

0.68 0.70 0.72 0.75 0.76 0.78 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.79

74000

0.68 0.70 0.72 0.75 0.75 0.77 0.78 0.78 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79

76000

0.69 0.70 0.72 0.74 0.75 0.76 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78

78000

0.69 0.71 0.72 0.73 0.74 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76

80000

0.69 0.70 0.71 0.72 0.73 0.73 0.73 0.73 0.73 0.73 0.73 0.73 0.73 0.73 0.73 0.73 0.73 0.73

Altitude: 37000 ft CORRECTED COST INDEX (100lb/h) Weight

AOM-1502-003

(lb)

0

5

10

15

20

25

30

35

40

45

50

60

70

80

90 100 110

120 & Above

60000

0.66 0.68 0.71 0.74 0.75 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.80 0.80

62000

0.66 0.69 0.72 0.74 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.80

64000

0.68 0.71 0.72 0.75 0.77 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.79

66000

0.69 0.70 0.73 0.75 0.78 0.78 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.79

68000

0.68 0.70 0.73 0.75 0.76 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78

70000

0.69 0.71 0.73 0.75 0.75 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77

72000

0.69 0.70 0.72 0.73 0.74 0.74 0.74 0.74 0.74 0.74 0.74 0.74 0.74 0.74 0.74 0.74 0.74 0.74

74000

0.68 0.70 0.71 0.71 0.71 0.71 0.71 0.71 0.71 0.71 0.71 0.71 0.71 0.71 0.71 0.71 0.71 0.71

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 75

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ECONOMIC CRUISE - ALL ENGINES OPERATING EMBRAER 170 CRUISE MACH NUMBER

Altitude: 39000 ft CORRECTED COST INDEX (100lb/h) Weight (lb)

0

5

10

15

20

25

30

35

40

45

50

60

70

80

90 100 110

120 & Above

60000

0.70 0.72 0.75 0.77 0.78 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.79

62000

0.69 0.72 0.74 0.76 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77

64000

0.70 0.72 0.74 0.75 0.75 0.75 0.75 0.75 0.75 0.75 0.75 0.75 0.75 0.75 0.75 0.75 0.75 0.75

66000

0.69 0.71 0.72 0.72 0.72 0.72 0.72 0.72 0.72 0.72 0.72 0.72 0.72 0.72 0.72 0.72 0.72 0.72

68000

0.68 0.68 0.68 0.68 0.68 0.68 0.68 0.68 0.68 0.68 0.68 0.68 0.68 0.68 0.68 0.68 0.68 0.68

Altitude: 41000 ft CORRECTED COST INDEX (100lb/h) Weight (lb) 60000

0

5

10

15

20

25

30

35

40

45

50

60

70

80

90 100 110

120 & Above

0.69 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 76

Cruise

REVISION 18

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

COST INDEX AND ECONOMIC CRUISE SPEED !EMBRAER 175 Models

The cost index represents the ratio between time related costs per fuel related costs and is a way to express the direct operational costs of an operator. Flying on an economic cruise speed will minimize the direct operational cost of the cruise phase for a given cost index. There are two types of tables: – Correction to cost index. – Corrected cost index. In order to find the economic speed for a given flight condition and cost index the following procedure should be applied: 1. Enter in the Correction to cost index table. Inputs: Route cost index and Wind speed (negative values for headwind and positive values for tailwind). Outputs: Cost index wind correction for the route cost index. 2. Add the cost index wind correction found in (1) to the route cost index. This new value is the corrected cost index. 3. Enter in Corrected cost index table for the current altitude. Inputs: Corrected cost index and Airplane current weight. Outputs: Mach number for the economic speed.

AOM-1502-003

NOTE: The values were calculated for ISA conditions and all engines operating. The ISA deviations corrections are negligible.

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 77

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ECONOMIC CRUISE - ALL ENGINES OPERATING EMBRAER 175 WIND CORRECTION

CRUISE MACH NUMBER

Wind Corrections CORRECTION TO COST INDEX (100lb/h) Wind 90 100 110

120 &

0

5

10

15

20

25

30

35

40

45

50

60

70

80

-200

34

38

42

46

50

53

57

60

64

67

71

78

86

94 102 109 117

125

-160

22

25

28

31

33

36

39

41

44

46

49

54

59

65

70

76

81

86

-130

15

18

20

22

24

26

28

30

32

34

36

40

44

48

52

56

60

64

-100

10

12

14

15

17

18

20

21

22

24

25

28

31

34

36

39

42

45

-80

8

9

10

11

13

14

15

16

17

18

19

21

23

25

28

30

32

34

-60

5

6

7

8

9

10

11

11

12

13

14

15

17

18

20

21

23

24

-40

3

4

5

5

6

6

7

7

8

8

9

10

11

12

12

13

14

15

-20

2

2

2

2

3

3

3

3

4

4

4

5

5

5

6

6

7

7

20

0

-2

-2

-2

-2

-3

-3

-3

-3

-4

-4

-4

-5

-5

-5

-6

-6

-7

40

0

-3

-4

-4

-5

-5

-6

-6

-6

-7

-7

-8

-9

-10 -10 -11 -12

-13

60

0

-5

-5

-6

-7

-7

-8

-9

-9

-10 -10 -12 -13 -14 -15 -16 -17

-19

80

0

-5

-7

-8

-9

-9

-10 -11 -12 -13 -13 -15 -16 -18 -19 -21 -22

-24

100

0

-5

-8

-9

-10 -11 -12 -13 -14 -15 -16 -18 -20 -22 -23 -25 -27

-29

130

0

-5

-10 -11 -13 -14 -15 -16 -17 -19 -20 -22 -24 -27 -29 -31 -33

-35

160

0

-5

-10 -13 -15 -16 -18 -19 -20 -22 -23 -26 -28 -31 -34 -36 -39

-42

200

0

-5

-10 -15 -17 -19 -21 -22 -24 -26 -27 -30 -33 -36 -40 -43 -46

-49

Above

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 78

Cruise

REVISION 18

AOM-1502-003

(kt)

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ECONOMIC CRUISE - ALL ENGINES OPERATING EMBRAER 175 CRUISE MACH NUMBER

Altitude: 27000 ft CORRECTED COST INDEX (100lb/h) Weight (lb)

0

5

10

15

20

25

30

35

40

45

50

60

70

80

90 100 110

120 & Above

60000

0.55 0.57 0.59 0.61 0.64 0.67 0.69 0.70 0.72 0.75 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.79

62000

0.55 0.57 0.60 0.62 0.64 0.67 0.69 0.70 0.72 0.75 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.79

64000

0.56 0.58 0.60 0.62 0.65 0.67 0.69 0.70 0.72 0.75 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.79

66000

0.56 0.58 0.60 0.62 0.65 0.67 0.68 0.70 0.72 0.75 0.75 0.78 0.78 0.78 0.79 0.79 0.79 0.79

68000

0.57 0.58 0.60 0.63 0.65 0.67 0.68 0.70 0.72 0.74 0.75 0.78 0.78 0.78 0.79 0.79 0.79 0.79

70000

0.57 0.59 0.61 0.63 0.65 0.67 0.69 0.71 0.73 0.74 0.75 0.78 0.78 0.78 0.79 0.79 0.79 0.79

72000

0.57 0.59 0.62 0.64 0.65 0.67 0.69 0.71 0.73 0.74 0.75 0.78 0.78 0.78 0.79 0.79 0.79 0.79

74000

0.58 0.60 0.62 0.64 0.66 0.67 0.70 0.72 0.73 0.74 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.79

76000

0.58 0.60 0.62 0.64 0.66 0.68 0.70 0.72 0.73 0.74 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.79

78000

0.59 0.61 0.62 0.65 0.66 0.68 0.70 0.72 0.73 0.74 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.79

80000

0.59 0.61 0.63 0.65 0.67 0.69 0.71 0.72 0.73 0.75 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.79

Altitude: 29000 ft CORRECTED COST INDEX (100lb/h) Weight

AOM-1502-003

(lb)

0

5

10

15

20

25

30

35

40

45

50

60

70

80

90 100 110

120 & Above

60000

0.56 0.58 0.60 0.63 0.66 0.67 0.70 0.72 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80

62000

0.57 0.59 0.61 0.63 0.66 0.67 0.70 0.72 0.74 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79

64000

0.57 0.59 0.62 0.64 0.66 0.68 0.70 0.72 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80

66000

0.57 0.60 0.62 0.64 0.66 0.68 0.70 0.72 0.75 0.75 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80

68000

0.58 0.60 0.62 0.65 0.67 0.68 0.71 0.73 0.75 0.75 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80

70000

0.58 0.61 0.63 0.65 0.67 0.69 0.71 0.73 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80

72000

0.59 0.61 0.63 0.65 0.67 0.69 0.72 0.74 0.74 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.80 0.80

74000

0.60 0.62 0.64 0.66 0.68 0.70 0.72 0.73 0.74 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80

76000

0.60 0.62 0.64 0.66 0.68 0.70 0.72 0.73 0.75 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80

78000

0.60 0.62 0.64 0.66 0.68 0.71 0.72 0.73 0.75 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80

80000

0.61 0.63 0.65 0.67 0.69 0.72 0.72 0.74 0.75 0.76 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 79

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ECONOMIC CRUISE - ALL ENGINES OPERATING EMBRAER 175 CRUISE MACH NUMBER

Altitude: 31000 ft CORRECTED COST INDEX (100lb/h) Weight (lb)

0

5

10

15

20

25

30

35

40

45

50

60

70

80

90 100 110

120 & Above

60000

0.58 0.60 0.63 0.65 0.67 0.69 0.72 0.74 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80

62000

0.58 0.61 0.64 0.66 0.67 0.69 0.72 0.74 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80

64000

0.59 0.61 0.64 0.66 0.68 0.70 0.72 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80

66000

0.59 0.62 0.64 0.66 0.68 0.70 0.73 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80

68000

0.60 0.62 0.64 0.66 0.68 0.71 0.73 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.80 0.80 0.80

70000

0.61 0.62 0.65 0.67 0.69 0.71 0.74 0.74 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.80 0.80 0.80

72000

0.61 0.63 0.65 0.67 0.70 0.72 0.74 0.74 0.76 0.77 0.78 0.78 0.79 0.79 0.79 0.80 0.80 0.80

74000

0.62 0.64 0.66 0.68 0.71 0.73 0.73 0.76 0.77 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.80 0.80

76000

0.62 0.65 0.67 0.69 0.72 0.72 0.74 0.76 0.77 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79

78000

0.64 0.66 0.68 0.70 0.71 0.73 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79

80000

0.65 0.67 0.69 0.70 0.72 0.74 0.75 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79

Altitude: 33000 ft CORRECTED COST INDEX (100lb/h) Weight 0

5

10

15

20

25

30

35

40

45

50

60

70

80

90 100 110

120 & Above

60000

0.60 0.62 0.65 0.67 0.69 0.71 0.74 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80 0.80

62000

0.60 0.63 0.65 0.68 0.69 0.72 0.74 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80 0.80

64000

0.61 0.63 0.65 0.68 0.70 0.72 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80 0.80

66000

0.62 0.64 0.66 0.68 0.71 0.73 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80 0.80

68000

0.62 0.65 0.67 0.69 0.72 0.74 0.75 0.77 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.80 0.80

70000

0.63 0.65 0.68 0.70 0.73 0.74 0.76 0.77 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.80

72000

0.64 0.67 0.69 0.72 0.73 0.75 0.76 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79

74000

0.65 0.68 0.70 0.71 0.73 0.75 0.76 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79

76000

0.67 0.69 0.70 0.72 0.74 0.75 0.78 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79

78000

0.68 0.69 0.71 0.73 0.74 0.77 0.78 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79

80000

0.68 0.70 0.72 0.73 0.75 0.77 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 80

Cruise

REVISION 18

AOM-1502-003

(lb)

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ECONOMIC CRUISE - ALL ENGINES OPERATING EMBRAER 175 CRUISE MACH NUMBER

Altitude: 35000 ft CORRECTED COST INDEX (100lb/h) Weight (lb)

0

5

10

15

20

25

30

35

40

45

50

60

70

80

90 100 110

120 & Above

60000

0.62 0.64 0.67 0.69 0.71 0.74 0.76 0.77 0.78 0.78 0.79 0.79 0.79 0.79 0.80 0.80 0.80 0.80

62000

0.63 0.65 0.67 0.70 0.73 0.75 0.76 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.80 0.80 0.80

64000

0.64 0.66 0.68 0.71 0.74 0.75 0.77 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.80 0.80

66000

0.64 0.67 0.70 0.72 0.74 0.76 0.78 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79

68000

0.66 0.68 0.71 0.73 0.75 0.77 0.78 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79

70000

0.67 0.70 0.71 0.73 0.76 0.77 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.79

72000

0.68 0.70 0.72 0.75 0.76 0.78 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.79

74000

0.68 0.70 0.72 0.74 0.75 0.77 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78

76000

0.68 0.70 0.72 0.73 0.75 0.76 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77

78000

0.69 0.70 0.71 0.73 0.74 0.75 0.75 0.75 0.75 0.75 0.75 0.75 0.75 0.75 0.75 0.75 0.75 0.75

80000

0.68 0.69 0.71 0.72 0.72 0.72 0.72 0.72 0.72 0.72 0.72 0.72 0.72 0.72 0.72 0.72 0.72 0.72

Altitude: 37000 ft CORRECTED COST INDEX (100lb/h) Weight

AOM-1502-003

(lb)

0

5

10

15

20

25

30

35

40

45

50

60

70

80

90 100 110

120 & Above

60000

0.66 0.67 0.71 0.73 0.74 0.77 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.80

62000

0.66 0.69 0.72 0.73 0.76 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.79

64000

0.67 0.70 0.72 0.74 0.77 0.78 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.79

66000

0.68 0.70 0.72 0.75 0.77 0.78 0.78 0.78 0.78 0.78 0.79 0.79 0.79 0.79 0.79 0.79 0.79 0.79

68000

0.68 0.70 0.72 0.75 0.76 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77 0.77

70000

0.69 0.71 0.72 0.74 0.75 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76

72000

0.69 0.70 0.72 0.72 0.73 0.73 0.73 0.73 0.73 0.73 0.73 0.73 0.73 0.73 0.73 0.73 0.73 0.73

74000

0.68 0.69 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70

6-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cruise

Page 81

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ECONOMIC CRUISE - ALL ENGINES OPERATING EMBRAER 175 CRUISE MACH NUMBER

Altitude: 39000 ft CORRECTED COST INDEX (100lb/h) Weight (lb)

0

5

10

15

20

25

30

35

40

45

50

60

70

80

90 100 110

120 & Above

60000

0.68 0.72 0.74 0.76 0.77 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78 0.78

62000

0.69 0.72 0.74 0.75 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76 0.76

64000

0.69 0.71 0.73 0.74 0.74 0.74 0.74 0.74 0.74 0.74 0.74 0.74 0.74 0.74 0.74 0.74 0.74 0.74

66000

0.69 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70 0.70

6-15 Copyright © by Embraer. Refer to cover page for details.

Page 82

Cruise

REVISION 18

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

DESCENT

!EMBRAER 170 Models

The descent table shows fuel consumption, distance and time from the top of descent to sea level for various cruise altitudes. The data are calculated for flight idle thrust setting, maintaining Mach 0.77 above 30200 ft, 290 KIAS between 30200 ft and 12000 ft, decreasing linearly to 250 KIAS at 10000 ft and maintaining 250 KIAS below 10000 ft. The approach and landing fuel consumption is not considered in the following tables. The associated conditions are:

AOM-1502-003

Final Altitude.............................................................. Sea Level Flaps.......................................................................... UP Gear........................................................................... UP Bleeds........................................................................ OPEN Anti-Ice...................................................................... OFF CG............................................................................. 18% Thrust Setting............................................................ FLIGHT IDLE

6-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Descent

Page 1

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

EXAMPLE: Given: Arrival Airport Elevation............................................. 3500 ft Top of Descent Weight.............................................. 70000 lb ISA Condition Cruise Altitude.................................... 35000 ft

RESULTS Data provided from 35000 ft (Top of Descent) to Sea Level table: Fuel: 214 lb Distance: 83 NM Time: 15 min Data for 5000 ft (3500 ft + 1500 ft above arrival airport) obtained from the 5000 ft descent table: Fuel: 60 lb Distance: 13 NM Time: 3 min The fuel, distance and time spent during the descent phase (from 35000 ft to 5000 ft) are: Fuel: 214 - 60 =154 lb Distance: 83 - 13 = 70 NM Time: 15 - 3 = 12 min

6-20 Copyright © by Embraer. Refer to cover page for details.

Page 2

Descent

REVISION 21

AOM-1502-003

The fuel consumption related to the approach and landing phase is provided on the Section 1-06-07.

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

DESCENT - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED OPEN FLIGHT IDLE AIRSPEED: M 0.77 / 290 KIAS / 250 KIAS ISA CONDITIONS

WEIGHT (lb)

84000

82000

80000

78000

76000

74000

72000

70000

68000

AOM-1502-003

66000

TOP OF DESCENT (ft) 5000 10000 15000 20000 25000 30000 35000 41000 Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

65 14 3 65 14 3 64 14 3 63 14 3 62 14 3 62 13 3 61 13 3 60 13 3 59 13 3 58 13 3

117 28 6 116 28 6 114 28 6 113 27 6 112 27 6 110 27 6 109 26 6 107 26 6 105 26 6 104 25 6

159 44 9 157 43 9 155 43 9 154 42 9 151 42 9 149 41 9 147 41 8 145 40 8 142 39 8 139 38 8

185 56 11 183 56 11 180 55 11 178 54 11 176 53 11 173 53 10 170 52 10 168 51 10 165 50 10 162 49 10

206 69 13 204 68 13 201 67 13 198 66 13 196 65 12 193 64 12 190 63 12 186 62 12 183 61 12 180 60 11

224 82 15 221 81 15 218 80 14 215 79 14 212 78 14 209 76 14 206 75 14 202 74 13 199 72 13 195 71 13

236 92 16 234 91 16 231 90 16 228 89 16 224 87 15 221 86 15 217 84 15 214 83 15 210 81 14 206 80 14

254 105 18 251 104 18 248 103 18 245 102 17 242 101 17 239 99 17 235 98 17 231 96 16 228 95 16 223 93 16

6-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Descent

Page 3

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

DESCENT - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED OPEN FLIGHT IDLE AIRSPEED: M 0.77 / 290 KIAS / 250 KIAS ISA CONDITIONS

WEIGHT (lb)

64000

62000

60000

58000

56000

54000

52000

50000

48000

TOP OF DESCENT (ft) 5000 10000 15000 20000 25000 30000 35000 41000 Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

57 12 3 56 12 3 54 12 3 53 12 3 52 11 3 50 11 3 49 11 2 47 10 2 46 10 2

102 25 6 99 24 5 97 24 5 95 23 5 92 22 5 90 22 5 87 21 5 85 20 5 82 20 4

137 38 8 134 37 8 130 36 8 127 35 7 124 34 7 120 33 7 117 32 7 113 31 7 109 30 6

158 48 10 155 47 9 151 46 9 147 44 9 143 43 9 139 42 8 135 41 8 130 39 8 126 38 8

176 58 11 172 57 11 168 56 11 164 54 10 159 53 10 155 51 10 150 50 9 145 48 9 140 46 9

191 69 13 187 68 12 182 66 12 178 64 12 173 63 11 168 61 11 163 59 11 157 57 10 152 55 10

202 78 14 197 76 13 192 74 13 188 73 13 183 71 12 177 69 12 172 67 12 167 64 11 161 62 11

219 91 16 215 90 15 210 88 15 205 85 15 199 83 14 194 81 14 188 79 13 182 76 13 176 74 13

6-20 Copyright © by Embraer. Refer to cover page for details.

Page 4

Descent

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

DESCENT

!EMBRAER 175 Models

The descent table shows fuel consumption, distance and time from the top of descent to sea level for various cruise altitudes. The data are calculated for flight idle thrust setting, maintaining Mach 0.77 above 30200 ft, 290 KIAS between 30200 ft and 12000 ft, decreasing linearly to 250 KIAS at 10000 ft and maintaining 250 KIAS below 10000 ft. The approach and landing fuel consumption is not considered in the following tables.

AOM-1502-003

The associated conditions are: Final Altitude.............................................................. Sea Level Flaps.......................................................................... UP Gear........................................................................... UP Bleeds........................................................................ OPEN Anti-Ice...................................................................... OFF CG............................................................................. 18% Thrust Setting............................................................ FLIGHT IDLE

6-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Descent

Page 5

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

EXAMPLE: Given: Arrival Airport Elevation............................................. 3500 ft Top of Descent Weight.............................................. 67000 lb ISA Condition Cruise Altitude.................................... 35000 ft

RESULTS Data provided from 35000 ft (Top of Descent) to Sea Level table: Fuel: 204 lb Distance: 79 NM Time: 14 min Data for 5000 ft (3500 ft + 1500 ft above arrival airport) obtained from the 5000 ft descent table: Fuel: 57 lb Distance: 12 NM Time: 3 min The fuel, distance and time spent during the descent phase (from 35000 ft to 5000 ft) are: Fuel: 204 - 57 = 147 lb Distance: 79 - 12 = 67 NM Time: 14 - 3 = 11 min

6-20 Copyright © by Embraer. Refer to cover page for details.

Page 6

Descent

REVISION 21

AOM-1502-003

The fuel consumption related to the approach and landing phase is provided on the Section 1-06-07.

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

DESCENT - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED OPEN FLIGHT IDLE AIRSPEED: M 0.77 / 290 KIAS / 250 KIAS ISA CONDITIONS

WEIGHT (lb)

85000

83000

81000

79000

77000

75000

73000

71000

AOM-1502-003

69000

TOP OF DESCENT (ft) 5000 10000 15000 20000 25000 30000 35000 41000 Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

64 14 3 64 14 3 63 14 3 63 14 3 62 13 3 61 13 3 60 13 3 59 13 3 58 13 3

115 28 6 114 28 6 113 27 6 112 27 6 111 27 6 109 26 6 108 26 6 106 26 6 104 25 6

157 43 9 155 43 9 154 42 9 152 42 9 150 41 9 148 41 9 146 40 8 143 39 8 141 39 8

182 56 11 181 55 11 179 54 11 176 54 11 174 53 11 171 52 10 169 51 10 166 50 10 163 50 10

204 68 13 201 67 13 199 67 13 196 66 12 194 65 12 191 64 12 188 63 12 185 62 12 182 60 11

221 81 15 219 80 15 216 79 14 213 78 14 210 77 14 207 76 14 204 74 14 201 73 13 197 72 13

234 91 16 231 90 16 228 89 16 225 88 15 222 86 15 219 85 15 216 84 15 212 82 15 208 81 14

251 104 18 248 103 18 246 102 17 243 101 17 240 100 17 236 98 17 233 97 17 229 96 16 226 94 16

6-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Descent

Page 7

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

DESCENT - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED OPEN FLIGHT IDLE AIRSPEED: M 0.77 / 290 KIAS / 250 KIAS ISA CONDITIONS

WEIGHT (lb)

67000

65000

63000

61000

59000

57000

55000

53000

51000

49000

TOP OF DESCENT (ft) 5000 10000 15000 20000 25000 30000 35000 41000 Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time Fuel Distance Time

lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min lb NM min

57 12 3 56 12 3 55 12 3 54 12 3 53 11 3 51 11 3 50 11 3 49 11 2 47 10 2 46 10 2

103 25 6 101 24 5 99 24 5 97 23 5 94 23 5 92 22 5 90 22 5 87 21 5 84 20 5 82 20 4

138 38 8 136 37 8 133 36 8 130 36 7 127 35 7 123 34 7 120 33 7 116 32 7 113 31 6 109 30 6

160 49 10 157 48 9 154 47 9 150 45 9 146 44 9 143 43 9 139 42 8 134 41 8 130 39 8 126 38 8

178 59 11 175 58 11 171 57 11 167 55 11 163 54 10 159 53 10 154 51 10 149 50 9 145 48 9 140 46 9

193 70 13 189 69 13 185 67 12 181 66 12 177 64 12 172 62 11 167 61 11 162 59 11 157 57 10 152 55 10

204 79 14 200 78 14 196 76 13 191 74 13 187 72 13 182 70 12 177 68 12 172 66 12 166 64 11 161 62 11

222 92 16 218 91 15 213 89 15 208 87 15 203 85 15 198 83 14 193 81 14 187 78 13 182 76 13 176 74 13

6-20 Copyright © by Embraer. Refer to cover page for details.

Page 8

Descent

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

IDLE DESCENT - CONSTANT FLIGHT PATH ANGLE !EMBRAER 170 Models

CONSIDERATIONS – Top of descent altitude is above 30000 ft – Bottom of descent is 12000 ft. – Speed at bottom of descent form 250 KIAS up to 260 KIAS – FMS descent mode VPATH is used. – Wind is constant with same intensity from top of descent up to bottom of descent. – Wind has only horizontal component. – VMO / MMO is never exceed during the descent procedure.

SPEED EXPLANATIONS The speeds published in the table are the speeds that must be inserted in the FMS in order to guarantee idle descent. They are not the speeds that the airplane will actually fly or reach. They are just a reference to guarantee idle thrust. Due this fact, the amber LIM on the FMA may be presented during the descent procedure when the auto throttle is engaged. The actual airplane speed will change according to the altitude. It will vary from the cruise speed to a range from 250 KIAS to 260 KIAS at 12000 ft, never exceeding VMO / MMO. The FMS VPATH mode prioritizes angle over speed, but if there is any waypoint with an altitude or speed constraint, the FMS will ignore the angle and respect this constraint.

RATE OF DESCENT

AOM-1502-003

As the speed changes according to the altitude, the rate of descent also changes. For the tables presented below, this variation will be within a range from 1400 ft/min up to 3000 ft/min.

6-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Descent

Page 9

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ANGLE CONSIDERATION The angle presented in the tables was calculated in such way that the speed at bottom of descent will be in the range from 250 KIAS to 260 KIAS.

EXAMPLE:

!!170 models, units in lb

Suppose: Anti-ice OFF TOD weight: 72000 lb Wind: 40 kt tailwind Find: FMS IAS / Mach and FPA angle to be inserted in the FMS: RESULTS: From the calm wind table 1 of 2 for Anti-ice OFF: For 72000 lb FMS IAS / Mach are: 244 / 0.62 Calm wind FPA is 3.5°. From the wind effect table 2 of 2: For 3.5° calm wind, the corrected angle is: 3.1° for 40 kt tailwind. Answer: FMS IAS / Mach: 244 / 0.62 FMS FPA : 3.1°.

6-20 Copyright © by Embraer. Refer to cover page for details.

Page 10

Descent

REVISION 21

AOM-1502-003

""

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL !!170 models, units in lb

IDLE DESCENT – CONSTANT FLIGHT PATH ANGLE ALL ENGINES CALM WIND - TABLE 1 of 2 - ANTI-ICE OFF TOD Weight [lb]

FMS IAS/MACH

FPA [deg] 4.7

48000

231 / 0.58

52000

234 / 0.59

4.4

56000

236 / 0.59

4.1

60000

237 / 0.59

3.9

64000

240 / 0.60

3.8

68000

242 / 0.61

3.6

72000

244 / 0.62

3.5

76000

246 / 0.63

3.4

80000

253 / 0.65

3.4

WIND EFFECT- TABLE 2 of 2 - ANTI-ICE OFF

AOM-1502-003

Headwind [kt] 100

80

60

40

20

10

6.7

6.2

5.7

5.3

5.0

4.8

6.3

5.8

5.4

5.0

4.7

4.5

5.8

5.4

5.0

4.7

4.4

5.6

5.1

4.8

4.4

4.1

5.4

5.0

4.6

4.3

5.1

4.7

4.4

5.0

4.6

4.3

4.8

4.4

4.1

FPA [deg]

Tailwind [kt] 10

20

40

60

80

100

4.7

4.6

4.4

4.2

4.0

3.8

3.6

4.4

4.3

4.2

3.9

3.7

3.6

3.4

4.2

4.1

4.0

3.9

3.7

3.5

3.3

3.2

4.0

3.9

3.8

3.7

3.5

3.3

3.1

3.0

4.0

3.9

3.8

3.7

3.6

3.4

3.2

3.1

2.9

4.1

3.8

3.7

3.6

3.5

3.4

3.2

3.1

2.9

2.8

4.0

3.7

3.6

3.5

3.4

3.3

3.1

3.0

2.8

2.7

3.9

3.6

3.5

3.4

3.3

3.2

3.0

2.9

2.8

2.6

6-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Descent

Page 11

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

IDLE DESCENT – CONSTANT FLIGHT PATH ANGLE ALL ENGINES CALM WIND - TABLE 1 of 2 - ANTI-ICE ON TOD Weight [lb]

FMS IAS/MACH

FPA [deg]

48000

228 / 0.60

3.7

52000

233 / 0.61

3.5

56000

236 / 0.62

3.3

60000

237 / 0.62

3.1

64000

239 / 0.62

3.0

68000

241 / 0.63

2.9

72000

245 / 0.64

2.9

76000

246 / 0.65

2.8

80000

256 / 0.70

2.8

WIND EFFECT- TABLE 2 of 2 - ANTI-ICE ON Headwind [kt] 100

80

60

40

20

10

5.2

4.8

4.5

4.2

3.9

3.8

4.9

4.6

4.2

4.0

3.7

4.6

4.3

4.0

3.7

3.5

4.4

4.0

3.8

3.5

4.2

3.9

3.6

3.4

4.1

3.8

3.5

3.9

3.6

3.4

FPA [deg]

Tailwind [kt] 10

20

40

60

80

100

3.7

3.6

3.5

3.3

3.1

3.0

2.9

3.6

3.5

3.4

3.3

3.1

3.0

2.8

2.7

3.4

3.3

3.2

3.1

3.0

2.8

2.7

2.6

3.3

3.2

3.1

3.0

2.9

2.8

2.6

2.5

2.4

3.2

3.1

3.0

2.9

2.8

2.7

2.6

2.4

2.3

3.3

3.1

3.0

2.9

2.8

2.7

2.6

2.5

2.4

2.2

3.2

3.0

2.9

2.8

2.7

2.6

2.5

2.4

2.3

2.2

6-20 Copyright © by Embraer. Refer to cover page for details.

Page 12

Descent

REVISION 21

AOM-1502-003

"" "

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

IDLE DESCENT - CONSTANT FLIGHT PATH ANGLE !EMBRAER 175 Models

CONSIDERATIONS – Top of descent altitude is above 30000 ft – Bottom of descent is 12000 ft. – Speed at bottom of descent form 250 KIAS up to 260 KIAS – FMS descent mode VPATH is used. – Wind is constant with same intensity from top of descent up to bottom of descent. – Wind has only horizontal component. – VMO / MMO is never exceed during the descent procedure.

SPEED EXPLANATIONS The speeds published in the table are the speeds that must be inserted in the FMS in order to guarantee idle descent. They are not the speeds that the airplane will actually fly or reach. They are just a reference to guarantee idle thrust. Due this fact, the amber LIM on the FMA may be presented during the descent procedure when the auto throttle is engaged. The actual airplane speed will change according to the altitude. It will vary from the cruise speed to a range from 250 KIAS to 260 KIAS at 12000 ft, never exceeding VMO / MMO. The FMS VPATH mode prioritizes angle over speed, but if there is any waypoint with an altitude or speed constraint, the FMS will ignore the angle and respect this constraint.

RATE OF DESCENT

AOM-1502-003

As the speed changes according to the altitude, the rate of descent also changes. For the tables presented below, this variation will be within a range from 1400 ft/min up to 3000 ft/min.

6-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Descent

Page 13

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ANGLE CONSIDERATION The angle presented in the tables was calculated in such way that the speed at bottom of descent will be in the range from 250 KIAS to 260 KIAS.

EXAMPLE:

!!175 models, units in lb

Suppose: Anti-ice OFF TOD weight: 72000 lb Wind: 40 kt tailwind Find: FMS IAS / Mach and FPA angle to be inserted in the FMS: RESULTS: From the calm wind table 1 of 2 for Anti-ice OFF: For 72000 lb FMS IAS / Mach are: 245 / 0.62 Calm wind FPA is 3.6°. From the wind effect table 2 of 2: For 3.6° calm wind, the corrected angle is: 3.2° for 40 kt tailwind. Answer: FMS IAS / Mach: 245 / 0.62 FMS FPA : 3.2°.

6-20 Copyright © by Embraer. Refer to cover page for details.

Page 14

Descent

REVISION 21

AOM-1502-003

""

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL !!175 models, units in lb

IDLE DESCENT – CONSTANT FLIGHT PATH ANGLE ALL ENGINES CALM WIND - TABLE 1 of 2 - ANTI-ICE OFF TOD Weight [lb]

FMS IAS/MACH

FPA [deg] 4.8

48000

231 / 0.58

52000

234 / 0.59

4.5

56000

236 / 0.59

4.2

60000

237 / 0.59

4.0

64000

238 / 0.60

3.8

68000

242 / 0.61

3.7

72000

245 / 0.62

3.6

76000

247 / 0.63

3.5

80000

251 / 0.66

3.4

WIND EFFECT- TABLE 2 of 2 - ANTI-ICE OFF

AOM-1502-003

Headwind [kt] 100

80

60

40

20

10

6.8

6.3

5.9

5.5

5.1

4.9

6.4

5.9

5.5

5.1

4.8

4.6

6.0

5.5

5.1

4.8

4.5

5.7

5.3

4.9

4.5

4.3

5.4

5.0

4.6

4.3

5.2

4.8

4.5

5.1

4.7

4.4

4.9

4.6

4.8

4.4

FPA [deg]

Tailwind [kt] 10

20

40

60

80

100

4.8

4.7

4.5

4.3

4.1

3.9

3.7

4.5

4.4

4.2

4.0

3.8

3.6

3.5

4.3

4.2

4.1

4.0

3.8

3.6

3.4

3.2

4.1

4.0

3.9

3.8

3.6

3.4

3.2

3.1

4.0

3.9

3.8

3.7

3.6

3.4

3.2

3.1

2.9

4.2

3.9

3.8

3.7

3.6

3.5

3.3

3.1

3.0

2.9

4.1

3.8

3.7

3.6

3.5

3.4

3.2

3.1

2.9

2.8

4.2

4.0

3.7

3.6

3.5

3.4

3.3

3.1

3.0

2.8

2.7

4.1

3.8

3.6

3.5

3.4

3.3

3.2

3.0

2.9

2.8

2.6

6-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Descent

Page 15

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

IDLE DESCENT – CONSTANT FLIGHT PATH ANGLE ALL ENGINES CALM WIND - TABLE 1 of 2 - ANTI-ICE ON TOD Weight [lb]

FMS IAS/MACH

FPA [deg]

48000

230 / 0.60

3.8

52000

233 / 0.61

3.6

56000

236 / 0.61

3.4

60000

236 / 0.62

3.2

64000

239 / 0.62

3.1

68000

242 / 0.63

3.0

72000

244 / 0.64

2.9

76000

248 / 0.65

2.9

80000

252 / 0.70

2.8

WIND EFFECT- TABLE 2 of 2 - ANTI-ICE ON Headwind [kt] 100

80

60

40

20

10

5.4

5.0

4.6

4.3

4.0

3.9

5.1

4.7

4.4

4.1

3.8

4.8

4.4

4.1

3.8

3.6

4.5

4.2

3.9

3.6

4.4

4.0

3.8

3.5

4.2

3.9

3.6

4.1

3.8

3.9

3.6

FPA [deg]

Tailwind [kt] 10

20

40

60

80

100

3.8

3.7

3.6

3.4

3.2

3.1

2.9

3.7

3.6

3.5

3.4

3.2

3.1

2.9

2.8

3.5

3.4

3.3

3.2

3.0

2.9

2.8

2.6

3.4

3.3

3.2

3.1

3.0

2.9

2.7

2.6

2.5

3.3

3.2

3.1

3.0

2.9

2.8

2.6

2.5

2.4

3.4

3.2

3.1

3.0

2.9

2.8

2.7

2.6

2.4

2.3

3.5

3.3

3.1

3.0

2.9

2.8

2.7

2.6

2.5

2.4

2.3

3.4

3.2

3.0

2.9

2.8

2.7

2.7

2.5

2.4

2.3

2.2

6-20 Copyright © by Embraer. Refer to cover page for details.

Page 16

Descent

REVISION 21

AOM-1502-003

"" "

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

HOLDING

!EMBRAER 170 Models

The holding tables show indicated and true airspeed, Mach number, N1, fuel flow for various weights, altitudes, anti-ice on (with and without ice accretion) and off condition. Data are presented in ISA condition for all engines operating configuration. The associated conditions are:

AOM-1502-003

Flaps.......................................................................... UP Gear........................................................................... UP Bleeds........................................................................ OPEN Airspeed A/I OFF....................................................... Minimum Fuel Consumption or 1.27 VS, whichever is higher. Airspeed A/I ON........................................................ Minimum Fuel Consumption or 210 KIAS , whichever is higher. Anti Ice...................................................................... OFF; ON and; ON (WITH ICE ACCRETION). CG............................................................................. 18%

6-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Holding

Page 1

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF SPEED: MINIMUM FUEL CONSUMPTION OR 1.27 VS STANDARD ATMOSPHERE

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 204 204 205 206 207 TAS kt 208 220 237 257 279 84000 MACH 0.317 0.338 0.372 0.410 0.455 N1 % 57.3 59.8 63.9 68.2 73.0 Fuel Flow lb/h/Eng 1550 1518 1478 1491 1532 IAS kt 202 202 202 203 204 TAS kt 206 217 234 254 276 82000 MACH 0.313 0.334 0.367 0.405 0.449 N1 % 56.8 59.2 63.2 67.3 72.4 Fuel Flow lb/h/Eng 1520 1484 1443 1439 1495 IAS kt 199 199 200 201 202 TAS kt 203 214 232 251 273 80000 MACH 0.309 0.330 0.363 0.400 0.444 N1 % 56.3 58.6 62.5 66.5 71.8 Fuel Flow lb/h/Eng 1490 1449 1408 1394 1456 IAS kt 197 197 197 198 199 TAS kt 201 212 229 248 269 78000 MACH 0.305 0.326 0.358 0.395 0.438 N1 % 55.8 58.0 61.8 65.8 71.1 Fuel Flow lb/h/Eng 1458 1413 1372 1356 1416 IAS kt 194 194 195 195 196 TAS kt 198 209 226 244 266 76000 MACH 0.301 0.321 0.354 0.390 0.432 N1 % 55.3 57.3 61.2 65.2 70.5 Fuel Flow lb/h/Eng 1427 1376 1339 1320 1373 IAS kt 191 192 192 193 194 TAS kt 196 206 223 241 262 74000 MACH 0.297 0.317 0.349 0.385 0.427 N1 % 54.7 56.7 60.6 64.5 69.7 Fuel Flow lb/h/Eng 1394 1342 1308 1286 1331 IAS kt 189 189 190 190 191 TAS kt 193 203 220 238 259 72000 MACH 0.293 0.313 0.344 0.380 0.421 N1 % 54.1 56.2 60.0 63.8 68.8 Fuel Flow lb/h/Eng 1362 1313 1276 1256 1290 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

208 305 0.506 76.4 1477 205 301 0.500 75.9 1442 203 297 0.494 75.3 1408 200 293 0.488 74.8 1374 197 290 0.481 74.2 1340 195 286 0.475 73.5 1307 192 282 0.468 72.8 1277

209 333 0.566 81.4 1540 207 329 0.559 80.6 1486 204 325 0.552 79.8 1433 201 321 0.545 78.8 1381 199 317 0.538 77.8 1329 196 313 0.531 76.9 1285 193 309 0.524 76.3 1254

212 366 0.635 87.4 1642 209 362 0.628 85.8 1552 206 357 0.620 85.1 1512 203 353 0.612 84.5 1474 201 348 0.604 83.8 1433 198 344 0.596 83.1 1392 195 339 0.588 82.4 1348

6-25 Copyright © by Embraer. Refer to cover page for details.

Page 2

Holding

REVISION 9

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF SPEED: MINIMUM FUEL CONSUMPTION OR 1.27 VS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

AOM-1502-003

IAS kt 186 186 187 188 188 TAS kt 190 200 217 235 255 70000 MACH 0.289 0.308 0.339 0.375 0.415 N1 % 53.4 55.6 59.3 63.1 67.8 Fuel Flow lb/h/Eng 1331 1283 1247 1226 1247 IAS kt 184 184 184 185 185 TAS kt 188 198 213 231 251 68000 MACH 0.285 0.304 0.334 0.369 0.409 N1 % 52.7 55.0 58.5 62.3 66.8 Fuel Flow lb/h/Eng 1298 1253 1217 1195 1202 IAS kt 181 181 181 182 183 TAS kt 185 195 210 228 248 66000 MACH 0.281 0.300 0.329 0.364 0.403 N1 % 52.0 54.4 57.7 61.6 65.7 Fuel Flow lb/h/Eng 1265 1224 1186 1164 1155 IAS kt 178 178 179 179 180 TAS kt 182 192 207 224 244 64000 MACH 0.276 0.295 0.324 0.358 0.397 N1 % 51.2 53.6 56.9 60.8 64.8 Fuel Flow lb/h/Eng 1230 1195 1154 1131 1121 IAS kt 175 175 176 176 177 TAS kt 179 189 204 221 240 62000 MACH 0.272 0.290 0.319 0.352 0.391 N1 % 50.6 52.9 56.1 60.0 63.9 Fuel Flow lb/h/Eng 1205 1165 1121 1101 1086 IAS kt 172 173 173 173 174 TAS kt 176 186 201 217 236 60000 MACH 0.268 0.286 0.314 0.347 0.384 N1 % 50.1 52.1 55.4 59.3 63.0 Fuel Flow lb/h/Eng 1181 1135 1095 1072 1053 IAS kt 169 170 170 170 171 TAS kt 173 183 197 214 232 58000 MACH 0.263 0.281 0.309 0.341 0.378 N1 % 49.4 51.3 54.6 58.4 62.1 Fuel Flow lb/h/Eng 1155 1104 1068 1041 1022 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

189 278 0.462 72.1 1246 186 274 0.455 71.4 1214 184 270 0.448 70.6 1180 181 266 0.442 69.7 1144 178 262 0.435 68.8 1107 175 257 0.428 67.9 1067 172 253 0.420 66.9 1025

190 304 0.516 75.6 1223 188 300 0.509 74.9 1191 185 295 0.501 74.2 1159 182 291 0.494 73.4 1127 179 286 0.486 72.6 1095 176 282 0.478 71.8 1062 173 277 0.470 71.0 1031

192 334 0.580 81.5 1298 189 330 0.572 80.5 1248 186 325 0.563 79.5 1198 183 320 0.555 78.4 1148 180 315 0.546 77.3 1098 177 310 0.537 76.1 1046 174 304 0.528 75.2 1006

6-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Holding

Page 3

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF SPEED: MINIMUM FUEL CONSUMPTION OR 1.27 VS STANDARD ATMOSPHERE

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 167 167 167 167 168 TAS kt 170 179 194 210 228 56000 MACH 0.259 0.276 0.303 0.335 0.371 N1 % 48.5 50.4 53.6 57.6 61.2 Fuel Flow lb/h/Eng 1128 1072 1039 1009 989 IAS kt 164 164 164 164 165 TAS kt 167 176 190 206 224 54000 MACH 0.254 0.271 0.298 0.329 0.365 N1 % 47.7 49.7 52.5 56.7 60.2 Fuel Flow lb/h/Eng 1100 1048 1010 975 956 IAS kt 160 161 161 161 162 TAS kt 164 173 187 202 220 52000 MACH 0.249 0.266 0.292 0.323 0.358 N1 % 46.8 48.8 51.4 55.6 59.2 Fuel Flow lb/h/Eng 1071 1023 980 941 922 IAS kt 157 158 158 158 159 TAS kt 161 169 183 198 215 50000 MACH 0.244 0.261 0.287 0.317 0.351 N1 % 45.9 47.9 50.3 54.6 58.4 Fuel Flow lb/h/Eng 1041 996 948 909 891 IAS kt 154 154 155 155 155 TAS kt 158 166 179 194 211 48000 MACH 0.239 0.255 0.281 0.310 0.344 N1 % 44.9 47.0 49.1 53.5 57.5 Fuel Flow lb/h/Eng 1010 969 915 882 861 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

169 249 0.413 65.8 981 166 244 0.406 64.7 933 162 240 0.398 63.6 893 159 235 0.390 62.6 859 156 230 0.382 61.5 828

170 272 0.462 70.2 1000 166 267 0.453 69.5 967 163 262 0.445 68.7 931 160 257 0.436 67.8 893 157 252 0.428 66.8 853

171 299 0.519 74.5 974 167 294 0.509 73.8 942 164 288 0.500 72.9 910 161 283 0.490 72.1 878 157 277 0.480 71.3 845

6-25 Copyright © by Embraer. Refer to cover page for details.

Page 4

Holding

REVISION 9

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON SPEED: MINIMUM FUEL CONSUMPTION OR 1.27 VS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

AOM-1502-003

IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 84000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 58.1 60.7 64.2 68.8 73.5 Fuel Flow lb/h/Eng 1657 1644 1603 1612 1644 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 82000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 57.6 60.1 63.5 68.0 72.9 Fuel Flow lb/h/Eng 1636 1617 1574 1568 1610 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 80000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 57.2 59.6 62.8 67.3 72.3 Fuel Flow lb/h/Eng 1616 1591 1545 1530 1576 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 78000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 56.8 59.0 62.1 66.8 71.8 Fuel Flow lb/h/Eng 1595 1564 1516 1498 1542 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 76000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 56.4 58.3 61.5 66.2 71.2 Fuel Flow lb/h/Eng 1575 1535 1491 1466 1508 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 74000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 55.9 57.8 60.9 65.6 70.6 Fuel Flow lb/h/Eng 1554 1510 1468 1435 1474 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 72000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 55.5 57.3 60.4 65.1 70.1 Fuel Flow lb/h/Eng 1533 1490 1446 1411 1440 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

210 308 0.511 76.8 1577 210 308 0.511 76.3 1547 210 308 0.511 75.9 1517 210 308 0.511 75.3 1487 210 308 0.511 74.7 1458 210 308 0.511 74.2 1430 210 308 0.511 73.6 1406

210 334 0.567 81.7 1641 210 334 0.567 81.0 1592 210 334 0.567 80.3 1544 210 334 0.567 79.5 1497 210 334 0.567 78.7 1452 210 334 0.567 78.0 1415 210 334 0.567 77.5 1389

212 366 0.635 87.9 1744 210 364 0.631 86.1 1653 210 364 0.631 85.5 1618 210 364 0.631 84.8 1583 210 364 0.631 84.1 1548 210 364 0.631 83.6 1516 210 364 0.631 83.0 1484

6-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Holding

Page 5

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 70000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 55.0 56.8 59.8 64.6 69.2 Fuel Flow lb/h/Eng 1512 1470 1423 1388 1409 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 68000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 54.6 56.3 59.3 64.0 68.4 Fuel Flow lb/h/Eng 1490 1449 1400 1364 1377 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 66000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 54.0 55.9 58.7 63.4 67.5 Fuel Flow lb/h/Eng 1466 1429 1378 1341 1346 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 64000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 53.5 55.4 58.2 62.8 66.7 Fuel Flow lb/h/Eng 1442 1409 1355 1318 1316 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 62000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 53.1 54.9 57.6 62.2 65.9 Fuel Flow lb/h/Eng 1427 1388 1333 1299 1287 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 60000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 52.8 54.5 57.2 61.7 65.2 Fuel Flow lb/h/Eng 1412 1368 1316 1282 1261 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 58000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 52.4 54.0 56.8 61.3 64.7 Fuel Flow lb/h/Eng 1397 1347 1300 1264 1242 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

210 308 0.511 73.0 1383 210 308 0.511 72.4 1359 210 308 0.511 71.8 1336 210 308 0.511 71.2 1312 210 308 0.511 70.6 1289 210 308 0.511 70.0 1265 210 308 0.511 69.4 1242

210 334 0.567 77.1 1364 210 334 0.567 76.6 1338 210 334 0.567 76.1 1313 210 334 0.567 75.7 1287 210 334 0.567 75.2 1262 210 334 0.567 74.7 1237 210 334 0.567 74.1 1218

210 364 0.631 82.3 1444 210 364 0.631 81.6 1404 210 364 0.631 80.9 1365 210 364 0.631 80.1 1327 210 364 0.631 79.3 1289 210 364 0.631 78.5 1254 210 364 0.631 77.8 1228

6-25 Copyright © by Embraer. Refer to cover page for details.

Page 6

Holding

REVISION 9

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

AOM-1502-003

IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 56000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 52.1 53.5 56.4 60.8 64.2 Fuel Flow lb/h/Eng 1382 1328 1285 1247 1224 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 54000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 51.8 53.3 56.0 60.3 63.7 Fuel Flow lb/h/Eng 1367 1315 1269 1229 1206 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 52000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 51.4 53.0 55.7 59.8 63.2 Fuel Flow lb/h/Eng 1352 1303 1253 1211 1188 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 50000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 51.1 52.7 55.3 59.3 62.9 Fuel Flow lb/h/Eng 1337 1291 1237 1196 1174 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 48000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 50.8 52.4 54.9 59.0 62.5 Fuel Flow lb/h/Eng 1323 1278 1221 1184 1161 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

210 308 0.511 68.7 1218 210 308 0.511 68.1 1195 210 308 0.511 67.5 1169 210 308 0.511 66.7 1142 210 308 0.511 66.2 1121

210 334 0.567 73.7 1200 210 334 0.567 73.2 1183 210 334 0.567 72.7 1165 210 334 0.567 72.3 1148 210 334 0.567 71.8 1130

210 364 0.631 77.3 1207 210 364 0.631 76.8 1186 210 364 0.631 76.3 1166 210 364 0.631 75.8 1145 210 364 0.631 75.3 1124

6-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Holding

Page 7

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITH ICE ACCRETION) SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 220 220 221 222 223 TAS kt 225 237 256 277 301 84000 MACH 0.341 0.364 0.400 0.442 0.490 N1 % 64.0 66.9 70.8 75.5 79.9 Fuel Flow lb/h/Eng 2053 2027 1999 2041 2074 IAS kt 217 218 218 219 220 TAS kt 222 234 252 274 297 82000 MACH 0.337 0.360 0.396 0.437 0.484 N1 % 63.5 66.3 70.3 74.7 79.3 Fuel Flow lb/h/Eng 2010 1978 1948 1980 2027 IAS kt 214 215 216 216 218 TAS kt 219 231 249 270 294 80000 MACH 0.333 0.355 0.391 0.431 0.478 N1 % 62.9 65.7 69.6 73.9 78.6 Fuel Flow lb/h/Eng 1967 1929 1901 1923 1981 IAS kt 212 212 213 214 215 TAS kt 216 228 246 267 290 78000 MACH 0.329 0.351 0.386 0.426 0.472 N1 % 62.3 65.1 68.9 73.1 77.9 Fuel Flow lb/h/Eng 1922 1882 1856 1872 1933 IAS kt 210 210 210 211 212 TAS kt 215 226 243 263 286 76000 MACH 0.326 0.347 0.381 0.420 0.466 N1 % 61.8 64.4 68.2 72.3 77.3 Fuel Flow lb/h/Eng 1885 1839 1815 1822 1885 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 74000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 61.5 64.0 67.8 71.7 76.6 Fuel Flow lb/h/Eng 1860 1816 1794 1788 1841 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 72000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 61.1 63.7 67.4 71.4 76.2 Fuel Flow lb/h/Eng 1835 1798 1773 1765 1811 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

225 328 0.545 83.5 2047 222 324 0.538 82.8 1997 219 320 0.532 82.2 1948 216 316 0.525 81.5 1899 213 312 0.518 80.8 1851 210 308 0.512 80.1 1804 210 308 0.511 79.7 1777

221 350 0.595 88.0 2057 218 346 0.587 86.7 1980 215 342 0.580 85.4 1902 212 337 0.572 84.4 1834 210 334 0.567 83.9 1790

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Page 8

Holding

REVISION 9

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITH ICE ACCRETION) SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

AOM-1502-003

IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 70000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 60.8 63.4 67.1 71.0 75.7 Fuel Flow lb/h/Eng 1811 1781 1752 1743 1780 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 68000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 60.4 63.0 66.7 70.6 75.2 Fuel Flow lb/h/Eng 1787 1763 1731 1721 1749 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 66000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 60.1 62.7 66.3 70.2 74.7 Fuel Flow lb/h/Eng 1763 1745 1710 1697 1717 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 64000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 59.7 62.3 66.0 69.8 74.2 Fuel Flow lb/h/Eng 1739 1727 1689 1674 1685 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 62000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 59.5 62.0 65.6 69.5 73.6 Fuel Flow lb/h/Eng 1725 1710 1669 1655 1653 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 60000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 59.2 61.6 65.3 69.2 73.2 Fuel Flow lb/h/Eng 1712 1692 1654 1637 1625 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 58000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 59.0 61.3 65.1 68.9 72.8 Fuel Flow lb/h/Eng 1700 1674 1639 1618 1606 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

210 308 0.511 79.4 1753 210 308 0.511 79.0 1728 210 308 0.511 78.6 1704 210 308 0.511 78.3 1679 210 308 0.511 77.9 1654 210 308 0.511 77.5 1630 210 308 0.511 77.2 1605

210 334 0.567 83.5 1763 210 334 0.567 83.1 1736 210 334 0.567 82.7 1708 210 334 0.567 82.3 1681 210 334 0.567 81.9 1653 210 334 0.567 81.5 1626 210 334 0.567 81.1 1604

6-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Holding

Page 9

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITH ICE ACCRETION) SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 56000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 58.7 61.0 64.8 68.5 72.5 Fuel Flow lb/h/Eng 1687 1657 1624 1600 1586 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 54000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 58.4 60.7 64.4 68.2 72.2 Fuel Flow lb/h/Eng 1674 1646 1608 1581 1567 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 52000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 58.2 60.5 64.0 67.9 71.9 Fuel Flow lb/h/Eng 1661 1635 1592 1562 1547 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 50000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 57.9 60.3 63.6 67.6 71.6 Fuel Flow lb/h/Eng 1649 1623 1576 1546 1532 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 48000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 57.6 60.0 63.2 67.4 71.4 Fuel Flow lb/h/Eng 1636 1612 1560 1533 1517 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

210 308 0.511 76.8 1581 210 308 0.511 76.5 1556 210 308 0.511 76.1 1529 210 308 0.511 75.6 1500 210 308 0.511 75.2 1479

210 334 0.567 80.8 1584 210 334 0.567 80.5 1564 210 334 0.567 80.3 1544 210 334 0.567 80.0 1524 210 334 0.567 79.6 1505

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Page 10

Holding

REVISION 9

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

HOLDING

!EMBRAER 175 Models

The holding tables show indicated and true airspeed, Mach number, N1, fuel flow for various weights, altitudes, anti-ice on (with and without ice accretion) and off condition. Data are presented in ISA condition for all engines operating configuration.

AOM-1502-003

The associated conditions are: Flaps.......................................................................... UP Gear........................................................................... UP Bleeds........................................................................ OPEN Airspeed A/I OFF....................................................... Minimum Fuel Consumption or 1.27 VS, whichever is higher. Airspeed A/I ON........................................................ Minimum Fuel Consumption or 210 KIAS , whichever is higher. Anti Ice...................................................................... OFF; ON and; ON (WITH ICE ACCRETION). CG............................................................................. 18% Minimum Remaining Rate of Climb.......................... 300 ft/min

6-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Holding

Page 11

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF SPEED: MINIMUM FUEL CONSUMPTION OR 1.27 VS STANDARD ATMOSPHERE

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 205 206 206 207 208 TAS kt 210 221 239 259 281 85000 MACH 0.319 0.340 0.374 0.413 0.457 N1 % 57.8 60.4 64.4 68.9 73.6 Fuel Flow lb/h/Eng 1579 1549 1509 1532 1566 IAS kt 203 203 204 204 205 TAS kt 207 218 236 255 278 83000 MACH 0.315 0.336 0.369 0.408 0.452 N1 % 57.3 59.8 63.8 68.0 73.0 Fuel Flow lb/h/Eng 1549 1515 1475 1480 1530 IAS kt 200 201 201 202 203 TAS kt 205 216 233 252 274 81000 MACH 0.311 0.332 0.365 0.403 0.446 N1 % 56.8 59.2 63.1 67.1 72.3 Fuel Flow lb/h/Eng 1518 1480 1439 1427 1491 IAS kt 198 198 199 199 200 TAS kt 202 213 230 249 271 79000 MACH 0.307 0.328 0.360 0.398 0.441 N1 % 56.3 58.5 62.4 66.4 71.7 Fuel Flow lb/h/Eng 1487 1444 1403 1388 1451 IAS kt 195 196 196 197 198 TAS kt 200 210 227 246 267 77000 MACH 0.303 0.324 0.356 0.393 0.435 N1 % 55.8 57.9 61.7 65.8 71.0 Fuel Flow lb/h/Eng 1455 1408 1367 1351 1409 IAS kt 193 193 194 194 195 TAS kt 197 208 224 243 264 75000 MACH 0.299 0.319 0.351 0.388 0.430 N1 % 55.2 57.2 61.2 65.1 70.3 Fuel Flow lb/h/Eng 1422 1370 1336 1315 1365 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

209 306 0.509 76.9 1510 207 303 0.503 76.4 1475 204 299 0.497 75.9 1440 201 295 0.491 75.3 1405 199 292 0.484 74.7 1371 196 288 0.478 74.1 1336

211 335 0.569 82.0 1585 208 331 0.562 81.2 1532 206 327 0.555 80.5 1477 203 323 0.549 79.6 1423 200 319 0.542 78.6 1371 197 315 0.534 77.6 1318

213 368 0.639 88.8 1721 210 364 0.632 86.9 1616 208 360 0.624 85.8 1551 205 355 0.616 85.2 1512 202 351 0.608 84.5 1472 199 346 0.600 83.8 1429

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Page 12

Holding

REVISION 9

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF SPEED: MINIMUM FUEL CONSUMPTION OR 1.27 VS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

AOM-1502-003

IAS kt 190 190 191 192 192 TAS kt 194 205 221 240 260 73000 MACH 0.295 0.315 0.346 0.382 0.424 N1 % 54.7 56.6 60.6 64.4 69.5 Fuel Flow lb/h/Eng 1389 1339 1304 1283 1323 IAS kt 188 188 188 189 190 TAS kt 192 202 218 236 257 71000 MACH 0.291 0.311 0.342 0.377 0.418 N1 % 54.0 56.1 59.9 63.7 68.6 Fuel Flow lb/h/Eng 1357 1309 1272 1252 1281 IAS kt 185 185 186 186 187 TAS kt 189 199 215 233 253 69000 MACH 0.287 0.306 0.337 0.372 0.412 N1 % 53.3 55.5 59.2 63.0 67.6 Fuel Flow lb/h/Eng 1325 1279 1242 1221 1237 IAS kt 182 182 183 183 184 TAS kt 186 196 212 230 249 67000 MACH 0.283 0.302 0.332 0.366 0.406 N1 % 52.6 54.9 58.4 62.2 66.5 Fuel Flow lb/h/Eng 1291 1249 1211 1190 1190 IAS kt 179 180 180 181 181 TAS kt 183 193 209 226 246 65000 MACH 0.279 0.297 0.327 0.361 0.400 N1 % 51.8 54.2 57.6 61.4 65.6 Fuel Flow lb/h/Eng 1257 1219 1180 1157 1148 IAS kt 177 177 177 178 178 TAS kt 180 190 205 223 242 63000 MACH 0.274 0.293 0.322 0.355 0.394 N1 % 51.1 53.5 56.8 60.6 64.7 Fuel Flow lb/h/Eng 1226 1189 1147 1124 1113 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

193 284 0.472 73.5 1305 191 280 0.465 72.8 1274 188 276 0.459 72.0 1242 185 272 0.452 71.2 1208 182 268 0.445 70.4 1173 179 264 0.438 69.6 1137

195 311 0.527 76.9 1283 192 306 0.520 76.2 1251 189 302 0.513 75.5 1220 186 298 0.505 74.8 1187 183 293 0.498 74.0 1155 180 289 0.490 73.3 1122

196 341 0.592 83.1 1386 193 337 0.584 82.2 1338 191 332 0.576 81.3 1287 188 327 0.567 80.3 1236 185 322 0.559 79.2 1186 182 317 0.550 78.1 1135

6-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Holding

Page 13

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF SPEED: MINIMUM FUEL CONSUMPTION OR 1.27 VS STANDARD ATMOSPHERE

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 174 174 174 175 175 TAS kt 178 187 202 219 238 61000 MACH 0.270 0.288 0.317 0.350 0.387 N1 % 50.5 52.7 56.0 59.9 63.7 Fuel Flow lb/h/Eng 1201 1159 1116 1096 1079 IAS kt 171 171 171 172 173 TAS kt 175 184 199 215 234 59000 MACH 0.265 0.283 0.311 0.344 0.381 N1 % 49.9 51.9 55.3 59.1 62.8 Fuel Flow lb/h/Eng 1176 1128 1090 1066 1047 IAS kt 168 168 169 169 170 TAS kt 172 181 195 212 230 57000 MACH 0.261 0.278 0.306 0.338 0.375 N1 % 49.2 51.1 54.4 58.2 61.9 Fuel Flow lb/h/Eng 1150 1095 1062 1034 1015 IAS kt 165 165 166 166 166 TAS kt 169 178 192 208 226 55000 MACH 0.256 0.273 0.301 0.332 0.368 N1 % 48.4 50.3 53.4 57.3 61.0 Fuel Flow lb/h/Eng 1122 1067 1033 1001 982 IAS kt 162 162 162 163 163 TAS kt 166 174 188 204 222 53000 MACH 0.252 0.268 0.295 0.326 0.361 N1 % 47.5 49.5 52.3 56.4 60.0 Fuel Flow lb/h/Eng 1094 1043 1003 967 947 IAS kt 159 159 159 160 160 TAS kt 162 171 185 200 218 51000 MACH 0.247 0.263 0.290 0.320 0.354 N1 % 46.6 48.7 51.1 55.3 59.0 Fuel Flow lb/h/Eng 1064 1017 971 931 914 IAS kt 156 156 156 157 157 TAS kt 159 168 181 196 213 49000 MACH 0.242 0.258 0.284 0.313 0.347 N1 % 45.6 47.7 49.9 54.4 58.2 Fuel Flow lb/h/Eng 1033 990 939 903 884 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

176 260 0.431 68.6 1098 173 255 0.424 67.6 1057 170 251 0.417 66.6 1013 167 246 0.409 65.5 967 164 242 0.402 64.3 919 161 237 0.394 63.4 884 158 233 0.386 62.3 850

177 284 0.482 72.5 1089 174 279 0.474 71.6 1057 171 275 0.466 70.8 1026 168 270 0.458 70.1 993 165 265 0.449 69.3 958 162 260 0.441 68.5 921 158 255 0.432 67.6 882

179 312 0.541 77.0 1084 175 307 0.533 75.8 1033 172 302 0.523 75.1 1001 169 296 0.514 74.4 968 166 291 0.505 73.6 935 163 285 0.495 72.8 902 159 280 0.485 71.9 870

6-25 Copyright © by Embraer. Refer to cover page for details.

Page 14

Holding

REVISION 9

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON SPEED: MINIMUM FUEL CONSUMPTION OR 1.27 VS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

AOM-1502-003

IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 85000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 58.5 61.2 65.0 69.4 74.0 Fuel Flow lb/h/Eng 1679 1669 1632 1649 1677 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 83000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 58.1 60.7 64.2 68.7 73.5 Fuel Flow lb/h/Eng 1659 1644 1603 1606 1643 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 81000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 57.7 60.1 63.5 67.9 72.9 Fuel Flow lb/h/Eng 1638 1618 1574 1562 1609 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 79000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 57.2 59.6 62.8 67.3 72.3 Fuel Flow lb/h/Eng 1618 1591 1545 1530 1575 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 77000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 56.8 59.0 62.1 66.8 71.8 Fuel Flow lb/h/Eng 1597 1564 1516 1497 1541 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 75000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 56.4 58.3 61.6 66.2 71.2 Fuel Flow lb/h/Eng 1577 1536 1494 1465 1507 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

210 308 0.511 77.2 1608 210 308 0.511 76.8 1578 210 308 0.511 76.3 1548 210 308 0.511 75.9 1518 210 308 0.511 75.4 1488 210 308 0.511 74.8 1459

211 335 0.569 82.3 1686 210 334 0.567 81.6 1635 210 334 0.567 80.9 1587 210 334 0.567 80.2 1538 210 334 0.567 79.4 1492 210 334 0.567 78.6 1447

210 364 0.632 87.4 1718 210 364 0.631 86.2 1656 210 364 0.631 85.5 1621 210 364 0.631 84.9 1586 210 364 0.631 84.2 1551

6-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Holding

Page 15

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 73000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 56.0 57.8 61.0 65.7 70.6 Fuel Flow lb/h/Eng 1556 1514 1471 1438 1473 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 71000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 55.5 57.4 60.5 65.2 70.0 Fuel Flow lb/h/Eng 1535 1494 1448 1414 1439 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 69000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 55.1 56.9 59.9 64.6 69.2 Fuel Flow lb/h/Eng 1514 1473 1426 1391 1408 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 67000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 54.6 56.4 59.3 64.1 68.4 Fuel Flow lb/h/Eng 1492 1453 1403 1367 1376 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 65000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 54.1 56.0 58.8 63.5 67.5 Fuel Flow lb/h/Eng 1468 1433 1381 1344 1346 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 63000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 53.6 55.5 58.2 62.9 66.7 Fuel Flow lb/h/Eng 1448 1412 1358 1322 1316 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

210 308 0.511 74.2 1433 210 308 0.511 73.7 1409 210 308 0.511 73.1 1386 210 308 0.511 72.5 1362 210 308 0.511 71.9 1339 210 308 0.511 71.3 1315

210 334 0.567 78.0 1418 210 334 0.567 77.6 1393 210 334 0.567 77.1 1367 210 334 0.567 76.7 1342 210 334 0.567 76.2 1316 210 334 0.567 75.7 1290

210 364 0.631 83.6 1518 210 364 0.631 83.0 1482 210 364 0.631 82.3 1442 210 364 0.631 81.6 1403 210 364 0.631 80.9 1363 210 364 0.631 80.1 1325

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Page 16

Holding

REVISION 9

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

AOM-1502-003

IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 61000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 53.3 55.0 57.7 62.4 65.9 Fuel Flow lb/h/Eng 1433 1392 1338 1305 1287 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 59000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 52.9 54.6 57.4 61.9 65.4 Fuel Flow lb/h/Eng 1418 1371 1322 1287 1266 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 57000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 52.6 54.1 57.0 61.4 64.9 Fuel Flow lb/h/Eng 1403 1351 1306 1269 1248 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 55000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 52.2 53.7 56.6 60.9 64.4 Fuel Flow lb/h/Eng 1388 1335 1290 1252 1230 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 53000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 51.9 53.4 56.2 60.4 63.9 Fuel Flow lb/h/Eng 1373 1322 1274 1234 1211 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 51000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 51.6 53.1 55.8 59.9 63.4 Fuel Flow lb/h/Eng 1358 1310 1259 1216 1195 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 49000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 51.2 52.9 55.4 59.6 63.1 Fuel Flow lb/h/Eng 1343 1298 1243 1204 1181 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

210 308 0.511 70.7 1292 210 308 0.511 70.0 1268 210 308 0.511 69.4 1245 210 308 0.511 68.8 1221 210 308 0.511 68.2 1197 210 308 0.511 67.5 1170 210 308 0.511 66.8 1143

210 334 0.567 75.3 1265 210 334 0.567 74.8 1241 210 334 0.567 74.3 1224 210 334 0.567 73.8 1206 210 334 0.567 73.4 1188 210 334 0.567 72.9 1171 210 334 0.567 72.4 1153

210 364 0.631 79.3 1288 210 364 0.631 78.5 1253 210 364 0.631 78.0 1232 210 364 0.631 77.4 1212 210 364 0.631 76.9 1191 210 364 0.631 76.4 1170 210 364 0.631 75.9 1150

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REVISION 9

Holding

Page 17

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITH ICE ACCRETION) SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 221 222 222 223 224 TAS kt 226 238 257 279 303 85000 MACH 0.343 0.366 0.403 0.445 0.493 N1 % 64.5 67.4 71.3 76.0 80.4 Fuel Flow lb/h/Eng 2091 2068 2043 2091 2117 IAS kt 218 219 220 221 222 TAS kt 223 235 254 275 299 83000 MACH 0.339 0.362 0.398 0.439 0.487 N1 % 63.9 66.8 70.8 75.3 79.8 Fuel Flow lb/h/Eng 2048 2019 1991 2028 2067 IAS kt 216 216 217 218 219 TAS kt 220 232 251 272 295 81000 MACH 0.335 0.357 0.393 0.434 0.481 N1 % 63.4 66.2 70.2 74.5 79.2 Fuel Flow lb/h/Eng 2004 1970 1940 1966 2020 IAS kt 213 214 214 215 216 TAS kt 218 229 248 268 292 79000 MACH 0.331 0.353 0.388 0.429 0.475 N1 % 62.8 65.6 69.5 73.7 78.5 Fuel Flow lb/h/Eng 1960 1920 1893 1913 1973 IAS kt 210 211 211 212 213 TAS kt 215 227 245 265 288 77000 MACH 0.327 0.348 0.383 0.423 0.469 N1 % 62.2 64.9 68.7 72.9 77.8 Fuel Flow lb/h/Eng 1915 1873 1848 1861 1924 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 75000 MACH 0.326 0.347 0.381 0.419 0.463 N1 % 61.8 64.4 68.2 72.2 77.1 Fuel Flow lb/h/Eng 1887 1840 1817 1815 1875 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

226 330 0.548 84.1 2091 223 326 0.542 83.4 2040 220 322 0.535 82.8 1990 218 318 0.529 82.1 1941 215 314 0.522 81.4 1892 212 310 0.515 80.7 1843

219 348 0.591 87.8 2040 216 344 0.583 86.5 1962 213 339 0.576 85.1 1882

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Page 18

Holding

REVISION 9

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITH ICE ACCRETION) SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

AOM-1502-003

IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 73000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 61.5 64.1 67.8 71.8 76.6 Fuel Flow lb/h/Eng 1862 1819 1796 1790 1841 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 71000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 61.2 63.8 67.5 71.4 76.1 Fuel Flow lb/h/Eng 1837 1802 1776 1768 1810 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 69000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 60.8 63.4 67.1 71.0 75.7 Fuel Flow lb/h/Eng 1813 1784 1755 1746 1779 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 67000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 60.5 63.1 66.7 70.7 75.2 Fuel Flow lb/h/Eng 1789 1766 1734 1723 1748 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 65000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 60.1 62.7 66.4 70.3 74.7 Fuel Flow lb/h/Eng 1765 1748 1713 1700 1717 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 63000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 59.8 62.4 66.0 69.9 74.2 Fuel Flow lb/h/Eng 1745 1730 1692 1678 1685 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

210 308 0.511 80.1 1805 210 308 0.511 79.8 1781 210 308 0.511 79.4 1756 210 308 0.511 79.0 1731 210 308 0.511 78.7 1707 210 308 0.511 78.3 1682

210 335 0.568 84.4 1825 210 334 0.567 83.9 1794 210 334 0.567 83.5 1766 210 334 0.567 83.1 1739 210 334 0.567 82.7 1712 210 334 0.567 82.3 1684

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REVISION 9

Holding

Page 19

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ALL ENGINES OPERATING ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITH ICE ACCRETION) SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 61000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 59.6 62.0 65.7 69.6 73.6 Fuel Flow lb/h/Eng 1730 1713 1673 1660 1653 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 59000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 59.3 61.7 65.4 69.3 73.3 Fuel Flow lb/h/Eng 1717 1695 1659 1642 1631 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 57000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 59.1 61.3 65.2 69.0 72.9 Fuel Flow lb/h/Eng 1705 1677 1644 1624 1611 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 55000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 58.8 61.1 64.9 68.6 72.6 Fuel Flow lb/h/Eng 1692 1663 1629 1605 1592 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 53000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 58.5 60.9 64.5 68.3 72.3 Fuel Flow lb/h/Eng 1679 1652 1613 1586 1572 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 51000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 58.3 60.7 64.1 68.0 72.0 Fuel Flow lb/h/Eng 1666 1641 1598 1567 1554 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 49000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 58.0 60.4 63.7 67.7 71.7 Fuel Flow lb/h/Eng 1654 1630 1582 1554 1540 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

210 308 0.511 78.0 1658 210 308 0.511 77.6 1633 210 308 0.511 77.2 1608 210 308 0.511 76.9 1584 210 308 0.511 76.5 1559 210 308 0.511 76.1 1530 210 308 0.511 75.6 1501

210 334 0.567 81.9 1657 210 334 0.567 81.5 1631 210 334 0.567 81.2 1611 210 334 0.567 80.9 1591 210 334 0.567 80.6 1571 210 334 0.567 80.3 1550 210 334 0.567 80.1 1530

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Page 20

Holding

REVISION 9

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

AOM-1502-003

"

6-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Holding

Page 21

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

6-25 Copyright © by Embraer. Refer to cover page for details.

Page 22

Holding

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

ONE ENGINE INOPERATIVE - LONG RANGE CRUISE !EMBRAER 170 Models

CRUISE TABLES The one engine inoperative long range cruise tables show N1, fuel flow, indicated airspeed, true airspeed, indicated Mach number, buffet margin and specific range. Data are presented for various weights and altitudes. Corrections for ISA deviation and Anti-ice are also presented. The associated conditions are:

AOM-1502-003

Flaps.......................................................................... UP Gear........................................................................... UP Bleeds........................................................................ OPEN Anti-ice....................................................................... OFF CG............................................................................. 18% Minimum Remaining Rate of Climb.......................... 100 ft/min

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REVISION 21

One Engine Inoperative Performance

Page 1

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ONE ENGINE INOPERATIVE ALL ENGINE TYPES ALTITUDE 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

N1 % 83.6 86.9 Fuel Flow lb/h/Eng 3735 3698 IAS kt 257 254 84000 TAS kt 276 293 Ind. MACH 0.425 0.459 Buffet Marg G 2.03 1.96 SR NM/lb 0.074 0.079 N1 % 82.9 86.3 87.1 87.8 Fuel Flow lb/h/Eng 3637 3603 3612 3617 IAS kt 255 251 251 251 82000 TAS kt 273 290 294 298 Ind. MACH 0.42 0.454 0.462 0.471 Buffet Marg G 2.04 1.97 1.96 1.95 SR NM/lb 0.075 0.08 0.081 0.082 N1 % 82.1 85.8 86.5 87.2 88 Fuel Flow lb/h/Eng 3523 3515 3517 3515 3523 IAS kt 251 249 248 248 248 80000 TAS kt 269 288 291 295 299 Ind. MACH 0.414 0.451 0.458 0.465 0.474 Buffet Marg G 2.03 1.98 1.97 1.95 1.95 SR NM/lb 0.076 0.082 0.083 0.084 0.085 N1 % 81.3 85.2 85.8 86.5 87.3 88.1 Fuel Flow lb/h/Eng 3420 3425 3421 3410 3425 3434 IAS kt 248 247 246 244 245 244 78000 TAS kt 266 285 288 291 296 300 Ind. MACH 0.409 0.447 0.453 0.459 0.468 0.477 Buffet Marg G 2.03 2 1.98 1.95 1.95 1.94 SR NM/lb 0.078 0.083 0.084 0.085 0.086 0.087 N1 % 80.5 84.5 85.2 85.9 86.7 87.3 88.3 Fuel Flow lb/h/Eng 3316 3331 3325 3332 3334 3325 3355 IAS kt 244 244 243 243 242 241 241 76000 TAS kt 262 282 285 289 293 296 300 Ind. MACH 0.404 0.442 0.448 0.456 0.464 0.471 0.479 Buffet Marg G 2.03 2.01 1.99 1.98 1.97 1.95 1.94 SR NM/lb 0.079 0.085 0.086 0.087 0.088 0.089 0.089 INCREASE/DECREASE N1% BY 0.8% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 5 KT PER 5ºC ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1% BY 0.4% AND FUEL FLOW BY 7%. 31000 FT AND ANTI-ICE ON • DECREASE SR% BY 7%.

-

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Page 2

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ONE ENGINE INOPERATIVE ALL ENGINE TYPES ALTITUDE 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

AOM-1502-003

N1 % 79.8 83.7 84.5 85.3 86 86.6 87.4 88.5 Fuel Flow lb/h/Eng 3221 3237 3231 3243 3240 3230 3235 3272 IAS kt 241 241 241 241 240 238 238 237 74000 TAS kt 259 278 282 287 290 293 297 300 Ind. MACH 0.399 0.436 0.444 0.452 0.459 0.465 0.474 0.482 Buffet Marg G 2.03 2.01 2.00 2.00 1.98 1.95 1.95 1.93 SR NM/lb 0.08 0.086 0.087 0.088 0.089 0.091 0.092 0.092 N1 % 79.1 83 83.8 84.6 85.3 86 86.7 87.5 Fuel Flow lb/h/Eng 3139 3142 3142 3147 3145 3141 3144 3146 IAS kt 239 238 238 238 237 236 236 235 72000 TAS kt 256 275 279 283 286 290 293 297 Ind. MACH 0.394 0.43 0.438 0.447 0.454 0.461 0.469 0.476 Buffet Marg G 2.04 2.01 2.01 2.01 1.99 1.97 1.96 1.94 SR NM/lb 0.082 0.087 0.089 0.09 0.091 0.092 0.093 0.094 N1 % 78.3 82.2 83 83.7 84.5 85.4 86.1 86.6 Fuel Flow lb/h/Eng 3054 3042 3045 3046 3050 3062 3055 3035 IAS kt 236 234 234 234 234 234 233 231 70000 TAS kt 253 271 275 279 283 288 291 293 Ind. MACH 0.389 0.424 0.432 0.44 0.449 0.457 0.464 0.469 Buffet Marg G 2.05 2.01 2.00 2.00 2.00 2.00 1.97 1.94 SR NM/lb 0.083 0.089 0.09 0.092 0.093 0.094 0.095 0.096 N1 % 77.5 81.4 82.2 82.9 83.7 84.7 85.3 86 Fuel Flow lb/h/Eng 2968 2951 2954 2950 2952 2970 2963 2955 IAS kt 233 231 231 231 231 232 230 229 68000 TAS kt 250 267 271 275 279 284 287 290 Ind. MACH 0.384 0.419 0.426 0.434 0.443 0.452 0.458 0.465 Buffet Marg G 2.05 2.01 2.01 2.00 2.00 2.01 1.98 1.96 SR NM/lb 0.084 0.091 0.092 0.093 0.095 0.096 0.097 0.098 N1 % 76.8 80.7 81.5 82.1 82.9 83.7 84.6 85.4 Fuel Flow lb/h/Eng 2885 2862 2864 2852 2859 2860 2871 2879 IAS kt 230 228 228 227 228 228 228 228 66000 TAS kt 247 264 268 271 275 280 284 288 Ind. MACH 0.38 0.414 0.421 0.427 0.436 0.445 0.453 0.462 Buffet Marg G 2.07 2.03 2.02 2.00 2.00 2.00 2.00 1.99 SR NM/lb 0.086 0.092 0.094 0.095 0.096 0.098 0.099 0.1 INCREASE/DECREASE N1% BY 0.8% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 5 KT PER 5ºC ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1% BY 0.4% AND FUEL FLOW BY 7%. 31000 FT AND ANTI-ICE ON • DECREASE SR% BY 7%.

88.7 3191 234 301 0.484 1.92 0.094 87.7 3062 231 297 0.477 1.93 0.097 86.8 2953 228 294 0.473 1.94 0.099 86.1 2865 226 291 0.467 1.96 0.101

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REVISION 21

One Engine Inoperative Performance

Page 3

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ONE ENGINE INOPERATIVE ALL ENGINE TYPES ALTITUDE 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

N1 % 76.1 79.9 80.7 81.4 82.1 82.9 83.7 84.6 Fuel Flow lb/h/Eng 2801 2773 2772 2766 2769 2765 2772 2790 IAS kt 227 226 225 224 224 224 225 225 64000 TAS kt 244 261 264 267 272 275 280 285 Ind. MACH 0.375 0.409 0.416 0.422 0.43 0.438 0.447 0.457 Buffet Marg G 2.08 2.04 2.03 2.01 2.01 2 2 2.01 SR NM/lb 0.087 0.094 0.095 0.097 0.098 0.1 0.101 0.102 N1 % 75.2 78.8 79.8 80.6 81.4 82 82.8 83.5 Fuel Flow lb/h/Eng 2708 2668 2680 2682 2680 2669 2672 2677 IAS kt 224 222 222 222 221 220 221 221 62000 TAS kt 240 257 261 264 268 271 275 280 Ind. MACH 0.37 0.402 0.41 0.417 0.424 0.431 0.44 0.448 Buffet Marg G 2.09 2.04 2.04 2.03 2.02 2 2 2 SR NM/lb 0.089 0.096 0.097 0.099 0.1 0.102 0.103 0.104 N1 % 74.2 77.9 78.8 79.8 80.5 81.2 81.9 82.6 Fuel Flow lb/h/Eng 2609 2586 2580 2593 2591 2583 2580 2573 IAS kt 220 219 219 219 218 218 217 217 60000 TAS kt 236 253 257 261 264 267 271 275 Ind. MACH 0.364 0.396 0.404 0.412 0.419 0.425 0.433 0.44 Buffet Marg G 2.08 2.05 2.04 2.04 2.03 2.01 2 1.99 SR NM/lb 0.091 0.098 0.099 0.101 0.102 0.104 0.105 0.107 N1 % 73.1 77 77.8 78.6 79.6 80.5 81.1 81.7 Fuel Flow lb/h/Eng 2504 2503 2493 2492 2500 2505 2494 2481 IAS kt 216 215 215 215 215 215 214 213 58000 TAS kt 232 249 253 257 261 265 267 270 Ind. MACH 0.357 0.391 0.397 0.405 0.413 0.421 0.427 0.433 Buffet Marg G 2.07 2.06 2.05 2.04 2.04 2.04 2.01 1.99 SR NM/lb 0.093 0.1 0.101 0.103 0.104 0.106 0.107 0.109 N1 % 72.1 76.1 76.9 77.6 78.5 79.6 80.3 81 Fuel Flow lb/h/Eng 2410 2419 2411 2401 2402 2415 2410 2400 IAS kt 212 212 212 212 212 212 211 210 56000 TAS kt 228 246 249 252 256 261 264 267 Ind. MACH 0.351 0.385 0.391 0.398 0.406 0.415 0.421 0.428 Buffet Marg G 2.08 2.06 2.06 2.05 2.04 2.05 2.03 2.01 SR NM/lb 0.095 0.101 0.103 0.105 0.107 0.108 0.109 0.111 INCREASE/DECREASE N1% BY 0.8% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 5 KT PER 5ºC ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1% BY 0.4% AND FUEL FLOW BY 7%. 31000 FT AND ANTI-ICE ON • DECREASE SR% BY 7%.

85.3 2777 223 287 0.462 1.97 0.103 84.5 2689 221 284 0.457 1.99 0.106 83.5 2589 217 280 0.45 2 0.108 82.5 2485 213 275 0.442 1.99 0.111 81.7 2400 210 271 0.436 2 0.113

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Page 4

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ONE ENGINE INOPERATIVE ALL ENGINE TYPES ALTITUDE 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

AOM-1502-003

N1 % 71.4 75.1 75.9 76.6 77.4 78.3 79.3 80.2 Fuel Flow lb/h/Eng 2345 2329 2328 2320 2310 2314 2318 2320 IAS kt 210 208 208 208 208 208 208 208 54000 TAS kt 225 241 245 248 252 256 260 264 Ind. MACH 0.347 0.378 0.385 0.392 0.399 0.407 0.414 0.422 Buffet Marg G 2.11 2.07 2.07 2.06 2.05 2.05 2.04 2.03 SR NM/lb 0.096 0.104 0.105 0.107 0.109 0.111 0.112 0.114 N1 % 70.8 74 74.9 75.7 76.4 77.2 78.1 79.1 Fuel Flow lb/h/Eng 2287 2236 2238 2237 2229 2222 2221 2226 IAS kt 208 205 205 205 204 204 204 204 52000 TAS kt 223 237 241 244 248 251 255 259 Ind. MACH 0.344 0.371 0.378 0.386 0.392 0.4 0.407 0.415 Buffet Marg G 2.15 2.07 2.07 2.07 2.06 2.05 2.04 2.04 SR NM/lb 0.098 0.106 0.107 0.109 0.111 0.113 0.115 0.116 N1 % 70.1 72.9 73.8 74.6 75.4 76.1 77 77.9 Fuel Flow lb/h/Eng 2224 2138 2145 2148 2144 2137 2126 2126 IAS kt 205 200 201 201 201 200 200 200 50000 TAS kt 221 232 236 240 243 247 250 254 Ind. MACH 0.34 0.364 0.371 0.378 0.385 0.392 0.399 0.407 Buffet Marg G 2.18 2.07 2.07 2.07 2.06 2.05 2.04 2.04 SR NM/lb 0.099 0.109 0.11 0.112 0.113 0.115 0.118 0.119 N1 % 69.2 71.8 72.7 73.5 74.3 75.1 75.9 76.8 Fuel Flow lb/h/Eng 2159 2037 2048 2053 2056 2052 2042 2031 IAS kt 203 196 197 197 197 197 196 196 48000 TAS kt 218 227 231 235 239 242 245 249 Ind. MACH 0.335 0.356 0.363 0.371 0.378 0.385 0.392 0.399 Buffet Marg G 2.22 2.06 2.07 2.07 2.07 2.06 2.05 2.04 SR NM/lb 0.101 0.112 0.113 0.114 0.116 0.118 0.12 0.122 INCREASE/DECREASE N1% BY 0.8% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 5 KT PER 5ºC ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1% BY 0.4% AND FUEL FLOW BY 7%. 31000 FT AND ANTI-ICE ON • DECREASE SR% BY 7%.

80.9 2313 207 267 0.429 2.02 0.115 79.9 2227 204 263 0.423 2.03 0.118 78.9 2138 200 258 0.416 2.04 0.121 77.7 2038 196 253 0.407 2.04 0.124

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REVISION 21

One Engine Inoperative Performance

Page 5

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ONE ENGINE INOPERATIVE ALL ENGINE TYPES ALTITUDE 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

N1 % Fuel Flow lb/h/Eng IAS kt 74000 TAS kt Ind. MACH Buffet Marg G SR NM/lb N1 % Fuel Flow lb/h/Eng IAS kt 72000 TAS kt Ind. MACH Buffet Marg G SR NM/lb N1 % 88.8 Fuel Flow lb/h/Eng 3086 IAS kt 229 70000 TAS kt 299 Ind. MACH 0.483 Buffet Marg G 1.89 SR NM/lb 0.097 N1 % 87.7 89 Fuel Flow lb/h/Eng 2959 2997 IAS kt 226 225 68000 TAS kt 295 298 Ind. MACH 0.477 0.484 Buffet Marg G 1.9 1.87 SR NM/lb 0.1 0.1 N1 % 86.7 87.8 89 Fuel Flow lb/h/Eng 2847 2873 2905 IAS kt 224 222 221 66000 TAS kt 293 295 298 Ind. MACH 0.473 0.478 0.485 Buffet Marg G 1.92 1.89 1.86 SR NM/lb 0.103 0.103 0.103 INCREASE/DECREASE N1% BY 0.8% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 5 KT PER 5ºC ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1% BY 0.5% AND FUEL FLOW BY 7%. 31000 FT AND ANTI-ICE ON • DECREASE SR% BY 8%.

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Page 6

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ONE ENGINE INOPERATIVE ALL ENGINE TYPES ALTITUDE 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

AOM-1502-003

N1 % 85.9 86.9 87.7 89.3 Fuel Flow lb/h/Eng 2764 2775 2766 2770 IAS kt 222 221 217 217 64000 TAS kt 290 294 293 297 Ind. MACH 0.469 0.476 0.477 0.486 Buffet Marg G 1.95 1.93 1.86 1.85 SR NM/lb 0.105 0.106 0.106 0.107 N1 % 85.3 86 86.6 87.9 Fuel Flow lb/h/Eng 2694 2678 2651 2636 IAS kt 221 219 215 213 62000 TAS kt 289 291 290 293 Ind. MACH 0.466 0.471 0.472 0.479 Buffet Marg G 1.99 1.95 1.88 1.85 SR NM/lb 0.107 0.109 0.109 0.111 N1 % 84.5 85.1 85.8 86.8 87.7 Fuel Flow lb/h/Eng 2607 2591 2578 2535 2529 IAS kt 218 216 215 212 208 60000 TAS kt 285 287 290 291 290 Ind. MACH 0.461 0.466 0.472 0.476 0.476 Buffet Marg G 2.01 1.97 1.94 1.89 1.82 SR NM/lb 0.109 0.111 0.113 0.115 0.115 N1 % 83.5 84.3 85.2 85.8 86.5 87.9 Fuel Flow lb/h/Eng 2500 2510 2513 2448 2425 2461 IAS kt 214 214 214 212 207 205 58000 TAS kt 280 284 289 290 288 291 Ind. MACH 0.452 0.461 0.47 0.474 0.473 0.48 Buffet Marg G 2.00 2.00 1.99 1.94 1.85 1.83 SR NM/lb 0.112 0.113 0.115 0.119 0.119 0.118 N1 % 82.4 83.4 84.3 84.9 85.7 86.7 87.8 Fuel Flow lb/h/Eng 2392 2412 2426 2365 2360 2363 2372 IAS kt 210 210 211 209 208 204 201 56000 TAS kt 275 280 285 287 290 290 290 Ind. MACH 0.443 0.454 0.464 0.469 0.476 0.478 0.48 Buffet Marg G 1.99 2.00 2.01 1.96 1.94 1.87 1.82 SR NM/lb 0.115 0.116 0.117 0.121 0.123 0.123 0.122 INCREASE/DECREASE N1% BY 0.8% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 5 KT PER 5ºC ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1% BY 0.5% AND FUEL FLOW BY 7%. 31000 FT AND ANTI-ICE ON • DECREASE SR% BY 8%.

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REVISION 21

One Engine Inoperative Performance

Page 7

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ONE ENGINE INOPERATIVE ALL ENGINE TYPES ALTITUDE 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

N1 % 81.5 82.3 83.2 84.1 85 85.7 86.3 88.1 Fuel Flow lb/h/Eng 2303 2308 2325 2292 2300 2285 2256 2307 IAS kt 206 207 207 207 207 204 199 199 54000 TAS kt 270 275 280 284 289 290 287 292 Ind. MACH 0.436 0.445 0.455 0.465 0.475 0.478 0.475 0.484 Buffet Marg G 2.00 2.00 2.01 2.00 2.00 1.95 1.84 1.83 SR NM/lb 0.117 0.119 0.12 0.124 0.126 0.127 0.127 0.126 N1 % 80.7 81.4 82.1 83.1 84 84.7 85.6 86.6 Fuel Flow lb/h/Eng 2225 2223 2220 2197 2207 2200 2202 2193 IAS kt 203 203 203 203 204 202 201 197 52000 TAS kt 267 270 274 279 284 287 290 289 Ind. MACH 0.43 0.438 0.447 0.457 0.467 0.473 0.48 0.48 Buffet Marg G 2.02 2.01 2.00 2.01 2.01 1.98 1.95 1.86 SR NM/lb 0.12 0.122 0.124 0.127 0.129 0.131 0.132 0.132 N1 % 79.8 80.5 81.2 82 82.9 83.8 84.7 85.3 Fuel Flow lb/h/Eng 2144 2137 2129 2096 2109 2121 2133 2098 IAS kt 201 200 199 199 200 200 201 196 50000 TAS kt 263 266 269 274 279 284 289 287 Ind. MACH 0.424 0.431 0.439 0.448 0.458 0.468 0.479 0.477 Buffet Marg G 2.04 2.02 2.01 2.01 2.01 2.01 2.02 1.92 SR NM/lb 0.123 0.124 0.127 0.131 0.132 0.134 0.136 0.137 N1 % 78.7 79.6 80.4 81.1 81.7 82.7 83.6 84.4 Fuel Flow lb/h/Eng 2050 2057 2059 2016 2008 2026 2036 2037 IAS kt 197 197 197 196 195 196 196 196 48000 TAS kt 258 262 266 270 273 278 283 287 Ind. MACH 0.416 0.425 0.434 0.441 0.448 0.459 0.469 0.477 Buffet Marg G 2.05 2.05 2.05 2.03 2.01 2.02 2.02 2.00 SR NM/lb 0.126 0.127 0.129 0.134 0.136 0.137 0.139 0.141 INCREASE/DECREASE N1% BY 0.8% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 5 KT PER 5ºC ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1% BY 0.5% AND FUEL FLOW BY 7%. 31000 FT AND ANTI-ICE ON • DECREASE SR% BY 8%.

87.8 2211 194 290 0.483 1.81 0.131 86.1 2088 191 286 0.477 1.84 0.137 85.2 2034 194 289 0.482 1.96 0.142

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Page 8

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ONE ENGINE INOPERATIVE ALL ENGINE TYPES ALTITUDE 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000

N1 % Fuel Flow lb/h/Eng IAS kt 54000 TAS kt Ind. MACH Buffet Marg G SR NM/lb N1 % Fuel Flow lb/h/Eng IAS kt 52000 TAS kt Ind. MACH Buffet Marg G SR NM/lb N1 % 88 Fuel Flow lb/h/Eng 2141 IAS kt 191 50000 TAS kt 290 Ind. MACH 0.487 Buffet Marg G 1.83 SR NM/lb 0.136 N1 % 86.1 87.6 Fuel Flow lb/h/Eng 2016 2040 IAS kt 188 186 48000 TAS kt 286 288 Ind. MACH 0.48 0.485 Buffet Marg G 1.85 1.81 SR NM/lb 0.142 0.141 INCREASE/DECREASE N1% BY 0.8% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 5 KT PER 5ºC ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1% BY 0.5% AND FUEL FLOW BY 7%. 31000 FT AND ANTI-ICE ON • DECREASE SR% BY 8%.

-

AOM-1502-003

"

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REVISION 21

One Engine Inoperative Performance

Page 9

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ONE ENGINE INOPERATIVE - LONG RANGE CRUISE !EMBRAER 175 Models

CRUISE TABLES The one engine inoperative long range cruise tables show N1, fuel flow, indicated airspeed, true airspeed, indicated Mach number, buffet margin and specific range. Data are presented for various weights and altitudes. Corrections for ISA deviation and Anti-ice are also presented.

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Page 10

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

The associated conditions are: Flaps.......................................................................... UP Gear........................................................................... UP Bleeds........................................................................ OPEN Anti-ice....................................................................... OFF CG............................................................................. 18% Minimum Remaining Rate of Climb.......................... 100 ft/min

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ONE ENGINE INOPERATIVE ALL ENGINE TYPES ALTITUDE 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

AOM-1502-003

N1 % 84.1 Fuel Flow lb/h/Eng 3807 IAS kt 257 85000 TAS kt 276 Ind. MACH 0.425 Buffet Marg G 2.01 SR NM/lb 0.073 N1 % 83.5 86.9 Fuel Flow lb/h/Eng 3714 3682 IAS kt 255 251 83000 TAS kt 273 290 Ind. MACH 0.421 0.454 Buffet Marg G 2.01 1.94 SR NM/lb 0.074 0.079 N1 % 82.7 86.3 87.1 87.8 Fuel Flow lb/h/Eng 3611 3588 3601 3606 IAS kt 252 249 249 248 81000 TAS kt 270 287 292 296 Ind. MACH 0.415 0.45 0.458 0.467 Buffet Marg G 2.01 1.95 1.95 1.94 SR NM/lb 0.075 0.08 0.081 0.082 N1 % 82 85.7 86.4 87.1 87.9 Fuel Flow lb/h/Eng 3510 3497 3504 3500 3512 IAS kt 249 247 246 245 245 79000 TAS kt 267 285 289 292 296 Ind. MACH 0.411 0.446 0.454 0.461 0.47 Buffet Marg G 2.02 1.97 1.96 1.94 1.94 SR NM/lb 0.076 0.081 0.082 0.083 0.084 N1 % 81.2 85.1 85.8 86.4 87.2 88 Fuel Flow lb/h/Eng 3400 3408 3406 3396 3412 3416 IAS kt 245 245 244 242 242 242 77000 TAS kt 263 283 286 288 293 297 Ind. MACH 0.405 0.443 0.449 0.455 0.464 0.473 Buffet Marg G 2.01 1.99 1.97 1.94 1.94 1.94 SR NM/lb 0.077 0.083 0.084 0.085 0.086 0.087 INCREASE/DECREASE N1% BY 1% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 4 KT PER 5ºC ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1% BY 0.4% AND FUEL FLOW BY 7%. 31000 FT AND ANTI-ICE ON • DECREASE SR% BY 8%.

-

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REVISION 21

One Engine Inoperative Performance

Page 11

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ONE ENGINE INOPERATIVE ALL ENGINE TYPES ALTITUDE 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

N1 % 80.4 84.4 85.1 85.8 86.6 87.3 88.2 Fuel Flow lb/h/Eng 3294 3320 3309 3316 3317 3315 3333 IAS kt 242 242 241 241 240 239 239 75000 TAS kt 260 279 283 286 290 293 298 Ind. MACH 0.4 0.438 0.444 0.452 0.459 0.467 0.475 Buffet Marg G 2.01 2 1.98 1.97 1.95 1.94 1.93 SR NM/lb 0.079 0.084 0.085 0.086 0.087 0.089 0.089 N1 % 79.7 83.6 84.4 85.2 85.9 86.5 87.4 88.3 Fuel Flow lb/h/Eng 3207 3221 3218 3228 3224 3215 3224 3249 IAS kt 239 238 238 239 237 236 236 235 73000 TAS kt 257 276 280 284 287 290 294 298 Ind. MACH 0.395 0.432 0.44 0.448 0.454 0.461 0.47 0.478 Buffet Marg G 2.02 1.99 1.99 1.99 1.97 1.94 1.94 1.92 SR NM/lb 0.08 0.086 0.087 0.088 0.089 0.09 0.091 0.092 N1 % 79 82.9 83.7 84.4 85.2 85.9 86.7 87.4 Fuel Flow lb/h/Eng 3123 3124 3128 3126 3127 3127 3133 3125 IAS kt 236 235 235 235 235 234 233 232 71000 TAS kt 254 272 276 280 284 287 291 294 Ind. MACH 0.39 0.426 0.434 0.442 0.449 0.457 0.465 0.472 Buffet Marg G 2.03 1.99 1.99 1.99 1.98 1.96 1.95 1.93 SR NM/lb 0.081 0.087 0.088 0.09 0.091 0.092 0.093 0.094 N1 % 78.2 82 82.9 83.6 84.4 85.3 86 86.6 Fuel Flow lb/h/Eng 3037 3022 3029 3032 3030 3046 3038 3021 IAS kt 233 232 232 232 232 232 231 229 69000 TAS kt 250 268 272 276 280 285 288 290 Ind. MACH 0.385 0.419 0.428 0.436 0.444 0.453 0.459 0.465 Buffet Marg G 2.03 1.99 1.99 1.99 1.99 1.99 1.96 1.93 SR NM/lb 0.082 0.089 0.09 0.091 0.093 0.094 0.095 0.096 N1 % 77.4 81.3 82.1 82.8 83.6 84.5 85.2 85.9 Fuel Flow lb/h/Eng 2954 2930 2936 2934 2936 2948 2943 2939 IAS kt 230 229 229 228 229 229 228 227 67000 TAS kt 247 264 268 272 277 281 284 288 Ind. MACH 0.381 0.414 0.422 0.43 0.438 0.448 0.454 0.461 Buffet Marg G 2.05 2 2 1.99 1.99 2 1.97 1.95 SR NM/lb 0.084 0.09 0.091 0.093 0.094 0.095 0.097 0.098 INCREASE/DECREASE N1% BY 1% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 3% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 7 KT PER 5ºC ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1% BY 0.4% AND FUEL FLOW BY 7%. 31000 FT AND ANTI-ICE ON • DECREASE SR% BY 8%.

88.6 3164 232 298 0.479 1.91 0.094 87.5 3037 229 294 0.473 1.92 0.097 86.7 2940 226 291 0.468 1.94 0.099

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Page 12

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ONE ENGINE INOPERATIVE ALL ENGINE TYPES ALTITUDE 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

AOM-1502-003

N1 % 76.7 80.6 81.3 82 82.8 83.6 84.4 85.3 Fuel Flow lb/h/Eng 2869 2843 2842 2836 2842 2844 2853 2861 IAS kt 228 226 226 225 225 225 225 225 65000 TAS kt 245 262 265 268 272 277 281 285 Ind. MACH 0.376 0.41 0.416 0.423 0.432 0.44 0.449 0.457 Buffet Marg G 2.06 2.02 2.01 1.99 1.99 1.99 1.99 1.98 SR NM/lb 0.085 0.092 0.093 0.095 0.096 0.097 0.099 0.1 N1 % 75.9 79.7 80.5 81.2 82 82.7 83.5 84.4 Fuel Flow lb/h/Eng 2779 2751 2751 2745 2750 2747 2749 2767 IAS kt 225 223 223 222 222 222 222 222 63000 TAS kt 241 258 262 265 269 272 277 282 Ind. MACH 0.371 0.405 0.411 0.418 0.426 0.433 0.442 0.452 Buffet Marg G 2.07 2.03 2.02 2 2 1.99 1.99 2 SR NM/lb 0.087 0.094 0.095 0.096 0.098 0.099 0.101 0.102 N1 % 75 78.7 79.6 80.5 81.2 81.9 82.6 83.3 Fuel Flow lb/h/Eng 2685 2653 2655 2662 2662 2651 2654 2652 IAS kt 221 220 220 220 219 218 218 218 61000 TAS kt 238 254 258 262 265 268 272 276 Ind. MACH 0.366 0.398 0.405 0.413 0.42 0.427 0.435 0.443 Buffet Marg G 2.07 2.03 2.03 2.02 2.01 1.99 1.99 1.98 SR NM/lb 0.089 0.096 0.097 0.098 0.1 0.101 0.103 0.104 N1 % 73.9 77.8 78.5 79.6 80.3 81.1 81.8 82.5 Fuel Flow lb/h/Eng 2580 2570 2559 2569 2570 2564 2564 2558 IAS kt 217 216 216 217 216 215 215 215 59000 TAS kt 233 250 254 258 262 265 268 272 Ind. MACH 0.359 0.392 0.399 0.407 0.414 0.421 0.428 0.436 Buffet Marg G 2.06 2.04 2.03 2.03 2.02 2 2 1.98 SR NM/lb 0.09 0.097 0.099 0.1 0.102 0.103 0.105 0.106 N1 % 72.8 76.8 77.6 78.4 79.4 80.3 81 81.6 Fuel Flow lb/h/Eng 2477 2486 2477 2465 2478 2484 2476 2463 IAS kt 213 213 213 213 213 213 212 211 57000 TAS kt 229 247 250 254 258 262 265 267 Ind. MACH 0.352 0.386 0.393 0.4 0.408 0.416 0.423 0.429 Buffet Marg G 2.06 2.05 2.04 2.03 2.03 2.03 2.01 1.98 SR NM/lb 0.092 0.099 0.101 0.103 0.104 0.105 0.107 0.109 INCREASE/DECREASE N1% BY 1% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 4 KT PER 5ºC ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1% BY 0.4% AND FUEL FLOW BY 7%. 31000 FT AND ANTI-ICE ON • DECREASE SR% BY 8%.

86 2851 224 288 0.463 1.95 0.101 85.1 2759 221 285 0.458 1.97 0.103 84.3 2669 218 281 0.453 1.98 0.105 83.3 2565 215 277 0.445 1.99 0.108 82.4 2467 211 272 0.437 1.98 0.11

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REVISION 21

One Engine Inoperative Performance

Page 13

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ONE ENGINE INOPERATIVE ALL ENGINE TYPES ALTITUDE 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000

N1 % 72 75.9 76.7 77.4 78.2 79.3 80.1 80.8 Fuel Flow lb/h/Eng 2394 2400 2395 2384 2376 2390 2388 2381 IAS kt 210 210 210 209 209 210 209 208 55000 TAS kt 226 243 246 250 253 258 261 264 Ind. MACH 0.347 0.38 0.387 0.394 0.401 0.41 0.417 0.423 Buffet Marg G 2.07 2.06 2.05 2.04 2.03 2.04 2.02 2.01 SR NM/lb 0.094 0.101 0.103 0.105 0.107 0.108 0.109 0.111 N1 % 71.3 74.8 75.7 76.4 77.2 78 79 80 Fuel Flow lb/h/Eng 2332 2304 2308 2301 2294 2285 2294 2299 IAS kt 208 206 206 206 206 205 205 205 53000 TAS kt 223 238 242 246 249 253 257 261 Ind. MACH 0.343 0.373 0.381 0.388 0.395 0.402 0.41 0.418 Buffet Marg G 2.1 2.05 2.06 2.05 2.04 2.03 2.03 2.03 SR NM/lb 0.096 0.103 0.105 0.107 0.109 0.111 0.112 0.113 N1 % 70.7 73.7 74.6 75.4 76.2 77 77.8 78.9 Fuel Flow lb/h/Eng 2273 2210 2214 2216 2209 2202 2192 2202 IAS kt 206 202 202 202 202 202 201 202 51000 TAS kt 221 234 238 241 245 248 252 256 Ind. MACH 0.34 0.367 0.374 0.381 0.388 0.395 0.402 0.41 Buffet Marg G 2.15 2.06 2.06 2.06 2.05 2.04 2.03 2.03 SR NM/lb 0.097 0.106 0.107 0.109 0.111 0.113 0.115 0.116 N1 % 69.9 72.6 73.5 74.3 75.1 75.9 76.7 77.6 Fuel Flow lb/h/Eng 2209 2109 2119 2123 2122 2116 2106 2097 IAS kt 203 198 198 198 198 198 198 197 49000 TAS kt 219 229 233 237 240 244 247 251 Ind. MACH 0.336 0.359 0.366 0.374 0.381 0.388 0.394 0.402 Buffet Marg G 2.18 2.05 2.06 2.06 2.06 2.05 2.04 2.03 SR NM/lb 0.099 0.109 0.11 0.112 0.113 0.115 0.117 0.119 INCREASE/DECREASE N1% BY 1% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 4 KT PER 5ºC ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1% BY 0.4% AND FUEL FLOW BY 7%. 31000 FT AND ANTI-ICE ON • DECREASE SR% BY 8%.

81.5 2380 208 268 0.431 2 0.113 80.7 2293 205 264 0.425 2.01 0.115 79.7 2206 202 260 0.418 2.03 0.118 78.6 2113 198 255 0.411 2.04 0.121

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Page 14

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ONE ENGINE INOPERATIVE ALL ENGINE TYPES ALTITUDE 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

AOM-1502-003

N1 % Fuel Flow lb/h/Eng IAS kt 75000 TAS kt Ind. MACH Buffet Marg G SR NM/lb N1 % Fuel Flow lb/h/Eng IAS kt 73000 TAS kt Ind. MACH Buffet Marg G SR NM/lb N1 % Fuel Flow lb/h/Eng IAS kt 71000 TAS kt Ind. MACH Buffet Marg G SR NM/lb N1 % 88.6 Fuel Flow lb/h/Eng 3058 IAS kt 227 69000 TAS kt 296 Ind. MACH 0.479 Buffet Marg G 1.88 SR NM/lb 0.097 N1 % 87.5 88.7 Fuel Flow lb/h/Eng 2932 2968 IAS kt 224 223 67000 TAS kt 293 296 Ind. MACH 0.473 0.48 Buffet Marg G 1.89 1.87 SR NM/lb 0.1 0.1 INCREASE/DECREASE N1% BY 1% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 3% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 7 KT PER 5ºC ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1% BY 0.4% AND FUEL FLOW BY 7%. 31000 FT AND ANTI-ICE ON • DECREASE SR% BY 8%.

-

6-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

One Engine Inoperative Performance

Page 15

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

LONG RANGE CRUISE - ONE ENGINE INOPERATIVE ALL ENGINE TYPES ALTITUDE 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

N1 % 86.6 87.6 88.7 Fuel Flow lb/h/Eng 2831 2842 2869 IAS kt 222 220 218 65000 TAS kt 290 292 295 Ind. MACH 0.469 0.474 0.479 Buffet Marg G 1.92 1.88 1.85 SR NM/lb 0.102 0.103 0.103 N1 % 85.9 86.7 87.4 88.8 Fuel Flow lb/h/Eng 2751 2755 2733 2723 IAS kt 220 219 215 214 63000 TAS kt 288 292 290 293 Ind. MACH 0.465 0.473 0.472 0.479 Buffet Marg G 1.94 1.93 1.85 1.82 SR NM/lb 0.105 0.106 0.106 0.108 N1 % 85.2 85.8 86.5 87.6 89 Fuel Flow lb/h/Eng 2677 2660 2648 2606 2643 IAS kt 219 217 215 211 210 61000 TAS kt 286 288 290 290 293 Ind. MACH 0.462 0.466 0.472 0.474 0.481 Buffet Marg G 1.98 1.94 1.91 1.84 1.82 SR NM/lb 0.107 0.108 0.109 0.111 0.111 N1 % 84.3 85 85.7 86.5 87.3 89.2 Fuel Flow lb/h/Eng 2582 2571 2564 2508 2496 2562 IAS kt 215 214 213 210 206 206 59000 TAS kt 282 284 288 289 287 293 Ind. MACH 0.455 0.461 0.468 0.472 0.472 0.482 Buffet Marg G 1.99 1.96 1.94 1.89 1.81 1.81 SR NM/lb 0.109 0.111 0.112 0.115 0.115 0.114 N1 % 83.2 84.2 85.1 85.7 86.2 87.6 Fuel Flow lb/h/Eng 2475 2490 2499 2431 2403 2434 IAS kt 211 212 212 209 205 204 57000 TAS kt 277 282 286 287 287 289 Ind. MACH 0.447 0.457 0.466 0.47 0.47 0.476 Buffet Marg G 1.99 1.99 1.99 1.94 1.86 1.83 SR NM/lb 0.112 0.113 0.115 0.118 0.119 0.119 INCREASE/DECREASE N1% BY 1% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 4 KT PER 5ºC ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1% BY 0.4% AND FUEL FLOW BY 7%. 31000 FT AND ANTI-ICE ON • DECREASE SR% BY 8%.

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Page 16

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

LONG RANGE CRUISE - ONE ENGINE INOPERATIVE ALL ENGINE TYPES ALTITUDE 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN/ISA CONDITION

WEIGHT (lb)

ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000

N1 % 82.2 83.1 84.1 84.8 85.6 86.4 87.3 Fuel Flow lb/h/Eng 2376 2388 2402 2350 2346 2335 2327 IAS kt 208 208 208 207 206 203 198 55000 TAS kt 272 277 282 284 288 288 286 Ind. MACH 0.439 0.449 0.458 0.465 0.472 0.474 0.474 Buffet Marg G 1.99 1.99 2 1.97 1.95 1.88 1.8 SR NM/lb 0.114 0.116 0.117 0.121 0.123 0.123 0.123 N1 % 81.3 82.1 83 83.9 84.8 85.4 86.1 87.5 Fuel Flow lb/h/Eng 2284 2290 2301 2273 2282 2257 2233 2261 IAS kt 204 204 205 205 205 202 198 196 53000 TAS kt 267 272 277 282 287 287 286 287 Ind. MACH 0.431 0.441 0.45 0.46 0.47 0.473 0.473 0.478 Buffet Marg G 1.99 2 2 2 2 1.94 1.86 1.81 SR NM/lb 0.117 0.119 0.12 0.124 0.126 0.127 0.128 0.127 N1 % 80.5 81.3 81.9 82.8 83.7 84.6 85.4 86.2 Fuel Flow lb/h/Eng 2207 2206 2200 2173 2186 2183 2185 2161 IAS kt 201 201 201 201 201 200 200 195 51000 TAS kt 264 268 271 276 281 285 289 286 Ind. MACH 0.426 0.434 0.442 0.451 0.462 0.469 0.478 0.475 Buffet Marg G 2.02 2.01 2 2 2 1.98 1.97 1.86 SR NM/lb 0.12 0.121 0.123 0.127 0.129 0.13 0.132 0.132 N1 % 79.6 80.3 81 81.8 82.4 83.6 84.5 85 Fuel Flow lb/h/Eng 2122 2118 2111 2075 2068 2099 2111 2075 IAS kt 198 198 197 197 196 198 198 194 49000 TAS kt 260 263 267 271 274 281 286 285 Ind. MACH 0.42 0.427 0.434 0.443 0.449 0.463 0.473 0.474 Buffet Marg G 2.04 2.02 2.01 2 1.98 2.01 2.01 1.93 SR NM/lb 0.122 0.124 0.126 0.131 0.132 0.134 0.135 0.137 INCREASE/DECREASE N1% BY 1% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE FUEL FLOW BY 2% PER 5ºC ABOVE/BELOW ISA CONDITIONS. INCREASE/DECREASE TAS BY 4 KT PER 5ºC ABOVE/BELOW ISA CONDITIONS. FOR ALTITUDES BELOW • INCREASE N1% BY 0.4% AND FUEL FLOW BY 7%. 31000 FT AND ANTI-ICE ON • DECREASE SR% BY 8%.

87 2144 190 283 0.473 1.77 0.132 85.9 2074 191 285 0.476 1.87 0.138

AOM-1502-003

"

6-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

One Engine Inoperative Performance

Page 17

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ONE ENGINE INOPERATIVE - DRIFTDOWN !EMBRAER 170 Models

In the event of an engine failure during cruise it will generally be necessary to reduce speed and descent to a lower altitude. Immediately after engine failure set maximum continuous N1 and allow the airplane to decelerate from the cruise speed to the driftdown speed shown in the driftdown table. When this speed is achieved, start the descend profile. The airplane should level off at the gross altitude and weight shown in the driftdown table.

NET LEVEL OFF ALTITUDE Federal regulations require terrain clearance flight planning based on net performance which is the gross (or real) gradient performance degraded by 1.1%. To estimate the net level off pressure altitude, enter with the gross weight, proceed to the ISA deviation and find the value within bracket. This is the net level off pressure altitude. The net level off pressure altitude must clear all en-route obstacles by at least 1000 ft. In case the obstacles heights are close to the values published in the tables below, a detailed driftdown analysis must be accomplished.

NOTE: – For initial flight levels above 30000 ft the Net and Gross Level Off altitudes are conservative. – Fixed driftdown speeds are obtained at AEO altitude capability for the respective start driftdown weight published.

6-30 Copyright © by Embraer. Refer to cover page for details.

Page 18

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

The associated conditions are: Drag Index................................................................. Zero Initial Flight Level for level off calculation................. 30000 ft Bleeds........................................................................ OPEN Anti-Ice...................................................................... Anti-ice OFF without Ice Accretion or Engine and Wing Anti-ice ON with Ice Accretion

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL DRIFTDOWN TABLES EMBRAER 170 – CF34-8E5/8E5A1 WITHOUT ICE ACCRETION WEIGHT (lb) START DRIFTDOWN

LEVEL OFF

82000

78600

225

78000

74900

219

74000

71300

213

70000

67600

207

66000

64000

200

62000

60200

197

58000

56500

186

54000

AOM-1502-003

FIXED DRIFTDOWN SPEED (KIAS)

52900

175

GROSS LEVEL OFF ALTITUDE - ft (NET LEVEL OFF ALTITUDE - ft) ISA +10°C & BELOW

ISA +15°C

ISA +20°C

18500

17800

16300

(12600)

(10900)

(8200)

19700

19200

17800

(14300)

(13900)

(11100)

21100

20700

19700

(16600)

(15900)

(14400)

22600

22300

21500

(18400)

(17800)

(16400)

24100

23900

23200

(20000)

(19600)

(18600)

25500

25300

24700

(21500)

(21200)

(20300)

27400

27300

26700

(23400)

(23200)

(22600)

29100

29000

28500

(25300)

(25200)

(24700)

6-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

One Engine Inoperative Performance

Page 19

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL DRIFTDOWN TABLES EMBRAER 170 – CF34-8E5/8E5A1 WITH ICE ACCRETION

WEIGHT (lb)

FIXED DRIFTDOWN SPEED (KIAS)

START DRIFTDOWN

LEVEL OFF

82000

78500

227

78000

74900

221

74000

71300

216

70000

67600

210

66000

63800

204

62000

60100

198

58000

56300

191

54000

52600

184

GROSS LEVEL OFF ALTITUDE - ft (NET LEVEL OFF ALTITUDE - ft) ISA -8°C & BELOW

ISA

ISA +10°C

16800

16600

14400

(10800)

(10300)

(7500)

18200

18100

16000

(12800)

(12700)

(8700)

19600

19500

17700

(14700)

(14600)

(11800)

21000

20900

19300

(16900)

(16700)

(14600)

22400

22300

20900

(18600)

(18500)

(16600)

23900

23900

22500

(20200)

(20100)

(18500)

25600

25500

24100

(21800)

(21800)

(20400)

27200

26800

25800

(23600)

(23600)

(22300)

6-30 Copyright © by Embraer. Refer to cover page for details.

Page 20

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

ONE ENGINE INOPERATIVE - DRIFTDOWN !EMBRAER 175 Models

In the event of an engine failure during cruise it will generally be necessary to reduce speed and descent to a lower altitude. Immediately after engine failure set maximum continuous N1 and allow the airplane to decelerate from the cruise speed to the driftdown speed shown in the driftdown table. When this speed is achieved, start the descend profile. The airplane should level off at the gross altitude and weight shown in the driftdown table.

NET LEVEL OFF ALTITUDE Federal regulations require terrain clearance flight planning based on net performance which is the gross (or real) gradient performance degraded by 1.1%. To estimate the net level off pressure altitude, enter with the gross weight, proceed to the ISA deviation and find the value within bracket. This is the net level off pressure altitude. The net level off pressure altitude must clear all en-route obstacles by at least 1000 ft. In case the obstacles heights are close to the values published in the tables below, a detailed driftdown analysis must be accomplished.

AOM-1502-003

The associated conditions are: Drag Index................................................................. Zero Initial Flight Level for level off calculation................. 30000 ft Bleeds........................................................................ OPEN Anti-Ice...................................................................... Anti-ice OFF without Ice Accretion or Engine and Wing Anti-ice ON with Ice Accretion NOTE: – For initial flight levels above 30000 ft the Net and Gross Level Off altitudes are conservative. – Fixed driftdown speeds are obtained at AEO altitude capability for the respective start driftdown weight published.

6-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

One Engine Inoperative Performance

Page 21

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL DRIFTDOWN TABLES EMBRAER 175 – CF34-8E5/8E5A1 WITHOUT ICE ACCRETION FIXED DRIFTDOWN SPEED (KIAS)

START DRIFTDOWN

LEVEL OFF

85000

81400

228

81000

77700

223

77000

74000

217

73000

70400

211

69000

66700

204

65000

63000

202

61000

59200

194

57000

55600

183

GROSS LEVEL OFF ALTITUDE - ft (NET LEVEL OFF ALTITUDE - ft) ISA +10°C & BELOW

ISA +15°C

ISA +20°C

17100

16200

14700

(10300)

(8400)

(6400)

18500

17800

16400

(12700)

(11200)

(8400)

19800

19400

18000

(14500)

(14100)

(11700)

21200

20900

19900

(16800)

(16100)

(14600)

22700

22400

21800

(18600)

(18100)

(16700)

24100

23800

23100

(20000)

(19600)

(18500)

25700

25500

25000

(21700)

(21400)

(20700)

27600

27500

26900

(23600)

(23500)

(22900)

6-30 Copyright © by Embraer. Refer to cover page for details.

Page 22

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

WEIGHT (lb)

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL DRIFTDOWN TABLES EMBRAER 175 – CF34-8E5/8E5A1 WITH ICE ACCRETION WEIGHT (lb)

FIXED DRIFTDOWN SPEED (KIAS)

START DRIFTDOWN

LEVEL OFF

85000

80200

231

81000

77600

225

77000

74000

220

73000

70400

214

69000

66600

208

65000

62800

203

61000

59100

196

57000

55400

189

GROSS LEVEL OFF ALTITUDE - ft (NET LEVEL OFF ALTITUDE - ft) ISA -8°C & BELOW

ISA

ISA +10°C

14900

14800

11800

(8300)

(8000)

(7300)

16800

16600

14400

(11000)

(10400)

(7500)

18300

18100

16100

(13000)

(12900)

(8900)

19700

19600

17800

(14900)

(14800)

(12200)

21100

21000

19400

(17100)

(16900)

(14800)

22500

22400

21000

(18800)

(18600)

(16800)

24000

24000

22700

(20300)

(20300)

(18700)

25700

25700

24300

(22000)

(22000)

(20600)

AOM-1502-003

"

6-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

One Engine Inoperative Performance

Page 23

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ONE ENGINE INOPERATIVE - ALTITUDE CAPABILITY !EMBRAER 170 Models

The table below permits quick determination of the altitude capability, based on the initial cruise weight. The table data are presented for various ISA conditions, one engine inoperative and Long Range Cruise schedule.

6-30 Copyright © by Embraer. Refer to cover page for details.

Page 24

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

The established associated conditions are: Flaps.......................................................................... UP Gears......................................................................... UP Bleeds........................................................................ OPEN CG............................................................................. 18% Minimum Remaining Rate of Climb.......................... 100 ft/min

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CRUISE ALTITUDE CAPABILITY ONE ENGINE INOPERATIVE EMBRAER 170, ALL ENGINE TYPES, LONG RANGE CRUISE Weight (lb) 82000 80000 78000 76000 74000 72000 70000 68000 66000 64000 62000 60000 58000 56000 54000 52000 50000 48000

-10 120 130 150 160 170 180 180 190 200 210 220 220 230 240 250 260 270 280

-5 120 130 140 150 160 170 180 190 200 210 220 220 230 240 250 260 270 280

0 120 130 140 150 160 170 180 190 200 210 210 220 230 240 250 260 270 280

5 120 130 140 150 160 170 180 190 200 210 210 220 230 240 250 260 270 280

ISA + 10 120 130 140 160 170 170 180 190 200 210 210 220 230 240 250 260 270 280

ºC 15 130 140 150 160 170 180 190 200 210 220 230 240 250 250 270 280

20 130 150 150 170 180 190 200 210 220 230 240 250 260 270

25 130 150 160 170 180 190 210 210 230 240 250 260

30 140 150 160 170 190 200 210 220 230 240

35 120 140 150 170 180 190 200 210 220

AOM-1502-003

"

6-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

One Engine Inoperative Performance

Page 25

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ONE ENGINE INOPERATIVE - ALTITUDE CAPABILITY !EMBRAER 175 Models

The table below permits quick determination of the altitude capability, based on the initial cruise weight. The table data are presented for various ISA conditions, one engine inoperative and Long Range Cruise schedule.

6-30 Copyright © by Embraer. Refer to cover page for details.

Page 26

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

The established associated conditions are: Flaps.......................................................................... UP Gears......................................................................... UP Bleeds........................................................................ OPEN CG............................................................................. 18% Minimum Remaining Rate of Climb.......................... 100 ft/min

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

CRUISE ALTITUDE CAPABILITY ONE ENGINE INOPERATIVE EMBRAER 175, ALL ENGINE TYPES, LONG RANGE CRUISE Weight (lb) 82000 80000 78000 76000 74000 72000 70000 68000 66000 64000 62000 60000 58000 56000 54000 52000 50000

-10 120 130 140 150 160 170 180 190 200 200 210 220 230 240 250 260 270

-5 120 130 140 150 160 170 180 190 200 200 210 220 230 240 250 260 270

0 120 130 140 150 160 170 180 190 190 200 210 220 230 240 250 260 270

5 110 130 130 150 160 170 180 190 190 200 210 220 230 240 250 260 270

ISA + 10 110 130 130 150 160 170 180 190 200 200 210 220 230 240 250 250 270

ºC 15 110 140 150 160 170 180 190 200 210 220 230 230 240 250 270

20 120 140 150 170 180 190 200 210 220 230 240 250 260

25 120 140 150 170 180 190 200 210 230 240 250

30 130 150 160 170 180 190 200 210 230

35 140 150 160 180 190 200 210

AOM-1502-003

"

6-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

One Engine Inoperative Performance

Page 27

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ONE ENGINE INOPERATIVE - HOLDING !EMBRAER 170 Models

The holding tables show indicated and true airspeed, Mach number, N1, fuel flow for various weights, altitudes, anti-ice on (with and without ice accretion) and off condition. Data are presented in ISA condition for one engine inoperative configuration.

6-30 Copyright © by Embraer. Refer to cover page for details.

Page 28

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

The associated conditions are: Flaps.......................................................................... UP Gear........................................................................... UP Bleeds........................................................................ OPEN CG............................................................................. 18% Minimum Remaining Rate of Climb.......................... 100 ft/min Airspeed A/I OFF....................................................... Minimum Fuel Consumption or 1.27 VS, whichever is higher. Airspeed A/I ON........................................................ Minimum Fuel Consumption or 210 KIAS, whichever is higher. Anti-ice....................................................................... OFF, ON and ON (WITH ICE ACCRETION).

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF SPEED: MINIMUM FUEL CONSUMPTION OR 1.27 VS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

AOM-1502-003

IAS kt 204 204 205 206 TAS kt 208 220 237 257 84000 MACH 0.317 0.338 0.372 0.410 N1 % 76.1 79.1 83.3 88.3 Fuel Flow lb/h/Eng 3095 3113 3136 3277 IAS kt 202 202 202 203 TAS kt 206 217 234 254 82000 MACH 0.313 0.334 0.367 0.405 N1 % 75.6 78.4 82.6 87.2 Fuel Flow lb/h/Eng 3023 3029 3050 3143 IAS kt 199 199 200 201 TAS kt 203 214 232 251 80000 MACH 0.309 0.330 0.363 0.400 N1 % 75.0 77.6 81.8 86.3 Fuel Flow lb/h/Eng 2950 2944 2961 3026 IAS kt 197 197 197 198 TAS kt 201 212 229 248 78000 MACH 0.305 0.326 0.358 0.395 N1 % 74.3 76.9 81.1 85.5 Fuel Flow lb/h/Eng 2877 2856 2870 2929 IAS kt 194 194 195 195 TAS kt 198 209 226 244 76000 MACH 0.301 0.321 0.354 0.390 N1 % 73.6 76.1 80.4 84.7 Fuel Flow lb/h/Eng 2803 2766 2789 2835 IAS kt 191 192 192 193 194 TAS kt 196 206 223 241 262 74000 MACH 0.297 0.317 0.349 0.385 0.427 N1 % 72.8 75.3 79.7 83.8 91.1 Fuel Flow lb/h/Eng 2728 2684 2713 2746 3019 IAS kt 189 189 190 190 191 TAS kt 193 203 220 238 259 72000 MACH 0.293 0.313 0.344 0.380 0.421 N1 % 72.1 74.6 78.8 83.1 89.5 Fuel Flow lb/h/Eng 2651 2614 2637 2665 2877 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

-

-

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6-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

One Engine Inoperative Performance

Page 29

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF SPEED: MINIMUM FUEL CONSUMPTION OR 1.27 VS STANDARD ATMOSPHERE

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 186 186 187 188 188 TAS kt 190 200 217 235 255 70000 MACH 0.289 0.308 0.339 0.375 0.415 N1 % 71.2 73.9 77.9 82.3 88.1 Fuel Flow lb/h/Eng 2572 2543 2559 2582 2745 IAS kt 184 184 184 185 185 TAS kt 188 198 213 231 251 68000 MACH 0.285 0.304 0.334 0.369 0.409 N1 % 70.4 73.1 77.0 81.5 86.7 Fuel Flow lb/h/Eng 2490 2472 2479 2497 2607 IAS kt 181 181 181 182 183 TAS kt 185 195 210 228 248 66000 MACH 0.281 0.300 0.329 0.364 0.403 N1 % 69.4 72.3 76.1 80.6 85.1 Fuel Flow lb/h/Eng 2408 2398 2397 2410 2463 IAS kt 178 178 179 179 180 TAS kt 182 192 207 224 244 64000 MACH 0.276 0.295 0.324 0.358 0.397 N1 % 68.2 71.5 75.1 79.7 84.1 Fuel Flow lb/h/Eng 2325 2322 2312 2321 2368 IAS kt 175 175 176 176 177 TAS kt 179 189 204 221 240 62000 MACH 0.272 0.290 0.319 0.352 0.391 N1 % 67.3 70.5 74.1 78.8 83.1 Fuel Flow lb/h/Eng 2265 2244 2224 2243 2279 IAS kt 172 173 173 173 174 TAS kt 176 186 201 217 236 60000 MACH 0.268 0.286 0.314 0.347 0.384 N1 % 66.4 69.5 73.3 77.9 82.2 Fuel Flow lb/h/Eng 2205 2165 2154 2168 2194 IAS kt 169 170 170 170 171 TAS kt 173 183 197 214 232 58000 MACH 0.263 0.281 0.309 0.341 0.378 N1 % 65.5 68.3 72.5 77.0 81.3 Fuel Flow lb/h/Eng 2143 2085 2084 2091 2114 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

175 257 0.428 90.2 2401 172 253 0.420 88.1 2254

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6-30 Copyright © by Embraer. Refer to cover page for details.

Page 30

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF SPEED: MINIMUM FUEL CONSUMPTION OR 1.27 VS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

AOM-1502-003

IAS kt 167 167 167 167 168 TAS kt 170 179 194 210 228 56000 MACH 0.259 0.276 0.303 0.335 0.371 N1 % 64.6 67.0 71.6 76.0 80.4 Fuel Flow lb/h/Eng 2078 2005 2010 2011 2030 IAS kt 164 164 164 164 165 TAS kt 167 176 190 206 224 54000 MACH 0.254 0.271 0.298 0.329 0.365 N1 % 63.7 66.1 70.8 74.9 79.3 Fuel Flow lb/h/Eng 2012 1947 1935 1930 1947 IAS kt 160 161 161 161 162 TAS kt 164 173 187 202 220 52000 MACH 0.249 0.266 0.292 0.323 0.358 N1 % 62.7 65.1 69.7 73.7 78.0 Fuel Flow lb/h/Eng 1943 1887 1858 1847 1863 IAS kt 157 158 158 158 159 TAS kt 161 169 183 198 215 50000 MACH 0.244 0.261 0.287 0.317 0.351 N1 % 61.6 64.1 68.5 72.5 76.9 Fuel Flow lb/h/Eng 1871 1825 1782 1770 1789 IAS kt 154 154 155 155 155 TAS kt 158 166 179 194 211 48000 MACH 0.239 0.255 0.281 0.310 0.344 N1 % 60.6 63.1 67.2 71.4 75.8 Fuel Flow lb/h/Eng 1797 1760 1704 1704 1715 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

169 249 0.413 86.1 2117 166 244 0.406 84.2 1981 162 240 0.398 82.8 1876 159 235 0.390 81.7 1787 156 230 0.382 80.6 1705

157 252 0.428 88.5 1897

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6-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

One Engine Inoperative Performance

Page 31

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 210 210 210 210 TAS kt 215 226 243 262 84000 MACH 0.326 0.347 0.381 0.419 N1 % 76.7 79.8 83.8 88.8 Fuel Flow lb/h/Eng 3264 3279 3297 3442 IAS kt 210 210 210 210 TAS kt 215 226 243 262 82000 MACH 0.326 0.347 0.381 0.419 N1 % 76.2 79.2 83.2 87.9 Fuel Flow lb/h/Eng 3206 3208 3224 3328 IAS kt 210 210 210 210 TAS kt 215 226 243 262 80000 MACH 0.326 0.347 0.381 0.419 N1 % 75.7 78.6 82.6 87.1 Fuel Flow lb/h/Eng 3148 3138 3150 3230 IAS kt 210 210 210 210 TAS kt 215 226 243 262 78000 MACH 0.326 0.347 0.381 0.419 N1 % 75.2 78.0 82.0 86.4 Fuel Flow lb/h/Eng 3089 3068 3077 3145 IAS kt 210 210 210 210 TAS kt 215 226 243 262 76000 MACH 0.326 0.347 0.381 0.419 N1 % 74.7 77.3 81.4 85.7 Fuel Flow lb/h/Eng 3031 2999 3014 3062 IAS kt 210 210 210 210 TAS kt 215 226 243 262 74000 MACH 0.326 0.347 0.381 0.419 N1 % 74.2 76.8 81.0 85.0 Fuel Flow lb/h/Eng 2979 2937 2957 2990 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 72000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 73.6 76.3 80.5 84.5 91.2 Fuel Flow lb/h/Eng 2929 2887 2899 2932 3164 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

-

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6-30 Copyright © by Embraer. Refer to cover page for details.

Page 32

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

AOM-1502-003

IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 70000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 73.1 75.8 80.0 84.0 89.9 Fuel Flow lb/h/Eng 2880 2837 2842 2877 3052 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 68000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 72.5 75.4 79.4 83.4 89.0 Fuel Flow lb/h/Eng 2831 2791 2796 2827 2973 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 66000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 72.0 74.9 78.8 82.9 88.1 Fuel Flow lb/h/Eng 2781 2746 2749 2776 2894 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 64000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 71.4 74.4 78.3 82.3 87.3 Fuel Flow lb/h/Eng 2732 2701 2702 2725 2820 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 62000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 71.1 73.9 77.7 81.9 86.5 Fuel Flow lb/h/Eng 2700 2659 2656 2683 2745 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 60000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 70.7 73.3 77.3 81.4 85.7 Fuel Flow lb/h/Eng 2672 2620 2622 2644 2680 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 58000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 70.4 72.8 76.9 81.0 85.2 Fuel Flow lb/h/Eng 2643 2580 2589 2605 2634 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

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6-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

One Engine Inoperative Performance

Page 33

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 56000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 70.0 72.3 76.5 80.6 84.7 Fuel Flow lb/h/Eng 2614 2541 2557 2565 2589 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 54000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 69.6 72.0 76.1 80.1 84.2 Fuel Flow lb/h/Eng 2586 2517 2524 2525 2543 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 52000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 69.1 71.7 75.7 79.6 83.7 Fuel Flow lb/h/Eng 2554 2493 2491 2484 2498 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 50000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 68.6 71.4 75.3 79.1 83.3 Fuel Flow lb/h/Eng 2523 2469 2459 2448 2462 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 48000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 68.1 71.0 74.9 78.8 82.9 Fuel Flow lb/h/Eng 2491 2444 2425 2419 2428 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

210 308 0.511 89.9 2594 210 308 0.511 88.7 2504 210 308 0.511 87.8 2442

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REVISION 21

AOM-1502-003

WEIGHT (lb)

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITH ICE ACCRETION) SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

AOM-1502-003

IAS kt 220 220 TAS kt 225 237 84000 MACH 0.341 0.364 N1 % 84.2 87.1 Fuel Flow lb/h/Eng 4261 4323 IAS kt 217 218 TAS kt 222 234 82000 MACH 0.337 0.360 N1 % 83.4 86.4 Fuel Flow lb/h/Eng 4157 4202 IAS kt 214 215 TAS kt 219 231 80000 MACH 0.333 0.355 N1 % 82.7 85.6 Fuel Flow lb/h/Eng 4051 4079 IAS kt 212 212 TAS kt 216 228 78000 MACH 0.329 0.351 N1 % 82.0 84.9 Fuel Flow lb/h/Eng 3943 3956 IAS kt 210 210 210 TAS kt 215 226 243 76000 MACH 0.326 0.347 0.381 N1 % 81.4 84.1 88.2 Fuel Flow lb/h/Eng 3851 3843 3907 IAS kt 210 210 210 TAS kt 215 226 243 74000 MACH 0.326 0.347 0.381 N1 % 81.0 83.6 87.8 Fuel Flow lb/h/Eng 3791 3779 3844 IAS kt 210 210 210 TAS kt 215 226 243 72000 MACH 0.326 0.347 0.381 N1 % 80.5 83.3 87.3 Fuel Flow lb/h/Eng 3731 3728 3783 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

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REVISION 21

One Engine Inoperative Performance

Page 35

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITH ICE ACCRETION) SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 210 210 210 TAS kt 215 226 243 70000 MACH 0.326 0.347 0.381 N1 % 80.1 82.9 86.9 Fuel Flow lb/h/Eng 3672 3676 3721 IAS kt 210 210 210 TAS kt 215 226 243 68000 MACH 0.326 0.347 0.381 N1 % 79.7 82.5 86.5 Fuel Flow lb/h/Eng 3612 3624 3659 IAS kt 210 210 210 TAS kt 215 226 243 66000 MACH 0.326 0.347 0.381 N1 % 79.2 82.1 86.1 Fuel Flow lb/h/Eng 3553 3572 3598 IAS kt 210 210 210 TAS kt 215 226 243 64000 MACH 0.326 0.347 0.381 N1 % 78.7 81.7 85.7 Fuel Flow lb/h/Eng 3495 3520 3536 IAS kt 210 210 210 210 TAS kt 215 226 243 262 62000 MACH 0.326 0.347 0.381 0.419 N1 % 78.4 81.3 85.3 90.0 Fuel Flow lb/h/Eng 3458 3469 3474 3572 IAS kt 210 210 210 210 TAS kt 215 226 243 262 60000 MACH 0.326 0.347 0.381 0.419 N1 % 78.0 80.9 85.0 89.5 Fuel Flow lb/h/Eng 3422 3417 3430 3516 IAS kt 210 210 210 210 TAS kt 215 226 243 262 58000 MACH 0.326 0.347 0.381 0.419 N1 % 77.7 80.5 84.6 89.0 Fuel Flow lb/h/Eng 3386 3366 3390 3460 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

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One Engine Inoperative Performance

REVISION 21

AOM-1502-003

WEIGHT (lb)

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITH ICE ACCRETION) SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 210 210 210 210 TAS kt 215 226 243 262 56000 MACH 0.326 0.347 0.381 0.419 N1 % 77.4 80.1 84.3 88.6 Fuel Flow lb/h/Eng 3350 3316 3350 3411 IAS kt 210 210 210 210 TAS kt 215 226 243 262 54000 MACH 0.326 0.347 0.381 0.419 N1 % 77.1 79.9 83.9 88.2 Fuel Flow lb/h/Eng 3313 3285 3310 3362 IAS kt 210 210 210 210 TAS kt 215 226 243 262 52000 MACH 0.326 0.347 0.381 0.419 N1 % 76.8 79.6 83.6 87.8 Fuel Flow lb/h/Eng 3277 3254 3270 3313 IAS kt 210 210 210 210 TAS kt 215 226 243 262 50000 MACH 0.326 0.347 0.381 0.419 N1 % 76.5 79.4 83.3 87.4 Fuel Flow lb/h/Eng 3241 3224 3230 3270 IAS kt 210 210 210 210 TAS kt 215 226 243 262 48000 MACH 0.326 0.347 0.381 0.419 N1 % 76.2 79.1 82.9 87.2 Fuel Flow lb/h/Eng 3205 3193 3190 3237 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

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REVISION 21

One Engine Inoperative Performance

Page 37

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ONE ENGINE INOPERATIVE - HOLDING !EMBRAER 175 Models

The holding tables show indicated and true airspeed, Mach number, N1, fuel flow for various weights, altitudes, anti-ice on (with and without ice accretion) and off condition. Data are presented in ISA condition for one engine inoperative configuration.

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One Engine Inoperative Performance

REVISION 21

AOM-1502-003

The associated conditions are: Flaps.......................................................................... UP Gear........................................................................... UP Bleeds........................................................................ OPEN CG............................................................................. 18% Minimum Remaining Rate of Climb.......................... 100 ft/min Airspeed A/I OFF....................................................... Minimum Fuel Consumption or 1.27 VS, whichever is higher. Airspeed A/I ON........................................................ Minimum Fuel Consumption or 210 KIAS, whichever is higher. Anti-ice....................................................................... OFF, ON and ON (WITH ICE ACCRETION).

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF SPEED: MINIMUM FUEL CONSUMPTION OR 1.27 VS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

AOM-1502-003

IAS kt 205 206 206 207 TAS kt 210 221 239 259 85000 MACH 0.319 0.340 0.374 0.413 N1 % 76.7 79.7 83.9 89.3 Fuel Flow lb/h/Eng 3164 3189 3214 3389 IAS kt 203 203 204 204 TAS kt 207 218 236 255 83000 MACH 0.315 0.336 0.369 0.408 N1 % 76.1 79.0 83.2 88.1 Fuel Flow lb/h/Eng 3091 3104 3128 3251 IAS kt 200 201 201 202 TAS kt 205 216 233 252 81000 MACH 0.311 0.332 0.365 0.403 N1 % 75.5 78.3 82.5 87.0 Fuel Flow lb/h/Eng 3018 3019 3039 3113 IAS kt 198 198 199 199 TAS kt 202 213 230 249 79000 MACH 0.307 0.328 0.360 0.398 N1 % 74.9 77.5 81.7 86.2 Fuel Flow lb/h/Eng 2943 2932 2949 3013 IAS kt 195 196 196 197 TAS kt 200 210 227 246 77000 MACH 0.303 0.324 0.356 0.393 N1 % 74.2 76.8 81.0 85.4 Fuel Flow lb/h/Eng 2869 2842 2858 2916 IAS kt 193 193 194 194 TAS kt 197 208 224 243 75000 MACH 0.299 0.319 0.351 0.388 N1 % 73.5 76.0 80.3 84.5 Fuel Flow lb/h/Eng 2794 2750 2781 2822 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

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REVISION 21

One Engine Inoperative Performance

Page 39

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF SPEED: MINIMUM FUEL CONSUMPTION OR 1.27 VS STANDARD ATMOSPHERE

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 190 190 191 192 192 TAS kt 194 205 221 240 260 73000 MACH 0.295 0.315 0.346 0.382 0.424 N1 % 72.7 75.3 79.6 83.8 90.8 Fuel Flow lb/h/Eng 2717 2676 2703 2737 2990 IAS kt 188 188 188 189 190 TAS kt 192 202 218 236 257 71000 MACH 0.291 0.311 0.342 0.377 0.418 N1 % 71.9 74.6 78.7 83.0 89.2 Fuel Flow lb/h/Eng 2638 2605 2626 2654 2849 IAS kt 185 185 186 186 187 TAS kt 189 199 215 233 253 69000 MACH 0.287 0.306 0.337 0.372 0.412 N1 % 71.1 73.8 77.8 82.2 87.8 Fuel Flow lb/h/Eng 2557 2533 2547 2569 2713 IAS kt 182 182 183 183 184 TAS kt 186 196 212 230 249 67000 MACH 0.283 0.302 0.332 0.366 0.406 N1 % 70.2 73.0 76.9 81.3 86.3 Fuel Flow lb/h/Eng 2474 2460 2465 2481 2569 IAS kt 179 180 180 181 181 TAS kt 183 193 209 226 246 65000 MACH 0.279 0.297 0.327 0.361 0.400 N1 % 69.1 72.2 75.9 80.4 84.9 Fuel Flow lb/h/Eng 2390 2384 2380 2392 2443 IAS kt 177 177 177 178 178 TAS kt 180 190 205 223 242 63000 MACH 0.274 0.293 0.322 0.355 0.394 N1 % 68.0 71.3 74.9 79.5 83.9 Fuel Flow lb/h/Eng 2316 2307 2293 2304 2350 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

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One Engine Inoperative Performance

REVISION 21

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF SPEED: MINIMUM FUEL CONSUMPTION OR 1.27 VS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

AOM-1502-003

IAS kt 174 174 174 175 175 TAS kt 178 187 202 219 238 61000 MACH 0.270 0.288 0.317 0.350 0.387 N1 % 67.2 70.3 74.0 78.6 82.9 Fuel Flow lb/h/Eng 2256 2227 2211 2229 2261 IAS kt 171 171 171 172 173 TAS kt 175 184 199 215 234 59000 MACH 0.265 0.283 0.311 0.344 0.381 N1 % 66.3 69.3 73.1 77.7 82.1 Fuel Flow lb/h/Eng 2194 2146 2141 2152 2179 IAS kt 168 168 169 169 170 TAS kt 172 181 195 212 230 57000 MACH 0.261 0.278 0.306 0.338 0.375 N1 % 65.3 68.0 72.3 76.8 81.2 Fuel Flow lb/h/Eng 2130 2065 2069 2073 2096 IAS kt 165 165 166 166 166 TAS kt 169 178 192 208 226 55000 MACH 0.256 0.273 0.301 0.332 0.368 N1 % 64.4 66.9 71.4 75.8 80.2 Fuel Flow lb/h/Eng 2064 1995 1993 1992 2011 IAS kt 162 162 162 163 163 TAS kt 166 174 188 204 222 53000 MACH 0.252 0.268 0.295 0.326 0.361 N1 % 63.4 65.9 70.5 74.6 79.0 Fuel Flow lb/h/Eng 1996 1935 1915 1909 1926 IAS kt 159 159 159 160 160 TAS kt 162 171 185 200 218 51000 MACH 0.247 0.263 0.290 0.320 0.354 N1 % 62.4 64.9 69.5 73.3 77.8 Fuel Flow lb/h/Eng 1925 1873 1838 1824 1844 IAS kt 156 156 156 157 157 TAS kt 159 168 181 196 213 49000 MACH 0.242 0.258 0.284 0.313 0.347 N1 % 61.4 63.9 68.1 72.2 76.6 Fuel Flow lb/h/Eng 1851 1809 1760 1755 1771 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

173 255 0.424 89.7 2365 170 251 0.417 87.6 2217 167 246 0.409 85.6 2077 164 242 0.402 83.7 1943 161 237 0.394 82.5 1852 158 233 0.386 81.4 1764

158 255 0.432 90.4 1999

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REVISION 21

One Engine Inoperative Performance

Page 41

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 210 210 210 210 TAS kt 215 226 243 262 85000 MACH 0.326 0.347 0.381 0.419 N1 % 77.2 80.4 84.4 89.8 Fuel Flow lb/h/Eng 3328 3351 3371 3555 IAS kt 210 210 210 210 TAS kt 215 226 243 262 83000 MACH 0.326 0.347 0.381 0.419 N1 % 76.7 79.8 83.8 88.7 Fuel Flow lb/h/Eng 3269 3280 3297 3428 IAS kt 210 210 210 210 TAS kt 215 226 243 262 81000 MACH 0.326 0.347 0.381 0.419 N1 % 76.2 79.2 83.2 87.8 Fuel Flow lb/h/Eng 3211 3209 3224 3313 IAS kt 210 210 210 210 TAS kt 215 226 243 262 79000 MACH 0.326 0.347 0.381 0.419 N1 % 75.7 78.6 82.6 87.1 Fuel Flow lb/h/Eng 3153 3139 3151 3228 IAS kt 210 210 210 210 TAS kt 215 226 243 262 77000 MACH 0.326 0.347 0.381 0.419 N1 % 75.2 78.0 82.0 86.4 Fuel Flow lb/h/Eng 3095 3069 3079 3144 IAS kt 210 210 210 210 TAS kt 215 226 243 262 75000 MACH 0.326 0.347 0.381 0.419 N1 % 74.7 77.3 81.5 85.7 Fuel Flow lb/h/Eng 3036 2999 3021 3061 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

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One Engine Inoperative Performance

REVISION 21

AOM-1502-003

WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

AOM-1502-003

IAS kt 210 210 210 210 TAS kt 215 226 243 262 73000 MACH 0.326 0.347 0.381 0.419 N1 % 74.2 76.8 81.0 85.1 Fuel Flow lb/h/Eng 2983 2946 2964 2997 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 71000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 73.7 76.4 80.5 84.6 91.2 Fuel Flow lb/h/Eng 2934 2896 2906 2939 3162 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 69000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 73.1 75.9 80.0 84.0 89.9 Fuel Flow lb/h/Eng 2884 2846 2849 2883 3050 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 67000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 72.6 75.4 79.5 83.5 89.0 Fuel Flow lb/h/Eng 2835 2799 2801 2833 2971 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 65000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 72.0 74.9 78.9 82.9 88.1 Fuel Flow lb/h/Eng 2785 2754 2755 2782 2894 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 63000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 71.6 74.5 78.3 82.4 87.3 Fuel Flow lb/h/Eng 2743 2709 2708 2733 2820 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

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REVISION 21

One Engine Inoperative Performance

Page 43

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 61000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 71.2 74.0 77.8 82.0 86.5 Fuel Flow lb/h/Eng 2712 2666 2667 2694 2745 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 59000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 70.9 73.4 77.4 81.6 85.9 Fuel Flow lb/h/Eng 2683 2627 2634 2655 2693 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 57000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 70.5 72.9 77.0 81.1 85.4 Fuel Flow lb/h/Eng 2655 2587 2601 2616 2647 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 55000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 70.1 72.5 76.6 80.7 84.9 Fuel Flow lb/h/Eng 2626 2555 2568 2577 2602 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 53000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 69.8 72.2 76.2 80.2 84.4 Fuel Flow lb/h/Eng 2597 2531 2536 2536 2556 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 51000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 69.3 71.9 75.8 79.7 83.9 Fuel Flow lb/h/Eng 2567 2507 2503 2495 2514 IAS kt 210 210 210 210 210 TAS kt 215 226 243 262 284 49000 MACH 0.326 0.347 0.381 0.419 0.462 N1 % 68.8 71.5 75.4 79.4 83.5 Fuel Flow lb/h/Eng 2535 2483 2470 2465 2480 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

210 308 0.511 90.0 2598 210 308 0.511 88.7 2508

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One Engine Inoperative Performance

REVISION 21

AOM-1502-003

WEIGHT (lb)

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITH ICE ACCRETION) SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

AOM-1502-003

IAS kt 221 222 TAS kt 226 238 85000 MACH 0.343 0.366 N1 % 84.7 87.7 Fuel Flow lb/h/Eng 4354 4426 IAS kt 218 219 TAS kt 223 235 83000 MACH 0.339 0.362 N1 % 84.1 87.0 Fuel Flow lb/h/Eng 4247 4305 IAS kt 216 216 TAS kt 220 232 81000 MACH 0.335 0.357 N1 % 83.4 86.3 Fuel Flow lb/h/Eng 4141 4181 IAS kt 213 214 TAS kt 218 229 79000 MACH 0.331 0.353 N1 % 82.6 85.5 Fuel Flow lb/h/Eng 4034 4057 IAS kt 210 211 TAS kt 215 227 77000 MACH 0.327 0.348 N1 % 81.9 84.7 Fuel Flow lb/h/Eng 3924 3932 IAS kt 210 210 210 TAS kt 215 226 243 75000 MACH 0.326 0.347 0.381 N1 % 81.5 84.1 88.2 Fuel Flow lb/h/Eng 3856 3843 3914 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

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REVISION 21

One Engine Inoperative Performance

Page 45

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITH ICE ACCRETION) SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 210 210 210 TAS kt 215 226 243 73000 MACH 0.326 0.347 0.381 N1 % 81.0 83.7 87.8 Fuel Flow lb/h/Eng 3796 3789 3852 IAS kt 210 210 210 TAS kt 215 226 243 71000 MACH 0.326 0.347 0.381 N1 % 80.6 83.3 87.4 Fuel Flow lb/h/Eng 3736 3737 3790 IAS kt 210 210 210 TAS kt 215 226 243 69000 MACH 0.326 0.347 0.381 N1 % 80.1 82.9 87.0 Fuel Flow lb/h/Eng 3677 3685 3729 IAS kt 210 210 210 TAS kt 215 226 243 67000 MACH 0.326 0.347 0.381 N1 % 79.7 82.6 86.6 Fuel Flow lb/h/Eng 3617 3633 3667 IAS kt 210 210 210 TAS kt 215 226 243 65000 MACH 0.326 0.347 0.381 N1 % 79.2 82.2 86.1 Fuel Flow lb/h/Eng 3558 3582 3605 IAS kt 210 210 210 TAS kt 215 226 243 63000 MACH 0.326 0.347 0.381 N1 % 78.8 81.8 85.7 Fuel Flow lb/h/Eng 3509 3530 3543 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

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One Engine Inoperative Performance

REVISION 21

AOM-1502-003

WEIGHT (lb)

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

HOLDING - ONE ENGINE INOPERATIVE ALL ENGINE TYPES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITH ICE ACCRETION) SPEED: MINIMUM FUEL CONSUMPTION OR 210 KIAS STANDARD ATMOSPHERE

WEIGHT (lb)

1500

ALTITUDE (ft) 5000 10000 15000 20000 25000 30000 35000

IAS kt 210 210 210 210 TAS kt 215 226 243 262 61000 MACH 0.326 0.347 0.381 0.419 N1 % 78.5 81.4 85.4 90.1 Fuel Flow lb/h/Eng 3473 3478 3489 3588 IAS kt 210 210 210 210 TAS kt 215 226 243 262 59000 MACH 0.326 0.347 0.381 0.419 N1 % 78.2 81.0 85.1 89.6 Fuel Flow lb/h/Eng 3437 3426 3446 3532 IAS kt 210 210 210 210 TAS kt 215 226 243 262 57000 MACH 0.326 0.347 0.381 0.419 N1 % 77.9 80.6 84.7 89.1 Fuel Flow lb/h/Eng 3400 3374 3405 3476 IAS kt 210 210 210 210 TAS kt 215 226 243 262 55000 MACH 0.326 0.347 0.381 0.419 N1 % 77.6 80.3 84.4 88.7 Fuel Flow lb/h/Eng 3364 3334 3365 3424 IAS kt 210 210 210 210 TAS kt 215 226 243 262 53000 MACH 0.326 0.347 0.381 0.419 N1 % 77.2 80.0 84.1 88.3 Fuel Flow lb/h/Eng 3328 3303 3325 3375 IAS kt 210 210 210 210 TAS kt 215 226 243 262 51000 MACH 0.326 0.347 0.381 0.419 N1 % 76.9 79.8 83.7 87.9 Fuel Flow lb/h/Eng 3292 3272 3284 3327 IAS kt 210 210 210 210 TAS kt 215 226 243 262 49000 MACH 0.326 0.347 0.381 0.419 N1 % 76.6 79.5 83.4 87.6 Fuel Flow lb/h/Eng 3255 3242 3244 3291 FOR HOLDING IN A RACETRACK INCREASE FUEL FLOW BY 5%.

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REVISION 21

One Engine Inoperative Performance

Page 47

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

ONE ENGINE INOPERATIVE - MAXIMUM DISTANCE FROM AN ADEQUATE AERODROME The maximum distance from an adequate aerodrome is an area limited to the maximum time approved by the local authority from an adequate aerodrome, computed using an one-engine-inoperative cruise speed under standard conditions in still air and considering that the driftdown starts at or near to the optimum flight level. The distance from any point along the proposed route of flight to an adequate aerodrome must be covered within the maximum allowed time using one of the speeds shown in the table provided in this section (assuming still air, ISA conditions and one engine inoperative). The data is based on OEI drifting down using Maximum Continuous Thrust at the Mach number until reaching the corresponding IAS and maintaining that airspeed during the remaining of the driftdown and level cruise.

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One Engine Inoperative Performance

REVISION 21

AOM-1502-003

Enter the table for the appropriate speed with the weight at the point of diversion and time selected and read the maximum distance from an adequate aerodrome.

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

!170 models, units in lb

Speed Schedule

0.77 M/ 290 KIAS

0.76 M/ 280 KIAS

0.74 M/ 250 KIAS

Weight at Diversion (lb) 64000 68000 72000 76000 80000 84000 64000 68000 72000 76000 80000 84000 64000 68000 72000 76000 80000 84000

DIVERSION DISTANCE (NM) Diversion Time 60 min 75 min 361 441 360 439 358 437 356 434 352 431 350 427 361 446 359 441 358 439 355 436 352 432 349 428 351 435 348 430 345 426 341 421 336 416 333 411

AOM-1502-003

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REVISION 21

One Engine Inoperative Performance

Page 49

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

!175 models, units in lb

Speed Schedule

0.77 M/ 290 KIAS

0.76 M/ 280 KIAS

0.74 M/ 250 KIAS

Weight at Diversion (lb) 64000 68000 72000 76000 80000 84000 64000 68000 72000 76000 80000 84000 64000 68000 72000 76000 80000 84000

DIVERSION DISTANCE (NM) Diversion Time 60 min 75 min 361 441 360 439 358 437 356 434 352 431 350 427 361 446 359 441 358 439 355 436 352 432 349 428 351 435 348 430 345 426 341 421 336 416 333 411

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Page 50

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

ONE ENGINE INOPERATIVE - INFLIGHT DIVERSION This chart enables rapid determination of fuel and time required to proceed to an alternate airport with One Engine Inoperative from the driftdown initial point. The chart data is based in a driftdown at Green Dot speed with the remaining cruise distance at LRC speed and the descent to approach phase at 290 KIAS. The following phases are included: driftdown, cruise and descent to approach. Fuel and time are determined in the same way as the simplified flight planning charts, with distance to destination instead of trip distance, disregarding the climb phase and the cruise phase until the driftdown point.

AOM-1502-003

The pilots can also use the charts in the opposite direction, i.e., entering with the fuel remaining on board and finding the range at an initial weight.

6-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

One Engine Inoperative Performance

Page 51

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

EMBRAER 170 INFLIGHT DIVERSION DIVERSION FUEL/TIME ALL ENGINE TYPES DRIFTDOWN/LONG RANGE CRUISE ONE ENGINE INOPERATIVE

ISA CONDITION 7600

84000

7200

MISSION SCHEDULE: DRIFTDOWN AT GREEN DOT AFTER LEVEL OFF − LRC 290 KIAS DESCENT

6800 6400

80000 76000 72000

6000

68000 & BELOW

5600

4800 4400 4000 3600

V DI

3200

ER

SI

ON

1600 AL

1200

L

D

E IV

RS

−

lb

150 140

120

2400 N IO

HT

130

2800

2000

W

G EI

W

EI

GH

110

TS

100 90 80 70

800

60

400

50 40

0

DIVERSION TIME − MIN

DIVERSION FUEL − lb

5200

30

WIND − kt TAIL HEAD

20 60

40

REF. LINE 50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800 DIVERSION DISTANCE − NM

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Page 52

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

60

EM170AOM060092A.DGN

0

40

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

EMBRAER 175 INFLIGHT DIVERSION DIVERSION FUEL/TIME ALL ENGINE TYPES DRIFTDOWN/LONG RANGE CRUISE ONE ENGINE INOPERATIVE

ISA CONDITION 7600 7200 6800 6400

84000

MISSION SCHEDULE: DRIFTDOWN AT GREEN DOT AFTER LEVEL OFF − LRC 290 KIAS DESCENT

80000 76000 72000 68000 & BELOW

5600 5200 4800 4400 4000

D

E IV

R

O SI

N

W

E

H IG

T

−

lb

150 140 130

3600 3200

120

2800

110

2400 2000 1600

A

LL

DI

R VE

SI

ON

W

EI

T GH

100

S

90 80 70 60 50

DIVERSION TIME − MIN

DIVERSION FUEL − lb

6000

40 30

60 30 0 REF. LINE

30

60 50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800

AOM-1502-003

DIVERSION DISTANCE − NM

EM170AOM060094A.DGN

WIND − kt TAIL HEAD

20

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REVISION 21

One Engine Inoperative Performance

Page 53

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

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Page 54

One Engine Inoperative Performance

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

INFLIGHT DIVERSION !EMBRAER 170 Models

These charts are provided for the pilots to determine if the fuel remaining is enough to complete the trip at Long Range Cruise (LRC) mode from one point in cruise to an alternate airport. The charts also enable rapid determination of fuel and time required to proceed to an alternate airport. Fuel and time are determined in the same way as the simplified flight planning charts, with distance to destination instead of trip distance, disregarding the climb phase.

AOM-1502-003

The pilots can also use the charts in the opposite direction, i.e., entering with the fuel remaining on board and finding the range at a given flight level at LRC.

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REVISION 21

Inflight Diversion

Page 1

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

EMBRAER 170 INFLIGHT DIVERSION TRIP FUEL ALL ENGINE TYPES LONG RANGE CRUISE ISA CONDITION FL 200 FL 250 FL 300

16000 BASED ON: M 0.77 / 290 / 250 DESCENT

FL 150

FL 350

14000

FUEL REQUIRED − lb

FL 370 AND ABOVE 12000 10000 8000 6000 4000

REF. LINE

77000 75000 73000 71000 69000 67000 60 30

REF. LINE

30 60 0

200

400

600

800 1000 1200 1400 1600 1800 2000 2200 2400

DISTANCE TO DESTINATION − NM

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Page 2

Inflight Diversion

REVISION 21

AOM-1502-003

0

EM170AOM060016F.DGN

WIND − kt TAIL HEAD

LANDING WEIGHT − lb

2000

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

EMBRAER 170 INFLIGHT DIVERSION TRIP TIME ALL ENGINE TYPES LONG RANGE CRUISE ISA CONDITION FL 200 FL 250

TIME REQUIRED − min

300

BASED ON: M 0.77 / 290 / 250 DESCENT

FL 300

FL 150 FL 350

250

FL 370 AND ABOVE 200

150

100

0 77000 75000 73000 71000 69000 67000 60

REF. LINE

30 0

REF. LINE

30 60 0

200

400

600

800 1000 1200 1400 1600 1800 2000 2200

AOM-1502-003

DISTANCE TO DESTINATION − NM

EM170AOM060018F.DGN

WIND − kt TAIL HEAD

LANDING WEIGHT − lb

50

"

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REVISION 21

Inflight Diversion

Page 3

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

INFLIGHT DIVERSION !EMBRAER 175 Models

These charts are provided for the pilots to determine if the fuel remaining is enough to complete the trip at Long Range Cruise (LRC) mode from one point in cruise to an alternate airport. The charts also enable rapid determination of fuel and time required to proceed to an alternate airport. Fuel and time are determined in the same way as the simplified flight planning charts, with distance to destination instead of trip distance, disregarding the climb phase.

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Page 4

Inflight Diversion

REVISION 21

AOM-1502-003

The pilots can also use the charts in the opposite direction, i.e., entering with the fuel remaining on board and finding the range at a given flight level at LRC.

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

EMBRAER 175 INFLIGHT DIVERSION TRIP FUEL ALL ENGINE TYPES LONG RANGE CRUISE

LANDING WEIGHT − lb

FUEL REQUIRED − lb

ISA CONDITION 23000 22000 21000 20000 19000 18000 17000 16000 15000 14000 13000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000

BASED ON: M 0.77 / 290 / 250 DESCENT

FL 150

FL 200 FL 250

FL 300 FL 350

FL370 AND ABOVE

74000 70000 68000 66000 62000 58000 54000

REF. LINE

30 REF. LINE

0 30 60 0

200

400

600

800

1000 1200 1400 1600 1800 2000 2200 2400 2600

AOM-1502-003

DISTANCE TO DESTINATION − NM

EM170AOM060067E.DGN

WIND − kt TAIL HEAD

60

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REVISION 21

Inflight Diversion

Page 5

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

EMBRAER 175 INFLIGHT DIVERSION TRIP TIME ALL ENGINE TYPES LONG RANGE CRUISE

WIND − kt LANDING WEIGHT − lb TAIL HEAD

FLIGHT TIME − min

ISA CONDITION FL 250

450 430 410 390 370 350 330 310 290 270 250 230 210 190 170 150 130 110 90 70 50 30 10

BASED ON: M 0.77 / 290 / 250 DESCENT

FL 150

FL 200

FL 300

FL 350

FL 370 AND ABOVE

74000 70000 66000 62000 58000 54000 60

60 0

200 400 600 800 1000 1200 1400 1600 1800 2000 2200 2400 2600 DISTANCE TO DESTINATION − NM

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Page 6

Inflight Diversion

REVISION 21

AOM-1502-003

0 30

EM170AOM060068E.DGN

30

AIRPLANE OPERATIONS MANUAL

FLIGHT PLANNING

"

FLIGHT OVER MOUNTAINOUS AREA Two situations must be considered when flying over mountainous areas, in order to clear route obstacles: Engine Failure For most normal cruise weights and altitudes, an airplane will not be able to maintain its cruise altitude following an engine failure, and will begin to descend (drift down). In order to remain as high as possible, the pilot will use maximum continuous thrust on the remaining engine and slow down to the optimum driftdown speed, which is the speed that results in the lower descent gradient. The airplane will then descend along what is called the optimum driftdown profile. The optimum driftdown profile will keep the airplane as high as possible during the descent. Regulations require that the actual airplane performance be calculated in the most conservative airplane configuration and then further decreased by a 1.1% climb gradient for two-engine airplanes. This reduced gradient path is called the en-route net flight path and is used to ensure en-route obstacle clearance (FAR 25.123 / CS 25.123). During a driftdown, the available thrust increases as the airplane descends. Eventually, at a certain altitude the available thrust will become equal to the airplane drag, and the airplane will level off. This altitude is called the gross level off altitude. The gross level-off altitude, when corrected by the 1.1% gradient margin, is called the net level-off altitude and will depend on the atmospheric temperature and the airplane weight. The airplane actual climb gradient (gross gradient) at the net level-off altitude will be 1.1%. The net gradient is the gross gradient subtracted by 1.1%. Obviously, the net gradient is zero at the net level off altitude, and the gross gradient is zero at the gross level off altitude. Regulations (FAR 121.191 / EU OPS 1.500) require that the airplane be able to clear all terrain by a given margin when an engine fails. Two means of compliance for en-route obstacle clearance are allowed:

AOM-1502-003

–

The net level-off altitude must clear all en-route obstacles by at least 1000 ft; or

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REVISION 21

Inflight Diversion

Page 7

FLIGHT PLANNING

–

AIRPLANE OPERATIONS MANUAL

The net flight path must clear all en-route obstacles between the point where the engine is assumed to fail and an airport where a landing can be made by at least 2000 ft.

NET DRIFTDOWN PATH 2000 ft NET LEVEL−OFF 1000 ft OBSTACLE

OBSTACLE

EM170AOM050077A.DGN

GROSS DRIFTDOWN PATH

Prior to departure a detailed analysis of the route should be made using contour maps of the high terrain and plotting the highest points within the corridor’s width along the route (or, alternatively, using Minimum En-Route Altitude, MEA, or Minimum Off Route Altitude, MORA). The next step is to determine if it is possible to maintain level flight with one engine inoperative 1000 ft above the highest point of the crossing. If this is not possible, or if the associated weight penalties are unacceptable, a driftdown procedure should be worked out, based on engine failure at the most critical point and clearing critical obstacles during the driftdown by at least 2000 ft. The minimum cruise altitude and the point of no return (PNR) are determined by the intersection of the two driftdown paths.

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Page 8

Inflight Diversion

REVISION 21

AOM-1502-003

If an engine failure occurs after the PNR, the airplane will drift down on course. If the failure occurs before PNR, the airplane will have to turn back. In either flight direction the net flight path must clear the obstacles by 2000 ft.

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL Depressurization

The following charts present the passenger chemical oxygen generator descent profile. In case of an emergency descent, the airplane path must be at or below the generator profile in order to ensure sufficient supplemental breathing oxygen to the passengers. 12 MINUTE CHEMICAL OXYGEN GENERATOR DESCENT PROFILE 42000 40000 38000

PRESSURE ALTITUDE (ft)

36000 34000 32000 30000 28000 26000 24000 22000 20000 16000 14000 12000 10000 0

1

2

3

4

5

7

6

8

9

AOM-1502-003

TIME (min)

10

11

12

13

EM170AOM060114A.DGN

18000

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REVISION 21

Inflight Diversion

Page 9

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

14 MINUTE CHEMICAL OXYGEN GENERATOR DESCENT PROFILE 42000 40000 38000

PRESSURE ALTITUDE (ft)

36000 34000 32000 30000 28000 26000 24000 22000 20000 18000

12000 10000 0

1

2

3

4

5

6

7

8

9

10

TIME (min)

11

12

13

14

15

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Page 10

Inflight Diversion

REVISION 21

AOM-1502-003

14000

EM170AOM060115A.DGN

16000

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

22 MINUTE CHEMICAL OXYGEN GENERATOR DESCENT PROFILE 42000 40000 38000

PRESSURE ALTITUDE (ft)

36000 34000 32000 30000 28000 26000 24000 22000 20000 18000 14000 12000 10000 0

1

2

3

4

5

6

7

8

9

10

11 12

13

14

15

16

AOM-1502-003

TIME (min)

17

18

19

20

21 22

23

EM170AOM060116A.DGN

16000

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REVISION 21

Inflight Diversion

Page 11

FLIGHT PLANNING

AIRPLANE OPERATIONS MANUAL

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Page 12

Inflight Diversion

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

WEIGHT AND BALANCE

SECTION 7 WEIGHT AND BALANCE TABLE OF CONTENTS Block

Page

Introduction.......................................................... 7-INTRO ....

1

Standard Terms and Definitions......................... 7-05 ........... STANDARD TERMS AND DEFINITIONS.............. 7-05 ...........

1 1

General Data......................................................... 7-10 ........... 1 GENERAL DATA.................................................... 7-10 ........... 1 BALANCE REFERENCE SYSTEM....................... 7-10 ........... 1 FUEL AS BALLAST................................................ 7-10 ........... 4 MOMENT/CG CHANGES...................................... 7-10 ........... 4 AIRPLANE JACKING............................................. 7-10 ........... 5 MISCELLANEOUS FLUIDS................................... 7-10 ........... 6 BAGGAGE LOADING............................................ 7-10 ........... 7 FUEL DATA............................................................ 7-10 ........... 12 PASSENGERS....................................................... 7-10 ........... 13 FLIGHT CREW ITEMS.......................................... 7-10 ........... 14

AOM-1502-003

Index System........................................................ 7-15 ........... INDEX SYSTEM.................................................... 7-15 ........... INDEX INFLUENCE............................................... 7-15 ........... FUEL INDEX VARIATION...................................... 7-15 ........... OEW/OEI DETERMINATION................................. 7-15 ...........

1 1 2 4 9

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REVISION 21

Table of Contents

Page 1

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

7-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

WEIGHT AND BALANCE

INTRODUCTION

AOM-1502-003

This section contains information equivalent to the Weight and Balance manual and is intended to assist the operator in defining the weight and balance system and constrained CG limits.

7-INTRO Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Page 1

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

7-INTRO Copyright © by Embraer. Refer to cover page for details.

Page 2

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

STANDARD TERMS AND DEFINITIONS EQUIPPED EMPTY WEIGHT (EEW) OR MANUFACTURER EMPTY WEIGHT (MEW) It is the weight of structure, powerplant, instruments, interior furnishings, systems, optional, portable, and emergency equipment and other items of equipment that are an integral part of the airplane configuration. It is essentially a dry weight, including only those fluids contained in closed systems such as oxygen, fire extinguisher agent, landing gear shock absorber fluid, etc.

BASIC EMPTY WEIGHT (BEW) It is the MEW plus the weight of the following items: – APU oil; – Engine oil; – Hydraulic fluid; – Unusable fuel.

OPERATIONAL EMPTY WEIGHT OPERATING WEIGHT (DOW)

(OEW)

OR

DRY

It is the BEW plus the weight of the operational items, which are those necessary for airplane operation and not included in the BEW. The operational items are: – Crew and crew baggage; – Navigation kit (manuals, charts, etc.); – Catering (beverages and foods) and removable service equipment for galley (such as standard units, etc.); – Lavatory rinse water; – Lavatory chemical fluid.

ACTUAL ZERO FUEL WEIGHT (AZFW) AOM-1502-003

This is the OEW plus actual payload.

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REVISION 9

Standard Terms and Definitions

Page 1

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

PAYLOAD OR TOTAL TRAFFIC LOAD This is the weight of passengers, baggage and cargo.

MAXIMUM ALLOWABLE PAYLOAD It is the maximum approved weight that can be loaded into the airplane. Maximum payload is the Maximum Zero Fuel Weight (MZFW) minus Operational Empty Weight (OEW).

MAXIMUM DESIGN ZERO FUEL WEIGHT (MZFW) This is the maximum authorized weight before usable fuel be loaded. The MZFW is related to airplane structural limitations.

MAXIMUM DESIGN RAMP WEIGHT (MRW) This is the maximum authorized ramp weight.

MAXIMUM DESIGN TAKEOFF WEIGHT (MTOW) This is the maximum authorized weight for takeoff.

MAXIMUM DESIGN LANDING WEIGHT (MLW) This is the maximum authorized weight for landing.

MINIMUM OPERATING WEIGHT (MOW) This is the minimum authorized weight to operate the airplane.

CENTER OF GRAVITY (CG) This is the position where the mass of the aircraft is considered concentrated for balance purposes. It is normally referred to in terms of % MAC.

AIRPLANE DATUM

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Page 2

Standard Terms and Definitions

REVISION 9

AOM-1502-003

This is a plane perpendicular to the fuselage centerline from where all arm measurements are taken.

AIRPLANE OPERATIONS MANUAL

WEIGHT AND BALANCE

MEAN AERODYNAMIC CHORD (MAC) This is the chord of an imaginary rectangular airfoil with the same area of the actual wing and which produces the same resulting force vectors of the actual wing. The airplane forward and aft CG limits are referred to in terms of % MAC.

INDEX SYSTEM

AOM-1502-003

This is a convention for presenting airplane or body moments. It is the moment of the body converted to a different measuring system.

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REVISION 9

Standard Terms and Definitions

Page 3

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

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Page 4

Standard Terms and Definitions

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

GENERAL DATA The general data presented in this section is used for specific weight and balance calculations and is equivalent to the information contained in the Weight & Balance Manual.

BALANCE REFERENCE SYSTEM AIRPLANE DATUM

!EMBRAER 170 models, length in British units

Airplane datum is a perpendicular plane to the fuselage centerline, located at 458.66 in ahead of the wing stub front spar. For external reference, datum is located at 473.34 in ahead of the wing jack points. "

AIRPLANE DATUM

!EMBRAER 175 models, length in British units

Airplane datum is a perpendicular plane to the fuselage centerline, located at 491.65 in ahead of the wing stub front spar. For external reference, datum is located at 506.34 in ahead of the wing jack points. "

BALANCE ARMS/BODY STATION Balance arms are the distances in meters from the airplane datum located at the zero station of the fuselage - of the centers of gravity (CG) regarding airplane and components identified throughout this manual.

WING MEAN AERODYNAMIC CHORD (MAC) !EMBRAER 170, Weight and Balance length in British units

MAC length LEMAC balance arm

= =

125.75 in 508.86 in

Percentage of MAC is obtained using the following formula: %MAC

=

(B.A. –508.86)x100 125.75

Where B.A. = Balance arm of airplane CG measured in inches. AOM-1502-003

"

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REVISION 21

General Data

Page 1

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

DATUM

!EMBRAER 170 Models

meters (feet)

MAC 0

5

10

20

12.92 m (42.38 ft)

25

29.90 m (98 ft 1 in.)

35

16.11 m (52.82 ft)

B.A.

% MAC =

BA ( BA − LEMAC ) X 100 MAC

% MAC =

(

BA − 12.925

(

BA − 508.86

% MAC =

3.194

125.75

EM170AOM070001A.DGN

DATUM

LEMAC B.A.

) X 100 ) X 100

WING MEAN AERODYNAMIC CHORD (MAC)

"

WING MEAN AERODYNAMIC CHORD (MAC) !EMBRAER 175 models, length in British units

MAC length LEMAC balance arm

= =

125.75 in 541.85 in

7-10 Copyright © by Embraer. Refer to cover page for details.

Page 2

General Data

REVISION 21

AOM-1502-003

Percentage of MAC is obtained using the following formula:

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

%MAC

=

(B.A. –541.85)x100 125.75

Where B.A. = Balance arm of airplane CG measured in inches. "

DATUM

!EMBRAER 175 Models

meters (feet)

MAC 0

5

10

13.763 m (45 ft 2 in.)

20

25

16.957 m (55 ft 8 in.)

35

30 31.68 m (103 ft 11 in.)

B.A.

% MAC =

BA ( BA − LEMAC ) X 100 MAC

% MAC =

(

BA − 13.763 3.194

EM170AOM070004A.DGN

DATUM

LEMAC B.A.

) X 100 WING MEAN AERODYNAMIC CHORD (MAC)

AOM-1502-003

"

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REVISION 21

General Data

Page 3

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

FUEL AS BALLAST Fuel may be used as ballast in order to relocate the ZFW inside the CG envelope. The ZFW informed in the FMS, however, must not consider the fuel quantity used as ballast. This additional fuel must not be consumed during flight.

MOMENT/CG CHANGES DUE TO ANY PASSENGER OR CREW MEMBER INFLIGHT MOVEMENT A person moving from the front to the rear of the cabin or vice-versa causes the following CG travel: !170 models, units in lb

– For 47400 lb: CG moves aft or forward in a maximum range of 1.7% of MAC. – For 81240 lb: CG moves aft or forward in a maximum range of 0.9% of MAC. " !175 models, units in lb

– For 50705 lb (low weights): CG moves aft or forward in a maximum range of 2.0% of MAC. – For 70546 lb (intermediate weights): CG moves aft or forward in a maximum range of 1.4% of MAC. – For 83774 lb (high weights): CG moves aft or forward in a maximum range of 1.2% of MAC. "

DUE TO LANDING GEAR CONFIGURATION When the landing gear is retracted, there is a moment reduction in respect to the airplane datum. !170 models, units in lb

– For 47400 lb: CG moves forward 0.2% of MAC (most critical case).

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Page 4

General Data

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

WEIGHT AND BALANCE

!175 models, units in lb

– For 50705 lb: CG moves forward 0.3% of MAC (most critical case). "

DUE TO FUEL CONSUMPTION VARIATION TEMPERATURE

AND

DENSITY

The fuel CG variation in relation to consumption is shown in the Fuel Distribution Table. The variation of fuel density with temperature has negligible effects in the airplane CG.

DUE TO FLAP MOVEMENT The movement of flaps and slats has negligible effects in the airplane CG.

AIRPLANE JACKING Refer to Chapter 7 of the Aircraft Maintenance Manual for airplane jacking procedures.

JACK POINTS LOCATION

!EMBRAER 170 models, length in British units

POINT

BALANCE ARM (inches)

A B

473.35 950.51

CENTERLINE DISTANCE (inches) 87.99 0

NOTE: The jack points balance arms refer to the Airplane Datum. "

JACK POINTS LOCATION

AOM-1502-003

!EMBRAER 175 models, length in British units

POINT

BALANCE ARM (inches)

A

506.33

CENTERLINE DISTANCE (inches) 87.99

7-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

General Data

Page 5

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

POINT

BALANCE ARM (inches)

B

1020.51

CENTERLINE DISTANCE (inches) 0

NOTE: The jack points balance arms refer to the Airplane Datum. "

A CENTER LINE

A B

EM170AOM990001.DGN

DATUM

JACK POINTS

MISCELLANEOUS FLUIDS !170 models, units in lb

FLUID ENGINE OIL [1] APU OIL [1] HYDRAULIC [2] WASTE TANK FLUID

WEIGHT (lb) 66.14 8.16 110.23 17.64

BALANCE ARM (in) 445.27 1116.14 554.68 920.08

7-10 Copyright © by Embraer. Refer to cover page for details.

Page 6

General Data

REVISION 21

AOM-1502-003

1. Engine oil density used (ref. MIL-L-7808): 8.17 lb/US Gal. 2. Hydraulic fluid density used (ref. SAE AS 1241A TYPE IV): 8.26 lb/US Gal.

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL FLUID POTABLE WATER

[1]

WEIGHT (lb) 242.50

BALANCE ARM (in) 858.27

1. Potable water is kept in a potable water tank. Tank capacity may vary between 35, 70, 90, and 110 liters. "

!175 models, units in lb

FLUID ENGINE OIL [1] APU OIL [1] HYDRAULIC [2] WASTE TANK FLUID POTABLE WATER [3]

WEIGHT (lb) 66.14 8.16 110.23 17.64 77.16

BALANCE ARM (in) 478.27 1185.19 587.68 990.08 950.00

1. Engine oil density used (ref. MIL-L-7808): 8.17 lb/US Gal. Engine oil is the oil from engine, integrated driven generator (IDG), oil lines and starter. 2. Hydraulic fluid density used (ref. SAE AS 1241A TYPE IV): 8.26lb/US Gal. 3. Potable water is kept in a potable water tank. Tank capacity may vary between 35, 70, 90, and 110 liters. "

BAGGAGE LOADING BAGGAGE WEIGHT AND LOCATION The baggage weight limits, location and the respective balance arm may be obtained from the applicable interior arrangement.

AOM-1502-003

The data shown enclosed are applicable to the airplane’s Standard Configuration. For other interior configuration options, the weight limits, location and the respective balance arm are supplied together with the “Airplane Weighing Form”, inserted in the “FINAL INSPECTION REPORT”.

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REVISION 21

General Data

Page 7

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

CARRY-ON BAGGAGE Carry-on volumes may be stowed in the overhead bins and in the wardrobe closet. There is no specific requirement for underseat carry-on volumes; however a maximum of 9.0 kg/20.0 lb is allowable, provided the volume is properly restrained to avoid sliding.

BAGGAGE COMPARTMENT Whenever possible, baggage should be distributed between both compartments, taking into account CG position. Regular baggage/volumes must be evenly distributed to prevent large displacements (length greater than one cargo compartment section) inside the baggage compartments. The use of vertical cargo nets is not required. In case of total or partial use of vertical nets in the forward or aft cargo compartments, maximum cargo compartment section weights must be observed. These weights must be observed even when the vertical cargo nets are not installed.

BAGGAGE LOADING PROCEDURES The aft tipping limit is at 56.0% CG, which corresponds to the CG of the main landing gear wheel axle position measured from airplane datum. From CG positions greater than this, tipping is expected. The minimum recommended static margin (difference between the aft tipping limit and the airplane CG) is 5%. Baggage loading and unloading procedures must be established for each Customer Configuration in order to maintain the airplane CG within the recommended static margin. In order to increase the static margin, it is recommended that the forward baggage compartment begins to be loaded before the aft baggage compartment. To avoid the occurrence of airplane tail tipping, some operational procedures may be established by the customer, such as:

– To block some forward or rear seats for ease of balancing the airplane.

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Page 8

General Data

REVISION 21

AOM-1502-003

– To have assigned seats avoiding a concentrated pax distribution. However, if it is detected a tendency of passengers concentration forward or aft, the crew shall move the passengers in order to allow for a better distribution along the cabin.

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

– To distribute the baggage at the forward and aft baggage compartments in the most convenient way to guarantee the best possible CG. The above recommendations (among other procedures) can be implemented by the Customer, in order to guarantee that the weight and CG of the airplane will be always inside the Weight x CG Envelope. !170 models, units in lb

Example of calculation and establishment of procedures for baggage loading for the EMBRAER 170 Standard Configuration: For calculation purposes, it was considered: – A typical BOW as follows: Pilot and Copilot; 2 Flight Attendant; Full Catering; Navigation kit; Toilet Chemical Fluids; Potable Water; Hydraulic Fluid; APU and Engine Oil; Unusable Fuel. – Half of total passengers (36 passengers) on board in the most rear of the airplane; – Airplane not refueled. Example Table: Critical Rear CG on the Ground:

Items

Occupied Pax Seat

Arm (in)

Moment (in.lb)

CG (m)

% MAC

BOW

-

46385.205

24958360

538.071

23.22

-

0.000

0.000

46385.205

24958360

538.067

23.22

PAX

72, 71, 70, 69

740.753

807.599

47125.957

25556591

542.304

26.60

PAX

68, 67, 66, 65

740.753

775.591

47866.709

26131112

545.914

29.47

PAX

64, 63, 62, 61

740.753

743.583

48607.462

26681923

548.926

31.86

PAX

60, 59, 58, 57

740.753

711.575

49348.214

27209024

551.368

33.81

740.753

679.567

50088.966

27712415

553.264

35.31

740.753

647.599

50829.719

28192125

554.639

36.41

PAX

56, 55, 54, 53 52, 51, 50, 49

46385.205 538.071

Total Weight (lb)

FUEL

PAX

AOM-1502-003

Weight (lb)

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REVISION 21

General Data

Page 9

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

Items

Occupied Pax Seat

Weight (lb)

Arm (in)

Total Weight (lb)

Moment (in.lb)

CG (m)

% MAC

PAX

48, 47, 46, 45

740.753

615.591

51570.471

28648125

555.514

37.10

740.753

583.583

52311.223

29080416

555.912

37.42

PAX

44, 43, 42, 41

PAX

40, 39, 38, 37

740.753

551.575

53051.976

29488996

555.851

37.37

FWD BAGG COMP.

-

0.000

304.725

53051.976

29488996

555.851

37.37

AFT BAGG COMP.

-

2270.759

729.528

55322.734

31145578

562.980

43.04

The results represents a Static Margin of 13% MAC, larger than the minimum recommended, that is 5%, for the criteria adopted and full baggage in the rear baggage compartment. " !175 models, units in lb

Example of calculation and establishment of procedures for baggage loading for the EMBRAER 175 Standard Configuration: For calculation purposes, it was considered: – A typical BOW as follows: Pilot and Copilot; 2 Flight Attendant; Full Catering; Navigation kit; Toilet Chemical Fluids; Potable Water; Hydraulic Fluid; APU and Engine Oil; Unusable Fuel. – Half of total passengers (40 passengers) on board in the most rear of the airplane; – Airplane not refueled.

Weight

Pax Seat

(lb)

BOW

-

47663.88

572.331

47663.88 27279575

572.323

24.23

FUEL

-

0.00

0.000

47663.88 27279575

572.332

24.23

Arm (in)

(lb)

Moment (in.lb)

CG (in)

% MAC

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Page 10

General Data

REVISION 21

AOM-1502-003

Total Weight

Occupied

Items

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

Items

Occupied Pax Seat

Weight (lb)

Arm (in)

PAX

80, 79, 78, 77

740.753

882.087

740.753

PAX

76, 75, 74, 73

Total Weight (lb)

Moment (in.lb)

CG (in)

% MAC

48404.64 27932983

577.072

28.01

850.079

49145.39 28562681

581.187

31.28

PAX

72, 71, 70, 69

740.753

818.071

49886.14 29168669

584.705

34.08

PAX

68, 67, 66, 65

740.753

786.103

50626.89 29750977

587.652

36.42

PAX

64, 63, 62, 61

740.753

754.095

51367.65 30309574

590.052

38.33

PAX

60, 59, 58, 57

740.753

722.087

52108.40 30844462

591.929

39.82

740.753

690.079

52849.15 31355639

593.305

40.92

PAX

56, 55, 54, 53

PAX

52, 51, 50, 49

740.753

658.071

53589.90 31843107

594.200

41.63

PAX

48, 47, 46, 45

740.753

626.103

54330.66 32306894

594.635

41.98

PAX

44, 43, 42, 41

740.753

594.095

55071.41 32746971

594.627

41.97

FWD BAGG COMP.

-

0.00

304.685

55071.41 32306894

594.627

41.97

AFT BAGG COMP.

-

2535.31

762.402

57606.72 34239822

602.011

47.84

The results represents a Static Margin of 8% MAC, larger than the minimum recommended, that is 5%, for the criteria adopted and full baggage in the rear baggage compartment.

AOM-1502-003

"

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REVISION 21

General Data

Page 11

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

FUEL DATA FUEL QUANTITIES !170 models, units in lb

FUEL CATEGORY UNUSABLE UNDRAINABLE UNUSABLE DRAINABLE TOTAL UNUSABLE USABLE

VOLUME (US Gal)

WEIGHT (lb)

CG BALANCE ARM (in)

5.00

33.07

525.59

17.00

116.84

518.11

22.00 3072.00

150.00 20786.00

519.68 527.28

The values specified above have been determined for an adopted fuel density of 6.767 lb/US Gal. "

FUEL QUANTITIES !175 models, units in lb

FUEL CATEGORY UNUSABLE UNDRAINABLE UNUSABLE DRAINABLE TOTAL UNUSABLE USABLE

VOLUME (US Gal)

WEIGHT (lb)

CG BALANCE ARM (in)

5.00

33.07

558.58

17.00

116.84

551.10

22.00 3072.00

149.91 20786.00

552.68 560.27

The values specified above have been determined for an adopted fuel density of 6.767 lb/US Gal.

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Page 12

General Data

REVISION 21

AOM-1502-003

"

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

PASSENGERS PASSENGER LOCATION The passenger location and respective balance arm are shown in the applicable interior arrangement.

PASSENGER WEIGHT According to AC 120-27E, the standard average passenger weights include 5 pounds (2.3 kg) for summer clothing, 10 pounds (4.5 kg) for winter clothing and a 16 pounds (7.3 kg) allowance for personal and carry-on bags. Where no gender is given, the standard average passenger weights are based on the assumption that 50 percent of passengers are male and 50 percent of passengers are female. An operator that chooses to use standard average weights for checked bags should use a standard average weight of at least 30 pounds (13.6 kg).

Adult Passenger Male Female Children (age 2-12)

Summer Operation 190 lb (86 kg) 200 lb (91 kg) 179 lb (81 kg) 82 lb (37 kg)

Winter Operation 195 lb (88 kg) 205 lb (93 kg) 184 lb (83 kg) 87 lb (39 kg)

AOM-1502-003

Children under age of 2 has been factored into the standard average and segmented adult passenger weights. Children 13 years or older should be treated as adult passengers for purposes of standard average weights.

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REVISION 21

General Data

Page 13

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

FLIGHT CREW ITEMS FLIGHT CREW ITEMS WEIGHT AND BALANCE ARM !170 models, units in lb

ITEM CAPTAIN [1] FIRST OFFICER [1] OBSERVER [1] FWD ATTENDANT [1] AFT ATTENDANT [1] CREW BAGGAGE (cargo compartment) NAVIGATION KIT

WEIGHT (lb) 190 190 190 180 180

BALANCE ARM (in) 110.63 110.63 137.80 194.49 860.23

33

232.28

22

138.58

1. Occupant balance arm. "

FLIGHT CREW ITEMS WEIGHT AND BALANCE ARM !175 models, units in lb

ITEM CAPTAIN [1] FIRST OFFICER [1] OBSERVER [1] FWD ATTENDANT [1] AFT ATTENDANT [1] CREW BAGGAGE (cargo compartment) NAVIGATION KIT

WEIGHT (lb) 190 190 190 180 180

BALANCE ARM (in) 110.63 110.63 137.80 194.49 930.24

33

232.28

22

138.58

1. Occupant balance arm.

NOTE: – The adopted flight crew items are in accordance with the approved average weight, not including the respective carry-on baggage.

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Page 14

General Data

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

WEIGHT AND BALANCE

AOM-1502-003

– The crew members and attendant weights presented herein refer to male. For female crew members and attendants, a weight equal to 160 lb may be adopted (FAA AC 120-27E). – Crew baggage location is considered at the forward cargo compartment.

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REVISION 21

General Data

Page 15

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

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Page 16

General Data

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

WEIGHT AND BALANCE

INDEX SYSTEM Moment, per definition, is weight multiplied by the distance to a reference point. If the moment of the airplane and of the items loaded on it is computed in reference to the aircraft datum, very long numeric expressions would result. As the operational usage of long numeric expressions may result in safety problems (since personnel may get confused with the long numbers), airlines usually adopt an Index System for weight and balance purposes. The Index System is just a convention for presenting airplane or body moments on a different measuring system. When using the Index System, short numeric expressions result. The Index System formula is presented below: I

=

Wx(Arm-A) B

+

C

where: I W Arm A

= = = =

B

=

C

=

Index. Aircraft or body weight Arm or body center of gravity. Reference arm. Selected arm around which all index values are calculated. On the balance chart CG envelope, the reference arm CG% line is the only vertical CG% line. [1] Constant used as a denominator to convert moment values into index values. On the balance chart CG envelope, B controls the CG% lines splay (splay decreases with increasing B). [1] Constant used as a plus value to avoid negative index figures. It is only used when computing the aircraft operating empty weight Index (OEI), and is not used when computing individual bodies index influence. On the balance chart CG envelope, the reference arm CG% vertical line is at C index units. [1]

AOM-1502-003

1. Values for A, B and C may be chosen at the operator discretion. Embraer recommended Index System Formulas is:

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REVISION 18

Index System

Page 1

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

!EMBRAER 170 models, mass units in lb, length in British units

I

=

Wx(Arm-530) 30380

+

50 "

!175 models, units in lb

I

=

Wx(Arm-567) 30500

+

60 "

INDEX INFLUENCE Index influence is the variation of index when a body is loaded or unloaded from the airplane. It is usually referred in index units per mass units for variable weight bodies (cargo, catering, etc.), index units per passenger when computing passenger influence or index units for fixed weight bodies (flight attendant, cockpit observer, etc.). The following tables show the index influence for various items: !EMBRAER 170 models, mass units in lb, length in British units

INDEX INFLUENCE Item Forward cargo Aft cargo Forward Galley G1 Forward Galley G2 Aft Galley G3 Wardrobe Fwd Flight Attendant Aft Flight Attendant Cockpit Observer

Arm (in) 304.7 729.5 156.3 218.3 890.2 242.5 194.5 860.2 137.8

Reference Weight (lb) 1 1 1 1 1 1 180 180 190

Index Influence -0.0074 IU/lb +0.0065 IU/lb -0.0123 IU/lb -0.0103 IU/lb +0.0118 IU/lb -0.0094 IU/lb -1.9879 IU +1.9566 IU -2.4529 IU

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Page 2

Index System

REVISION 18

AOM-1502-003

NOTE: The galley, wardrobe and cargo compartment arms are for the standard configuration. Check the airplane actual configuration arms in AOM Loading Section.

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL Example:

I

Computation of cargo index influence for the EMBRAER 170. The EMBRAER 170 forward cargo compartment centroid is located 304.72 in from the airplane datum. The index influence per lb is: 1x (304.72 – 530) 30380

=

=

–0.0074

IU

So, for each lb of cargo loaded in the cargo compartment, the index decreases by 0.0074 index units. " !175 models, units in lb

INDEX INFLUENCE Item Forward cargo Aft cargo Forward Galley G1 Forward Galley G2 Aft Galley G3 Wardrobe Fwd Flight Attendant Aft Flight Attendant Cockpit Observer

Arm (in) 324.53 781.89 156.3 218.3 960.19 242.01 194.49 923.34 137.80

Reference Weight (lb) 1 1 1 1 1 1 180 180 190

Index Influence -0.0079 IU/lb +0.0070 IU/lb -0.0135 IU/lb -0.0114 IU/lb +0.0129 IU/lb -0.0107 IU/lb -2.1984 IU +2.1030 IU -2.6688 IU

NOTE: The galley, wardrobe and cargo compartment arms are for the standard configuration. Check the airplane actual configuration arms in AOM Loading Section.

AOM-1502-003

Example:

Computation of cargo index influence for the EMBRAER 175. The EMBRAER 175 forward cargo compartment centroid is located 324.53 in from the airplane datum. The index influence per lb is:

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REVISION 18

Index System

Page 3

WEIGHT AND BALANCE

I

=

AIRPLANE OPERATIONS MANUAL

1x (324.53– 567) 30500

=

–0.0080

IU

So, for each lb of cargo loaded in the cargo compartment, the index decreases by 0.0080 index units. "

FUEL INDEX VARIATION EMBRAER 170 ALL MODELS !EMBRAER 170 models, mass units in lb, length in British units

WEIGHT [1] (lb) 338 677 1015 1353 1692 2030 2368 2707 3045 3384 3722 4060 4399 4737 5075 5075 5752 6090 6429 6767 7105 7444

ARM (in) 509.25 507.40 506.14 505.51 505.16 504.96 504.88 504.84 504.84 504.88 504.92 505.00 505.12 505.24 505.35 505.47 505.63 505.79 505.94 506.10 506.26 506.46

Index (IU) –0.23 –0.50 –0.80 –1.09 –1.38 –1.67 –1.96 –2.24 –2.52 –2.80 –3.07 –3.34 –3.60 –3.86 –4.12 –4.37 –4.61 –4.85 –5.09 –5.32 –5.55 –5.77

1. The weights above have been determined for an adopted fuel density of 6.767 lb/US Gal.

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Page 4

Index System

REVISION 18

AOM-1502-003

VOLUME (US Gal) 50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800 850 900 950 1000 1050 1100

AIRPLANE OPERATIONS MANUAL

AOM-1502-003

VOLUME (US Gal) 1150 1200 1250 1300 1350 1400 1450 1500 1550 1600 1650 1700 1750 1800 1850 1900 1950 2000 2050 2100 2150 2200 2250 2300 2350 2400 2450 2500 2550 2600 2650

WEIGHT [1] (lb) 7782 8120 8459 8797 9135 9474 9812 10151 10489 10827 11166 11504 11842 12181 12519 12857 13196 13534 13872 14211 14549 14887 15226 15564 15902 16241 16579 16918 17256 17594 17933

ARM (in) 506.65 506.81 507.01 507.20 507.36 507.56 507.76 507.95 508.15 508.35 508.58 508.78 509.02 509.21 509.41 509.61 509.84 510.04 510.28 510.47 510.75 511.06 511.50 512.01 512.60 513.27 513.98 514.72 515.59 516.46 517.36

WEIGHT AND BALANCE

Index (IU) –5.98 –6.20 –6.40 –6.60 –6.81 –7.00 –7.18 –7.37 –7.54 –7.72 –7.87 –8.04 –8.18 –8.33 –8.49 –8.63 –8.76 –8.89 –9.01 –9.13 –9.22 –9.28 –9.27 –9.22 –9.11 –8.95 –8.75 –8.51 –8.18 –7.84 –7.46

1. The weights above have been determined for an adopted fuel density of 6.767 lb/US Gal.

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REVISION 18

Index System

Page 5

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

WEIGHT [1] (lb) 18271 18609 18948 19286 19624 19963 20301 20639 20781

VOLUME (US Gal) 2700 2750 2800 2850 2900 2950 3000 3050 3071

ARM (in) 518.31 519.33 520.39 521.53 522.72 523.98 525.28 526.69 527.28

Index (IU) –7.03 –6.54 –5.99 –5.37 –4.71 –3.96 –3.16 –2.25 –1.86

1. The weights above have been determined for an adopted fuel density of 6.767 lb/US Gal. "

EMBRAER 175 ALL MODELS !175 models, units in lb

WEIGHT [1] (lb) 338 677 1015 1353 1692 2030 2368 2707 3045 3384 3722 4060 4399 4737

ARM (in) 542.24 540.39 539.13 538.50 538.19 537.95 537.87 537.83 537.83 537.87 537.91 538.03 538.11 538.23

Index (IU) -0.28 -0.59 -0.93 -1.27 -1.60 -1.94 -2.27 -2.60 -2.92 -3.24 -3.56 -3.87 -4.18 -4.48

1. The weights above have been determined for an adopted fuel density of 6.767 lb/US Gal.

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Page 6

Index System

REVISION 18

AOM-1502-003

VOLUME (US Gal) 50 100 150 200 250 300 350 400 450 500 550 600 650 700

AIRPLANE OPERATIONS MANUAL

AOM-1502-003

VOLUME (US Gal) 750 800 850 900 950 1000 1050 1100 1150 1200 1250 1300 1350 1400 1450 1500 1550 1600 1650 1700 1750 1800 1850 1900 1950 2000 2050 2100 2150 2200 2250

WEIGHT [1] (lb) 5075 5414 5752 6090 6429 6767 7105 7444 7782 8120 8459 8797 9135 9474 9812 10151 10489 10827 11166 11504 11842 12181 12519 12857 13196 13534 13872 14211 14549 14887 15226

ARM (in) 538.35 538.46 538.62 538.78 538.94 539.13 539.29 539.45 539.64 539.80 540.00 540.20 540.39 540.59 540.79 540.94 541.18 541.34 541.57 541.81 541.97 542.20 542.40 542.60 542.79 543.03 543.27 543.46 543.74 544.09 544.49

WEIGHT AND BALANCE

Index (IU) -4.78 -5.08 -5.37 -5.65 -5.93 -6.20 -6.48 -6.75 -7.00 -7.27 -7.51 -7.76 -8.00 -8.23 -8.46 -8.70 -8.91 -9.14 -9.34 -9.53 -9.75 -9.94 -10.13 -10.32 -10.51 -10.67 -10.83 -11.00 -11.13 -11.22 -11.27

1. The weights above have been determined for an adopted fuel density of 6.767 lb/US Gal.

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REVISION 18

Index System

Page 7

WEIGHT AND BALANCE

VOLUME (US Gal) 2300 2350 2400 2450 2500 2550 2600 2650 2700 2750 2800 2850 2900 2950 3000 3050 3071

AIRPLANE OPERATIONS MANUAL

WEIGHT [1] (lb) 15564 15902 16241 16579 16918 17256 17594 17933 18271 18609 18948 19286 19624 19963 20301 20639 20785

ARM (in) 545.04 545.63 546.26 546.97 547.75 548.58 549.49 550.39 551.34 552.36 553.46 554.57 555.79 557.01 558.35 559.72 560.27

Index (IU) -11.24 -11.18 -11.08 -10.92 -10.71 -10.46 -10.13 -9.80 -9.41 -8.96 -8.44 -7.89 -7.24 -6.56 -5.78 -4.94 -4.60

1. The weights above have been determined for an adopted fuel density of 6.767 lb/US Gal.

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Page 8

Index System

REVISION 18

AOM-1502-003

"

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

OEW/OEI DETERMINATION The OEW (Operational Empty Weight) is the BEW plus the weight of the operational items (crew, catering, lavatory fluid, etc.). The OEI (Operational Empty Index) is the index for the OEW. In order to determine the OEW and OEI, it is necessary to add to the BEW all the weight and moment variations referent to the operational items. The BEW is obtained from the aircraft weighting record. !EMBRAER 170 models, mass units in lb, length in British units

Example: Computation of OEW/OEI for the EMBRAER 170. For a BEW equal 45044.20 lb and BEW moment equal 2435022.00 lb.in: Item BEW Captain and First Officer Fwd flight attendant Aft flight attendant Waste Tank Fluid Potable Water Flight kit Crew baggage Catering galley G1 Catering galley G3 OEW

Weight (lb) 45044.20

Arm (in) 540.59

Moment (lb.in) 24350220.00

380.00

110.63

42039.29

180.00

194.49

35007.80

180.00

860.23

154842.21

17.64 242.50 22.00 33.00

920.08 858.27 138.58 232.28

16227.11 208133.29 3048.81 7665.34

176.37

156.31

27567.33

564.37

890.16

502380.64

46840.08

541.14

25347131.23

AOM-1502-003

NOTE: – BEW computation considers APU oil, engine oil, hydraulic fluid and unusable fuel. – Potable water is stored in a potable water tank. Tank capacity may vary between 35, 70, 90 and 110 liters. The OEW calculated in this example takes into account potable water tank’s maximum capacity.

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REVISION 18

Index System

Page 9

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

– Catering weight was considered above, but its weight is not constant. Use the airplane actual internal configuration for galleys location. – The values above are an example. Use the airplane actual BEW for determining the OEW. Aircraft arm Aircraft index

= =

25347131.23/46840.08

=

46840.08 . (541.14 –530) 30380

+

541.14 in 50

=

66 IU "

!175 models, units in lb

Example: Computation of OEW/OEI for the EMBRAER 175. For a BEW equal 26186643.83 lb.in: Item BEW Captain and First Officer Fwd flight attendant Aft flight attendant Waste Tank Fluid Potable Water Flight kit Crew baggage Catering galley G1 Catering galley G3 OEW

45626.10

lb

and

BEW

moment

equal

Weight (lb) 45626.10

Arm (in) 573.94

Moment (lb.in) 26186643.83

360.00

110.63

39826.8

180.00

198.54

35737.20

180.00

923.34

166201.20

35.27 242.50 22.00 33.00

508.86 950.00 138.58 232.28

17947.49 230375.00 3048.76 7665.24

176.37

156.31

27567.33

564.37

960.19

541902.43

47419.61

574.81

27256916.35

7-15 Copyright © by Embraer. Refer to cover page for details.

Page 10

Index System

REVISION 18

AOM-1502-003

NOTE: – BEW computation considers APU oil, engine oil, hydraulic fluid and unusable fuel.

AIRPLANE OPERATIONS MANUAL

WEIGHT AND BALANCE

– Potable water is stored in a potable water tank. Tank capacity may vary between 35, 70, 90 and 110 liters. The OEW calculated in this example takes into account potable water tank’s maximum capacity. – Catering weight was considered above, but its weight is not constant. Use the airplane actual internal configuration for galleys location. – The values above are an example. Use the airplane actual BEW for determining the OEW. Aircraft arm Aircraft index

=

=

27256916.35/47419.61 47419.61 . (574.81 –567) 30400

= + 60

574.81 in =

71 IU

AOM-1502-003

"

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REVISION 18

Index System

Page 11

WEIGHT AND BALANCE

AIRPLANE OPERATIONS MANUAL

7-15 Copyright © by Embraer. Refer to cover page for details.

Page 12

Index System

REVISION 18

AOM-1502-003

INTENTIONALLY BLANK

LOADING

AIRPLANE OPERATIONS MANUAL

SECTION 8 LOADING TABLE OF CONTENTS Block

Page

Introduction.......................................................... 8-INTRO ....

1

External Dimensions............................................ 8-10 ........... EXTERNAL DIMENSIONS..................................... 8-10 ........... GROUND CLEARANCES...................................... 8-10 ........... DOOR CLEARANCES........................................... 8-10 ...........

1 1 4 8

Cabin Cross Section............................................ 8-20 ........... FIRST CLASS CROSS SECTION......................... 8-20 ........... STANDARD CABIN CROSS SECTION................ 8-20 ...........

1 1 2

Interior Arrangement............................................ 8-30 ........... INTERIOR ARRANGEMENTS............................... 8-30 ...........

1 1

Overhead Bin........................................................ 8-40 ........... CARRY-ON BAGGAGE......................................... 8-40 ........... OVERHEAD BINS.................................................. 8-40 ........... OVERHEAD BINS CAPACITY AND LENGTH...... 8-40 ...........

1 1 1 1

Cargo Compartment Door................................... 8-50 ........... CARGO DOORS.................................................... 8-50 ........... CARGO DOOR OPENING.................................... 8-50 ........... CARGO DOOR CLOSING..................................... 8-50 ...........

1 1 2 3

AOM-1502-003

Cargo Compartment............................................ 8-60 ........... 1 CARGO COMPARTMENT..................................... 8-60 ........... 1 DIMENSIONS AND LIMITS................................... 8-60 ........... 2 BAGGAGE AND CARGO LOADING..................... 8-60 ........... 9 PACKAGE SIZE TABLES...................................... 8-60 ........... 24 Cargo Nets............................................................ 8-70 ........... 1 CARGO NETS....................................................... 8-70 ........... 1 VERTICAL NETS AND SECTION LOADING DISTRIBUTION................................................ 8-70 ........... 10

8-TOC Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Table of Contents

Page 1

LOADING

AIRPLANE OPERATIONS MANUAL

Magnetized Material Transportation................... 8-85 ........... MAGNETIZED MATERIAL TRANSPORTATION. . . 8-85 ...........

1 1

Dry Ice................................................................... 8-90 ........... DRY ICE TRANSPORTATION............................... 8-90 ...........

1 1

8-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 20

AOM-1502-003

Block Page Live Animals......................................................... 8-80 ........... 1 LIVE ANIMALS TRANSPORTATION..................... 8-80 ........... 1

AIRPLANE OPERATIONS MANUAL

LOADING

INTRODUCTION

AOM-1502-003

This Section contains airplane dimensions, interior arrangement data for loading purposes and loading capacity information in the passenger cabin and cargo compartment.

8-INTRO Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Page 1

LOADING

AIRPLANE OPERATIONS MANUAL

8-INTRO Copyright © by Embraer. Refer to cover page for details.

Page 2

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

LOADING

AIRPLANE OPERATIONS MANUAL

EXTERNAL DIMENSIONS !EMBRAER 170 Models

9.85 m (32 ft 3 in.)

10.60 m (34 ft 9 in.)

29.90 m (98 ft 1 in.)

AOM-1502-003

5.20 m (17 ft) 26.00 m (85 ft 4 in.)

EM170AOM140001A.DGN

10.00 m (32 ft 9 in.)

"

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REVISION 20

External Dimensions

Page 1

LOADING

AIRPLANE OPERATIONS MANUAL

!EMBRAER 175 Models with wing tip

9.86 m (32 ft 4 in)

11.41 m (37 ft 5 in) 31.68 m (103 ft 11 in)

5.20 m (17 ft 1 in) 26.00 m (85 ft 4 in)

EM170AOM140500B.DGN

10.00 m (32 ft 10 in)

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External Dimensions

REVISION 20

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

LOADING

!EMBRAER 175 Models with enhanced wing tip or POST-MOD SB-170-57-0058

9.86 m (32 ft 4 in)

11.41 m (37 ft 5 in) 31.68 m (103 ft 11 in)

4.88 m (15 ft 12 in)

5.20 m (17 ft 1 in) 28.65 m (93 ft 11 in)

EM170AOM141336B.DGN

10.00 m (32 ft 10 in)

AOM-1502-003

"

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REVISION 20

External Dimensions

Page 3

LOADING

AIRPLANE OPERATIONS MANUAL

GROUND CLEARANCES !EMBRAER 170 Models

FUSELAGE ANGLE (HORIZ. REF.)

VERTICAL TAIL

TAIL SKID ANGULAR CLEARANCE

NOSE FORWARD CARGO DOOR

AFT CARGO DOOR

FORWARD PASSENGER DOOR

AFTER SERVICE DOOR AFT PASSENGER DOOR

NACELLE

"

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External Dimensions

REVISION 20

AOM-1502-003

WINGLET

EM170AOM080001B.DGN

FORWARD SERVICE DOOR

LOADING

AIRPLANE OPERATIONS MANUAL VERTICAL GROUND CLEARANCES TABLE !EMBRAER 170 models, length units in meter, feet and inch

VERTICAL CLEARANCE Aft Cargo Door Aft Passenger Door Aft Service Door Forward Cargo Door Forward Passenger Door Forward Service Door Fuselage Angle Nacelle Nose Tailskid Angular Clearance Vertical Tail Winglet

MINIMUM

MAXIMUM

1.44 m (4 ft 9 in) 2.40 m (7 ft 10 in) 2.40 m (7 ft 10 in) 1.47 m (4 ft 10 in) 2.54 m (8 ft 4 in) 2.54 m (8 ft 4 in) 0° 0.48 m (1 ft 6 in) 2.13 m (7 ft)

1.60 m (5 ft 3 in) 2.59 m (8 ft 6 in) 2.59 m (8 ft 6 in) 1.56 m (5 ft 1 in) 2.63 m (8 ft 7 in) 2.64 m (8 ft 8 in) 0.6° 0.57 m (1 ft 10 in) 2.24 m (7 ft 5 in)

12.3°

13.4°

9.56 m (31 ft 4 in) 4.47 m (14 ft 8 in)

9.83 m (32 ft 3 in) 4.62 m (15 ft 2 in)

AOM-1502-003

"

8-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

External Dimensions

Page 5

LOADING

AIRPLANE OPERATIONS MANUAL

!EMBRAER 175 Models

FUSELAGE ANGLE (HORIZ. REF.)

VERTICAL TAIL

TAIL SKID ANGULAR CLEARANCE

NOSE FORWARD CARGO DOOR

AFT SERVICE DOOR

AFT CARGO DOOR

AFT PASSENGER DOOR

FORWARD PASSENGER DOOR

WINGLET

NACELLE

EM170AOM080024C.DGN

FORWARD SERVICE DOOR

8-10 Copyright © by Embraer. Refer to cover page for details.

Page 6

External Dimensions

REVISION 20

AOM-1502-003

"

LOADING

AIRPLANE OPERATIONS MANUAL VERTICAL GROUND CLEARANCES TABLE !EMBRAER 175 Models

VERTICAL CLEARANCE Aft Cargo Door Aft Passenger Door Aft Service Door Forward Cargo Door Forward Passenger Door Forward Service Door Fuselage Angle Nacelle Nose Tailskid Angular Clearance Vertical Tail Winglet

MINIMUM

MAXIMUM

1.41 m (4 ft 8 in) 2.37 m (7 ft 9 in) 2.37 m (7 ft 9 in) 1.46 m (4 ft 9 in) 2.54 m (8 ft 4 in) 2.54 m (8 ft 4 in) 0° 0.46 m (1 ft 6 in) 2.14 m (7 ft)

1.58 m (5 ft 2 in) 2.56 m (8 ft 5 in) 2.56 m (8 ft 5 in) 1.56 m (5 ft 1 in) 2.64 m (8 ft 8 in) 2.65 m (8 ft 8 in) 0.6° 0.56 m (1 ft 10 in) 2.25 m (7 ft 5 in)

11.4°

12.4°

9.53 m (31 ft 3 in) 4.44 m (14 ft 7 in)

9.80 m (32 ft 2 in) 4.60 m (15 ft 1 in)

AOM-1502-003

"

8-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

External Dimensions

Page 7

LOADING

AIRPLANE OPERATIONS MANUAL

DOOR CLEARANCES

1.71 m (5 ft 7.3 in.) 1.37 m (4 ft 5.9 in.)

0.90 m (2 ft 11.4 in.)

0.61 m (2 ft 0 in.)

1.10 m (3 ft 7.3 in.)

0.78 m (2 ft 6.7 in.)

0.87 m (2 ft 10 in.)

0.99 m (3 ft 3 in.)

0.76 m (2 ft 5.9 in.)

0.63 m (2 ft 0.8 in)

0.66 m (2 ft 1.9 in.)

8-10 Copyright © by Embraer. Refer to cover page for details.

Page 8

External Dimensions

REVISION 20

AOM-1502-003

1.82 m (5 ft 11.6 in.)

EM170AOM080004A.DGN

1.36 m (4 ft 5.5 in.)

LOADING

AIRPLANE OPERATIONS MANUAL

FIRST CLASS CROSS SECTION !Airplanes with first-class passenger seats

0.86 m (3 ft)

0.6 m (1 ft 10 in.) 0.20 m (8 in.)

0.51 m (1 ft 8 in.)

0.69 m (2 ft 3 in.)

0.07 m (3 in.)

1.44 m (4 ft 9 in.)

1.1 m (3 ft 8 in.)

2.6 m (8 ft 5 in.) 3.01 m (9 ft 11 in.)

EM170AOM080002.DGN

0.61 m (2 ft)

FIRST CLASS CROSS SECTION DIMENSIONS

AOM-1502-003

"

8-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 12

Cabin Cross Section

Page 1

LOADING

AIRPLANE OPERATIONS MANUAL

STANDARD CABIN CROSS SECTION 0.78 m (2 ft 7 in.)

0.46 m

0.05 m (2.0 in.)

(1 ft 6 in.)

2.00 m (6 ft 7 in.)

1.44 m (4 ft 9 in.) 3.35 m (11 ft 0 in.)

0.49 m (1 ft 7 in.)

EM170AOM080003.DGN

0.94 m (3 ft 1 in.)

2.74 m (9 ft) 3.01 m (9 ft 11 in.)

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Page 2

Cabin Cross Section

REVISION 12

AOM-1502-003

STANDARD CABIN CROSS SECTION DIMENSIONS

LOADING

AIRPLANE OPERATIONS MANUAL

INTERIOR ARRANGEMENTS !EMBRAER 170 U S AIRWAYS Configuration

G F H

H

PITCH 32 in

A. B. C. D. E. F. G. H.

WARDROBE FWD GALLEY G1 FWD LAVATORY FLIGHT ATTENDANT SEAT DIVIDER AFT GALLEY G3 AFT LAVATORY AFT BULKHEAD

72 SEATS PITCH 33 in

E D

A

C

AOM-1502-003

EM170AOM080014A.DGN

B

72 PAX

8-30

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REVISION 21

Interior Arrangement

Page 1

LOADING

AIRPLANE OPERATIONS MANUAL PASSENGER BALANCE ARM

!EMBRAER 170 U S AIRWAYS Configuration

SEATS ROW 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18

PASSENGER SEATS 1A, 1B, 2A, 2B, 3A, 3B, 4A, 4B, 5A, 5B, 6A, 6B, 7A, 7B, 8A, 8B, 9A, 9B, 10A, 10B, 11A, 11B, 12A, 12B, 13A, 13B, 14A, 14B, 15A, 15B, 16A, 16B, 17A, 17B, 18A, 18B,

1C, 1D 2C, 2D 3C, 3D 4C, 4D 5C, 5D 6C, 6D 7C, 7D 8C, 8D 9C, 9D 10C, 10D 11C, 11D 12C, 12D 13C, 13D 14C, 14D 15C, 15D 16C, 16D 17C, 17D 18C, 18D

PAX BALANCE ARM (m) (in) 6.515 256.5 7.353 289.5 8.191 322.5 9.03 355.5 9.868 388.5 10.706 421.5 11.544 454.5 12.382 487.5 13.195 519.5 14.008 551.5 14.821 583.5 15.634 615.5 16.446 647.5 17.259 679.5 18.072 711.5 18.885 743.5 19.698 775.5 20.510 807.5

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Interior Arrangement

REVISION 21

AOM-1502-003

"

LOADING

AIRPLANE OPERATIONS MANUAL FURNISHINGS AND EQUIPMENT BALANCE ARM !EMBRAER 170 U S AIRWAYS Configuration

Balance Arm FWD Galley (G1) FWD Lavatory FWD Flight Attendant Seat Wardrobe FWD Divider Aft Bulkhead Aft Flight Attendant Seat Aft Galley (G3) Aft Lavatory

(m) 3.970 4.220 4.940 5.370 5.690 21.090 21.850 22.610 22.610

(in) 156.3 166.1 194.5 211.4 224.0 830.3 860.2 890.2 890.2

AOM-1502-003

"

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REVISION 21

Interior Arrangement

Page 3

LOADING

AIRPLANE OPERATIONS MANUAL

!EMBRAER 170 U S AIRWAYS Configuration AFT GALLEY G3

AFT LAVATORY

AFT FLT ATTENDANT SEAT (CC2)

AFT BULKHEAD RH

AFT BULKHEAD LH

WINDSCREEN WARDROBE FWD FLT ATTENDANT SEAT (CC1)

OBSERVER SEAT PILOTS SEATS

EM170AOM080095A.DGN

FWD LAVATORY FWD GALLEY G1

"

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Interior Arrangement

REVISION 21

AOM-1502-003

76 PAX

AIRPLANE OPERATIONS MANUAL

LOADING

PASSENGER BALANCE ARM !EMBRAER 170 U S AIRWAYS Configuration

SEATS ROW 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19

PASSENGER SEATS A1, C1, A2, C2, A3, C3, A4, C4, A5, C5, A6, C6, A7, C7, A8, C8, A9, C9, A10, C10, A11, C11, A12, C12, A13, C13, A14, C14, A15, C15, A16, C16, A17, C17, A18, C18, A19, C19,

D1, F1 D2, F2 D3, F3 D4, F4 D5, F5 D6, F6 D7, F7 D8, F8 D9, F9 D10, F10 D11, F11 D12, F12 D13, F13 D14, F14 D15, F15 D16, F16 D17, F17 D18, F18 D19, F19

PAX BALANCE ARM (m) (in) 6.460 254.3 7.247 285.3 8.035 316.3 8.822 347.3 9.610 378.3 10.397 409.3 11.184 440.3 11.972 471.3 12.759 502.3 13.547 533.3 14.334 564.3 15.121 595.3 15.909 626.3 16.696 657.3 17.484 688.3 18.271 719.3 19.058 750.3 19.846 781.3 20.633 812.3

AOM-1502-003

"

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REVISION 21

Interior Arrangement

Page 5

LOADING

AIRPLANE OPERATIONS MANUAL FURNISHINGS AND EQUIPMENT BALANCE ARM

!EMBRAER 170 U S AIRWAYS Configuration

Balance Arm FWD Galley (G1) FWD Lavatory FWD Flight Attendant Seat Wardrobe Windscreen LH Aft Bulkhead RH Aft Bulkhead Aft Flight Attendant Seat Aft Galley (G3) Aft Lavatory

(m) 3.970 4.220 4.940 5.370 5.690 21.090 21.090 21.850 22.610 22.610

(in) 156.3 166.1 194.5 211.4 224.0 830.3 830.3 860.2 890.2 890.2

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Interior Arrangement

REVISION 21

AOM-1502-003

"

LOADING

AIRPLANE OPERATIONS MANUAL !EMBRAER 170 DELTA Configuration

H

I

F

F

G

A: WARDROBE B: FWD GALLEY G1 C: FWD LAVATORY D: FWD FLT ATTENDANT SEAT E: WINDSCREEN F: AFT DIVIDER G: AFT FLT ATTENDANT SEAT H: AFT LAVATORY I: AFT GALLEY G3

E A D

C

EM170AOM080018B.DGN

B

AOM-1502-003

70 PAX

"

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REVISION 21

Interior Arrangement

Page 7

LOADING

AIRPLANE OPERATIONS MANUAL PASSENGER BALANCE ARM

!EMBRAER 170 DELTA Configuration

SEATS ROW 1 1 2 2

FIRST CLASS PAX SEATS PAX BALANCE ARM PASSENGER SEATS (m) (in) 1A 6.511 256.3 1D, 1F 6.384 251.3 2A 7.425 292.3 2D, 2F 7.298 287.3 "

PASSENGER BALANCE ARM !EMBRAER 170 DELTA Configuration

SEATS ROW 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18

ELITE PAX SEATS PAX BALANCE ARM PASSENGER SEATS (m) (in) 3A, 3C, 3D, 3F 8.441 332.3 4A, 4C, 4D, 4F 9.254 364.3 5A, 5C, 5D, 5F 10.067 396.3 6A, 6C, 6D, 6F 10.879 428.3 7A, 7C, 7D, 7F 11.692 460.3 8A, 8C, 8D, 8F 12.505 492.3 9A, 9C, 9D, 9F 13.318 524.3 10A, 10C, 10D, 10F 14.131 556.3 11A, 11C, 11D, 11F 14.943 588.3 12A, 12C, 12D, 12F 15.756 620.3 13A, 13C, 13D, 13F 16.569 652.3 14A, 14C, 14D, 14F 17.382 684.3 15A, 15C, 15D, 15F 18.195 716.3 16A, 16C, 16D, 16F 19.007 748.3 17A, 17C, 17D, 17F 19.820 780.3 18A, 18C, 18D, 18F 20.633 812.3

8-30 Copyright © by Embraer. Refer to cover page for details.

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Interior Arrangement

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

LOADING

PASSENGER BALANCE ARM !EMBRAER 170 UNITED EXPRESS Configuration

SEATS ROW 1 1 2 2

FIRST CLASS PAX SEATS PAX BALANCE ARM PASSENGER SEATS (m) (in) 1A 6.537 257.3 1D, 1F 6.460 254.3 2A 7.502 295.3 2D, 2F 7.400 291.3 "

PASSENGER BALANCE ARM !EMBRAER 170 UNITED EXPRESS Configuration

SEATS ROW 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18

ELITE PAX SEATS PAX BALANCE ARM PASSENGER SEATS (m) (in) 3A, 3C, 3D, 3F 8.594 338.3 4A, 4C, 4D, 4F 9.458 372.3 5A, 5C, 5D, 5F 10.321 406.3 6A, 6C, 6D, 6F 11.185 440.3 7A, 7C, 7D, 7F 11.972 471.3 8A, 8C, 8D, 8F 12.759 502.3 9A, 9C, 9D, 9F 13.547 533.3 10A, 10C, 10D, 10F 14.334 564.3 11A, 11C, 11D, 11F 15.122 595.3 12A, 12C, 12D, 12F 15.909 626.3 13A, 13C, 13D, 13F 16.696 657.3 14A, 14C, 14D, 14F 17.484 688.3 15A, 15C, 15D, 15F 18.271 719.3 16A, 16C, 16D, 16F 19.059 750.3 17A, 17C, 17D, 17F 19.846 781.3 18A, 18C, 18D, 18F 20.633 812.3

AOM-1502-003

"

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REVISION 21

Interior Arrangement

Page 9

LOADING

AIRPLANE OPERATIONS MANUAL FURNISHINGS AND EQUIPMENT BALANCE ARM

!EMBRAER 170 SHUTTLE AMERICA Configuration

Balance Arm FWD Galley (G1) FWD Lavatory FWD Flight Attendant Seat Wardrobe Windscreen Aft Divider Aft Flight Attendant Seat Aft Galley (G3) Aft Lavatory

(m) 3.970 4.220 4.940 5.370 5.690 21.090 21.850 22.610 22.610

(in) 156.3 166.1 194.5 211.4 224.0 830.3 860.2 890.2 890.2

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Page 10

Interior Arrangement

REVISION 21

AOM-1502-003

"

LOADING

AIRPLANE OPERATIONS MANUAL

AFT GALLEY G3

AFT LAVATORY

AFT FLT ATTENDANT SEAT (CC2)

AFT CABIN BULKHEAD

WINDSCREEN WARDROBE FWD FLT ATTENDANT SEAT (CC1)

OBSERVER SEAT PILOTS SEATS

EM170AOM080110A.DGN

FWD LAVATORY FWD GALLEY G1

AOM-1502-003

76 PAX

8-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Interior Arrangement

Page 11

LOADING

AIRPLANE OPERATIONS MANUAL PASSENGER BALANCE ARM PASSENGER SEATS A1, B1 C1, D1 A2, B2, C2, D2 A3, B3, C3, D3 A4, B4, C4, D4 A5, B5, C5, D5 A6, B6, C6, D6 A7, B7, C7, D7 A8, B8, C8, D8 A9, B9, C9, D9 A10, B10, C10, D10 A11, B11, C11, D11 A12, B12, C12, D12 A13, B13, C13, D13 A14, B14, C14, D14 A15, B15, C15, D15 A16, B16, C16, D16 A17, B17, C17, D17 A18, B18, C18, D18 A19, B19, C19, D19

PAX BALANCE ARM (m) (in) 6.460 254.3 6.485 255.3 7.247 285.3 8.035 316.3 8.822 347.3 9.610 378.3 10.397 409.3 11.184 440.3 11.972 471.3 12.759 502.3 13.547 533.3 14.334 564.3 15.121 595.3 15.909 626.3 16.696 657.3 17.484 688.3 18.271 719.3 19.058 750.3 19.846 781.3 20.633 812.3

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Interior Arrangement

REVISION 21

AOM-1502-003

SEATS ROW 1 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19

LOADING

AIRPLANE OPERATIONS MANUAL FURNISHINGS AND EQUIPMENT BALANCE ARM Balance Arm

AOM-1502-003

FWD Galley (G1) FWD Lavatory FWD Flight Attendant Seat (CC1) Wardrobe Windscreen Aft Cabin Bulkhead Aft Flight Attendant Seat (CC2) Aft Galley (G3) Aft Lavatory

(m) 3.970 4.220

(in) 156.3 166.1

4.940

194.5

5.436 5.690 21.090

214.0 224.0 830.3

21.850

860.2

22.610 22.610

890.2 890.2

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REVISION 21

Interior Arrangement

Page 13

LOADING

AIRPLANE OPERATIONS MANUAL

!EMBRAER 175 U S AIRWAYS Configuration AFT LAVATORY

AFT GALLEY G3

AFT FLT ATTENDANT SEAT (CC2)

LH AFT BULKHEAD

RH AFT BULKHEAD

WINDSCREEN LH WINDSCREEN RH

FWD FLT ATTENDANT SEAT (CC1)

FWD GALLEY G1

OBSERVER SEAT

PILOTS SEATS

EM170AOM080093A.DGN

FWD LAVATORY

"

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Interior Arrangement

REVISION 21

AOM-1502-003

86 SEATS

AIRPLANE OPERATIONS MANUAL

LOADING

PASSENGER BALANCE ARM !EMBRAER 175 U S AIRWAYS Configuration

SEATS ROW 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22

PASSENGER SEATS D1, A2, C2, A3, C3, A4, C4, A5, C5, A6, C6, A7, C7, A8, C8, A9, C9, A10, C10, A11, C11, A12, C12, A13, C13, A14, C14, A15, C15, A16, C16, A17, C17, A18, C18, A19, C19, A20, C20, A21, C21, A22, C22,

F1 D2, F2 D3, F3 D4, F4 D5, F5 D6, F6 D7, F7 D8, F8 D9, F9 D10, F10 D11, F11 D12, F12 D13, F13 D14, F14 D15, F15 D16, F16 D17, F17 D18, F18 D19, F19 D20, F20 D21, F21 D22, F22

PAX BALANCE ARM (m) (in) 5.876 231.3 6.663 262.3 7.451 293.3 8.238 324.3 9.026 355.4 9.813 386.3 10.600 417.3 11.388 448.3 12.175 479.3 12.963 510.4 13.750 541.3 14.537 572.3 15.325 603.3 16.112 634.3 16.900 665.4 17.687 696.3 18.474 727.3 19.262 758.3 20.049 789.3 20.837 820.4 21.624 851.3 22.411 882.3

AOM-1502-003

"

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REVISION 21

Interior Arrangement

Page 15

LOADING

AIRPLANE OPERATIONS MANUAL FURNISHINGS AND EQUIPMENT BALANCE ARM

!EMBRAER 175 U S AIRWAYS Configuration

Balance Arm Observer Seat FWD Galley (G1) FWD Lavatory FWD Flight Attendant Seat (CC1) RH Windscreen LH Windscreen LH Aft Bulkhead RH Aft Bulkhead LH Aft Flight Attendant Seat (CC2) Aft Galley (G3) Aft Lavatory

(m) 3.500 3.970 4.220

(in) 137.8 156.3 166.1

4.940

194.5

5.179 5.690 22.868 22.868

203.9 224.0 900.3 900.3

23.628

930.2

24.388 24.388

960.2 960.2

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Page 16

Interior Arrangement

REVISION 21

AOM-1502-003

"

LOADING

AIRPLANE OPERATIONS MANUAL !EMBRAER 175 DELTA Configuration AFT LAVATORY

GALLEY G3

AFT FLT ATTENDANT SEAT (CC2)

AFT CABIN BULKHEAD

WINDSCREEN WARDROBE FWD FLT ATTENDENT SEAT (CC1) GALLEY G1

OBSERVER SEAT

PILOTS SEATS

EM170AOM080129A.DGN

FWD LAVATORY

AOM-1502-003

76 SEATS

"

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REVISION 21

Interior Arrangement

Page 17

LOADING

AIRPLANE OPERATIONS MANUAL PASSENGER BALANCE ARM

!EMBRAER 175 DELTA Configuration

SEATS ROW 1 1 2 2 3 3 4 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

PASSENGER SEATS A1 C1, D1 A2 C2, D2 A3 C3, D3 A4 C4, D4 A5, B5, C5, D5 A6, B6, C6, D6 A7, B7, C7, D7 A8, B8, C8, D8 A9, B9, C9, D9 A10, B10, C10, D10 A11, B11, C11, D11 A12, B12, C12, D12 A13, B13, C13, D13 A14, B14, C14, D14 A15, B15, C15, D15 A16, B16, C16, D16 A17, B17, C17, D17 A18, B18, C18, D18 A19, B19, C19, D19 A20, B20, C20, D20

PAX BALANCE ARM (m) (in) 6.638 261.3 6.536 257.3 7.578 298.3 7.476 294.3 8.518 335.4 8.416 331.3 9.457 372.3 9.355 368.3 10.550 415.4 11.337 446.3 12.125 477.4 12.912 508.3 13.700 539.4 14.487 570.4 15.274 601.3 16.062 632.4 16.849 663.3 17.637 694.4 18.424 725.4 19.211 756.3 19.999 787.4 20.786 818.3 21.574 849.4 22.361 880.4

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Interior Arrangement

REVISION 21

AOM-1502-003

"

LOADING

AIRPLANE OPERATIONS MANUAL FURNISHINGS AND EQUIPMENT BALANCE ARM !EMBRAER 175 DELTA Configuration

Balance Arm PILOT SEAT OBSERVER SEAT GALLEY G1 FWD LAVATOTY FWD FLT ATTENDANT SEAT (CC1) WARDROBE AFT CABIN BULKHEAD AFT FLT ATTENDANT SEAT (CC2) AFT LAVATORY GALLEY G3

(m) 2.810 3.500 3.970 4.220

(in) 110.6 137.8 156.3 166.1

4.940

194.5

5.374 22.868

211.6 900.3

23.628

930.2

24.388 24.388

960.2 960.2

AOM-1502-003

"

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REVISION 21

Interior Arrangement

Page 19

LOADING

AIRPLANE OPERATIONS MANUAL

!EMBRAER 175 AMERICAN EAGLE Configuration AFT LAVATORY

GALLEY G3

AFT FLT ATTENDANT SEAT (CC2)

AFT FLT ATTENDANT SEAT (CC3)

WINDSCREEN

WINDSCREEN WARDROBE FWD FLT ATTENDENT SEAT (CC1) GALLEY G1

OBSERVER SEAT

PILOTS SEATS

EM170AOM110570A.DGN

FWD LAVATORY

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Page 20

Interior Arrangement

REVISION 21

AOM-1502-003

76 SEATS

AIRPLANE OPERATIONS MANUAL

LOADING

PASSENGER BALANCE ARM SEATS ROW 1 2 3 4

AOM-1502-003

5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

PASSENGER SEATS A1 D1, F1 A2 D2, F2 A3 D3, F3 A4 D4, F4 A8, B8, D8, F8 A9, B9, D9, F9 A10, B10, D10, F10 A11, B11, D11, F11 A12, B12, D12, F12 A13, B13, D13, F13 A14, B14, D14, F14 A15, B15, D15, F15 A16, B16, D16, F16 A17, B17, D17, F17 A18, B18, D18, F18 A19, B19, D19, F19 A20, B20, D20, F20 A21, B21, D21, F21 A22, B22, D22, F22 A23, B23, D23, F23

PAX BALANCE ARM (m) (in) 6.602 259.9 6.500 255.9 7.542 296.9 7.440 292.9 8.481 333.9 8.380 329.9 9.421 370.9 9.320 366.9 10.576 416.4 11.440 450.4 12.303 484.4 13.167 518.4 14.030 552.4 14.792 582.4 15.554 612.4 16.316 642.4 17.078 672.4 17.840 702.4 18.602 732.4 19.364 762.4 21.126 792.4 20.888 822.4 21.650 852.4 22.412 882.4

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REVISION 21

Interior Arrangement

Page 21

LOADING

AIRPLANE OPERATIONS MANUAL FURNISHINGS AND EQUIPMENT BALANCE ARM

GALLEY G1 WARDROBE FWD LAVATORY LH FWD FLIGHT ATTND SEAT OBSERVER SEAT FWD WINDSCREEN LH PILOT SEAT AFT WINDSCREEN RH AFT WINDSCREEN LH AFT FLIGHT ATTND LH SEAT AFT LAVATORY LH GALLEY G3 AFT FLIGHT ATTND RH SEAT

Balance Arm (m) (in) 3.970 156.30 5.374 211.56 4.220 166.14 4.940 194.49 3.500 137.80 5.688 223.94 2.810 110.63 22.868 900.31 22.868 900.31 23.628

930.23

24.388 24.388

960.16 960.16

23.120

910.23

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Interior Arrangement

REVISION 21

AOM-1502-003

"

LOADING

AIRPLANE OPERATIONS MANUAL !EMBRAER 175 UNITED Configuration AFT LAVATORY

GALLEY G3

AFT FLT ATTENDANT SEAT (CC2)

AFT FLT ATTENDANT SEAT (CC3)

AFT CABIN BULKHEAD

WINDSCREEN WARDROBE FWD FLT ATTENDENT SEAT (CC1) GALLEY G1

AOM-1502-003

OBSERVER SEAT

PILOTS SEATS

EM170AOM080219A.DGN

FWD LAVATORY

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REVISION 21

Interior Arrangement

Page 23

LOADING

AIRPLANE OPERATIONS MANUAL PASSENGER BALANCE ARM

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16

PASSENGER SEAT NUMBER 1A 1C, 1D 2A 2C, 2D 3A 3C, 3D 4A 4C, 4D 7A, 7B 7C, 7D 8A, 8B 8C, 8D 9A, 9B 9C, 9D 10A, 10B 10C, 10D 11A, 11B 11C, 11D 12A, 12B 12C, 12D 15A, 15B 15C, 15D 16A, 16B 16C, 16D 17A, 17B 17C, 17D 18A, 18B 18C, 18D 19A, 19B 19C, 19D 20A, 20B 20C, 20D

PAX BALANCE ARM (m) (in) 6.424 252.91 6.322 248.91 7.364 289.91 7.262 285.91 8.303 326.91 8.202 322.91 9.243 363.91 9.142 359.91 10.326 406.54 10.351 407.54 11.190 440.54 11.215 441.54 12.053 474.54 12.079 475.54 12.917 508.54 12.942 509.54 13.704 539.54 13.730 540.54 14.492 570.54 14.517 571.54 15.279 601.54 15.304 602.54 16.066 632.54 16.092 633.54 16.854 663.54 16.879 664.54 17.641 694.54 17.667 695.54 18.429 725.54 18.454 726.54 19.216 756.54 19.241 757.54

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Interior Arrangement

REVISION 21

AOM-1502-003

ROW NUMBER

LOADING

AIRPLANE OPERATIONS MANUAL

ROW NUMBER 17 18 19 20

PAX BALANCE ARM (m) (in) 20.003 787.54 20.029 788.54 20.791 818.54 20.816 819.54 21.578 849.54 21.604 850.54 22.366 880.54 22.391 881.54

PASSENGER SEAT NUMBER 21A, 21B 21C, 21D 22A, 22B 22C, 22D 23A, 23B 23C, 23D 24A, 24B 24C, 24D

FURNISHINGS AND EQUIPMENT BALANCE ARM Balance Arm GALLEY G1 WARDROBE FWD LAVATORY LH FWD FLIGHT ATTND SEAT OBSERVER SEAT FWD WINDSCREEN LH PILOT SEAT AFT BULKHEAD RH AFT BULKHEAD LH AFT FLIGHT ATTND SEAT LH AFT LAVATORY LH GALLEY G3 AFT FLT ATTENDANT SEAT RH

(m) 3.970 5.374 4.220 4.940 3.500 5.688 2.810 22.868 22.868

(in) 156.30 211.56 166.14 194.49 137.80 223.94 110.63 900.31 900.31

23.628

930.23

24.388 24.388

960.16 960.16

23.120

910.24

AOM-1502-003

"

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REVISION 21

Interior Arrangement

Page 25

LOADING

AIRPLANE OPERATIONS MANUAL

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Interior Arrangement

REVISION 21

AOM-1502-003

For maximum weight of the furnishings, refer to Aircraft Illustrated Parts Catalog, in Placards and Markings section.

AIRPLANE OPERATIONS MANUAL

LOADING

CARRY-ON BAGGAGE Carry-on volumes may be stowed in the overhead bins and in the wardrobe. There is no specific requirement for underseat carry-on volumes; however a maximum of 0.04 m3 (1.4 ft3) or 9.0 kg (20 lb) is allowable, provided the volume is properly restrained to avoid sliding.

OVERHEAD BINS In a typical Economy Class, the overhead bins comprise of eight Economy Class Standard overhead bin assemblies, and one Economy Class Long and one Economy Class Short overhead bin assembly, on the both sides of the passenger cabin. !Airplanes with first-class passenger seats

In a typical First Class, on the right side, the overhead bins comprise of one First Class Standard overhead bin assembly (in the middle position) and two Right First Class Short overhead bin assemblies; on the left side, the overhead bins comprise of one First Class Shallow overhead bin assembly (in the middle position) and two Left First Class Short overhead bin assemblies. "

Overhead stowage compartments provide carry-on provisions for rollon bags (61 cm x 35.5 cm x 25.4 cm or 24 in x 14 in x 10 in size). The average volume of overhead bins is 0.06 m3 (2.12 ft3) per passenger.

AOM-1502-003

OVERHEAD BINS CAPACITY AND LENGTH

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REVISION 11

Overhead Bin

Page 1

LOADING

AIRPLANE OPERATIONS MANUAL

ACTUATOR ACTUATOR

EM170AOM080151A.DGN

D

A B C

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Page 2

Overhead Bin

REVISION 11

AOM-1502-003

OVERHEAD BIN SCHEMATIC - FRONT VIEW

LOADING

AIRPLANE OPERATIONS MANUAL OVERHEAD BINS: STANDARD CABIN Capacity and Dimensions A B C D Capacity

Standard Overhead Bin 151.3 cm (60 in) 157.0 cm (62 in) 160.6 cm (63 in) 22.8 cm (9 in) 36.3 kg (80 lb)

Long Overhead Bin 165.1 cm (65 in) 170.9 cm (67 in) 174.6 cm (69 in) 22.8 cm (9 in) 36.3 kg (80 lb)

OVERHEAD BINS: FIRST CLASS !Airplanes with first-class passenger seats

Capacity and Dimensions A B C D Capacity

Standard Overhead Bin 151.3 cm (60 in) 157.0 cm (62 in) 160.6 cm (63 in) 22.8 cm (9 in) 54.4 kg (120 lb)

Shallow Bin 151.3 cm (60 in) 157.0 cm (62 in) 160.6 cm (63 in) 22.8 cm (9 in) 18.1 kg (40 lb)

AOM-1502-003

"

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REVISION 11

Overhead Bin

Page 3

LOADING

AIRPLANE OPERATIONS MANUAL

44.6 cm 17.6 in

ROLL−ON BAG (61 cm x 35.5 cm x 25.4 cm (24in x 14 in x 10 in)

EM170AOM080013.DGN

29.4 cm 11.6 in

27.8 cm 10.9 in

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Page 4

Overhead Bin

REVISION 11

AOM-1502-003

OVERHEAD BINS

AIRPLANE OPERATIONS MANUAL

LOADING

!Airplanes with first-class passenger seats

26.9 cm 10.6 in

EM170AOM080135A.DGN

60.5 cm 23.8 in

AOM-1502-003

RIGHT FIRST CLASS OVERHEAD BINS "

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REVISION 11

Overhead Bin

Page 5

LOADING

AIRPLANE OPERATIONS MANUAL

!Airplanes with first-class passenger seats

23.1 cm 9.1 in

EM170AOM080134A.DGN

22.3 cm 8.8 in

"

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Page 6

Overhead Bin

REVISION 11

AOM-1502-003

LEFT FIRST CLASS SHALLOW BINS

AIRPLANE OPERATIONS MANUAL

LOADING

CARGO DOORS The cargo doors are manually operated from the outside. The initial opening movement (displacement of the door inward) and final closing and latching movement (displacement of the door outward) are achieved by means of a door locking mechanism controlled by an external handle. Two actuators are installed in each cargo door to give assistance in door opening and closing movements. So, the door operator must support the door weight by using the rod during all opening and closing movements. The forward cargo door is 1.10 m (3 ft 7.3 in) wide and 0.90 m (2 ft 11.4 in) high.

AOM-1502-003

The aft cargo door is a trapezoid 0.99 m (3 ft 3 in) wide and with minor high of 0.78 m (2 ft 6.7 in) and major high of 0.87 m (2 ft 10 in).

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REVISION 12

Cargo Compartment Door

Page 1

LOADING

AIRPLANE OPERATIONS MANUAL

CARGO DOOR OPENING

TO OPEN:

1

2

HANDLE COVER VENT PANEL BUTTON MAIN HANDLE VENT PANEL PUSH IN THE MAIN DOOR HANDLE COVER. PULL THE MAIN DOOR HANDLE FULLY UP TO RELEASE THE DOOR.

PUSH DOWN THE VENT PANEL BUTTON. PUSH IN THE VENT PANEL.

3

4

VIEWED FROM INSIDE CARGO COMPARTMENT

ROD

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Page 2

Cargo Compartment Door

REVISION 12

AOM-1502-003

OPEN AND HOLD THE DOOR. REMOVE ROD FROM STOWAGE.

ENGAGE THE ROD TO DOOR’S ROD ATTACHMENT AND LIFT DOOR TO FULLY OPEN POSITION WITH ASSISTANCE OF ROD. CHECK IF DOOR IS LOCKED IN FULLY OPEN POSITION. STOW THE ROD.

EM170AOM080005D.DGN

ROD

LOADING

AIRPLANE OPERATIONS MANUAL

CARGO DOOR CLOSING TO CLOSE:

1

STABILIZATION HANDLE

2

VIEWED FROM INSIDE THE CARGO COMPARTMENT

ROD STOWAGE

ROD

ROD REMOVE THE ROD FROM THE STOWAGE. ENGAGE THE ROD TO THE DOOR’S ROD ATTACHMENT (HANDLE), AND WHILE PUSHING IT UP, TURN IT CLOCKWISE.

PULL THE DOOR DOWN WITH THE ROD AND GRASP THE INTERNAL HANDLE. REMOVE THE ROD FROM THE DOOR AND PUT IT INTO THE CARGO COMPARTMENT STOWAGE.

LOCK HANDLE

3

4

MAIN HANDLE (OPEN)

VENT−FLAP (OPEN)

CORRECT POSITION

MAIN HANDLE (OPEN)

VENT−FLAP (OPEN)

MAKE SURE THAT LOCK HANDLE IS IN THE OPEN POSITION (DOWN) BEFORE CLOSING THE DOOR.

MOVE THE DOOR DOWN AND INTO THE FUSELAGE.

5

6 MAIN HANDLE (CLOSED)

MAIN HANDLE VENT−FLAP (OPEN)

CHECK IF THE DOOR IS LATCHED. GRAB THE DOOR BY VENT−FLAP APERTURE AND PULL THE DOOR. IF THE DOOR MOVES, LIFT THE MAIN HANDLE AND LATCH THE DOOR AGAIN (STEP 5).

PUSH THE DOOR MAIN HANDLE FULLY DOWN.

7

VENT−FLAP (OPEN)

VENT−FLAP

AOM-1502-003

LATCH

LOCK

LATCH

PULL OUT THE VENT−FLAP. ENSURE THAT MAIN HANDLE AND VENT−FLAP ARE FLUSH WITH THE DOOR. ENSURE THAT DOOR IS CORRECTLY CLOSED (FLUSH WITH FUSELAGE). CHECK LOCK AND LATCH GREEN INDICATIONS.

EM170AOM140703C.DGN

FLUSH

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REVISION 12

Cargo Compartment Door

Page 3

LOADING

AIRPLANE OPERATIONS MANUAL

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Page 4

Cargo Compartment Door

REVISION 12

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

LOADING

CARGO COMPARTMENT Cargo compartments are located in the forward and rear part of the fuselage. Both cargo compartments are pressurized. They are “class-C” compartments and have the following systems installed: • Smoke Detection System. • Fire Extinguishing System. • Ventilation System (FWD). NOTE: The airplane fire extinguishing system was not designed to deal with fire from high-density packages of lithium batteries. No dedicated temperature control is available for cargo compartments. The air flowing from passenger cabin heats the FWD cargo compartment, providing proper conditions for live animals carriage. The following cargo nets may be installed in the cargo compartment:

AOM-1502-003

• •

Doors Safety Nets. Cargo Barrier Net (vertical net).

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REVISION 21

Cargo Compartment

Page 1

LOADING

AIRPLANE OPERATIONS MANUAL

DIMENSIONS AND LIMITS

!EMBRAER 170 models, length units in meter, feet and inch

2.41 m 7 ft 10.9 in 5.41 m 17 ft 9 in

FORWARD CARGO COMPARTMENT

"

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Page 2

Cargo Compartment

REVISION 21

AOM-1502-003

1.82 m 5 ft 11.7 in

EM170AOM080011A.DGN

0.90 m 2 ft 11.4 in

LOADING

AIRPLANE OPERATIONS MANUAL !EMBRAER 175 Models

2.66 m 8 ft 8.7 in

2.41 m 7 ft 10.9 in 6.26 m 20 ft 6.5 in

EM170AOM080032C.DGN

0.90 m 2 ft 11.4 in

AOM-1502-003

FORWARD CARGO COMPARTMENT

"

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REVISION 21

Cargo Compartment

Page 3

LOADING

AIRPLANE OPERATIONS MANUAL

45 cm 17.7 in 166 cm 65.3 in

94 cm 37.0 in

74 cm 29.1 in EM170AOM080007.DGN

272 cm 107.1 in

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Cargo Compartment

REVISION 21

AOM-1502-003

FORWARD CARGO COMPARTMENT CROSS SECTION

AIRPLANE OPERATIONS MANUAL

LOADING

!EMBRAER 170 models, not equipped with IFE, length units in meter, feet and inch

1.31 m

1.85 m 6 ft 07 in

4 ft 3.6 in 4.30 m 14 ft 1.3 in

EM170AOM080012A.DGN

0.78 m 2 ft 6.7 in

0.88 m 2 ft 10,6 in

AOM-1502-003

AFT CARGO COMPARTMENT

"

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REVISION 21

Cargo Compartment

Page 5

LOADING

AIRPLANE OPERATIONS MANUAL

!EMBRAER 175 models, not equipped with IFE

2.27 m 7 ft 5.4 in

1.85 m 6 ft 0.8 in 5.26 m 17 ft 3.1 in

EM170AOM080033D.DGN

0.78 m 2 ft 6.7 in

0.88 m 2 ft 10.6 in

"

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Cargo Compartment

REVISION 21

AOM-1502-003

AFT CARGO COMPARTMENT

LOADING

AIRPLANE OPERATIONS MANUAL

45 cm 17.7 in 164 cm 64.5 in

94 cm 37.0 in

74 cm 29.1 in

142 cm 55.9 in

54 cm 21.2 in 167 cm 65.7 in

27 cm 10.6 in

55 cm 21.6 in

EM170AOM080131B.DGN

206 cm 81.1 in

AOM-1502-003

AFT CARGO COMPARTMENT CROSS SECTION

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REVISION 21

Cargo Compartment

Page 7

LOADING

AIRPLANE OPERATIONS MANUAL CARGO COMPARTMENT BALANCE ARM

!EMBRAER 170 models, not equipped with IFE FORWARD

7.739 m (304.7 in)

AFT

18.527 m (729.4 in)

"

CARGO COMPARTMENT BALANCE ARM !EMBRAER 175 models, not equipped with IFE FORWARD

8.243 m (324.5 in)

AFT

19.860 m (781.9 in)

"

FORWARD CARGO COMPARTMENT LIMITS !EMBRAER 170 models, length units in meter, feet and inch 7.21 m3

Cargo Compartment Available Volume (usable)

488 kg/m2

Maximum Floor Distributed Load Maximum Floor Concentrated Load

254.60 ft3

[1]

100 lb/ft2

2

Total Maximum Capacity

0.59 kg/cm

8.41 lb/in2

1370 kg

3020 lb

1. Any number of contact points can be used as long as, in total, they do not exceed the maximum cargo compartment weights and maximum weights adjacent to vertical nets described in block 8-70. "

FORWARD CARGO COMPARTMENT LIMITS !EMBRAER 175 Models 8.48 m3

Cargo Compartment Available Volume

299.50 ft3

(usable) 488 kg/m2

Maximum Floor Distributed Load Maximum Floor Concentrated Load

[1]

2

Total Maximum Capacity

100 lb/ft2

0.59 kg/cm

8.41 lb/in2

1500 kg

3306 lb

"

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Page 8

Cargo Compartment

REVISION 21

AOM-1502-003

1. Any number of contact points can be used as long as, in total, they do not exceed the maximum cargo compartment weights and maximum weights adjacent to vertical nets described in block 8-70.

LOADING

AIRPLANE OPERATIONS MANUAL AFT CARGO COMPARTMENT LIMITS

!EMBRAER 170 models, not equipped with IFE, length units in meter, feet and inch 4.59 m3

Cargo Compartment Available Volume (usable)

488 kg/m2

Maximum Floor Distributed Load Maximum Floor Concentrated Load

162.10 ft3

[1]

2

Total Maximum Capacity

100 lb/ft2

0.70 kg/cm

10 lb/in2

1030 kg

2271 lb

1. Any number of contact points can be used as long as, in total, they do not exceed the maximum cargo compartment weights and maximum weights adjacent to vertical nets described in block 8-70. "

AFT CARGO COMPARTMENT LIMITS !EMBRAER 175 models, not equipped with IFE Cargo Compartment Available Volume (usable) Maximum Floor Distributed Load Maximum Floor Concentrated Load

[1]

Total Maximum Capacity

6.04 m3

213.30 ft3

488 kg/m2

100 lb/ft2

0.70 kg/cm2

10 lb/in2

1150 kg

2535 lb

1. Any number of contact points can be used as long as, in total, they do not exceed the maximum cargo compartment weights and maximum weights adjacent to vertical nets described in block 8-70. "

BAGGAGE AND CARGO LOADING Baggage and cargo should be evenly distributed over the cargo compartment to avoid load concentration.

AOM-1502-003

Baggage/Cargo must not become a hazard to the airplane structure or systems as a result of shifting under operational loads. Therefore, sharp edge volumes (like wooden or metal containers) and/or dense cargo (objects significantly more dense than typical passenger baggage) must be arranged with adjacent soft volumes or protections thus preventing airplane damage in case of baggage/cargo shifting due to operational loads. To ensure proper operation of the smoke detection and fire suppression

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REVISION 21

Cargo Compartment

Page 9

LOADING

AIRPLANE OPERATIONS MANUAL

systems under all operating conditions, a placard, located on the inside sidewall panel of the cargo compartment, clearly visible when the cargo door is opened, is installed in the compartment to restrict cargo from being loaded to within 2.0 in (51 mm) of the cargo compartment ceiling. Cargo loaded up to the ceiling may cause a baffle effect and prevent dispersion of smoke in the compartment, resulting in delays in detection time. The proper dispersion of fire suppression agent in the compartment may also be affected if the cargo is installed in such a manner that it blocks the area surrounding the protection cage of the suppression nozzle. If no procedures are established to ensure the airplane remains within aft tipping limit established under General Data, the forward cargo compartment should be loaded before the aft cargo compartment, while the aft cargo compartment should begin to be unloaded before the forward cargo compartment, in order to avoid airplane taildown.

BAGGAGE AND CARGO TIE DOWN PROCEDURE The vertical cargo net attachment points may be used to tie down volumes. When using attachment points to tie down volumes, all the following conditions must be met: – Volumes must be tied down in a manner to prevent shifting; – Vertical cargo net located at that position must be removed; – Loose volumes are not allowed in the same section where tie down fitting cups are being used to restrain cargo. NOTE: Cargo door nets and crew baggage net attachment points as well as attachment points located on the cargo compartment ceiling shall not be used to tie down volumes.

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Page 10

Cargo Compartment

REVISION 21

AOM-1502-003

Considering the following positions of the nets:

LOADING

AIRPLANE OPERATIONS MANUAL

E

NET 3

D

NET 2

C

NET 1

B

NET 7

D

A

NET 6

C

NET 5

B

A

EM170AOM080193B.DGN

NET 4

The following schemes of attachment should be used to attach volumes. Each scheme has its related table which specifies the limits for volume dimensions and weight that can be alocated in each pair of nets. !170 models, units in lb

For example, in the case of a volume of 15 in of width, 23 in of length, 20 in of height and 132 lb of weight, its allocation could be in the forward compartment through scheme 2. " !175 models, units in lb

For example, in the case of a volume of 12 in of width, 24 in of length, 16 in of height and 120 lb of weight, its allocation could be in the forward compartment through scheme 2.

AOM-1502-003

"

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REVISION 21

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LOADING

AIRPLANE OPERATIONS MANUAL

SCHEME 1

HEIGHT

WIDTH

EM170AOM080186B.DGN

LENGTH

!170 models, units in lb

HEIGHT (in) FORWARD CARGO AFT CARGO

WIDTH (in) 9.8 – 15.7 PACKAGE MAXIMUM LENGTH (in) WEIGHT (lb)

3.9 – 31.5

9.8 – 19.7

22.0

3.9 – 19.7

9.8 – 19.7

15.4 "

!175 models, units in lb

FORWARD CARGO

3.9 – 31.5

9.8 – 19.7

41.9

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REVISION 21

AOM-1502-003

HEIGHT (in)

WIDTH (in) 9.8 – 15.7 PACKAGE MAXIMUM LENGTH (in) WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

HEIGHT (in) AFT CARGO

3.9 – 19.7

LOADING

WIDTH (in) 9.8 – 15.7 PACKAGE MAXIMUM LENGTH (in) WEIGHT (lb) 9.8 – 19.7 17.6

AOM-1502-003

"

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Page 13

LOADING

AIRPLANE OPERATIONS MANUAL

SCHEME 2

HEIGHT

EM170AOM080187B.DGN

LENGTH

WIDTH

!170 models, units in lb

HEIGHT (in) FORWARD CARGO AFT CARGO

WIDTH (in) 9.84 – 15.7 PACKAGE MAXIMUM LENGTH (in) WEIGHT (lb)

13.4 – 31.5

9.8 – 26.4

149.9

15.7 – 19.7

9.8 – 23.2

83.8 "

!175 models, units in lb

FORWARD CARGO

13.4 – 31.5

9.8 – 26.4

191.8

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Cargo Compartment

REVISION 21

AOM-1502-003

HEIGHT (in)

WIDTH (in) 9.8 – 15.7 PACKAGE MAXIMUM LENGTH (in) WEIGHT (lb)

AIRPLANE OPERATIONS MANUAL

HEIGHT (in) AFT CARGO

15.7 – 19.7

LOADING

WIDTH (in) 9.8 – 15.7 PACKAGE MAXIMUM LENGTH (in) WEIGHT (lb) 9.8 – 23.2 110.2

AOM-1502-003

"

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LOADING

AIRPLANE OPERATIONS MANUAL

SCHEME 3

LENGTH WIDTH

EM170AOM080188B.DGN

HEIGHT

!170 models, units in lb

HEIGHT (in) NET NET NET NET NET

1 2 3 5 6

– – – – –

NET NET NET NET NET

2 3 4 6 7

13.4 13.4 13.4 15.7 13.8

– – – – –

34.3 19.7 24.8 19.7 22.4

WIDTH (in) 9.8 – 15.7 PACKAGE MAXIMUM LENGTH (in) WEIGHT (lb) 39.0 – 53.9 348.3 94.1 – 110.2 343.9 56.7 – 89.8 299.8 93.7 – 110.2 224.9 43.7 – 63.8 231.5

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REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

LOADING

!175 models, units in lb

HEIGHT (in) NET NET NET NET NET

1 2 3 5 6

– – – – –

NET NET NET NET NET

2 3 4 6 7

13.4 13.4 13.4 15.7 13.8

– – – – –

22.0 18.9 22.0 21.7 22.4

WIDTH (in) 9.8 – 15.0 PACKAGE MAXIMUM LENGTH (in) WEIGHT (lb) 72.4 – 103.9 432.1 107.5 – 122.0 595.2 56.7 – 89.8 432.1 93.7 – 102.4 306.4 43.7 – 63.8 262.3

AOM-1502-003

"

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Page 17

LOADING

AIRPLANE OPERATIONS MANUAL

SCHEME 4

HEIGHT

EM170AOM080189B.DGN

LENGTH

WIDTH

!170 models, units in lb

HEIGHT (in) NET NET NET NET NET

1 2 3 5 6

– – – – –

NET NET NET NET NET

2 3 4 6 7

20.5 – 34.3 19.7 – 22.4

WIDTH (in) 15.7 – 24.8 PACKAGE MAXIMUM LENGTH (in) WEIGHT (lb) 39 – 53.9 138.9 50.4 – 59.1 189.6

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REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

LOADING

!175 models, units in lb

HEIGHT (in) NET NET NET NET NET

1 2 3 5 6

– – – – –

NET NET NET NET NET

2 3 4 6 7

20.5 – 24.8 16.5 – 22.0

WIDTH (in) 15.7 – 24.8 PACKAGE MAXIMUM LENGTH (in) WEIGHT (lb) 56.7 – 66.9 141.1 43.7 – 59.1 136.7

AOM-1502-003

"

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Cargo Compartment

Page 19

LOADING

AIRPLANE OPERATIONS MANUAL

SCHEME 5

EM170AOM080190B.DGN

HEIGHT

LENGTH WIDTH

!170 models, units in lb

HEIGHT (in) NET NET NET NET NET

1 2 3 5 6

– – – – –

NET NET NET NET NET

2 3 4 6 7

9.8 9.8 9.8 9.8 9.8

– – – – –

34.3 18.9 24.8 13.0 27.2

WIDTH (in) 9.8 – 13.8 PACKAGE MAXIMUM LENGTH (in) WEIGHT (lb) 39.0 – 53.9 39.7 94.1 – 118.1 35.3 56.7 – 78.7 37.5 93.7 – 122.0 11.0 43.7 – 63.8 11.0

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Cargo Compartment

REVISION 21

AOM-1502-003

"

LOADING

AIRPLANE OPERATIONS MANUAL !175 models, units in lb

HEIGHT (in) NET NET NET NET NET

1 2 3 5 6

– – – – –

NET NET NET NET NET

2 3 4 6 7

9.8 9.8 9.8 9.8 9.8

– – – – –

24.8 15.0 24.8 19.7 27.2

WIDTH (in) 9.8 – 16.9 PACKAGE MAXIMUM LENGTH (in) WEIGHT (lb) 72.4 – 94.5 28.7 93.7 – 122.0 35.3 56.7 – 89.8 35.3 93.7 – 110.2 13.2 43.7 – 63.8 13.2 "

COFFINS ATTACHMENT Standard coffins with dimensions as shown in the table below can be attached using the attachment points of the following net pairs: !EMBRAER 170 Models

Net Pairs

1-2 or 3-4 "

!EMBRAER 175 Models

Net Pairs

3-4 "

The maximum allowable coffin weight that can be attached is 149 kg (328 lb). COFFIN 1 DIMENSIONS 200 cm (78.7 in) 50 x 40 cm (19.7 x 15.7 in) 35 x 30 cm (13.8 x 11.8 in)

Length Cross Section Head

AOM-1502-003

Cross Section Foot

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LOADING

AIRPLANE OPERATIONS MANUAL

HEIGHT

WIDTH

EM170AOM080191B.DGN

LENGTH

COFFIN 1 ATTACHMENT SCHEME

COFFIN 2 DIMENSIONS

Cross Section Head Cross Section Foot

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Cargo Compartment

REVISION 21

AOM-1502-003

205 cm (80.7 in) 59 x 42 cm (23.2 x 16.5 in) 46 x 35 cm (18.1 x 13.8 in)

Length

LOADING

AIRPLANE OPERATIONS MANUAL

HEIGHT

WIDTH

EM170AOM080192B.DGN

LENGTH

COFFIN 2 ATTACHMENT SCHEME

LOADING PROCEDURE RECOMMENDATIONS To avoid the occurrence of airplane tail tipping, some operational procedures may be established by the customer, such as: – To have assigned seats avoiding a concentrated pax distribution. However, if it is detected a tendency of passengers concentration forward or aft, the crew shall move the passengers in order to allow for a better distribution along the cabin. – To block some forward or rear seats for ease of balancing the airplane. – To distribute the baggage at the forward and aft baggage compartments in the most convenient way to guarantee the best possible CG.

AOM-1502-003

– To establish a determined order for refueling, loading passengers and loading cargo to minimize aft CG movement. The above recommendations (among other procedures) can be

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REVISION 21

Cargo Compartment

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LOADING

AIRPLANE OPERATIONS MANUAL

implemented by the Customer, in order to guarantee that the weight and CG of the airplane will be always within limits.

PACKAGE SIZE TABLES The following tables show packages dimensions which pass through the cargo compartments doors without interference with airplane fuselage or cargo compartments interior. Enter the package width and height and read the maximum package length that can be stowed in the cargo compartment.

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Cargo Compartment

REVISION 21

AOM-1502-003

NOTE: Packages with dimensions (width and height) not covered by the table may fit in the cargo compartment. Respect to the weight capacity, maximum load distribution and clearance to the compartment ceiling is mandatory.

LOADING

AIRPLANE OPERATIONS MANUAL

FORWARD CARGO COMPARTMENT MAXIMUM PACKAGE SIZE WIDTH in (cm) 5.00

10.00

15.00

20.00

25.00

30.00

35.00

40.00

(12.70)

(25.40)

(38.10)

(50.80)

(63.50)

(76.20)

(88.90)

(101.60)

HEIGHT

MAXIMUM PACKAGE LENGTH

AOM-1502-003

in (cm)

in (cm)

5.00

157.48

157.48

133.86

118.11

110.24

106.30

86.61

78.74

(12.70)

(400.00)

(400.00)

(340.00)

(300.00)

(280.00)

(270.00)

(220.00)

(200.00)

8.00

149.61

141.73

125.98

114.17

110.24

94.49

86.61

78.74

(20.32)

(380.00)

(360.00)

(320.00)

(290.00)

(280.00)

(240.00)

(220.00)

(200.00)

10.00

147.63

141.73

125.98

114.17

102.36

90.55

78.74

66.93

(25.40)

(375.00)

(360.00)

(320.00)

(290.00)

(260.00)

(230.00)

(200.00)

(170.00)

13.00

143.70

139.76

122.05

110.24

102.36

90.55

78.74

66.93

(33.02)

(365.00)

(355.00)

(310.00)

(280.00)

(260.00)

(230.00)

(200.00)

(170.00)

16.00

141.73

137.80

122.05

110.24

94.49

82.68

74.80

62.99

(40.64)

(360.00)

(350.00)

(310.00)

(280.00)

(240.00)

(210.00)

(190.00)

(160.00)

19.00

141.73

137.80

118.11

106.30

94.49

82.68

66.93

59.06

(48.26)

(360.00)

(350.00)

(300.00)

(270.00)

(240.00)

(210.00)

(170.00)

(150.00)

22.00

133.86

125.98

102.36

84.65

70.87

66.93

59.06

51.18

(55.88)

(340.00)

(320.00)

(260.00)

(215.00)

(180.00)

(170.00)

(150.00)

(130.00)

25.00

118.11

94.49

78.74

70.87

66.93

59.06

51.18

51.18

(63.50)

(300.00)

(240.00)

(200.00)

(180.00)

(170.00)

(150.00)

(130.00)

(130.00)

28.00

90.55

82.68

62.99

59.06

55.12

55.12

51.18

47.24

(71.12)

(230.00)

(210.00)

(160.00)

(150.00)

(140.00)

(140.00)

(130.00)

(120.00)

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AIRPLANE OPERATIONS MANUAL

AFT CARGO COMPARTMENT MAXIMUM PACKAGE SIZE WIDTH in (cm) 5.00

10.00

15.00

20.00

25.00

30.00

35.00

40.00

(12.70)

(25.40)

(38.10)

(50.80)

(63.50)

(76.20)

(88.90)

(101.60)

HEIGHT

MAXIMUM PACKAGE LENGTH in (cm)

5.00

125.98

125.98

125.98

118.11

76.77

72.83

72.83

70.87

(12.70)

(320.00)

(320.00)

(320.00)

(300.00)

(195.00)

(185.00)

(185.00)

(180.00)

8.00

122.05

122.05

122.05

116.14

74.80

70.87

70.87

66.14

(20.32)

(310.00)

(310.00)

(310.00)

(295.00)

(190.00)

(180.00)

(180.00)

(168.00)

10.00

122.05

122.05

122.05

106.3

74.80

70.87

70.87

63.78

(25.40)

(310.00)

(310.00)

(310.00)

(270.00)

(190.00)

(180.00)

(180.00)

(162.00)

13.00

122.05

122.05

106.30

95.67

74.80

70.87

63.78

61.81

(33.02)

(310.00)

(310.00)

(270.00)

(243.00)

(190.00)

(180.00)

(162.00)

(157.00)

16.00

98.43

98.43

94.49

86.61

61.02

59.06

59.06

58.66

(40.64)

(250.00)

(250.00)

(240.00)

(220.00)

(155.00)

(150.00)

(150.00)

(149.00)

19.00

92.52

92.52

90.55

78.74

61.02

59.06

59.06

57.09

(48.26)

(235.00)

(235.00)

(230.00)

(200.00)

(155.00)

(150.00)

(150.00)

(145.00)

22.00

86.61

86.61

82.68

78.74

59.06

57.09

56.30

55.51

(55.88)

(220.00)

(220.00)

(210.00)

(200.00)

(150.00)

(145.00)

(143.00)

(141.00)

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Cargo Compartment

REVISION 21

AOM-1502-003

in (cm)

AIRPLANE OPERATIONS MANUAL

LOADING

CARGO NETS Cargo door nets prevent cargo doors from being damaged or jammed. Attachments in the forward and aft cargo compartments allow the installation of optional vertical cargo nets. The vertical cargo nets prevent the luggage shifting and optimizes the loading. !Airplanes equipped with crew luggage net

One cargo crew-luggage net is installed in the forward cargo compartment to isolate an area for crewmembers luggage. "

The use of vertical cargo nets is not required. If total or partial use of vertical nets in the forward or aft cargo compartments, maximum cargo compartment section weights must be observed. When segregated cargo nets are not used the maximum total cargo compartment weight limit must be observed. Decals on the net assembly indicate orientation (FWD, AFT, UP, or RIGHT/LEFT). Positioning of Cargo Compartment Divisions and Vertical Cargo Nets Attachments - m (ft) - in transversal way, are shown in the table below. !EMBRAER 170 models equipped with crew luggage net, units in meters and feet

Forward Bulkhead Position 1st Vertical Net Attachment Position 2nd Vertical Net Attachment Position 3rd Vertical Net Attachment Position Aft Bulkhead Position

FORWARD 5.00 m (16.40 ft) 6.36 m (20.87 ft) 8.45 m (27.72 ft) 9.59 m (31.46 ft) 10.42 m (34.19 ft)

AFT 16.91 m (55.48 ft) 17.78 m (58.33 ft) 19.86 m (65.16 ft) 20.67 m (67.81 ft) 21.26 m (69.75 ft)

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REVISION 18

Cargo Nets

Page 1

LOADING

AIRPLANE OPERATIONS MANUAL

!EMBRAER 170 models equipped with crew luggage net, units in meters and feet

CARGO CREW−LUGGAGE NET

CARGO NET

CARGO NET CEILING ATTACHMENTS FOR CARGO NET (OPTIONAL POSITION)

EM170AOM080016A.DGN

DOOR SAFETY NET

FLOOR ATTACHMENTS FOR CARGO NET (OPTIONAL POSITION)

"

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Cargo Nets

REVISION 18

AOM-1502-003

FORWARD CARGO COMPARTMENT

LOADING

AIRPLANE OPERATIONS MANUAL

!EMBRAER 170 models equipped with crew luggage net, units in meters and feet

CARGO NET

DOOR SAFETY NET

EM170AOM080010A.DGN

CARGO NET

AOM-1502-003

AFT CARGO COMPARTMENT

"

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REVISION 18

Cargo Nets

Page 3

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AIRPLANE OPERATIONS MANUAL

Positioning of Cargo Compartment Divisions and Vertical Cargo Nets Attachments - m (ft) - in transversal way, are shown in the table below. !EMBRAER 170 models without cargo compartment nets

Forward Bulkhead Position 1st Vertical Net Attachment Position 2nd Vertical Net Attachment Position 3rd Vertical Net Attachment Position 4th Vertical Net Attachment Position Aft Bulkhead Position

FORWARD 5.00 m (16.40 ft) 5.67 m (18.60 ft) 6.36 m (20.87 ft) 8.45 m (27.72 ft) 9.59 m (31.46 ft) 10.42 m (34.19 ft)

AFT 16.91 m (55.48 ft) 17.78 m (58.33 ft) 19.86 m (65.16 ft) 20.67 m (67.81 ft) NA 21.26 m (69.75 ft)

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Cargo Nets

REVISION 18

AOM-1502-003

"

LOADING

AIRPLANE OPERATIONS MANUAL !EMBRAER 170 models without cargo compartment nets

CEILING ATTACHMENTS FOR CARGO NET (OPTIONAL POSITION)

FLOOR ATTACHMENTS FOR CARGO NET (OPTIONAL POSITION) CEILING ATTACHMENTS FOR CARGO NET (OPTIONAL POSITION)

FLOOR ATTACHMENTS FOR CARGO NET (OPTIONAL POSITION)

CEILING ATTACHMENTS FOR CARGO NET (OPTIONAL POSITION)

FLOOR ATTACHMENTS FOR CARGO NET (OPTIONAL POSITION)

FLOOR ATTACHMENTS FOR CARGO NET (OPTIONAL POSITION)

EM170AOM080019A.DGN

CARGO DOOR NET

AOM-1502-003

FORWARD CARGO COMPARTMENT

"

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REVISION 18

Cargo Nets

Page 5

LOADING

AIRPLANE OPERATIONS MANUAL

!EMBRAER 170 models without cargo compartment nets

CEILING ATTACHMENTS FOR CARGO NET (OPTIONAL POSITION)

FLOOR ATTACHMENTS FOR CARGO NET (OPTIONAL POSITION)

CARGO DOOR NET

FLOOR ATTACHMENTS FOR CARGO NET (OPTIONAL POSITION)

EM170AOM080020A.DGN

CEILING ATTACHMENTS FOR CARGO NET (OPTIONAL POSITION)

"

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Cargo Nets

REVISION 18

AOM-1502-003

AFT CARGO COMPARTMENT

AIRPLANE OPERATIONS MANUAL

LOADING

Positioning of Cargo Compartment Divisions and Vertical Cargo Nets Attachments - m (ft) - in transversal way, are shown in the table below. !EMBRAER 175 models, without crew luggage net and not equipped with IFE

Forward Bulkhead Position 1st Vertical Net Attachment Position 2nd Vertical Net Attachment Position 3rd Vertical Net Attachment Position 4th Vertical Net Attachment Position Aft Bulkhead Position

FORWARD 5.00 m (16.40 ft) 5.67 m (18.60 ft) 7.21 m (23.65 ft) 9.29 m (30.48 ft) 10.43 m (34.22 ft) 11.25 m (36.91 ft)

AFT 17.76 m (58.27 ft) 19.17 m (64.17 ft) 21.64 m (71.00 ft) 22.45 m (73.65 ft) NA 23.04 m (75.59 ft)

AOM-1502-003

"

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REVISION 18

Cargo Nets

Page 7

LOADING

AIRPLANE OPERATIONS MANUAL

EM170AOM080034B.DGN

!EMBRAER 175 models, without crew luggage net and not equipped with IFE

FORWARD CARGO COMPARTMENT

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Page 8

Cargo Nets

REVISION 18

AOM-1502-003

"

LOADING

AIRPLANE OPERATIONS MANUAL

!EMBRAER 175 models, without crew luggage net and not equipped with IFE

CARGO NET

DOOR SAFETY NET

EM170AOM080035B.DGN

CARGO NET

AFT CARGO COMPARTMENT

AOM-1502-003

"

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REVISION 18

Cargo Nets

Page 9

LOADING

AIRPLANE OPERATIONS MANUAL

VERTICAL NETS AND SECTION LOADING DISTRIBUTION Each vertical net attachment position divides the cargo compartment in different cargo compartment sections as depicted below: !EMBRAER 170 models equipped with crew luggage net, units in meters and feet

D

A

C

EM170AOM080049B.DGN

E

B

9.59 m (31.46 ft) 10.42 m 8.45 m (34.19 ft) (27.72 ft)

6.36 m (20.87 ft)

5.00 m (16.40 ft)

FORWARD COMPARTMENT

" !EMBRAER 170 models equipped with crew luggage net, units in meters and feet

C

B

20.67 m (67.81 ft) 19.86 m 21.26 m (65.16 ft) (69.75 ft)

A

17.78 m (58.33 ft.) 16.91 m (55.48 ft)

EM170AOM080046C.DGN

D

AFT COMPARTMENT

"

MAXIMUM CARGO COMPARTMENT WEIGHTS

!EMBRAER 170 models equipped with crew luggage net, units in meters and feet

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Page 10

Cargo Nets

REVISION 18

AOM-1502-003

The table below details the maximum cargo compartment weights allowable for each section:

LOADING

AIRPLANE OPERATIONS MANUAL MAXIMUM COMPARTMENT COMPARTMENT WEIGHT

FORWARD

AFT

MAXIMUM MAXIMUM SECTION DISTRIBUTED WEIGHT LOAD

1370 kg/ 3020 lb

1030 kg/ 2271 lb

A

137 kg/ 302 lb

B

320 kg/ 706 lb

C

457 kg/ 1007 lb

D

240 kg/ 529 lb

E

216 kg/ 476 lb

A

342 kg/ 754 lb

B

344 kg/ 759 lb

C

172 kg/ 379 lb

D

172 kg/ 379 lb

488 kg/m2/ 100 lb/ft2

"

MAXIMUM WEIGHTS ADJACENT TO VERTICAL NETS !EMBRAER 170 models equipped with crew luggage net, units in meters and feet

Each vertical cargo net withstands a maximum adjacent weight according to the following table: MAXIMUM ALLOWABLE WEIGHT COMPARTMENT

AOM-1502-003

FORWARD

ATTACHMENT POSITION

FWD (⇒)

AFT (⇐)

6.36 m (20.87 ft)

456 kg/ 1005 lb

456 kg/ 1005 lb

8.45 m (27.72 ft)

456 kg/ 1005 lb

456 kg/ 1005 lb

9.59 m (31.46 ft)

456 kg/ 1005 lb

456 kg/ 1005 lb

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REVISION 18

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Page 11

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AIRPLANE OPERATIONS MANUAL

MAXIMUM ALLOWABLE WEIGHT COMPARTMENT

AFT

ATTACHMENT POSITION

FWD (⇒)

AFT (⇐)

17.78 m (58.33 ft)

342 kg/ 754 lb

342 kg/ 754 lb

19.86 m (65.16 ft)

343 kg/ 756 lb

343 kg/ 756 lb

20.67 m (67.81 ft)

342 kg/ 754 lb

342 kg/ 754 lb

NOTE: – Maximum allowable FWD weight is the maximum cargo weight withstood by the vertical net considering a forward acceleration of the cargo located behind the net. – Maximum allowable AFT weight is the maximum cargo weight withstood by the vertical net considering an aft acceleration of the cargo located in front of the net. – Should the operator use the vertical nets in different positions or quantities than the ones described above, the limiting cargo weight should be the smaller value between the MAXIMUM WEIGHTS ADJACENT TO VERTICAL NETS and MAXIMUM CARGO COMPARTMENT WEIGHTS tables. "

Each vertical net attachment position divides the cargo compartment in different cargo compartment sections as depicted below: !EMBRAER 170 models without cargo compartment nets

9.59 m (31.46 ft) 10.42 m 8.45 m (34.19 ft) (27.72 ft)

C

B

A

5.67m (18.60 ft) 6.36 m 5.00 m (20.87 ft) (16.40 ft)

FORWARD COMPARTMENT

8-70

"

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Cargo Nets

REVISION 18

AOM-1502-003

D

EM170AOM080045B.DGN

E

LOADING

AIRPLANE OPERATIONS MANUAL !EMBRAER 170 models without cargo compartment nets

C

B

20.67 m (67.81 ft) 19.86 m 21.26 m (65.16 ft) (69.75 ft)

A

17.78 m (58.33 ft.) 16.91 m (55.48 ft)

EM170AOM080046C.DGN

D

AFT COMPARTMENT

"

MAXIMUM CARGO COMPARTMENT WEIGHTS !EMBRAER 170 models without cargo compartment nets

AOM-1502-003

The table below details the maximum cargo compartment weights allowable for each section:

8-70 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cargo Nets

Page 13

LOADING

AIRPLANE OPERATIONS MANUAL

MAXIMUM COMPARTMENT COMPARTMENT WEIGHT

FORWARD

AFT

MAXIMUM MAXIMUM SECTION DISTRIBUTED WEIGHT LOAD

1370 kg/ 3020 lb

1030 kg/ 2271 lb

A

229 kg/ 505 lb

B

229 kg/ 505 lb

C

456 kg/ 1005 lb

D

240 kg/ 529 lb

E

216 kg/ 476 lb

A

342 kg/ 754 lb

B

344 kg/ 759 lb

C

172 kg/ 379 lb

D

172 kg/ 379 lb

488 kg/m2/ 100 lb/ft2

"

MAXIMUM WEIGHTS ADJACENT TO VERTICAL NETS !EMBRAER 170 models without cargo compartment nets

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Cargo Nets

REVISION 18

AOM-1502-003

Each vertical cargo net withstands a maximum adjacent weight according to the following table:

LOADING

AIRPLANE OPERATIONS MANUAL

MAXIMUM ALLOWABLE WEIGHT COMPARTMENT

FORWARD

AFT

ATTACHMENT POSITION

FWD (⇒)

AFT (⇐)

5.67 m (18.60 ft)

456 kg/ 1005 lb

456 kg/ 1005 lb

6.36 m (20.87 ft)

456 kg/ 1005 lb

456 kg/ 1005 lb

8.45 m (27.72 ft)

456 kg/ 1005 lb

456 kg/ 1005 lb

9.59 m (31.46 ft)

456 kg/ 1005 lb

456 kg/ 1005 lb

17.78 m (58.33 ft)

342 kg/ 754 lb

342 kg/ 754 lb

19.86 m (65.16 ft)

343 kg/ 756 lb

343 kg/ 756 lb

20.67 m (67.81 ft)

342 kg/ 754 lb

342 kg/ 754 lb

NOTE: – Maximum allowable FWD weight is the maximum cargo weight withstood by the vertical net considering a forward acceleration of the cargo located behind the net. – Maximum allowable AFT weight is the maximum cargo weight withstood by the vertical net considering an aft acceleration of the cargo located in front of the net. – Should the operator use the vertical nets in different positions or quantities than the ones described above, the limiting cargo weight should be the smaller value between the MAXIMUM WEIGHTS ADJACENT TO VERTICAL NETS and MAXIMUM CARGO COMPARTMENT WEIGHTS tables. "

AOM-1502-003

Each vertical net attachment position divides the cargo compartment in different cargo compartment sections as depicted below:

8-70 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cargo Nets

Page 15

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AIRPLANE OPERATIONS MANUAL

!EMBRAER 175 models, without crew luggage net and not equipped with IFE

D

10.43 m (34.22 ft) 9.29 m 11.25 m (30.48 ft) (36.91 ft)

C

B

A EM170AOM080047B.DGN

E

5.67 m (18.60 ft) 5.00 m 7.21 m (16.40 ft) (23.65 ft)

FORWARD COMPARTMENT

!EMBRAER 175 models, without crew luggage net and not equipped with IFE

B

C

23.04 m 21.64 m (75.59 ft) (71.00 ft) 22.45 m (73.65 ft)

A

19.56 m (64.17 ft)

17.76 m (58.27 ft)

EM170AOM080083B.DGN

D

"

AFT COMPARTMENT

"

MAXIMUM CARGO COMPARTMENT WEIGHTS

!EMBRAER 175 models, without crew luggage net and not equipped with IFE

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Page 16

Cargo Nets

REVISION 18

AOM-1502-003

The table below details the maximum cargo compartment weights allowable for each section:

LOADING

AIRPLANE OPERATIONS MANUAL MAXIMUM COMPARTMENT COMPARTMENT WEIGHT

FORWARD

AFT

MAXIMUM MAXIMUM SECTION DISTRIBUTED WEIGHT LOAD

1500 kg/ 3306 lb

1150 kg/ 2535 lb

A

210 kg/ 463 lb

B

423 kg/ 933 lb

C

434 kg/ 956 lb

D

228 kg/ 502 lb

E

205 kg/ 452 lb

A

506 kg/ 1115 lb

B

322 kg/ 710 lb

C

161 kg/ 355 lb

D

161 kg/ 355 lb

488 kg/m2/ 100 lb/ft2

"

MAXIMUM WEIGHTS ADJACENT TO VERTICAL NETS !EMBRAER 175 models, without crew luggage net and not equipped with IFE

AOM-1502-003

Each vertical cargo net withstands a maximum adjacent weight according to the following table:

8-70 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cargo Nets

Page 17

LOADING

AIRPLANE OPERATIONS MANUAL MAXIMUM ALLOWABLE WEIGHT

COMPARTMENT

FORWARD

AFT

ATTACHMENT POSITION

FWD (⇒)

AFT (⇐)

5.67 m (18.60 ft)

456 kg/ 1005 lb

456 kg/ 1005 lb

7.21 m (23.65 ft)

456 kg/ 1005 lb

456 kg/ 1005 lb

9.29 m (30.49 ft)

456 kg/ 1005 lb

456 kg/ 1005 lb

10.43 m (34.21 ft)

456 kg/ 1005 lb

456 kg/ 1005 lb

19.56 m (64.16 ft)

343 kg/ 756 lb

506 kg/ 1115 lb

21.64 m (71.00 ft)

343 kg/ 756 lb

343 kg/ 756 lb

22.45 m (73.64 ft)

343 kg/ 756 lb

343 kg/ 756 lb

NOTE: – Maximum allowable FWD weight is the maximum cargo weight withstood by the vertical net considering a forward acceleration of the cargo located behind the net. – Maximum allowable AFT weight is the maximum cargo weight withstood by the vertical net considering an aft acceleration of the cargo located in front of the net. – Should the operator use the vertical nets in different positions or quantities than the ones described above, the limiting cargo weight should be the smaller value between the MAXIMUM WEIGHTS ADJACENT TO VERTICAL NETS and MAXIMUM CARGO COMPARTMENT WEIGHTS tables.

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Page 18

Cargo Nets

REVISION 18

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

LOADING

LIVE ANIMALS TRANSPORTATION This section presents the general conditions for live animal transportation in the forward cargo compartment. The main reference that regulates and state methods and procedures to handling, appropriate packaging, legal aspects for animal transportation, etc. is the IATA Live Animal Regulations.

GENERAL RECOMMENDATIONS Generically, animals should be protected from stressing situations, like excessive noise, solar radiation, draft, high or low temperatures. The containers should be appropriate for the type of animal to be transported, as recommended by IATA Live Animal Regulations. Animals shall be handled with great care, to minimize the stress associated to handling. While waiting for the shipment, animals should be maintained in a waiting room with controlled temperature and protected from noise and draught. The adverse climatic conditions could cause additional stress to the animals. The ambient should be dark to make the animals calmer and comfortable while waiting for shipment. Animals of different species, specially which are natural enemies, such as cats and dogs, must be kept apart one from another. On the other hand, animals of the same species would be calmer if kept together. Animals shall be loaded just before departure and unloaded just after arrival, in order to minimize the exposition to high or low temperatures on ground, where the cargo compartment ventilation is not completely effective. Live animals shall be placed as close as possible to the cargo ventilation inflow. Care need to be taken to avoid obstruction between the cargo ventilation inflow and the cage(s).

AOM-1502-003

Specially in the hot season, it should be preferable to schedule the animal shipment for the night period, when the temperatures are lower than during the day. For the more sensitive animals, such as little birds, which would not resist to high temperatures, this is an important requirement. In addition, these animals would be too susceptible to low temperatures achieved during long cruise flights, so it could be necessary to limit the flight cruise altitude to reduce the temperature drop in the cargo compartment and protect them. The containers should not be placed near the compartment floor, in order to isolate the animals from low temperatures in that region. The recommendations for animal load limitations should be observed, in

8-80 Copyright © by Embraer. Refer to cover page for details.

REVISION 10

Live Animals

Page 1

LOADING

AIRPLANE OPERATIONS MANUAL

order to prevent animals being exposed to adverse environmental conditions.

LOADING The data below are based on IATA Live Animal Regulations. The limitations for the load in the compartment are defined mainly by temperature, carbon dioxide concentration and humidity that are a result of animal metabolism. These items are compensated with the cargo compartment ventilation system that draws air from passenger cabin to the cargo compartment, as air exchange reduces CO2 concentration and humidity and controls the compartment temperature. The maximum and minimum shipment temperature (OAT) allowed to carry animals must be observed in the table 1 below. The minimum temperature (SAT) during flight is presented in the table 2. Table 1 - ON GROUND TEMPERATURE LIMITATION Outside Air Temperature (OAT) Minimum Maximum LOAD Temperature Temperature 0 to Half Load -7°C 35°C Half Load to Full -7°C 30°C Load

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Page 2

Live Animals

REVISION 10

AOM-1502-003

Table 2 - INFLIGHT TEMPERATURE LIMITATION Static Air Temperature (SAT) Block Time and Minimum Temperature LOAD 2 hours or below more than 2 hours 0 to 1/3 Part Load -34°C 1/3 Part Load to 2/3 -40°C Part Load -65°C 2/3 Part Load to Full -54°C Load

AIRPLANE OPERATIONS MANUAL

LOADING

DOGS AND CATS The temperature limits for these animals are within 10°C to 30°C range. Considering this and the humidity and CO2 generation by animals metabolism, the number of animals as function of animal mass are stated in the table 3, as follows. Table 3: DOG AND CAT LOAD Dog or Cat mass (kg) Load Limitation 1 140 5 36 10 18 25 8 50 4

[1]

1. Volume capacity is not take into account herein. SMALL BIRDS These are very sensitive animals. This kind of animal is very susceptible to high and low temperatures. It may be necessary to avoid flights at high temperatures during the day and schedule the shipment to night flights. In case of low temperatures during cruise flight, depending on the flight extension, it might be necessary to limit the maximum flight altitude in order to reduce the temperature drop in the baggage compartment. The containers should be placed at some distance from the compartment floor, avoiding the contact with low temperatures coming from the area below the floor. The limitations for the maximum load of these animals are stated in the table 4, as follows.

AOM-1502-003

Table 4: SMALL BIRDS LOAD Mass (kg) Load Limitation 0.03 4500 0.10 1500 0.30 500 1.00 160 2.50 80

[1]

1. Volume capacity is not taken into account herein.

8-80 Copyright © by Embraer. Refer to cover page for details.

REVISION 10

Live Animals

Page 3

LOADING

AIRPLANE OPERATIONS MANUAL

OTHERS

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Page 4

Live Animals

REVISION 10

AOM-1502-003

For the other animals not mentioned in this section, estimations could be developed considering the data presented herein. In case of special animal shipment, Embraer Customer Support may be consulted.

AIRPLANE OPERATIONS MANUAL

LOADING

MAGNETIZED MATERIAL TRANSPORTATION Magnetized materials shall not be transported in the forward cargo compartment. In the after cargo compartment a maximum load of 260 lb (118 kg) is acceptable. If the standby compass is inoperative, the restrictions above are not applicable and magnetized materials may be transported in any cargo compartment in accordance with standard loading limitations.

AOM-1502-003

There is no need for special packaging of magnetized materials and no additional maintenance procedures are required after the flight, such as specific inspections or demagnetization tasks.

8-85 Copyright © by Embraer. Refer to cover page for details.

REVISION 16

Magnetized Material Transportation

Page 1

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AIRPLANE OPERATIONS MANUAL

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Page 2

Magnetized Material Transportation

REVISION 16

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LOADING

DRY ICE TRANSPORTATION This section presents the general conditions for dry ice (carbon solid dioxide) transportation in the forward cargo compartment. The aft cargo compartment does not have adequate ventilation to transport this kind of material. The main reference that regulates and state methods and procedures to handling, appropriate packaging, legal aspects for dry ice transportation, etc. is the IATA Dangerous Goods Regulations.

GENERAL RECOMMENDATIONS It is not recommended to transport dry ice in the cabin and in the galleys. If small quantities are present in the galley, it is required to compute this dry ice mass in the calculation of the total dry ice. Prior to enter into the forward cargo compartment, in which a large amount of dry ice has been loaded, ensure that adequate ventilation is provided checking that the cargo ventilation system is running properly. If this condition is not met, avoid storing dry ice on airplanes for extended periods of time. Similar precautions must be followed when entering any area, adjacent to a cargo compartment, loaded with dry ice. If adequate ventilation is not provided, it is recommended to wear oxygen mask and portable oxygen cylinder inside these areas. In addition, animals should not be transported on a forward cargo compartment loaded with dry ice. Both air conditioning packs (or equivalent ground cart ventilation) shall be operating while persons are on board of an airplane transporting dry ice. In case of failure of the cargo ventilation system during flight, the CO2 sublimated in the cargo compartment may spread in the airplane, but the fresh air flow that comes from the packs dilutes the CO2 concentration below 0.5% CO2 in volume. The airplane can continue the flight normally, but after landing it is required to follow special procedures to ventilate the place in which CO2 buildup is suspected.

AOM-1502-003

Notify the flight crew whenever the amount of dry ice stowed in the cargo compartment exceeds 440 lb (200 kg), as recommended by the IATA Dangerous Goods Regulations. In case of suspect of CO2 leakage from forward cargo compartment, the crew may start Emergency Procedures. If large quantities of dry ice appear in the cabin, it is recommended to start an emergency descent to

8-90 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Dry Ice

Page 1

LOADING

AIRPLANE OPERATIONS MANUAL

FL100 to allow activate the emergency ram air ventilation. It is also necessary to alert personnel for symptoms of excessive CO2 gas concentrations when around dry ice.

LOAD LIMITATIONS Significant concentration of gaseous CO2 by sublimation of dry ice in airplanes may affect the breathing of passengers and crew. For this reason, it is necessary to establish dry ice carriage limits. Dry ice sublimation rates may be affected by many factors, which include: – Amount of insulation surrounding the dry ice; – Type of container; – Compartment ambient temperature; – Amount of dry ice surface area; – Cargo temperature being cooled by the dry ice.

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Page 2

Dry Ice

REVISION 9

AOM-1502-003

Sublimation rates may be obtained from shippers or may be calculated from service experience by measuring the percentage of dry ice sublimated over time. Table 1 provides an example of sublimation rates and the values presented are used as reference only.

LOADING

AIRPLANE OPERATIONS MANUAL Table 1 – SAMPLE SUBLIMATION RATES Approximate Sublimation Rate 1.0% per hour 2.0% per hour

[2]

2.3% per hour

[2]

3.0% per hour

[2]

--4.0% per hour [2] 6.0% per hour [2] 11.0% per hour [3]

Characteristics Parameters FAA Advisory Circular AC 103-4 Paper wrapped 50 pound block Paper wrapped 50 pound block Paper wrapped 50 pound block Exposed 50 pound block Exposed 50 pound block Exposed 50 pound block Exposed 7 pound block

[1]

Ambient Compartment Temperature unknown 0°F 32°F 75°F 0°F 32°F 75°F unknown

1. Sublimation rates are approximate and will vary widely depending on the compartment temperature, packaging, and form (snow, nuggets or blocks). Operators should independently determine their own sublimation rates by contacting the shipper or by determining the percentage of dry ice lost (sublimated) over a given amount of time. 2. Reference values obtained from a manufacturer of dry ice. 3. Reference values calculated by an operator. The following graphics provide recommended maximum allowable dry ice carriage load based upon sublimation rates. In general, higher sublimation rates will reduce the amount of dry ice which may be carried.

AOM-1502-003

The recommended dry ice carriage limits were calculated based upon the limits for CO2 concentration defined by FAR, part 25, Paragraph 25.831. To calculate the carriage limits, it was conservatively assumed that the gaseous CO2 sublimating from a cargo of dry ice dissipates and distributes uniformly throughout the passenger cabin. Additionally, the analysis took into consideration CO2 generated by passenger and crew respiration and the amount introduced from the outside air.

8-90 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Dry Ice

Page 3

LOADING

AIRPLANE OPERATIONS MANUAL

RECOMMENDED DRY ICE MAXIMUM LOAD 2200 2000

MAXIMUM DRY ICE LOADING − lb

1800 1600 1400 1200 1000 800 600 400

0

1

2

3

4

5

6

7

8

9

10

11

DRY ICE SUBLIMATION RATE (% WEIGHT/HOUR) EMBRAER 170

EMBRAER 175

EMBRAER 190

EMBRAER 195

12

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Page 4

Dry Ice

REVISION 9

AOM-1502-003

0

EM170AOM080107C.DGN

200

AIRPLANE OPERATIONS MANUAL

CONFIGURATION DEVIATION LIST

SECTION 9 CONFIGURATION DEVIATION LIST TABLE OF CONTENTS Block

Page

AOM-1502-003

General Information............................................. 9-01 ........... CONFIGURATION DEVIATION LIST.................... 9-01 ...........

1 1

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REVISION 9

Table of Contents

Page 1

CONFIGURATION DEVIATION LIST

AIRPLANE OPERATIONS MANUAL

9-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

CONFIGURATION DEVIATION LIST

CONFIGURATION DEVIATION LIST This Configuration Deviation List contains additional certificate limitations for operation of the airplane without certain secondary airframe and engine parts.

AOM-1502-003

This section is reserved for the operator to include its approved CDL. The CDL is an approved document and published as an Appendix of the AFM. EMBRAER issues an illustrated version of the CDL on the Dispatch Deviation Procedures Manual (DDPM) as Section 4.

9-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

General Information

Page 1

CONFIGURATION DEVIATION LIST

AIRPLANE OPERATIONS MANUAL

9-01 Copyright © by Embraer. Refer to cover page for details.

Page 2

General Information

REVISION 21

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AIRPLANE OPERATIONS MANUAL

MINIMUM EQUIPMENT LIST

SECTION 10 MINIMUM EQUIPMENT LIST TABLE OF CONTENTS Block

Page

AOM-1502-003

General Information............................................. 10-01 ......... GENERAL.............................................................. 10-01 .........

1 1

10-TOC Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Table of Contents

Page 1

MINIMUM EQUIPMENT LIST

AIRPLANE OPERATIONS MANUAL

10-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 9

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AIRPLANE OPERATIONS MANUAL

MINIMUM EQUIPMENT LIST

GENERAL This section is reserved for the operator to include its approved Minimum Equipment List. The Minimum Equipment List – MEL is a list developed to provide for the operation of the airplane with some instruments, equipment or functions inoperative at the beginning of the flight. The MEL is prepared by the operator for his own particular airplane taking account of their airplane configuration and the relevant operational and maintenance conditions in accordance with procedures approved by the Authority. The MEL shall be based upon, but no less restrictive than, the airplane manufacturer MMEL approved by the Authority. The operator is responsible to ensure that the MEL reflects the guidance given in the MMEL on the effects of multiple unserviceabilities.

AOM-1502-003

Operators shall take operational and maintenance procedures referenced in the MMEL into account when preparing their MEL. Appropriate procedures are required to be published as a part of the operator MEL. Embraer provides operational and maintenance procedures in the Dispatch Deviation Procedures Manual – DDPM.

10-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

General Information

Page 1

MINIMUM EQUIPMENT LIST

AIRPLANE OPERATIONS MANUAL

10-01 Copyright © by Embraer. Refer to cover page for details.

Page 2

General Information

REVISION 9

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

SECTION 11 EMERGENCY INFORMATION TABLE OF CONTENTS Block

Page

Introduction.......................................................... 11-INTRO ..

1

Emergency Equipment........................................ 11-05 .........

1

Emergency Equipment Lay Out......................... 11-06 ......... EMERGENCY EQUIPMENT PLAN VIEW............. 11-06 .........

1 1

AOM-1502-003

Oxygen Masks Location...................................... 11-08 ......... 1 PASSENGER OXYGEN MASKS LOCATION........ 11-08 ......... 1 OXYGEN MASK MANUAL DEPLOYMENT........... 11-08 ......... 10 PASSENGER AND CABIN CREW OXYGEN SYSTEM.......................................................... 11-08 ......... 10 Floatable Seats and Life Jackets....................... 11-10 ......... PASSENGER FLOATABLE SEAT AND LIFE JACKET........................................................... 11-10 .........

1

Fire Extinguisher.................................................. 11-15 ......... HALON FIRE EXTINGUISHER............................. 11-15 ......... FIRE EXTINGUISHER OPERATION..................... 11-15 .........

1 1 2

Emergency Locator Transmitter......................... 11-20 ......... EMERGENCY LOCATOR TRANSMITTER (ELT).. 11-20 ......... CONTROLS AND INDICATIONS........................... 11-20 .........

1 1 2

Oxygen, NAV, COMM, Lighting........................... 11-25 ......... LIGHTING.............................................................. 11-25 ......... OXYGEN................................................................ 11-25 ......... NAVIGATION AND COMMUNICATION................. 11-25 .........

1 1 1 1

Least Risk Location............................................. 11-30 ......... LEAST RISK LOCATION....................................... 11-30 .........

1 1

1

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REVISION 20

Table of Contents

Page 1

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

11-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 20

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AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

INTRODUCTION This Section presents emergency information, which may be used at operator’s discretion to develop customized emergency procedures. Such procedures may be associated to contingencies not related to the airplane. Emergency equipment includes those items used during in-flight emergencies (such as first-aid kits and fire extinguishers), and to assist in the airplane evacuation (such as crash hatchet and escape ropes).

AOM-1502-003

The information presented herein is focused on its technical aspects. Being so, it is not mandatory.

11-INTRO Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Page 1

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

11-INTRO Copyright © by Embraer. Refer to cover page for details.

Page 2

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

EQUIPMENT CHECKLIST COCKPIT AREA

AOM-1502-003

Escape Rope.......................................................... ON BOARD Flashlight................................................................. CHECK LED ON Life Vest.................................................................. ON BOARD Hatchet.................................................................... ON BOARD Oxygen Mask/Goggle............................................. CHECK PBE......................................................................... SEALED Fire Extinguisher..................................................... CONDITION

CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Emergency Equipment

Page 1

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

...CONTINUED ESCAPE ROPE

LIFE JACKET (2 BEHIND THE PILOT SEAT AND 1 BEHIND THE COPILOT SEAT)

OXYGEN MASK

ESCAPE ROPE

PBE

EM170AOM110005D.DGN

FIRE EXTINGUISHER

HATCHET

FLASHLIGHT

CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

Page 2

Emergency Equipment

REVISION 21

AOM-1502-003

COCKPIT AREA

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

...CONTINUED !EMBRAER 170 DELTA Configuration

FRONT PASSENGER CABIN AREA Flashlight................................................................. CHECK LED ON First Aid Kit.............................................................. SEALED Life Vest.................................................................. ON BOARD Portable Oxygen Cylinder....................................... CONDITION PBE......................................................................... SEALED Fire Extinguisher..................................................... CONDITION Oxygen Box Deploy Tool........................................ ON BOARD "

!EMBRAER 170 DELTA Configuration

REAR PASSENGER CABIN AREA Flashlight................................................................. CHECK LED ON First Aid Kit.............................................................. SEALED Life Vest.................................................................. ON BOARD Medical Kit.............................................................. SEALED Megaphone............................................................. ON BOARD Portable Oxygen Cylinder....................................... SEALED PBE......................................................................... SEALED Fire Extinguisher..................................................... CONDITION Oxygen Box Deploy Tool........................................ ON BOARD NOTE: Emergency equipment set may be different than the one presented here in this manual depending on specific client request.

AOM-1502-003

"

CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Emergency Equipment

Page 3

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

...CONTINUED !EMBRAER 170 DELTA Configuration

FLASHLIGHT

LIFE VEST

OXYGEN BOX DEPLOY TOOL (UNDER ATTENDANT SEAT)

PBE

FIRST AID KIT

PORTABLE OXYGEN CYLINDER

FIRE EXTINGUISHER (2)

EM170AOM110028A.DGN

WHEEL CHAIR (PROVISIONS FOR)

" CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

Page 4

Emergency Equipment

REVISION 21

AOM-1502-003

FRONT PASSENGER CABIN AREA

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL ...CONTINUED !EMBRAER 170 DELTA Configuration

MEDICAL KIT FLASHLIGHT

PBE (2)

DEFIBRILLATOR (AED) INFANT LIFE VEST (2)

LIFE VEST

SEAT BELT EXTENSION (2)

MEGAPHONE

EM170AOM110029A.DGN

OXYGEN BOX DEPLOY TOOL

INFANT LIFE VEST (4)

FIRE EXTINGUISHER (2) FIRST AID KIT PORTABLE OXYGEN CYLINDER

AOM-1502-003

REAR PASSENGER CABIN AREA

" CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Emergency Equipment

Page 5

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

...CONTINUED !EMBRAER 170 U S AIRWAYS Configuration

FRONT PASSENGER CABIN AREA (72 PAX) Flashlight................................................................. CHECK LED ON First Aid Kit.............................................................. SEALED Life Vest.................................................................. ON BOARD Medical Kit.............................................................. SEALED Portable Oxygen Cylinder....................................... CONDITION PBE......................................................................... SEALED Fire Extinguisher..................................................... CONDITION Oxygen Box Deploy Tool........................................ ON BOARD "

!EMBRAER 170 U S AIRWAYS Configuration

REAR PASSENGER CABIN AREA (72 PAX) Defibrillator.............................................................. ON BOARD Flashlight................................................................. CHECK LED ON First Aid Kit.............................................................. SEALED Life Vest.................................................................. ON BOARD Medical Kit.............................................................. SEALED Megaphone............................................................. ON BOARD Portable Oxygen Cylinder....................................... SEALED PBE......................................................................... SEALED Fire Extinguisher..................................................... CONDITION Oxygen Box Deploy Tool........................................ ON BOARD NOTE: Emergency equipment set may be different than the one presented here in this manual depending on specific client request.

CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

Page 6

Emergency Equipment

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

...CONTINUED !EMBRAER 170 U S AIRWAYS Configuration

FIRST AID KIT (OVERHEAD BIN)

OXYGEN BOTTLE (2) (OVERHEAD BIN)

FIRE EXTINGUISHERS (2) (OVERHEAD BIN)

LIFE VEST (UNDER ATTENDANT SEAT)

OXYGEN BOX DEPLOY TOOL (UNDER ATTENDANT SEAT)

EM170AOM110022A.DGN

FLASHLIGHT (BESIDE ATTENDANT SEAT)

PBE (OVERHEAD BIN)

AOM-1502-003

FRONT PASSENGER CABIN AREA (72 PAX)

" CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Emergency Equipment

Page 7

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

...CONTINUED !EMBRAER 170 U S AIRWAYS Configuration

FIRE EXTINGUISHER

FLASHLIGHT MEDICAL KIT DEFIBRILLATOR (AED)

OXYGEN BOTTLE

INFANT LIFE VEST (10) LIFE VEST PBE

OXYGEN BOX DEPLOY TOOL

SEAT BELT EXTENSION (4)

EM170AOM110023A.DGN

FIRST AID KIT

MEGAPHONE

PBE

" CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

Page 8

Emergency Equipment

REVISION 21

AOM-1502-003

REAR PASSENGER CABIN AREA (72 PAX)

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

...CONTINUED !EMBRAER 170 U S AIRWAYS Configuration

FRONT PASSENGER CABIN AREA (76 PAX) Automatic Fire Extinguisher.................................... ON BOARD Demo Kit................................................................. ON BOARD Demo Masks........................................................... ON BOARD Fire Extinguishers................................................... CONDITION First Aid Kit.............................................................. SEALED Flashlight................................................................. CHECK LED ON Life Vest.................................................................. ON BOARD Manual Deployment Tool........................................ ON BOARD Portable Oxygen Cylinder....................................... CONDITION PBE......................................................................... SEALED Extensions............................................................... ON BOARD "

!EMBRAER 170 U S AIRWAYS Configuration

REAR PASSENGER CABIN AREA (76 PAX) Automatic Fire Extinguisher.................................... ON BOARD Defibrillator.............................................................. ON BOARD Fire Extinguishers................................................... CONDITION First Aid Kit.............................................................. SEALED Flashlight................................................................. CHECK LED ON Infant Life Vests...................................................... ON BOARD Life Vest.................................................................. ON BOARD Manual Deployment Tool........................................ ON BOARD Medical Kit.............................................................. SEALED Megaphone............................................................. ON BOARD Portable Oxygen Cylinders..................................... SEALED PBE......................................................................... SEALED Wheelchair.............................................................. ON BOARD NOTE: Emergency equipment set may be different than the one presented here in this manual depending on specific client request.

AOM-1502-003

"

CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Emergency Equipment

Page 9

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

...CONTINUED !EMBRAER 170 U S AIRWAYS Configuration

SEAT BELT EXTENSION (4)

DEMO MASK (2)

FLASHLIGHT AUTOMATIC FIRE EXTINGUISHER

DEMO KIT PBE

MANUAL DEPLOYMENT TOOL (UNDER ATTENDANT SEAT)

FIRE EXTINGUISHER (2)

EM170AOM110165A.DGN

FIRST AID KIT

LIFE VEST

PORTABLE OXYGEN CYLINDER

" CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

Page 10

Emergency Equipment

REVISION 21

AOM-1502-003

FRONT PASSENGER CABIN AREA (76 PAX)

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

...CONTINUED !EMBRAER 170 U S AIRWAYS Configuration

AUTOMATIC FIRE EXTINGUISHER MEDICAL KIT WHEELCHAIR INFANT LIFE VEST (10)

FLASHLIGHT

MEGAPHONE

EM170AOM110166B.DGN

MANUAL DEPLOYMENT TOOL (UNDER ATTENDANT SEAT)

FIRST AID KIT PORTABLE OXYGEN CYLINDER DEFIBRILLATOR

LIFE VEST

AOM-1502-003

REAR PASSENGER CABIN AREA (76 PAX)

" CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Emergency Equipment

Page 11

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

...CONTINUED !EMBRAER 170 U S AIRWAYS Configuration

FIRE EXTINGUISHER

EM170AOM110167A.DGN

FIRE EXTINGUISHER

PBE

PBE

REAR PASSENGER CABIN AREA (76 PAX)

CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

Page 12

Emergency Equipment

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

...CONTINUED !EMBRAER 170 DELTA Configuration

FRONT PASSENGER CABIN AREA Automatic Fire Extinguisher.................................... ON BOARD Demonstration Equipment (Operator installed)...... ON BOARD ELT.......................................................................... ON BOARD Fire Extinguishers................................................... CONDITION First Aid Kit.............................................................. SEALED Flashlight................................................................. CHECK LED ON Life Rafts................................................................. ON BOARD Life Vest.................................................................. ON BOARD Manual Deployment Tool........................................ ON BOARD Portable Oxygen Cylinder....................................... CONDITION Protective Breathing Equipment (PBE).................. SEALED "

REAR PASSENGER CABIN AREA Automatic Fire Extinguisher.................................... ON BOARD Defibrillator.............................................................. ON BOARD Fire Extinguishers................................................... CONDITION First Aid Kit.............................................................. SEALED Flashlight................................................................. CHECK LED ON Infant Life Vests...................................................... ON BOARD Life Vest.................................................................. ON BOARD Manual Deployment Tool........................................ ON BOARD Medical Kit.............................................................. SEALED Megaphone............................................................. ON BOARD Portable Oxygen Cylinder....................................... CONDITION Protective Breathing Equipment (PBE).................. SEALED Weelchair................................................................ ON BOARD

AOM-1502-003

NOTE: Emergency equipment set may be different than the one presented here in this manual depending on specific client request.

CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Emergency Equipment

Page 13

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

...CONTINUED !EMBRAER 170 DELTA Configuration

AUTOMATIC FIRE EXTINGUISHER DEMONSTRATION EQUIPMENT (OPERATOR INSTALLED)

FLASHLIGHT

FIRE EXTINGUISHER

MANUAL DEPLOYMENT TOOL (UNDER ATTENDANT SEAT)

PBE

FIRST AID KIT

PORTABLE OXYGEN CYLINDER

LIFE VEST

LIFE RAFT / SURVIVAL KIT

EM170AOM110200A.DGN

ELT

" CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

Page 14

Emergency Equipment

REVISION 21

AOM-1502-003

FRONT PASSENGER AREA

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

...CONTINUED !EMBRAER 170 DELTA Configuration

AUTOMATIC FIRE EXTINGUISHER MEDICAL KIT

WHEELCHAIR

INFANT LIFE VEST (10)

FLASHLIGHT

MEGAPHONE

EM170AOM110201A.DGN

MANUAL DEPLOYMENT TOOL (UNDER ATTENDANT SEAT)

FIRST AID KIT PORTABLE OXYGEN CYLINDER DEFIBRILLATOR

LIFE VEST

AOM-1502-003

REAR PASSENGER AREA

" CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Emergency Equipment

Page 15

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

...CONTINUED !EMBRAER 170 DELTA Configuration

FIRE EXTINGUISHER FIRE EXTINGUISHER

PBE

EM170AOM110206A.DGN

PBE

" CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

Page 16

Emergency Equipment

REVISION 21

AOM-1502-003

REAR PASSENGER AREA

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

...CONTINUED !EMBRAER 175 U S AIRWAYS Configuration

FRONT PASSENGER CABIN AREA Automatic Fire Extinguisher.................................... ON BOARD Demo Kits............................................................... ON BOARD Fire Extinguishers................................................... CONDITION First Aid Kit.............................................................. SEALED Flashlight................................................................. CHECK LED ON Life Vest.................................................................. ON BOARD Manual Deployment Tool........................................ ON BOARD Portable Oxygen Cylinder....................................... CONDITION PBE......................................................................... SEALED Seat Belt Extensions............................................... ON BOARD "

!EMBRAER 175 U S AIRWAYS Configuration

REAR PASSENGER CABIN AREA Automatic Fire Extinguisher.................................... ON BOARD Defibrillator.............................................................. ON BOARD Fire Extinguishers................................................... CONDITION First Aid Kit.............................................................. SEALED Flashlight................................................................. CHECK LED ON Infant Life Vest........................................................ ON BOARD Life Vest.................................................................. ON BOARD Manual Deployment Tool........................................ ON BOARD Medical Kit.............................................................. SEALED Megaphone............................................................. ON BOARD Portable Oxygen Cylinders..................................... CONDITION PBE......................................................................... SEALED Wheelchair.............................................................. ON BOARD NOTE: Emergency equipment set may be different than the one presented here in this manual depending on specific client request.

AOM-1502-003

"

CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Emergency Equipment

Page 17

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

...CONTINUED !EMBRAER 175 U S AIRWAYS Configuration

PBE

AUTOMATIC FIRE EXTINGUISHER

FIRST AID KIT FIRE EXTINGUISHER FIRE EXTINGUISHER

FLASHLIGHT

MANUAL DEPLOYMENT TOOL (UNDER ATTENDANT SEAT)

DEMO KIT (2) LIFE VEST

PORTABLE OXYGEN CYLINDER

EM170AOM110159A.DGN

SEAT BELT EXTENSION (4)

" CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

Page 18

Emergency Equipment

REVISION 21

AOM-1502-003

FRONT PASSENGER CABIN AREA

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

...CONTINUED !EMBRAER 175 U S AIRWAYS Configuration

AUTOMATIC FIRE EXTINGUISHER

MEDICAL KIT

WHEELCHAIR

DEFIBRILLATOR

FLASHLIGHT

MANUAL DEPLOYMENT TOOL (UNDER ATTENDANT SEAT)

PBE

PORTABLE OXYGEN CYLINDER

EM170AOM110160A.DGN

FIRE EXTINGUISHER

FIRE EXTINGUISHER PORTABLE OXYGEN CYLINDER

LIFE VEST

AOM-1502-003

REAR PASSENGER CABIN AREA

" CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Emergency Equipment

Page 19

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

...CONTINUED !EMBRAER 175 U S AIRWAYS Configuration

FIRST AID KIT

MEGAPHONE

EM170AOM110163A.DGN

INFANT LIFE VEST (3)

INFANT LIFE VEST (3)

" CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

Page 20

Emergency Equipment

REVISION 21

AOM-1502-003

REAR PASSENGER CABIN AREA

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

...CONTINUED !EMBRAER 175 DELTA Configuration

FRONT PASSENGER CABIN AREA Automatic Fire Extinguisher.................................... ON BOARD Demo Kit................................................................. ON BOARD Fire Extinguishers................................................... CONDITION First Aid Kit.............................................................. SEALED Flashlight................................................................. CHECK LED ON Life Vests................................................................ ON BOARD Manual Deployment Tool........................................ ON BOARD Portable Oxygen Cylinder....................................... CONDITION PBE......................................................................... SEALED Seat Belt Extension................................................ ON BOARD "

!EMBRAER 175 DELTA Configuration

REAR PASSENGER CABIN AREA Automatic Fire Extinguisher.................................... ON BOARD Defribillator.............................................................. ON BOARD Demo Kit................................................................. ON BOARD Fire Extinguishers................................................... CONDITION First Aid Kit.............................................................. SEALED Flashlights............................................................... CHECK LED ON Infant Life Vests...................................................... ON BOARD Life Vests................................................................ ON BOARD Manual Deployment Tools...................................... ON BOARD Medical Kit.............................................................. ON BOARD Megaphone............................................................. ON BOARD Portable Oxygen Cylinders..................................... CONDITION PBE......................................................................... SEALED Wheelchair.............................................................. ON BOARD NOTE: Emergency equipment set may be different than the one presented here in this manual depending on specific client request.

AOM-1502-003

"

CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Emergency Equipment

Page 21

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

...CONTINUED !EMBRAER 175 DELTA Configuration

AUTOMATIC FIRE EXTINGUISHER SEAT BELT EXTENSION (4)

FLASHLIGHT PBE

DEMO KIT (2) (PROVISIONS)

MANUAL DEPLOYMENT TOOL (UNDER ATTENDANT SEAT)

EM170AOM110282A.DGN

FIRST AID KIT

LIFE VEST FIRE EXTINGUISHER (2) (HALON)

PORTABLE OXYGEN CYLINDER

" CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

Page 22

Emergency Equipment

REVISION 21

AOM-1502-003

FWD PASSENGER CABIN AREA

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

...CONTINUED !EMBRAER 175 DELTA Configuration

MEDICAL KIT WHEELCHAIR

INFANT LIFE VEST (6)

AUTOMATIC FIRE EXTINGUISHER DEFIBRILLATOR

DEMO KIT (PROVISIONS)

FLASHLIGHT

MEGAPHONE

PORTABLE OXYGEN CYLINDER

EM170AOM110283A.DGN

MANUAL DEPLOYMENT TOOL (UNDER ATTENDANT SEAT)

FIRST AID KIT LIFE VEST

AOM-1502-003

REAR PASSENGER CABIN AREA

" CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Emergency Equipment

Page 23

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

...CONTINUED !EMBRAER 175 DELTA Configuration

FIRE EXTINGUISHER (HALON) FIRE EXTINGUISHER (HALON)

EM170AOM110284A.DGN

PBE

PBE

" CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

Page 24

Emergency Equipment

REVISION 21

AOM-1502-003

REAR PASSENGER CABIN AREA

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

...CONTINUED !EMBRAER 175 AMERICAN EAGLE Configuration

FRONT PASSENGER CABIN AREA Automatic Fire Extinguisher.................................... ON BOARD Flashlight................................................................. CHECK LED ON Life Vest.................................................................. ON BOARD Manual Deployment Tool........................................ ON BOARD First Aid Kit.............................................................. SEALED Fire Extinguishers (Halon)...................................... CONDITION Portable Oxygen Cylinder....................................... CONDITION Protective Breathing Equipment (PBE).................. SEALED "

!EMBRAER 175 AMERICAN EAGLE Configuration

REAR PASSENGER CABIN AREA Automatic Fire Extinguisher.................................... ON BOARD Flashlights............................................................... CHECK LED ON Manual Deployment Tools...................................... ON BOARD Life Vests................................................................ ON BOARD Fire Extinguishers (Halon)...................................... CONDITION Protective Breathing Equipment (PBE).................. SEALED Megaphone............................................................. ON BOARD Portable Oxygen Cylinder....................................... CONDITION First Aid Kit.............................................................. SEALED ELT.......................................................................... ON BOARD Medical Kit.............................................................. SEALED Defribillator.............................................................. ON BOARD Weelchair................................................................ ON BOARD NOTE: Emergency equipment set may be different than the one presented here in this manual depending on specific client request.

AOM-1502-003

"

CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Emergency Equipment

Page 25

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

...CONTINUED

FLASHLIGHT

LIFE VEST

PBE

FIRST AID KIT

PORTABLE OXYGEN CYLINDER

FIRE EXTINGUISHER (2)

EM170AOM110571A.DGN

OXYGEN BOX DEPLOY TOOL (UNDER ATTENDANT SEAT)

CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

Page 26

Emergency Equipment

REVISION 21

AOM-1502-003

FWD PASSENGER CABIN AREA

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

...CONTINUED

AUTOMATIC FIRE EXTINGUISHER WHEELCHAIR MEDICAL KIT

ELT

FLASHLIGHT

MEGAPHONE

EM170AOM110572A.DGN

MANUAL DEPLOYMENT TOOL (UNDER ATTENDANT SEAT)

FIRST AID KIT PORTABLE OXYGEN CYLINDER (2) DEFIBRILLATOR

LIFE VEST

AOM-1502-003

REAR PASSENGER CABIN AREA

CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Emergency Equipment

Page 27

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

...CONTINUED

FIRE EXTINGUISHER FIRE EXTINGUISHER

PBE

EM170AOM110206A.DGN

PBE

CONTINUED...

11-05 Copyright © by Embraer. Refer to cover page for details.

Page 28

Emergency Equipment

REVISION 21

AOM-1502-003

REAR PASSENGER CABIN AREA

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

...CONTINUED

OXYGEN BOX DEPLOY TOOL

LIFE VEST

EM170AOM110036A.DGN

FLASHLIGHT

AOM-1502-003

REAR FLIGHT ATTENDANT SEAT (CC3)

11-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Emergency Equipment

Page 29

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

11-05 Copyright © by Embraer. Refer to cover page for details.

Page 30

Emergency Equipment

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

EMERGENCY EQUIPMENT PLAN VIEW FORWARD

!EMBRAER 170 DELTA Configuration

10

11

12

4

3

2

13

7 6

5

ITEM 1 2

AOM-1502-003

3 4 5 6 7 8

1 1 1 1 1 1 2 1 1 1 1

1

EM170AOM110030A.DGN

9

8

EQUIPMENT Flashlight Life vest Oxygen box deploy tool Fire Extinguisher PBE Hatchet Life vests Escape Rope Flashlight Pilot Oxygen Mask Copilot Oxygen Mask

11-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Emergency Equipment Lay Out

Page 1

EMERGENCY INFORMATION

ITEM 9 10 11 12

13

1 1 1 1 2 1 1 1 1

AIRPLANE OPERATIONS MANUAL

EQUIPMENT Flashlight Escape Rope Life vest Observer Oxygen Mask Fire Extinguishers First Aid Kit PBE Portable Oxygen Cylinder Provision for wheelchair

11-06 Copyright © by Embraer. Refer to cover page for details.

Page 2

Emergency Equipment Lay Out

REVISION 17

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

AFT

!EMBRAER 170 DELTA Configuration

16

ITEM 14

15

AOM-1502-003

16

1 1 1 1 1 4 1 1 1

15

EM170AOM110031A.DGN

17

14

EQUIPMENT Flashlight Life vest Oxygen box deploy tool Fire Extinguisher First Aid Kit Infant Life Vests PBE Portable Oxygen Cylinder Medical Kit

11-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Emergency Equipment Lay Out

Page 3

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

ITEM

17

1 1 2 2 1 1

EQUIPMENT Defibrillator (AED) Fire Extinguisher Infant Life Vests Infant Seat Belts Megaphone PBE

11-06 Copyright © by Embraer. Refer to cover page for details.

Page 4

Emergency Equipment Lay Out

REVISION 17

AOM-1502-003

"

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

FORWARD

!EMBRAER 170 DELTA Configuration

11

9

8

12

7

13

15

14

6

4

3

2

1

AOM-1502-003

5

EM170AOM110202A.DGN

10

11-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Emergency Equipment Lay Out

Page 5

EMERGENCY INFORMATION

ITEM 1 2 3 4 5 6 7 8 9 10 11 12 13 14

15

AIRPLANE OPERATIONS MANUAL

EQUIPMENT (OVERHEAD BIN) Demonstration Equipment (Operator installed) 1 Flashlight 1 Life Vest 1 Manual Deployment Tool 1 Automatic Fire Extinguisher 1 Fire Extinguisher 1 PBE 1 Hatchet 2 Life Vests 1 Escape Rope 1 Flashlight 1 Pilot Oxygen Mask 1 Copilot Oxygen Mask 1 Flashlight 1 Escape Rope 1 Life Vest 1 Observer Oxygen Mask 1 ELT 2 Fire Extinguishers 1 First Aid Kit 3 Life Rafts 1 PBE 1 Portable Oxygen Cylinder

11-06 Copyright © by Embraer. Refer to cover page for details.

Page 6

Emergency Equipment Lay Out

REVISION 17

AOM-1502-003

"

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

AFT

!EMBRAER 170 DELTA Configuration

19

ITEM 16 17

18

19

AOM-1502-003

20

21

18

17

22

EM170AOM110168A.DGN

20

16

EQUIPMENT 1 Automatic Fire Extinguisher 1 Flashlight 1 Life Vest 1 Manual Deployment Tool 1 Fire Extinguisher 1 First Aid Kit 1 PBE (OVERHEAD BIN) 1 Defibrillator 1 Medical Kit 10 Infant Life Vests

11-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Emergency Equipment Lay Out

Page 7

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

ITEM 21 22

1 1 1 1 1

EQUIPMENT Fire Extinguisher Megaphone Portable Oxygen Cylinder PBE Weelchair

78 PAX Life Vests (one under each seat).

11-06 Copyright © by Embraer. Refer to cover page for details.

Page 8

Emergency Equipment Lay Out

REVISION 17

AOM-1502-003

"

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

FORWARD (72 PAX)

!EMBRAER 170 U S AIRWAYS Configuration

10

11

12

13

4

3

14

8 7

ITEM 1

2 3

AOM-1502-003

4 5 6

6

5

2

1

EM170AOM110012A.DGN

9

EQUIPMENT (OVERHEAD BIN) 2 Demo Pounches 2 Fire Extinguishers 1 PBE 1 Flashlight 1 Life vest 1 Oxygen box deploy tool 1 PBE 1 Fire Extinguisher 1 Hatchet 2 Life vests 1 Escape Rope

11-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Emergency Equipment Lay Out

Page 9

EMERGENCY INFORMATION

ITEM 7 8 9 10 11 12 13 14

AIRPLANE OPERATIONS MANUAL

EQUIPMENT 1 Flashlight 1 Pilot Oxygen Mask 1 Copilot Oxygen Mask 1 Flashlight 1 Escape Rope 1 Life vest 1 Observer Oxygen Mask (OVERHEAD BIN) 1 First Aid Kit 2 Portable Oxygen Cylinders

11-06 Copyright © by Embraer. Refer to cover page for details.

Page 10

Emergency Equipment Lay Out

REVISION 17

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

AFT (72 PAX)

!EMBRAER 170 U S AIRWAYS Configuration

17

ITEM 15

16

AOM-1502-003

17

16

15

EM170AOM110013A.DGN

18

EQUIPMENT 1 Flashlight 1 Life vest 1 Oxygen box deploy tool 1 Fire Extinguisher 4 Seat Belt Extensions 1 PBE 1 Megaphone (OVERHEAD BIN) 1 AED 1 Medical Kit

11-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Emergency Equipment Lay Out

Page 11

EMERGENCY INFORMATION

ITEM

18

AIRPLANE OPERATIONS MANUAL

EQUIPMENT 1 First Aid Kit 1 Portable Oxygen Cylinder 1 Fire Extinguisher 1 PBE 10 Infant Life Vests

11-06 Copyright © by Embraer. Refer to cover page for details.

Page 12

Emergency Equipment Lay Out

REVISION 17

AOM-1502-003

"

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

FORWARD (76 PAX)

!EMBRAER 170 U S AIRWAYS Configuration

11

12

13

14

5

4

15

9 8

ITEM 1

2 3 4

AOM-1502-003

5 6

7

6

3

2

1

EM170AOM110169A.DGN

10

EQUIPMENT (OVERHEAD BIN) 1 Demo Kit 2 Demo Masks 4 Seat Belt Extensions 1 Flashlight 1 Life Vest 1 Manual Deployment Tool 1 Automatic Fire Extinguisher 1 PBE 1 Fire Extinguisher 1 Hatchet 2 Life Vests

11-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Emergency Equipment Lay Out

Page 13

EMERGENCY INFORMATION

ITEM 7 8 9 10 11 12 13 14

15

AIRPLANE OPERATIONS MANUAL

EQUIPMENT 1 Escape Rope 1 Flashlight 1 Pilot Oxygen Mask 1 Copilot Oxygen Mask 1 Flashlight 1 Escape Rope 1 Life Vest 1 Observer Oxygen Mask (OVERHEAD BIN) 1 Fire Extinguisher 1 First Aid Kit 1 Portable Oxygen Cylinder 1 PBE

11-06 Copyright © by Embraer. Refer to cover page for details.

Page 14

Emergency Equipment Lay Out

REVISION 17

AOM-1502-003

"

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

AFT (76 PAX)

!EMBRAER 170 U S AIRWAYS Configuration

19

ITEM 16 17

18

19

AOM-1502-003

20

21

18

17

22

16

EM170AOM110168A.DGN

20

EQUIPMENT 1 Automatic Fire Extinguisher 1 Flashlight 1 Life Vest 1 Manual Deployment Tool 1 Fire Extinguisher 1 First Aid Kit 1 Portable Oxygen Cylinder 1 PBE (OVERHEAD BIN) 1 Defibrillator 1 Medical Kit 10 Infant Life Vests

11-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Emergency Equipment Lay Out

Page 15

EMERGENCY INFORMATION

ITEM 21 22

1 1 1 1 1

AIRPLANE OPERATIONS MANUAL

EQUIPMENT Fire Extinguisher Megaphone Portable Oxygen Cylinder PBE Wheelchair

11-06 Copyright © by Embraer. Refer to cover page for details.

Page 16

Emergency Equipment Lay Out

REVISION 17

AOM-1502-003

"

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

FORWARD

!EMBRAER 175 U S AIRWAYS Configuration

11

9

8

12

7

13

15

14

6

4

3

2

1

5

ITEM 1

2 3 4

AOM-1502-003

5 6

EM170AOM110161A.DGN

10

EQUIPMENT 1 Defibrillator 1 Medical Kit 4 Seat Belt Extensions 2 Demo Kits 1 Flashlight 1 Life Vest 1 Manual Deployment Tool 1 Automatic Fire Extinguisher 1 Fire Extinguisher 1 PBE 1 Hatchet 2 Life Vests

11-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Emergency Equipment Lay Out

Page 17

EMERGENCY INFORMATION

ITEM 7 8 9 10 11 12 13 14 15

1 1 1 1 1 1 1 1 2 1 1 1

AIRPLANE OPERATIONS MANUAL

EQUIPMENT Escape Rope Flashlight Pilot Oxygen Mask Copilot Oxygen Mask Flashlight Escape Rope Life Vest Observer Oxygen Mask Fire Extinguishers First Aid Kit PBE Portable Oxygen Cylinder

11-06 Copyright © by Embraer. Refer to cover page for details.

Page 18

Emergency Equipment Lay Out

REVISION 17

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

AFT

!EMBRAER 175 U S AIRWAYS Configuration

19

ITEM 16 17

18

AOM-1502-003

19

18

17

21

16

EM170AOM110162A.DGN

20

EQUIPMENT 1 Automatic Fire Extinguisher 1 Flashlight 1 Life Vest 1 Oxygen Box Deployment Tool 3 Infant Life Vests 1 Fire Extinguisher 1 First Aid Kit 1 Portable Oxygen Cylinder 1 PBE 1 Defibrillator 1 Medical Kit

11-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Emergency Equipment Lay Out

Page 19

EMERGENCY INFORMATION

ITEM

20

21

1 1 3 1 1 1

AIRPLANE OPERATIONS MANUAL

EQUIPMENT Fire Extinguisher Megaphone Infant Life Vests Portable Oxygen Cylinder PBE Wheelchair

86 PAX Life Vests (one under each seat).

11-06 Copyright © by Embraer. Refer to cover page for details.

Page 20

Emergency Equipment Lay Out

REVISION 17

AOM-1502-003

"

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

FORWARD

!EMBRAER 175 DELTA Configuration

11

9

8

12

7

13

15

14

6

4

3

2

EM170AOM110202A.DGN

10

1

5

ITEM 1 2 3 4

AOM-1502-003

5 6 7 8

EQUIPMENT 2 Demo Kits (provisions) 4 Seat Belt Extensions 1 Flashlight 1 Life Vest 1 Oxygen box deploy tool 1 Automatic Fire Extinguisher 1 PBE 1 Fire Extinguisher 1 Axe 2 Life Vests 1 Escape Rope 1 Flashlight

11-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Emergency Equipment Lay Out

Page 21

EMERGENCY INFORMATION

ITEM 9 10 11 12 13 14 15

AIRPLANE OPERATIONS MANUAL

1 1 1 1 1 1 2 1 1 1

EQUIPMENT Pilot Oxygen Mask Copilot Oxygen Mask Flashlight Escape Rope Life Vest Observer Oxygen Mask Fire Extinguishers (Halon) First Aid Kit PBE Portable Oxygen Cylinder

11-06 Copyright © by Embraer. Refer to cover page for details.

Page 22

Emergency Equipment Lay Out

REVISION 17

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

AFT

!EMBRAER 175 DELTA Configuration

19

ITEM 16 17

18

AOM-1502-003

19

22

21

18

17

EM170AOM110285A.DGN

20

16

EQUIPMENT 1 Automatic Fire Extinguisher 1 Flashlight 1 Life Vest 1 Oxygen Box deploy tool 1 Fire Extinguisher (Halon) 1 First Aid Kit 1 PBE 1 Portable Oxygen Cylinder (OVERHEAD BIN) 1 Defibrillator 1 Medical Kit

11-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Emergency Equipment Lay Out

Page 23

EMERGENCY INFORMATION

ITEM 20

21 22

AIRPLANE OPERATIONS MANUAL EQUIPMENT (OVERHEAD BIN) 6 Infant Life Vests 1 Demo Kit (provisions) 1 Fire Extinguisher (Halon) 1 Megaphone 1 Portable Oxygen Cylinder 1 PBE 1 Wheelchair

11-06 Copyright © by Embraer. Refer to cover page for details.

Page 24

Emergency Equipment Lay Out

REVISION 17

AOM-1502-003

"

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

FORWARD

!EMBRAER 175 AMERICAN EAGLE Configuration

10

11

12

4

3

2

13

7 6

5

ITEM 1 2

AOM-1502-003

3 4 5 6 7 8 9

1

EM170AOM110030A.DGN

9

8

EQUIPMENT 1 1 1 1 1 1 2 1 1 1 1 1

Flashlight Life vest Oxygen box deploy tool Fire Extinguisher PBE Hatchet Life vests Escape Rope Flashlight Pilot Oxygen Mask Copilot Oxygen Mask Flashlight

11-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Emergency Equipment Lay Out

Page 25

EMERGENCY INFORMATION

ITEM 10 11 12 13

1 1 1 2 1 1 1

AIRPLANE OPERATIONS MANUAL

EQUIPMENT Escape Rope Life vest Observer Oxygen Mask Fire Extinguishers First Aid Kit PBE Portable Oxygen Cylinder "

AFT

!EMBRAER 175 AMERICAN EAGLE Configuration

17

16

20

15

14

EQUIPMENT 1 Automatic Fire Extinguisher

11-06 Copyright © by Embraer. Refer to cover page for details.

Page 26

Emergency Equipment Lay Out

REVISION 17

AOM-1502-003

ITEM 14

19

EM170AOM110573A.DGN

18

AIRPLANE OPERATIONS MANUAL

ITEM 15

16

17

18

19 20

1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1

EMERGENCY INFORMATION

EQUIPMENT Flashlight Life Vest Manual Deployment Tool First Aid Kit Portable Oxygen Cylinder Fire Extinguisher PBE Medical Kit ELT Defibrillator Megaphone Portable Oxygen Cylinder Fire Extinguisher PBE Flashlight Life Vest Manual Deployment Tool Provision for wheelchair

76 Pax Life Vests (one under each seat)

AOM-1502-003

"

11-06 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Emergency Equipment Lay Out

Page 27

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

11-06 Copyright © by Embraer. Refer to cover page for details.

Page 28

Emergency Equipment Lay Out

REVISION 17

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

PASSENGER OXYGEN MASKS LOCATION

AOM-1502-003

Oxygen masks are provided for each passenger for use in case of emergency. They are located in the dispensing units above each seat row and are automatically or manually deployed.

11-08 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Oxygen Masks Location

Page 1

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

QUANTITY AND LOCATION !EMBRAER 170 DELTA Configuration

2 2

2

3

3

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3 3 2 2

70 SEATS INTERIOR ARRANGEMENT

"

11-08 Copyright © by Embraer. Refer to cover page for details.

Page 2

Oxygen Masks Location

REVISION 21

AOM-1502-003

EM170AOM110019B.DGN

2

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

!EMBRAER 170 DELTA Configuration

2 2 3

3

3

3

3

3

3

3

3

3

3

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3

3

3

3

3

3

3

3

3 2 2 EM170AOM110164B.DGN

2

AOM-1502-003

76 SEATS INTERIOR ARRANGEMENT

"

11-08 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Oxygen Masks Location

Page 3

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

!EMBRAER 175 U S AIRWAYS Configuration

2 2 3

3

3

3

3

3

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3

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3

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3

3

3

3

3

3

3

3

3

3

3 2 2 EM170AOM110158B.DGN

2

"

11-08 Copyright © by Embraer. Refer to cover page for details.

Page 4

Oxygen Masks Location

REVISION 21

AOM-1502-003

86 SEATS INTERIOR ARRANGEMENT

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

!EMBRAER 175 DELTA Configuration

2 2 3

3

3

3

3

3

3

3

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3

3

3

3

3

3

3

3

3

2 2 EM170AOM110281B.DGN

2

AOM-1502-003

76 SEATS INTERIOR ARRANGEMENT

"

11-08 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Oxygen Masks Location

Page 5

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

!EMBRAER 170 U S AIRWAYS Configuration

2 3

3

3

3

3

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3

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3

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3

3

3

2

EM170AOM110015A.DGN

2

"

11-08 Copyright © by Embraer. Refer to cover page for details.

Page 6

Oxygen Masks Location

REVISION 21

AOM-1502-003

72 SEATS INTERIOR ARRANGEMENT

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

!EMBRAER 170 U S AIRWAYS Configuration

2 2 3

3

3

3

3

3

3

3

3

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3

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3

3

3

3

3

3

3 2 2 EM170AOM110164B.DGN

2

AOM-1502-003

76 SEATS INTERIOR ARRANGEMENT

"

11-08 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Oxygen Masks Location

Page 7

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

!EMBRAER 175 AMERICAN EAGLE Configuration

2 2

2

3

3

3

3

3

3

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3

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3

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3

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3

3

3

3

3

3

2

EM170AOM110569A.DGN

2

"

11-08 Copyright © by Embraer. Refer to cover page for details.

Page 8

Oxygen Masks Location

REVISION 21

AOM-1502-003

76 SEATS INTERIOR ARRANGEMENT

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

!EMBRAER 175 UNITED Configuration

2 2

2

3

3

3

3

3

3

3

3

3

3

3

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3

3

3

3

3

3

3

2

EM170AOM110616A.DGN

2

AOM-1502-003

76 SEATS INTERIOR ARRANGEMENT

"

11-08 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Oxygen Masks Location

Page 9

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

OXYGEN MASK MANUAL DEPLOYMENT A manual deploy tool is provided near each cabin crew station. Placards indicate their location. If a dispensing unit door fails to open and the automatic deployment of passenger oxygen masks is not commanded, insert the manual deploy tool in the small hole diameter in the PSU to manually actuate the electrical latch. The masks are deployed and oxygen is available to the occupant.

DISPENSING UNITS ATTENDANT CALL BUTTON

MANUAL DEPLOY TOOL

PASSENGER SIGNS GASPER OUTLETS

PASSENGER LIGHT BUTTON

EM170AOM140027B.DGN

INDIVIDUAL READING LIGHTS

PASSENGER SERVICE UNIT

11-08 Copyright © by Embraer. Refer to cover page for details.

Page 10

Oxygen Masks Location

REVISION 21

AOM-1502-003

PASSENGER AND CABIN CREW OXYGEN SYSTEM

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

PASSENGER OXYGEN SYSTEM

DISPENSING UNIT

MASK RETAINER

GREEN IN−LINE FLOW INDICATOR

ELASTIC STRAP

OXYGEN MASK

MASK RESERVOIR BAG

CORD

EM170AOM140184C.DGN

ACTUATOR PIN DISCONNECTED

HOSE

AOM-1502-003

PASSENGER OXYGEN MASKS DEPLOYED AND MASKS RETAINERS

11-08 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Oxygen Masks Location

Page 11

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

2

1

PULL OUT THE YELLOW MASK OF THE RETAINER

4

OXYGEN MASKS ARE DEPLOYED SOFTLY HELD IN A MASK RETAINER

3

PULL THE OXYGEN MASK DOWNWARD TO INITIATE THE OXYGEN FLOW

5

DON THE OXYGEN MASK OVER THE NOSE AND MOUTH

BREATH NORMALLY BE SURE TO SECURE YOUR OWN MASK BEFORE ASSISTING OTHERS

EM170AOM110040C.DGN

6

11-08 Copyright © by Embraer. Refer to cover page for details.

Page 12

Oxygen Masks Location

REVISION 21

AOM-1502-003

PROCEDURE FOR PASSENGER OXYGEN MASKS

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

CABIN CREW OXYGEN SYSTEM WITH RETAINER Two oxygen masks are installed at each crew dispensing unit.

DISPENSING UNIT

MASK RETAINER

GREEN IN−LINE FLOW INDICATOR

ELASTIC STRAP

OXYGEN MASK

AOM-1502-003

MASK RESERVOIR BAG

CORD

EM170AOM980151A.DGN

ACTUATOR PIN DISCONNECTED

HOSE

CABIN CREW OXYGEN MASKS DEPLOYED AND MASKS RETAINERS

11-08 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Oxygen Masks Location

Page 13

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

1

2

PULL OUT THE YELLOW MASK OF THE RETAINER OXYGEN MASKS ARE DEPLOYED SOFTLY HELD IN A MASK RETAINER

4 3

DON THE OXYGEN MASK OVER THE NOSE AND MOUTH

PULL THE OXYGEN MASK DOWNWARD TO INITIATE THE OXYGEN FLOW

EM170AOM980149B.DGN

5

BREATH NORMALLY

11-08 Copyright © by Embraer. Refer to cover page for details.

Page 14

Oxygen Masks Location

REVISION 21

AOM-1502-003

PROCEDURE FOR CABIN CREW OXYGEN MASKS WITH RETAINER

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

CABIN CREW OXYGEN SYSTEM WITH STREAMER Two oxygen masks are installed at each crew dispensing unit.

DISPENSING UNIT

GREEN IN−LINE FLOW INDICATOR

AOM-1502-003

ACTUATOR PIN DISCONNECTED

MASK RESERVOIR BAG

CORD HOSE

EM170AOM980152A.DGN

ELASTIC STRAP

OXYGEN MASK

CABIN CREW OXYGEN MASKS DEPLOYED AND STREAMER

11-08 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Oxygen Masks Location

Page 15

EMERGENCY INFORMATION

1

AIRPLANE OPERATIONS MANUAL

2

PULL STREAMER TO ACCESS THE MASK OR GRAB IT DIRECTLY

OXYGEN MASKS ARE DEPLOYED

4

3

DON THE OXYGEN MASK OVER THE NOSE AND MOUTH

PULL THE OXYGEN MASK DOWNWARD TO INITIATE THE OXYGEN FLOW

EM170AOM980150B.DGN

5

BREATH NORMALLY

11-08 Copyright © by Embraer. Refer to cover page for details.

Page 16

Oxygen Masks Location

REVISION 21

AOM-1502-003

PROCEDURE FOR CABIN CREW OXYGEN MASKS WITH STREAMER

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

PASSENGER FLOATABLE SEAT AND LIFE JACKET PASSENGER FLOATABLE SEAT

1

2

REMOVE CUSHION FROM SEAT

4

AOM-1502-003

GRASP THE CUSHION TO FLOAT

EM170AOM110002B.DGN

3

11-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 13

Floatable Seats and Life Jackets

Page 1

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

LIFE JACKET

1

2

REMOVE LIFE VEST FROM ITS BAG

3

PUT THE STRAPS AROUND BACK MAKING SURE INFLATION TAB IS NOT UNDER WAIST STRAP

DON VEST

4

5

6

ORAL TUBE

JERK THE TAB TO INFLATE

IF LIFE VEST FAILS TO INFLATE USE ORAL TUBE

PULL TO LIGHT

EM170AOM110422A.DGN

LIGHT INFLATION TAB

11-10 Copyright © by Embraer. Refer to cover page for details.

Page 2

Floatable Seats and Life Jackets

REVISION 13

AOM-1502-003

LIFE JACKET - MANUALLY ACTIVATED SURVIVOR LOCATOR LIGHT

AIRPLANE OPERATIONS MANUAL

1

2

REMOVE LIFE VEST FROM ITS BAG

EMERGENCY INFORMATION

3

PUT THE STRAPS AROUND BACK MAKING SURE INFLATION TAB IS NOT UNDER WAIST STRAP

DON VEST

4

5

6

ORAL TUBE

JERK THE TAB TO INFLATE

IF LIFE VEST FAILS TO INFLATE USE ORAL TUBE

IN CONTACT WITH WATER THE LIGHT WILL ILLUMINATE

EM170AOM110004C.DGN

LIGHT INFLATION TAB

AOM-1502-003

LIFE JACKET – AUTOMATICALLY ACTIVATED SURVIVOR LOCATOR LIGHT

11-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 13

Floatable Seats and Life Jackets

Page 3

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

11-10 Copyright © by Embraer. Refer to cover page for details.

Page 4

Floatable Seats and Life Jackets

REVISION 13

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

HALON FIRE EXTINGUISHER The fire extinguisher contains a Halon blend composed by two different fire-fighting agents.

AOM-1502-003

This blend evaporates on contact, leaving no damaging powdery residue. It may be used to extinguish the following classes of fire: • Class A (paper, wood, fabric, rubber); • Class B (oils, greases, flammable liquids); • Class C (electrical or electronic equipment, live electrical).

11-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 12

Fire Extinguisher

Page 1

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

FIRE EXTINGUISHER OPERATION

1. UNSNAP "QUICK RELEASE" AND REMOVE FIRE EXTINGUISHER.

2. HOLD UPRIGHT, PULL LOCKING PIN.

4. AIM NOZZLE AT FIRE BASE. SPRAY QUICKLY SIDE TO SIDE ACCROSS FIRE. MOVE CLOSER AS FIRE IS EXTINGUISHED. DISCHARGE ALL OF THE AGENT. MAKE SURE THE FIRE IS COMPLETELY OUT.

EM170AOM110003A.DGN

3. STAND AWAY FROM FIRE [8 ft (2m)] PRESS LEVER TO DISCHARGE.

FIRE EXTINGUISHER OPERATION

11-15 Copyright © by Embraer. Refer to cover page for details.

Page 2

Fire Extinguisher

REVISION 12

AOM-1502-003

Precautions after fire extinguishing: • Look out for “flashback”; • Ventilate the compartment as promptly as possible.

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

EMERGENCY LOCATOR TRANSMITTER (ELT) The Emergency Locator Transmitter (ELT) assists in the swift location of the airplane during search and rescue operations transmitting a radio signal on 121.5 MHz, 243.0 MHz and 406 MHz. The 406 MHz component may be 406.025, 406.028, 406.037 MHz, etc. This frequency must be checked on the equipment installed in the airplane. The system comprises a transmitter with an ON/OFF switch and an impact switch installed in the rear rack, an antenna located on the top rear and a remote panel located in the cockpit. The ELT may be manually or automatically activated. In both cases, a red light flashes on the cockpit panel to indicate the ELTs activation. Manual activation may be performed when any switch is set to the ON position. Automatic activation occurs when the transmitter switch is set to the OFF position, the cockpit switch is set to the ARM position and the airplane suffers a deceleration whose intensity triggers the impact switch.

AOM-1502-003

Using an optional configuration with the ELT/NAV interface unit, the ELT is able to transmit the geographical position of the airplane when activated.

11-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Emergency Locator Transmitter

Page 1

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

CONTROLS AND INDICATIONS REMOTE PANEL 1 - ELT ALERT LIGHT (RED) – Flashes when the ELT is transmitting. 2 - ELT SWITCH (GUARDED) ON: Activates the ELT. ARM: Allows the ELT to be automatically activated. NOTE: – The TEST/RESET function is provided by pressing ON, waiting 1 second and then pressing ARM. – RESET function allows ELT deactivating, after a manual or automatic activation. – During TEST/RESET function, the ELT alert light flashes to indicate that the system is transmitting.

MAIN PANEL ARTEX ELT

1

ARM

TEST/RESET PRESS ON WAIT 1 SECOND PRESS ARM

EM170AOM110298B.DGN

2

ON

11-20 Copyright © by Embraer. Refer to cover page for details.

Page 2

Emergency Locator Transmitter

REVISION 17

AOM-1502-003

REMOTE PANEL

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

ON/OFF SWITCH ON

OFF

EM170AOM110290B.DGN

EMERGENCY LOCATOR TRANSMITTER

AOM-1502-003

EMERGENCY LOCATOR TRANSMITTER

11-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Emergency Locator Transmitter

Page 3

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

11-20 Copyright © by Embraer. Refer to cover page for details.

Page 4

Emergency Locator Transmitter

REVISION 17

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

LIGHTING Refer to AOM - Section 14-01 – AIRPLANE GENERAL.

OXYGEN Refer to AOM - Section 14-14 – OXYGEN.

NAVIGATION AND COMMUNICATION

AOM-1502-003

Refer to AOM – Section INSTRUMENTS/COMM/NAV/FMS.

14-09

–

FLIGHT

11-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Oxygen, NAV, COMM, Lighting

Page 1

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

11-25 Copyright © by Embraer. Refer to cover page for details.

Page 2

Oxygen, NAV, COMM, Lighting

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY INFORMATION

LEAST RISK LOCATION

AOM-1502-003

The location inside the airplane’s cabin where structural or system damage are least likely to jeopardize flight safety. The Least Risk Location is sited aft, as close as possible to the center of the second window from the last window on the airplane left side.

11-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 12

Least Risk Location

Page 1

EMERGENCY INFORMATION

AIRPLANE OPERATIONS MANUAL

11-30 Copyright © by Embraer. Refer to cover page for details.

Page 2

Least Risk Location

REVISION 12

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY EVACUATION

SECTION 12 EMERGENCY EVACUATION TABLE OF CONTENTS Block

Page

Introduction.......................................................... 12-INTRO ..

1

Emergency Evacuation Procedure..................... 12-05 .........

1

AOM-1502-003

Doors and Exits.................................................... 12-40 ......... 1 DOORS AND EXITS.............................................. 12-40 ......... 1 PASSENGER AND SERVICE DOORS................. 12-40 ......... 1 ESCAPE SLIDE..................................................... 12-40 ......... 7 COCKPIT EVACUATION....................................... 12-40 ......... 11

12-TOC Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Table of Contents

Page 1

EMERGENCY EVACUATION

AIRPLANE OPERATIONS MANUAL

12-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 17

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY EVACUATION

INTRODUCTION

AOM-1502-003

This Section presents information, which may be used at operator’s discretion to develop customized evacuation procedures.

12-INTRO Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Page 1

EMERGENCY EVACUATION

AIRPLANE OPERATIONS MANUAL

12-INTRO Copyright © by Embraer. Refer to cover page for details.

Page 2

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

EMERGENCY EVACUATION

EMERGENCY EVACUATION PROCEDURE

Emergency/Parking Brake.................................... ON Thrust Levers........................................................ IDLE Start/Stop Selectors.............................................. STOP Fire Extinguishing Handles................................... PULL AND ROTATE (1-L and 2-R) APU Emergency Stop Button............................... PUSH IN APU Fire Extinguishing Button............................. PUSH Pressurization Dump Button................................. PUSH IN ATC....................................................................... NOTIFY Emergency Evacuation......................................... ANNOUNCE Batteries................................................................ OFF

AOM-1502-003

END

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REVISION 14

Emergency Evacuation Procedure

Page 1

EMERGENCY EVACUATION

AIRPLANE OPERATIONS MANUAL

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Page 2

Emergency Evacuation Procedure

REVISION 14

AOM-1502-003

INTENTIONALLY BLANK

EMERGENCY EVACUATION

AIRPLANE OPERATIONS MANUAL

DOORS AND EXITS This airplane has two jetway passenger doors on the left side (forward and aft location), two jetway services doors on the right side (forward and aft location) and two cockpit windows, one each side, that can be used for emergency evacuation.

SERVICE DOOR

MAIN DOOR

EM170AOM120001A.DGN

SERVICE DOOR

MAIN DOOR

DOORS AND EXIT LOCATION

PASSENGER AND SERVICE DOORS This airplane has one passenger door located at the left forward fuselage section and another located at the aft fuselage section. Passenger door operation is manual and it is identical for both passenger doors. Passenger doors are semi-plug-in type and they are designed as type I doors.

AOM-1502-003

One service door is located at the right forward fuselage section and another located at the aft fuselage section. Service doors are used primarily for galley servicing and cabin cleaning between flights. It may also be used as an emergency exit. The operation of service and passenger doors is similar.

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REVISION 21

Doors and Exits

Page 1

EMERGENCY EVACUATION

AIRPLANE OPERATIONS MANUAL

DOOR OPENING TO OPEN: ARMED

2

1 A

B

A

OPEN THE LINING COVER.

B LOCK

3

GRAB BOTH ESCAPE SLIDE AND VENT FLAP LEVERS AND LIFT THEM UP. ENSURE THAT ALL THE FINGERS ARE FIRMLY HOLDING BOTH LEVERS. CLOSE THE LINING COVER.

DISARMED

C

LOCK

C

CHECK ESCAPE SLIDE INDICATION (DISARMED) AND GIRT BAR WITH NO RED INDICATION.

ESCAPE SLIDE DISARM

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Page 2

Doors and Exits

REVISION 21

AOM-1502-003

GIRT BAR INDICATION

EM170AOM140328G.DGN

C

AIRPLANE OPERATIONS MANUAL

EMERGENCY EVACUATION

4 D

5 F E D

LIFT THE MAIN HANDLE ALL THE WAY UP.

6

G

E

HOLD THE ASSISTANCE HANDLE.

F

PUSH THE DOOR OUT.

EM170AOM140329D.DGN

G

FULLY OPEN THE DOOR TO LOCK IT OPEN.

AOM-1502-003

MAIN HANDLE ACTUATION

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REVISION 21

Doors and Exits

Page 3

EMERGENCY EVACUATION

AIRPLANE OPERATIONS MANUAL

DOOR OUTSIDE OPENING !PRE-MOD SB 0170-52-0031

TO OPEN:

1 A B

2 A

ENSURE VENT FLAP IS CLOSED (FLUSH).

B

PUSH THE COVER AND GRAB THE HANDLE.

D

3

C

FULLY PUSH THE DOOR AND LOCK IT OPEN.

"

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Page 4

Doors and Exits

REVISION 21

AOM-1502-003

D

LIFT THE MAIN HANDLE ALL THE WAY UP.

EM170AOM140025C.DGN

C

AIRPLANE OPERATIONS MANUAL

EMERGENCY EVACUATION

!POST-MOD SB 0170-52-0031 TO OPEN:

1 A

2 A

PUSH THE COVER AND GRAB THE HANDLE.

C

3

B

C

LIFT THE MAIN HANDLE ALL THE WAY UP.

FULLY PUSH THE DOOR AND LOCK IT OPEN.

EM170AOM141077A.DGN

B

AOM-1502-003

"

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REVISION 21

Doors and Exits

Page 5

EMERGENCY EVACUATION

AIRPLANE OPERATIONS MANUAL

DOOR EMERGENCY OPENING

1 A

2 B

A

LIFT THE MAIN HANDLE ALL THE WAY UP.

3

THE DOOR OPENS AND ESCAPE SLIDE DEPLOYS.

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Page 6

Doors and Exits

REVISION 21

AOM-1502-003

C

FIRMLY PUSH THE DOOR.

EM170AOM140022B.DGN

B

AIRPLANE OPERATIONS MANUAL

EMERGENCY EVACUATION

ESCAPE SLIDE The evacuation slides are designed to provide passengers and crew a means to safely descend from the airplane to the ground during an emergency evacuation. In the event of emergency evacuation, the slides deploy automatically when the exit door is opened. Upon completion of the inflation sequence, the slide is fully inflated and ready to assist passengers and crew in descending to the ground. The evacuation slides are armed by raising the slide arming lever cover located on the door and moving the slide arming lever to the “armed” position. The lever attaches the girt bar to the cabin floor brackets. The evacuation slide is attached to the girt bar by means of a fabric girt. Opening the door from the outside automatically disengages the girt bar from the floor fittings, disarming the slide. !PRE-MOD SB 0170-52-0031

WARNING: MAKE SURE THAT THE VENT FLAP IS CLOSED (FLUSH WITH THE DOOR) BEFORE OPENING THE DOOR FROM THE OUTSIDE. IF THE EXTERNAL HANDLE IS USED TO OPEN THE DOOR WHILE THE SLIDE IS ARMED AND THE VENT FLAP IS OPEN, DOOR EMERGENCY OPENING OPERATION WILL OCCUR AND THE ESCAPE SLIDE WILL DEPLOY.

AOM-1502-003

"

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REVISION 21

Doors and Exits

Page 7

EMERGENCY EVACUATION

AIRPLANE OPERATIONS MANUAL

SLIDE ARM−DISARM HANDLE

INFLATION CYLINDER PRESSURE READINESS INSPECTION WINDOW

GIRT BAR ENGAGEMENT INDICATOR WINDOW

NO GO INDICATION

GO INDICATION

TEMP COMP NMC

PRESSURE GAUGE

MANUAL INFLATION HANDLE

EM170AOM120003.DGN

Goodrich

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Page 8

Doors and Exits

REVISION 21

AOM-1502-003

ESCAPE SLIDE – PACKED

AIRPLANE OPERATIONS MANUAL

EMERGENCY EVACUATION

GIRT ASSEMBLY

RESTRAINT PATCH

INFLATABLE TUBES

RESTRAINT PATCH

SLIDE SURFACE LIFELINE

DETACHABLE MOORING LINE

LED

LED

EM170AOM120002B.DGN

DEFLATED HANDLE

LED

AOM-1502-003

ESCAPE SLIDE – DEPLOYED

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REVISION 21

Doors and Exits

Page 9

AIRPLANE OPERATIONS MANUAL

EM170AOM140391A.DGN

EMERGENCY EVACUATION

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Page 10

Doors and Exits

REVISION 21

AOM-1502-003

DEFLATED ESCAPE SLIDE

AIRPLANE OPERATIONS MANUAL

EMERGENCY EVACUATION

COCKPIT EVACUATION

2

1

2 1

1

PRESSING LOCK BUTTON

3

3

3

TO ESCAPE MAKE USE OF ESCAPE ROPE

PULL THE HANDLE IN AND BACKWARD

4

5

7

AOM-1502-003

EM170AOM140228B.DGN

6

2

COCKPIT WINDOW EMERGENCY EXIT

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REVISION 21

Doors and Exits

Page 11

EMERGENCY EVACUATION

AIRPLANE OPERATIONS MANUAL

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Page 12

Doors and Exits

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

SECTION 13 GROUND SERVICING TABLE OF CONTENTS

AOM-1502-003

Block

Page

Introduction.......................................................... 13-INTRO ..

1

External Connections.......................................... 13-05 ......... ELECTRICAL POWER SUPPLY........................... 13-05 .........

1 1

Towing................................................................... 13-10 ......... TOWING WITH TOWBAR..................................... 13-10 .........

1 1

TOWBARLESS TOWING...................................... 13-11 ......... TOWBARLESS TOWING....................................... 13-11 .........

1 1

Parking and Mooring........................................... 13-15 ......... PARKING............................................................... 13-15 .........

1 1

Fuel........................................................................ 13-25 .........

1

Engine Oil............................................................. 13-30 ......... ENGINE OIL SERVICING...................................... 13-30 .........

1 1

APU Oil.................................................................. 13-35 ......... APU OIL SERVICING............................................ 13-35 .........

1 1

Landing Gear........................................................ 13-40 ......... TIRE PRESSURE CHECK.................................... 13-40 .........

1 1

Oxygen.................................................................. 13-45 ......... OXYGEN................................................................ 13-45 .........

1 1

Potable Water....................................................... 13-50 ......... POTABLE WATER TANK SERVICING.................. 13-50 .........

1 1

Waste..................................................................... 13-55 ......... WASTE TANK SERVICING................................... 13-55 .........

1 1

GROUND RESETS................................................ 13-60 ......... GENERAL.............................................................. 13-60 .........

1 1

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REVISION 21

Table of Contents

Page 1

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

Block Page LIMITATIONS......................................................... 13-60 ......... 2 INDEX BY EICAS MESSAGE............................... 13-60 ......... 3 INDEX BY FAULTS NOT ANNUNCIATED THROUGH EICAS MESSAGES...................... 13-60 ......... 4 1 1 3 6

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Page 2

Table of Contents

REVISION 21

AOM-1502-003

Cold Weather Operation...................................... 13-70 ......... COLD SOAK PREPARATION................................ 13-70 ......... DEICING AND ANTI-ICING FLUIDS..................... 13-70 ......... FORCED AIR DEICING......................................... 13-70 .........

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

INTRODUCTION General guidelines are provided herein related to the ground handling and servicing of the airplane. They are intended to make flight crews familiar with the ordinary aspects of the subject, as those tasks described herein normally are the responsibility of the maintenance personnel.

AOM-1502-003

For further instructions pertaining the subjects covered herein refer to the Aircraft Maintenance Manual.

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REVISION 9

Page 1

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

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Page 2

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

ELECTRICAL POWER SUPPLY AC POWER SUPPLY

EM170AOM130008A.DGN

The 115/200 VAC, three-phase, 400 Hz AC external power supply is connected to the airplane through the receptacle installed on the left side of the forward fuselage.

AOM-1502-003

AC EXTERNAL POWER CONNECTION

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REVISION 16

External Connections

Page 1

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

AC GPU

IN USE

GROUND SERVICE SW EM170AOM130014A.DGN

AVAILABLE

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Page 2

External Connections

REVISION 16

AOM-1502-003

GROUND SERVICE PANEL – G1 GALLEY

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

EXTERNAL AC POWER SUPPLY PROCEDURES CONNECTION Make sure that the external power supply has an earth grounded neutral with no open or floating ground in the neutral circuit. An open or floating ground can cause an electrical potential in the airplane ground circuit. Make sure that the external power supply operates correctly before supplying power to the airplane. If the ground return circuit of the external power supply does not operate correctly, do the Static Grounding Safety Procedure. Static Grounding Safety Procedures...................... ACCOMPLISH When using an AC-fed external power source, a ground connection between the hangar structure and the power source, and another one between the power source and the airplane are necessary. Attach the ground cable to the ground connection before attach it to the airplane. GPU........................................................................ ON Output Voltage........................................................ SET Adjust the output voltage of the external AC power supply to 115 +3/-2 VAC. GPU........................................................................ OFF AC Power Supply Connection Door....................... OPEN GPU........................................................................ CONNECT Connect the GPU cable to the AC external power receptacle. ELECTRICAL SUPPLY FOR AIRPLANE POWER UP GPU........................................................................ ON The AVAIL indication illuminates on both the Ground Service SW button (AC external power receptable) and the Ground Power Unit button (cockpit overhead panel). POWER UP Procedure........................................... ACCOMPLISH Proceed according to the Normal Procedures Power Up checklist. DISCONNECTION

AOM-1502-003

Ground Power Unit Button...................................... PUSH OUT The AVAIL indication turns on. CONTINUED...

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REVISION 16

External Connections

Page 3

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

BATT 1 & 2............................................................. OFF GPU........................................................................ OFF The AVAIL indication turns off. GPU........................................................................ DISCONNECT AC External Power Receptable Door..................... CLOSE ELECTRICAL SUPPLY FOR GROUND SERVICING GPU........................................................................ ON The AVAIL indication illuminates on both the Ground Service SW button (AC external power receptable) and the flight attendant’s Ground Service Panel (galley G1). Ground Service SW Button.................................... PUSH IN Ground personnel may choose to push in either of the two Ground Service SW buttons. The IN USE indication illuminates on both the Ground Service SW button and the flight attendant’s Ground Service Panel. DISCONNECTION Ground Service SW Button.................................... PUSH OUT Ground personnel may choose to push out either of the two Ground Service SW buttons. The AVAIL indication illuminates on both the Ground Service SW button and the flight attendant’s Ground Service Panel. GPU........................................................................ OFF The AVAIL indication turns off. GPU........................................................................ DISCONNECT AC External Power Receptable Door..................... CLOSE

DC POWER SUPPLY PROCEDURE

CONTINUED...

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Page 4

External Connections

REVISION 16

AOM-1502-003

The 28 VDC external power supply is connected to the airplane through the receptacle installed on the LH side of the rear fuselage. The DC power supply DC is used to start the APU.

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

EM170AOM130015B.DGN

...CONTINUED

DC EXTERNAL POWER CONNECTION

CONNECTION Make sure that the external power supply has an earth grounded neutral with no open or floating ground in the neutral circuit. An open or floating ground can cause an electrical potential in the airplane ground circuit. Make sure that the external power supply operates correctly before supplying power to the airplane. If the ground return circuit of the external power supply or the external power receptacle of the airplane does not operate correctly, do the Static Grounding Safety Procedure.

AOM-1502-003

Static Grounding Safety Procedures...................... ACCOMPLISH When using an AC-fed external power source, a ground connection between the hangar structure and the power source, and another one between the power source and the airplane are necessary. Attach the ground cable to the ground connection before attach it to the airplane. GPU........................................................................ ON Output Voltage........................................................ SET CONTINUED...

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REVISION 16

External Connections

Page 5

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Adjust the output voltage of the external DC-power supply to 28 ± 0.5 VDC. GPU........................................................................ OFF DC Power Supply Connection Door....................... OPEN GPU........................................................................ CONNECT Connect the GPU cable to the external DC power supply receptacle. GPU........................................................................ ON The AVAIL indication on the DC GPU PWR button in the DC power supply receptacle turns on. DC GPU PWR Button............................................. PUSH IN The IN USE indication turns on.

DISCONNECTION DC GPU PWR Button............................................. PUSH OUT The AVAIL indication turns on. GPU........................................................................ OFF The AVAIL indication turns off. GPU........................................................................ DISCONNECT AC Power Supply Connection Door....................... CLOSE

EXTERNAL PNEUMATIC POWER SOURCE PROCEDURE The pneumatic start unit is connected to the airplane through the engine start ground connection (HP ground connection) installed in the wing-to-fuselage fairing. Pressure supplied by the unit should be set above the minimum bleed duct pressure to compensate for pressure drop.

Engine..................................................................... CHECK

CONTINUED...

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Page 6

External Connections

REVISION 16

AOM-1502-003

Check if the engines are stopped. APU Bleed Button................................................... PUSHED OUT APU......................................................................... AS REQUIRED PACKS.................................................................... PUSHED OUT

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

CAUTION: MAKE SURE TO KEEP PACKS 1 AND 2 OFF WHILE PNEUMATIC PRESSURE SOURCE IS IN USE. DAMAGE CAN OCCUR AND DIRT CAN GET INTO THE AIRPLANE AIR CONDITIONING DUCTS IF PACKS 1 AND 2 ARE ON. Pneumatic Connections Access Door.................... OPEN Hose Adapter.......................................................... CONNECT Connect the hose adapter of the pneumatic start unit to the airplane engine start ground connection. External Pneumatic Power Source......................... START Pneumatic Start Unit............................................... ON Duct Pressure......................................................... AS REQUIRED For minimum recommended bleed duct pressure refer to the table in ENGINE GROUND PNEUMATIC START supplementary procedure, in block 3-70. If the equipment does not have an adjustment feature, set the pressure just above the minimum bleed duct pressure required. Do not set the pressure higher than 100 psi. Only the RH engine should be started with the HPU. For the LH engine perform a crossbleed start. External Pneumatic Power Source Valve............... OPEN Engine Start............................................................ ACCOMPLISH External Pneumatic Power Source Valve............... CLOSE External Pneumatic Power Source......................... STOP Hose Adapter.......................................................... DISCONNECT Pneumatic Connections Access Door.................... CLOSE APU Bleed Button................................................... PUSH IN PACKS.................................................................... AS REQUIRED

AIR CONDITIONING GROUND UNIT PROCEDURE A ground air conditioning source can be connected to the airplane to supply hot or cold air directly into the cabin.

AOM-1502-003

Cooling packs should be OFF, given that they are not able to control air temperature when a ground air source is being operated at the same time. NOTE: – If the cooling packs and the ground air conditioning source are used simultaneously, the air conditioned pressure may become excessive. CONTINUED...

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REVISION 16

External Connections

Page 7

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

– Open at least one airplane entrance or cargo door, and keep it open when operating the ground conditioned-air source. This is to prevent an increase in cabin pressure during the ground source operation.

CONNECTION PACKS 1 & 2.......................................................... OFF Pneumatic Connections Access Door.................... OPEN Air Conditioning Ground Unit.................................. CONNECT Connect the air conditioning unit to the airplane. The maximum permitted value of pressure airflow to the aircraft is 203.2 mm H2O (8 in H2O). Conditioned Air........................................................ SUPPLY

DISCONNECTION Conditioned Air........................................................ STOP Air Conditioning Ground Unit.................................. DISCONNECT

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Page 8

External Connections

REVISION 16

AOM-1502-003

Carefully disconnect the air conditioning unit from the airplane. Pneumatic Connections Access Door.................... CLOSE

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

TOWING WITH TOWBAR Ground towing can be accomplished by using a tow bar coupled to the landing gear. The tow bar incorporates breakable sections (fuse) with the purpose of causing the tow bar to break in case of any towing abnormality, to protect the airplane structure or the nose landing gear from damage.

TOW BAR

SHEAR PIN

EM170AOM130002B.DGN

TOWING LEVER LOCKPIN

AOM-1502-003

TOWING EQUIPMENT

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REVISION 17

Towing

Page 1

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

STEERING

D I S E N G AC GPU GROUND SERVICE SW

CKPT CALL

LAN

MIC/PHONE E N G A G E

EM170AOM140177B.DGN

AVAIL IN USE

RAMP INPH

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Page 2

Towing

REVISION 17

AOM-1502-003

EXTERNAL STEERING DISENGAGEMENT SWITCH

GROUND SERVICING

EM170AOM140286B.DGN

AIRPLANE OPERATIONS MANUAL

AOM-1502-003

TOWING LIGHTS

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REVISION 17

Towing

Page 3

GROUND SERVICING

EM170AOM140172B.DGN

AIRPLANE OPERATIONS MANUAL

EMERGENCY/PARKING BRAKE HANDLE

MAIN PANEL

EMERG/ PRKG BRAKE

EM170AOM130018B.DGN

GND PROX TERR INHIB

ON

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Page 4

Towing

REVISION 17

AOM-1502-003

EMERGENCY/PARKING BRAKE LIGHT

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

MFD

BRAKES

EMER ACCU PSI

S Y S 1

S Y S 2 3OOO

3OOO

OB 2OO

IB 2OO

IB 2OO

EM170AOM130020B.DGN

TEMP C OB 2OO

MFD STATUS PAGE

TOWING PROCEDURES

Doors....................................................................... CLOSED Close passenger doors, service doors, cargo doors and engine cowls. Seatbelts................................................................. FASTEN All the persons in the cockpit must be in a seat and seatbelts must be fastened. Emergency/Parking brake....................................... SET Landing Gear Safety Pins....................................... INSTALLED

AOM-1502-003

Make sure that the landing gear downlock safety pins are correctly installed on the main and nose landing gears. Landing Gear Shock Struts.................................... CHECK CONTINUED...

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REVISION 17

Towing

Page 5

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Make sure that the main landing gear and nose landing gear shock struts have sufficient extension. RAT Stow Lock Pin................................................. INSTALL Lock the RAT with stow lock pin and REMOVE-BEFORE-FLIGHT streamer. APU......................................................................... ON

install

the

Energize the airplane with the APU Emergency/Parking Brake...................................... CHECK Check if emergency/parking brake accumulator is pressurized. Pull the emergency/parking brake handle and check if emergency/parking brake light is ON. Steering System...................................................... DISENGAGE Disengage the steering system setting the external steering switch to the “DISENGAGE” position. EICAS message...................................................... CHECK Check the STEER OFF message is displayed on EICAS. Towing Indication Light........................................... RED Tow Bar................................................................... INSTALL Pull the locking pin and put the towing lever in the released position. Install the towbar on the towing attachment on the NLG. Pull the locking pin and set the towing lever to the towing position. Install the other end of the towbar to the tow tractor. Wheel Chocks......................................................... REMOVE Remove the wheel chocks from all tires. Emergency/Parking brake....................................... RELEASE Release the emergency/parking brake handle in the cockpit (brakes off). Towing Indication Light........................................... GREEN Make sure that the towing-indication light box shows the green light on. Towing..................................................................... ACCOMPLISH

CONTINUED...

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Page 6

Towing

REVISION 17

AOM-1502-003

Tow the airplane slowly straight ahead before turn.

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

CAUTION: DO NOT STEER THE NOSE LANDING GEAR MORE THAN THE MAXIMUM ANGLE PERMITTED THAT IS +/-170°. IF THE STEERING ANGLE IS MORE THAN +/170°, DAMAGE TO THE STEERING SYSTEM CAN OCCUR. Complete the airplane towing in a straight line for a minimum of 3 m (10 ft) in order to align the steering as close as possible to the zero-degree position and in the range of 76° (maximum angle for steering engagement). Emergency/Parking brake....................................... SET Check if Emergency/Parking Brake light is ON. Wheel Chocks......................................................... INSTALL Install the wheel chocks around all tires. Tow Bar................................................................... REMOVE Remove the tow bar from the tractor. Pull the locking pin and set the towbar lever to the released position. Remove the tow bar from the nose landing gear. Steering System...................................................... ENGAGE Set the external steering switch to the “ENGAGE” position. EICAS Message...................................................... CHECK Press and release the handwheel in the cockpit and check if the STEER OFF message on EICAS goes off. Towing Indication Light........................................... RED APU......................................................................... OFF, IF APPLICABLE RAT Stow Lock Pin................................................. REMOVE Landing Gear Safety Pins....................................... REMOVE Make sure that the landing gear downlock safety pins are removed from the main and nose landing gears.

PUSHBACK PROCEDURES

AOM-1502-003

The pushback is accomplished by using a tow bar coupled to the landing gear. Pushback procedure is used to move the airplane from the terminal gate before flight, with passengers and flight crew members on board and to push an airplane back with the ground towing crew only. CONTINUED...

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REVISION 17

Towing

Page 7

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

One towing supervisor is necessary to control the towing operation. One pushback crew at each wing tip and one pushback crew behind the tail are necessary to monitor sufficient clearance during the turns. The towing supervisor must have visual and radio communication with all the towing and flight crewmembers at all times. !Airplanes not equipped with Autobrake

If the pushback speed is higher than 5 kt and either Hydraulic System 1 or 2 is depressurized, EICAS messages BRK LH (RH) FAULT or BRK LH (RH) FAIL will be displayed until the wheel speed is reduced to less than 5 kt or the referred Hydraulic Systems are pressurized. " !Airplanes equipped with Autobrake OR POST-MOD SB 170-32-0014

If the pushback speed is higher than 5 kt and either Hydraulic System 1 or 2 is depressurized, the Autobrake will be automatically disarmed and EICAS messages BRK LH (RH) FAULT or BRK LH (RH) FAIL will be displayed until the wheel speed is reduced to less than 5 kt or the referred Hydraulic Systems are pressurized. "

Seatbelts................................................................. FASTEN All the persons in the cockpit must be in a seat and seatbelts must be fastened. RAT Stow Lock Pin................................................. CHECK Make sure that the stow lock pin is removed from the RAT. Landing Gear Safety Pins....................................... CHECK Make sure that the landing gear downlock safety pins are removed from the main and nose landing gears. Wheel Chocks......................................................... INSTALL

Check if emergency/parking brake accumulator is pressurized. Pull the emergency/parking brake handle and check if emergency/parking brake light is ON. Towing Indication Light........................................... RED CONTINUED...

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Page 8

Towing

REVISION 17

AOM-1502-003

Install the wheel chocks around all tires. Emergency/Parking Brake...................................... SET

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

Steering System...................................................... DISENGAGE Disengage the steering system setting the external steering switch to the “DISENGAGE” position. EICAS Message...................................................... CHECK Check if the STEER OFF message is displayed on EICAS. Ground Equipment.................................................. CHECK Make sure that all ground equipment is removed from areas adjacent to the airplane and all external services are disconnected from the airplane. Doors....................................................................... CLOSED Close passenger doors, service doors, cargo doors and engine cowls. Tow Bar................................................................... INSTALL Pull the locking pin and set the towing lever to the released position. Install the towbar on the towing attachment on the NLG. Pull the locking pin and set the towing lever to the towing position. Install the other end of the towbar to the tow tractor. Wheel Chocks......................................................... REMOVE Remove the wheel chocks from all tires. Emergency/Parking Brake...................................... RELEASE Release the emergency/parking brake handle in the cockpit (brakes off). Towing Indication Light........................................... GREEN Make sure that the towing-indication light box shows the green light on. Pushback................................................................ ACCOMPLISH Tow the airplane slowly straight ahead before turn.

AOM-1502-003

CAUTION: DO NOT STEER THE NOSE LANDING GEAR MORE THAN THE MAXIMUM ANGLE PERMITTED THAT IS +/-170°. IF THE STEERING ANGLE IS MORE THAN +/170°, DAMAGE TO THE STEERING SYSTEM CAN OCCUR. Complete the airplane towing in a straight line for a minimum of 3 m (10 ft) in order to align the steering as close as possible to the zero-degree position and in the range of 76° (maximum angle for steering engagement). Emergency/Parking Brake...................................... SET CONTINUED...

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REVISION 17

Towing

Page 9

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Check if emergency/parking brake light is ON. Towing Indication Light........................................... RED Tow bar................................................................... REMOVE Remove the tow bar from the tractor. Pull the locking pin and set the towbar lever to the released position. Remove the tow bar from the nose landing gear. Flight Crew.............................................................. ADVISE Notify the pilot that towbar is removed. Steering System...................................................... ENGAGE Set the external steering switch to the “ENGAGE” position. EICAS Message...................................................... CHECK Press and release the handwheel in the cockpit and check if the STEER OFF message on EICAS goes off. Access Door .......................................................... CLOSE

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Page 10

Towing

REVISION 17

AOM-1502-003

Close and latch the external steering access door.

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

TOWBARLESS TOWING Towbarless towing is prohibited, unless the towbarless towing operations are performed in compliance with the appropriate operational requirements using towbarless towing vehicles that are designed and operated to preclude damage to the airplane nose landing gear, steering system and associated fuselage structure. For steering system, if damage cannot be precluded a reliable and unmistakable warning must be provided when damage to the steering system may have occurred.

EM170AOM140286B.DGN

Towbarless towing vehicles that are specifically accepted for this type of airplane are listed in the AMM Chapter 9.

AOM-1502-003

TOWING LIGHTS

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REVISION 20

TOWBARLESS TOWING

Page 1

GROUND SERVICING

EM170AOM140172B.DGN

AIRPLANE OPERATIONS MANUAL

EMERGENCY/PARKING BRAKE HANDLE

MAIN PANEL

EMERG/ PRKG BRAKE

EM170AOM130018B.DGN

GND PROX TERR INHIB

ON

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Page 2

TOWBARLESS TOWING

REVISION 20

AOM-1502-003

EMERGENCY/PARKING BRAKE LIGHT

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

MFD

BRAKES

EMER ACCU PSI

S Y S 1

S Y S 2 3OOO

3OOO

OB 2OO

IB 2OO

IB 2OO

OB 2OO

EM170AOM130020B.DGN

TEMP C

MFD STATUS PAGE

COMMUNICATION

!Operation with Power Push Unit

The operation with PPU requires perfect synergy between the ground personnel and the crew as the ground personnel will depend on pilot commands to steer the airplane. Therefore, strong communication standards are required. Ground Personnel will use the interphone to provide the crew with directional information. If the interphone fails, the ground personnel will bring the airplane to a stop. The airplane dispatcher will advise the pilot by using standard hand signals to apply the airplane parking brake. Embraer suggests a terminology to be used, but the operator is responsible for developing communication standards for PPU operations. Following is Embraer suggestion for such standards:

AOM-1502-003

Flight Deck: Ready for pushback Ground: Brakes Off

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REVISION 20

TOWBARLESS TOWING

Page 3

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Central Left, left (Right, Right) Back off Steady Pushback complete Set Parking Brakes Flight Deck: Brakes set Ground: Power Push removed TERMINOLOGY ’Left, left’: pilot applies left tiller. Continues to apply more left tiller until airplane dispatcher says: ’Steady’: which means hold tiller in current position. ’Right, Right’: pilot applies right tiller. Continues to apply more right tiller until airplane dispatcher says: ’Steady’: which means hold tiller in current position. ’Back-off’: means reduce the tiller input.

CONTINUED...

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Page 4

TOWBARLESS TOWING

REVISION 20

AOM-1502-003

’Central’: means to place the tiller in a central position.

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL ...CONTINUED

PUSHBACK COMPLETE

POWER PUSH REMOVED. STAND BY.

SET PARK BRAKE

CENTRAL

START AND FINISH EVERY MANEUVER IN A STRAIGHT LINE. PARK BRAKE SET

STEADY

LEFT, LEFT

COMMUNICATIONS COCKPIT READY FOR PUSHBACK GROUND BRAKES OFF CENTRAL LEFT, LEFT RIGHT, RIGHT BACK OFF STEADY PUSHBACK COMPLETE SET PARK BRAKES COCKPIT BRAKES SET GROUND POWER PUSH REMOVED BRAKE OFF. CENTRAL. START AND FINISH EVERY MANEUVER IN A STRAIGHT LINE.

EM170AOM130028A.DGN

READY FOR PUSHBACK

COMMUNICATION

AOM-1502-003

" CONTINUED...

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REVISION 20

TOWBARLESS TOWING

Page 5

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

TOWBARLESS TOWING PROCEDURES

Landing Gear Safety Pins....................................... INSTALLED Make sure that the landing gear downlock safety pins are correctly installed on the main and nose landing gears. Doors....................................................................... CLOSED Close passenger doors, service doors, cargo doors and engine cowls. Emergency/Parking Brake...................................... CHECK Check if emergency/parking brake accumulator is pressurized. Pull the emergency/parking brake handle and check if emergency/parking brake light is ON. Steering System...................................................... DISENGAGE Disengage the steering system setting the external steering switch to the “DISENG” position. EICAS Message...................................................... CHECK Check if the STEER OFF message is displayed on EICAS. Ground Equipment.................................................. CHECK Make sure that all ground equipment is removed from areas adjacent to the airplane and all external services are disconnected from the airplane. Tug Vehicle............................................................. POSITION Make sure that the tug vehicle is in the correct position near the nose wheels. Wheel Chocks......................................................... REMOVE Make sure that the wheel chocks are removed. NOTE: Coordinate with ground personnel to release and apply the emergency/parking brake of the airplane. Tug Vehicle............................................................. COUPLE

CONTINUED...

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Page 6

TOWBARLESS TOWING

REVISION 20

AOM-1502-003

Make sure that the tug vehicle is coupled and correctly set to tow the airplane. Towing..................................................................... ACCOMPLISH

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

Tow the airplane slowly straight ahead before turn. Complete the airplane towing in a straight line for a minimum of 3 m (10 ft) in order to align the steering as close as possible to the zero-degree position. NOTE: Make sure that nose wheel displacement is below the maximum operational limit. Handwheel actuation with nose wheels beyond their operational limits may cause damage to the steering system. Emergency/Parking Brake...................................... SET Check if emergency/parking brake light is ON. Tug Vehicle............................................................. REMOVE Make sure that the tug vehicle is away from the airplane. Steering System...................................................... ENGAGE Set the external steering switch to the “ENGAGE” position. Press and release the handwheel to engage the steering system. EICAS Message...................................................... CHECK Check if the STEER OFF message is not displayed on EICAS. Landing Gear Safety Pins....................................... REMOVE Make sure that the landing gear downlock safety pins are removed from the main and nose landing gears.

!Operation with Power Push Unit

Forward and Backwards movements will be commanded by the ground personnel. If for any reason the crew wishes to discontinue the pushback the ground personnel will be responsible to bring the airplane to a stop. NOTE: Braking of airplane during the towing operation is prohibited unless in emergency situations. The necessary steering control during towing operations, differently from other towing vehicles, will be provided by the airplane steering system. The engine at the side PPU is connected must not be started before PPU is removed.

AOM-1502-003

Landing Gear Safety Pins....................................... REMOVED Make sure that the landing gear downlock safety pins are removed on the main and nose landing gears. Doors....................................................................... CLOSED Electric Hydraulic Pumps Sys 1 and 2................... On Emergency/Parking Brake...................................... CHECK/SET CONTINUED...

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REVISION 20

TOWBARLESS TOWING

Page 7

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Check if emergency/parking brake accumulator is pressurized. Pull the emergency/parking brake handle and check if emergency/parking brake light is ON. Ground Equipment.................................................. CHECK Make sure that all ground equipment is removed from areas adjacent to the airplane and all external services are disconnected from the airplane. Wheel Chocks......................................................... REMOVED Make sure that wheel chocks are removed. Flap......................................................................... CHECK Make sure that flaps are not set more than number 2 position. PPU......................................................................... CONNECTED Steering System...................................................... ENGAGE Make sure that the steering system is engaged by setting the external steering switch to the “ENGAGE” position and pressing the handwheel steering handle (EICAS message STEER OFF not displayed). Emergency/Parking Brake...................................... RELEASE Release the emergency/parking brake of the airplane. Towing lights RED................................................... CHECK Towing indication light on the nose landing gear must be RED, otherwise steering is disengaged. Towing..................................................................... ACCOMPLISH Emergency/Parking Brake...................................... SET Check if emergency/parking brake light is ON. PPU......................................................................... DISCONNECTED Electric Hydraulic Pumps Sys 1 and 2................... AUTO

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Page 8

TOWBARLESS TOWING

REVISION 20

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

TOWBARLESS PUSHBACK PROCEDURES Landing Gear Safety Pins....................................... REMOVED Make sure that the landing downlock safety pins are removed on the main and nose landing gears. Doors....................................................................... CLOSED Close passenger doors, service doors, cargo doors, and engine cowls. Emergency/Parking Brake...................................... CHECK/SET Check if emergency/parking brake accumulator is pressurized. Pull the emergency/parking brake handle and check if emergency/parking brake light is ON. Steering System...................................................... DISENGAGE Disengage the steering system setting the external steering switch to the ″DISENG″ position. EICAS Message...................................................... CHECK Check if the STEER OFF message is displayed on EICAS. Ground Equipment.................................................. CHECK Make sure that all ground equipment is removed from areas adjacent to the airplane and all external services are disconnected from the airplane. Tug Vehicle............................................................. POSITION Make sure that the tug vehicle is in the correct position near the nose wheels. Wheel Chocks......................................................... REMOVE Make sure that the wheel chocks are removed. NOTE: Coordinate with ground personnel to release and apply the emergency/parking brake of the airplane. Tug Vehicle............................................................. COUPLE

AOM-1502-003

Make sure that the tug vehicle is coupled and correctly set to tow the airplane. Emergency/Parking Brake...................................... RELEASE

CONTINUED...

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REVISION 20

TOWBARLESS TOWING

Page 9

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Release the emergency/parking brake handle in the cockpit (brakes off). NOTE: Braking the airplane during pushback operation is not permitted unless in emergency situations. Pushback................................................................ ACCOMPLISH Tow the airplane slowly straight ahead before turn. Complete the airplane towing in a straight line for a minimum of 3 m (10 ft) in order to align the steering as close as possible to the zero-degree position. NOTE: Make sure that nose wheel displacement is below the maximum operational limit. Handwheel actuation with nose wheels beyond their operational limits may cause damage to the steering system. Emergency/Parking Brake...................................... SET Check if emergency/parking brake light is ON. Tug Vehicle............................................................. REMOVE Make sure that the tug vehicle is away from the airplane. Steering System...................................................... ENGAGE Set the external steering switch to the ″ENGAGE″ position. Press and release the handwheel to engage the steering system. EICAS Message...................................................... CHECK Check if the STEER OFF message is not displayed on EICAS.

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Page 10

TOWBARLESS TOWING

REVISION 20

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

PARKING When parking, a minimum distance should be kept regarding other airplanes in order to permit airplane movement. Landing gear control lever should be in the down position and downlock pins must be installed given that a landing gear retraction could occur and cause injuries to persons and damage to the equipment. If the parking area has ice or snow, a mat, a layer of thick sand or other applicable material should be placed under the tires in order to prevent them from freezing. Emergency/parking brake should be set to the PARKING position and flaps retracted if they are extended. Having the airplane in the desired position, chocks may be placed against the landing gear wheels and covers for sensors may be installed.

PARKING PROCEDURE

AOM-1502-003

Landing Gear lever................................................. CHECK Check if landing Gear Lever is set to DOWN position. Landing Gear Safety Pins....................................... INSTALLED Make sure that the landing gear downlock safety pins are correctly installed on the main and nose landing gears. RAT Stow Lock Pin................................................. INSTALLED Make sure that the RAT is locked with stow lock pin, and the REMOVE-BEFORE-FLIGHT streamer is installed. Airplane to Parking Position................................... TAXI/TOWING Taxi or tow the airplane to the position specified for parking. If there is ice or snow in the parking area, put a mat and a layer of thick sand or other applicable material to prevent freezing of tires on ground. Mooring................................................................... ACCOMPLISH, IF NECESSARY Emergency/Parking brake....................................... SET Flaps....................................................................... RETRACT Retract the flaps if they are extended. Covers..................................................................... INSTALL Install covers to antennas, wheels, TAT sensor, ice-detector, smart probes, flaps trailing edge and winglets.

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REVISION 9

Parking and Mooring

Page 1

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

MOORING Mooring is necessary when the weather conditions are bad or unknown. The area where the airplane is to be parked in and moored must be paved and level, with ground tie down anchors available. There is one mooring attachment point installed on each primary brace strut of the main landing gear.

MOORING PROCEDURE

CONTINUED...

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Page 2

Parking and Mooring

REVISION 9

AOM-1502-003

Parking Procedures................................................ ACCOMPLISH Mooring................................................................... PROCEED Hold the airplane in the parking area with nylon ropes. Attach the rope to the mooring attachment point and attach the anchor with a bowline knot.

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL ...CONTINUED

BOWLINE KNOT MOORING ATTACHMENT POINT

1 2 4 5

EM170AOM130001.DGN

3

AOM-1502-003

MOORING THE AIRPLANE

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REVISION 9

Parking and Mooring

Page 3

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

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Page 4

Parking and Mooring

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

GRAVITY FUELING Emergency/Parking Brake...................................... ON Chocks.................................................................... IN PLACE Airplane and Fuel Nozzle....................................... STATICALLY GROUNDED WARNING: DO NOT TRANSMIT WITH THE HF COMMUNICATION SYSTEM IF ANY AIRPLANE IS REFUELING OR DEFUELING IN A RANGE OF 30 M (100 FT) FROM THE HF ANTENNA. IF YOU DO NOT OBEY THE APPROVED SAFETY STANDARDS AN EXPLOSION CAN OCCUR AND CAUSE INJURIES TO PERSONS AND DAMAGE TO THE AIRPLANE. Use an AC GPU or start the APU. If the power is not available use the fuel stick level indicator. Refer to fuel stick level indicator supplementary procedure. NOTE: The battery use may cause its discharge. Gravity Fill Cap (left/right)....................................... OPEN Introduce the fueling nozzle into the gravity refueling adapter. Start the fueling operation and monitor the fuel quantity in the tank. When the fueling operation is completed: Gravity Fill Cap (left/right)..................................... CLOSED Remove the grounding cables.

PRESSURE FUELING Emergency/Parking Brake...................................... ON Chocks.................................................................... IN PLACE Airplane and Fuel Nozzle ...................................... STATICALLY GROUNDED

AOM-1502-003

WARNING: DO NOT TRANSMIT WITH THE HF COMMUNICATION SYSTEM IF ANY AIRPLANE IS REFUELING OR DEFUELING IN A RANGE OF 30 M (100 FT) FROM THE HF ANTENNA. IF YOU DO NOT OBEY THE APPROVED CONTINUED...

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REVISION 20

Fuel

Page 1

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

SAFETY STANDARDS AN EXPLOSION CAN OCCUR AND CAUSE INJURIES TO PERSONS AND DAMAGE TO THE AIRPLANE. Use an AC GPU or start the APU and then set the POWER SELECTION switch to the NORMAL position on the refueling/defueling control panel. If AC power source is not available, set the POWER SELECTION switch to the BATTERY position. Gain access to the refueling/defueling control panel. NOTE: The battery use may cause its discharge. LH and RH refueling indication lights..................... VERIFY OFF Defueling indication light......................................... VERIFY OFF For Pressure Fueling in AUTO Mode REFUEL SELECTION switch............................... AUTO Fuel Quantity on Repeater indicator.................... SET Pressure refueling/defueling adapter assembly cap...................................................................... REMOVE Connect the fuel nozzle to the pressure refueling/defueling adapter assembly. Valve handle on fuel nozzle................................. OPEN Pressurize the fuel system from 241.32 kPa - 344.74 kPa (35 psig - 50 psig). LH and RH refueling indication lights................... VERIFY ON Make sure that there is no fuel flow while the lights are illuminated. REFUELING switch.............................................. OPEN LH and RH refueling indication lights................... VERIFY OFF When reaching the pre-set fuel quantity: LH and RH refueling indication lights................... VERIFY ON Make sure that there is no fuel flow while the lights are illuminated. REFUELING switch.............................................. CLOSED Valve handle on fuel nozzle................................. CLOSE

CONTINUED...

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Page 2

Fuel

REVISION 20

AOM-1502-003

Disconnect the fuel nozzle from the pressure refueling/defueling adapter assembly. Pressure refueling/defueling adapter assembly cap...................................................................... INSTALL

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

For Pressure Fueling in MANUAL Mode: REFUEL SELECTION switch............................... MANUAL Pressure refueling/defueling adapter assembly cap...................................................................... REMOVE Connect the fuel nozzle to the pressure refueling/defueling adapter assembly. Valve handle on fuel nozzle................................. OPEN Pressurize the fuel system from 241.32 kPa - 344.74 kPa (35 psig 50 psig). LH and RH refueling indication lights................... VERIFY ON Make sure that there is no fuel flow while the lights are illuminated. REFUELING switch.............................................. OPEN LH and RH refueling indication lights................... VERIFY OFF When reaching the required fuel quantity: REFUELING switch.............................................. CLOSED LH and RH refueling indication lights................... VERIFY ON Make sure that there is no fuel flow while the lights are illuminated. Valve handle on fuel nozzle................................. CLOSE

AOM-1502-003

Disconnect the fuel nozzle from the pressure refueling/defueling adapter assembly. Pressure refueling/defueling adapter assembly cap...................................................................... INSTALL

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REVISION 20

Fuel

Page 3

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

DEFUELING Emergency/Parking Brake...................................... ON Airplane and Fuel Nozzle....................................... STATICALLY GROUNDED WARNING: DO NOT TRANSMIT WITH THE HF COMMUNICATION SYSTEM IF ANY AIRPLANE IS REFUELING OR DEFUELING IN A RANGE OF 30 M (100 FT) FROM THE HF ANTENNA. IF YOU DO NOT OBEY THE APPROVED SAFETY STANDARDS AN EXPLOSION CAN OCCUR AND CAUSE INJURIES TO PERSONS AND DAMAGE TO THE AIRPLANE. AC GPU.................................................................. CONNECTED Defueling Open Light (Refuel/Defuel Control Panel).................................................................... OFF Remove the cap from the pressure refueling/defueling adapter assembly and connect the fueling nozzle to the pressure refueling/defueling adapter assembly. Open the valve handle on the fuel nozzle. Defueling Switch (Refuel/Defuel Control Panel)..... OPEN Check that the defueling open light illuminates. To defuel both wing tanks: Crossfeed Selector Knob...................................... LOW 1 Fuel AC Pump 1 and 2 Selector Knobs............... ON The fuel pumps must be in ON position if no suction on the fuel nozzle is applied. To defuel the left wing tank: Crossfeed Selector Knob...................................... OFF Fuel AC Pump 1 Selector Knob........................... ON The fuel pump must be in ON position if no suction on the fuel nozzle is applied.

Fuel AC Pump 2 Selector Knob........................... ON CONTINUED...

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Page 4

Fuel

REVISION 20

AOM-1502-003

To defuel the right wing tank: Crossfeed Selector Knob...................................... LOW 1

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

The fuel pump must be in ON position if no suction on the fuel nozzle is applied. After defueling is completed: Defueling Switch (Refuel/Defuel Control Panel). . CLOSED Check the defueling open light extinguished. Crossfeed Selector Knob...................................... OFF Fuel AC Pump 1 and 2 Selector Knobs............... AUTO Remove the grounding cable and the fuel nozzle.

FUEL TRANSFER BETWEEN WING TANKS Emergency/Parking Brake...................................... ON Chocks.................................................................... IN PLACE Use an AC GPU or start the APU. On the refueling/defueling control panel: POWER SELECTION switch................................ NORMAL DEFUELING switch.............................................. OPEN Defueling indication light....................................... VERIFY ON In the cockpit: AC Pumps selector knobs.................................... AUTO For Fuel Transfer from RH to LH Tank REFUEL 1 Circuit Breaker............................... PULL AND SAFETY XFEED selector knob....................................... LOW 1 For Fuel Transfer from LH to RH Tank REFUEL 2 Circuit Breaker............................... PULL AND SAFETY XFEED selector knob....................................... LOW 2 After the desired fuel transfer is completed: XFEED selector knob........................................... OFF

AOM-1502-003

REFUEL 1 or 2 Circuit Breaker............................ RESET On the refueling/defueling control panel: DEFUELING switch.............................................. CLOSED CONTINUED...

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REVISION 20

Fuel

Page 5

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Defueling indication light....................................... VERIFY OFF

FUEL MAGNETIC LEVER The best readings are within the values: – Pitch up: up to 0.8°. – Roll: up to 0.3°.

LEVER INDICATION 0.2 0.4 0.6 0.8 1.0 1.2 1.4 1.6 1.8 2.0 2.2 2.4 2.6 2.8 3.0 3.2 3.4 3.6 3.8 4.0 4.2 4.4 4.6 4.8

FUEL QUANTITY INTERNAL MIDDLE EXTERNAL LITERS US GAL LITERS US GAL LITERS US GAL 231 61 2953 780 4214 1113 251 66 2985 789 4246 1122 272 72 3017 797 4279 1130 293 77 3049 805 4312 1139 315 83 3082 814 4344 1148 336 89 3115 823 4377 1156 358 95 3149 832 4410 1165 380 100 3182 841 4443 1174 402 106 3216 850 4475 1182 424 112 3251 859 4508 1191 446 118 3285 868 4541 1200 469 124 3320 877 4573 1208 492 130 3356 887 4606 1217 515 136 3392 896 4639 1225 538 142 3428 906 4671 1234 562 148 3464 915 4704 1243 586 155 3501 925 4737 1251 610 161 3538 935 4770 1260 634 167 3575 944 4802 1269 658 174 3613 954 4835 1277 683 180 3651 964 4868 1286 707 187 3689 975 4900 1294 732 193 3728 985 4933 1303 757 200 3767 995 4966 1312 CONTINUED...

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Page 6

Fuel

REVISION 20

AOM-1502-003

For other ranges of airplane leveling refer to AMM Part II - Chapter 12.

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

AOM-1502-003

LEVER INDICATION 5.0 5.2 5.4 5.6 5.8 6.0 6.2 6.4 6.6 6.8 7.0 7.2 7.4 7.6 7.8 8.0 8.2 8.4 8.6 8.8 9.0 9.2 9.4 9.6 9.8 10.0 10.2 10.4 10.6 10.8 11.0 11.2 11.4

FUEL QUANTITY INTERNAL MIDDLE EXTERNAL LITERS US GAL LITERS US GAL LITERS US GAL 783 207 3806 1005 4999 1321 808 213 3846 1016 5031 1329 834 220 3886 1027 5064 1338 860 227 3927 1037 5097 1346 886 234 3967 1048 5129 1355 913 241 4008 1059 5162 1364 939 248 4050 1070 5195 1372 966 255 4091 1081 5227 1381 993 262 4133 1092 5260 1390 1020 269 4176 1103 5293 1398 1048 277 4218 1114 5326 1407 1075 284 4261 1126 --1103 291 4305 1137 --1131 299 4349 1149 --1160 306 4393 1161 --1188 314 4437 1172 --1217 321 4482 1184 --1246 329 4527 1196 --1275 337 4572 1208 --1304 344 4618 1220 --1333 352 4664 1232 --1363 360 4710 1244 --1393 368 4757 1257 --1423 376 4804 1269 --1454 384 4851 1281 --1484 392 4899 1294 --1515 400 ----1546 408 ----1577 417 ----1608 425 ----1640 433 ----1672 442 ----1704 450 ----CONTINUED...

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REVISION 20

Fuel

Page 7

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

LEVER INDICATION 11.6 11.8 12.0 12.2 12.4 12.6 12.8 13.0 13.2 13.4 13.6 13.8 14.0 14.2 14.4 14.6 14.8 15.0 15.2 15.4 15.6 15.8 16.0 16.2 16.4 16.6 16.8 17.0 17.2 17.4 17.6 17.8 18.0

FUEL QUANTITY INTERNAL MIDDLE EXTERNAL LITERS US GAL LITERS US GAL LITERS US GAL 1736 459 ----1768 467 ----1801 476 ----1833 484 ----1866 493 ----1900 502 ----1933 511 ----1967 520 ----2001 529 ----2035 538 ----2069 547 ----2103 556 ----2138 565 ----2173 574 ----2208 583 ----2243 593 ----2279 602 ----2314 611 ----2350 621 ----2386 630 ----2423 640 ----2459 650 ----2496 659 ----2533 669 ----2570 679 ----2607 689 ----2645 699 ----2682 709 ----2720 719 ----2759 729 ----2797 739 ----2835 749 ----2874 759 ----CONTINUED...

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Page 8

Fuel

REVISION 20

AOM-1502-003

...CONTINUED

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

LEVER INDICATION

AOM-1502-003

18.2 18.4 18.6 18.8 19.0 19.2 19.4 19.6 19.8 20.0 20.2 20.4 20.6 20.8 21.0 21.2 21.4 21.6 21.8 22.0

FUEL QUANTITY INTERNAL MIDDLE EXTERNAL LITERS US GAL LITERS US GAL LITERS US GAL 2913 770 ----2952 780 ----2992 790 ----3031 801 ----3071 811 ----3111 822 ----3151 832 ----3192 843 ----3232 854 ----3273 865 ----3314 875 ----3356 887 ----3397 897 ----3439 908 ----3481 920 ----3523 931 ----3565 942 ----3607 953 ----3650 964 ----3693 976 -----

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REVISION 20

Fuel

Page 9

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

REFUELING WITH ONE ENGINE RUNNING Refueling the airplane with an engine running is a special procedure and should be kept to a minimum. Apart from the risk of fire, there is the risk posed for the maintenance and other personnel who are required to move around the airplane. There may be circumstances in which an Airport Authority agrees with a detailed procedure that offers an acceptable level of safety to all parts involved. This would, however, be a matter between the Airport Authority and the individual operator. Therefore, contact the Airport Authority prior to performing this operation and/or obtain the necessary approval from the operations inspector. BASIC STATEMENTS – This procedure must only be used when the APU is unserviceable and no ground pneumatic power is available at the airport; – Only pressure refueling is permitted; – Normal refueling electrical bonding procedures between the airplane and the refueling equipment must be performed. Refer to AMM Part II Chapter 20; – Refueling is permitted to a maximum volume of 90% of each tank capacity; – Refueling should account for the additional fuel consumption of the operating engine to avoid jeopardizing flight autonomy and the fuel tanks balance; – At least one pilot must remain in the cockpit throughout the refueling procedure. This pilot should be responsible for informing all flight and ground crew that the airplane is being refueled and the engine is running; – The airplane must be parked in an area designated by the Airport Authority; – Coordination with the Airport Authority on the possibility of the Airport Fire Department to standby the airplane during the refueling procedure should be conducted;

– Qualified personnel on board of the airplane must be prepared for an immediate emergency evacuation; CONTINUED...

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Page 10

Fuel

REVISION 20

AOM-1502-003

– Maintenance and other servicing operations are prohibited during the refueling procedure;

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

– Smoking and the use of portable electronic devices is prohibited during the refueling, both inside and outside the cabin; To refuel the airplane with an engine running, proceed as follows: – Obtain ATC clearance as required; – Shut down engine 2 and set engine 1 to idle; – Whenever practical, turn off pack 2 when using the air conditioning system. This avoids blowing hot air from the pack 2 heat exchangers exhaust towards the refueling personnel; – Deplane all passengers through the forward service door (1R) and suspend all ground support operations; ensure the passengers and personnel are directed away from the operating engine; – Ensure at least one jetway door is open and a passenger stairs or bridge is connected to it; – Set all airplane systems before initiating refueling in order to avoid moving controls during refueling. Avoid turning switches to on, except those required to operate the fuel system. Sparks of any kind must be avoided; – Maintain all electric/electronic equipment unnecessary to the operation de-energized; – Follow the PRESSURE FUELING procedure, as specified earlier in this section, disregarding the instruction to use either a GPU or the APU as power source; – Monitor the fuel quantity indications throughout procedure; – In case of fuel spillage, shut down the operating engine immediately; – Once the refueling is completed, authorize the ground support teams to proceed with cleaning, cargo loading, galley loading, etc; always by the opposite side of the operating engine; – Proceed with passengers boarding through 1R door.

AOM-1502-003

NOTE: At stations where a passenger bridge is available, the use of the main passenger door in lieu of the forward service door for passengers planning/deplaning is subject to the Airport Authority approval.

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REVISION 20

Fuel

Page 11

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

DEPLANING OR BOARDING WITH ONE ENGINE RUNNING The following precautions are recommended: – At least one pilot must remain in the cockpit. – Turn off the engine 1. – Set the engine 2 to idle power. – Provide safety precautions for passengers on the ground. Isolate the right side of the airplane so that no passenger can get access to this area.

REFUELING WITH APU RUNNING If the APU is operating during refueling, in case of an APU fire: – Stop the refueling operation. – Accomplish the APU FIRE procedure. In case of fuel spillage: – Stop the refueling operation. – Shut down the APU. – Do not start the APU until the spillage is removed.

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Page 12

Fuel

REVISION 20

AOM-1502-003

NOTE: – Do not start the APU during refueling/defueling procedures after an automatic shutdown or a failed start of the APU. – If fuel spillage occurs, stop the APU and do not start it again.

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

ENGINE OIL SERVICING Engine oil check may be done from 15 min up to 2 h after engine stop. After 2 h from the last engine stop, it is necessary to start the engine to do the oil level check again. The oil level can be checked in the MFD Status page or directly in the engine.

MFD

EM170AOM130019A.DGN

ENG OIL LEVEL

6.5 QT 2.4 ENGINE OIL INDICATION ON MFD

The oil level check direct in the engine is performed by removing the access panel to reach TEST/POWER button. It is not necessary to energize the airplane for oil level check. Engine oil is toxic and flammable, use personal protection equipment and manipulate the oil in a well-ventilated area.

ENGINE OIL LEVEL CHECK - MFD Power Up................................................................ ACCOMPLISH MFD........................................................................ SET Select the Status Page on the MFD positioning the cursor at the Systems menu. Engine Oil Level...................................................... CHECK

AOM-1502-003

Check if the engine oil level in Full position. Fill the engine oil if necessary. Power Off................................................................ ACCOMPLISH

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REVISION 17

Engine Oil

Page 1

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

ENGINE OIL LEVEL CHECK - ENGINE Test/Power Button .................................................. PUSH AND HOLD On the oil tank level indicator, push and hold down the TEST/POWER button for 15 s. POWER ON and TANK FULL indicator lights turn on. Test/Power Button .................................................. RELEASE Indicator Lights ...................................................... CHECK If the POWER ON and TANK FULL indicator lights remains on the oil level is correct. If the TANK FULL indicator light turns off, add oil to the engine.

ENGINE OIL - FILLING

Access Panels........................................................ OPEN Test/Power Button .................................................. PUSH AND HOLD Test/Power Button .................................................. RELEASE Check if the POWER ON light remains on. Check if the TANK FULL light turns off. Engine-Oil Filler Cap............................................... OPEN Follow the instructions on the cap. Oil Reservoir........................................................... FILL Fill the oil reservoir until TANK FULL light comes on. Engine-Oil Filler Cap............................................... CLOSE

CONTINUED...

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Page 2

Engine Oil

REVISION 17

AOM-1502-003

Follow the instructions on the cap. Access Panels........................................................ CLOSE

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL ...CONTINUED

TANK FULL

POWER ON

TEST/POWER

CL

EM170AOM130011.DGN

E

10.5 U .S . QUA RTS OIL (10.0 LI TERS ) SO

AOM-1502-003

ENGINE OIL LEVEL CHECK

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REVISION 17

Engine Oil

Page 3

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

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Page 4

Engine Oil

REVISION 17

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

APU OIL SERVICING APU oil tank servicing is done through the access at the airplane tail cone, which provides access to a sight glass and an oil filler cap when open. The sight glass has a FULL indication that must never be exceeded. The APU oil capacity is 3.90  (4.12 qt).

GENERATOR

OIL LEVEL SIGHT GLASS

EM170AOM130009.DGN

OIL FILL CAP

AOM-1502-003

APU OIL LEVEL CHECK

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REVISION 9

APU Oil

Page 1

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

APU OIL LEVEL CHECK

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Page 2

APU Oil

REVISION 9

AOM-1502-003

APU selector knob.................................................. OFF AC GPU.................................................................. CONNECT Power Up................................................................ ACCOMPLISH Circuit Breakers...................................................... OPEN Open the following circuit breakers on the MCDU: • APU START CMD-SPDA2 (CBMENU/CB BY SYSTEM/CB SYSTEM-APU) • APU FADEC-SPDA2 (CBMENU/CB BY SYSTEM/CB SYSTEM-APU) • APU FUEL SOV OPN-SPDA2 (CBMENU/CB BY SYSTEM/CB SYSTEM-APU) Access Panel.......................................................... REMOVE Inlet Silencer .......................................................... UNLATCH AND OPEN Oil Level Sight Glass.............................................. CHECK The oil level must be between the FULL mark and ADD mark on the oil level sight glass. Fill the oil system to the FULL mark on the oil level sight glass, if necessary. Inlet Silencer .......................................................... CLOSE AND LATCH Access Panel.......................................................... INSTALL Circuit Breakers...................................................... CLOSE Close the following circuit breakers on the MCDU: • APU START CMD-SPDA2 (CBMENU/CB BY SYSTEM/CB SYSTEM-APU) • APU FADEC-SPDA2 (CBMENU/CB BY SYSTEM/CB SYSTEM-APU) • APU FUEL SOV OPN-SPDA2 (CBMENU/CB BY SYSTEM/CB SYSTEM-APU) Power Off................................................................ ACCOMPLISH AC GPU.................................................................. DISCONNECT

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

APU OIL FILLING APU selector knob.................................................. OFF AC GPU.................................................................. CONNECT Power Up................................................................ ACCOMPLISH Circuit Breakers...................................................... OPEN Open the following circuit breakers on the MCDU: • APU START CMD-SPDA2 (CBMENU/CB BY SYSTEM/CB SYSTEM-APU) • APU FADEC-SPDA2 (CBMENU/CB BY SYSTEM/CB SYSTEM-APU) • APU FUEL SOV OPN-SPDA2 (CBMENU/CB BY SYSTEM/CB SYSTEM-APU) Access Panel.......................................................... REMOVE Inlet Silencer .......................................................... UNLATCH AND OPEN Magnetic Drain Plug............................................... INSTALLED APU Oil Fill Cap...................................................... OPEN Oil Reservoir........................................................... FILL Fill the oil system to the FULL mark on the oil level sight glass. APU Oil Fill Cap...................................................... CLOSE AND LOCK

AOM-1502-003

Inlet Silencer .......................................................... CLOSE AND LATCH Access Panel.......................................................... INSTALL Circuit Breakers...................................................... CLOSE Close the following circuit breakers on the MCDU: • APU START CMD-SPDA2 (CBMENU/CB BY SYSTEM/CB SYSTEM-APU) • APU FADEC-SPDA2 (CBMENU/CB BY SYSTEM/CB SYSTEM-APU) • APU FUEL SOV OPN-SPDA2 (CBMENU/CB BY SYSTEM/CB SYSTEM-APU) Power Off................................................................ ACCOMPLISH AC GPU.................................................................. DISCONNECT

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REVISION 9

APU Oil

Page 3

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

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Page 4

APU Oil

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

TIRE PRESSURE CHECK The procedure is the same for the tires of the left and the right MLG. Do not go near the airplane’s tires while it is hot. If the measure of tires temperature is necessary, go to them from the front. There is tire explosion risk while tire is hot. Tire pressure must be measured with the tires cold and on ground.

AOM-1502-003

A calibrated pressure gauge is necessary to check the pressure gauge.

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REVISION 12

Landing Gear

Page 1

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

VALVE

CAP

EM170AOM140398A.DGN

PRESSURE GAUGE

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Page 2

Landing Gear

REVISION 12

AOM-1502-003

PRESSURE CHECK

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

MAIN LANDING GEAR TIRE PRESSURE CHECK Tire Temperature..................................................... CHECK Check if the tire temperature is the same as the ambient temperature. Wheel’s Valve Cap.................................................. REMOVE Pressure Gauge...................................................... CONNECT Pressure.................................................................. CHECK Tire pressure must be between 136 psi (938 kPa) and 146 psi (1007 kPa) with airplane on ground. If tire pressure is at (or close to) the bottom limit of the range, it is recommended to inflate the tire to 146 psi (1007 kPa). With the airplane on jack, the pressure in the tire must be 4% lower than the pressure with airplane on ground. If the temperature at destination airport is lower than the temperature at the departure airport and the difference is greater than 25°C (77°F), increase the tire pressure by 1% for each 3°C (5.4°F) of temperature difference. Pressure Gauge...................................................... DISCONNECT If tire pressure is between 123 psi (848 kPa) and 137 psi (945 kPa) connect the hose of tire inflation trolley to the valve on the wheel and adjust the pressure. Replacement of wheel is necessary for tire pressures below 123 psi (848 kPa). Refer to AMM. Leakage.................................................................. CHECK

AOM-1502-003

Check if there is no gas leakage from the valve. Wheel’s Valve Cap.................................................. INSTALL

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REVISION 12

Landing Gear

Page 3

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

NOSE LANDING GEAR TIRE PRESSURE CHECK Tire Temperature..................................................... CHECK Check if the tire temperature is the same as the ambient temperature. Wheel’s Valve Cap.................................................. REMOVE Pressure Gauge...................................................... CONNECT Pressure.................................................................. CHECK Tire pressure must be between 102 psi (703 kPa) and 112 psi (772 kPa) with airplane on ground. If tire pressure is at (or close to) the bottom limit of the range, it is recommended to inflate the tire to 112 psi (772 kPa). If the temperature at destination airport is lower than the temperature at departure airport and the difference is greater than 25°C (77°F), increase the tire pressure by 1% for each 3°C (5.4°F) of temperature difference. Pressure Gauge...................................................... DISCONNECT If tire pressure is above 112 psi (772 kPa), adjust the tire pressure to maximum of usual range. If tire pressure is between 94 psi (648 kPa) and 104 psi (717 kPa), connect the hose of tire inflation trolley to the valve on the wheel and adjust the pressure. Replacement of wheel is necessary for tire pressures below 94 psi (648 kPa). Refer to AMM. Leakage.................................................................. CHECK

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Page 4

Landing Gear

REVISION 12

AOM-1502-003

Check if there is no gas leakage from the valve. Wheel’s Valve Cap.................................................. INSTALL

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

BRAKE WEAR INDICATOR CHECK PROCEDURE Wheel Chock........................................................... IN PLACE Put the wheel chocks around all tires. Emergency/Parking Brake...................................... RELEASE External AC Power.................................................. CONNECT Connect the external AC power supply to the airplane. Hydraulic Systems 1 & 2........................................ PRESSURIZE Emergency/Parking Brake...................................... SET Set the emergency/parking brake handle totally to the parking position. Brake Wear Pins..................................................... CHECK Brake wear indicators flush with the bracket outer face or less indicate necessity of brakes replacement. Check both main landing gear brakes. Emergency/Parking brake....................................... RELEASE Hydraulic Systems 1 & 2........................................ DEPRESSURIZE External AC Power.................................................. DISCONNECT

AOM-1502-003

Disconnect the external AC power supply from the airplane. Emergency/Parking Brake...................................... SET Wheel Chock........................................................... REMOVE

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REVISION 12

Landing Gear

Page 5

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

BRAKE ASSEMBLY

BRACKET

EM170AOM140419.DGN

WEAR PIN

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Page 6

Landing Gear

REVISION 12

AOM-1502-003

BRAKE WEAR INDICATOR CHECK

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

OXYGEN Flight crew oxygen is provided via a conventional, high-pressure, gaseous-type system in which the oxygen is stored in a 77 ft3 cylinder, pressurized up to 1850 psi at 21°/70°F. The cylinder is installed in the forward cargo compartment.

AOM-1502-003

When servicing crew oxygen, shutoff valve on the oxygen cylinder should be open slowly; otherwise oxygen can become hot and can cause sudden combustion.

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REVISION 18

Oxygen

Page 1

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

OVERBOARD DISCHARGE INDICATOR

CHARGING VALVE

PRESSURE GAUGE

PROTECTIVE CAP

REGULATOR − OXYGEN SERVICING ACCESS DOOR

OXYGEN CYLINDER SHUTOFF VALVE

EM170AOM130012A.DGN

OXYGEN CHARGING ADAPTER

OXYGEN SOURCE

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Page 2

Oxygen

REVISION 18

AOM-1502-003

CREW OXYGEN REFILL POINT LOCATION

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

CREW OXYGEN FILLING Refill Point Location Access Door.......................... OPEN Protective Cap........................................................ REMOVE Connect the oxygen source to the cockpit oxygen cylinder charging valve, make sure that there is no leakage and do not let oil, grease, flammable solvents, dust metal filings and others materials that burn touch the components that will be open to pressurized oxygen. Fill the cockpit oxygen cylinder slowly until it reaches the required pressure. Gauge Pressure...................................................... MONITOR After reaching the required pressure, carefully disconnect the oxygen source from the charging valve and make sure that there is no leakage. NOTE: The filling nominal pressure is 1850 psi at an ambient temperature of 21°C (70°F). For other temperature values, refer to Oxygen Pressure Correction Chart. Refill Point Location Access Door.......................... CLOSE

MINIMUM CREW OXYGEN PRESSURE FOR DISPATCH Minimum oxygen pressure for dispatch in the cockpit oxygen cylinder is depicted below: Minimum Pressure for Dispatch (psi) Number of Flight Crewmembers in the Cockpit 2 (pilot and co-pilot) 3 (pilot, co-pilot and observer)

Oxygen Cylinder Volume (ft3) 50

77

1190

842

1664

1150

NOTE: The minimum crew oxygen pressure for dispatch was calculated at an ambient temperature of 21°C (70°F). If reading the External Gauge, for other temperature values, refer to Oxygen Pressure Correction Chart.

AOM-1502-003

CREW OXYGEN PRESSURE CHECK - EXTERNAL Refill Point Location Access Door.......................... OPEN CONTINUED...

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REVISION 18

Oxygen

Page 3

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Gauge Pressure...................................................... CHECK Read the oxygen pressure gauge to make sure that the oxygen pressure is above the minimum required for dispatch. If necessary, fill the cockpit oxygen cylinder. NOTE: The minimum oxygen pressure for dispatch was calculated at an ambient temperature of 21°C (70°F). For other temperature values, refer to Oxygen Pressure Correction Chart. Refill Point Location Access Door.......................... CLOSE

CREW OXYGEN PRESSURE CHECK - COCKPIT Power Up................................................................ ACCOMPLISH MFD........................................................................ SET Select the Status Page on the MFD, which provides oxygen pressure indication. !Commercial airplanes equipped with MAU load 21.2 and on OR POST-MOD SB 0170-31-0028

MFD

OXY PRESS

CREW

EM170AOM130031A.DGN

PSI 171O

"

Crew Oxygen Pressure........................................... CHECK Check the crew oxygen pressure range according to the following colors definition: – Digital Pressure GREEN/Scale WHITE/Pointer GREEN: Normal operating range.

•

Crew Oxygen Pressure: minimum for dispatch with three crew members in the cockpit.

•

Crew Oxygen Pressure: minimum for dispatch with two crew members in the cockpit. CONTINUED...

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Page 4

Oxygen

REVISION 18

AOM-1502-003

– Digital Pressure CYAN/Scale CYAN/Pointer CYAN: Advisory operating range.

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL ...CONTINUED

– Digital Pressure AMBER/Scale Cautionary operating range.

AMBER/Pointer

AMBER:

• Crew Oxygen Pressure: dispatch is not allowed. Power Off................................................................ ACCOMPLISH CREW OXYGEN PRESSURE CORRECTION CHART An Oxygen Pressure Correction Chart is provided for maintenance personnel or flight crew use when recharging the oxygen cylinder. Additionally, it may be used to check if the oxygen cylinder pressure is above the minimum oxygen pressure for dispatch. To use the chart for recharging purposes: – Enter the chart with the ambient temperature then go vertically up to the desired pressure at 21°C. From the intersection point, trace to the left to read the indicated gauge pressure to be attained. To use the chart for dispatching purposes:

AOM-1502-003

– Enter the chart simultaneously with the ambient temperature and indicated gauge oxygen pressure. The intersection determines the oxygen cylinder equivalent pressure at 21°C, by interpolating the two adjacent standard curves.

CONTINUED...

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REVISION 18

Oxygen

Page 5

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

(70°F)

2100 2000

RE SSU PRE 0°F) N E C (7 YG OX AT 21°

1900 1800

185

INDICATED GAUGE PRESSURE − PSI

1700 1600

0

167

0

1500 1400 1400

1300 1200

1200

1100 1000

1000

900

21°C

850

800 700 600 −30

−20

−10

0

10

20

30

40

50

−40

−20

−0

20

40

60

80

60

52

OUTSIDE AIR TEMPERATURE − °C 100

120

OUTSIDE AIR TEMPERATURE − °F

140

EM170AOM130013B.DGN

−40

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Page 6

Oxygen

REVISION 18

AOM-1502-003

CREW OXYGEN PRESSURE CORRECTION CHART

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

POTABLE WATER TANK SERVICING Potable water tank filling and draining is done through a panel installed on the rear left side of the fuselage. CAUTION: DO NOT TOUCH THE DRAIN MAST, IT HAS A HEATER INSTALLED AND CAUSES BURNS.

DOOR SWITCH

FILL/DRAIN SWITCH NORMAL

DR

AIN

FIL

L

FULL

FULL/DRAIN INDICATOR

FILL/DRAIN NIPPLE

EM170AOM130006.DGN

DRAIN

AOM-1502-003

POTABLE WATER TANK DRAINING AND FILLING

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REVISION 9

Potable Water

Page 1

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

AC GPU.................................................................. CONNECT Power Up................................................................ ACCOMPLISH MID Avionics Compartment.................................... ACCESS Open the access panel and open and remove the access door. Circuit Breakers...................................................... CHECK Check if the following circuit breakers are closed: • WATER WASTE HTR-LICC (AC GND SVC BUS) • WATER WASTE CTRL1-LICC (DC GND SVC BUS) • WATER WASTE CTRL2-LICC (DC BUS 1) • SPDA1 AC GND SVC-LICC (AC GND SVC BUS) Aft Avionics Compartment...................................... ACCESS Open the access door. Circuit Breakers...................................................... CHECK Check if the following circuit breaker is closed: • WATER WASTE CTRL3-AICC (HOT BATT BUS 2) Potable Water Access Door.................................... OPEN Protection Cap........................................................ REMOVE Remove the protection cap from the fill/drain nipple. Hose........................................................................ CONNECT Connect the hose to the water fill/drain nipple. Fill/Drain Switch...................................................... FILL Fill the tank with water until the full/drain indicator shows FULL. Aft Flight Attendant Panel....................................... CHECK Check if the potable water level is correct on the aft FAP. Fill/Drain Switch...................................................... NORMAL Water Supply.......................................................... CLOSE Hose........................................................................ DISCONNECT Protection Cap........................................................ INSTALL Let all excess water drain out before close the fill/drain nipple. Install the protection cap in the fill/drain nipple. Power Off................................................................ ACCOMPLISH AC GPU.................................................................. DISCONNECT Aft Avionics Compartment...................................... CLOSE Mid Avionics Compartment .................................... CLOSE CONTINUED...

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Page 2

Potable Water

REVISION 9

AOM-1502-003

POTABLE WATER TANK FILL

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

Install and close the access door and close the access panel. Potable Water Access Door.................................... CLOSE AND LATCH

AOM-1502-003

POTABLE WATER TANK DRAIN AC GPU.................................................................. CONNECT Power Up................................................................ ACCOMPLISH MID Avionics Compartment.................................... ACCESS Open the access panel and open and remove the access door. Circuit Breakers...................................................... CHECK Check if the following circuit breakers are closed: • WATER WASTE HTR-LICC (AC GND SVC BUS) • WATER WASTE CTRL1-LICC (DC GND SVC BUS) • WATER WASTE CTRL2-LICC (DC BUS 1) • SPDA1 AC GND SVC-LICC (AC GND SVC BUS) Aft Avionics Compartment...................................... ACCESS Open the access door. Circuit Breakers...................................................... CHECK Check if the following circuit breaker is closed: • WATER WASTE CTRL3-AICC (HOT BATT BUS 2) Potable Water Access Door.................................... OPEN Protection Cap........................................................ REMOVE Remove the protection cap from the fill/drain nipple. Hose........................................................................ CONNECT Connect the hose to the water fill/drain nipple. Use a container for liquids as auxiliary equipment to drain the water tank. Fill/Drain Switch...................................................... DRAIN Make sure that the full/drain indicator shows DRAIN. Let all the water drain. Aft Flight Attendant Panel....................................... CHECK Check if the potable water level is correct on the aft FAP. Fill/Drain Switch...................................................... NORMAL Water Supply.......................................................... CLOSE Hose........................................................................ DISCONNECT Protection Cap........................................................ INSTALL Let all excess water drain out before close the fill/drain nipple. Install the protection cap in the fill/drain nipple. CONTINUED...

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REVISION 9

Potable Water

Page 3

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

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Page 4

Potable Water

REVISION 9

AOM-1502-003

Power Off................................................................ ACCOMPLISH AC GPU.................................................................. DISCONNECT Aft Avionics Compartment...................................... CLOSE MID Avionics Compartment.................................... CLOSE Install and close the access door and close the access panel. Potable Water Access Door.................................... CLOSE AND LATCH

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

WASTE TANK SERVICING Toilet waste disposal servicing is accomplished by accessing a panel on the rear right side of the fuselage. Do not let the toilet system cleaner touch the eyes or skin. If it happens, flush the eyes or skin with water and get medical aid.

FLAPPER VALVE ACTUATOR LEVER DRAIN CONTROL HANDLE WASTE DRAIN VALVE

RINSE NIPPLE

HANDLE

LAVATORY FILLING COUPLING

PROTECTIVE CAP

DRAIN VALVE PROTECTIVE CAP

TOILET GROUND SERVICING CART

EM170AOM130005.DGN

LAVATORY DUMPING COUPLING

AOM-1502-003

WASTE TANK SERVICING

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REVISION 9

Waste

Page 1

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

WASTE TANK SERVICING PROCEDURES

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Page 2

Waste

REVISION 9

AOM-1502-003

Waste Tank Panel Door.......................................... OPEN Handle..................................................................... PULL Drain Valve Protective Cap..................................... OPEN Lavatory Dumping Coupling................................... INSTALL Install the lavatory dumping coupling in the waste drain valve. Check if the lavatory dumping coupling is correctly installed. Rinse Nipple Protective Cap................................... REMOVE Lavatory Filling Coupling........................................ INSTALL Install the lavatory filling coupling in the rinse nipple. Flapper Valve Actuator............................................ PUSH Push the flapper-valve actuator lever to open the waste drain valve. Drain Control Handle.............................................. PULL Pull the drain control handle to empty the waste tank. Rinse Fluid.............................................................. SUPPLY Make sure that the waste tank is completely drained before you start to supply the rinse fluid. Supply the rinse fluid for at least 2 min. Pre-charge the waste tank with 6 - 8 (1.6 US Gal - 2.1 US Gal) of rinse fluid. Drain Control Handle.............................................. PUSH Flapper Valve Actuator............................................ PULL Lavatory Filling Coupling........................................ REMOVE Rinse Nipple Protective Cap................................... INSTALL Lavatory Dumping Coupling................................... INSTALL Slowly remove the lavatory dumping coupling from the waste drain valve. Drain Valve Protective Cap..................................... CLOSE Handle..................................................................... LOCK Waste Tank Panel................................................... CLEAN Waste Tank Panel Door.......................................... CLOSE AND LATCH

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

GENERAL The purpose of this chapter is to provide flight crew with information and procedures to clear nuisance EICAS messages and miscellaneous nuisance faults. This chapter does not cover all messages/faults that may be detected on the airplane. Any message/fault not covered by this document must be reported to the maintenance personnel. Standard procedures must be established to instruct the flight crew how to proceed when a nuisance message/fault is presented before starting to follow this chapter after dispatch. These procedures may vary for different airports. This chapter is organized by messages/faults, alphabetically ordered. Following the messages, the proper procedures required to clear the nuisances are displayed. It may also provide the effectivity of the procedure and/or Fault Condition in which the procedure applies. The location of the fault or annunciation is also displayed. For the EICAS messages, there is an index sorted by message level Caution, Advisory, and Status. There is also the index of faults not annunciated through EICAS messages, which is sorted by the location of the messages. NOTE: – In the effectivity field, airplanes defined as E170 comprises EMBRAER 170 and 175, and the airplanes defined as E190 comprises EMBRAER 190 and 195. If no effectivity is referenced, the procedure is applicable to the E170 and E190. This chapter is based on the FAULT ISOLATION MANUAL (FIM). Therefore, in case a discrepancy is found between this chapter and FIM, the FIM shall prevail. The final solution for most of these nuisance messages/faults requires software upgrades of specific equipments. As soon as the final solutions become available and incorporated in the fleet, the related procedures will be removed.

AOM-1502-003

NOTE: This chapter does not constitute an operational approval. If Local Regulatory Authority approval is required, it should be obtained by the Operator.

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NUISANCE EICAS MESSAGE OR FAULT Some procedures may require the reset of more than one CB. In these cases, unless specified, the CBs can be reset one by one or open all of them at one time then reset all of them next.

LIMITATIONS This chapter shall be used under the following condition: – Airplane on the ground with parking brake set; – Each procedure may be performed only once per flight leg. If the nuisance EICAS message/fault is not cleared, if applicable, the maintenance personnel must be notified to clear the condition.

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– Effectivity and Fault Condition must be observed. Ground Resets Procedures should be accomplished only if the applicable effectivity and fault conditions are satisfied. Applicable effectivity and fault conditions are listed above the procedures. Those procedures that do not have effectivity and fault conditions listed above the procedures can be accomplished to every model and conditions, observing the items above.

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GROUND SERVICING

INDEX BY EICAS MESSAGE TYPE

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C A U T I O N

MESSAGE ADS 1 FAIL ADS 2 FAIL ADS 3 FAIL A-I WING FAIL AOA LIMIT FAIL APU FAIL AVNX MAU 1A FAIL AVNX MAU 1B FAIL AVNX MAU 2A FAIL AVNX MAU 2B FAIL AVNX MAU 3A FAIL AVNX MAU 3B FAIL BLEED 1 FAIL BLEED 2 FAIL EICAS FAULT FLT CTRL BIT EXPIRED FLT CTRL NO DISPATCH ICE DETECTOR 1 FAIL ICE DETECTOR 2 FAIL IRS 1 FAIL IRS 2 FAIL LG NO DISPATCH MFD 1 FAULT MFD 2 FAULT PFD 1 FAULT PFD 2 FAULT STEER FAIL WINDSHEAR FAIL WINDSHIELD 1 HTR FAIL WINDSHIELD 2 HTR FAIL

13-60 PAGE 9 9 9 12 13 13 14 14 14 14 14 14 15 15 16 18 19 21 21 22 22 22 23 24 24 24 27 28 29 29

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TYPE

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MESSAGE

ADS PROBE 1 FAIL ADS PROBE 2 FAIL ADS PROBE 3 FAIL ADS PROBE 4 FAIL A-I ENG 1 FAULT A-I ENG 2 FAULT AVNX MAU 1A FAULT A AVNX MAU 1B FAULT D AVNX MAU 2A FAULT V AVNX MAU 2B FAULT I S AVNX MAU 3A FAULT O AVNX MAU 3B FAULT R BRK CONTROL FAULT Y BRK LH FAULT BRK RH FAULT ENG 1 SHORT DISPATCH ENG 2 SHORT DISPATCH FLT CTRL FAULT FUEL FEED 1 FAULT FUEL FEED 2 FAULT STATUS PRINTER FAULT

13-60 PAGE 9 9 10 11 12 12 14 14 14 14 14 14 15 16 16 17 17 19 20 20 24

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INDEX BY FAULTS NOT ANNUNCIATED THROUGH EICAS MESSAGES LOCATION

CONDITION / ANNUNCIATION

ACARS ACP

ACARS Frozen Audio Control Panel Inoperative MCDU 1 Frozen/ Blank/ Blinking/ Red X/ TIMEOUT MSG MCDU 2 Frozen/ Blank/ Blinking/ Red X/ TIMEOUT MSG WX FAIL Printer not Working

MCDU

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MFD PRINTER

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GROUND RESET PROCEDURES MAU SAFETY PROCEDURES This procedure must be accomplished when a reset of the MAU 1, 2 or 3 is necessary. MAU 1 SAFETY PROCEDURES Electric Hydraulic Pumps 1, 2, 3A and 3B............. OFF Both Engines........................................................ SHUTDOWN NOTE: Shut down the engines before attempting a MAU reset in order to avoid engine related messages being displayed on the EICAS. NOTE: When resetting the MAU 1, the SPOILER FAULT and A-I WING FAIL EICAS messages may be displayed. When all procedures have been completed: Electric Hydraulic Pumps 1, 2 and 3B................. AUTO Electric Hydraulic Pump 3A.................................. OFF Engines................................................................. AS REQUIRED MAU 2 SAFETY PROCEDURES Both Engines........................................................ SHUTDOWN NOTE: Shut down the engines before attempting a MAU reset in order to avoid engine related messages being displayed on the EICAS. When all procedures have been completed: Engines............................................................. AS REQUIRED MAU 3 SAFETY PROCEDURES If APU is running and MAU 3 PWR 1 CB is to be opened: Electrical............................................................... ON GPU APU....................................................................... SHUTDOWN

CONTINUED...

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Electric Hydraulic Pumps 1, 2, 3A and 3B............. OFF

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...CONTINUED

Both Engines........................................................ SHUTDOWN NOTE: Shut down the engines before attempting a MAU reset in order to avoid engine related messages being displayed on the EICAS. NOTE: When resetting the MAU 3, the SPOILER FAULT and A-I WING FAIL EICAS messages may be displayed. When all procedures have been completed: Electric Hydraulic Pumps 1, 2 and 3B................. AUTO Electric Hydraulic Pump 3A.................................. OFF APU....................................................................... AS REQUIRED Engines................................................................. AS REQUIRED AIRPLANE POWER RESET This procedure is to be considered when a complete power reset (power down – power up) is necessary. Emergency/Parking Brakes.................................... SET Electric Hydraulic Pumps 1, 2 and 3B.................... AUTO Electric Hydraulic Pumps 3A.................................. OFF Electrical.................................................................. ON GPU/APU Thrust Levers.......................................................... IDLE Start/Stop Selector knobs 1 and 2......................... STOP Hydraulic System 1, 2 and 3 Pressure................... BELOW 500 PSI NOTE: – Hydraulic pressure drop below 500 psi is expected to take less than 5 s and it is necessary to ensure that the EDP motor has stopped spinning. Power up with the motor still rotating may cause excessive voltage spikes. – Do not move the flight controls surfaces to lower the hydraulic pressure. – Moving the flight controls surfaces will speed up the hydraulic pressure bleed down process but may cause a discrepancy between surface position and yoke command triggering the FLT CTRL NO DISPATCH message on the EICAS.

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Emergency Lights................................................... OFF Electrical.................................................................. OFF GPU/APU CONTINUED...

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...CONTINUED

If APU is available turn the APU OFF by selecting the APU Master Selector knob to OFF and after the 2 min cool down period, wait until the APU rpm drops below 3%, before positioning both battery selectors to OFF. NOTE: For airplanes Post-Mod SB 170-49-0003 or SB 190-49-0001 (APU FADEC 02.00) or with an equivalent modification factory incorporated, the cooldown period is 1 min, followed by a spooldown period. The EICAS message APU SHUTTING DOWN disappears at the end of spool down period, afterwards turn both battery selectors to the OFF position. If a GPU is available, push out the GPU button. Batteries 1 and 2.................................................... OFF Wait 1 min. Power up using normal procedures.

ACARS FROZEN LOCATION: ACARS. EFFECTIVITY: Airplanes with CMF. SURE THAT THE INTEGRATED CAUTION: MAKE PITOT/STATIC/AOA SENSORS, TAT SENSORS, ICE DETECTORS AND STATIC PORTS HAVE NO COVERS ON THEM BEFORE ACCOMPLISHING THIS PROCEDURE. THESE COMPONENTS CAN BECOME HOT DURING THIS PROCEDURE DAMAGING THEM. NOTE: Refer to the MAU SAFETY accomplishing this procedure.

PROCEDURES

before

Open the following CBs, wait 5 s, then reset: RHCBP.................................................................... MAU 3 PWR 2

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ADS 1 FAIL Open the following CBs, wait 30 s, then reset: LHCBP.................................................................... ADS 1 PROBE 1A-2A LHCBP.................................................................... ADS FC PROBE 1B-2B END

ADS 2 (3) FAIL Open the following CBs, wait 30 s, then reset: RHCBP.................................................................... ADS 2 PROBE 3A RHCBP.................................................................... ADS 2 PROBE 4A RHCBP.................................................................... ADS 3/STBY PROBE 3B RHCBP.................................................................... ADS 3/STBY PROBE 4B END

ADS PROBE 1 (2) FAIL EFFECTIVITY: Airplanes with Primus EPIC Load up to 21.5. FAULT CONDITION 1: Message displayed any time until Clear Into Position and ADS 1 FAIL caution message is not displayed. Power down then power up the airplane, using the Airplane Power Reset procedures. FAULT CONDITION 2: Message displayed upon landing. Open the following CBs, wait 30 s, then reset:

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LHCBP.................................................................... ADS 1 PROBE 1A-2A LHCBP.................................................................... ADS FC PROBE 1B-2B EFFECTIVITY: Airplanes with Primus EPIC Load 23.1 and on. CONTINUED...

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...CONTINUED

FAULT CONDITION: Message displayed upon landing. Open the following CBs, wait 30 s, then reset: LHCBP.................................................................... ADS 1 PROBE 1A-2A LHCBP.................................................................... ADS FC PROBE 1B-2B END

ADS PROBE 3 FAIL EFFECTIVITY: Airplanes with Primus EPIC Load up to 21.5. FAULT CONDITION 1: Message displayed any time until Clear Into Position and ADS 2 FAIL and ADS 3 FAIL caution messages are not displayed. Power down then power up the airplane, using the Airplane Power Reset procedure. FAULT CONDITION 2: Message displayed upon landing. Open the following CBs, wait 30 s, then reset: RHCBP.................................................................... ADS 2 PROBE 3A RHCBP.................................................................... ADS 3/STBY PROBE 3B EFFECTIVITY: Airplanes with Primus EPIC Load 23.1 and on. FAULT CONDITION 2: Message displayed upon landing. Open the following CB, wait 30 s, then reset: RHCBP.................................................................... ADS 2 PROBE 3A RHCBP.................................................................... ADS 3/STBY PROBE 3B

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GROUND SERVICING

ADS PROBE 4 FAIL EFFECTIVITY: Airplanes with Primus EPIC Load up to 21.5. FAULT CONDITION 1: Message displayed any time until Clear Into Position and ADS 2 FAIL and ADS 3 FAIL caution messages are not displayed. Power down then power up the airplane, using the Airplane Power Reset procedure. FAULT CONDITION 2: Message displayed upon landing. Open the following CBs, wait 30 s, then reset: RHCBP.................................................................... ADS 2 PROBE 4A RHCBP.................................................................... ADS 3/STBY PROBE 4B EFFECTIVITY: Airplanes with Primus EPIC Load 23.1 and on. FAULT CONDITION 2: Message displayed upon landing. Open the following CBs, wait 30 s, then reset: RHCBP.................................................................... ADS 2 PROBE 4A RHCBP.................................................................... ADS 3/STBY PROBE 4B

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END

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A-I ENG 1 (2) FAULT FAULT CONDITION 1: A-I ENG 1 FAULT EICAS message displayed 30 s after landing, due to the respective bleed system being OFF during any flight phase; OR FAULT CONDITION 2: Bleed system 1 or 2 is OFF and the Cross Bleed valve is closed. Push out the ENGINE 1 and ENGINE 2 Ice Protection buttons on the ICE PROTECTION control panel. NOTE: After 10 s, the A-I SWITCH OFF advisory message is displayed on the EICAS. Push in the ENGINE 1 and ENGINE 2 Ice Protection buttons on the ICE PROTECTION control panel. NOTE: The A-I SWITCH OFF advisory message extinguishes. END

A-I WING FAIL LOCATION: PFD FAULT CONDITION 1: The A-I WING FAIL message is displayed on the EICAS during the BIT (Built-in Test). OR FAULT CONDITION 2: The A-I WING FAIL message is displayed on the EICAS and the CAS MSG annunciation is displayed on both PFDs. Ice Protection TEST Selector Knob........................ WING Ice Protection WING button.................................... PUSH OUT ...........................................Wait 10 seconds........................................... A-I SWITCH OFF.................................................... Displayed on EICAS Verify the A-I SWITCH OFF CAS message displayed on EICAS. Ice Protection WING button.................................... PUSH IN

CONTINUED...

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Verify the A-I SWITCH OFF CAS message is NOT displayed on EICAS.

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GROUND SERVICING

...CONTINUED

A-I SWITCH OFF.................................................... Extinguished ...........................................Wait 60 seconds........................................... A-I WING FAIL........................................................ Not displayed on EICAS END

AOA LIMIT FAIL On the maintenance panel, make sure that the FCS MAINT switch is in the OFF position. END

APU FAIL On the MCDU, press CB key then CB MENU/CB BY SYS/APU. Open these electronic CBs, wait 10 s, then reset: APU FADEC ABC CMD PWR ASC CMD PWR Try another APU start.

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END

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AUDIO CONTROL PANEL INOPERATIVE LOCATION: ACP FAULT CONDITION: Audio Control Panel not energized after airplane power up. Open the CB related to the inoperative ACP, wait 5 s, then reset: ACP 1: LHCBP....................................................... AUDIO 1 ACP 2: RHCBP....................................................... COMM AUDIO 2 ACP 3: LHCBP....................................................... COMM AUDIO 3 END

AVNX MAU 1 (2,3) A (B) FAIL Power down and then power up the airplane, using the Airplane Power Reset procedure. END

AVNX MAU 1 (2, 3) A (B) FAULT Power down and then power up the airplane, using the Airplane Power Reset procedure.

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GROUND SERVICING

BLEED 1 (2) FAIL FAULT CONDITION 1: EICAS message BLEED 1 (2) FAIL displayed together with ″CAS MSG″ annunciation on both PFDs. Push out the associated BLEED pushbutton COND/PNEUMATIC overhead panel, then push in.

on

the

AIR

FAULT CONDITION 2: EICAS message BLEED 1 (2) FAIL displayed during the BIT (Built-in Test). Push out the associated BLEED pushbutton COND/PNEUMATIC overhead panel, then push in.

on

the

AIR

EFFECTIVITY: E170 with AMS Black Label 6 and on or Post-Mod. SB 170-21-0016. E190 with AMS Black Label 6 and on or Post-Mod. SB 190-21-0002. FAULT CONDITION 3: EICAS message BLEED 1 (2) FAIL message displayed, but the associated BLEED OFF message is not displayed. Push out the associated BLEED pushbutton on the COND/PNEUMATIC overhead panel, wait 60 s, then push in.

AIR

END

BRK CONTROL FAULT CAUTION: MAKE SURE THAT THE INTEGRATED PITOT/STATIC/AOA SENSORS, TAT SENSORS, ICE DETECTORS AND STATIC PORTS HAVE NO COVERS ON THEM BEFORE ACCOMPLISHING THIS PROCEDURE. THESE COMPONENTS CAN BECOME HOT DURING THIS PROCEDURE DAMAGING THEM. NOTE: – Refer to MAU SAFETY PROCEDURES before accomplishing this procedure. – Crosscheck flap setting after the reset on MCDU’s Takeoff page 2/3. Open the following CB, wait 3 s but not more than 5 s, then reset: AOM-1502-003

LHCBP.................................................................... MAU 1 PWR 1 CONTINUED...

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...CONTINUED

If the message is still displayed, open the following CB, wait 3 s but not more than 5 s, then reset: RHCBP.................................................................... MAU 2 PWR 2 PRI RHCBP.................................................................... MAU 2 PWR 2 SEC If after CB reset the message persists, accomplish AIRPLANE POWER RESET procedure. END

BRK LH (RH) FAULT EFFECTIVITY: E190. FAULT CONDITION: BRK LH FAULT and BRK RH FAULT messages are displayed at the same time on EICAS after landing, before takeoff and during taxi. Power down then power up the airplane, using the Airplane Power Reset procedure. END

EICAS FAULT Open the following CB, wait 5 s, then reset: LHCBP.................................................................... EICAS

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GROUND SERVICING

ENG 1 SHORT DISPATCH FAULT CONDITION: Message displayed during power-up. NOTE: If the ENG 1 SHORT DISPATCH EICAS message is displayed during any other flight phase, even if the message disappears after engines shutdown, this procedure must not be performed and the maintenance personnel must be notified. Open the following CBs, wait 5 s, then reset: LHCBP.................................................................... FADEC 1A RHCBP.................................................................... FADEC 1B END

ENG 2 SHORT DISPATCH FAULT CONDITION: Message displayed during power-up. NOTE: If the ENG 2 SHORT DISPATCH EICAS message is displayed during any other flight phase, even if the message disappears after engine shutdown, this procedure must not be performed and the maintenance personnel must be notified. Open the following CBs, wait 5 s, then reset: LHCBP.................................................................... FADEC 2A RHCBP.................................................................... FADEC 2B

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END

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FLT CTRL BIT EXPIRED Open the Flight Controls Synoptic Page and check which PBIT remaining time readout is equal to 0 (zero). Perform the hydraulic PBIT or Airplane Power Reset procedure for whichever is applicable. Perform the hydraulic PBIT: set electric hydraulic pumps 1, 2 and 3A to ON. Wait until the EICAS message FLT CTRL TEST IN PROG extinguishes. Set electric hydraulic pumps 1 and 2 to AUTO, and 3A to OFF. NOTE: – Do not move the flight controls until the flight control actuators engage in the daily switch configuration (Odd-Even Day Engage configuration). – Make sure that the rudder surface is not fully deflected to the LEFT position (due to wind action, for instance). If the message is still displayed: Perform the Airplane Power Reset procedure. NOTE: – Do not move the flight controls while hydraulic pressure is OFF. – The electrical PBIT is complete 3 min after power-up. If any electric hydraulic pump is set to ON before the electrical PBIT is complete, the PBIT is canceled.

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FLT CTRL FAULT Power down and then power up the airplane, using the Airplane Power Reset procedure. END

FLT CTRL NO DISPATCH FAULT CONDITION 1: Message displayed after airplane power-up. – Set electric hydraulic pumps 1, 2, and 3A to ON. – On the FLIGHT CONTROLS MODE panel, push the ELEVATORS, RUDDER, and SPOILERS pushbuttons, wait 3 s, then push again. If message is still displayed: – Power down then power up the airplane. Refer to Airplane Power Reset. FAULT CONDITION 2: Message displayed after landing. – Set electric hydraulic pumps 1, 2, and 3A to ON. – On the FLIGHT CONTROLS MODE panel, push the ELEVATORS, RUDDER, and SPOILERS pushbuttons, wait 3 s, then push again. FAULT CONDITION 3: The airplane is operating at low external temperature, with temperature in the hydraulic reservoirs lower than 10°C (50°F), and the EICAS message FLT CTRL BIT EXPIRED displayed. – Set electric hydraulic pumps 1, 2, and 3A to ON. – Perform 10 full cycles on rudder. – Perform 10 full cycles on elevator. – Set electric hydraulic pumps 1, 2, and 3A to OFF.

AOM-1502-003

– Wait until the hydraulic pressure on systems 1, 2, and 3 is less than 250 psi.

CONTINUED...

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...CONTINUED

– Pressurize hydraulic systems 1, 2 and 3 once more and wait until the hydraulic PBIT is complete. NOTE: – The hydraulic PBIT is complete after 2 min. – Do not push the FCP pushbuttons while the hydraulic PBIT is in progress. – Do not move the flight controls. If the flight controls are moved, the hydraulic PBIT is canceled. END

FUEL FEED 1 (2) FAULT NOTE: The associated Engine must be running to accomplish this procedure. – Ensure that the associated AC PUMP knob, on the FUEL control panel, is in the AUTO position. – Advance the associated Engine Thrust Lever to a N2 above 65%. – Set the associated AC PUMP knob to ON, wait 5 s, then set it back to AUTO. NOTE: If the message does not disappear at this point, report to maintenance. – Reduce associated Engine Thrust Lever to IDLE.

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GROUND SERVICING

ICE DETECTOR 1 (2) FAIL EFFECTIVITY: E170 with Primus EPIC Load 17.1 and on or Post-Mod. SB 170-31-0010/01. E190 with Primus EPIC Load 4.2 and on. WARNING: DO NOT OPERATE THE ENGINE OR PRESSURIZE THE BLEED AIR SYSTEM. THE BLEED AIR WILL FLOW OUT OF THE BLEED AIR LINE AND MAY CAUSE INJURIES TO PERSONS. WARNING: DO NOT TOUCH THE INTEGRATED PITOT/STATIC/AOA SENSOR, TAT SENSOR, STATIC PORT AND ICE DETECTORS IMMEDIATELY AFTER THE HEATER WAS SET TO OFF TO PREVENT INJURY. SURE THAT THE INTEGRATED CAUTION: MAKE PITOT/STATIC/AOA SENSORS, TAT SENSORS, ICE DETECTORS AND STATIC PORTS HAVE NO COVERS ON THEM BEFORE ACCOMPLISHING THIS PROCEDURE. THESE COMPONENTS CAN BECOME HOT DURING THIS PROCEDURE DAMAGING THEM. – On the ICE PROTECTION control panel, turn the Ice Protection System TEST Selector knob to the WING or ENG position and hold for 3 s, then release. – Wait 60 s and check if the ICE DETECTOR 1 FAIL message is not displayed on the EICAS again.

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END

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IRS 1 FAIL Open the following CBs, wait 5 s, then reset: LHCBP.................................................................... IRS 1 PWR 1 RHCBP.................................................................... IRS 1 PWR 2 END

IRS 2 FAIL Open the following CBs, wait 5 s, then reset: RHCBP.................................................................... IRS 2 PWR 1 LHCBP.................................................................... IRS 2 PWR 2 END

LG NO DISPATCH FAULT CONDITION: Message displayed during power-up. CAUTION: MAKE SURE THAT THE INTEGRATED PITOT/STATIC/AOA SENSORS, TAT SENSORS, ICE DETECTORS AND STATIC PORTS HAVE NO COVERS ON THEM BEFORE ACCOMPLISHING THIS PROCEDURE. THESE COMPONENTS CAN BECOME HOT DURING THIS PROCEDURE DAMAGING THEM. NOTE: Refer to the MAU SAFETY accomplishing this procedure.

PROCEDURES

before

Open the following CB, wait 5 s, then reset: LHCBP.................................................................... MAU 1 PWR 1 If the message is still displayed, open the following CB, wait 5 s, then reset: RHCBP.................................................................... MAU 3 PWR 1 If the message is still displayed, power down and then power up the airplane, using the Airplane Power Reset procedure.

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GROUND SERVICING

MCDU 1 FROZEN / BLANK / BLINKING / RED X / TIMEOUT MSG LOCATION: MCDU Open these CB and, after approximately 5 s, close them: LHCBP.................................................................... MCDU 1 END

MCDU 2 FROZEN / BLANK / BLINKING / RED X / TIMEOUT MSG LOCATION: MCDU Open the following CB, wait 5 s, then reset: RHCBP.................................................................... MCDU 2 END

MFD 1 FAULT Open the following CB, wait 5 s, then reset: RHCBP.................................................................... MFD 1

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MFD 2 FAULT Open the following CB, wait 5 s, then reset: LHCBP.................................................................... MFD 2 END

PFD 1 FAULT Open the following CB, wait 5 s, then reset: LHCBP.................................................................... PFD 1 END

PFD 2 FAULT Open the following CB, wait 5 s, then reset: RHCBP.................................................................... PFD 2 END

PRINTER FAULT LOCATION: PRINTER Ensure that the Printer door is completely latched. If it is not, close it properly and check if the message disappears. If Printer door is closed and message is still displayed: – Reset the Printer through the OFF button.

CONTINUED...

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If message is still displayed:

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

CAUTION: MAKE SURE THAT THE INTEGRATED PITOT/STATIC/AOA SENSORS, TAT SENSORS, ICE DETECTORS AND STATIC PORTS HAVE NO COVERS ON THEM BEFORE ACCOMPLISHING THIS PROCEDURE. THESE COMPONENTS CAN BECOME HOT DURING THIS PROCEDURE DAMAGING THEM. NOTE: Refer to MAU SAFETY PROCEDURES before accomplishing this procedure. – Open the following CBs, wait 5 s, then reset: RHCBP.................................................................... MAU 3 PWR 2 RHCBP.................................................................... MAU 2 PWR 1 LHCBP.................................................................... PRINTER If message is still displayed: – Open the following CB, wait 3 min, then reset: LHCBP.................................................................... MAU 1 PWR 3 NOTE: Wait until ″Maintenance″ is selectable on MFD 2 before testing whether printing has been restored. Note that the CMC complete power-up takes approximately 5 min. If message is still displayed: – Power down and then power up the airplane, using the Airplane Power Reset procedure.

AOM-1502-003

END

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PRINTER NOT WORKING LOCATION: PRINTER FAULT CONDITION: Printer does not print, PRINTER FAULT message is not displayed, and FAULT and LOW PPR lights do not illuminate. If any of the following conditions exist, correct it properly and check whether the printer works: – Paper roll is not properly installed. – Paper jammed. If conditions above are not found or printer still does not work: – Reset the Printer through the OFF button. If printer is still not working: CAUTION: MAKE SURE THAT THE INTEGRATED PITOT/STATIC/AOA SENSORS, TAT SENSORS, ICE DETECTORS AND STATIC PORTS HAVE NO COVERS ON THEM BEFORE ACCOMPLISHING THIS PROCEDURE. THESE COMPONENTS CAN BECOME HOT DURING THIS PROCEDURE DAMAGING THEM. NOTE: Refer to MAU SAFETY PROCEDURES before accomplishing this procedure. – Open the following CBs, wait 5 s, then reset: RHCBP.................................................................... MAU 3 PWR 2 RHCBP.................................................................... MAU 2 PWR 1 LHCBP.................................................................... PRINTER If printer is still not working: – Open the following CB, for at least 10 s, then reset: LHCBP.................................................................... MAU 1 PWR 3 NOTE: Wait until ″Maintenance″ is selectable on MFD 2 before testing whether printing has been restored. Note that the CMC complete power-up takes approximately 5 min.

CONTINUED...

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If printer is still not working:

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

– Power down and then power up the airplane, using the Airplane Power Reset procedure. END

STEER FAIL EFFECTIVITY: All airplanes. SURE THAT THE INTEGRATED CAUTION: MAKE PITOT/STATIC/AOA SENSORS, TAT SENSORS, ICE DETECTORS AND STATIC PORTS HAVE NO COVERS ON THEM BEFORE ACCOMPLISHING THIS PROCEDURE. THESE COMPONENTS CAN BECOME HOT DURING THIS PROCEDURE DAMAGING THEM. NOTE: – For airplanes Pre-Mod Load 21.2, refer to the MAU SAFETY PROCEDURES before accomplishing this procedure. – Crosscheck flap setting after the reset on MCDU’s Takeoff page 2/3. Open the following CB, after approximately 3 s, reset them: RHCBP.................................................................... MAU 2 PWR 1 EFFECTIVITY: Airplanes Post-Mod SB 170-32-0034 or SB 190-32-0022 or with equivalent factory modification incorporated. Press and hold Steer Disc Switch, press and release the Nosewheel Steering Handle and then release Steer Disc Switch.

AOM-1502-003

END

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REVISION 21

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AIRPLANE OPERATIONS MANUAL

WINDSHEAR FAIL FAULT CONDITION 1: WINDSHEAR FAIL EICAS message displayed together with GND PROX FAIL and TERRAIN FAIL EICAS messages. Power down and then power up the airplane, using the Airplane Power Reset procedure. FAULT CONDITION 2: GND PROX FAIL and TERRAIN FAIL EICAS messages NOT displayed. SURE THAT THE INTEGRATED CAUTION: MAKE PITOT/STATIC/AOA SENSORS, TAT SENSORS, ICE DETECTORS AND STATIC PORTS HAVE NO COVERS ON THEM BEFORE ACCOMPLISHING THIS PROCEDURE. THESE COMPONENTS CAN BECOME HOT DURING THIS PROCEDURE DAMAGING THEM. NOTE: – Refer to the MAU SAFETY PROCEDURES before accomplishing this procedure. – Crosscheck flap setting after the reset on MCDU’s Takeoff page 2/3. Open the following CBs, wait 5 s, then reset: RHCBP.................................................................... MAU 2 PWR 1 RHCBP.................................................................... MAU 2 PWR 2 PRI RHCBP.................................................................... MAU 2 PWR 2 SEC

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REVISION 21

AOM-1502-003

END

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

WINDSHIELD 1 (2) HTR FAIL Push out the 1 and 2 buttons on the WINDSHIELD HEATING control panel, then push them in. Wait 120 s and check if the message extinguishes. If the message is still displayed, power down and then power up the airplane, using the Airplane Power Reset procedure. END

WX FAIL LOCATION: MFD On the MCDU, press CB key then CB MENU/CB BY SYS/NAV. Open the following electronic CB, wait 15 s, then reset: WX RADAR

AOM-1502-003

END

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REVISION 21

GROUND RESETS

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!Flight Control Return to Service

FLIGHT CONTROL RETURN TO SERVICE The Flight Controls Return-to-Service Test may be performed to clear the EICAS messages FLT CTRL NO DISPATCH, FLT CTRL FAULT, SPOILERS FAULT, or GROUND SPOILERS FAIL when displayed after airplane power-up. WARNING: THIS PROCEDURE IS INTENDED TO BE ACCOMPLISHED BY QUALIFIED CREW, WITH THE AIRPLANE PARKED IN A SAFE POSITION, CLEAR OF PERSONNEL AND OTHER EQUIPMENT AND WITH BOTH ENGINES SHUTDOWN. Emergency/Parking Brake...................................... ON MAU and FCS CB.................................................. CHECK On the Circuit Brake Panels, make sure that the following CBs are pushed in: – MAU 1 PWR 1 - LHCBP (DC ESS BUS 1) – MAU 1 PWR 2 - LHCBP (DC ESS BUS 1) – MAU 1 PWR 3 - LHCBP (DC BUS 1) – MAU 3 PWR 1 - RHCBP (DC ESS BUS 2) – MAU 3 PWR 2 - RHCBP (DC BUS 2) – FCM 1 PRI - RHCBP (DC BUS 2 FLIGHT CONTROLS) – FCM 1 SEC - LHCBP (DC ESS BUS 1 FLIGHT CONTROLS) – FCM 2 PRI - RHCBP (DC ESS BUS 2 FLIGHT CONTROLS) – FCM 2 SEC - LHCBP (DC BUS 1 FLIGHT CONTROLS) – FCM 3 PRI - LHCBP (DC BUS 1 FLIGHT CONTROLS) – FCM 3 SEC - RHCBP (DC ESS BUS 2 FLIGHT CONTROLS) – FCM 4 PRI - LHCBP (DC ESS BUS 1 FLIGHT CONTROLS) – FCM 4 SEC - RHCBP (DC BUS 2 FLIGHT CONTROLS). APU or GPU........................................................... ON Make sure that the electrical PBIT is complete before starting the return-to-service test. TRIM Panel............................................................. CHECK Make sure that YAW TRIM and ROLL TRIM are in neutral position. Thrust Levers.......................................................... IDLE

CONTINUED...

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Make sure that both thrust levers are in the IDLE position. Cockpit Maintenance Panel.................................... OPEN

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

If applicable, before accessing the CMC RTS page, use an appropriate tool to get access to the FCS MAINT switch on the Cockpit Maintenance Panel (RH AFT CONSOLE). Refer to Figure 10. CMC RTS Page...................................................... SET Using CCD 2 set the cursor on the MFD 2 Systems soft key and push the enter key on CCD to open the Systems Menu. Select MAINTENANCE menu and push the CCD enter key. On the CMC MAIN MENU, access the RETURN TO SERVICE TEST page through the following sequence: SYSTEM DIAGNOSTICS → 27 FLIGHT CONTROLS → 03 FLIGHT CONTROL SYSTEM → RETURN TO SERVICE TEST. WARNING: KEEP PERSONS AND EQUIPMENT CLEAR OF THE AILERONS, ELEVATOR AND RUDDER, THESE SURFACES WILL MOVE AUTOMATICALLY AND QUICKLY DURING THIS TEST. INJURY TO PERSONS OR DAMAGE TO THE EQUIPMENT CAN OCCUR. Return-to-Service Test............................................ ACCOMPLISH To accomplish the return-to-service test, proceed as follows: 1 - On the RETURN TO SERVICE TEST page, make sure that PBIT STATUS shows PBIT PASSED for all FCMs. If all show PBIT PASSED, proceed to step (2). If one or more shows PBIT FAILED, proceed as follows: 1.1 - Make sure that the FCS MAINT switch is OFF (Figure 10, item 1). 1.2 - Power down then power up the airplane to restart the PBIT. NOTE: – It is not necessary to disconnect the external power supply from the airplane. – The electrical PBIT is complete 3 min after power-up. If any electric hydraulic pump is set to ON before the electrical PBIT is complete, the PBIT is canceled. – If the electrical PBIT is canceled, the return-to-service test cannot be performed.

AOM-1502-003

1.3 - Start the flight control system return-to-service test again. CONTINUED...

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REVISION 21

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...CONTINUED

2 - Pressurize the hydraulic system 1, 2, and 3 by setting SYS 1 – ELEC PUMP, SYS 2 – ELEC PUMP and SYS 3 ELEC PUMP A selector knobs to ON on the HYDRAULIC Panel. NOTE: Before continuing the test, make sure that the hydraulic PBIT and the daily switch configuration (Odd-Even Day Engage configuration) are complete. The Odd-Even Day Engage configuration is complete after 2 minutes and the MFD indications on the flight controls synoptic page are as follows (refer to AOM 14-08-10 for details): FLT CTRL SYNOPTIC PAGE INDICATION (MFD) RUDDER ELEV LH ELEV RH

ODD DAY

EVEN DAY

Upper Channel: HYD SYS 1 Inboard Channel: HYD SYS 2 Outboard Channel: HYD SYS 3

Lower Channel: HYD SYS 3 Outboard Channel: HYD SYS 1 Inboard Channel: HYD SYS 2

3 - Use the CCD to access the FCS synoptic page on the MFD. 4 - Make sure that in the FCS status the MODE column shows all the actuators in NORMAL mode (Figure 8, item 1). 5 - To start the test, push the START RTS TEST button (Figure 1, item 1). NOTE: If the MAIN MENU button is pushed during the test, the test stops (Figure 1, item 2). 6 - Push the FWD button (Figure 1, item 4) to go to page 2.

7.1 - Make sure that the thrust levers are in the IDLE position. If they are not, set the thrust levers to the IDLE position and restart the test on step 1. CONTINUED...

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7 - Make sure that the INHIBIT CONDITION STATUS lights show green for all FCM (Figure 2, item 5). If all are green proceed to step (8). If one or more are red, proceed as follows:

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

7.2 - If thrust levers are in the IDLE position, stop the return-to-service test and notify maintenance personnel. 8 - Set the FCS MAINT switch to ON (Figure 10, item 1). 9 - Push the CLEAR RAM button (Figure 2, item 6). 10 - Push the FWD button (Figure 2, item 7). 11 - Set the FCS MAINT switch to OFF. 12 - Examine the EICAS message window for messages related to the flight control system. If there are active error messages related to the flight control system, stop the return-to-service test and notify maintenance personnel. 13 - Push the START FCS OPS TEST button (Figure 3, item 8). 14 - Push the FWD button (Figure 3, item 9). 15 - Check the elevator control system as follows: WARNING: KEEP PERSONS AND EQUIPMENT CLEAR OF THE AILERONS, ELEVATOR AND RUDDER, THESE SURFACES WILL MOVE AUTOMATICALLY AND QUICKLY DURING THIS TEST. INJURY TO PERSONS OR DAMAGE TO THE EQUIPMENT CAN OCCUR. 15.1 - Move the pilot or copilot control column fully forward and hold it in this position for 3 s minimum. NOTE: Use a stopwatch or the airplane stopwatch as a reference to guarantee the 3 s minimum. This time requirement is very important to have this test correctly done.

AOM-1502-003

15.2 - Release the pilot or copilot control column and let it return to the neutral position.

CONTINUED...

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REVISION 21

GROUND RESETS

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AIRPLANE OPERATIONS MANUAL

...CONTINUED

15.3 - Move the pilot or copilot control column fully aft and hold it in this position for 3 s minimum. NOTE: Use a stopwatch or the airplane stopwatch as a reference to guarantee the 3 s minimum. This time requirement is very important to have this test correctly done. 15.4 - Release the pilot or copilot control column and let it return to the neutral position. 15.5 - On the FLIGHT CONTROLS MODE panel, push the ELEVATORS pushbutton (Figure 9, item 2). After 3 s, push it again. NOTE: The EICAS message ELEVATOR FAULT is displayed while the actuators are in direct mode. If the message is not displayed, stop the return-to-service test and notify maintenance personnel. 15.6 - Move the pilot or copilot control column fully forward and hold it in this position for 3 s minimum. NOTE: Use a stopwatch or the airplane stopwatch as a reference to guarantee the 3 s minimum. This time requirement is very important to have this test correctly done. 15.7 - Release the pilot or copilot control column and let it return to the neutral position. 15.8 - Move the pilot or copilot control column fully aft and hold it in this position for 3 s minimum. NOTE: Use a stopwatch or the airplane stopwatch as a reference to guarantee the 3 s minimum. This time requirement is very important to have this test correctly done. 15.9 - Release the pilot or copilot control column and let it return to the neutral position. 16 - Push the FWD button (Figure 4, item 10).

CONTINUED...

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17 - Check the rudder control system as follows:

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

WARNING: KEEP PERSONS AND EQUIPMENT CLEAR OF THE AILERONS, ELEVATOR AND RUDDER, THESE SURFACES WILL MOVE AUTOMATICALLY AND QUICKLY DURING THIS TEST. INJURY TO PERSONS OR DAMAGE TO THE EQUIPMENT CAN OCCUR. 17.1 - Move the LH rudder pedal to the end of its travel and hold it in this position for 3 s minimum. NOTE: Use a stopwatch or the airplane stopwatch as a reference to guarantee the 3 s minimum. This time requirement is very important to have this test correctly done. 17.2 - Release the LH rudder pedal and let it return to the neutral position. Hold it in this position for 3 s minimum. NOTE: Use a stopwatch or the airplane stopwatch as a reference to guarantee the 3 s minimum. This time requirement is very important to have this test correctly done. 17.3 - Move the RH rudder pedal to the end of its travel and hold it in this position for 3 s minimum. NOTE: Use a stopwatch or the airplane stopwatch as a reference to guarantee the 3 s minimum. This time requirement is very important to have this test correctly done. 17.4 - Release the RH rudder pedal and let it return to the neutral position. Hold it in this position for 3 s minimum. NOTE: Use a stopwatch or the airplane stopwatch as a reference to guarantee the 3 s minimum. This time requirement is very important to have this test correctly done. 17.5 - On the FLIGHT CONTROLS MODE panel, push the RUDDER pushbutton (Figure 9, item 3). After 3 s, push it again.

AOM-1502-003

NOTE: The EICAS messages RUDDER FAULT and YD OFF are displayed while the actuators are in direct mode. If the messages are not displayed, stop the return-to-service test and notify maintenance personnel.

CONTINUED...

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REVISION 21

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AIRPLANE OPERATIONS MANUAL

...CONTINUED

17.6 - Move the LH rudder pedal to the end of its travel and hold it in this position for 3 s minimum. NOTE: Use a stopwatch or the airplane stopwatch as a reference to guarantee the 3 s minimum. This time requirement is very important to have this test correctly done. 17.7 - Release the LH rudder pedal and let it return to the neutral position. Hold it in this position for 3 s minimum. NOTE: Use a stopwatch or the airplane stopwatch as a reference to guarantee the 3 s minimum. This time requirement is very important to have this test correctly done. 17.8 - Move the RH rudder pedal to the end of its travel and hold it in this position for 3 s minimum. NOTE: Use a stopwatch or the airplane stopwatch as a reference to guarantee the 3 s minimum. This time requirement is very important to have this test correctly done. 17.9 - Release the RH rudder pedal and let it return to the neutral position. Hold it in this position for 3 s minimum. NOTE: Use a stopwatch or the airplane stopwatch as a reference to guarantee the 3 s minimum. This time requirement is very important to have this test correctly done. 18 - Push the FWD button (Figure 5, item 11). 19 - Check the aileron control system as follows: WARNING: KEEP PERSONS AND EQUIPMENT CLEAR OF THE AILERONS, ELEVATOR AND RUDDER, THESE SURFACES WILL MOVE AUTOMATICALLY AND QUICKLY DURING THIS TEST. INJURY TO PERSONS OR DAMAGE TO THE EQUIPMENT CAN OCCUR. 19.1 - Turn the pilot or copilot control wheel fully in the counterclockwise direction and hold it in this position for 3 s minimum.

CONTINUED...

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REVISION 21

AOM-1502-003

NOTE: Use a stopwatch or the airplane stopwatch as a reference to guarantee the 3 s minimum. This time requirement is very important to have this test correctly done.

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

19.2 - Release the pilot or copilot control wheel and let it return to the neutral position. 19.3 - Turn the pilot or copilot control wheel fully in the clockwise direction and hold it in this position for 3 s minimum. NOTE: Use a stopwatch or the airplane stopwatch as a reference to guarantee the 3 s minimum. This time requirement is very important to have this test correctly done. 19.4 - Release the pilot or copilot control wheel and let it return to the neutral position. 20 - Check the speedbrake system as follows: WARNING: KEEP PERSONS AND EQUIPMENT CLEAR OF THE AILERONS, ELEVATOR AND RUDDER, THESE SURFACES WILL MOVE AUTOMATICALLY AND QUICKLY DURING THIS TEST. INJURY TO PERSONS OR DAMAGE TO THE EQUIPMENT CAN OCCUR. 20.1 - Move the speedbrake handle to the fully extended position and hold it in this position for 2 s minimum. NOTE: – The EICAS message SPEEDBRAKE LEVER DISAGREE is displayed while the speedbrake handle is not in the retracted position. – Use a stopwatch or the airplane stopwatch as reference to guarantee the 2 s minimum. This time requirement is very important to have this test correctly done. 20.2 - Move the speedbrake handle to the fully retracted position. 21 - Push the FWD (Figure 6, item 12). 22 - Set the FCS MAINT switch to ON (Figure 10, item 1). 23 - Push the CLEAR NVM button (Figure 7, item 13).

AOM-1502-003

24 - After 60 s, set the FCS MAINT switch to OFF (Figure 10, item 1). CONTINUED...

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AIRPLANE OPERATIONS MANUAL

...CONTINUED

25 - Examine the EICAS message window for messages related to the flight controls system. Proceed as follows: 25.1 - If there are EICAS messages related to flight control system, set SYS 1 – ELEC PUMP, SYS 2 – ELEC PUMP and SYS 3 ELEC PUMP A selector knobs to OFF on the HYDRAULIC Panel. Stop the return-to-service test and notify maintenance personnel. 25.2 - If there are no EICAS messages related to the flight controls system proceed to the next steps. 26 - Push the TEST COMPLT button (Figure 7, item 14). 27 - On the HYDRAULIC Panel set SYS 1 – ELEC PUMP, SYS 2 – ELEC PUMP and SYS 3 ELEC PUMP A selector knobs to OFF on the HYDRAULIC Panel. 28 - Make sure the FCS MAINT switch is in the OFF position (Figure 10, item 1). After all steps from (1) to (28) are successfully accomplished and there are no EICAS messages related to the flight control system: Cockpit Maintenance Panel.................................... CLOSE APU or GPU........................................................... AS REQUIRED If the return-to-service test is accomplished successfully, the flight crew must record a Maintenance Log entry. After performing the return-to-service test, if EICAS messages related to the flight control system remain displayed, notify the maintenance personnel.

CONTINUED...

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AOM-1502-003

......................................END OF PROCEDURE......................................

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL ...CONTINUED !!Flight Control Return to Service

RETURN TO SERVICE TEST (1 OF 7) 1. FOLLOW THE AMM DURING THIS TEST. THE PAGES THAT FOLLOWS ARE A REFERENCE ONLY. 2. PRESSURIZE THE HYDRAULIC SYSTEMS 3. PUSH THE "START RTS TEST" BUTTON TO START THE TEST. BE SURE TLA IS IN THE IDLE POSITION 1. START RTS TEST BUTTON

START RTS TEST

TEST STATUS Test Not Started PBIT STATUS FCM 1A Test Not Started FCM 1B Test Not Started FCM 2A Test Not Started FCM 2B Test Not Started FCM 3A Test Not Started FCM 3B Test Not Started FCM 4A Test Not Started FCM 4B Test Not Started PUSH THE "FWD" BUTTON TO CONTINUE THE TEST. PUSH THE "TEST MENU" BUTTON TO ABORT THE TEST AT ANY POINT OF THE TEST.

MAIN MENU

TEST MENU

FWD

3. TEST MENU BUTTON

EM170AOM130036A.DGN

2. MAIN MENU BUTTON

4. FWD BUTTON

FIGURE 1

AOM-1502-003

""

CONTINUED...

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REVISION 21

GROUND RESETS

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GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED !!Flight Control Return to Service

RETURN TO SERVICE TEST (2 OF 7) IF THE INHIBIT CONDITION STATUS IS NOT GREEN VERIFY AMM TO CONTINUE THE PROCEDURE. INHIBIT CONDITION STATUS FCM 1A

1B

2A

2B

3A

3B

4A

4B

1. SET THE FCS MAINT SWITCH TO THE ON POSITION. 5. INHIBIT CONDITION STATUS LIGHTS

FCS MAINT SWITCH STATUS FCM 1A

1B

2A

2B

3A

3B

4A

4B

3B

4A

4B

FCM ON GROUND STATUS. FCM 1A

1B

2A

2B

3A

PUSH THE "CLEAR RAM" BUTTON TO CLEAR RAM

7. FWD BUTTON

CLEAR RAM

PUSH THE "FWD" BUTTON TO CONTINUE THE TEST OR THE "PREV" BUTTON TO GO TO PREVIOUS PAGE. MAIN MENU

TEST MENU

PREV

EM170AOM130042A.DGN

6. CLEAR RAM BUTTON

FWD

FIGURE 2

CONTINUED...

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AOM-1502-003

""

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL ...CONTINUED !!Flight Control Return to Service

RETURN TO SERVICE TEST (3 OF 7) 1. SET THE FCS MAINT SWITCH TO OFF.

FCS MAINT SWITCH STATUS FCM 1A

8. START FCS OPS TEST BUTTON

1B

2A

2B

3A

3B

4A

4B

2. MAKE SURE THAT THERE ARE NO FCS ACTIVE EICAS MESSAGES. IF THERE ARE REFER TO AMM. PUSH THE "START FCS OPS TEST" TO START THE TEST

START FCS OPS TEST

WARNING: FROM NOW ON KEEP PERSONS AND EQUIPMENT CLEAR OF THE FLIGHT CONTROL SURFACES. THESE SURFACES WILL MOVE DURING THIS TEST. INJURY TO PERSONS OR EQUIPMENT CAN OCCUR.

MAIN MENU

TEST MENU

PREV

EM170AOM130037A.DGN

PUSH THE "FWD" BUTTON TO CONTINUE THE TEST OR THE "PREV" BUTTON TO GO TO PREVIOUS PAGE

FWD

9. FWD BUTTON

FIGURE 3

AOM-1502-003

""

CONTINUED...

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REVISION 21

GROUND RESETS

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AIRPLANE OPERATIONS MANUAL

...CONTINUED !!Flight Control Return to Service

RETURN TO SERVICE TEST (4 OF 7) 1. MOVE THE COLUMN FULLY FWD AND HOLD IT FOR 3 SEC MINIMUM THEN, RETURN IT TO NEUTRAL. MOVE IT FULLY AFT AND HOLD IT FOR 3 SEC MINIMUM AND RETURN IT TO NEUTRAL. 2. PUSH THE ELEVATOR FCP PUSHBUTTON AND AFTER 3 SEC, PUSH IT AGAIN. PITCH ACTIVE STATUS FCM 1A

1B

2A

2B

3A

3B

4A

4B

3A

3B

4A

4B

PITCH STANDBY STATUS FCM 1A

1B

2A

2B

3. MOVE THE COLUMN FULLY FWD AND HOLD IT FOR 3 SEC MINIMUM THEN, RETURN IT TO NEUTRAL MOVE IT FULLY AFT AND HOLD IT FOR 3 SEC MINIMUM AND RETURN IT TO NEUTRAL. FCS OPERATIONAL TEST STATUS FCM 1A FCM 1B FCM 2A FCM 2B FCM 3A FCM 3B FCM 4A FCM 4B

FCS OP test ready FCS OP test ready FCS OP test ready FCS OP test ready FCS OP test ready FCS OP test ready FCS OP test ready FCS OP test ready

MAIN MENU

TEST MENU

PREV

EM170AOM130043A.DGN

PUSH THE "FWD" BUTTON TO CONTINUE THE TEST OR THE "PREV" BUTTON TO GO TO PREVIOUS PAGE

FWD

10. FWD BUTTON

FIGURE 4

CONTINUED...

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""

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL ...CONTINUED !!Flight Control Return to Service

RETURN TO SERVICE TEST (5 OF 7) 1. MOVE THE LH RUDDER PEDAL TO THE END AND HOLD IT FOR 3 SEC MINIMUM. MOVE THE RH RUDDER PEDAL TO THE END AND HOLD IT FOR 3 SEC MINIMUM. RETURN TO NEUTRAL. 2. PUSH THE RUDDER FCP PUSHBUTTON AND AFTER 3 SEC, PUSH IT AGAIN. RUDDER ACTIVE STATUS FCM 1A 1B 2A 2B

3A

3B

4A

4B

RUDDER STANDBY STATUS FCM 1A 1B 2A 2B 3A

3B

4A

4B

3. MOVE THE LH RUDDER PEDAL TO THE END AND HOLD IT FOR 3 SEC MINIM. MOVE THE RH RUDDER PEDAL TO THE END AND HOLD IT FOR 3 SEC MINIMUM. RETURN TO NEUTRAL. FCS OPERATIONAL TEST STATUS FCM 1A FCS OP test ready FCM 1B FCS OP test ready FCM 2A FCS OP test ready FCM 2B FCS OP test ready FCM 3A FCS OP test ready FCM 3B FCS OP test ready FCM 4A FCS OP test ready FCM 4B FCS OP test ready PUSH THE "FWD" BUTTON TO CONTINUE THE TEST OR THE "PREV" BUTTON TO GO TO PREVIOUS PAGE TEST MENU

PREV

FWD

EM170AOM130038A.DGN

MAIN MENU

11. FWD BUTTON

FIGURE 5

AOM-1502-003

""

CONTINUED...

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REVISION 21

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AIRPLANE OPERATIONS MANUAL

...CONTINUED !!Flight Control Return to Service

RETURN TO SERVICE TEST (6 OF 7) 1. TURN THE CONTROL YOKE FULLY IN THE CCW DIRECTION AND HOLD IT FOR 3 SEC MINIMUN. RETURN IT TO THE NEUTRAL POSITION. 2. TURN THE CONTROL YOKE FULLY IN THE CW DIRECTION AND HOLD IT FOR 3 SEC MINIMUM. RETURN IT TO THE NEUTRAL POSITION. ROLL AXIS STATUS FCM 1A 1B 2A

2B

3A

3B

4A

4B

3. MOVE THE SPEEDBRAKE HANDLE TO THE FULLY EXTENDED POSITION AND HOLD IT FOR 2 SEC MINIMUM. RETURN IT TO THE RETRACTED POSITION. SPEEDBRAKE STATUS FCM 1A 1B 2A 2B

3A

3B

4A

4B

FCS OPERATIONAL TEST STATUS FCM 1A FCM 1B FCM 2A FCM 2B FCM 3A FCM 3B FCM 4A FCM 4B

FCS OP test ready FCS OP test ready FCS OP test ready FCS OP test ready FCS OP test ready FCS OP test ready FCS OP test ready FCS OP test ready

MAIN MENU

TEST MENU

PREV

EM170AOM130044A.DGN

PUSH THE "FWD" BUTTON TO CONTINUE THE TEST OR THE "PREV" BUTTON TO GO TO PREVIOUS PAGE

FWD

12. FWD BUTTON

FIGURE 6

CONTINUED...

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""

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL ...CONTINUED !!Flight Control Return to Service

RETURN TO SERVICE TEST (7 OF 7) 1. SET THE FCS MAINT SWITCH TO ON. FCS MAINT SWITCH STATUS FCM

1A

1B

2A

2B

3A

3B

4A

4B

2A

2B

3A

3B

4A

4B

NVM RESET READY FCM

1A

1B

2. PUSH THE "NVM CLEAR" BUTTON TO CLEAR NVM. 13. CLEAR NVM BUTTON CLEAR NVM

3. SET THE FCS MAINT SWITCH TO OFF. NVM CLEARED FCM

1A

1B

2A

2B

3A

3B

4A

4B

PUSH THE "TEST COMPLT" BUTTON TO COMPLETE THE TEST OR "PREV" BUTTON TO GO TO PREVIOUS PAGE

TEST MENU

TEST PREV

COMPLT

14. TEST COMPLETE

AOM-1502-003

BUTTON

EM170AOM130039A.DGN

MAIN MENU

FIGURE 7

CONTINUED...""

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REVISION 21

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AIRPLANE OPERATIONS MANUAL

...CONTINUED !!Flight Control Return to Service

Map

Plan

Systems FltCtrl

STATUS SURFACE

HYD SYS

MODE

RUDDER

3

NORMAL

ON

- -

ELEV LH

1

DIRECT

ON

STBY

ELEV RH

-

FAIL

- -

- -

TCAS

ACTUATORS

Weather

Checklist EM170AOM130041B.DGN

1. FCS STATUS

MFD 2

FIGURE 8

CONTINUED...

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""

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL ...CONTINUED !!Flight Control Return to Service

2. ELEVATORS PUSHBUTTON

3. RUDDER PUSHBUTTON

FLIGHT CONTROLS MODE ELEVATORS

RUDDER

SPOILERS

STALL WARNING SHAKER 2 CUTOUT

FLIGHT CONTROLS MODE PANEL

EM170AOM130045C.DGN

SHAKER 1 CUTOUT

FIGURE 9

AOM-1502-003

""

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REVISION 21

GROUND RESETS

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GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

!!Flight Control Return to Service

COPILOT SEAT RH AFT CONSOLE

NAL

ER EXT

RED

BCN

COCKPIT MAINTENANCE PANEL

BRT MAL

L AL Y STB AL M NOR

NOR

1. FCS MAINT SWITCH

EM170AOM130040B.DGN

V

NA

HTS

LIG

"" "

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GROUND RESETS

REVISION 21

AOM-1502-003

FIGURE 10

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

COLD SOAK PREPARATION The general statements below must be taken into consideration in the event of extended airplane exposure to low temperatures.

PARKING Emergency/Parking Brakes The use of Emergency/Parking Brakes may result in brakes freezing in certain conditions. Emergency/Parking Brakes should only be applied in the case of sloping and/or icy ramps. Snow or ice may be melted by the heat retained in the brakes. Wheels and tires Parking main tires in a layer of sand or mat may prevent tires from freezing on pavement surfaces. Wheel chocks should be placed against the landing gear wheels. Water and waste Drain water and waste from all tanks, if cold soak temperature is expected to be below 0°C (32°F). Covers Install all the protective covers. Flight Controls Set pitch trim to full nose down and slat/flaps up. Batteries

AOM-1502-003

If the airplane is parked powered off and not heated by an external heat source remove the batteries according to the graphic below:

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REVISION 21

Cold Weather Operation

Page 1

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

AMBIENT TEMPERATURE VERSUS EXPOSURE TIME

12 REMOVE BATTERIES

8

6

4

NO ACTION

0 −30

−25

−20 AMBIENT TEMPERATURE (°C)

−15

−10

EM170AOM030002A.DGN

EXPOSURE TIME − PARKING (HOURS)

16 OR MORE

NOTE: – The time count starts when the airplane is powered down. – The ambient temperature to be used to enter the graphic must be lowest that the airplane is to be exposed. Doors

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Cold Weather Operation

REVISION 21

AOM-1502-003

All doors and windows must be closed to avoid moisture from entering the airplane.

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

DEICING AND ANTI-ICING FLUIDS GENERAL STATEMENTS Airplane surfaces contaminated by ice, frozen precipitation or frost must be deiced before departure. The airplane must be anti-iced when the risk of freezing precipitation exists at dispatch or freezing precipitation is actually taking place. While deicing removes ice, anti-icing protects against additional icing for a certain period of time, called holdover time. A combination of both deicing and anti-icing may be performed based on the judgment of the flight crew and procedures developed by the operator. For snow pellets, snow grains, ice pellets, moderate and heavy freezing rain and hail the anti-ice fluids have little or no effect. If these conditions exist, perform a careful contamination check shortly before takeoff.

HOW IT WORKS Deicing and anti-icing fluids lower the freezing point of frozen precipitation thus delaying the accumulation of contamination on the airplane. When applied to a clean surface, the fluid forms a thin layer that has a lower freezing point than precipitation. The fluid is highly soluble in water, thus the precipitation or ice melts on contact with the fluid. These fluids also delay the onset of frost on airplane surfaces. As the ice melts, the fluid dilutes with the water, thereby causing the mixture to become less effective or to run off. Ice can begin to form again after enough dilution has occurred and the freezing point begins to rise.

DEICING Deicing is required to clean airplane surfaces contaminated by ice, snow, frost or slush.

ANTI-ICING Anti-icing is required to prevent ice accumulation.

AOM-1502-003

EFFECTS IN FLIGHT Deicing/anti-icing fluids are not intended to provide icing protection during flight. The fluid must flow off the surface during takeoff. EMBRAER has performed flight tests to investigate the effects of approved fluids on performance and handling characteristics. The flight tests demonstrated these fluids did not have a measurable effect on takeoff and climb performance.

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REVISION 21

Cold Weather Operation

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TYPES OF FLUIDS Fluids are generally mixtures of glycol, water, inhibitors, thickening agents and wetting agents. Glycol lowers the freezing point and prevents the formation of ice contamination at temperatures below freezing. The wetting agent allows the fluid to conform to the airplane surfaces. The inhibitors prevent corrosion and increase the flash point. The thickening agent, normally propylene glycol with polymers, enables the coating of fluid to remain on airplane surfaces for longer periods. All fluids must be used in accordance with the manufacturer recommendations.

ANTI ICE FLUIDS Anti-icing fluids include fluid types I, II, III or IV, in a mixture with water or undiluted. NOTE: The use of Alkali Organic Salt-based fluid is not recommended. Type I Fluid Type I fluid is not thickened and characteristically forms a thin wetting film which provides relatively limited hold-over time. Type I fluid is usually used for deicing and provides protection against refreezing when no precipitation is present. Types II, III and IV Fluids Types II, III and IV fluids form a thicker film that provides a longer holdover time. The hold-over time of the type IV fluid is greater than that of type II, which in its turn has a longer hold-over time than type III fluid. Type IV is an enhanced-performance fluid, with anti-icing effectiveness superior to Type II and provides an increased holdover time.

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Cold Weather Operation

REVISION 21

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Type IV fluids offer significant operational advantages in terms of holdover times. However, all thickened fluids may dry out and residues may accumulate in aerodynamically quiet areas. The residues may rehydrate and refreeze during flight, which can potentially restrict the movement of flight controls. Operators are reminded to frequently inspect control surfaces, gaps and tab hinges for signs of fluid residues.

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

DE ICE FLUIDS A deicing fluid is composed of heated water, or a mixture of water and type I, II, III or IV fluids. Heating is applied to a minimum temperature of 60°C to assure maximum deicing efficiency. NOTE: The use of Alkali Organic Salt-based fluid is not recommended.

HOLDOVER TIME Holdover times for the fluids are shown in tables derived for each specific fluid brand, under various temperatures, fluid concentration and precipitation category.

•

The lower limit of the published holdover time is used to indicate the estimated time of protection during moderate precipitation;

• •

The upper limit indicates the estimated time during light precipitation; Heavy conditions are not covered.

Therefore, crew experience and airline operational guidelines are required to clearly settle what heavy, moderate or light conditions are. The holdover time for the existing weather conditions has to be greater than the time from the start of fluid application to the start of takeoff roll. Holdover times should be seen as rough approximations. They simply reflect the average estimated time that an anti-icing fluid should prevent the formation of frozen contaminants on the protected surfaces. The following conditions can reduce actual holdover times:

• • • •

Windy conditions; Jet blast; Heavy precipitation or; High moisture content.

Recommended practice is to use holdover times in conjunction with a pre-takeoff check to ascertain that frozen deposits have not started to accumulate on treated surfaces. This is a check normally conducted from inside the cockpit.

AOM-1502-003

In the case of ice build-up after deicing/anti-icing fluid application, do not assume that ice will be blown off during takeoff roll. If the hold-over time expires, return for another deicing/anti-icing fluid

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REVISION 21

Cold Weather Operation

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AIRPLANE OPERATIONS MANUAL

application.

PRE-TAKEOFF CONTAMINATION CHECK This check is normally accomplished from outside the airplane when the airplane cannot be effectively inspected by a pre-takeoff check or when the holdover times has been exceeded. It must be completed within 5 min prior to beginning takeoff. The assistance of ground personnel trained and qualified to inspect the wing, empennage and fuselage is required. It is the pilot’s responsibility to decide whether or not to accept the airplane for flight. If contamination is suspected, the airplane should return for additional deicing or anti-icing. Takeoff in conditions of moderate and heavy freezing rain is not approved.

FORCED AIR DEICING GENERAL Forced air deicing is other alternative process to ground deicing only. Forced air uses an air stream to remove accumulations of frozen contamination from the airplane with or without fluid. Forced air could provide the option of injecting heated or unheated fluid into the air stream for removal of heavier frozen contamination. The pressure supply unit may be used and the forced air must be applied according to the following: – From a distance of 1.5 m to 6 m (5 ft to 20 ft). – With a maximum pressure of 34.5 kPa (5 psi). – At the minimum angle of the surface. Additionally, the following precautions must be adopted: – Forced air can not remove adhering contaminants and therefore will not eliminate the need for deicing processes.

– Forced air must not be used in areas that are made of rubber, plastic or other soft material, because damage may result.

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– Forced air can not be directed into engines, auxiliary intakes/exhausts or the Integrated Pitot/Static/AOA sensor, Static Port and TAT.

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL ...CONTINUED

– Forced air must not be used near windscreen wipers, because damage may result. – Be careful not to cause damage to landing gear and wheel bays components when removing ice. – Take care to prevent ice, snow or slush from entering and accumulating in aerodynamically quiet areas such as control surface hinge areas or from entering engine inlets. – To ensure the safety of ground personnel and passengers, the forced air application should be carefully coordinated with the flight crew. – Forced air applications can deicing/anti-icing processes.

not

eliminate

the

need

for

– A subsequent inspection of the critical surfaces will be required after the use of forced air.

DEICING AND ANTI-ICING PROCEDURES GENERAL Application of deicing and anti-icing fluid must be done by trained and qualified personnel. If both anti-icing and deicing are required, the procedure may be performed in either one or two-step process. However, a two-step deicing/anti-icing fluid application is recommended, so that residue accumulation in the critical areas is minimized. Ensure that deicing and anti-icing are performed at the latest possible time before taxiing to the takeoff position.

ONE STEP DEICING / ANTI-ICING METHOD In a one-step deicing/anti-icing procedure the holdover time starts to run from the beginning of the procedure.

TWO STEPS DEICING / ANTI-ICING METHOD

AOM-1502-003

Mixing fluids in a two-step procedure may only be performed if approved by the fluid manufacturer. With a two-step procedure the holdover time starts to run at the beginning of the anti-icing procedure. CONTINUED...

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REVISION 21

Cold Weather Operation

Page 7

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

Deicing can be performed by using:

• •

Heated water only or Heated mixture of deicing or anti-icing fluid.

Anti-Icing must be applied before residual liquids from the first deicing step freezes (typically within three minutes). This is especially important when only heated water is used to de-ice. Anti-icing can be performed with diluted or undiluted anti-icing fluid.

INFRARED DEICING Infrared deicing is an alternative process to fluid ground deicing only. The InfraTek® infrared deicing system uses infrared (IR) energy of controlled amplitude and targeted wavelength to melt frozen ice and snowfrom airplane. This electromagnetic wave form strikes the surface of materials, causing the molecules of the surface to move rapidly and generate heat. Because the IR energy does not penetrate the surface, only the outermost layers experience any direct heat from the IR. During the IR deicing process, airplane surfaces that contain ice are not exposed to any infrared energy until after the surface contamination is completely removed. NOTE: The InfraTek® Infrared deicing equipment must be FAA approved. The Infrared deicing facility operator is responsible for quality assurance during operations. The infrared deicing facility operator needs to establish communication with the crew regarding aircraft preparation: engine status, aircraft configuration and clearance to taxi both into and out of the facility. Airplane configuration: Parking Brake......................................................... ON Doors....................................................................... CLOSED Thrust Levers.......................................................... IDLE Pitch Trim................................................................ FULL NOSE DOWN EMBRAER recommends that during the Infrared deicing process flaps stay in the retracted position.

However, if the airplane will be anti-iced after an infrared deicing, use APU bleed/Engine bleed/Air Conditioning OFF configuration during fluid CONTINUED...

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Cold Weather Operation

REVISION 21

AOM-1502-003

During the infrared deicing process, engines and APU may be running, bleeds can be ON and Packs can be ON as well.

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

application. Turn bleeds on 1 min after finishing fluid application, and packs 3 min later. The Infrared deicing facility operator may request the status of contamination of aircraft being treated, request assistance on remaining contamination if not apparent from the control booth, and inform crew and the anti-ice team of the requirement to anti-ice, the type of fluid to be used and anti-icing start time. NOTE: – More than one Infrared deicing cycle may be necessary to clean up the aircraft from frozen contamination; however, the skin temperature in any aircraft surface shall be under the maximum operational temperature specified by the IR equipment specification of 130°F (55°C). – Anti-icing fluid must be applied after the IR de-ice either in case of precipitation or in case temperatures is below 35°F (2°C) and any residual water is present, so as to avoid water refreezing. – An anti-iced aircraft cannot be deiced again with the Infrared process in case the holdover time expires. The aircraft shall be deiced with regular fluid de-ice procedure.

DEICING ANTI-ICING REPETITION If the hold over time expires or contamination is found over the airplane before take off a complete deicing/anti-icing procedure must be performed. Residues from previous treatment must be flushed off first. Under no circumstances should an airplane that has been previously anti-iced receive a further spray of anti-icing fluid directly on top of the anti-icing contaminated film.

GROUND DEICING / ANTI-ICING STRATEGY

AOM-1502-003

To prevent frozen contamination on airplane surfaces deice and anti-icing operation requires that fluids are distributed uniformly over surfaces. In order to control uniformity, all horizontal surfaces must be visually checked during fluid application. The correct amount is indicated by fluid just beginning to drip off the leading edge. Do not use tools to scrape or scratch compacted snow from the airframe surfaces or from the gaps between fixed or movable surfaces. Once the CONTINUED...

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REVISION 21

Cold Weather Operation

Page 9

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

airplane has been fully deiced, then it is time to consider the prevention of any further ice contamination prior to takeoff by application of an anti-icing treatment. The following surfaces must be protected: – wing upper surface and leading edge, – horizontal stabilizer upper surface and leading edge, – elevator upper surface, – vertical stabilizer and rudder, Soft Snow can be mechanically removed by blowing cold air across the airplane surface, using brooms, soft hand scrappers or rubber scrappers. Airplane Configuration – Doors and windows – CLOSED; – THRUST LEVERS – IDLE; – PARKING BRAKE – SET; – FLAPS – UP; – Pitch trim - full nose down to help in removing contaminants; – Ailerons - neutral position; – APU – is recommended to be OFF. If APU is required during the deicing procedure deicing/anti-ice fluids must not applied directly to or near the APU air inlet; – Engine Bleeds – PUSH OUT; – Air conditioning PACKS – PUSH OUT. APU – Do not apply deice anti-ice fluid direct to the APU air inlets and exhaust duct.

Do not apply deicing/anti-icing fluids into the engine inlet duct, exhaust, precooler inlets and thrust reverser. CONTINUED...

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Cold Weather Operation

REVISION 21

AOM-1502-003

Engines deposits of snow should be mechanically removed from engine intakes using brooms, soft hand scrapers or rubber scrappers. Frozen deposits adhering to the lower surface of the intake or to the fan blades should be removed by the applying hot air. To ensure the safety of ground personnel and passengers, this should be carefully coordinated with the flight crew.

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

Fuselage – Remove all accumulated snow on the nose to avoid snow blowing back during takeoff and restricting pilot visibility. Do not apply deicing or anti-icing fluid directly on the windshield and on the cockpit windows. Fluid should be sprayed along the top centerline of the fuselage and then outboard, letting the fluid cascade down and across the windows. Fluid must not be sprayed directly onto windows and window seals, doors and doors seals, scoops or NACA air inlets. A thin layer of hoar frost on the fuselage is permitted, but only to the point you can still see the airplane markings. Be careful not to cause damage to the antennas installed along the fuselage. Landing gear and wheel bays – application of fluid in this area must be kept to a minimum. Do not allow water or fluid mixture spray on wheels and brakes to avoid damage to carbon brakes. In these areas of the airplane, it is preferable to clear snow or slush using a brush. Smart probe sensors, TAT probes, pressurization static port, and ice detectors – The fluids should be sprayed along the top of the sensors, allowing the fluid to cascade down across the sensor and deice it. Do not spray deicing fluid directly to the probes, scoops, vents, drains and static ports. Vertical surfaces: start at the top and then work down. The rudder should be in the neutral position.

AOM-1502-003

Wings and Stabilizer: Spray from the tip inboard to the root, sweeping from the leading edge in the aft direction. A 3 mm (1/8 in) frost layer is permitted under the wing surfaces. Frost is not permitted on the lower or upper surface of the horizontal stabilizer or the upper surface of the wing. It is important that the fluid be applied symmetrically to both wings so as to ensure that the aerodynamic effect of the fluid remaining is the same on both sides of the airplane. Wait one minute to use the engine or open the APU bleed valve and three minutes to use the pack valves after the deicing and anti-icing procedures are complete. The vapor from the deicing and anti-icing fluid can go into the air conditioning system when the engine or APU is in operation. This can cause damage to the air conditioning system. CONTINUED...

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REVISION 21

Cold Weather Operation

Page 11

GROUND SERVICING

AIRPLANE OPERATIONS MANUAL

...CONTINUED

A check for fluid coverage and residual ice is required immediately following application of the deicing/anti-icing fluids and should be accomplished by a qualified person. It is possible that the fluid may not flow evenly over the protected surfaces. It is essential that the wings, horizontal and vertical stabilizer are properly coated with fluid. Only Deicing/Anti-icing fluids certified under specifications below are approved to be used in the EMBRAER-170/175/190/195 airplane models: Deicing/Anti-icing Fluid Type I Types II, III and IV

Specification SAE AMS 1424 SAE AMS 1428

Refer to the fluid manufacturer’s recommendations for fluid mixture, if applicable, and holdover times. END

FORCED AIR DEICING PROCEDURES Application of deicing method must be done by trained and qualified personnel. Airplane Configuration – Doors and windows – CLOSED; – THRUST LEVERS – IDLE; – PARKING BRAKE – SET; – FLAPS – UP; – Pitch trim - full nose down to help in removing contaminants; – Ailerons - neutral position; – APU – is recommended to be OFF. If APU is required during the deicing procedure, hot air must not be applied directly to or near the APU air inlet; – Air conditioning PACKS – PUSH OUT. CONTINUED...

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REVISION 21

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– Engine Bleeds – PUSH OUT;

AIRPLANE OPERATIONS MANUAL

GROUND SERVICING

...CONTINUED

Wing and Horizontal Stabilizers – Apply the forced air from tip inboard to root, from the highest point of surface camber to the lowest. The hot air temperature must not be greater than 80°C (176°F) on these areas. Vertical Stabilizer, Dorsal Fin, and Rudder – Start at the top and then work down. The hot air temperature must not be greater than 80°C (176°F) on these areas. Fuselage – Apply the hot air along the top centerline and then outboard, letting the melted ice cascade down and across the windows. The hot air temperature must not be greater than 80°C (176°F) on these areas. Nose Radome Area, Windows and Windshields – Do not apply hot air directly on cold windshields and windows. It can cause damage to the windows. The hot air temperature must not be greater than 80°C (176°F) on these areas. Smart Probe Sensors, TAT probes, Pressurization Static Port, and Ice Detectors – If ice cause blockage of the static port holes or Integrated Pitot/Static/AOA sensors, carefully apply hot air until the ice melts. Landing Gear and Wheel Bay Areas – Remove quantities of blown snow, applying hot air directly towards the wheels, wheel bays, brakes, or tires. The hot air may also be applied to remove the ice and to release the tires from the ground. The hot air temperature must not be greater than 85°C (194°F) and the maximum air speed must not be greater than 400 km/h (250 mph) on these areas. Nacelle/Engine and APU – Forced air shall not be directed into engines and/or auxiliary intakes/exhausts, APU inlet/outlet, air/oil cooling intake, and rear fuselage door. Remove any frozen deposits that can be bonded to either lower surface of the intake or the fan blades with the application of hot air. The hot air temperature must not be greater than 93°C (200°F) on these areas.

AOM-1502-003

END

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REVISION 21

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AIRPLANE OPERATIONS MANUAL VOLUME 2 Embraer S.A.

This manual is applicable to the EMBRAER 170 airplanes LR, SU and SE models equipped with CF34-8E5 engines, the EMBRAER 175 airplanes LR model equipped with CF34-8E5 engines, operating under FAA certification.

THIS PUBLICATION IS INCOMPLETE WITHOUT AIRPLANE OPERATIONS MANUAL AOM-1502 VOLUME 1.

AOM-1502-003 DECEMBER 10, 2003 REVISION 21 - OCTOBER 20, 2016

In connection with the use of this document, Embraer does not provide any express or implied warranties and expressly disclaims any warranty of merchantability or fitness for a particular purpose. Copyright © 2016 by EMBRAER S.A. All rights reserved.

AIRPLANE OPERATIONS MANUAL

LIST OF EFFECTIVE PAGES

LIST OF EFFECTIVE PAGES (VOLUME 2) ORIGINAL ...................................0 ................................... DEC 10, 2003 REVISION ...................................1 ................................... FEB 20, 2004 REVISION ...................................2 ................................... MAY 31, 2004 REVISION ...................................3 ................................... DEC 23, 2004 REVISION ...................................4 ................................... SEP 05, 2005 REVISION ...................................5 ................................... JUL 28, 2006 REVISION ...................................6 ................................... MAY 15, 2007 REVISION ...................................7 ................................... SEP 28, 2007 REVISION ...................................8 ................................... APR 29, 2008

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REVISION Rev. 11 Rev. 11 Rev. 11 Rev. 11 Rev. 17 Rev. 17 Rev. 17 Rev. 17 Rev. 13 Rev. 13 Rev. 13 Rev. 13 Rev. 13 Rev. 13 Rev. 20 Rev. 20 Rev. 20 Rev. 20 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 10 Rev. 10 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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REVISION Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21 Rev. 21

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AIRPLANE OPERATIONS MANUAL

AOM-1502-003

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REVISION 21

AOM-1502-003

BLOCK 14-15-10 14-15-10 14-15-10 14-15-10 14-15-10 14-15-10 14-15-10 14-15-10 14-15-15 14-15-15 14-15-15 14-15-15 14-15-20 14-15-20 14-15-25 14-15-25 14-15-30 14-15-30 14-15-30 14-15-30 14-15-30 14-15-30 14-15-30 14-15-30 14-15-30 14-15-30 14-15-30 14-15-30 14-15-30 14-15-30 14-15-30 14-15-30 14-15-35 14-15-35 14-15-35 14-15-35 14-15-35 14-15-35 14-15-40 14-15-40 14-15-40 14-15-40

AIRPLANE OPERATIONS MANUAL

AIRPLANE OPERATIONS MANUAL

TABLE OF CONTENTS

AOM-1502-003

VOLUME 2 TABLE OF CONTENTS

SECTION 14-01

Airplane General Description

SECTION 14-02

Air Management System

SECTION 14-03

Automatic Flight

SECTION 14-04

Auxiliary Power Unit

SECTION 14-05

Electrical

SECTION 14-06

Engine

SECTION 14-07

Fire Protection

SECTION 14-08

Flight Controls

SECTION 14-09

Flight Instruments/COMM/NAV/FMS

SECTION 14-10

Fuel

SECTION 14-11

Hydraulic

SECTION 14-12

Ice and Rain Protection

SECTION 14-13

Landing Gear and Brakes

SECTION 14-14

Oxygen

SECTION 14-15

Warning System

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REVISION 9

Table of Contents

Page 1

TABLE OF CONTENTS

AIRPLANE OPERATIONS MANUAL

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Page 2

Table of Contents

REVISION 9

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

SECTION 14-01 AIRPLANE GENERAL DESCRIPTION TABLE OF CONTENTS Block

Page

General Information............................................. 14-01-01 .... GENERAL INFORMATION.................................... 14-01-01 ....

1 1

Airplane Basic Data............................................. 14-01-05 .... AIRPLANE BASIC DATA....................................... 14-01-05 .... EXTERNAL DIMENSIONS..................................... 14-01-05 .... CROSS SECTION................................................. 14-01-05 .... AIRPLANE ANTENNAS......................................... 14-01-05 .... MAIN SERVICE POINTS....................................... 14-01-05 ....

1 1 2 5 7 9

AOM-1502-003

Cockpit General.................................................... 14-01-10 .... 1 COCKPIT ARRANGEMENT.................................. 14-01-10 .... 1 COCKPIT PARTITION........................................... 14-01-10 .... 2 COCKPIT SEATS................................................... 14-01-10 .... 3 PILOT SEAT ADJUSTMENT.................................. 14-01-10 .... 8 PEDAL ADJUSTMENT........................................... 14-01-10 .... 9 RAMP HORN......................................................... 14-01-10 .... 10 OBSERVER SEAT................................................. 14-01-10 .... 11 COCKPIT WINDOW.............................................. 14-01-10 .... 13 Cockpit Philosophy.............................................. 14-01-15 .... COCKPIT PHILOSOPHY....................................... 14-01-15 .... DARK AND QUIET COCKPIT............................... 14-01-15 ....

1 1 2

Instrument Panels................................................ 14-01-20 .... INSTRUMENTS PANELS...................................... 14-01-20 ....

1 1

Controls and Indications..................................... 14-01-22 .... 1 AIRPLANE CONTROLS AND INDICATIONS........ 14-01-22 .... 1 COCKPIT LIGHTING............................................. 14-01-22 .... 7 PASSENGER CABIN............................................. 14-01-22 .... 12 EXTERNAL LIGHTING.......................................... 14-01-22 .... 27 SYNOPTIC PAGE ON MFD.................................. 14-01-22 .... 29

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REVISION 21

Table of Contents

Page 1

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

Block Page REINFORCED COCKPIT DOOR.......................... 14-01-22 .... 30 1

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Table of Contents

REVISION 21

AOM-1502-003

Controls and Indications..................................... 14-01-22 .... {amtosno1}14-01-22 {pg_no1}32

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

Block

Page

PC POWER/IFE PANEL.................................. Electronic Display System.................................. 14-01-25 .... ELECTRONIC DISPLAY SYSTEM (EDS)............. 14-01-25 .... PRIMARY FLIGHT DISPLAY (PFD)...................... 14-01-25 .... MULTI FUNCTION DISPLAY (MFD)...................... 14-01-25 .... ELECTRONIC CHECKLIST................................... 14-01-25 .... ENGINE INDICATION AND CREW ALERTING SYSTEM (EICAS) DISPLAY............................ 14-01-25 .... MULTIFUNCTION CONTROL DISPLAY UNIT (MCDU)............................................................ 14-01-25 .... CURSOR CONTROL DEVICE (CCD)................... 14-01-25 .... GUIDANCE PANEL................................................ 14-01-25 .... MODULAR AVIONICS UNIT (MAU)...................... 14-01-25 ....

1 1 4 7 11 15 20 21 22 22

Passenger Cabin.................................................. 14-01-35 .... 1 PASSENGER CABIN............................................. 14-01-35 .... 1 ATTENDANT STATIONS AND SEATS.................. 14-01-35 .... 6 WARDROBE.......................................................... 14-01-35 .... 9 PASSENGER SERVICE UNIT............................... 14-01-35 .... 11 LAVATORY............................................................. 14-01-35 .... 12 PC Power System................................................ 14-01-37 ....

1

Airplanes equipped with Passenger Cabin PC Power system

CABIN PC POWER SYSTEM............................... 14-01-37 ....

1

Airplanes equipped with Passenger Cabin PC Power system

CABIN PC POWER OUTLET................................ 14-01-37 ....

1

Airplanes equipped with Passenger Cabin PC Power system

CABIN PC POWER PROTECTIONS.................... 14-01-37 ....

2

Airplanes equipped with Cockpit PC Power outlets

COCKPIT PC POWER SYSTEM.......................... 14-01-37 ....

5

Airplanes equipped with Cockpit PC Power outlets

COCKPIT PC POWER OUTLET........................... 14-01-37 ....

5

AOM-1502-003

Airplanes equipped with Cockpit PC Power outlets

COCKPIT PC POWER PROTECTIONS............... 14-01-37 ....

8

Lighting................................................................. 14-01-40 .... LIGHTING.............................................................. 14-01-40 .... EXTERNAL LIGHTING.......................................... 14-01-40 .... INTERNAL LIGHTING............................................ 14-01-40 ....

1 1 1 6

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REVISION 21

Table of Contents

Page 3

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

Doors..................................................................... 14-01-45 .... DOORS.................................................................. 14-01-45 .... PASSENGER AND SERVICE DOORS................. 14-01-45 .... EMERGENCY EXITS............................................. 14-01-45 .... CARGO DOORS.................................................... 14-01-45 .... ACCESS DOORS.................................................. 14-01-45 .... DOORS WARNING SYSTEM................................ 14-01-45 ....

1 1 1 16 18 21 21

Escape Slide......................................................... 14-01-50 .... ESCAPE SLIDE..................................................... 14-01-50 .... ESCAPE SLIDE DISCONNECTION...................... 14-01-50 .... ABNORMAL OPERATION..................................... 14-01-50 .... DEFLATED ESCAPE SLIDE OPERATION........... 14-01-50 ....

1 1 4 7 8

Cockpit Door......................................................... 14-01-60 .... REINFORCED COCKPIT DOOR.......................... 14-01-60 ....

1 1

Water and Waste.................................................. 14-01-65 .... WATER................................................................... 14-01-65 .... WASTE................................................................... 14-01-65 .... WATER AND WASTE HEATING SYSTEM........... 14-01-65 .... POTABLE AND GRAY WATER SCHEMATIC....... 14-01-65 ....

1 1 2 2 3

Cargo Compartment............................................ 14-01-70 .... CARGO COMPARTMENTS................................... 14-01-70 ....

1 1

EICAS Messages.................................................. 14-01-80 .... EICAS MESSAGES............................................... 14-01-80 ....

1 1

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Table of Contents

REVISION 21

AOM-1502-003

Block Page EMERGENCY LIGHTING...................................... 14-01-40 .... 13 CARGO COMPARTMENTS LIGHTS..................... 14-01-40 .... 18

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

GENERAL INFORMATION

AOM-1502-003

This section provides a general overview of the airplane. More details of the airplane and its systems are given within each section of this manual.

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REVISION 11

General Information

Page 1

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

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General Information

REVISION 11

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE BASIC DATA The airplane is a low wing, conventional tail, pressurized airplane powered by two high by-pass ratio wing-mounted turbofan engines. The tricycle landing gear is fully retractable with dual wheels/tires for each strut. A glass panel cockpit is installed with a highly integrated on-board avionic system enabling the pilots to better monitor the airplane’s operation. !170 models, ANAC/FAA certification

The passenger configuration has four seats abreast (two to each side of the aisle) with a front galley and a rear toilet. The passenger cabin allows configurations with maximum 78 seats. Configuration with first class seats is optional. Convenient accommodations are supplied for the flight crew. " !175 models, EASA/FAA certification

The passenger configuration has four seats abreast (two to each side of the aisle) with a front galley and a rear toilet. The passenger cabin allows configuration with maximum 88 seats. Configuration with first class seats is optional. Convenient accommodations are supplied for the flight crew. "

AOM-1502-003

For detailed information on each system, refer to the appropriate section of this manual.

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REVISION 20

Airplane Basic Data

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

EXTERNAL DIMENSIONS !EMBRAER 170 Models

9.85 m (32 ft 3 in.)

10.60 m (34 ft 9 in.)

29.90 m (98 ft 1 in.)

THREE VIEW DRAWING

14-01-05

"

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Page 2

Airplane Basic Data

REVISION 20

AOM-1502-003

5.20 m (17 ft) 26.00 m (85 ft 4 in.)

EM170AOM140001A.DGN

10.00 m (32 ft 9 in.)

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

!EMBRAER 175 Models with wing tip

9.86 m (32 ft 4 in)

11.41 m (37 ft 5 in) 31.68 m (103 ft 11 in)

5.20 m (17 ft 1 in) 26.00 m (85 ft 4 in)

EM170AOM140500B.DGN

10.00 m (32 ft 10 in)

AOM-1502-003

THREE VIEW DRAWING

"

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REVISION 20

Airplane Basic Data

Page 3

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

!EMBRAER 175 Models with enhanced wing tip or POST-MOD SB-170-57-0058

9.86 m (32 ft 4 in)

11.41 m (37 ft 5 in) 31.68 m (103 ft 11 in)

4.88 m (15 ft 12 in)

5.20 m (17 ft 1 in) 28.65 m (93 ft 11 in)

EM170AOM141336B.DGN

10.00 m (32 ft 10 in)

"

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Page 4

Airplane Basic Data

REVISION 20

AOM-1502-003

THREE VIEW DRAWING

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

CROSS SECTION

ROLL ON BAG SIZE 61 X 35.5 X 25.4 cm (24 X 14 X 10 in)

78 cm

ROLL ON BAG SIZE 56 X 36 X 23 cm (22 X 14 X 9 in)

(30.80 in)

46.3 cm

5.1 cm (2 in)

(18.25 in)

2.00 m (6 ft 7 in) 1.44 m (4 ft 9 in) 3.35 m (11 ft 0 in)

48.9 cm (19.25 in)

2.52 m (8 ft 3 in) 3.01 m (9 ft 11 in)

EM170AOM140003.DGN

0.94 m (3 ft 1 in)

AOM-1502-003

STANDARD CABIN

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REVISION 20

Airplane Basic Data

Page 5

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

!Airplanes with first-class passenger seats

0.86 m (3 ft)

0.6 m (1 ft 10 in.) 0.20 m (8 in.)

0.51 m (1 ft 8 in.)

0.07 m (3 in.)

0.69 m (2 ft 3 in.) 1.44 m (4 ft 9 in.)

1.1 m (3 ft 8 in.)

2.6 m (8 ft 5 in.) 3.01 m (9 ft 11 in.)

EM170AOM080002.DGN

0.61 m (2 ft)

FIRST CLASS

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Page 6

Airplane Basic Data

REVISION 20

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE ANTENNAS !EMBRAER 170 Models

TDR 1

TCAS

TDR 2 GPS 1 COM 1

LSS GPS 2 ADF 2 VOR 2/LOC 2 VOR 1/LOC 1

ADF 1

COM 3 VOR 3 HF

SAT COM

ELT

LEGEND: TDR: TRANSPONDER MB: MARKER BEACON RAT: RADIO ALTIMETER TRANSMITTER RAR: RADIO ALTIMETER RECEIVER LOC: LOCALIZER GLIDESLOPE

DME 1 TCAS TDR 1 COM 2

TDR 2

DME 2 MB

RAT 2

RAR 1 RAR 3

AOM-1502-003

RAR 2

EM170AOM140253C.DGN

RAT 1 RAT 3

AIRPLANE ANTENNAS

14-01-05

"

Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Airplane Basic Data

Page 7

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

!EMBRAER 175 Models

TDR 1 TCAS LSS

TDR 2

ADF 1

GPS 1 COM 1

ADF 2 GPS 2

COM 3

VOR 2/LOC 2

VOR 1/LOC 1

HF SAT COM ELT

VOR 3

LEGEND: TDR: TRANSPONDER MB: MARKER BEACON RAT: RADIO ALTIMETER TRANSMITTER RAR: RADIO ALTIMETER RECEIVER LOC: LOCALIZER

GLIDESLOPE

DME 1 TCAS TDR 1 COM 2

TDR 2

DME 2

RAT 1 RAR 1 RAR 3

RAR 2 RAT 2

RAT 3

EM170AOM140533C.DGN

MB

"

14-01-05 Copyright © by Embraer. Refer to cover page for details.

Page 8

Airplane Basic Data

REVISION 20

AOM-1502-003

AIRPLANE ANTENNAS

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

MAIN SERVICE POINTS !EMBRAER 170 Models

WASTE TANK ACCESS DOOR AFT SERVICE DOOR

REFUEL/DEFUEL CONTROL PANEL

WATER TANK ACCESS DOOR

FWD CARGO DOOR

EM170AOM140247.DGN

FWD SERVICE DOOR

AFT CARGO DOOR

MAIN SERVICE POINTS

AOM-1502-003

"

14-01-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Airplane Basic Data

Page 9

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

!EMBRAER 175 Models

WASTE TANK ACCESS DOOR AFT SERVICE DOOR REFUEL/DEFUEL CONTROL PANEL WATER TANK ACCESS DOOR AFT CARGO DOOR

FWD CARGO DOOR

EM170AOM140535B.DGN

FWD SERVICE DOOR

MAIN SERVICE POINTS

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Page 10

Airplane Basic Data

REVISION 20

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

COCKPIT ARRANGEMENT

GLARESHIELD PANEL

OVERHEAD PANEL

CENTER PANEL FIRST OFFICER PANEL

CAPTAIN PANEL

CONTROL STAND

CONTROL PEDESTAL AFT PANEL

AOM-1502-003

LANDING GEAR FREE FALL LEVER COMPARTMENT

CONTROL PEDESTAL

CONTROL PEDESTAL FORWARD PANEL

OBSERVER CONSOLE

EM170AOM140002.DGN

FIRST OFFICER CONSOLE

CAPTAIN CONSOLE

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REVISION 20

Cockpit General

Page 1

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

COCKPIT PARTITION

COCKPIT DOOR HANGER

HANGER

OBSERVER SEAT

EM170AOM140006B.DGN

OBSERVER HEADSET

OBSERVER CONSOLE

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Page 2

Cockpit General

REVISION 20

AOM-1502-003

COCKPIT PARTITION

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

COCKPIT SEATS Pilot seats are fixed to slide rails that permit fore and aft adjustments. When the seats are in their aft most position, a lateral movement is also available in order to ease crew access to the seat. Manual adjustments of pilot seats are possible for vertical, lateral, aft and fore movements. A crank handle is located under the seat and allows vertical adjustments by attaching it to the plug at the aft lower part of the seat. The manual control handle allows aft and fore adjustments. Lateral movement is provided actuating both lateral locking pins.

AOM-1502-003

The five-points restraint system is equipped with a rotary buckle and an inertial reel to improve pilots comfort. The locking control is manual and simple to use.

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REVISION 20

Cockpit General

Page 3

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

!Airplanes equipped with Pneumatic Lumbar Support

RESTRAINT SYSTEM

PULL AT HINGE LEVEL FOR ARMREST SPREADING OUT

LUMBAR SUPPORT

THIGHREST UPWARD SETTING

LUMBAR SUPPORT PUSH BUTTON

THIGHREST DOWNWARD SETTING INERTIAL REAL LOCKED

SEAT UPWARD SETTING SEAT HEIGHT LOCKING

BACKREST LOCKING BACKREST RECLINING

SEAT LONGITUDINAL UNLOCKING SEAT LATERAL UNLOCKING

SPARE BACKREST LOCKING

SEAT DOWNWARD SETTING

SEAT LOCKING (NEUTRAL POSITION)

EM170AOM140007D.DGN

INERTIAL REAL UNLOCKED

COCKPIT SEATS WITH PNEUMATIC LUMBAR SUPPORT

"

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Page 4

Cockpit General

REVISION 20

AOM-1502-003

The pneumatic lumbar support has a foam bag with air inside. Using the dedicated pushbutton on the lateral of the seat, it is possible to adjust in different positions.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

!Airplanes equipped with Mechanical Lumbar Support

RESTRAINT SYSTEM

PULL AT HINGE LEVEL FOR ARMREST SPREADING OUT

LUMBAR SUPPORT

AFT

THIGHREST UPWARD SETTING

LH SIDE KNOB FWD

THIGHREST DOWNWARD SETTING INERTIAL REAL LOCKED

DOWN

SEAT UPWARD SETTING SEAT HEIGHT LOCKING

RH SIDE KNOB

BACKREST LOCKING BACKREST RECLINING

SEAT LONGITUDINAL UNLOCKING SEAT LATERAL UNLOCKING

SPARE BACKREST LOCKING

SEAT DOWNWARD SETTING

SEAT LOCKING (NEUTRAL POSITION)

EM170AOM141375A.DGN

INERTIAL REAL UNLOCKED

UP

COCKPIT SEATS WITH MECHANICAL LUMBAR SUPPORT

"

AOM-1502-003

The mechanical lumbar support has adjustments in two directions: vertical and longitudinal. A dedicated knob performs each adjustment. The RH side knob is used for vertical adjustment and the LH side knob is used for longitudinal adjustment.

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REVISION 20

Cockpit General

Page 5

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

MANUAL CONTROL HANDLE

LATERAL LOCKING PIN

EM170AOM140372.DGN

PLUG

CRANK HANDLE (UNDER THE SEAT)

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Page 6

Cockpit General

REVISION 20

AOM-1502-003

COCKPIT SEATS MANUAL ADJUSTMENTS

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

1

1

Hold the armrest at the hinge level.

2

2

Move it from the stowed position.

3

EM170AOM141158A.DGN

3

4

Move the armrest downwards to the extended position.

AOM-1502-003

COCKPIT SEAT ARMREST OPERATION

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REVISION 20

Cockpit General

Page 7

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

PILOT SEAT ADJUSTMENT The seat should be adjusted up or down until the pilot’s line of sight reaches the same horizontal plane of a sight device made up of two white spheres and a black sphere. Then, move the seat forward or aft until the opposite white sphere is aligned with the black one.

LI NE O F SI G HT

BLACK

WHITE

WHITE

FRONT VIEW

EM170AOM140008.DGN

LOWER VIEW

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Page 8

Cockpit General

REVISION 20

AOM-1502-003

PILOT SEAT ADJUSTMENT

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

PEDAL ADJUSTMENT

EM170AOM140009.DGN

Spring-loaded switches installed on the captain’s and first officer’s panels allow rudder pedal adjustments performed by electric actuators. When operating the switch, the actuator moves the pedals forward or aft, to assure pilot comfort and full rudder throw from the adjusted seat position. For rudder pedal manual adjustment call maintenance.

AOM-1502-003

PEDAL ADJUSTMENT

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REVISION 20

Cockpit General

Page 9

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

RAMP HORN

EM170AOM141267A.DGN

The ramp horn buttons installed on the captain’s and first officer’s consoles allow the cockpit crew to call the ground personnel attention. While the button is pressed, a continuous horn sounds.

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Page 10

Cockpit General

REVISION 20

AOM-1502-003

RAMP HORN

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

OBSERVER SEAT The observer seat is located aft of and between the captain’s and first officer’s seats. When in use, it’s positioned in front of the cockpit door. The seat can be stowed by folding and rotating it away from the door area against the left side of the cockpit partition behind the captain’s seat. The cockpit door can be opened or closed when the observer seat is either stowed or in use.

1

A

RELEASE THE SEAT

B

LET THE SEAT FOLD DOWN SLOWLY INTO POSITION

COCKPIT DOOR

A

2 B

F

C

F D

C

RELEASE THE STRAP

D

BRING THE SEAT BOTTOM TO A HORIZONTAL POSITION

E

PULL THE BACKREST UP TO TOP−OFF FITTING

F

LOCK THE BACKREST

EM170AOM140010.DGN

E

AOM-1502-003

OBSERVER SEAT - UNFOLD PROCEDURE

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REVISION 20

Cockpit General

Page 11

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

1 E

B

A

FASTEN THE OBSERVER SEAT SEATBELT

B

UNLOCK THE BACKREST

C

LOWER THE BACKREST DOWN

D

BRING THE SEAT BOTTOM TO VERTICAL POSITION

E

CLOSE THE STRAP

B D C

A

2

COCKPIT DOOR

F

STOW THE SEAT BEHIND THE PILOT SEAT

G

ENGAGE THE LATCH

G

EM170AOM141083B.DGN

F

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Page 12

Cockpit General

REVISION 20

AOM-1502-003

OBSERVER SEAT - FOLD PROCEDURE

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

COCKPIT WINDOW Cockpit windows may be opened in case of loss of visibility through the windshield, or for cockpit emergency evacuation on the ground. A pin protrudes near the opening handle when the window is not properly locked in the closed position.

NORMAL OPENING

1

1

PRESSING LOCK BUTTON

RED PIN

AOM-1502-003

2

PULL THE HANDLE IN AND BACKWARD

EM170AOM140011.DGN

2

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REVISION 20

Cockpit General

Page 13

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

EMERGENCY OPENING

2

1

2 1

1

PRESSING LOCK BUTTON

3

3

3

TO ESCAPE MAKE USE OF ESCAPE ROPE

PULL THE HANDLE IN AND BACKWARD

4

5

7

COCKPIT WINDOW EMERGENCY EXIT

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Page 14

Cockpit General

REVISION 20

AOM-1502-003

EM170AOM140228B.DGN

6

2

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

COCKPIT PHILOSOPHY The airplane flight deck is designed to: • Provide the necessary means to accomplish the required tasks.

• • • •

Provide acceptable and reasonable workloads. Minimize pilot errors and its consequences. Facilitate training with the commonality among the E-Jets Family. Provide optimized ergonomics aimed at safety, ease of operation, control and comfort requirements.

Both pilots can access all essential information and necessary controls for safe flying and landing. Control of the airplane systems is done via the overhead panel. Some knobs on the overhead panel have detent protection and must be pulled out to allow knob rotation. This protection prevents inadvertent knob rotation and is indicated with a detent mark between knob positions. Knob stationary positions are marked with a white rectangle, and knob momentary positions are marked with a white triangle. To assure proper signal transmission when using the selector knobs that have momentary positions, hold the knob for at least two seconds at the positions before releasing it. System failures are primarily monitored via EICAS message. The CCD and synoptics are included as an aid to the pilot monitoring systems status.

AOM-1502-003

Critical systems give total authority to the pilot by employing intuitive procedures for maximum airplane performance with minimum workload. Cockpit design facilitates simple tasks as much as possible, thus leading to increased control of situation and systems. Automation is used only to improve the task accomplishment, complementing but not substituting for the crew.

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REVISION 10

Cockpit Philosophy

Page 1

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

DARK AND QUIET COCKPIT The concept used to design and operate the airplane was based on the assumption that while in flight, all systems are normal when: • Overhead, main, glareshield and control pedestal panels have no lights on.

• •

No aural warnings are being issued. The selector knobs are positioned at twelve o’clock.

14-01-15 Copyright © by Embraer. Refer to cover page for details.

Page 2

Cockpit Philosophy

REVISION 10

AOM-1502-003

A white striped bar illuminates on any button to indicate that it is not in its normal position.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

INSTRUMENTS PANELS

AOM-1502-003

The Instruments Panels presented in this block are the Main/Glareshield/Control Pedestal Panels and the Overhead Panel.

14-01-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Instrument Panels

Page 1

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

14-01-20 Copyright © by Embraer. Refer to cover page for details.

Page 2

Instrument Panels

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

!Airplanes not equipped with Autobrake nor Printer

VS WX

FMS

PREV

V/L

HSI

BARO SET IN

MINIMUMS

hPa

RA

FD

NAV

HDG

AP

CRS

APP

HDG

YD

A/T

VNAV

DN

ALT

FPA

ALT SEL

FPA SEL

VS

FD

HSI

BARO SET IN

BARO

WX

FMS

PREV

V/L

MINIMUMS

hPa

RA

BARO

SPEED MAN

FMS

CRS

BRG

EIC

AS

WARN

CAUT

BRG

FLCH

FPR

PUSH STD

PUSH TEST

BANK

TORM

DIM

ILS

STD

16O

1OOO

4OOO 4

15O

2O

2O

14O

1O

1O

1OO

1O

1O

1 2

9O

2O

2O

3OOO 4

N

33

3O

35OO

CRS

HDG

33O

21O

21O

ILS1

21

O8:12

10

−

87.O

BARO

EICAS

ADS

IRS

VHF1 118 5O 119 25

5 A WX/R/T S STAB TGT LX

N

NEXT DEST

WPT ZUN GUP

FUEL QTY

DIST ETE FUEL 55.6 O1+32 11.4 95 O2+52 1O.4

78O

ITT

78O

88.O

N2

88.O

57OO

FF PPH 57OO FQ LB

5OOO

33

DME1 LAX 65.3 NM 2O MIN

GUP44

DN

PRESS PSI 64 TEMP

E

APU

45O C

1OO %

NEXT DEST

WPT ZUN GUP

O.7 O.9

TRIMS

SPDBRK

21OO -3OO O.1 8OO

UP

LG WRN INHIB

GND PROX G/S INHIB

3.O

YAW

4

TEST/RESET PRESS ON WAIT 1 SECOND PRESS ARM

DN

PITCH

ROLL

F

FT FPM PSI FT

2O 1O

1OO

1O

1O

9O

FSBY OVRD

LX SECT

TGT

GMAP

STAB Off

RCT

STBY

VAR Gain

ACT

Off

Gain

LX Clear

92

Weather

TURB

1OOO

2O

2O

2 1

35OO -3.O

1 2

3OOO 4 29.92 IN

M

GSPD 3OO KT

WX

TCAS

S/F

35 OO

4OOO 4 2O 1O

19O

DIST ETE FUEL 55.6 O1+32 11.4 95 O2+52 1O.4

ARM

ALT RATE P LFE

EMERG/ PRKG BRAKE

GND PROX TERR INHIB

Weather

O.O5 L

PROGRESS

CABIN

97

LP HP

S

DN

ARTEX ELT

ON

64 97 1.4 1.O

DN LOCK REL

DN

A 5 WX/R/T S STAB TGT LX

HDG ALT LOC GS

AP AT

14O

11O

1OO

WEATHER

5OOO

SPD T 125 16O 15O

125 ZUN

UP

LG/AUTOBRAKE

1OOOO OIL

TCAS

Fuel 15 SAT ^C 25 TAT ^C 3OO TAS KTS

GUP

1OO O.O5 L

PROGRESS

5

PUMPS

MIN

ZUN

1OO

WEATHER

1O

NAV1 119 1O 119 15

ET

Systems

O1O

ZUN 55. 6 NM 23 MIN

SEC/Y

87.O

N1

HR

CAGE

FMS1

INT

MIN/DY

RST

IRS1

Plan

Map GPS

SET HR/MO

AUTO

500

.57 M

CHR

SEC

UTC

26000

260

12 MFD

6

VOR1 VOR2

SENSORS

AUTO

MIN

SET

DATE

VIB

3

REVERSIONARY PANEL DISPLAYS PFD

87.O

2O

269 OO

280

15

S

CHR

10

2 28 O

GUP

W 29.92 IN

M

GSPD 3OO KT

320

FLEX TO-2 ATTCS 39

87.O

28000

+

Fuel 15 SAT ^C 25 TAT ^C 3OO TAS KTS

DME1 LAX 65.3 NM 2O MIN

GUP44

-3.O

11O

5

PUMPS

2 1

125

19O

36 O

ZUN 55.6 NM 23 MIN

Systems

CRS

HDG

33O

21O

21O

ILS1

S

21

CHR

WATER

CABIN LT TIMER

DUMP

O8:12

ARM RESET

1O

15

35 OO

FMS1

3O

125

Plan

Map

HDG ALT LOC GS

AP AT

CHR

RST

8199 M

1013 hPa

340

SPD T

12

ILS1

OFF PTT

VOR1 VOR2 VHF1 118 5O 119 25

REVERSIONARY PANEL

E

BRT

DIM

DIM

SENSORS

DISPLAYS

6

OFF

WARN

PUSH IAS−MACH

BRT BRT

BRT

CAUT

PUSH TEST

PUSH DIR

3

D/S

UP

PUSH FT−M

BRT

PFD FLOO T CHAR

FPR

PUSH STD

SRC PUSH SYNC

PUSH DIR

MFD

NAV1 119 1O 119 15

MFD MODE

AUTO PFD

MFD

ADS

IRS

EICAS

MFD MODE

CONTROLS

FLIGHT ELEVATORS

RADIO COM1

MODE

RUDDER

SPOILERS

ACARS

1 / 2

SQ

COM2

123 . 200

123 . 200

FMS AUTO

STALL

NAV2 117 . 4

SHAKER 1 CUTOUT

STBY

SHAKER 2 CUTOUT

MSGS SENT

POST FLT

116 . 8

MSGS RCVD

FREE TEXT

1471

VOX CONTACT STATUS

FLT TIMES

IDENT

TA/RA

NEW MSGS

IN FLT

WARNING

N 123 XPDR TCAS/XPDR

MAIN MENU

PRE FLT

118 . 600

118 . 600 NAV1 114 . 8 DME H PXR 115 . 6

SYS MENU

POWERPLANT

ATS MENU

START/STOP

RUN

RUN STOP

A

B

G

H

I

J

K

L

1

2

3

+/ −

M

N

O

C

D

P

Q

E

R

F

4

5

6

/

S

T

U

V

W

7

8

9

X

Y

Z

STOP

START

START

A

2

1 IGNITION

0

B

C

D

E

F

G

H

I

J

K

L

1

2

3

+/ −

M

N

O

P

Q

R

4

5

6

/

S

T

U

V

W

7

8

9

X

Y

Z

AUTO

AUTO OVRD

OFF

OFF

OVRD

2

1

T/O

0

CONFIG

EICAS FULL DISPLAY

DISPLAY

MAX TO/GA

CLOSE 0

0

RAT MANUAL DEPLOY

IDLE

1/2

MIN REV MAX REV FULL

FULL OPEN GND PROX FLAP OVRD

MIC

MIC

VHF1

VHF2

VHF3

HF

PA

SAT

AUD

VHF1

VHF2

VHF3

HF

PA

SAT

AUD

EMER NAV1

NAV2

NAV3

DME1

DME2

MKR

SELCAL

BKUP

ADF1

ADF2

ID

RAMP

SPKR

INPH

CAB

HDPH

VOL

MIC

EMER NAV1

NAV2

NAV3

DME1

DME2

MKR

SELCAL

AUTO

ADF2

ID

RAMP

INPH

CAB

HDPH

UP VOL

MIC

VHF1: 47 NORM BKUP

ADF1

SPKR

BKUP

0

VHF1: 47

MASK

NORM BKUP

AUTO

0

MASK

1

TRIM

1

COCKPIT DOOR CONTROL PITCH

ROLL

LOCK

BACKUP SW

INHIB

UNLOCKED

DN

SLAT / FLAP

TEST ON

LWD

RWD

UP YAW LEFT

SYS 1 CUTOUT

5

5

SYS 2 CUTOUT

FULL

FULL

RIGHT

OPEN PUSH

DOWN

PAX

PAX

OFF

AIRT RST

TEST

EM170AOM140499B.DGN

AILERON DISCONNECT

PUSH TO CLOSE

ELEVATOR DISCONNECT

OPEN PUSH

PPR ADV

AOM-1502-003

MAIN/GLARESHIELD/CONTROL PEDESTAL PANELS

"

14-01-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Instrument Panels

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

!Airplanes equipped with Autobrake and not equipped with Printer

VS WX

FMS

PREV

V/L

HSI

BARO SET IN

MINIMUMS

hPa

RA

FD

NAV

HDG

AP

CRS

APP

HDG

YD

A/T

VNAV

DN

ALT

FPA

ALT SEL

FPA SEL

VS

FD

HSI

BARO SET IN

BARO

WX

FMS

PREV

V/L

MINIMUMS

hPa

RA

BARO

SPEED MAN

FMS

CRS

BRG

EIC

AS

WARN

CAUT

BRG

FLCH

FPR

PUSH STD

PUSH TEST

BANK

FLOO

D/S

BRT

BRT

OFF

STBY

WARN

CAUT

PUSH TEST

/CL

K

PUSH DIR

MFD

PUSH IAS−MACH

BRT

BRT

UP

PUSH FT−M

DIM

BRT

PFD TORM

T CHAR

FPR

PUSH STD

SRC PUSH SYNC

PUSH DIR

MFD

BRT

DIM

PFD FLOO

DIM BRT

DIM

OFF

SPD T 125

HDG ALT LOC GS

AP AT

35 OO

16O

1OOO

4OOO 4

15O 14O

2O

2O

1O

1O

Plan

Map

FMS1

36 O

ZUN 55.6 NM 23 MIN

5

PUMPS

N

33

2 1

GUP44

15 SAT ^C 25 TAT ^C 3OO TAS KTS

10

87.O

MIN

10 .57 M

SET HR/MO

MIN/DY

IRS1

87.O

N1

78O

ITT

O1O

ZUN 55. 6 NM 23 MIN

SEC/Y RST

HR

ET

Fuel 15 SAT ^C 25 TAT ^C 3OO TAS KTS

5

PUMPS

N

87.O

BARO

CAGE

FMS1

AUTO

500

Systems

SPD T

GPS

SET

DATE

26000

260

OFF

Plan

Map

SEC INT

280

−

T

BRT

CHR

UTC

2O 269 OO

2 28 O

DME1 LAX 65.3 NM 2O MIN

3

320

FLEX TO-2 ATTCS 39

87.O

28000

+

Fuel

Systems

CHR

RST

8199 M

340

PTT

OFF

STD 1013 hPa

ILS1

TORM CHAR

BRT

ILS

D/S

DIM

DIM

33

MIN

DME1 LAX 65.3 NM 2O MIN

3

GUP44

125

HDG ALT LOC GS

AP AT

35 OO

16O

BRT

PTT

1OOO

4OOO 4

15O 14O

2O

2O

1O

1O

2 1

6

3O FQ LB

APU

45O C

1OO %

WPT ZUN GUP

19O

DIST ETE FUEL 55.6 O1+32 11.4 95 O2+52 1O.4

O.7 O.9

TRIMS

SPDBRK

21OO -3OO O.1 8OO

UP

LG WRN INHIB

GND PROX G/S INHIB

3.O

YAW

4

TEST/RESET PRESS ON WAIT 1 SECOND PRESS ARM

DN

PITCH

ROLL

F

FT FPM PSI FT

FSBY OVRD

LX

WX

SECT

TGT

GMAP

STAB Off

RCT

STBY

VAR Gain

ACT

Off

Gain

LX Clear

TCAS

S/F

92

Weather

TURB

1O

1O

2O

2O

1 2

3OOO 4 29.92 IN

M

GSPD 3OO KT

ARM

ALT RATE P LFE

EMERG/ PRKG BRAKE

3O

GND PROX TERR INHIB

NEXT DEST

9O

O.O5 L

PROGRESS

CABIN

97

LP HP

S

DN

A 5 WX/R/T S STAB TGT LX

ARTEX ELT

ON

PRESS PSI 64 TEMP

Weather

DN LOCK REL

DN DN

64 97 1.4 1.O

1OO 1OO

WEATHER LG/AUTOBRAKE

5OOO

1OOOO

HI

VIB

TCAS

UP

88.O

FF PPH 57OO

5OOO

OIL

NAV1 119 1O 119 15

78O

N2

57OO

CRS

HDG

33O

21O

21O

ILS1

S

21

VOR1 VOR2 VHF1 118 5O 119 25

CHR

WATER

CABIN LT TIMER

DUMP

O8:12

ARM RESET

1O

24

REVERSIONARY PANEL SENSORS

DISPLAYS

NAV1 119 1O 119 15

3

6

MFD MODE

AUTO PFD

MFD

ADS

IRS

EICAS

MFD MODE

CONTROLS

FLIGHT ELEVATORS

RADIO COM1

MODE

RUDDER

SPOILERS

ACARS

1 / 2

SQ

COM2

123 . 200

123 . 200

FMS AUTO

STALL

NAV2 117 . 4

SHAKER 1 CUTOUT

STBY

SHAKER 2 CUTOUT

MSGS SENT

POST FLT

116 . 8

MSGS RCVD

FREE TEXT

1471

VOX CONTACT STATUS

FLT TIMES

IDENT

TA/RA

NEW MSGS

IN FLT

WARNING

N 123 XPDR TCAS/XPDR

MAIN MENU

PRE FLT

118 . 600

118 . 600 NAV1 114 . 8 DME H PXR 115 . 6

SYS MENU

POWERPLANT

ATS MENU

START/STOP

RUN

RUN STOP

A

B

G

H

I

J

K

L

1

2

3

+/ −

M

N

O

C

D

P

Q

E

R

F

4

5

6

/

S

T

U

V

W

7

8

9

X

Y

Z

STOP

START

START

A

2

1 IGNITION

0

B

C

D

E

F

G

H

I

J

K

L

1

2

3

+/ −

M

N

O

P

Q

R

4

5

6

/

S

T

U

V

W

7

8

9

X

Y

Z

AUTO

AUTO OVRD

OFF

OFF

OVRD

2

1

T/O

0

CONFIG

EICAS FULL DISPLAY

DISPLAY

MAX TO/GA

CLOSE 0

0

RAT MANUAL DEPLOY

IDLE

1/2

MIN REV MAX REV FULL

FULL OPEN GND PROX FLAP OVRD

MIC

MIC

VHF1

VHF2

VHF3

HF

PA

SAT

AUD

VHF1

VHF2

VHF3

HF

PA

SAT

AUD

EMER NAV1

NAV2

NAV3

DME1

DME2

MKR

SELCAL

BKUP

ADF1

ADF2

ID

RAMP

SPKR

INPH

CAB

HDPH

VOL

MIC

EMER NAV1

NAV2

NAV3

DME1

DME2

MKR

SELCAL

AUTO

ADF2

ID

RAMP

INPH

CAB

HDPH

UP VOL

MIC

VHF1: 47 NORM BKUP

ADF1

SPKR

BKUP

0

VHF1: 47

MASK

NORM BKUP

AUTO

0

MASK

1

TRIM

1

COCKPIT DOOR CONTROL PITCH

ROLL

LOCK

BACKUP SW

INHIB

UNLOCKED

DN

SLAT / FLAP

TEST ON

LWD

RWD

UP YAW LEFT

SYS 1 CUTOUT

SYS 2 CUTOUT

5

5 FULL

FULL

RIGHT

DOWN

PAX

PAX

AILERON DISCONNECT

EM170AOM140741A.DGN

ELEVATOR DISCONNECT

MAIN/GLARESHIELD/CONTROL PEDESTAL PANELS

"

14-01-20 Copyright © by Embraer. Refer to cover page for details.

Page 4

Instrument Panels

REVISION 21

AOM-1502-003

12

E

N

VHF1 118 5O 119 25

FUEL QTY

MED

33

IRS

88.O

LO

3O

ADS

OFF RTO

W

EICAS

AUTOBRAKE

DIST ETE FUEL 55.6 O1+32 11.4 95 O2+52 1O.4

33

MFD

NEXT DEST

WPT ZUN GUP

3O

VOR1 VOR2

SENSORS

AUTO

O8:12

1OO O.O5 L

PROGRESS

1O

24

15

21

5 A WX/R/T S STAB TGT LX

15

21O

21O

S

1OO

WEATHER

12

33O

CHR

E

CRS

W

REVERSIONARY PANEL DISPLAYS

3OOO 4 29.92 IN

ILS1

PFD

W

2O

35OO -3.O

11O

6

1O

2O

HDG

ZUN

3

1O

M

E

9O GSPD 3OO KT

125

GUP

ZUN

E

1OO

19O

GUP

1 2

N

35OO -3.O

11O

6

125

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

!Commercial airplanes equipped with NO ELEC DEVICES switch and Honeywell or L3 DVDR

DVDR CONTROL PANEL

FIRE EXTINGUISHER

WINDSHIELD HEATING

CARGO SMOKE

AFT

FWD

AFT

1

2

FWD HEADPHONE

CVR DVDR ERASE TEST

1

2

APU

ICE PROTECTION

TEST

ELECTRIC AC POWER

ENGINE 1

WING

ENGINE 2

IDG 2

IDG 1 AUTO

AUTO

OFF

OFF

DISC

DISC

ROTATE TO EXTING

PULL TO SHUTOFF

ROTATE TO EXTING

PULL TO SHUTOFF

APU CONTROL OFF

MODE

TEST

AUTO

EMER STOP

ON

OFF ON

ENG

WING

AC BUS 2

AC BUS 1 GPU

HYDRAULIC

START

FUEL

AC BUS TIES APU GEN AUTO

1 OPEN

AVAIL

ENG 1

2 OPEN

ENG PUMP SHUTOFF

ENG 2

XFEED OFF LOW 1

IN USE

ENG PUMP SHUTOFF

PTU AUTO

MASTER

ON

OFF

LOW 2

AIR COND / PNEUMATIC WINDSHIELD WIPER

DC POWER TRU 1

OFF

TRU ESS

APU

TRU 2

AUTO

TIMER

AUTO

OFF

LOW

LOW

TIMER

HI

HI

S Y S 1

ELEC PUMP

ELEC PUMP

AUTO

AUTO ON

OFF

ON

OFF

S Y S 2 C

H

C ATTND

DC PUMP OFF

AUTO

OFF OFF

DC BUS 1

DC ESS BUS

BATT 2

ON

AUTO

OFF

2

PACK 1

SYS 3

EXTERNAL LIGHTS AC PUMP 1

AC PUMP 2

AUTO

AUTO ON

OFF

H

PACK 2

ON

DC BUS 2

BATT 1 DC BUS TIES AUTO

1

PAX CABIN

RECIRC

CKPT

OFF

NAV

ON

OFF

STROBE

ELEC PUMP A RED BCN

ON

ON

OFF

OFF

ELEC PUMP B AUTO

ON OFF

XBLEED

ON

OFF

WING 1 START 1

GND CONN

WING 2 START 2

OFF

MAIN PNL

OVHD PNL

EMER LT ARMED

PEDESTAL OFF

INSP

TAXI

LOGO

PASSENGER SIGNS

COCKPIT LIGHTS

NOSE ON

ON

ON

OFF

OFF

OFF

STOP DOWN

ON

APU BLEED

BLEED 2

MODE

CABIN ALT

ATTND CALL

BLEED 1

PRESSURIZATION

SIDE

AUTO UP

LFE CTRL

MAN

LANDING OFF

BRT

OFF

BRT

OFF

LEFT

ON

ON

NO ELEC DEVICES ON

OFF

OFF

OFF

DOME

STERILE

FSTN BELTS

NOSE

RIGHT

ON

ON

OFF

OFF

DUMP

AUTO

STOP DOWN

UP

LFE

OFF

OVRD

MASK DEPLOYED

MASK DEPLOY

EM170AOM140487A.DGN

ANNUNCIATORS TEST

PASSENGER OXYGEN

BRT

AOM-1502-003

OVERHEAD PANEL

"

14-01-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Instrument Panels

Page 5

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

!Commercial airplanes equipped with NO ELEC DEVICES switch and Universal DVDR

PASS/ FAIL

FDR 1

FIRE EXTINGUISHER

PASS/ FAIL

FDR 2 CVR 1

FWD EVENT

HEADPHONE

TEST

WINDSHIELD HEATING

CARGO SMOKE

CVR 2

AFT

1

2

AUDIO

ERASE

1

2

APU

ICE PROTECTION

TEST

ELECTRIC AC POWER

ENGINE 1

WING

ENGINE 2

IDG 2

IDG 1 AUTO

AUTO

OFF

OFF

DISC

DISC

ROTATE TO EXTING

PULL TO SHUTOFF

ROTATE TO EXTING

PULL TO SHUTOFF

APU CONTROL OFF

MODE

ON

TEST

AUTO

EMER STOP

OFF ON

ENG

WING

AC BUS 2

AC BUS 1

FUEL

AC BUS TIES GPU

HYDRAULIC

START

APU GEN AUTO

1 OPEN

AVAIL

ENG 1

2 OPEN

ENG PUMP SHUTOFF

ENG 2

XFEED OFF LOW 1

IN USE

ENG PUMP SHUTOFF

PTU AUTO

MASTER

ON

OFF

LOW 2

AIR COND / PNEUMATIC WINDSHIELD WIPER

DC POWER TRU 1

OFF

TRU ESS

APU

TRU 2

AUTO

TIMER

AUTO

OFF

LOW

LOW

TIMER

HI

HI

S Y S 1

ELEC PUMP

ELEC PUMP

AUTO

AUTO ON

OFF

ON

OFF

S Y S 2 C

H

C ATTND

DC PUMP OFF

AUTO

OFF OFF

DC BUS 1

DC ESS BUS

BATT 2 DC BUS TIES AUTO

OFF

AUTO

2

PACK 1

PACK 2

SYS 3

EXTERNAL LIGHTS AC PUMP 1

AC PUMP 2

AUTO

AUTO ON

OFF

H

ON

DC BUS 2

BATT 1 ON

1

PAX CABIN

RECIRC

CKPT

OFF

NAV

ON

OFF

STROBE

ELEC PUMP A RED BCN

ON

ON

OFF

OFF

ELEC PUMP B AUTO

ON OFF

XBLEED

ON

OFF

WING 1 START 1

GND CONN

WING 2 START 2

OFF

MAIN PNL

OVHD PNL

EMER LT ARMED

PEDESTAL OFF

INSP

TAXI

LOGO

PASSENGER SIGNS

COCKPIT LIGHTS

NOSE

ON

OFF

OFF

OFF

STOP DOWN

ATTND CALL ON

APU BLEED

BLEED 2

MODE

CABIN ALT

ON

BLEED 1

PRESSURIZATION

SIDE

ON

AUTO UP

LFE CTRL

MAN

LANDING OFF

BRT

OFF

LEFT ANNUNCIATORS TEST

ON

ON

NO ELEC DEVICES ON

OFF

OFF

OFF

DOME

PASSENGER OXYGEN

BRT STERILE

FSTN BELTS

NOSE

RIGHT

ON

ON

OFF

OFF

DUMP

AUTO

STOP DOWN

UP

LFE

OFF

OVRD

MASK DEPLOYED

MASK DEPLOY

OVERHEAD PANEL

"

14-01-20 Copyright © by Embraer. Refer to cover page for details.

Page 6

Instrument Panels

REVISION 21

AOM-1502-003

BRT

EM170AOM141186A.DGN

OFF

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

!Commercial airplanes equipped with NO SMKG switch and Universal DVDR

PASS/ FAIL

FDR 1

FIRE EXTINGUISHER

PASS/ FAIL

FDR 2 CVR 1

FWD EVENT

HEADPHONE

TEST

WINDSHIELD HEATING

CARGO SMOKE

CVR 2

AFT

1

2

AUDIO

ERASE

1

2

APU

ICE PROTECTION

TEST

ELECTRIC AC POWER

ENGINE 1

WING

ENGINE 2

IDG 2

IDG 1 AUTO

AUTO

OFF

OFF

DISC

DISC

ROTATE TO EXTING

PULL TO SHUTOFF

ROTATE TO EXTING

PULL TO SHUTOFF

APU CONTROL OFF

MODE

TEST

AUTO

EMER STOP

ON

OFF ON

ENG

WING

AC BUS 2

AC BUS 1

START

FUEL

AC BUS TIES GPU

HYDRAULIC

APU GEN AUTO

1 OPEN

AVAIL

ENG 1

2 OPEN

ENG PUMP SHUTOFF

ENG 2

XFEED OFF LOW 1

IN USE

ENG PUMP SHUTOFF

PTU AUTO

MASTER

ON

OFF

LOW 2

AIR COND / PNEUMATIC WINDSHIELD WIPER

DC POWER TRU 1

OFF

TRU ESS

APU

TRU 2

AUTO

TIMER

AUTO

OFF

LOW

TIMER

LOW

HI

HI

S Y S 1

ELEC PUMP

ELEC PUMP

AUTO

AUTO ON

OFF

ON

OFF

S Y S 2 C

H

C ATTND

DC PUMP OFF

AUTO

OFF

1

OFF DC BUS 1

DC ESS BUS

ON

BATT 2 DC BUS TIES AUTO

OFF

AUTO

PACK 1

PACK 2

SYS 3

EXTERNAL LIGHTS AC PUMP 1

AC PUMP 2

AUTO

AUTO ON

OFF

H

ON

DC BUS 2

BATT 1

2

PAX CABIN

RECIRC

CKPT

OFF

NAV

ON

OFF

STROBE

ELEC PUMP A RED BCN

ON

ON

OFF

OFF

ELEC PUMP B AUTO

ON OFF

XBLEED

ON

OFF

WING 1 START 1

GND CONN

WING 2 START 2

OFF

MAIN PNL

OVHD PNL

EMER LT ARMED

PEDESTAL OFF

INSP

TAXI

LOGO

PASSENGER SIGNS

COCKPIT LIGHTS

NOSE ON

ON

ON

OFF

OFF

OFF

STOP DOWN

ON

APU BLEED

BLEED 2

MODE

CABIN ALT

ATTND CALL

BLEED 1

PRESSURIZATION

SIDE

AUTO UP

LFE CTRL

MAN

LANDING OFF

BRT

OFF

BRT

OFF

LEFT DOME

STERILE

NO SMKG

ON

ON

ON

OFF

OFF

OFF

FSTN BELTS

NOSE

RIGHT

ON

ON

OFF

OFF

DUMP

AUTO

STOP DOWN

UP

LFE

OFF

OVRD

MASK DEPLOYED

MASK DEPLOY

EM170AOM141187A.DGN

ANNUNCIATORS TEST

PASSENGER OXYGEN

BRT

AOM-1502-003

OVERHEAD PANEL

"

14-01-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Instrument Panels

Page 7

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

14-01-20 Copyright © by Embraer. Refer to cover page for details.

Page 8

Instrument Panels

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE CONTROLS AND INDICATIONS ELECTRONIC DISPLAY SYSTEM CURSOR CONTROL DEVICE (CCD)

2

1

1 EICAS

2

MFD

PFD

3

4

4 LEFT

RIGHT

EM170AOM140116.DGN

3

CURSOR CONTROL DEVICE

1 - TUNING KNOB – Outer and inner knobs select value or mode in the data field enclosed by the cursor. 2 - FORMAT LOCATION BUTTONS – Places cursor on associated display (PFD, MFD or EICAS). 3 - TOUCH PAD

AOM-1502-003

– Used to move cursor.

14-01-22 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Controls and Indications

Page 1

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

4 - ENTER KEYS

14-01-22 Copyright © by Embraer. Refer to cover page for details.

Page 2

Controls and Indications

REVISION 20

AOM-1502-003

– Used to select soft keys.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

MULTI FUNCTION DISPLAY (MFD)

3

Map Navaids Airports

1

Plan

Systems

36O

5

PUMPS

WPT Ident

X

Status 15 SAT ^C 25 TAT ^C 3OO TAS KTS

N

DME1 65.3 NM LAX

GUP44

Progress

Missed APPR

2

GUP

TCAS

ZUN

Weather Terrain

]

Off

[ 1OO ]

TCAS

Weather

EM170AOM140115E.DGN

O.O5 L

1 - SOFT KEYS – Selected through the CCD cursor and enter key. 2 - MENU CONTROLS

AOM-1502-003

– Consist of checkboxes that can be selected and deselected for each function by using the CCD cursor and enter key. Square

14-01-22 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Controls and Indications

Page 3

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

checkboxes are mutually selectable, while circle checkboxes are exclusively selectable. 3 - EXIT KEY – Allows quick exit of each MFD soft key’s respective menu.

FLIGHT STATUS INFORMATION Flight number, flight time, total air temperature (TAT), static air temperature (SAT) and gross weight are displayed on the synoptic status page. It can be selected by flight crew on either MFDs.

MFD

FLIGHT EMB 9999 23 H 14 TAT -4O C SAT -56 C G.W. 696OO LB

4

3

2

EM170AOM140496A.DGN

1

1 - FLIGHT – Displays airplane flight abbreviation, number and time. 2 - STATIC AIR TEMPERATURE (SAT) – Displays static air temperature – information obtained from ADS/ADA. 3 - GROSS WEIGHT – Displays airplane gross weight – information obtained from FMS. 4 - TOTAL AIR TEMPERATURE (TAT)

14-01-22 Copyright © by Embraer. Refer to cover page for details.

Page 4

Controls and Indications

REVISION 20

AOM-1502-003

– Displays total air temperature – information obtained from ADS/ADA.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

REVERSIONARY PANEL

MAIN PANEL

2

REVERSIONARY PANEL

1

AUTO PFD

MFD

ADS

EICAS

MFD MODE

IRS

3

EM170AOM140117.DGN

SENSORS

DISPLAYS

1 - DISPLAY SELECTOR KNOB PFD: AUTO: MFD: EICAS:

display PFD information in the associated display unit. automatically reverts the MFD in case of display failure. display MFD information in the associated display unit. display EICAS information in the associated display unit.

2 - ADS SENSOR BUTTON Momentary action pushbutton: – Reverts the ADS source.

AOM-1502-003

– When ADS source reversion is selected, a white stripped bar illuminates on the button.

14-01-22 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Controls and Indications

Page 5

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

3 - IRS SENSOR BUTTON Momentary action pushbutton: – Reverts the IRS source. – When IRS source reversion is selected, a white stripped bar illuminates on the button. NOTE: Associated ADS or IRS source flag is displayed on the PFD after a reversion takes place.

EICAS FULL PANEL

EICAS FULL

1

EM170AOM140350.DGN

CONTROL PEDESTAL

1 - EICAS FULL PUSHBUTTON

14-01-22 Copyright © by Embraer. Refer to cover page for details.

Page 6

Controls and Indications

REVISION 20

AOM-1502-003

PUSH IN: EICAS full information presented. PUSH OUT: Enables the automatic EICAS de-clutter logic.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

COCKPIT LIGHTING COCKPIT LIGHTS CONTROL PANEL

OVERHEAD PANEL

1

2

3

COCKPIT LIGHTS

OFF

OVHD PNL

BRT

OFF

BRT

ANNUNCIATORS TEST

PEDESTAL

OFF

BRT

DOME ON

OFF

5

4

EM170AOM140037A.DGN

MAIN PNL

COCKPIT LIGHTS CONTROL PANEL

1 - MAIN PANEL KNOB – Turns on/off and regulates the lighting brightness of the main panel. 2 - OVERHEAD PANEL KNOB – Turns on/off and regulates the brightness of the overhead panel’s integral lighting. 3 - PEDESTAL KNOB

AOM-1502-003

– Turns on/off and regulates pedestal lighting brightness. NOTE: When the DIM POT is at OFF position, the button/window indications remain illuminated full bright as a default operations configuration.

14-01-22 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Controls and Indications

Page 7

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

4 - DOME LIGHT SWITCH – Turns two cockpit dome lights on/off. 5 - ANNUNCIATORS TEST BUTTON

14-01-22 Copyright © by Embraer. Refer to cover page for details.

Page 8

Controls and Indications

REVISION 20

AOM-1502-003

– When actuated to the TEST position (momentary position) allows checking of the striped bars and caption indications in all pushbuttons located on the main panel, overhead panel, control pedestal, allowing verification of lamp integrity.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

AOM-1502-003

4 3 4

EM170AOM140039.DGN

OFF PTT

CHA

RT

BRT

FLO

OFF

T OD/S

ORM

BRT

DIM

PFD

3

BRT

DIM

MFD

2

BRT

EIC

DIM

AS

BRT

MAIN PANEL

1

DIM

STB

BRT

Y/C

LK

DIM

2

BRT

MFD

DIM

BRT

PFD

OFF

FLO

BRT

OD/S

TOR

M

OFF

CHA

BRT

RT

PTT

GLARESHIELD LIGHTS CONTROL PANEL

14-01-22 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Controls and Indications

Page 9

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

1 - STANDBY/CLOCK CONTROL KNOB – Regulates the brightness of the standby/clock lighting. 2 - DISPLAY LIGHTING CONTROL KNOB – Regulates the brightness of the associated electronic display. 3 - FLOOD/STORM LIGHTS CONTROL KNOB – Turns on/off and regulates the brightness of the flood/storm panel lighting. – Provides maximum brightness for storm conditions in the BRT position. 4 - CHART HOLDER LIGHTING CONTROL KNOB

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Page 10

Controls and Indications

REVISION 20

AOM-1502-003

– Turns on/off and regulates the brightness of associated chart holder lighting.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

2

1

EM170AOM140040A.DGN

FLIGHT CREW READING LIGHTS

1 - OUTER RING – Turn on/off and provides dimming control. 2 - INNER RING

AOM-1502-003

– Adjusts aperture size of light pattern.

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REVISION 20

Controls and Indications

Page 11

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

PASSENGER CABIN PASSENGER SIGNS CONTROL PANEL !Airplanes equipped with NO SMKG Switch OVERHEAD PANEL

PASSENGER SIGNS

1

EMER LT ARMED OFF

ATTND CALL

2

ON

3 5

NO SMKG ON

ON

OFF

OFF

4

FSTN BELTS EM170AOM140241.DGN

STERILE

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Page 12

Controls and Indications

REVISION 20

AOM-1502-003

"

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

!Airplanes equipped with NO ELEC DEVICES switch OVERHEAD PANEL

PASSENGER SIGNS

1

EMER LT ARMED OFF

ATTND CALL ON

2

3 5

OFF

OFF

4

FSTN BELTS EM170AOM140486A.DGN

ON

NO ELEC DEVICES ON

STERILE

AOM-1502-003

"

14-01-22 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Controls and Indications

Page 13

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

1 - EMERGENCY LIGHT SELECTOR KNOB OFF: ARMED:

ON:

prevents all emergency lights from illuminating if airplane electrical power is turned off or fails. automatically illuminates all emergency lights if DC buses lose electrical power or if airplane electrical power is turned off. turns on all emergency lights.

2 - ATTENDANT CALL BUTTON – Pressing this button sounds a single hi/lo tone chime in the passenger cabin. 3 - FASTEN SEAT BELTS TOGGLE SWITCH ON: illuminates the FASTEN SEAT BELTS signs. OFF: turns off the FASTEN SEAT BELTS signs. FASTEN SEAT BELTS signs will automatically turn ON whenever the passenger mask doors are commanded open regardless of the switch position. 4 - PAX ILLUMINATED SIGNS SWITCH !Airplanes equipped with NO SMKG Switch

ON: OFF:

illuminates the NO SMOKING signs. turns off the NO SMOKING signs. "

!Airplanes equipped with NO SMKG Switch

NO SMOKING signs will automatically turn ON whenever the passenger mask doors are commanded open regardless of the switch position.

14-01-22 Copyright © by Embraer. Refer to cover page for details.

Page 14

Controls and Indications

REVISION 20

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

!Airplanes equipped with NO ELEC DEVICES switch

ON: OFF:

illuminates the TURN OFF ELECTRONIC DEVICES signs. turns off the TURN OFF ELECTRONIC DEVICES signs. "

5 - STERILE TOGGLE SWITCH ON:

AOM-1502-003

OFF:

illuminates the sterile lights located in the rainbow lights. turns off the sterile lights located in the rainbow lights.

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REVISION 20

Controls and Indications

Page 15

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

FORWARD ATTENDANT CONTROL PANEL

1

TEMPERATURE SETTING

ATTENDANT SEAT (REF.)

C

H

ENABLED

2

CABIN TEMPERATURE

CABIN LIGHTING

ON

ON

GALLEY MASTER

ON

ON

3

14 CEILING

11

FWD GALLEY AREA

BRIGHT

BRIGHT

BRIGHT

BRIGHT

DIM

DIM

DIM

DIM

EMERGENCY LIGHT

ON/ ARMED

TEST

PANEL LIGHTS

4 TEST

5

COURTESY LIGHT

RESET

OFF AUTO

LAVATORY SMOKE TEST

FWD

AFT

6

PSU

TEST

RESET

ATTENDANT PANEL

7

ATTND CALL

10 RESET

8

9

14-01-22 Copyright © by Embraer. Refer to cover page for details.

Page 16

Controls and Indications

REVISION 20

AOM-1502-003

12

FWD ENTRANCE

EM170AOM140423.DGN

13

SIDEWALL

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

1 - CABIN TEMPERATURE CONTROL – Controls cabin temperature. – The “ENABLED” led turns on to indicate the knob controls the cabin temperature. The led turns on only if the Passenger Cabin Temperature Rotating Knob in the cockpit is set to ATTND position (Refer to Section 14-02 – AMS). 2 - GALLEY MASTER SWITCH (GUARDED) – Turns off all galleys (AC power off). !Airplanes equipped with Passenger Cabin PC Power system

– Turns off the PC Power system. "

3 - PANEL LIGHTS TEST SWITCH – Provides a test of the attendant panel lights. 4 - COURTESY LIGHT RESET SWITCH – Turns on all courtesy lights for 5 min every time it is pressed. 5 - COURTESY LIGHT SWITCH AUTO: OFF:

turns on or off the courtesy lights according to passenger door position (OPEN or CLOSED). turns off the courtesy lights regardless of passenger door position.

6 - PSU TEST SWITCH – Allows the testing of the following lights: – flight attendant reading lights. – passenger reading lights. – lavatory dome light.

AOM-1502-003

– lavatory fluorescent light (from DIM to BRT mode). – attendant call indicator lights.

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REVISION 20

Controls and Indications

Page 17

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

– lavatory occupied signs. 7 - PSU RESET SWITCH – Turns off the lights previously turned on by the PSU test switch. 8 - ATTND CALL RESET SWITCH – Turns off the attendant call indicator lights, zonal lights and PSU switch lights, previously turned on due to an attendant call. 9 - AFT LAVATORY SMOKE TEST SWITCH – The switch needs to be pressed for 9 s to test the AFT lavatory smoke detector and both the cabin crew and flight crew indications. 10 - FWD LAVATORY SMOKE TEST SWITCH – The switch needs to be pressed for 9 s to test the FWD lavatory smoke detector and both the cabin crew and flight crew indications. 11 - EMERGENCY LIGHT ON/ARMED SWITCH (GUARDED) ON:

ARMED:

– turns on all emergency lights. – emergency light indication illuminates on the flight attendant control panel. automatically illuminates all emergency lights in case of DC bus electrical power loss or if airplane electrical power is turned off.

12 - EMERGENCY LIGHT TEST SWITCH – Provides a one-minute test of all passenger cabin emergency lights. 13 - CABIN LIGHTING BRIGHT/DIM SWITCH

BRIGHT: DIM:

sets the lights of the respective area to full brightness. reduces the brightness of the respective area lights.

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Page 18

Controls and Indications

REVISION 20

AOM-1502-003

Momentary press.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

14 - CABIN LIGHTING ON SWITCH

AOM-1502-003

– Turns the respective cabin light on and off.

14-01-22 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Controls and Indications

Page 19

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

AFT ATTENDANT CONTROL PANEL

LAVATORY DOOR (REF.)

1

TEMPERATURE SETTING

C

ATTENDANT SEAT (REF.)

H

ENABLED

2

CABIN TEMPERATURE

CABIN LIGHTING

ON

ON

GALLEY MASTER

ON

3

16 CEILING

13

BRIGHT

BRIGHT

BRIGHT

DIM

DIM

DIM

EMERGENCY LIGHT

ON/ ARMED

TEST

PANEL LIGHTS

4 TEST

5

COURTESY LIGHT

OFF

RESET

6

AUTO

WASTE SYSTEM

12 FWD

TANK FULL

AFT

7 SERVICE TANK

FAULT

LAVATORY FAULT

8

11 ATTND CALL

WATER SYSTEM WATER QUANTITY

10

RESET

9

FAULT 0

ATTENDANT PANEL

14-01-22 Copyright © by Embraer. Refer to cover page for details.

Page 20

Controls and Indications

REVISION 20

AOM-1502-003

14

AFT ENTRANCE

EM170AOM140424.DGN

15

SIDEWALL

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

1 - CABIN TEMPERATURE CONTROL – Controls cabin temperature. – The “ENABLED” led turns on to indicate the knob is controlling the cabin temperature. The led turns on when the Passenger Cabin Temperature Rotating Knob in the cockpit is set to ATTND position (Refer to Section 14-02 – AMS). – Available only for airplanes with dual cabin temperature control. 2 - GALLEY MASTER SWITCH (GUARDED) – Turns off all galleys (AC power off). !Airplanes equipped with Passenger Cabin PC Power system

– Turns off the PC Power system. "

3 - PANEL LIGHTS TEST SWITCH – Provides a test of the attendant panel lights. 4 - COURTESY LIGHT RESET SWITCH – Turns on all courtesy lights for 5 min. 5 - COURTESY LIGHT SWITCH AUTO: OFF:

turns on or off the courtesy lights according to passenger door position (OPEN or CLOSED). turns off the courtesy lights despite of passenger door position.

6 - TANK FULL INDICATION – Illuminates to indicate that the waste tank has reached 100% of its capacity.

AOM-1502-003

7 - SERVICE TANK INDICATION – Illuminates to indicate that the waste tank has reached 75% of its capacity.

14-01-22 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Controls and Indications

Page 21

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

8 - FAULT INDICATION – Illuminates to indicate that a fault in the waste system has been detected. NOTE: Some FWD/AFT LAVATORY FAULT indications may be cleared by means of repeated toilet flush cycles. If the FAULT indication extinguishes after repeated flush cycles, the toilet may be normally operated. If the FAULT indication does not extinguish, report to maintenance personnel. 9 - WATER TANK CAPACITY AND FAULT INDICATION – Indicates the water tank capacity. The fault light indicates one of the following conditions: – A fault in the respective (FWD or AFT) drain valve is detected. – Water level indication is not available. – In-flight drainage is not available due to a fault in the drain valve or in the drain mast heater. 10 - ATTND CALL RESET SWITCH – Turns off the attendant call indicator lights, zonal lights and PSU switch lights, previously turned on due to an attendant call. 11 - FORWARD LAVATORY FAULT INDICATION – Illuminates to indicate that the forward lavatory is out of order. 12 - AFT LAVATORY FAULT INDICATION – Illuminates to indicate that the aft lavatory is out of order. 13 - EMERGENCY LIGHT ON/ARMED SWITCH (GUARDED) turns on all emergency lights. automatically illuminates all emergency lights in case of DC bus electrical power loss or if airplane electrical power is turned off.

14-01-22 Copyright © by Embraer. Refer to cover page for details.

Page 22

Controls and Indications

REVISION 20

AOM-1502-003

ON: ARMED:

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

14 - EMERGENCY LIGHT TEST SWITCH – Provides a one-minute test of all passenger cabin emergency lights. 15 - CABIN LIGHTING BRIGHT/DIM SWITCH – Momentary press. BRIGHT: DIM:

sets the lights of the respective area to full brightness. reduces light brightness of the respective area.

16 - CABIN LIGHTING SWITCH

AOM-1502-003

– Turns on and off the respective cabin light.

14-01-22 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Controls and Indications

Page 23

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

INTERPHONE HANDSET/CRADLE ASSEMBLY

1

2

PA

3

ATTND PILOT

4

EMER PILOT

HANDSET CRADLE

EM170AOM970023A.DGN

ATTENDANT HANDSET

1 - PA BUTTON – Provides passenger announcements. 2 - ATTND BUTTON – Provides communication among flight attendants. 3 - PILOT BUTTON – Provides communication among flight attendant and cockpit crew in normal condition (normal mode).

14-01-22 Copyright © by Embraer. Refer to cover page for details.

Page 24

Controls and Indications

REVISION 20

AOM-1502-003

NOTE: If the “PILOT” button is pressed in the electrical emergency configuration (RAT deployed), the green light will illuminate and the call chime will be annunciated, but the communication channel will be unavailable. The “EMER PILOT” button can be used normally.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

4 - EMER PILOT BUTTON – Provides communication among flight attendant and cockpit crew in emergency condition (emergency mode).

PRE RECORDED ANNOUNCEMENT (PRA)

!Airplanes equipped with Pre Recorded Announcement - PBS 400 MODEL

2

3

4

5

PBS−400

1 ON

PLAY

EF

LAND

3

BRIEFING

8

9

2

LANGUAGE

7

6

4

5

EM170AOM141289A.DGN

1

1 - ON PUSH BUTTON – Turns the unit on/off. 2 - PHOTOSENSOR – Automatically controls the intensity of the LED display. 3 - LED DISPLAY – Shows diagnostic messages, available messages titles, active language and whether or not the unit is currently speaking. 4 - UP PUSH BUTTON – Used to scroll through the list of available messages. 5 - LANGUAGE SELECT

AOM-1502-003

– Select/Deselect languages for subsequent play.

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REVISION 20

Controls and Indications

Page 25

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

6 - PLAY PUSH BUTTON – Starts or pauses a messages. Pushing the PLAY push button when the message is paused will return the message from its beginning. 7 - DOWN PUSH BUTTON – Used to scroll through the list of available messages. 8 - ACTIVE LANGUAGE – Shows the symbols of the available languages. 9 - ACTIVE MESSAGE – Shows the titles of the available messages.

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Page 26

Controls and Indications

REVISION 20

AOM-1502-003

"

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

EXTERNAL LIGHTING EXTERNAL LIGHTS CONTROL PANEL OVERHEAD PANEL

1

EXTERNAL LIGHTS NAV

STROBE

RED BCN

ON

ON

OFF

OFF

2 LOGO

5

TAXI NOSE

INSP SIDE

ON

ON

ON

OFF

OFF

OFF

4

NOSE

RIGHT

ON

ON

OFF

OFF

3

EM170AOM140038.DGN

LANDING LEFT

1 - NAVIGATION, STROBE AND RED BEACON SWITCHES

AOM-1502-003

– Turns the associated light on/off.

14-01-22 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Controls and Indications

Page 27

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

2 - INSPECTION LIGHT SWITCH – Turns the inspection lights on/off. 3 - LANDING LIGHT SWITCHES – Turns the associated landing light on/off. 4 - TAXI LIGHT SWITCHES – Turns the taxi lights on/off. 5 - LOGOTYPE LIGHT SWITCH

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Page 28

Controls and Indications

REVISION 20

AOM-1502-003

– Turns the logotype lights on/off.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

SYNOPTIC PAGE ON MFD Door information is displayed on the synoptic status page. It can be selected by flight crew on either MFDs.

MFD

FWD AVIONICS COMPARTMENT ACCESS HATCH

FWD SERVICE DOOR

DOORS FWD PASSENGER DOOR

FWD CARGO COMPARTMENT DOOR

FUELING/DEFUELING COMPARTMENT ACCESS DOOR

AFT CARGO COMPARTMENT DOOR

MID AVIONICS COMPARTMENT ACCESS DOOR

AOM-1502-003

AFT PASSENGER DOOR

REAR FUSELAGE DOOR

EM170AOM140248B.DGN

AFT SERVICE DOOR

14-01-22 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Controls and Indications

Page 29

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

DOOR – On synoptic page, the door is shown as a colored solid square. GREEN: the associated door is closed. RED: the associated passenger, service or cargo door is open. AMBER: the associated access door is open. AMBER DASHED: the associated door status is undetermined. NOTE: An annunciation is displayed at the right top of the doors status windows whenever the respective door is not properly closed.

REINFORCED COCKPIT DOOR CONTROL PANEL IN THE COCKPIT

CONTROL PEDESTAL

COCKPIT DOOR CONTROL LOCK

INHIB

UNLOCKED TEST

4

3

1

2

EM170AOM140331.DGN

ON

1 - TEST BUTTON – Continually tests the DING-DONG alarm while the test button is pressed, regardless of audio selection. 2 - UNLOCKED INDICATION – Turns on when door is unlocked.

– Turns off when the INHIB pushbutton is pressed.

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Page 30

Controls and Indications

REVISION 20

AOM-1502-003

– Starts flashing when the EMERG ENTRY pushbutton on the passenger cabin control panel is pressed.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

3 - INHIB PUSHBUTTON – Inhibits the EMERG ENTRY command from cockpit door control panel in the passenger cabin for 500 s. – Lights up the red LED in the passenger cabin control panel. – The cockpit door opens if the INHIB pushbutton is not pressed up to 30 s after the EMERG ENTRY pushbutton on the passenger cabin control panel is pressed. 4 - LOCK PUSHBUTTON (GUARDED) – Controls the cockpit door’s power supply. – Activates and deactivates the electromechanical door latch. – Deactivates the inhibition control. – Resets the DING-DONG alarm and EMERG ENTRY command. – Resets the green led on the door’s control panel in the passenger cabin.

CONTROL PANEL IN THE PASSENGER CABIN !Airplanes equipped with Reinforced Cockpit Doors - latch at door !!Airplanes equipped with Reinforced Cockpit Doors - latch at door

2

3

EM170AOM140332.DGN

1

""

1 - RED LED

AOM-1502-003

– Indicates that the INHIB pushbutton in the cockpit was pressed and EMERG ENTRY is temporarily inhibited.

14-01-22 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Controls and Indications

Page 31

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

2 - GREEN LED – Indicates the cockpit door is unlocked. 3 - EMERG ENTRY PUSHBUTTON (GUARDED) – Activates the DING-DONG alarm sequence in the cockpit. "

CONTROL PANEL IN THE PASSENGER CABIN

!Airplanes equipped with Reinforced Cockpit Doors - latch at bulkhead !!Airplanes equipped with Reinforced Cockpit Doors - latch at bulkhead

4 EM170AOM140579B.DGN

3 2 1

""

1 - WHITE LED – Indicates that the unlock sequence has been started. 2 - RED LED – Indicates that the INHIB pushbutton in the cockpit was pressed and EMERG ENTRY is temporarily inhibited. 3 - GREEN LED – Indicates the cockpit door is unlocked. 4 - EMERG ENTRY PUSHBUTTON – The button needs to be pressed steadily for at least 3 s to activate the DING-DONG alarm sequence in the cockpit.

14-01-22 Copyright © by Embraer. Refer to cover page for details.

Page 32

Controls and Indications

REVISION 20

AOM-1502-003

"

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

PC POWER/IFE PANEL

!Airplanes with Cabin PC Power or IFE systems installed CONTROL PEDESTAL

PC POWER / IFE

2

IFE

1

EM170AOM140571A.DGN

CABIN PC POWER

" !Airplanes equipped with PC Power System and not equipped with IFE

1 - IFE (UNAVAILABLE) 2 - PC POWER BUTTON PUSH IN: supplies power to the AC-outlet units. PUSH OUT:disables the power supply to the AC-outlet units. A striped bar illuminates in the button.

AOM-1502-003

"

14-01-22 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Controls and Indications

Page 33

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

14-01-22 Copyright © by Embraer. Refer to cover page for details.

Page 34

Controls and Indications

REVISION 20

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

ELECTRONIC DISPLAY SYSTEM (EDS) The EDS is an advanced system that displays primary flight, navigation and system information to the flight crew and consists of: – Five Display Units (DU). – One Guidance Panel. – – – –

Two Cursor Control Devices (CCD). Two Multi-function Control Display Units (MCDU). One EICAS FULL panel. Two Reversionary Panels.

– MAU hardware. – Control I/O modules. – EDS application software on processor module. Five display units (DUs) are located on the main instrument panel. There are two Primary Flight Displays (PFD), two Multifunction Displays (MFD) and one Engine Indication and Crew Alerting System (EICAS). They are identical and interchangeable. The guidance panel is located in the center of the glareshield above the DUs. The two CCDs, one EICAS FULL panel and the MCDUs are located on the pedestal, whereas the reversionary panels are located on the main instrument panel. There are four different modes for the DU reversion control for each pilot: PFD, MFD, EICAS and AUTO. Only DU 2 and DU 4 can be reverted. DU 1 and DU 5 always operate as PFDs, and DU 3 is always an EICAS. In case of failure of one display, an automatic logic transfer will allow its information to be presented in the remaining units provided that the display selector knob is set to auto position. If the failed display is recovered, it is necessary to manually revert the affected side display selector knob to have the MFD information on associated DU (DU 2 or DU 4) and then return to the AUTO position. Both sides need to be in AUTO position in order to restore the DU failure mode condition and normal reversion operation. Rotating the display selector knob to a position other than AUTO forces that selection onto the MFD. When a pilot selected reversion occurs, the “failed/reverted from” DU is shutdown and the display will be blank.

AOM-1502-003

The auto DU reversion function will have the following display format reversion priority (highest to lowest): PFD, EICAS and MFD.

14-01-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Electronic Display System

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

PFD

EICAS

AUTO

EICAS

PFD

PFD

EICAS

MFD

AUTO

AUTO

PFD

AUTO

PFD

AUTO

EICAS

PFD

AUTO

EICAS

AUTO

PFD

PFD

MFD

EICAS

AUTO

PFD

PFD

AUTO

PFD

EICAS

EM170AOM140488D.DGN

AUTO

14-01-25 Copyright © by Embraer. Refer to cover page for details.

Page 2

Electronic Display System

REVISION 18

AOM-1502-003

EDS AUTO REVERSION LOGIC

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

PFD

MFD

AIRPLANE GENERAL DESCRIPTION

EICAS

MFD

PFD

VS WX

FMS

PREV

V/L

HSI

BARO SET IN

FD

MINIMUMS

hPa

RA

NAV

HDG

AP

A/T

VNAV

DN

ALT

FPA

ALT SEL

FPA SEL

VS

FD

HSI

BARO SET IN

BARO

WX

FMS

PREV

V/L

MINIMUMS

hPa

RA

BARO

SPEED CRS

HDG

APP

MAN

FMS

YD

CRS

BRG

EICA

S

WARN

CAUT

BRG

FLCH

FPR

PUSH STD

PUSH TEST

BANK

UP

PUSH FT−M

PUSH SYNC

CAUT

PUSH TEST

WARN

PUSH DIR

PUSH IAS−MACH

BRT DIM BRT

D/STO DIM BRT DIM

ILS

STD

1O

1 2

2O

3OOO 4

19O

FMS1

36O

ZUN 55.6 NM 23 MIN

N

33

CRS

HDG

33O

21O

21O

21

3O CHR

O8:12

10

SET

EICAS

ADS

IRS

VHF1 118 5O 119 25

HR/MO

MIN/DY

RST

87.O

N1

78O

ITT

78O

88.O

N2

88.O

5 A WX/R/T S STAB TGT LX

O1O

ZUN 55. 6 NM 23 MIN

SEC/Y AUTO

500

ET

O.O5 L

PROGRESS

NEXT DEST

WPT ZUN GUP

OFF

DIST ETE FUEL 55.6 O1+32 11.4 95 O2+52 1O.4

57OO

LO

FUEL QTY

MED

RTO

N

MIN

33

15 SAT ^C 25 TAT ^C 3OO TAS KTS DME1 LAX 65.3 NM 2O MIN

GUP44

FF PPH 57OO FQ LB

5OOO

LG/AUTOBRAKE

OIL

VIB

DN

E

DN

A 5 WX/R/T S STAB TGT LX

ARTEX ELT

ON

64

PRESS PSI 64

97

TEMP

1.4 1.O

APU

45O C

1OO %

O.O5 L

PROGRESS

NEXT DEST

WPT ZUN GUP

21OO -3OO O.1 8OO

ALT RATE P LFE

O.7 O.9

TRIMS

SPDBRK

FT FPM PSI FT

TEST/RESET PRESS ON WAIT 1 SECOND PRESS ARM

DN

PITCH

ROLL

F

UP

LG WRN INHIB

GND PROX G/S INHIB

3.O

YAW

4

LX SECT

RCT

VAR Gain

ACT

Off

Gain

92

TURB

Weather

1OOO

2O

1O

2 1

1O

35OO

1O

1O

1 2

2O

2O

3OOO 4 29.92 IN

M

GSPD 3OO KT

LX Clear

STAB Off

STBY

S/F

35 OO

4OOO 4 2O

9O

CRS

HDG

33O

21O

21O

ILS1

TGT

GMAP

TCAS

HDG ALT LOC GS

AP AT

-3.O

1OO

19O

DIST ETE FUEL 55.6 O1+32 11.4 95 O2+52 1O.4

FSBY OVRD WX

ARM

CABIN

97

LP HP

S

DN LOCK REL

DN

5OOO

1OOOO

HI

Weather

SPD T 125 16O 15O

11O

1OO

WEATHER

14O

125 ZUN

UP

EMERG/ PRKG BRAKE

GND PROX TERR INHIB

TCAS

5

PUMPS

87.O HR

AUTOBRAKE

1O

NAV1 119 1O 119 15

FMS1

SET

DATE

26000 IRS1

BARO

CAGE

Fuel

GPS INT

269 OO

10 .57 M

1OO

12 MFD

6

VOR1 VOR2

SENSORS

AUTO

3

REVERSIONARY PANEL DISPLAYS

UTC

2O

2

28 O 260

Systems

GUP

1OO

WEATHER

15

S

320

280

−

ZUN

W 29.92 IN

M

GSPD 3OO KT

15 SAT ^C 25 TAT ^C 3OO TAS KTS

DME1 LAX 65.3 NM 2O MIN

GUP44

GUP

-3.O

ILS1

5

PUMPS

2 1

35OO

Plan

Map

S

21

CHR

WATER

CABIN LT TIMER

DUMP

O8:12

ARM RESET

1O

15

1O

2O

CHR

SEC

12

1OOO

4OOO 4 2O

1O

MIN

VOR1 VOR2 VHF1 118 5O 119 25

REVERSIONARY PANEL

E

35 OO

2O 1O

9O

11O

87.O

3O

HDG ALT LOC GS

AP AT

1OO

FLEX TO-2 ATTCS 39

87.O

28000

+

Fuel

SENSORS

DISPLAYS

6

SPD T 125 16O 15O 14O

125

Systems

CHR

RST

8199 M

1013 hPa

ILS1

340

Plan

Map

3

BRT OFF BRT OFF PTT

PFD

FPR

PUSH STD

SRC

PUSH DIR

MFD PFD RM FLOO T CHAR

MFD MODE

NAV1 119 1O 119 15

AUTO PFD

MFD

ADS

IRS

EICAS

MFD MODE

CONTROLS

FLIGHT ELEVATORS

RADIO COM1

MODE SPOILERS

ACARS

123 . 200

FMS AUTO

STALL

NAV2 117 . 4

NEW MSGS

IN FLT

WARNING

SHAKER 1 CUTOUT

SHAKER 2 CUTOUT

MSGS SENT

POST FLT

116 . 8

MSGS RCVD

FREE TEXT

N 123 XPDR 1471

VOX CONTACT

FLT TIMES

IDENT

TA/RA

MAIN MENU

PRE FLT

118 . 600

118 . 600

TCAS/XPDR STBY

RUDDER

1 / 2 COM2

SQ

123 . 200

NAV1 114 . 8 DME H PXR 115 . 6

STATUS

SYS MENU

POWERPLANT

ATS MENU

START/STOP

RUN

RUN STOP

REVERSIONARY PANEL

A

B

G

H

I

J

K

L

1

2

3

+/ −

M

N

O

C

D

P

Q

E

R

F

4

5

6

/

S

T

U

V

W

7

8

9

X

Y

Z

STOP

START

START

A

2

1 IGNITION

0

B

C

D

E

F

G

H

I

J

K

L

1

2

3

+/ −

M

N

O

P

Q

R

4

5

6

/

U

V

W

7

8

9

MCDU

AUTO

AUTO OVRD

OFF

OFF

OVRD

2

1

T/O

S

T

X

Y

0

Z

CONFIG

EICAS FULL DISPLAY

DISPLAY

MAX TO/GA

CLOSE 0

0

RAT MANUAL DEPLOY

IDLE

1/2

MIN REV MAX REV FULL

FULL OPEN GND PROX FLAP OVRD

MIC

MIC

VHF2

VHF3

HF

SAT

NAV1

NAV2

NAV3

ADF1

ADF2

DME1

VHF1

DME2

MKR

PA

AUD

VHF2

VHF3

HF

SAT

NAV1

NAV2

NAV3

ADF1

ADF2

DME1

VHF1

DME2

MKR

PA

AUD

EMER

SELCAL

BKUP

ID

RAMP

SPKR

INPH

CAB

HDPH

VOL

MIC

EMER

SELCAL

BKUP

AUTO

INPH

CAB

HDPH

UP VOL

MIC

VHF1: 47 NORM BKUP

ID

RAMP

SPKR

0

VHF1: 47

MASK

NORM BKUP

AUTO

0

MASK

1

TRIM

1

PITCH

ROLL

BACKUP SW

SLAT / FLAP

DN LWD

RWD

UP YAW LEFT

SYS 1 CUTOUT

5

SYS 2 CUTOUT

5

FULL

FULL

RIGHT

OPEN PUSH

DOWN

PAX

PAX

OFF

AILERON DISCONNECT

AIRT RST

TEST

PUSH TO CLOSE

ELEVATOR DISCONNECT

OPEN PUSH

PPR ADV

EICAS FULL PANEL

EM170AOM140112B.DGN

MCDU

CCD

AOM-1502-003

AIRPLANE DISPLAYS

14-01-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Electronic Display System

Page 3

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

PRIMARY FLIGHT DISPLAY (PFD) The PFD displays information such as airspeed indicator, altitude indicator, ADI, HSI, vertical speed indicator, radio aids, autopilot, flight director and radio altitude data. They are displayed in two sections, each one presenting a group of information. In the event of a display failure, information may be presented in the MFD by appropriately setting the reversionary panel. Certain PFD internal failures will result in a large red “X” covering the PFD screen. In case of mismatched information between two PFDs, a monitor warning annunciation is displayed when an unacceptable cross compare of any of the parameters that follow are detected. – Pitch – – – –

Roll Attitude Heading BARO altitude

– Airspeed – Localizer – – – – –

Glideslope Radar altitude Flight path angle EICAS Crew Alerting System (CAS)

14-01-25 Copyright © by Embraer. Refer to cover page for details.

Page 4

Electronic Display System

REVISION 18

AOM-1502-003

The display controller portion of the guidance panel allows the selection of PFD HSI formats, navigation sources, weather display, and bearing pointer selection.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

MAIN PANEL

AVIATE

3O OO

16O

4OOO 4

15O

FS

14O

2O

2O

1O

1O

2 1

AC

125

35OO

AP

-3.O

11O

RF

1OO

1O

9O

19O

1OOO

2O

1O

1 2

2O

3OOO 4 29.92 IN

M

GSPD 3OO KT

CRS

HDG

21O

21O

21O

ILS1

21

3O

12

W

E

33

3

6

VHF1 118 5O 119 25

N

VOR1 VOR2

CHR

O8:12

1O

24

15

S

− AUTOPILOT APPROACH STATUS ANNUNCIATOR − FLIGHT MODE ANNUNCIATOR − ATTITUDE AND SIDE SLIP − ALTITUDE − AIRSPEED/MACH − AIRSPEED TREND VECTOR − VERTICAL SPEED − FLIGHT PATH ANGLE − FPA ACCELERATION POINTER − FLIGHT DIRECTOR − TCAS RESOLUTION ADVISORY − WINDSHEAR − RADIO ALTIMETER − MINIMUMS

NAV1 119 1O 119 15

NAVIGATE AND COMMUNICATE − HEADING − ILS/VOR/DME − ADF − RADIO COMMUNICATION TUNING − RADIO NAVIGATION TUNING − FMS ANNUNCIATION/INDICATION − WIND − ELAPSED TIME − GROUND SPEED − RNP (FMS)

EM170AOM140190C.DGN

AP AT

SPD T

115

APPR2 LOC GS

AOM-1502-003

PFD DISPLAY PHILOSOPHY

14-01-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Electronic Display System

Page 5

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

MAIN PANEL

APPR1 LOC GS

AP AT

SPD T 115

3O OO

16O

4OOO 4

15O

FS

14O

2O

2O

1O

1O

2 1

AC

125

35OO

AP

1OOO

-3.O RF

1OO 9O

1O

1O

2O

2O

1 2

GSPD 3OO KT

CRS

21O

21O

21

1O

24

15

S

CHR

O8:12

3O

12

W

E

33 N

3

6

VHF1 118 5O 119 25

29.92 IN

HDG

21O

ILS1

VOR1 VOR2

3OOO 4

BARO 4OO

M

NAV1 119 1O 119 15

EM170AOM140401A.DGN

11O

19O

1OOO

14-01-25 Copyright © by Embraer. Refer to cover page for details.

Page 6

Electronic Display System

REVISION 18

AOM-1502-003

PFD DISPLAY

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

MULTI FUNCTION DISPLAY (MFD) The MFD displays map and plan navigation formats, various systems synoptic formats selectable by the flight crew, and also the status page. The MFD provides redundancy to display both the PFD and EICAS formats based upon reversion. It also has the ability to display maintenance information. The MFD consists of menu softkeys, on the top and bottom of the screen, which are used to select formats and control various systems.

MAIN PANEL

Map

FMS1 ZUN 55.6 NM 23 MIN

Plan

Systems

36 O

5

PUMPS

N

33

3O

GUP44

Fuel 15 SAT ^C 25 TAT ^C 3OO TAS KTS

DME1 LAX 65.3 NM 2O MIN

3

6

GUP

1OO

WEATHER

5 A WX/R/T S STAB TGT LX

1OO O.O5 L

PROGRESS

NEXT DEST

− MAP − PLAN − SYSTEM SYNOPTIC PAGES − TCAS − WEATHER RADAR − EGPWS (TERRAIN) − PROGRESS

E

W

ZUN

NAVIGATE

WPT ZUN GUP

DIST ETE FUEL 55.6 O1+32 11.4 95 O2+52 1O.4

− TCAS ZOOM − WEATHER RADAR CONTROLLER − TCAS CONTROLLER − VERTICAL PROFILE TCAS

Weather

EM170AOM140192B.DGN

NAVIGATE (Vnav)

AOM-1502-003

MFD DISPLAY PHILOSOPHY

14-01-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Electronic Display System

Page 7

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

MFD

STN

SATNB

N I

45.5 NM 8 MIN

Systems STATUS

Plan

Map

FMS2

0 CGO

0

SAT -33 ^C TAT -17 ^C TAS 346 KTS DME2

RDE 25

PROGRESS

380 00

NM SATNB

Maypoint Center

6.6R

WPT DIST ETA NEXT SATNB 45 . 5 NM O7H54 DEST RW20L 232 NM O8H30 FMS2 25

360 00

FUEL 46 00 KG 39 00 KG 25

SATNB

340 00 320 00 300 00

Maypoint Center Weather

Checklist

EM170AOM940068B.DGN

TCAS

14-01-25 Copyright © by Embraer. Refer to cover page for details.

Page 8

Electronic Display System

REVISION 18

AOM-1502-003

MFD DISPLAY

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

STATUS PAGE A dedicated page on MFD is available for pilots to achieve status information about:

• • • • • •

Flight; Battery; Engine Oil level; Brake; Crew oxygen; Door and Access Panel.

AOM-1502-003

Refer to the associated section of the AOM for more information:

14-01-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Electronic Display System

Page 9

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

!EMBRAER 170/175 models, units in lb, equipped with Load 21.2 and on

14−01 AIRPLANE GENERAL

14−06 ENGINE

Plan

Map FLIGHT EMB 9999 23 H 14 TAT -4O C SAT -56 C G.W. 696OO LB ELEC

14−05 ELECTRICAL

Systems

Status

DOORS

OXY PRESS

ENG OIL LEVEL

PSI

BATT1 28.O V BATT2 28.O V

14−02 AIR MANAGEMENT SYSTEM

14−14 OXYGEN

CREW

6.5

171O 45 PSI

45 PSI

QT 2.4

BRAKES

3OOO

S Y S 2 3OOO

TEMP C OB 25O

IB 25O

TCAS

IB 25O

14−01 AIRPLANE GENERAL

OB 25O

Weather

Checklist

EM170AOM140919B.DGN

14−13 LANDING GEAR AND BRAKES

EMER ACCU PSI

S Y S 1

14-01-25 Copyright © by Embraer. Refer to cover page for details.

Page 10

Electronic Display System

REVISION 18

AOM-1502-003

"

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

ELECTRONIC CHECKLIST The airplane’s Electronic Checklist (ECL) presents the checklists on the lower part of the MFDs. The ECL permits automation of checklist’s items reducing crew workload. The flight crew uses both the CCDs to respond manual checklist items and to navigate through the checklist pages.

ECL DATABASE LOADING PAGE After an airplane Power Up, clicking the Checklist Softkey opens the ECL DATABASE LOADING page. At this page, the airplane available ECL Database names are displayed. Selecting the database and clicking enter with the CCD loads the database. After loading the database, the ECL automatically opens the ECL NORMAL page.

CHECKLIST DB

Chkl Funct

ERJ17OQRH15O8OOA.ecl

Ovrd CAS MSG Main Menu Weather

Checklist

CHECKLIST DB LOADING ERJ17OQRH15O8OOA.ecl

99%

Chkl Funct Ovrd CAS MSG Main Menu

AOM-1502-003

TCAS

Weather

Checklist

EM170AOM140563A.DGN

TCAS

14-01-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Electronic Display System

Page 11

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ECL OPERATION Clicking the CHECKLIST softkey on the MFD allows access to ECL pages. When both MFDs are displaying the ECL pages, they are synchronized, however only one side at a time has control over the ECL. The first side to access the ECL has the control over it through its respective CCD. In this condition, the ECL can be opened on the cross-side MFD, however, the cross-side CCD cannot do any input on the ECL. If the side with control over the ECL allows one second without providing any input, the first side to do an input in ECL gains the control over it. The ECL combines automatic and manual response functions. Automatic responses receive information from the airplane systems and sensors to verify an item’s accomplishment (Closed Loops); manual responses are flight crew inputs from the CCD. The following controls have closed loops in the normal checklists: – Autobrake knob position (RTO selected or not). – Brake Temperature (acceptable or not for takeoff). – Engine Start/Stop Selectors. – Fuel AC Pumps Knobs position. – Gear Lever position. – Hydraulic Pumps Knobs position – Pack Buttons status. – Parking Brake Lever status. – Flap/Slat Lever position (0 or FULL or neither 0 nor FULL). – TLA Levers position (IDLE or TOGA or neither IDLE nor TOGA). For the emergency and abnormal checklists there are no closed loops available. The following softkeys are available on the ECL: – Main Menu: Opens a new menu presenting the following checklist categories:

– Non Annunciated.

14-01-25 Copyright © by Embraer. Refer to cover page for details.

Page 12

Electronic Display System

REVISION 18

AOM-1502-003

– Normal.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

– Emergency. – Abnormal. – User Defined. Selecting one of the categories opens an index with all the associated procedures. – CAS MSG: Opens the ECL ACTIVE ABNORMAL page. – Ovrd: Allows the pilot to override a checklist step or an entire checklist. – Chkl Funct: Opens three more softkeys:

• • •

Undo: Undoes last pilot action on the checklist. Chkl Reset: Resets current or a selected checklist. Reset All: Resets all checklists.

Along the execution of each checklist, smart features are available to reduce crew workload. They are: – Timers: automatically started when a checklist item requires so. – Branches: the “if” clauses that, upon the “Yes or No” response from the pilot, displays only the applicable actions to be followed from that point on. – Hyperlinks: links to synoptic pages are available (green button in the left side of the checklist item) when applicable during the procedures.

AOM-1502-003

– Closed loops: items that are automatically checked by airplane systems upon action completion. (Closed loops are only available for NORMAL checklists).

14-01-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Electronic Display System

Page 13

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

BEFORE START Pax Signs Panel ................................. SET Pressurization Panel ......................... SET Oxygen Masks ...................................... CKD Flight Instruments ......................... X-CKD Thrust Lever 1 ................................... IDLE

Chkl Funct Ovrd

Thrust Lever 2 .................................. IDLE

CAS MSG

Trim panel ................................... CHK/SET ...............................................................

Main Menu

TCAS

Weather

Checklist

NORMAL PROCEDURE ENG 1 OIL LO PRESS

1

No

Ovrd

ENGINE SHUTDOWN Procedure ........................ ACCOMPLISH END

Weather

CAS MSG Main Menu

CHECKLIST COMPLETE

TCAS

1

Checklist

ABNORMAL PROCEDURE

EM170AOM140737A.DGN

Yes

9

Chkl Funct

OIL PRESSURE INDICATION ABNORMAL ?

ECL PROCEDURES

ECL WINDOWS ORGANIZATION The ECL has at least six groups where the checklists can be grouped: NORMAL, ABNORMAL, EMERGENCY, NON-ANNUNCIATED, ACTIVE ABNORMAL and USER DEFINED.

14-01-25 Copyright © by Embraer. Refer to cover page for details.

Page 14

Electronic Display System

REVISION 18

AOM-1502-003

The procedures on the EMERGENCY and ABNORMAL pages have a priority according to the related EICAS message they are linked to, i.e., warning, caution or advisory. The NON-ANNUNCIATED and USER DEFINED categories permit to rate the procedures in emergency, abnormal, advisory or normal level.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

ECL ACTIVE ABNORMAL PAGE The ACTIVE Abnormal PAGE presents the procedures related to the active EICAS messages. As in the EICAS, the messages are grouped according to the priority category: warning, caution or advisory; with the warning at top, followed by the caution and the advisory categories. Within a category, the checklist that comes at the top is the last EICAS message generated of that category. Once a checklist is completed or overridden, it is removed from the ACTIVE ABNORMAL PAGE. However, any checklist is still accessible navigating on the checklist’s windows through the Main Menu. Application of the function RESET ALL restores the checklists to the ACTIVE ABNORMAL PAGE if the respective message is still displayed in the EICAS.

ACTIVE ABNORMAL ENG 1 OIL LO PRESS

2

ENG 2 OIL LO PRESS BLEED 1 FAIL

1

CAS MSG

ENG 1 REV TLA FAIL CRG AFT FIRE SYS FAIL

Main Menu

FLT CTRL FAULT

Weather

Checklist

EM170AOM140738A.DGN

Ovrd

PRESN AUTO FAIL PRESN MAN FAIL

TCAS

9

Chkl Funct

ECL ACTIVE ABNORMAL PAGE

ENGINE INDICATION AND CREW ALERTING SYSTEM (EICAS) DISPLAY

AOM-1502-003

The EICAS displays engine and system parameters such as flap, gear, spoilers and trim positions, total fuel quantity, APU and environmental information. The EICAS also displays crew awareness messages. For further information on engine parameters and CAS messages shown, refer to section 14-06 Engine and 14-15 Warnings respectively. In case of failure in the EICAS display, its information may be presented in the MFD by appropriately setting the reversionary panel. An automatic mode de-clutters the EICAS after takeoff. De-cluttering occurs 30 seconds after landing gear retraction and flap/slat retraction, if all parameters are displaying normal indications.

14-01-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Electronic Display System

Page 15

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

The following items are de-cluttered from EICAS: • Oil pressure.

• • • • • • • •

Oil temperature. Engine vibration. Slat position. Flap position. Speed brake position. Landing gear position. Pitch trim green band. APU.

The EICAS FULL pushbutton on the control pedestal inhibits the automatic de-clutter of EICAS. The EICAS is fully displayed when a cautionary condition is detected on one of de-cluttered indications.

14-01-25 Copyright © by Embraer. Refer to cover page for details.

Page 16

Electronic Display System

REVISION 18

AOM-1502-003

In normal conditions, de-clutter is disabled when the landing gear is extended and/or flap/slat is not at 0.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

MAIN PANEL

FLEX TO-2 ATTCS 39

87.O

87.O

87.O

87.O

N1

MANAGEMENT − ENGINE

ITT

78O

88.O

N2

88.O

57OO

FF PPH 57OO

5OOO

FQ LB

LG/AUTOBRAKE

DN

5OOO DN

1OOOO OIL

VIB

64

PRESS PSI 64

97

TEMP

1.4 1.O

LP HP

4

45O C

1OO %

CABIN

97

ALT RATE P LFE

O.7 O.9

SPDBRK

S

DN

APU

TRIMS

F

21OO -3OO O.1 8OO

ROLL

FT FPM PSI FT

GEAR FLAPS TRIM

PITCH UP

YAW

3.O

S/F

EM170AOM140194.DGN

FUEL QTY

78O

AOM-1502-003

EICAS DISPLAY PHILOSOPHY

14-01-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Electronic Display System

Page 17

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

MAIN PANEL

FLEX TO-2 ATTCS 39

FUEL QTY

87.O

87.O

N1

87.O

78O

ITT

78O

88.O

N2

88.O

57OO

FF PPH 57OO

5OOO

FQ LB

LANDING GEAR

DN

5OOO DN

1OOOO OIL

64

VIB

APU

PRESS PSI 64

97

TEMP

1.4 1.O

LP HP

45O C

1OO %

CABIN

97

ALT RATE P LFE

O.7 O.9

SPDBRK

S

DN

TRIMS

F

21OO -3OO O.1 8OO

ROLL

PITCH UP

YAW

4

FT FPM PSI FT

S/F

5.5

EM170AOM140195B.DGN

87.O

14-01-25 Copyright © by Embraer. Refer to cover page for details.

Page 18

Electronic Display System

REVISION 18

AOM-1502-003

FULL EICAS DISPLAY

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

MAIN PANEL

87.O

FUEL QTY

FLEX TO-2 ATTCS 39

87.O

87.O

N1

87.O

78O

ITT

78O

88.O

N2

88.O

57OO

FF PPH 57OO

5OOO

FQ LB

5OOO

1OOOO APU

45O C

1OO %

CABIN

TRIMS

21OO -3OO O.1 8OO

ROLL

FT FPM PSI FT

PITCH UP

YAW

5.5

EM170AOM140280B.DGN

ALT RATE P LFE

AOM-1502-003

DECLUTTERED EICAS DISPLAY

14-01-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Electronic Display System

Page 19

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

MULTIFUNCTION CONTROL DISPLAY UNIT (MCDU) The MCDU allows radio tuning, PFD radio tuning display setup, manual engine rating selection, engine takeoff data set, avionics display setup and test, performance initialization, flight planning, access to electronics CBs, among others. The EDS allows either MCDU to perform any of the functions available.

RADIO COM1

1 / 2

SQ

123 . 200

COM2 123 . 200 118 . 600

118 . 600 NAV1 114 . 8 DME H PXR 115 . 6

FMS AUTO

NAV2 117 . 4 116 . 8 N 123 XPDR 1471

TCAS/XPDR

IDENT

A

B

C

D

E

F

G

H

I

J

K

L

1

2

3

+/ −

M

N

O

P

Q

R

4

5

6

/

S

T

U

V

W

7

8

9

X

Y

Z

0

14-01-25 Copyright © by Embraer. Refer to cover page for details.

Page 20

Electronic Display System

REVISION 18

AOM-1502-003

TA/RA

EM170AOM140196A.DGN

STBY

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

CURSOR CONTROL DEVICE (CCD) Two CCDs are installed on the control pedestal and allow the flight crew to quickly position the cursor within the different selectable menus and displays. Each CCD has three function keys corresponding to the respective flight crew’s display. Pressing a function key activates the CCD on the corresponding display (PFD, MFD or EICAS). The middle button has a different shape to make the identification easier under low visibility condition or turbulence. ENTER buttons are provided on both sides of CCD. A dual concentric rotary knob on the CCD is used to control the: – WX radar tilt angle and range selection; – Selection of Radio frequency; – Scrolling of EICAS messages (caution, advisory, and status). !MAU load 17.5 and on AND previous than load 19.3 OR SB 0170-31-0017 AND PRE-MOD SB 0170-31-0019;

Touching the touch pad moves the cyan box selector around the display. The touch pad has six hot spots: one in each corner and at top and bottom centers. Touching a hot spot instantly moves the cursor to correspondent position on the selected screen. A cyan box shows the menu in control whenever a display is selected. " !MAU load 19.3 and on OR POST-MOD SB 170-31-0019

Touching the touch pad moves a crosshair pointer on the MFD selectable areas. The cyan selector box selects the soft key under the crosshair pointer. There are no hot spots in the MFD. "

The cursor automatically goes to a default position if the CCD is not operated for more than 20 s, provided there are no virtual control panel and pull-down menus opened.

AOM-1502-003

An opened pull-down menu closes automatically if a different display is selected. This logic is not applicable for WX radar control panel on MFD.

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REVISION 18

Electronic Display System

Page 21

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

!MAU load 19.3 and on OR POST-MOD SB 170-31-0019

CURSOR Map Navaids Airports

Plan

Systems

36O

5

PUMPS

WPT Ident

X

N

GUP44

Progress

Status 15 SAT ^C 25 TAT ^C 3OO TAS KTS DME1 65.3 NM LAX

3

Missed APPR

ZUN

Weather Terrain

[ 1OO ] O.O5 L

E

]

Off

EM170AOM980099A.DGN

6

GUP

TCAS

"

GUIDANCE PANEL The guidance panel houses the display controllers, used for display control, autopilot and yaw damper engagement functions, flight director mode engagement and selection of display data source for the flight director.

MODULAR AVIONICS UNIT (MAU) MAUs are cabinets that house modules assigned to different functions in an integrated architecture and also avionics and non-avionics functions. Among the avionics functions are the air data application, autopilot, autothrottle, data acquisition, display control functions, flight director, Flight Management System (FMS), flight control modules, global position system, monitor/warning system, stall protection/warning and windshear guidance.

MAU 1 is a 20-slot cabinet while MAU 2 and MAU 3 are 16 slot cabinets.

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Electronic Display System

REVISION 18

AOM-1502-003

MAU 1 and 2 are located in the forward electronics bay and MAU 3 is located in the center electronics bay.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

The typical layout of the MAUs, showing the location of each module, is provided on the next page. Where each MAU module is named as: NIC: AIOP: PROC 1: PROC 2: PROC 3: PROC 4:

AOM-1502-003

PROC 5: PROC 6:

network interface controller. actuator input/output processor. ADA 1(air data application), MW 1 (monitor warning), UTIL 1 (utility), CAL/MCDU 1, and CMS 1. CMF 2 (communication management function) (optional). FMS 1. ADA 2, MW 2, UTIL 2 (utility), CAL/MCDU 2, and CMS 2 (configuration management system). FMS 2, ADA 3, FBW. CMF 1, ECL.

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REVISION 18

Electronic Display System

Page 23

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

MODULAR AVIONICS UNIT 1 BUS

CH

20 19 18 17

2 2 2

B B B B

2

B

16 15 14 13

12 11 10 9

2 2 2 2

B B B B

POWER SUPPLY 3 DC 1

SLOT

BUS

B

FCM 1 CUSTOM I/O 1

1

A

1

A A

1 1

A A

1 1

A A A

1 1 1

A A

1 1

CH

BUS

NIC 2 PROC 2 GENERIC I/O

FCM 2 CONTROL I/O 1 BRAKES (OUTBD) PSEM 1 AIOPA1

CH

A

CMC GPS 1 POWER SUPPLY DC ESS 1

PROC 1 NIC 1 2

BUS

SPARE

AIOPB1

8 7 6 5 4 3 2 1

CH

POWER SUPPLY 1 DC ESS 1

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Electronic Display System

REVISION 18

AOM-1502-003

SLOT

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

MODULAR AVIONICS UNIT 2 SLOT

BUS

CH

16 15 14 13 12 11 10 9

2 2

B B

2

B

AOM-1502-003

SLOT

CH

BUS

A

1

A A

1 1

A

1

A

1

SPARE

A A

1

POWER SUPPLY 1 DC 2

CH

BUS

AIOPA2 SPARE SPARE

2 2 2

8 7 6 5 4 3 2 1

POWER SUPPLY 2 DC ESS 2/DC 2 BRAKES (INBD) CONTROL I/O 2

2 2

BUS

B B B

B B

CH

GENERIC I/O 2 NIC 4 PROC 4 PROC 3 NIC 3 SPARE DATABASE AUTOBRAKE EGPWM NOSEWHEEL STEERING

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REVISION 18

Electronic Display System

Page 25

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

MODULAR AVIONICS UNIT 3 SLOT

BUS

CH

16 15 14 13 12 11 10 9

1

B

POWER SUPPLY 2 DC 2 ENGINE VIBE GPS 2 PSEM 2

1

B

1

B

1 1

8 7 6 5 4 3 2 1

1

SLOT

BUS

B B

B

FCM 3 GENERIC I/O 3 NIC 6 PROC 6 PROC 5 NIC 5 CUSTOM I/O 2 AIOPB2

CH

BUS

A

2 2

A A

2

A

2

A A

2 2

A A

2 2

A

2

CH

BUS

1

B CH

FCM 4 POWER SUPPLY 1 DC ESS 2

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Electronic Display System

REVISION 18

AOM-1502-003

SPARE SPARE

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

PASSENGER CABIN GALLEY The galleys provide means for food preparation as well as stowage for food and miscellaneous items. A work deck is provided to assist flight attendants with their tasks. !Galley G1-B

COFFEE MAKER MISCELLANEOUS COMPARTMENT ELECTRICAL PANEL STANDARD CONTAINER

SINK WASTE DISPOSAL

MISCELLANEOUS COMPARTMENT

MANUAL SHUT−OFF VALVE

HALF SIZE CART

EM170AOM140433.DGN

WASTE COMPARTMENT

FORWARD GALLEY (G1)

AOM-1502-003

"

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REVISION 20

Passenger Cabin

Page 1

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

!Galley G1-L

COFFEE MAKER MISCELLANEOUS COMPARTMENT ELECTRICAL PANEL

FAUCET

STANDARD UNIT

MISCELLANEOUS COMPARTMENT

SINK WORK TABLE

WASTE DISPOSAL

HALF SIZE TROLLEY

MANUAL SHUT OFF VALVE

EM170AOM140842B.DGN

WASTE COMPARTMENT

FORWARD GALLEY (G1)

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Page 2

Passenger Cabin

REVISION 20

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

!Galley G3-D

ELECTRICAL PANEL

MISCELLANEOUS STOWAGE

MISCELLANEOUS STOWAGE

COFFEE MAKER STANDARD UNIT SINK AND FAUCET

WORK TABLE

ELECTRICAL POWER OUTLET

HALF SIZE/ FULL SIZE CART NOTE: THERE ARE TWO MISCELLANEOUS STOWAGE COMPARTMENTS BEHIND THE CARTS.

EM170AOM140558C.DGN

WASTE COMPARTMENT

AOM-1502-003

AFT GALLEY (G3)

"

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REVISION 20

Passenger Cabin

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

!Galley G3-M

ELECTRICAL PANEL

MISCELLANEOUS STOWAGE

MISCELLANEOUS STOWAGE

COFFEE MAKER STANDARD UNIT

SINK AND FAUCET

WORK TABLE

ELECTRICAL POWER OUTLET

HALF SIZE/ FULL SIZE CART

EM170AOM140352A.DGN

WASTE COMPARTMENT

"

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Page 4

Passenger Cabin

REVISION 20

AOM-1502-003

AFT GALLEY (G3)

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

!Galley G3-AB

ELECTRICAL PANEL

MISCELLANEOUS STOWAGE

MISCELLANEOUS STOWAGE

COFFEE MAKER STANDARD UNIT SINK AND FAUCET

OVEN

WORK TABLE

ELECTRICAL POWER OUTLET

HALF SIZE/ FULL SIZE CART

EM170AOM140854A.DGN

WASTE COMPARTMENT

AOM-1502-003

AFT GALLEY (G3)

"

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REVISION 20

Passenger Cabin

Page 5

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ATTENDANT STATIONS AND SEATS

TEMPERATURE SETTING

C

H

ENABLED

CABIN TEMPERATURE

CABIN LIGHTING

ON

ON

ON

ON

CEILING

SIDEWALL

FWD ENTRANCE

FWD GALLEY AREA

BRIGHT

BRIGHT

BRIGHT

BRIGHT

DIM

DIM

DIM

DIM

EMERGENCY LIGHT

ATTENDANT SEAT (REF.)

GALLEY MASTER

ON/ ARMED

TEST

PANEL LIGHTS

TEST

COURTESY LIGHT

RESET

OFF AUTO

LAVATORY SMOKE TEST

FWD

PSU

AFT

TEST

RESET

ATTND CALL

RESET

ATTENDANT PANEL

HANDSET CRADLE

PA

ATTND PILOT

EMER PILOT

FWD FLIGHT ATTENDANT STATION AND SEAT (CC1)

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Page 6

Passenger Cabin

REVISION 20

AOM-1502-003

EM170AOM140425.DGN

ATTENDANT HANDSET

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

TEMPERATURE SETTING

C

H

ENABLED

CABIN TEMPERATURE

CABIN LIGHTING

ON

ON

SIDEWALL

AFT ENTRANCE

BRIGHT

BRIGHT

BRIGHT

DIM

DIM

DIM

ON/ ARMED

TEST

GALLEY MASTER

ON

CEILING

EMERGENCY LIGHT

AFT LH LAVATORY

PANEL LIGHTS

TEST

ATTENDANT SEAT

COURTESY LIGHT

OFF

RESET

AUTO

WASTE SYSTEM

FWD

TANK FULL

AFT

SERVICE TANK

FAULT

LAVATORY FAULT

ATTND CALL

WATER SYSTEM WATER QUANTITY

RESET

FAULT 0

ATTENDANT PANEL PA

ATTND PILOT

EMER PILOT

HANDSET CRADLE

EM170AOM140655B.DGN

ATTENDANT HANDSET

AOM-1502-003

AFT FLIGHT ATTENDANT STATION AND SEAT (CC2)

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REVISION 20

Passenger Cabin

Page 7

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

!Airplanes equipped with 3rd flight attendant seat

FLASHLIGHT

AFT RH BULKHEAD

ATTENDANT SEAT

PA

ATTND PILOT

EMER PILOT

HANDSET CRADLE

EM170AOM140683A.DGN

ATTENDANT HANDSET

"

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Page 8

Passenger Cabin

REVISION 20

AOM-1502-003

AFT FLIGHT ATTENDANT STATION AND SEAT (CC3)

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

WARDROBE

CD PLAYER COMPARTMENT

MIRROR

HANDLE

EM170AOM140557B.DGN

ROLL−UP DOOR

AOM-1502-003

RH FWD WARDROBE

WARDROBE TYPE 1

14-01-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Passenger Cabin

Page 9

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

LITERATURE POCKETS

EM170AOM140312B.DGN

TAMBOUR DOOR

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Page 10

Passenger Cabin

REVISION 20

AOM-1502-003

WARDROBE TYPE 2

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

PASSENGER SERVICE UNIT The PSU provides: – Reading light at each passenger seat. !Airplanes equipped with NO ELEC DEVICES switch

– FASTEN SEAT BELTS and TURN OFF ELECTRONIC DEVICES signs. " !Airplanes equipped with NO SMKG Switch

– NO SMOKING and FASTEN SEAT BELTS signs. "

– Pushbutton and indicator for attendant call. – Air gasper for each individual passenger seat. – Oxygen mask dispensing unit. – Loudspeaker for internal communication.

DISPENSING UNITS ATTENDANT CALL BUTTON

AOM-1502-003

MANUAL DEPLOY TOOL

PASSENGER SIGNS GASPER OUTLETS

PASSENGER LIGHT BUTTON

EM170AOM140027B.DGN

INDIVIDUAL READING LIGHTS

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REVISION 20

Passenger Cabin

Page 11

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

LAVATORY

CUP DISPENSER

MIRROR FAUCET

SEAT COVER DISPENSER WASTE FLAP

TOILET SHROUD SERVICE PANEL

MANUAL SHUT−OFF VALVE

FORWARD LAVATORY

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Page 12

Passenger Cabin

REVISION 20

AOM-1502-003

EM170AOM140018A.DGN

TOILET BOWL

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

TISSUE DISPENSER

WASTE DISPOSAL SERVICE PANEL

MANUAL SHUT−OFF VALVE

EM170AOM140019A.DGN

TOILET SEAT COVER AND SHROUD

AOM-1502-003

AFT LAVATORY

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REVISION 20

Passenger Cabin

Page 13

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

14-01-35 Copyright © by Embraer. Refer to cover page for details.

Page 14

Passenger Cabin

REVISION 20

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

Airplanes equipped with PC Power system

CABIN PC POWER SYSTEM

!Airplanes equipped with Passenger Cabin PC Power system

The PC Power system is designed to supply passenger seats with 110 V/60 Hz AC power for personal electronic devices (PED) such as laptop computers and other passenger equipment. The AC BUS 1 supplies power to converters, which then provide AC power to all passenger seat outlets. The PC power system operates only if the electrical system is operating in normal mode. In case of loss of any of the electrical generators the system will not operate. The PC Power/IFE panel for system operation is installed in the control pedestal. The galley master switch, installed on flight attendant panel, also turns off the system. "

CABIN PC POWER OUTLET

!Airplanes equipped with Passenger Cabin PC Power system

Each outlet incorporates an LED that is visible to the passengers and indicates that AC power is available. The green color indicates power is supplied to the outlets and the red color indicates power is not available. The LED is turned off when the system is not energized. The outlet provides power for use only when the plug is correctly connected into the socket and PED power is available. The cabin crew can monitor the power outlets in use by an outlets in-use panel installed in the passenger cabin.

AOM-1502-003

"

14-01-37 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

PC Power System

Page 1

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

CABIN PC POWER PROTECTIONS !Airplanes equipped with Passenger Cabin PC Power system

A self-test is performed during power-up and will shut down the system if an error is detected. The system provides protection against under-voltage, over-voltage, over-current, short circuit and over temperature. The PC power system controls the power available to the AC outlet units and monitors the total electrical current in use and, if necessary, disables or enables the power outlets. The system is turned off automatically in case of cabin decompression. Pressing the cabin PC power button on the control panel resets the system.

14-01-37 Copyright © by Embraer. Refer to cover page for details.

Page 2

PC Power System

REVISION 17

AOM-1502-003

The outlet provides protection from thin metal objects being inserted into the sockets.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

!!Airplanes equipped with Passenger Cabin PC Power system PASSENGER SEAT

FIRST−CLASS PASSENGER SEAT

FIRST−CLASS PASSENGER SEAT LED

OUTLET

EM170AOM140573A.DGN

PLUG

PC POWER OUTLETS

AOM-1502-003

""

14-01-37 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

PC Power System

Page 3

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

!!Airplanes equipped with Passenger Cabin PC Power system

EM170AOM140572A.DGN

CABIN PC−POWER MONITORING

OUTLETS IN-USE PANEL

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Page 4

PC Power System

REVISION 17

AOM-1502-003

"" "

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

COCKPIT PC POWER SYSTEM !Airplanes equipped with Cockpit PC Power outlets

The PC power system supplies 110 VAC/60 Hz two outlets installed in the cockpit, and/or two outlets installed into the forward and mid electronic compartments. The PC power outlets are used by the flight crew or maintenance personnel to connect laptops or other PEDs (Portable Electronic Devices). Each PC power outlet unit is connected to an AC converter that is powered by the AC BUS 2. The PC power control switch is installed above the RH side PC power outlet and a striped bar illuminates when the AC power is available (pushed in). The electronic compartment PCpower outlets are intended for use only on ground while the cockpit PC power outlets can be used on ground or in flight. The use of cockpit PC power outlets in flight is restricted to equipment and procedures approved by the local authority. NOTE: Ensure laptop batteries are charged (above 75%) before plugging them into the outlets. Low battery levels may require power greater than the designed limit for the outlet. If the power limit of the outlet is exceeded, the outlet will be disabled and maintenance action will be required to reset the system. "

COCKPIT PC POWER OUTLET !Airplanes equipped with Cockpit PC Power outlets

!!Cockpit PC Power outlet powered by 225 VA converter

Pushing IN the PC Power Outlet Control button illuminates the striped bar on the button and a green LED at the outlet. Inserting the plug completely into the outlet makes the AC power available. ""

The LED is turned off when the system is not energized. The outlet provides power for use only when the plug is correctly connected into the socket and PED power is enabled.

AOM-1502-003

The LED is shown in red color when a fault condition is detected or the over-temperature limit is exceeded. NOTE: Ensure the plug is not inserted into the outlet before power up of the airplane. If the plug is inside the outlet when the airplane is powered up the power outlet unit will not be energized. Remove the plug from the outlet and insert it again according to the procedures above to energize the

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REVISION 17

PC Power System

Page 5

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

power outlet unit.

!!Airplanes equipped with Cockpit PC Power outlets

PC POWER OUTLET

COCKPIT PC POWER OUTLETS

""

14-01-37 Copyright © by Embraer. Refer to cover page for details.

Page 6

PC Power System

REVISION 17

AOM-1502-003

EM170AOM140739A.DGN

PC POWER OUTLET

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

!!Cockpit PC Power outlet powered by 225 VA converter

1

2 LED

PRESS THE PC OUTLET BUTTON. THE STRIPED BAR WILL TURN ON THE GREEN LED WILL TURN ON

INSERT THE MALE CONNECTOR INTO THE OUTLET

EM170AOM140740A.DGN

LED

COCKPIT PC POWER OUTLETS - PROCEDURES TO ENERGIZE THE PC POWER OUTLETS

AOM-1502-003

""

14-01-37 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

PC Power System

Page 7

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL "

COCKPIT PC POWER PROTECTIONS !Airplanes equipped with Cockpit PC Power outlets

The system provides protection against under-voltage, over-voltage, over-current, short circuit and over temperature. The PC power system controls the power available to the AC outlet units and monitors the total electrical current in use and, if necessary, disables or enables the power outlets. The system is turned off automatically in case of cabin decompression. Pressing the PC power control switch resets the system.

14-01-37 Copyright © by Embraer. Refer to cover page for details.

Page 8

PC Power System

REVISION 17

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

LIGHTING INTRODUCTION The lighting system provides lighting to all essential parts located inside and outside of the fuselage and ensures proper and safe operation of the airplane. The lighting system includes:

• • • •

External Lights. Cockpit Lights. Passenger Cabin Lights. Emergency lighting.

The system also provides lighting for baggage and service compartments.

EXTERNAL LIGHTING The external lights necessary for a proper and safe operation of the airplane are: – Landing and taxi lights. – Navigation and anti-collision lights. – Wing inspection and logotype lights.

LANDING AND TAXI LIGHTS Landing and taxi lights are fitted to each wing roots behind glazed covers. A third landing light and a third taxi light are mounted on the nose gear structure. The landing light units provide adequate lighting during final approach, flare out and takeoff. The taxi light provides sufficient intensity and beam spread to aid pilots during all taxi operation phases, covering the runway and adjacent areas.

AOM-1502-003

Different switches for nose and root landing and taxi lights are located at the overhead panel.

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REVISION 21

Lighting

Page 1

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

NAVIGATION AND ANTI COLLISION LIGHTS

!EMBRAER 170/175 Models except EMBRAER 175 with enhanced wing tip or POST-MOD SB-170-57-0058

The navigation lights, red on the left, green on the right and white on both wings, are fitted on each wing tip. A switch located at the overhead panel controls the navigation lights. The anti collision lights, two white strobe lights per wing tip and two red beacon lights mounted on the upper and lower fuselage provide illumination for visual recognition and collision avoidance during all flight/taxi operations. Two different switches, one for strobe lights and another for the red beacon lights are located at the overhead panel. Each navigation light assembly is composed of two lamps while the strobe light assembly is composed of only one lamp. Normally only one navigation lamp is on, while the second lamp is on standby. In case of failure, maintenance personnel through a maintenance panel in the cockpit manually switch navigation lights. "

NAVIGATION AND ANTI COLLISION LIGHTS

!EMBRAER 175 Models with enhanced wing tip or POST-MOD SB-170-57-0058

The enhanced wing tip is equipped with LED navigation and anti collision lights. The navigation lights, red on the left, green on the right, and white on both wings, are fitted on each enhanced wing tip. A switch located at the overhead panel controls the navigation lights. The anti collision lights, two white strobe lights per enhanced wing tip and two red beacon lights mounted on the upper and lower fuselage provide illumination for visual recognition and collision avoidance during all flight/taxi operations. Two different switches, one for strobe lights and another for the red beacon lights are located at the overhead panel. The forward light assembly is composed of one navigation light and one strobe light. On the trailing edge of the enhanced wing tip is installed a combined LED navigation/anti collision light assembly.

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Page 2

Lighting

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

WING INSPECTION AND LOGOTYPE LIGHTS Wing inspection lights provide proper illumination of the engine intake and of the wing leading edges of the wings for Captain and crew to inspect for ice formation. A switch located at the overhead panel controls the engine and wing illumination light system.

AOM-1502-003

The logo lights are installed in the upper surface of both horizontal stabilizers and are directed to the vertical fin perpendicular to the centerline of the airplane, in order to provide adequate illumination of the airplane’s logo during operation on the ground and in flight. A switch located at the overhead panel controls the logotype lights.

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REVISION 21

Lighting

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

!EMBRAER 175 Models with wing tip UPPER RED BEACON LIGHT

WING INSPECTION LIGHT

NAV. LIGHT/ STROBE LIGHT

LOWER RED BEACON LIGHT

NAV. LIGHT (GREEN) STROBE LIGHT NAV. LIGHT (WHITE) STROBE LIGHT

LANDING/ TAXI LIGHT− WING ROOT WING INSPECTION LIGHT UPPER RED BEACON LIGHT

LOGO LIGHT

WING INSPECTION LIGHT LANDING/ TAXI LIGHT− WING ROOT

NAV. LIGHT (WHITE) STROBE LIGHT

NAV. LIGHT (RED) STROBE LIGHT

WING INSPECTION LIGHT

WING INSPECTION LIGHT

LANDING LIGHT NOSE GEAR

LANDING/TAXI LIGHT− WING ROOT

EM170AOM140229A.DGN

TAXI LIGHT NOSE GEAR

"

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Page 4

Lighting

REVISION 21

AOM-1502-003

EXTERNAL LIGHTING

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

!EMBRAER 175 Models with enhanced wing tip or POST-MOD SB-170-57-0058 UPPER RED BEACON LIGHT

WING INSPECTION LIGHT

NAV. LIGHT/ STROBE LIGHT

LOWER RED BEACON LIGHT

NAV. LIGHT (GREEN) STROBE LIGHT NAV. LIGHT (WHITE) STROBE LIGHT

LANDING/ TAXI LIGHT− WING ROOT WING INSPECTION LIGHT UPPER RED BEACON LIGHT

LOGO LIGHT

WING INSPECTION LIGHT LANDING/ TAXI LIGHT− WING ROOT

NAV. LIGHT (WHITE) STROBE LIGHT

NAV. LIGHT (RED) STROBE LIGHT

WING INSPECTION LIGHT

WING INSPECTION LIGHT

LANDING LIGHT NOSE GEAR

LANDING/TAXI LIGHT− WING ROOT

EM170AOM141339A.DGN

TAXI LIGHT NOSE GEAR

AOM-1502-003

EXTERNAL LIGHTING

"

14-01-40 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Lighting

Page 5

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

INTERNAL LIGHTING COCKPIT LIGHTS Cockpit lighting consists of: – Chart lights. – Dome lights. – Fluorescent flood/storm light. – Reading lights. The system provides lighting for instruments, control panels and buttons. CHART LIGHTS Provide variable intensity lights to illuminate chart holders located at the cockpit side windows. DOME LIGHTS Provide fixed intensity cockpit illumination above Captain and First Officer’s seats. FLUORESCENT FLOOD/STORM LIGHT Provide high quality illumination to ensure panel readability under high intensity ambient lighting (lightning). READING LIGHTS

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Page 6

Lighting

REVISION 21

AOM-1502-003

Provide illumination to help the pilots read maps, check lists and manuals.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AREA CONTROLLED BY THE OVERHEAD PANEL LIGHTING CONTROL

PILOT READING LIGHT

AIRPLANE GENERAL DESCRIPTION

EMERGENCY LIGHT DOME LIGHT

DOME LIGHT

OBSERVER READING LIGHT CO−PILOT READING LIGHT

CHART LIGHT FLOODSTORM LIGHTS

AREA CONTROLLED BY THE CO−PILOT’S PANEL LIGHTING CONTROL

AREA CONTROLLED BY THE PILOT’S PANEL LIGHTING CONTROL

EM170AOM140028.DGN

CHART LIGHT

COCKPIT LIGHTS

COURTESY AND STAIRS LIGHTS

AOM-1502-003

Provide lighting for safe boarding of crewmembers and passengers. Courtesy and stair lights consist of the main door light (entry area), service door light (galley area), stairway lights and cockpit step light.

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REVISION 21

Lighting

Page 7

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

PASSENGER CABIN LIGHTS A general passenger cabin illumination, reading lights in the passenger service unit, lavatory lights, galley lights and cabin signs make up the passenger cabin lighting. PASSENGER CABIN SIGNS Passenger cabin signs provide passengers and flight attendants with signs like: !Commercial airplanes equipped with NO SMKG switch

•

NO SMOKING.

• • • •

TURN OFF ELECTRONIC DEVICES.

"

FASTEN SEAT BELTS. RETURN TO SEAT. LAVATORY OCCUPIED.

!Commercial airplanes equipped with NO SMKG switch

The signs are available on every passenger service unit (PSU). An aural signal sounds whenever any passenger sign is turned on or off by the crew. NO SMOKING and FASTEN SEAT BELTS signs are also activated when the oxygen dispensing units are open. "

The signs are available on every passenger service unit (PSU). An aural signal sounds whenever any passenger sign is turned on or off by the crew. NO ELECTRONIC DEVICES and FASTEN SEAT BELTS signs are also activated when the oxygen dispensing units are open. STERILE LIGHTS

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Lighting

REVISION 21

AOM-1502-003

An amber sterile light located on the cockpit/passenger partition indicates when entry into the cockpit is not allowed. An aural signal sounds whenever the sterile light is illuminated.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

COURTESY AND STAIRS LIGHTS Provide lighting for safe boarding of crewmembers and passengers. Courtesy and stair lights consist of the main door light (entry area), service door light (galley area), stairway lights and cockpit step light. SERVICE COMPARTMENT LIGHTS Provide lighting in the service compartments for quick inspection and accomplishment of several tasks. Service lights are installed in the refueling panel, mid and forward electronic bays, APU, tail cone and rear hydraulic compartment. The lights are controlled by door micro-switches or dedicated standard switches installed in each compartment, which turn on the associated light when the access door is open.

RAINBOW LIGHTS The rainbow lights located on the forward and aft main ceiling panel areas provide a visual indication to attendants when there is a call from the flight crew or passengers. The rainbow lights consist of following colored indicator lights: – ORANGE: a steady orange light illuminates when a passenger calls from the lavatory. Flashing orange light illuminates when smoke is detected in the lavatory. – BLUE: a steady blue light illuminates when a passenger calls from the main cabin area. – RED: a flashing red indicator illuminates when the flight crew makes an emergency call to the flight attendant from the cockpit. The light stops flashing after the call is taken. – GREEN: a flashing green indicator illuminates when the pilot calls the flight attendant from the cockpit. The light stops flashing after the call is taken. – AMBER: a steady amber light illuminates for a sterile light call.

AOM-1502-003

An audible tone is sounded by the passenger address system whenever a passenger presses any attendant call switch located in a PSU or the attendant call switch in the lavatory or flight crew call switches. There is also a blue steady light on the cabin ceiling, indicating from which cabin

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REVISION 21

Lighting

Page 9

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

area the respective passenger call was made. NOTE: There is no indication on the rainbow lights when a flight attendant calls another flight attendant station. It only flashes green on both handset cradles. CALL SYSTEM TABLE !Commercial airplanes equipped with NO SMKG switch

VISUAL INDICATION Steady ORANGE light Flashing ORANGE light

AURAL INDICATION Single hi tone chime Lavatory fire protection alarm

Steady BLUE light Flashing RED light

Single hi tone chime Triple hi/lo tone chime in PAX cabin Triple hi/lo tone chime in cockpit Single hi/lo tone chime in PAX cabin Single hi/lo tone chime in cockpit Single hi tone chime Single lo tone chime

Flashing GREEN light

AMBER sterile cockpit light No smoking or fasten belt signs illuminate / extinguish

FROM Respective lavatory call Respective lavatory smoke detection Passenger PSU Cockpit

TO Attendant station Attendant station Attendant station Attendant Station

Attendant Station Cockpit

Cockpit

Attendant Station Cockpit

Cockpit

Cockpit

Attendant Station

Attendant station Passenger cabin, lavatories and galleys "

VISUAL INDICATION Steady ORANGE light

AURAL INDICATION Single hi tone chime

FROM

TO

Respective lavatory call

Attendant station

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Lighting

REVISION 21

AOM-1502-003

CALL SYSTEM TABLE

AIRPLANE OPERATIONS MANUAL

VISUAL INDICATION Flashing ORANGE light Steady BLUE light Flashing RED light

Flashing GREEN light

AOM-1502-003

AMBER sterile cockpit light Turn off electronic devices or fasten belt signs illuminate / extinguish

SYSTEMS DESCRIPTION

AURAL FROM INDICATION Lavatory fire Respective protection alarm lavatory smoke detection Single hi tone Passenger PSU chime Triple hi/lo tone Cockpit chime in PAX cabin Triple hi/lo tone Attendant chime in cockpit Station Single hi/lo tone Cockpit chime in PAX cabin Single hi/lo tone Attendant chime in cockpit Station Single hi tone Cockpit chime Single lo tone Cockpit chime

AIRPLANE GENERAL DESCRIPTION

TO Attendant station Attendant station Attendant Station Cockpit Attendant Station Cockpit Attendant station Passenger cabin, lavatories and galleys

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REVISION 21

Lighting

Page 11

AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

PILOT PILOT (STERILE LIGHT)

PILOT (EMERG)

PAX

TOILET

EM170AOM970007B.DGN

SYSTEMS DESCRIPTION

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Lighting

REVISION 21

AOM-1502-003

ATTENDANT LIGHTS (RAINBOW LIGHTS)

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

EMERGENCY LIGHTING Emergency lighting consists of internal and external lights. The internal emergency lights are powered by four dedicated Emergency Lights Power Units (ELPU) with internal batteries connected to the DC BUS 1. The charge of the batteries is sufficient to supply all emergency lights for approximately 10 minutes. External emergency lighting is provided by each of the escape slides located on each of the four doors of the airplane. A switch located in the cockpit enables the pilots to turn ON, OFF or ARM the emergency lights. Additional switches on the FWD and AFT Flight Attendant Panels enable flight attendant to turn ON or OFF (ARM) the emergency lights. In ARM mode (cockpit switch), the emergency lights are activated automatically when the airplane loses its normal electrical power.

AOM-1502-003

Internal emergency lights comprise the exit locator signs, exit marker signs, exit identifier signs, cabin/cockpit emergency floodlights and passage way emergency exit floodlights. A cockpit light is located at the cockpit ceiling and provides general emergency illumination of the cockpit area.

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REVISION 21

Lighting

Page 13

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

EXIT LOCATOR SIGN

COCKPIT EMERGENCY FLOODLIGHT PASSAGE WAY EMERGENCY FLOODLIGHT

EXIT IDENTIFIER SIGN EXIT MARKER SIGN

EXIT MARKER SIGN EXIT IDENTIFIER SIGN

PASSAGE WAY EMERGENCY FLOODLIGHT EMERGENCY LIGHT

EXIT LOCATOR SIGN

EXIT MARKER SIGN

EXIT MARKER SIGN

PASSAGE WAY EMERGENCY FLOODLIGHT

PASSAGE WAY EMERGENCY FLOODLIGHT

EM170AOM140251B.DGN

EXIT IDENTIFIER SIGN

EXIT IDENTIFIER SIGN

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Lighting

REVISION 21

AOM-1502-003

EMERGENCY LIGHTING

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

PHOTOLUMINESCENT STRIPS Photoluminescent strips are installed along the passenger cabin floor to provide means of identifying the emergency escape path even in dense smoke conditions. Double red dots on the strips indicate the end of each exit path. Photoluminescent escape path strips must be charged prior to the first flight of the day by interior cabin lighting. For 15 minutes of ceiling and entrance cabin lighting exposure in BRIGHT mode the strip luminescence will be available for 7 hours.

AOM-1502-003

Luminescence time is not limited if during flight either daylight or cabin lighting exist in the cabin.

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REVISION 21

Lighting

Page 15

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

!EMBRAER 170 Models

AFT GALLEY SERVICE DOOR

AFT MAIN DOOR

FWD MAIN DOOR

EM170AOM140305.DGN

FWD GALLEY SERVICE DOOR

"

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Lighting

REVISION 21

AOM-1502-003

PHOTOLUMINESCENT STRIPS

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

!EMBRAER 175 Models

AFT GALLEY SERVICE DOOR

AFT MAIN DOOR

FWD MAIN DOOR EM170AOM140682A.DGN

FWD GALLEY SERVICE DOOR

AOM-1502-003

PHOTOLUMINESCENT STRIPS

"

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REVISION 21

Lighting

Page 17

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

CARGO COMPARTMENTS LIGHTS !EMBRAER 170 Models

The forward cargo bay has 4 cargo lights and 1 loading light and the aft cargo bay has 3 cargo lights and 1 loading light. " !EMBRAER 175 models, not equipped with IFE

The forward cargo bay has 5 cargo lights and 1 loading light and the aft cargo bay has 4 cargo lights and 1 loading light. "

There is a manual switch located at each cargo door that gives “AUTO” and “OFF” selections. In “AUTO” mode, the cargo lights come on when the cargo door is opened and turn off when the door is closed. The “OFF” mode turns off the lights regardless of the door position.

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Lighting

REVISION 21

AOM-1502-003

The cargo lights have protective grills installed to protect them against damage from the cargo.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

!EMBRAER 170 Models CARGO COMPARTMENT LIGHTS

LOADING LIGHT

LOADING LIGHT

EM170AOM140357.DGN

CARGO COMPARTMENT LIGHTS

CARGO COMPARTMENT LIGHTS

AOM-1502-003

"

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REVISION 21

Lighting

Page 19

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

!EMBRAER 175 models, not equipped with IFE

CARGO COMPARTMENT LIGHTS

LOADING LIGHT

LOADING LIGHT

EM170AOM140559A.DGN

CARGO COMPARTMENT LIGHTS

CARGO COMPARTMENT LIGHTS

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Lighting

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

DOORS This airplane has two jetway passenger doors on the left side (forward and aft location), two jetway service doors on the right side (forward and aft location), and a number of access doors for different airplane systems along the fuselage.

PASSENGER AND SERVICE DOORS This airplane has one passenger door located at the left forward fuselage section and another located at the aft fuselage section. Passenger door operation is manual and it is identical for both passenger doors. Passenger doors are plug type and they are of type 1 design. One service door is located at the right forward fuselage section and another located at the aft fuselage section. Service doors are used for galley servicing and cabin cleaning between flights. It may also be used as an emergency exit. The operation of service and passenger doors is identical. One external, three internal handles and one vent flap are installed in each door for opening and closing operation.

AOM-1502-003

The doors support maximum wind gusts of 40 kt, valid for positions between fully closed and fully open. For the open and locked position, the wind load limitation is 65 kt.

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REVISION 16

Doors

Page 1

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

DOOR EXTERNAL HANDLE The vent flap function ensures the correct latching and locking of the door so that the airplane can be pressurized. The vent flap also ensures that there is no residual indoor pressure on the ground before the door opening. The escape slide is automatically disarmed when door is opened from outside. The vent flap opens automatically when the lower part of the external handle is pulled. For further information on the escape slide refer to escape slide description in this section. !PRE-MOD SB 0170-52-0031

WARNING: MAKE SURE THAT THE VENT FLAP IS CLOSED (FLUSH WITH THE DOOR) BEFORE OPENING THE DOOR FROM THE OUTSIDE. IF THE EXTERNAL HANDLE IS USED TO OPEN THE DOOR WHILE THE SLIDE IS ARMED AND THE VENT FLAP IS OPEN, DOOR EMERGENCY OPENING OPERATION WILL OCCUR AND THE ESCAPE SLIDE WILL DEPLOY. "

VENT FLAP

EM170AOM140371A.DGN

EXTERNAL HANDLE

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Doors

REVISION 16

AOM-1502-003

EXTERNAL HANDLE AND VENT FLAP

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

DOOR INTERNAL HANDLES The main handle activates the door’s latch mechanism. The vent flap and the door’s lock mechanism are linked together. The airplane pressurization loads the vent flap against the door structure. The effort required to unlock the door (lift the vent flap lever) increases with the airplane pressurization level. The arming lever arms/disarms the emergency system (escape slide and door’s emergency assisting system) and engages/disengages the girt bar.

EM170AOM140367C.DGN

ARMING LEVER

VENT FLAP LEVER

MAIN HANDLE

AOM-1502-003

INTERNAL HANDLES

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REVISION 16

Doors

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

DOOR INDICATIONS One green latch and two green lock indications are provided to ensure the door is secured in the locked position. An escape slide ARMED/DISARMED indication provides the escape slide armed/disarmed condition. A red indication in the bottom of the door provides means to verify if the girt bar is engaged.

ESCAPE SLIDE ARMED/DISARMED LATCH LOCK

LOCK

EM170AOM140370C.DGN

ESCAPE SLIDE GIRT BAR

DOOR INDICATIONS

Door indications change according to the handle’s position. MAIN HANDLE DOWN – Door: Closed – Latch indication: GREEN MAIN HANDLE UP – Door: Open

VENT FLAP LEVER DOWN

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Doors

REVISION 16

AOM-1502-003

– Latch indication: NO green indication

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

– Vent flap: Closed – Lock indications: GREEN VENT FLAP LEVER UP – Vent flap: Open – Lock indications: NO green indications ARMING LEVER DOWN – Escape slide: Armed – Escape slide indication: RED ARMED – Girt bar indication: RED – girt bar connected to airplane. ARMING LEVER UP – Escape slide: Disarmed – Escape slide indication: GREEN DISARMED

AOM-1502-003

– Girt bar indication: NO red indication – girt bar disconnected from airplane.

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REVISION 16

Doors

Page 5

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

The following door indications are shown for different internal handles positions. – Main handle DOWN (Door closed and latched) – Vent Flap lever DOWN (Vent Flap closed and door locked) – Arming lever DOWN (Escape Slide ARMED)

ARMED LOCK

LOCK

ESCAPE SLIDE

EM170AOM140369A.DGN

LATCH

GIRT BAR

– Main handle UP (Door unlatched and opened) – Vent Flap lever UP (Vent Flap opened and door unlocked) – Arming lever UP (Escape Slide DISARMED)

DISARMED ESCAPE SLIDE

GIRT BAR

LOCK

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Doors

REVISION 16

AOM-1502-003

LOCK

EM170AOM140387A.DGN

LATCH

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

– Main handle UP (Door unlatched and opened) – Vent Flap lever UP (Vent Flap opened and door unlocked) – Arming lever DOWN (Escape Slide DEPLOYED)

ARMED LOCK

ESCAPE SLIDE

LOCK

EM170AOM140368A.DGN

LATCH

GIRT BAR

– Main handle DOWN (Door closed and latched) – Vent Flap lever UP (Vent Flap opened and door unlocked) – Arming lever DOWN (Escape Slide ARMED)

ARMED LOCK

AOM-1502-003

GIRT BAR

ESCAPE SLIDE

LOCK EM170AOM140388A.DGN

LATCH

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REVISION 16

Doors

Page 7

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

– Main handle DOWN (Door closed and latched) – Vent Flap lever DOWN (Vent Flap closed and door locked) – Arming lever UP (Escape Slide DISARMED)

DISARMED

GIRT BAR

ESCAPE SLIDE

LOCK

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Doors

REVISION 16

AOM-1502-003

LOCK

EM170AOM140389A.DGN

LATCH

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

DOOR OPENING – NORMAL OPERATION TO OPEN: ARMED

2

1 A

B

A

OPEN THE LINING COVER.

B LOCK

3

GRAB BOTH ESCAPE SLIDE AND VENT FLAP LEVERS AND LIFT THEM UP. ENSURE THAT ALL THE FINGERS ARE FIRMLY HOLDING BOTH LEVERS. CLOSE THE LINING COVER.

DISARMED

C

LOCK

GIRT BAR INDICATION

AOM-1502-003

C

CHECK ESCAPE SLIDE INDICATION (DISARMED) AND GIRT BAR WITH NO RED INDICATION.

EM170AOM140328G.DGN

C

ESCAPE SLIDE DISARM

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REVISION 16

Doors

Page 9

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

4 D

5 F E D

LIFT THE MAIN HANDLE ALL THE WAY UP.

6

G

E

HOLD THE ASSISTANCE HANDLE.

F

PUSH THE DOOR OUT.

EM170AOM140329D.DGN

G

FULLY OPEN THE DOOR TO LOCK IT OPEN.

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Doors

REVISION 16

AOM-1502-003

MAIN HANDLE ACTUATION

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

DOOR CLOSING – NORMAL OPERATION TO CLOSE:

1 A

B A

HOLD THE ASSISTANCE HANDLE

B

ACTUATE THE LOCK TO RELEASE THE DOOR.

C

PULL THE HANDLE TO CLOSE THE DOOR

2

C

3

E D

AOM-1502-003

E

PULL THE DOOR AND BRING IT TO THE CLOSED POSITION. EM170AOM140021B.DGN

D

MOVE THE MAIN HANDLE ALL THE WAY DOWN.

MAIN HANDLE ACTUATION

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REVISION 16

Doors

Page 11

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

4

DISARMED

E

E

5

OPEN THE LINING COVER.

F LOCK

6

ARMED

G

LATCH

G

G F

G

GRAB BOTH ESCAPE SLIDE AND VENT FLAP LEVERS AND MOVE THEM DOWN. ENSURE THAT ALL THE FINGERS ARE FIRMLY HOLDING BOTH LEVERS.

LOCK

GIRT BAR INDICATION

G

CHECK ESCAPE SLIDE INDICATION (ARMED), THE LOCK AND LATCH GREEN INDICATIONS, AND GIRT BAR RED INDICATION.

EM170AOM140330F.DGN

G

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Doors

REVISION 16

AOM-1502-003

ARMING ESCAPE SLIDE

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

DOOR OUTSIDE OPENING !PRE-MOD SB 0170-52-0031

TO OPEN:

1 A B

2 A

ENSURE VENT FLAP IS CLOSED (FLUSH).

B

PUSH THE COVER AND GRAB THE HANDLE.

D

3

C

AOM-1502-003

D

LIFT THE MAIN HANDLE ALL THE WAY UP.

FULLY PUSH THE DOOR AND LOCK IT OPEN.

EM170AOM140025C.DGN

C

"

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REVISION 16

Doors

Page 13

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

!POST-MOD SB 0170-52-0031

TO OPEN:

1 A

2 A

PUSH THE COVER AND GRAB THE HANDLE.

C

3

B

C

LIFT THE MAIN HANDLE ALL THE WAY UP.

FULLY PUSH THE DOOR AND LOCK IT OPEN.

EM170AOM141077A.DGN

B

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Doors

REVISION 16

AOM-1502-003

"

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

DOOR OUTSIDE CLOSING

TO CLOSE:

1

2

A

A

ACTUATE THE LOCK TO RELEASE THE DOOR.

B

PULL THE HANDLE TO CLOSE THE DOOR.

C

B

3 C

PULL THE DOOR TO THE CLOSED POSITION.

4

D

MOVE THE HANDLE FULLY DOWN.

E

AOM-1502-003

E

PULL OUT THE VENT FLAP.

EM170AOM140026B.DGN

D

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REVISION 16

Doors

Page 15

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

EMERGENCY EXITS Both service and passenger doors are designed as type I emergency doors. Emergency slides are provided at both passenger and service doors. The direct vision windows in the cockpit are designed as emergency exits. Opening the door from inside in emergency mode will activate the Emergency Assisting System that will fully open the door after lifting up the main internal handle. The Emergency Assisting System is installed in passenger and service doors. !EMBRAER 170 Models

In case of ditching, the aft passenger and service doors are supposed to be under the water line. Forward doors must be used to evacuate the airplane. " !EMBRAER 175 Models

In case of ditching, all emergency exits are supposed to be over the water line.

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Doors

REVISION 16

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

DOOR OPENING – EMERGENCY OPERATION

1 A

2 B

A

LIFT THE MAIN HANDLE ALL THE WAY UP.

3

AOM-1502-003

C

FIRMLY PUSH THE DOOR.

EM170AOM140022B.DGN

B

THE DOOR OPENS AND ESCAPE SLIDE DEPLOYS.

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REVISION 16

Doors

Page 17

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

CARGO DOORS The cargo doors located aft and forward of the wing on the right side of the fuselage are manually operated from the outside. They have a locking mechanism controlled by an external handle, stowed in the lower half of the door. The vent flap prevents pressurization of the airplane above 0.5 psi when the door is not fully closed, latched and locked. The cargo doors open outward and are hinged along the upper edge and are latched at the lower edge with four hooks.

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Doors

REVISION 16

AOM-1502-003

The cargo doors support maximum wind gusts of 40 kt, valid for positions between fully closed and fully open. For the open and locked position, the wind load limitation is 60 kt.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

CARGO DOORS OPENING

TO OPEN:

1

2

HANDLE COVER VENT PANEL BUTTON MAIN HANDLE VENT PANEL PUSH IN THE MAIN DOOR HANDLE COVER. PULL THE MAIN DOOR HANDLE FULLY UP TO RELEASE THE DOOR.

PUSH DOWN THE VENT PANEL BUTTON. PUSH IN THE VENT PANEL.

3

4

VIEWED FROM INSIDE CARGO COMPARTMENT

ROD

AOM-1502-003

OPEN AND HOLD THE DOOR. REMOVE ROD FROM STOWAGE.

ENGAGE THE ROD TO DOOR’S ROD ATTACHMENT AND LIFT DOOR TO FULLY OPEN POSITION WITH ASSISTANCE OF ROD. CHECK IF DOOR IS LOCKED IN FULLY OPEN POSITION. STOW THE ROD.

EM170AOM080005D.DGN

ROD

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REVISION 16

Doors

Page 19

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

CARGO DOORS CLOSING TO CLOSE: STABILIZATION HANDLE

1

VIEWED FROM INSIDE THE CARGO COMPARTMENT

2

ROD STOWAGE

ROD

ROD REMOVE THE ROD FROM THE STOWAGE. ENGAGE THE ROD TO THE DOOR’S ROD ATTACHMENT (HANDLE), AND WHILE PUSHING IT UP, TURN IT CLOCKWISE.

PULL THE DOOR DOWN WITH THE ROD AND GRASP THE INTERNAL HANDLE. REMOVE THE ROD FROM THE DOOR AND PUT IT INTO THE CARGO COMPARTMENT STOWAGE.

LOCK HANDLE

3

MAIN HANDLE (OPEN)

4

VENT−FLAP (OPEN)

CORRECT POSITION

MAIN HANDLE (OPEN)

VENT−FLAP (OPEN)

MAKE SURE THAT LOCK HANDLE IS IN THE OPEN POSITION (DOWN) BEFORE CLOSING THE DOOR.

MOVE THE DOOR DOWN AND INTO THE FUSELAGE.

5

6 MAIN HANDLE (CLOSED)

MAIN HANDLE VENT−FLAP (OPEN)

CHECK IF THE DOOR IS LATCHED. GRAB THE DOOR BY VENT−FLAP APERTURE AND PULL THE DOOR. IF THE DOOR MOVES, LIFT THE MAIN HANDLE AND LATCH THE DOOR AGAIN (STEP 5).

PUSH THE DOOR MAIN HANDLE FULLY DOWN.

7

VENT−FLAP (OPEN)

VENT−FLAP

LOCK

LATCH

PULL OUT THE VENT−FLAP. ENSURE THAT MAIN HANDLE AND VENT−FLAP ARE FLUSH WITH THE DOOR. ENSURE THAT DOOR IS CORRECTLY CLOSED (FLUSH WITH FUSELAGE). CHECK LOCK AND LATCH GREEN INDICATIONS.

14-01-45 Copyright © by Embraer. Refer to cover page for details.

Page 20

Doors

REVISION 16

AOM-1502-003

LATCH

EM170AOM140703C.DGN

FLUSH

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

ACCESS DOORS A number of access doors, which provides access for servicing the airplane systems and equipment, can be found along the fuselage. • Forward avionics compartment access door. • Mid avionics compartment access door. • Fueling/defueling compartment access door.

•

Rear fuselage door.

FWD CARGO COMPARTMENT DOOR

RAT

REFUELING/DEFUELING COMPARTMENT ACCESS DOOR

FWD AVIONICS COMPARTMENT ACCESS HATCH

AFT CARGO COMPARTMENT DOOR REAR FUSELAGE DOOR (HYD 3)

MID AVIONICS COMPARTMENT ACCESS DOOR

EM170AOM140354.DGN

NOSE LANDING GEAR DOOR

ACCESS DOORS

DOORS WARNING SYSTEM Door warning is provided for all external and access doors and hatches in the pressurized vessel. Proximity sensors processed by the proximity sensor evaluation modules (PSEM), monitor the doors.

AOM-1502-003

An EICAS message displays whenever an unlocked condition of any external door has occurred. Additionally the MFD indicates the open door condition in a graphical representation.

14-01-45 Copyright © by Embraer. Refer to cover page for details.

REVISION 16

Doors

Page 21

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

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Page 22

Doors

REVISION 16

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

ESCAPE SLIDE The escape slides are designed to provide passengers and crew a means to safely descend from the airplane to the ground during an emergency evacuation. In the event of emergency evacuation, the slides deploy automatically when the exit door is opened. Upon completion of the inflation sequence, the slide is fully inflated and ready to assist passengers and crew in descending to the ground. The emergency evacuation slides are equipped with a lighting system independent from the airplane. The unfolding process activates the lighting system illuminating the sliding surface and the area where evacuees make first contact with the ground. A battery contained within the slide provides electrical power to the lights. The escape slides are armed by raising the slide arming lever cover located on the door and moving the slide arming lever to the “armed” position (down). The lever movement attaches the girt bar to the cabin floor brackets. The escape slide is attached to the girt bar by means of a fabric girt. Opening the door from the outside automatically disengages the girt bar from the floor fittings, disarming the slide. !PRE-MOD SB 0170-52-0031

WARNING: MAKE SURE THAT THE VENT FLAP IS CLOSED (FLUSH WITH THE DOOR) BEFORE OPENING THE DOOR FROM THE OUTSIDE. IF THE EXTERNAL HANDLE IS USED TO OPEN THE DOOR WHILE THE SLIDE IS ARMED AND THE VENT FLAP IS OPEN, DOOR EMERGENCY OPENING OPERATION WILL OCCUR AND THE ESCAPE SLIDE WILL DEPLOY. "

A dedicated battery powers the escape slide lights, which will be on for a minimum of 10 min even after the escape slide is disconnected. The scape slide may be used as a flotation device after disconnection from airplane.

AOM-1502-003

If the mooring line is not manually detached from the airplane in an emergency situation, the system is fail safe in that the mooring line will break free from the slide if enough load is applied.

14-01-50 Copyright © by Embraer. Refer to cover page for details.

REVISION 11

Escape Slide

Page 1

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

SLIDE ARM−DISARM HANDLE

INFLATION CYLINDER PRESSURE READINESS INSPECTION WINDOW

GIRT BAR ENGAGEMENT INDICATOR WINDOW

NO GO INDICATION

GO INDICATION

TEMP COMP NMC

PRESSURE GAUGE

MANUAL INFLATION HANDLE

EM170AOM120003.DGN

Goodrich

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Page 2

Escape Slide

REVISION 11

AOM-1502-003

ESCAPE SLIDE – PACKED

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

GIRT ASSEMBLY

RESTRAINT PATCH

INFLATABLE TUBES

RESTRAINT PATCH

SLIDE SURFACE LIFELINE

DETACHABLE MOORING LINE

LED

LED

EM170AOM120002B.DGN

DEFLATED HANDLE

LED

AOM-1502-003

ESCAPE SLIDE – DEPLOYED

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REVISION 11

Escape Slide

Page 3

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

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Page 4

Escape Slide

REVISION 11

AOM-1502-003

ESCAPE SLIDE DISCONNECTION

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

B

A

RAISE THE FLAP.

PULL THE HANDLE.

C

AOM-1502-003

EM170AOM140373B.DGN

THE SLIDE BREAKS FREE FROM THE AIRPLANE, BUT IS RETAINED BY THE MOORING LINE.

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REVISION 11

Escape Slide

Page 5

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

MOORING LINE

INSTRUCTIONS

CABIN CREW POSITIONED ON TOP OF THE EVACUATION SLIDE SHOULD FOLLOW THE INSTRUCTIONS WRITTEN IN RED INK.

E D

UNSNAP THE POCKET

E

PULL AND RELEASE THE RED HANDLE

THE SLIDE BREAKS FREE FROM THE AIRPLANE THE MOORING LINE STAYS WITH THE AIRPLANE

EM170AOM140765A.DGN

D

14-01-50 Copyright © by Embraer. Refer to cover page for details.

Page 6

Escape Slide

REVISION 11

AOM-1502-003

MOORING LINE DISCONNECTION

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

ABNORMAL OPERATION The airplane escape slide is equipped with a manual inflation actuation control. In the event that the inflation system does not actuate automatically, the cabin attendant should pull on the manual inflation handle, which activates the inflation system and fully inflates the slide. The airplane escape slide is designed to permit use with ground personnel assistance as a non-inflatable device in the event of puncture or tear. The resulting damage may render the device incapable of holding air and sustaining an inflated condition.

AOM-1502-003

If the slide is not fully inflated during evacuation, people already positioned on the ground may pull the slide tightly by its handles while other passengers continue to evacuate the airplane.

14-01-50 Copyright © by Embraer. Refer to cover page for details.

REVISION 11

Escape Slide

Page 7

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

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Page 8

Escape Slide

REVISION 11

AOM-1502-003

DEFLATED ESCAPE SLIDE OPERATION

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AOM-1502-003

EM170AOM140391A.DGN

AIRPLANE OPERATIONS MANUAL

14-01-50 Copyright © by Embraer. Refer to cover page for details.

REVISION 11

Escape Slide

Page 9

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

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Page 10

Escape Slide

REVISION 11

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

REINFORCED COCKPIT DOOR GENERAL The Reinforced Cockpit Door is ballistic and intrusion resistant door designed in accordance with requirements issued by international airworthiness authorities. The door weight is approximately 25.4 kg (56 lb). A Cockpit Door Control Panel and a passenger cabin control panel command the door latch. The door’s electromechanical latch installed on the cockpit side can be remotely or manually operated. !Airplanes equipped with Reinforced Cockpit Doors - latch at door UPPER BLOW OUT PANEL UPPER PIVOT PIN

PEEPHOLE DOOR PANEL

DOORKNOB LOWER PIVOT PIN

MAINTENANCE LOCK

BLOW OUT PANEL QUICK RELEASE PASSIVE LOCK

PEEPHOLE

STRAP HANDLE

DOORKNOB LOWER BLOW OUT PANEL

ELECTROMECHANICAL LATCH MAINTENANCE LOCK

EM170AOM140333A.DGN

DOOR PANEL

AOM-1502-003

"

14-01-60 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cockpit Door

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

!Airplanes equipped with Reinforced Cockpit Doors - latch at bulkhead UPPER BLOW OUT PANEL UPPER PIVOT PIN

PEEPHOLE DOOR PANEL

DOORKNOB MAINTENANCE LOCK

LOWER PIVOT PIN

BLOW OUT PANEL QUICK RELEASE PASSIVE LOCK

PEEPHOLE

DOORKNOB LOWER BLOW OUT PANEL

STRAP HANDLE ELECTROMECHANICAL LATCH MAINTENANCE LOCK

EM170AOM140580A.DGN

DOOR PANEL

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Page 2

Cockpit Door

REVISION 18

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

ELECTROMECHANICAL LATCH !Airplanes equipped with Reinforced Cockpit Doors - latch at door

An electrically-actuated solenoid closes the electromechanical latch. A spring opens the latch when the solenoid is not energized, ensuring the door will not lock closed in case of electrical failure of the latch. The door will not close if the electromechanical latch is locked while the door is opened. It is necessary to unlock the electromechanical latch to place the door to the closed position.

MECHANICAL HANDLE

EM170AOM140334A.DGN

NOTE: – The electromechanical latch will not open if the flight crew commands the reinforced cockpit door to UNLOCK while the door is pulled towards the cabin side. It is recommended to wait until latch is unlocked before pulling open the door. The sound of the mechanism is heard when the latch unlocks. – A pre flight test should be performed daily to check the buzzer of the emergency access cycle aural alarm.

AOM-1502-003

"

14-01-60 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cockpit Door

Page 3

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

!Airplanes equipped with Reinforced Cockpit Doors - latch at bulkhead

An electrically-actuated solenoid closes the electromechanical latch. The control panel in the cockpit sends an electrical pulse to the electromechanical latch, which actuates a bolt and locks the door. The door is unlocked when a new electrical pulse is sent to the electromechanical latch. The DC BUS 2 powers the door′s electromechanical latch. In case of electrical failure the door latch will stay in its previous setting. In this case the manual override inside the cockpit can be used to lock or unlock the door. The door will not close if the electromechanical latch is locked while the door is opened. It is necessary to unlock the electromechanical latch to place the door to the closed position. NOTE: – The electromechanical latch will not open if the flight crew commands the reinforced cockpit door to UNLOCK while the door is pulled towards the cabin side. It is recommended to wait until latch is unlocked before pulling open the door. The sound of the mechanism is heard when the latch unlocks. – A pre flight test should be performed daily to check the buzzer of the emergency access cycle aural alarm.

EM170AOM140581A.DGN

MECHANICAL HANDLE

14-01-60 Copyright © by Embraer. Refer to cover page for details.

Page 4

Cockpit Door

REVISION 18

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

!Airplanes equipped with Reinforced Cockpit Doors - Adams Rite cockpit door system

The electrical operation is made through the cockpit control panel. An electrically-actuated solenoid closes the electromechanical latch. The control panel in the cockpit sends an electrical pulse to the electromechanical latch, which actuates a bolt and locks the door. The door is unlocked when a new electrical pulse is sent to the electromechanical latch. The DC BUS 2 powers the door′s electromechanical latch. In case of electrical failure the door latch will stay in its previous setting. The manual operation is made through the manual override lock/unlock knob located on the electromechanical latch. To lock, the manual override knob is moved upward until a stop is reached, then it is released. Once the manual override knob has come to rest, a green flag will be exposed. To manually unlock the electromechanical latch, the manual override knob is moved upward until a stop is reached, then the manual override knob is released. Once the manual override knob has come to rest, a red flag will be exposed. The lock/unlock indication (green/red flag) occurs independent of how the electromechanical latch is operated (electrically or manually). The door will not close if the electromechanical latch is locked while the door is opened. It is necessary to unlock the electromechanical latch to place the door to the closed position.

AOM-1502-003

NOTE: – The electromechanical latch will not open if the flight crew commands the reinforced cockpit door to UNLOCK while the door is pulled towards the cabin side. It is recommended to wait until latch is unlocked before pulling open the door. The sound of the mechanism is heard when the latch unlocks. – A pre flight test should be performed daily to check the buzzer of the emergency access cycle aural alarm.

14-01-60 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cockpit Door

Page 5

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

ALTERNATE LOCK/INHIBIT KNOB

ELECTROMECHANICAL DOOR LATCH

MANUAL LOCK/UNLOCK KNOB REINFORCED COCKPIT DOOR LOCK

EM170AOM141248B.DGN

REINFORCED COCKPIT DOOR LOCK HANDLE

14-01-60 Copyright © by Embraer. Refer to cover page for details.

Page 6

Cockpit Door

REVISION 18

AOM-1502-003

"

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

SYSTEM LOGIC Actuating the EMERG ENTRY pushbutton starts the chime alarm sequence. The DING-DONG sound chime remains on for 4 s and is repeated three times at 9-second intervals during which the sound chime remains paused. After the third chime cycle ends, the door will unlock if the INHIB pushbutton is not pressed within 30 s after EMERG ENTRY pushbutton actuation.

DOOR OPENING

30s 0s 26s ALARM ON ALARM ON

ALARM OFF 9s

17s

4s

4s

EM170AOM140335A.DGN

4s

ALARM OFF 9s

ALARM ON 4s

13s

!Airplanes equipped with Electromechanical Door Latch with Security Lever

Security Lever In case of failure in the inhibition function, the security lever locks the override switch and prevents the door from opening 30 s after the beginning of the system’s logic.

UNLOCKED INDICATION

LOCKED INDICATION

SECURITY LEVER

EM170AOM140582A.DGN

OVERRIDE SWITCH

AOM-1502-003

SECURITY LEVER

"

14-01-60 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cockpit Door

Page 7

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

!Airplanes equipped with Electromechanical Door Latch with Inhibit Knob

Inhibit Knob In case of failure in the inhibition function, the inhibit knob locks the manual override button and prevents the door from opening 30 s after the beginning of the system’s logic.

FREE

FREE

INHIBIT

INHIBIT KNOB

EMERGENCY ONLY

INHIBIT

INHIBIT KNOB

EMERGENCY ONLY

FREE

INHIBIT

EMERGENCY ONLY

MANUAL OVERRIDE BUTTON

FLIGHT CREW ONLY

FLIGHT CREW ONLY

FLIGHT CREW ONLY

LOCKED

LOCKED

LOCKED

UNLOCKED

UNLOCKED

UNLOCKED

EM170AOM140847A.DGN

MANUAL OVERRIDE BUTTON

" !Airplanes equipped with Reinforced Cockpit Doors - Adams Rite cockpit door system

Alternate Lock/Inhibit Knob The alternate lock/inhibit knob must remain in the unlock position if the system is properly working.

In case of the electromechanical latch is failed on the locked position,

14-01-60 Copyright © by Embraer. Refer to cover page for details.

Page 8

Cockpit Door

REVISION 18

AOM-1502-003

In case the electromechanical latch is failed in the unlocked position, being not possible to lock it through the Cockpit Door Control Panel or using the manual lock/unlock knob, the door can be closed and locked positioning the Alternate Lock/Inhibit knob on AL 1. This position is also to be used as inhibit backup, if the electrical inhibit system is failed.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

being not possible to unlock it through the cabin control panel activation or using the manual lock/unlock knob, the door can be closed and locked positioning the Alternate Lock/Inhibit knob on AL 2. To close and lock the door, in the case the electromechanical latch stuck failed, use Alternate Lock/Inhibit knob on AL 2 position. This condition overrides the door pin actuator, and avoids the occurrence of the door locked with no one in the cockpit.

AL 2 POSITION: LOCKED WITH DOOR LATCH FAILED LOCKED

EM170AOM141247B.DGN

AL 1 POSITION: LOCKED WITH DOOR LATCH FAILED UNLOCKED

UNLOCKED POSITION

"

MANUAL OVERRIDE

!Airplanes equipped with Reinforced Cockpit Doors - latch at door

AOM-1502-003

A mechanical handle overrides the latch locking system. Normally the handle is pointing down. Turning the handle upward 90° disconnects the latch from the solenoid, allowing the manual lock and unlock of the cockpit door. Turning the handle upwards locks the bolt in LOCKED position. NOTE: Latch manual operation through the mechanical handle must be used to override the locking system solely in case of system electrical failure.

14-01-60 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cockpit Door

Page 9

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

EM170AOM140336A.DGN

AIRPLANE GENERAL DESCRIPTION

"

MANUAL OVERRIDE

!Airplanes equipped with Reinforced Cockpit Doors - latch at bulkhead

The latch locking system can be overridden by actuating either a mechanical handle installed on the door or a manual override button installed on the electromechanical latch. The door lock bolt retracts by turning down the mechanical handle. It opens the door and allows an emergency egress. A red mark on the handle indicates that the door is unlocked. Turning the handle upwards will set the bolt to the LOCKED position.

The manual override button installed in the electromechanical latch

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Page 10

Cockpit Door

REVISION 18

AOM-1502-003

EM170AOM140583B.DGN

NOTE: Latch manual operation through the mechanical handle must be used to override the locking system solely in case of system electrical failure.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

manually unlocks the door. Actuating downwards the manual override button alternates between locked and unlocked status. If the door is unlocked, a red indication is shown on the button. The door is locked when a green indication is shown. "

MANUAL OVERRIDE

!Airplanes equipped with Reinforced Cockpit Doors - Adams Rite cockpit door system

The latch locking system can be overridden by actuating either a mechanical handle installed on the door or the manual override lock/unlock knob installed on the electromechanical latch. The door lock bolt retracts by turning down the mechanical handle. It opens the door and allows an emergency egress. A red mark on the handle indicates that the door is unlocked. Turning the handle upwards will set the bolt to the LOCKED position.

EM170AOM141250A.DGN

NOTE: – Latch manual operation through the mechanical handle must be used to override the locking system only in case of system electrical and/or mechanical failure. – The alternate lock/inhibit knob must be in the unlock position for manual override.

AOM-1502-003

"

14-01-60 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cockpit Door

Page 11

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE GENERAL DESCRIPTION

AUXILIARY LOCKS PASSIVE LOCK A passive lock installed on the cockpit door does not permit the door to be pushed towards the passenger cabin whenever the door is closed. The normal position of the quick release pin is locked. The passive lock is unlocked when the pin is removed. NOTE: The passive lock must be unlocked only under emergency conditions, for an emergency cockpit egress procedure. !Airplanes equipped with Reinforced Cockpit Doors - latch at door

EM170AOM140337A.DGN

QUICK RELEASE LOCK

" !Airplanes equipped with Reinforced Cockpit Doors - latch at bulkhead

EM170AOM140584A.DGN

QUICK RELEASE LOCK

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Page 12

Cockpit Door

REVISION 18

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

MAINTENANCE LOCK A maintenance lock blocks the door during the airplane’s overnight parking. A key is necessary to lock and unlock it. The keyhole is located on the passenger cabin side of the door.

UPPER BLOW OUT PANEL UPPER PIVOT PIN

PEEPHOLE DOOR PANEL

DOORKNOB LOWER PIVOT PIN

MAINTENANCE LOCK

BLOW OUT PANEL QUICK RELEASE PASSIVE LOCK

PEEPHOLE

STRAP HANDLE

DOORKNOB LOWER BLOW OUT PANEL

ELECTROMECHANICAL LATCH

AOM-1502-003

MAINTENANCE LOCK

EM170AOM140333A.DGN

DOOR PANEL

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REVISION 18

Cockpit Door

Page 13

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

BLOWOUT PANELS The reinforced cockpit door assembly possesses two blowout panels to equalize sudden decompression. When a sudden decompression occurs, the blowout bags automatically unfold and deploy forward. The blowout bags installed within grill-protected openings maintain the door’s full ballistic and impact-resistant characteristics even when deployed. Both blowout bags can be deployed with the observer seat in use and without any type of interference or hazard to the observer. A door grill opening equalizes the pressure in the event of decompression in the passenger cabin area. !Airplanes equipped with Reinforced Cockpit Doors - latch at door

LOWER BLOWOUT BAG

EM170AOM140339A.DGN

UPPER BLOWOUT BAG

" !Airplanes equipped with Reinforced Cockpit Doors - latch at bulkhead

LOWER BLOWOUT BAG

EM170AOM140585A.DGN

UPPER BLOWOUT BAG

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Page 14

Cockpit Door

REVISION 18

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

PEEPHOLE The reinforced cockpit door is equipped with a ballistic-resistant peephole. The peephole field of view inhibits any hidden threats.

AOM-1502-003

EM170AOM140340A.DGN

BALLISTIC PEEPHOLE

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REVISION 18

Cockpit Door

Page 15

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

JAMMED DOOR EMERGENCY EGRESS

!Airplanes equipped with Reinforced Cockpit Doors - latch at door

1

2

B

CHECK THE RED INDICATION TO ASSURE THE DOOR IS UNLATCHED

C

REMOVE THE QUICK RELEASE PIN

4

PUSH THE DOOR OUTBOARDS WHILE HOLDING THE HANDLE

D

REMOVE THE DOOR

"

14-01-60 Copyright © by Embraer. Refer to cover page for details.

Page 16

Cockpit Door

REVISION 18

AOM-1502-003

3

B

EM170AOM140437B.DGN

A

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

!Airplanes equipped with Reinforced Cockpit Doors - latch at bulkhead

1

2

B

CHECK THE RED INDICATION TO ASSURE THE DOOR IS UNLATCHED

3

C

B

REMOVE THE QUICK RELEASE PIN

4

PUSH THE DOOR OUTBOARDS WHILE HOLDING THE HANDLE

D

REMOVE THE DOOR

EM170AOM140586A.DGN

A

AOM-1502-003

"

14-01-60 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Cockpit Door

Page 17

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

!Airplanes equipped with Reinforced Cockpit Doors - Adams Rite cockpit door system

1

2

B

CHECK THE RED INDICATION TO ASSURE THE DOOR IS UNLATCHED AND MAKE SURE THE "ALTERNATE LOCK/INHIBIT KNOB" IS UNLOCKED

3

C

B

REMOVE THE QUICK RELEASE PIN

4

PUSH THE DOOR OUTBOARDS WHILE HOLDING THE HANDLE

D

REMOVE THE DOOR

EM170AOM141249A.DGN

A

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Page 18

Cockpit Door

REVISION 18

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

WATER A central storage tank holds potable water. Pressurized water is supplied to the heaters and faucets in the lavatories and water spigots, and coffee makers in the galleys. Water is also supplied for flushing of the vacuum toilets in the lavatories. Engine and APU bleed air pressurizes the potable water system. If the engines or APU are not running on the ground, or bleed air pressure is below the optimal range during the flight, an optional air compressor pressurizes the water system. The potable water storage tank’s maximum capacity is configured to 70 . The AFT flight attendant panel indicates the percentage of total water quantity remaining in the tank. The lavatory faucet has a single cap. Water flow is started by pressing the cap, while rotating it allows water temperature control. Water from lavatory washbasins and galleys is automatically drained through forward and aft drain masts on ground and in flight. In case of water system leakage at either the galley or the lavatory, the respective shutoff valve may be actuated to isolate the system. If the auto-drain valve clogs, the flight attendant may manually actuate the remote actuation cable located on the front of the galley. Pulling on the self drain valve handle clears the galley drain valve. Access to the lavatory valve is through the under sink cabinet door. Pulling up on the ring handle clears the lavatory drain valve. The flight attendant panel indicates a FAULT condition whenever: – A fault in the respective (FWD or AFT) drain valve is detected; – Water level indication is not available;

AOM-1502-003

– In-flight drainage is not available due to a fault in the drain valve or in the drain mast heater.

14-01-65 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Water and Waste

Page 1

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

WASTE The vacuum waste system collects waste from the lavatory toilets to an aft mounted vertical waste tank. A vacuum generator is used to create differential pressure on the ground or at altitudes below 18000 ft. At higher altitudes, the differential between the airplane’s cabin pressure and ambient pressure is sufficient to transport the waste. Pushing the flushing switch located inside the lavatory initiates toilet-flushing sequence. Water is introduced to rinse the bowl before opening of the toilet-flushing valve. The usable capacity of the waste tank is 95 liters. The Service Tank indication illuminates on the flight attendant’s panel when waste tank capacity reaches 75%. When the waste tank’s full capacity is reached, the Tank Full indication illuminates and the vacuum toilets are disabled. Waste tank draining is performed through the service panel on the aft right-hand side of the fuselage.

WATER AND WASTE HEATING SYSTEM

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Page 2

Water and Waste

REVISION 20

AOM-1502-003

Electrical heating for the water and waste system is provided to prevent ice accumulation on fill/drain nipples and forward and rear drain masts. The water system controller monitors the system and indicates any failure on the flight attendant panel as described in the Airplane General – Controls and Indications section.

AOM-1502-003

REVISION 20

Water and Waste

FWD DRAIN VALVE

SUMP

AUTO− DRAIN VALVE

SINK

FWD GALLEY SPIGOT

EM170AOM141084A.DGN

MANUAL SHUTOFF VALVE

WATER FILTER

COFFEE MAKER

FWD DRAIN MAST

MANUAL SHUTOFF VALVE

WATER HEATER

SUMP

AUTO− DRAIN VALVE

TOILET BOWL

DRAIN

SINK

FWD LAVATORY FAUCET

SUMP

AUTO− DRAIN VALVE

SINK

MANUAL SHUTOFF VALVE

FILL/ DRAIN NIPPLE

LEVER SENSOR

INDICATION PANEL

DOOR SWITCH

FILL/ DRAIN SWITCH

COMPRESSOR

AIR MANIFOLD

CABIN FLOOR

FILL/DRAIN VALVE

POTABLE WATER TANK

OVERFLOW TUBE

BLEED AIR

SUMP

AUTO− DRAIN VALVE

TOILET BOWL

DRAIN

SINK

AFT LAVATORY FAUCET

FILL/DRAIN VALVE

WATER HEATER

POTABLE WATER SERVICE PANEL

AFT GALLEY SPIGOT

AFT DRAIN MAST

MANUAL SHUTOFF VALVE

WATER FILTER

COFFEE MAKER

AIRPLANE OPERATIONS MANUAL SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

POTABLE AND GRAY WATER SCHEMATIC

Copyright © by Embraer. Refer to cover page for details.

14-01-65

Page 3

Page 4

Copyright © by Embraer. Refer to cover page for details.

14-01-65

Water and Waste

REVISION 20

AOM-1502-003

FLUSH VALVE

POTABLE WATER

MANUAL SHUTOFF VALVE

RINSE VALVE

AIRPLANE FLOOR

TOILET BOWL FLUSH VALVE

FLUSH SWITCH

POTABLE WATER

WASTE DRAIN BALL VALVE HANDLE

WASTE DRAIN BALL VALVE

WASTE LINE

DRAIN LINE

WASTE TANK

RINSE FILL NIPPLE SERVICE PANEL SWITCH

LIQUID LEVEL SENSORS

SERVICE PANEL DRAIN VALVE & CAP

HEATERS

MANUAL SHUTOFF VALVE

RINSE VALVE

VACUUM WASTE SERVICE PANEL

AFT LAV

RINSE LINE

OVERBOARD VENT

CHECK VALVE

AIRPLANE GENERAL DESCRIPTION

EM170AOM140279.DGN

TOILET BOWL

FLUSH SWITCH

FWD LAV

VACUUM GENERATOR

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

WASTE SCHEMATIC

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

CARGO COMPARTMENTS The airplane has two class C cargo compartments. Both compartments are equipped with fire detection and extinguishing systems providing protection against fire damage.

AOM-1502-003

REAR CARGO COMPARTMENT

EM170AOM140254.DGN

FORWARD CARGO COMPARTMENT

14-01-70 Copyright © by Embraer. Refer to cover page for details.

REVISION 10

Cargo Compartment

Page 1

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

14-01-70 Copyright © by Embraer. Refer to cover page for details.

Page 2

Cargo Compartment

REVISION 10

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

EICAS MESSAGES TYPE

WARNING

AOM-1502-003

CAUTION

MESSAGE DOOR CRG AFT (FWD) OPEN DOOR PAX AFT (FWD) OPEN

MEANING Associated baggage door open or not properly locked. Main door is open or not properly locked either on the ground with any engine running or in flight. DOOR SERV AFT Service door is open or not (FWD) OPEN properly locked either on the ground with any engine running or in flight. APM FAIL At least three APMs have failed. APM MISCOMP One or more APMs do not match. AVNX MAU 1 (2) (3) A All functions in the (B) FAIL associated MAU channel have failed. AVNX MAU 1 (2) (3) A None of the functions in the (B) OVHT associated MAU channel is available. AVNX MAU 1 (2) (3) Fan 2, fan 3, or more than FAN FAIL one fan of associated MAU (Pre-Mod Load 25.5) failed. AVNX MAU 1 (2) (3) More than one fan of FAN FAIL associated MAU failed. (Post-Mod Load 25.5) CMS FAIL Both CMSs have failed. No dispatch relief. DOOR CENTER Associated electronic bay is (FWD) EBAY OPEN open or not properly locked. DOOR HYD OPEN Hydraulic system 3 access door is open or not properly locked. EICAS FAULT DU has suffered failure condition(s) that affect the functionality.

14-01-80 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

EICAS Messages

Page 1

AIRPLANE GENERAL DESCRIPTION

TYPE

AIRPLANE OPERATIONS MANUAL

MESSAGE EICAS OVHT

EMER LT NOT ARMED EMER LT ON MFD 1 (2) FAULT

MFD 1 (2) OVHT CAUTION PFD 1 (2) FAULT

PFD 1 (2) OVHT

SYS CONFIG FAIL

MEANING DU has suffered an over temperature condition. Continued operation may result in the loss of DU. Emergency lighting system is not armed. Emergency lighting system is on. DU has suffered failure condition(s) that affect the functionality. DU has suffered an over temperature condition. Continued operation may result in the loss of DU. DU has suffered failure condition(s) that affect the functionality. DU has suffered an over temperature condition. Continued operation may result in the loss of DU. Automatic configuration monitoring system has found non-dispatchable configuration miscompare.

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Page 2

EICAS Messages

REVISION 20

AOM-1502-003

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

TYPE

AOM-1502-003

ADVISORY

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

MESSAGE APM FAULT

MEANING One or two APMs have failed. AVNX DB MODULE On board database module FAIL has failed. AVNX MAU 1 (2) (3) A The associated MAU (B) FAULT channel suffered failure condition(s) that does not affect its functionality, but may cause loss of redundancy. AVNX MAU 1 (2) (3) Only fan 1 of associated FAN FAULT MAU failed. (Pre-Mod Load 25.5) AVNX MAU 1 (2) (3) Only one fan of associated FAN FAULT MAU failed. (Post-Mod Load 25.5) CCD 1 (2) FAULT Cursor control of one or more DUs has been lost. CMS FAULT One CMS has failed, dispatch relief possible. DOOR FUELING Fueling door open or not OPEN properly locked. EMER LT BATT One of the four emergency FAULT batteries is not working properly.

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REVISION 20

EICAS Messages

Page 3

SYSTEMS DESCRIPTION AIRPLANE GENERAL DESCRIPTION

AIRPLANE OPERATIONS MANUAL

14-01-80 Copyright © by Embraer. Refer to cover page for details.

Page 4

EICAS Messages

REVISION 20

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

SECTION 14-02 AIR MANAGEMENT SYSTEM TABLE OF CONTENTS

AOM-1502-003

Block

Page

General Description............................................. 14-02-01 .... GENERAL DESCRIPTION..................................... 14-02-01 ....

1 1

Controls and Indications..................................... 14-02-05 .... AIR CONDITIONING AND PNEUMATIC CONTROL PANEL........................................... 14-02-05 .... PRESSURIZATION CONTROL PANEL................. 14-02-05 .... EICAS INDICATION............................................... 14-02-05 .... SYNOPTIC PAGE ON MFD.................................. 14-02-05 ....

1

Bleed Air System.................................................. 14-02-10 .... PNEUMATIC SYSTEM.......................................... 14-02-10 .... SYSTEM SCHEMATIC.......................................... 14-02-10 .... ENGINE BLEED SYSTEM..................................... 14-02-10 .... APU BLEED........................................................... 14-02-10 .... CROSS BLEED (XBLEED).................................... 14-02-10 .... GROUND CONNECTION...................................... 14-02-10 .... OVERHEAT DETECTION SYSTEM...................... 14-02-10 .... BLEED AIR DISTRIBUTION.................................. 14-02-10 .... BLEED SOURCE PRIORITIZATION..................... 14-02-10 ....

1 1 2 3 4 4 5 5 6 7

Air Conditioning System..................................... 14-02-15 .... ENVIRONMENTAL CONTROL SYSTEM.............. 14-02-15 .... AIR CONDITIONING PACKS................................ 14-02-15 .... CABIN AIR DISTRIBUTION................................... 14-02-15 .... GASPER VENTILATION........................................ 14-02-15 .... RECIRCULATION FANS........................................ 14-02-15 .... ELECTRONIC COMPARTMENTS VENTILATION.. 14-02-15 .... FORWARD CARGO BAY VENTILATION.............. 14-02-15 .... EMERGENCY RAM AIR VENTILATION................ 14-02-15 ....

1 1 1 1 2 2 3 3 4

1 4 6 8

Airplanes equipped with Ram Air Inlet Door

RAM AIR INLET DOOR......................................... 14-02-15 ....

4

14-02-TOC Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Table of Contents

Page 1

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

AIRPLANE OPERATIONS MANUAL

Pressurization System......................................... 14-02-20 .... CABIN PRESSURE CONTROL SYSTEM............. 14-02-20 .... SYSTEM COMPONENTS...................................... 14-02-20 .... OPERATING MODES............................................ 14-02-20 .... CPCS FLIGHT MODES......................................... 14-02-20 ....

1 1 1 3 6

EICAS Messages.................................................. 14-02-25 .... EICAS MESSAGES............................................... 14-02-25 ....

1 1

14-02-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 18

AOM-1502-003

Block Page ECS DISTRIBUTION............................................. 14-02-15 .... 6 AMS AUTOMATION............................................... 14-02-15 .... 7

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

GENERAL DESCRIPTION The Air Management System (AMS) consists of: – The Pneumatic System. – The Environmental Control System (ECS). The Cabin Pressure Control System (CPCS) is part of the AMS, but it has a separate controller. The AMS controller provides primary control for various airplane subsystems such as bleed control, air conditioning control, hot air leak detection, crew oxygen monitoring and wing and engine ice protection. The AMS controller also interfaces with the smoke detectors providing fault detection, isolation, and reporting.

AOM-1502-003

During the AMS operation, if the active channel fails, the control of the system will be automatically transferred to the other channel, with no interruption of AMS system functions.

14-02-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

General Description

Page 1

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

AIRPLANE OPERATIONS MANUAL

14-02-01 Copyright © by Embraer. Refer to cover page for details.

Page 2

General Description

REVISION 17

AOM-1502-003

INTENTIONALLY BLANK

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIR CONDITIONING CONTROL PANEL

AIR MANAGEMENT SYSTEM

AND

PNEUMATIC

OVERHEAD PANEL

3 AIR COND / PNEUMATIC PAX CABIN

RECIRC

CKPT

2

4 C

H

C ATTND

PACK 1

H

PACK 2

1 XBLEED

5 WING 1 START 1

GND CONN

BLEED 1

APU BLEED

WING 2 START 2

BLEED 2

AOM-1502-003

7

EM170AOM140044A.DGN

6

14-02-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 16

Controls and Indications

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIR MANAGEMENT SYSTEM

1 - PACK 1 (2) BUTTON PUSH IN:

allows automatic operation by the AMS. This position opens the respective pack flow control valve. PUSH OUT: manually closes the respective pack flow control valve. 2 - COCKPIT TEMPERATURE ROTATING KNOB – Controls cockpit temperature relative to the knob position. 3 - RECIRCULATION BUTTON PUSH IN:

allows automatic operation by the AMS. This position turns on both recirculation fans, according to system operational logic. PUSH OUT: turns off both recirculation fans. 4 - PASSENGER CABIN TEMPERATURE ROTATING KNOB – Controls passenger cabin temperature relative to the knob position. – Rotating the knob to the ATTND position allows the cabin temperature to be controlled by the flight attendant control panel. 5 - CROSS-BLEED BUTTON PUSH IN:

allows automatic operation by the AMS. This position opens the cross-bleed valve, according to system logic. PUSH OUT: manually closes the cross-bleed valve. 6 - BLEED AIR BUTTON allows automatic operation by the AMS. This position commands the respective engine bleed valves, according to system logic. PUSH OUT:manually closes the engine bleed valves.

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Page 2

Controls and Indications

REVISION 16

AOM-1502-003

PUSH IN:

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

NOTE: When leak is detected, the button amber striped bar is illuminated. 7 - APU BLEED BUTTON PUSH IN:

allows automatic operation by the AMS. This position commands the APU bleed valve, according to system logic. PUSH OUT:closes the APU bleed valve.

AOM-1502-003

NOTE: When leak is detected, the button amber striped bar is illuminated.

14-02-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 16

Controls and Indications

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIR MANAGEMENT SYSTEM

PRESSURIZATION CONTROL PANEL OVERHEAD PANEL

PRESSURIZATION CABIN ALT

MODE

STOP

AUTO UP

LFE CTRL

MAN

2

1

3

4

DUMP

STOP DOWN

UP

LFE

EM170AOM140042.DGN

DOWN

1 - DUMP BUTTON (GUARDED) Momentary pushbutton:

– When pressed the dump function is activated and a white striped bar illuminates on the button. When pressed a second time the

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Page 4

Controls and Indications

REVISION 16

AOM-1502-003

– Provides rapid cabin depressurization, by opening the outflow valve and commanding the packs and recirculation fans to off.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

system returns to normal. NOTE: When operating in manual mode, the outflow valve will not be commanded open. 2 - CABIN ALTITUDE SELECTOR KNOB DOWN: STOP: UP:

(momentary action) manually closes the outflow valve. normal operation position. (momentary action) manually opens the outflow valve.

NOTE: Manual actuation of the outflow valve is possible only with the PRESSURIZATION MODE SELECTOR KNOB set to MAN position. 3 - PRESSURIZATION MODE SELECTOR KNOB MAN: AUTO:

allows manual control of the outflow valve. allows automatic operation of the pressurization system. LFE CTRL: allows manual input of landing field elevation, although the pressurization system will remain in automatic mode. 4 - LANDING FIELD ELEVATION (LFE) SELECTOR KNOB DOWN: STOP: UP:

(momentary action) decreases the LFE in 100 ft increments. normal operation position. (momentary action) increases the LFE in 100 ft increments.

AOM-1502-003

NOTE: Manual input of the LFE is possible only with the PRESSURIZATION MODE SELECTOR KNOB set to LFE CTRL position.

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REVISION 16

Controls and Indications

Page 5

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIR MANAGEMENT SYSTEM

EICAS INDICATION

!Airplanes Pre-Mod MAU load 23.1 EICAS

ALT RATE P LFE

68OO -5OO 7.7 21OO

FT FPM PSI FT

1 2 3 4

EM170AOM140043.DGN

CABIN

PRESSURE INDICATION ON EICAS

"

!MAU load 23.1 and on EICAS

5

ALT RATE P LFE

6800 -500 7.7 2100

FT FPM PSI FT

1 2 3 4

EM170AOM141092A.DGN

HI FIELD

CABIN

PRESSURE INDICATION ON EICAS

"

1 - CABIN ALTITUDE INDICATION – Displays cabin altitude in feet, regardless of the operating mode. GREEN: normal operating range. AMBER: cautionary operating range. RED: warning operating range. AMBER DASHED: invalid information.

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Page 6

Controls and Indications

REVISION 16

AOM-1502-003

2 - CABIN RATE OF CHANGE INDICATION

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

– Displays the cabin rate of change in feet per minute, regardless of the operating mode. GREEN: normal operating range. AMBER: cautionary operating range. AMBER DASHED: invalid information or value out of displayable range. 3 - DIFFERENTIAL PRESSURE INDICATION – Displays the differential pressure between the cabin interior and the outside in pounds per square inch, regardless of the operating mode. GREEN: normal operating range. AMBER: caution operating range. RED: warning operating range. AMBER DASHED: invalid information. 4 - LANDING FIELD ELEVATION INDICATION – Displays the landing field elevation in feet, regardless of the operating mode. GREEN: inputs from FMS. CYAN: manual input. A cyan “M” in front of altitude readout indicates manual input. AMBER DASHED: invalid information or value out of displayable range. Manual operation is active. NOTE: Flight plan on MCDU must be closed to display landing field elevation (LFE) on EICAS.

!MAU load 23.1 and on

5 - HI FIELD INDICATION – Displays HI FIELD label whenever the Cabin Altitude Warning set point is shifted from its original value of 9700 ft indicating the airplane is in High Altitude operation mode.

AOM-1502-003

"

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REVISION 16

Controls and Indications

Page 7

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIR MANAGEMENT SYSTEM

SYNOPTIC PAGE ON MFD The environmental control system synoptic page provides a visual representation of the system operation and parameters. It can be selected by flight crew on both MFDs.

MAIN PANEL

5

4 3 Plan TEMP

RECIRC

RAM AIR

SET

Systems C

ACTUAL

25

CKPT

25

25

FWD CAB

25

25

AFT CAB

25

PACK 1

ECS OFV

RECIRC

OPEN

SAFETY VALVE

PACK 2

6

1 45 PSI

FCV1

XBLD

FCV2

45 PSI

FWD CARGO BAY

APU

1

CLOSED

GND CART

7

8

TCAS

Weather

Checklist

14-02-05 Copyright © by Embraer. Refer to cover page for details.

Page 8

Controls and Indications

REVISION 16

AOM-1502-003

Map

EM170AOM140258A.DGN

2

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

1 - AIR SHUTOFF VALVES STATUS – Air shutoff valves are shown as a circle and an internal line representing the valve position. – OPEN: a green circle and a green line aligned with the flow line. – CLOSED: a white circle and a white line perpendicular to the flow line. – UNDETERMINED: an amber dashed circle with no line. – IN TRANSIT: a white circle and a white line in diagonal to the flow line. – FAILED CLOSED: a white circle and a white line perpendicular to the flow line covered by an amber cross. – FAILED OPEN: a green circle and a green line aligned with the flow line covered by an amber cross. 2 - PACK STATUS – ON: a green rectangle. – OFF: a white rectangle. – UNDETERMINED: an amber dashed rectangle. – FAILED: an amber dashed rectangle covered by an amber cross. 3 - RECIRCULATION FAN STATUS – The recirculation fan is shown as a circle and an internal windmill, representing the fan status. – ON: a gray circle and a green windmill. – OFF: a gray circle and a gray windmill. – UNDETERMINED: an amber dashed circle and an amber windmill.

AOM-1502-003

– FAILED: a gray circle and a white windmill beneath an amber cross.

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REVISION 16

Controls and Indications

Page 9

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIR MANAGEMENT SYSTEM

4 - COCKPIT/CABIN TEMPERATURE INDICATION – Digital Temperature. – The digital information displays selectable and actual temperature for the cockpit, forward cabin and aft cabin. GREEN: used for all actual temperature indication. CYAN: used for all set temperature indication. AMBER DASHED: invalid information or value out of displayable range. Temperatures – are set using the Cockpit/Passenger Cabin Temperature rotating knob on the Air Conditioning and Pneumatic control panel. Cabin temperatures can also be set on the Flight Attendant panel. 5 - OUTFLOW VALVE (OFV) POSITION INDICATION – Outflow Valve Scale/Pointer: The pointer on the scale indicates the actual OFV position. When the OFV is fully open at 90°, the pointer will be parked at the OPEN position, at the top of the scale. When the OFV is fully closed at 0°, the pointer will be parked at the CLOSED position, at the bottom of the scale. If the OFV signal is invalid the pointer will be removed from view. – Scale: WHITE: always, despite of OFV position. – Pointer: GREEN (hollow): always, despite of OFV position. 6 - MANIFOLD PRESSURE INDICATION – Digital Pressure.

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Page 10

Controls and Indications

REVISION 16

AOM-1502-003

– Colors: GREEN: normal operating range. AMBER: caution operating range. GRAY: label (psi). AMBER DASHED: invalid information or value out of displayable range.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

7 - FLOW LINE – The flow line is shown as a colorful line. GREEN: indicates an air flow condition. WHITE: indicates a no air flow condition. WHITE/AMBER DASHED: the associated line flow information is invalid. AMBER: overheat condition. 8 - GROUND CART

AOM-1502-003

– Ground cart connection is displayed only when it is connected to the airplane.

14-02-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 16

Controls and Indications

Page 11

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

AIRPLANE OPERATIONS MANUAL

14-02-05 Copyright © by Embraer. Refer to cover page for details.

Page 12

Controls and Indications

REVISION 16

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

PNEUMATIC SYSTEM Bleed air is provided to the Air Management System by the engines, or the APU. The bleed air is used for: – Environmental Control System (ECS); – Engine start; – Engine anti-ice and wing anti-ice; – Water pressurization.

AOM-1502-003

The external ground connections can also be used to supply pressurized air for engine start and for air conditioning.

14-02-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Bleed Air System

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIR MANAGEMENT SYSTEM

SYSTEM SCHEMATIC FLIGHT DECK

E−BAY FWD

PRESSURE REGULATOR VALVE SHUTOFF VALVE

FAN

CHECK VALVE CABIN FWD CARGO

FWD CABIN E−BAY MID FAN E−BAY AFT NEGATIVE PRESSURE RELIEF VALVE

GASPERS

POSITIVE PRESSURE RELIEF VALVE MIXER

FILTER RECIRC

COMPARTMENT RECIRCULATION

AFT CABIN

FILTER RECIRC

FAN

COMPARTMENT RECIRCULATION

FAN

PRESSURIZED OFV

UNPRESSURIZED

AIR COND GND CART

EMERG RAM AIR VALVE

RAM AIR

EMERG RAM AIR CHECK VALVE

6th LP 10th HP

P

FLOW CONTROL VALVE

RAM AIR OVBD

P

PRECOOLER

ENGINE ANTI−ICE

FAMV

WAIV LOW STAGE BLEED CHK VLV

WATER SUPPLY

APU BLEED CHECK VALVE

LP 6th

T

X BLEED VALVE

ENGINE ANTI−ICE

FAMV

ENG START GND CART APU

ENGINE BLEED VALVE

FAN BLEED

HP 10th

PRECOOLER

T

HIGH STAGE BLEED VALVE

FLOW CONTROL VALVE

APU BLEED VALVE

ENGINE BLEED VALVE

STARTER

STARTER

HIGH STAGE BLEED VALVE

14-02-10 Copyright © by Embraer. Refer to cover page for details.

Page 2

Bleed Air System

REVISION 21

AOM-1502-003

RAM AIR OVBD

WAIV LOW STAGE BLEED CHK VLV

ENGINE RAM AIR (POST−MODE SB170−36−0008/01)

PACK 2

PACK 1

FAN BLEED

WING ANTI−ICE

EM170AOM140299B.DGN

WING ANTI−ICE

ENGINE RAM AIR (POST−MODE SB170−36−0008/01)

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

ENGINE BLEED SYSTEM The engine bleed system alternately selects between low pressure and high pressure engine bleed sources in order to maintain adequate and safe bleed supply pressure at any engine-operating condition. This control is established via opening/closing of the Low Pressure Check Valve and of the High Stage Bleed Valve located in the nacelle. The Engine Bleed Valve EBV is installed at the nacelle to regulate the bleed pressure provided by the engine bleed system. Engine bleed air temperature is regulated by a precooler, which uses the engine fan air modulated by the Fan Air Valve (FAMV) to cool the hot bleed air. The bleed system control functions are integrated with anti-ice and air conditioning functions through the AMS controller.

NORMAL OPERATION The Engine Bleed Valve is commanded open when the following conditions occur simultaneously: – Respective bleed switch is set to AUTO. – Respective engine bleed is available. – No fire is detected in the respective engine. – No bleed duct leak is detected. !Airplanes with AMS Black Label 13 and on

During single AMS pack operation with both bleed valves available, the engine bleed valve associated to the inoperative pack is commanded to close and the crossbleed valve is commanded to open. The EICAS message BLEED 1 (2) OFF is not displayed in this condition. "

ABNORMAL OPERATION

AOM-1502-003

The system will automatically shut down the affected bleed system by closing the engine bleed valves when a leak, overpressure or fail condition is identified.

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REVISION 21

Bleed Air System

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIR MANAGEMENT SYSTEM

APU BLEED The APU supplies bleed air on the ground or inflight. However, it is used primarily as a ground pneumatic source for the air conditioning packs (ECS) and engine starting. The APU Bleed Check Valve prevents engine bleed air from flowing to the APU when the engine bleed is the pneumatic source. The APU Bleed Valve (ABV) controls the APU bleed airflow to the pneumatic system. The APU Bleed Valve is commanded open when the following conditions occur simultaneously: – APU switch is set to AUTO. – APU Bleed is available. – No APU and left bleed duct leak. – Left engine bleed is unavailable. – Anti-ice system not requested (or anti-ice system requested ON and anti-ice system is failed).

CROSS BLEED (XBLEED) NORMAL OPERATION The cross bleed is commanded open when the XBLEED button is pushed in (AUTO) and any of the following conditions are met: – One side provides manifold pressure and there is not a bleed air source on the opposite side. – APU Bleed button pushed out for main engine start. – Engine #2 start in the air. – APU bleed OFF and engine #1 start in the air. – No bleed leak, unless starting an engine.

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Page 4

Bleed Air System

REVISION 21

AOM-1502-003

– Neither engine fire extinguishing handle has been pulled.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

ABNORMAL OPERATION The Engine Bleed #1 will be commanded closed if the cross bleed fails OPEN and the other bleed source is the #2 engine.

GROUND CONNECTION A dedicated high pressure Engine Start Ground Connection is available for engine starting and a low pressure Air Conditioned Ground Connection is available for air conditioning. Both pneumatic ground connection ports are located on the lower section of the fairing area of the airplane.

OVERHEAT DETECTION SYSTEM The Overheat Detection System (ODS) consists of overheat sensors and electronic control which provide rapid and reliable overheat and leak detection for the engine bleed, air conditioning ducts, APU bleed air distribution and anti-ice supply ducting. Normally the overheat sensors use dual loop sensing. In this configuration an overheat is indicated only when both loops detect an overheat condition.

AOM-1502-003

If a single loop fails, the remaining will monitor for an overheat condition (single loop operation).

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REVISION 21

Bleed Air System

Page 5

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIR MANAGEMENT SYSTEM

BLEED AIR DISTRIBUTION LEGEND RH WING

BLEED DUCTING ODS APU BLEED DUCT ODS BLEED 1 (LH) ODS BLEED 2 (RH) ODS LEFT WING ANTI−ICE ODS RIGHT WING ANTI−ICE ODS TRIM

PACK 2

EM170AOM140297D.DGN

PACK 1

LH WING

BLEED AIR DISTRIBUTION AND OVERHEAT DETECTION ZONES

OVERHEAT DETECTION ZONES

LEFT AIR SUPPLY RIGHT ANTI-ICE RIGHT AIR SUPPLY OPTIONAL TRIM SYSTEM

MONITORED AREA APU Bleed Duct Left slat anti-ice supply ducts Left bleed system ducts and left air conditioning ducts Right slat anti-ice supply ducts Right bleed system ducts and right air conditioning ducts Optional trim pressure ducts

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Bleed Air System

REVISION 21

AOM-1502-003

ZONE APU LEFT ANTI-ICE

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

BLEED SOURCE PRIORITIZATION The AMS controller automatically selects the bleed source on ground and during flight between the engines, the APU and the external connections. The selection is based on input from the flight deck control panel, takeoff data setting, engine status, APU status, flow demands, fault status, manifold pressures, and valve position switches. The AMS controller will choose one bleed source between the APU bleed and the engine bleeds when both are available. It is not possible to have both the APU and the engines as bleed sources simultaneously.

APU AS BLEED SOURCE While the airplane is on ground and the APU is on, the AMS gives priority to APU bleed supply when all of the following conditions are met: – The APU bleed and the cross bleed push buttons are set to AUTO. – The APU bleed valve and the cross bleed valve are operating normally. – Ground speed is below 50 kt and 30 s have passed after touchdown. – Either REF ECS is OFF and REF A/I is not ALL on the MCDU T/O DATA SET MENU page or the airplane is single engine taxiing. When all the conditions above are satisfied, the engine bleed valves are commanded closed (engine bleed unavailable) and the APU will supply bleed to both packs. If the ground speed exceeds 50 kt when taxiing only with the left engine, this engine will supply bleed to both packs. And if the ground speed exceeds 50 kt when taxiing only with the right engine, the APU and this engine will supply bleed for packs 1 and 2 respectively. The APU bleed cannot be used for the anti-ice system operation.

AOM-1502-003

During airborne engine start without Anti-Ice the left engine will be started with the opposite engine if the right bleed pressure is greater than the minimum required for engine start. The right engine will be started with the bleed source that is available at engine start (APU or left engine).

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REVISION 21

Bleed Air System

Page 7

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIR MANAGEMENT SYSTEM

ENGINE AS BLEED SOURCE The AMS gives priority to the Engine supply bleeds when the following conditions are simultaneously met, with the engine and APU bleed available simultaneously: – Engine bleed is available. – The XBLEED valve is operating normally. – ENG REF ECS is selected ON. During engine start with Anti-ice, the AMS controller will prioritize cross bleed start.

BLEED SOURCE PRIORITIZATION LOGIC The following tables describe bleed priority logic until liftoff. The logic considers bleed source availability, takeoff data setting on the MCDU, anti-ice requirements and the flight phase. The tables show the bleed valve position to identify the bleed source and the air conditioning availability according to the ECS and Anti-ice pre takeoff selection, APU bleed availability and the flight phase. NOTE: – No selection changes are evaluated. – Ice conditions are known and pre-selected. – APU bleed selection is retained until liftoff. MCDU T/O DATASET page Setting and APU bleed availability

1st engine start

ENG REF ECS

ENG REF ECS

ON

ON

ENG REF AI OFF

ENG REF AI OFF

APU bleed AUTO

APU bleed OFF

- EBV: closed

- EBV: closed

- EBV: closed

- EBV: closed

- ABV: open

- ABV: closed

- ABV: open

- ABV: closed

- Bleed Source:

- Bleed Source:

- Bleed Source:

- Bleed Source:

APU

GND Cart

APU

GND Cart

- PACKS OFF

- PACKS OFF

- PACKS OFF

- PACKS OFF

during eng start

with GND Cart

during eng start

with GND Cart

ON ENG REF AI ALL APU bleed AUTO

ON ENG REF AI ALL APU bleed OFF

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Bleed Air System

REVISION 21

AOM-1502-003

Flight Phase

ENG REF ECS

ENG REF ECS

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIR MANAGEMENT SYSTEM

MCDU T/O DATASET page Setting and APU bleed availability

Flight Phase

Taxi single engine

2nd engine start

Taxi with 2 engines

Takeoff

ENG REF ECS

ENG REF ECS

ON

ON

ENG REF AI OFF

ENG REF AI OFF

APU bleed AUTO

APU bleed OFF

- EBV: closed

- EBV: open

- EBV: closed

- EBV: open

- ABV: open

- ABV: closed

- ABV: open

- ABV: closed

- Bleed Source:

- Bleed Source:

- Bleed Source:

- Bleed Source:

APU

ENG

APU

ENG

- PACKS ON

- PACKS ON

- PACKS ON

- PACKS ON

- EBV: closed

- EBV: open

- EBV: closed

- EBV: open

- ABV: open

- ABV: closed

- ABV: open

- ABV: closed

- Bleed Source:

- Bleed Source:

- Bleed Source:

- Bleed Source:

APU

ENG

APU

ENG

- PACKS OFF

- PACKS OFF

- PACKS OFF

- PACKS OFF

during eng start

during eng start

during eng start

during eng start

- EBV: open

- EBV: open

- EBV: open

- EBV: open

- ABV: closed

- ABV: closed

- ABV: closed

- ABV: closed

- Bleed Source:

- Bleed Source:

- Bleed Source:

- Bleed Source:

ENG

ENG

ENG

ENG

- PACKS ON

- PACKS ON

- PACKS ON

- PACKS ON

- EBV: open

- EBV: open

ON ENG REF AI ALL APU bleed AUTO

ON ENG REF AI ALL APU bleed OFF

- EBV: open

- EBV: open

- ABV: closed

- ABV: closed

- ABV: closed

- ABV: closed

- Bleed Source:

- Bleed Source:

- Bleed Source:

- Bleed Source:

ENG

ENG

ENG

ENG

- PACKS ON

- PACKS ON

- PACKS ON

- PACKS ON

- SAI ON after

- SAI ON after

- EBV: open

- EBV: open

- ABV: closed

- ABV: closed

500 ft after takeoff - Bleed Source:

AOM-1502-003

ENG REF ECS

ENG REF ECS

- Bleed Source:

ENG

ENG

- PACKS ON

- PACKS ON

WSPEED40kt

WSPEED40kt

- EBV: open

- EBV: open

- ABV: closed

- ABV: closed

- Bleed Source:

- Bleed Source:

ENG

ENG

- PACKS ON

- PACKS ON

-SAI ON

-SAI ON

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REVISION 21

Bleed Air System

Page 9

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIR MANAGEMENT SYSTEM

MCDU T/O DATASET page Setting and APU bleed availability

1st engine start

Taxi single engine

2nd engine start

Taxi with 2 engines

OFF

OFF

ENG REF AI OFF

ENG REF AI OFF

APU bleed AUTO

APU bleed OFF

- EBV: closed

- EBV: closed

- EBV: closed

- EBV: closed

- ABV: open

- ABV: closed

- ABV: open

- ABV: closed

- Bleed Source:

- Bleed Source:

- Bleed Source:

- Bleed Source:

APU

GND Cart

APU

GND Cart

- PACKS OFF

- PACKS OFF

- PACKS OFF

- PACKS OFF

during eng start

with GND Cart

during eng start

with GND Cart

- EBV: closed

- EBV: open

- EBV: closed

- EBV: open

- ABV: open

- ABV: closed

- ABV: open

- ABV: closed

- Bleed Source:

- Bleed Source:

- Bleed Source:

- Bleed Source:

APU

ENG

APU

ENG

- PACKS ON

- PACKS ON

- PACKS ON

- PACKS ON

- EBV: closed

- EBV: open

- EBV: open

- EBV: open

- ABV: open

- ABV: closed

- ABV: closed

- ABV: closed

- Bleed Source:

- Bleed Source:

- Bleed Source:

- Bleed Source:

APU

ENG

ENG

ENG

- PACKS OFF

- PACKS OFF

- PACKS OFF

- PACKS OFF

during eng start

during eng start

during eng start

during eng start

- EBV: closed

- EBV: open

- EBV: open

- EBV: open

- ABV: open

- ABV: closed

- ABV: closed

- ABV: closed

- Bleed Source:

- Bleed Source:

- Bleed Source:

- Bleed Source:

APU

ENG

ENG

ENG

- PACKS ON

- PACKS ON

- PACKS ON

- PACKS ON

- EBV: open

- EBV: open

- EBV: open

- ABV: closed

- ABV: closed

- ABV: closed

- Bleed Source:

- Bleed Source:

- Bleed Source:

ENG

ENG

ENG

- PACKS OFF

- PACKS OFF

- PACKS OFF

during takeoff

during takeoff

during takeoff

- SAI ON after

- SAI ON after

WSPEED40kt

WSPEED40kt

- EBV: closed - ABV: open Takeoff

ENG REF ECS

ENG REF ECS

- Bleed Source: APU - PACKS ON

OFF ENG REF AI ALL APU bleed AUTO

OFF ENG REF AI ALL APU bleed OFF

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Bleed Air System

REVISION 21

AOM-1502-003

Flight Phase

ENG REF ECS

ENG REF ECS

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIR MANAGEMENT SYSTEM

MCDU T/O DATASET page Setting and APU bleed availability

Flight Phase

ENG REF ECS

ENG REF ECS

OFF

OFF

ENG REF AI OFF

ENG REF AI OFF

APU bleed AUTO

APU bleed OFF

- EBV: open

- EBV: open

- ABV: closed

- ABV: closed

AOM-1502-003

500 ft after takeoff - Bleed Source:

- Bleed Source:

ENG

ENG

- PACKS ON

- PACKS ON

ENG REF ECS OFF ENG REF AI ALL APU bleed AUTO

ENG REF ECS OFF ENG REF AI ALL APU bleed OFF

- EBV: open

- EBV: open

- ABV: closed

- ABV: closed

- Bleed Source:

- Bleed Source:

ENG

ENG

- PACKS ON

- PACKS ON

-SAI ON

-SAI ON

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REVISION 21

Bleed Air System

Page 11

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

AIRPLANE OPERATIONS MANUAL

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Bleed Air System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

ENVIRONMENTAL CONTROL SYSTEM GENERAL The Environmental Control System (ECS) provides pressurized and conditioned air for the flight deck and passenger cabin, filtered cabin air recirculation, conditioned air supply for gaspers, fan air cooling for avionics and emergency ram air ventilation for flight deck smoke clearance. The ECS can also provide cargo bay ventilation. The cargo bay ventilation system is optional.

AIR CONDITIONING PACKS Two ECS cooling packs are installed in the wing-to-fuselage fairings. The AMS controller sets the bleed airflow to each pack independently, through the respective pack flow control valve (FCV). Each engine normally supplies bleed air to the respective pack. A single pack is capable of keeping adequate cabin/cargo hold pressurization and temperature. Single engine bleed can supply both ECS packs using the cross bleed.

CABIN AIR DISTRIBUTION During normal operation, pack 1 adjusts the airflow and flight deck temperature according to the CKPT temperature selector knob position. Pack 2 adjusts the airflow to control passenger cabin temperature according to PAX CABIN selector knob position.

SINGLE PACK OPERATING INFORMATION When operating with a single air conditioning pack, the zone related to the disabled pack will receive air from the operational pack through the mixer. The temperature selector knob associated with the disabled pack will have no effect on the temperature of the disabled pack zone.

AOM-1502-003

In order to improve cabin temperature control, keep the operative temperature selector knob at 12 o‘clock position when on ground. During climb, keep the operative temperature selector knob between 12 and 14 o’clock position. During cruise, make slight temperature changes as required, observing 10 min interval between selections. During descent, increase the temperature of the operative selecting knob between 14 and 16 o’clock position to compensate the reduced airflow to the cabin. Monitor cabin temperature and, if necessary, make slight adjustments,

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REVISION 18

Air Conditioning System

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIR MANAGEMENT SYSTEM

respecting the 10 min interval among them for system stabilization.

GASPER VENTILATION The gasper air distribution system provides air to each pilot and passenger position. Air flowing from the mixing manifold through the gasper check valve supplies the gasper ventilation system. When the gasper valve is opened, air from the right recirculation fan supplies the gasper system. During normal system operation the gasper shutoff valve remains closed. It automatically opens whenever the gasper air supply exceeds 35°C (95°F). This prevents hot air from blowing on the passengers during cabin heating.

RECIRCULATION FANS Recirculated air from the passenger cabin and cockpit is ducted to the mixing manifold via two recirculation fans located in the pressurized section of the airplane. The recirculation fans draw air from the recirculation bays and impel the air back into the flight deck and cabin distribution system. The total flow entering the cockpit and the passenger cabin is made up of approximately 52% of fresh air and 48% of recirculation air.

NORMAL OPERATION Recirculation fans are automatically ON during ground and in flight. On hot and humid days, with doors opened, the recirculation fans may be switched OFF to avoid fog in the cockpit.

ABNORMAL OPERATION The recirculation fans are commanded OFF when: – Both packs are commanded OFF; – During on ground, cabin warm-up mode with the APU as bleed source according to a function of ambient temperature and altitude; – The cargo bay fire signal activates;

– Smoke is detected in the recirculation bay.

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Page 2

Air Conditioning System

REVISION 18

AOM-1502-003

– The DUMP button is pressed;

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

ELECTRONIC COMPARTMENTS VENTILATION FORWARD ELECTRONIC BAY (E-BAY) The forward e-bay ventilation consists of three fans, which provide forced cooling air for # 1 Secondary Power Distribution Assembly (SPDA 1), Emergency Integrated Control Center (EICC) and all other avionics located in this e-bay. The fans draw air from the cockpit and expel air toward the underfloor recirculation bay. A flow sensor is used for fan/flow health monitoring.

CENTER ELECTRONIC BAY (E-BAY) The center e-bay ventilation consists of three fans, which provide forced cooling air for the center e-bay electronics, Left Integrated Control Center (LICC), Right Integrated Control Center (RICC) and SPDA 2. The fans draw air from the rear cabin return and expel it towards the underfloor recirculation bay. Flow sensors are used for fans/flow health monitoring.

AFT ELECTRONIC BAY (E-BAY) Forced cooling is not necessary in the aft e-bay and, therefore, no fan is installed in this compartment. Air flowing from passenger cabin provides cooling of the aft e-bay and is expelled towards the underflow recirculation bay.

FORWARD CARGO BAY VENTILATION

AOM-1502-003

The ECS provides ventilation for live animals in the forward cargo bay. This optional system contains a fan on the side of the bay which provides underfloor recirculation air into the bay. The system also contains a shutoff valve at the outlet of the bay that closes in the event of fire and thus preventing halon from leaving the bay. In addition, in the event of fire, the forward cargo compartment fan is commanded OFF, thus closing the check valve and preventing halon from entering the cabin.

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REVISION 18

Air Conditioning System

Page 3

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

AIRPLANE OPERATIONS MANUAL

EMERGENCY RAM AIR VENTILATION Emergency ram air ventilation is provided in case of pack shutdown or for smoke removal. The flight deck pack emergency ram air ventilation valve is commanded OPEN only if both ECS cooling packs are commanded OFF or failed OFF and the plane’s altitude is less than 25000 ft. An emergency ram air ventilation check valve is provided and does not require electronic control. The emergency ram air check valve will be open whenever the pressure in the ram air circuit is greater than cabin pressure. During smoke removal, both ECS cooling packs will be commanded OFF and therefore, the flight deck emergency ram air ventilation valve will be commanded OPEN.

RAM AIR INLET DOOR

!Airplanes equipped with Ram Air Inlet Door

The Ram Air Inlet Door (RAID) modulates and optimizes the quantity of ram air sent to the packs through changes in the door deflection. This modulation decreases drag and fuel consumption. The AMS controller controls the RAID mechanism, which is installed in the wing-to-fuselage fairing. There is one mechanism for each RAID. The ram air inlet area with the RAIDs fully open is equivalent to the inlet area without the RAIDs. The AMS controller commands the two RAIDs to OPEN when one of the following conditions occur: – Airplane is on ground and until 17500 ft during the climb phase. – Airplane is below 17000 ft during descent. – Pressurization Dump Button is activated. – RAT is deployed. – Anti-ice system is activated.

– Related ECS pack is commanded OFF by automatism or manual pilot command.

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Air Conditioning System

REVISION 18

AOM-1502-003

The AMS controller commands one of the RAIDs to OPEN when one of the following conditions occur: – Related ECS pack failure.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

The AMS controller commands the two RAIDs to CLOSE when all of the following conditions occur: – Airplane is on ground. – Ground speed is less than 50 KIAS. – ECS packs 1 and 2 are detected OFF by the AMS controller. – Pack 1 and 2 buttons are selected OFF on the overhead panel. – The Pressurization Dump Button is not activated. In flight, a RAID failure when it is more than 90% CLOSED causes the EICAS message PACK 1 (2) FAIL. A RAID failure when it is more than 10% OPEN causes the EICAS message RAM AIR FAULT only after landing. On ground, a RAID failure when it is more than 90% CLOSED causes the two EICAS messages PACK 1 (2) FAIL and RAM AIR FAULT. A RAID failure when it is more than 10% OPEN causes the EICAS message RAM AIR FAULT.

AOM-1502-003

"

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REVISION 18

Air Conditioning System

Page 5

Page 6

Copyright © by Embraer. Refer to cover page for details.

14-02-15

Air Conditioning System

REVISION 18

AOM-1502-003

FLOW SENSOR

E−ICC

FWD CARGO

RETURN AIR

SHUTOFF VALVE

OFV SMOKE DETECTOR

FLOW SENSOR CENTRAL E−BAY

L−ICC

AFT CARGO

RETURN AIR

STATIC PRESSURE PORT

POSITIVE PRESSURE RELIEF VALVE (SAFETY VALVE)

AFT E−BAY

AIR MANAGEMENT SYSTEM

EM170AOM140298B.DGN

FWD E−BAY

COCKPIT FLOW

RECIRCULATION BAY

NEGATIVE PRESSURE RELIEF VALVE

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ECS DISTRIBUTION

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

AMS AUTOMATION AMS Controller functional logic provides automatic control of engine bleed, APU bleed, ECS packs, Anti-Ice systems, Pressurization and recirculation bay smoke detection according to the airplane’s operation and condition.

ECS PACKS LOGIC An ECS pack is OFF when its associated pack flow control valve (FCV) is closed. The ECS packs 1 or 2 are OFF if any of the following conditions occur: – Bleed air source is NOT available for the pack; – The associated Pack push button is OFF on the overhead panel; – Any engine is starting and there is weight-on-wheels (both packs OFF); – The associated engine is starting, there is no weight-on-wheels and the opposite engine is not starting; – Any engine is starting AND APU is the bleed source (both packs OFF); – Associated bleed system duct leak; – Associated packs BIT shutdown failures are present (PACK 1(2) FAIL EICAS message displayed); – Ram air valve BIT is running (Pack 1 OFF). !Airplanes with MAU Load 25.4 or airplanes Pre-Mod MAU Load 25.3

AOM-1502-003

NOTE: According to the logic implemented on Black Label Software version 9.0 and on, the Emergency Ram Air Valve Built-In Test (BIT) initiates during the first engine start procedure, commands Pack 1 OFF and takes 1.5 min to be completed. Considering that, when REF ECS is selected ON in the MCDU T/O DATASET MENU page, and both engines start are completed before 1.5 min, the FADEC identifies a discrepancy between actual Packs configuration (Pack 1 OFF) and the one selected on the MCDU (REF ECS ON requires both Packs ON). As a result, the EICAS message ENG REF ECS DISAG is temporarily displayed until the Emergency Ram Air Valve Built-In Test is completed and both Packs are ON. "

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REVISION 18

Air Conditioning System

Page 7

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

AIRPLANE OPERATIONS MANUAL

!Airplanes equipped with Ram Air Inlet Door

– Above 17500 ft, with a RAID failure when it is more than 90% CLOSED and the other ECS pack ON, regardless of the Mach number; – Below 17500 ft, with a RAID failure when it is more than 90% CLOSED. In this case, the two ECS packs are commanded OFF. As a result, the two RAIDs and the emergency ram air ventilation valve are commanded OPEN. Above 17500 ft and Mach number higher than 0.65, after a RAID failure when it is more than 35% OPEN, the related ECS pack is not shut down. After a RAID failure when it is more than 10% OPEN, the related ECS pack is not shut down, regardless of the altitude value. "

FADEC ECS OFF SIGNAL The FADEC may send an ECS OFF signal to the AMS controller, requesting that no bleed is extracted from the engine for the air-conditioning system. The FADEC sets this signal depending on the T/O DATASET input (REF ECS OFF), pressure altitude, flight phase, and engine inoperative detection. The AMS controller disregards the ECS OFF signal when the airplane is above 15000 ft. The ECS OFF signal CLOSES the packs during takeoff if any of the following conditions occur: – One engine inoperative and APU bleed is not available; – Thrust levers set to MAX position and APU bleed is not available; – T/O DATASET REF ECS set to OFF on the MCDU and APU bleed is not available; – T/O DATASET REF ECS set to OFF and T/O DATASET REF A/I set to ALL on the MCDU. The ECS OFF signal CLOSES both packs during go-around if any of the following conditions occur: – One engine inoperative and APU bleed is not available up to 9700 ft;

– Thrust levers set to MAX position and Wing Ice Protection System is requested ON.

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Air Conditioning System

REVISION 18

AOM-1502-003

– Thrust levers set to MAX position and APU bleed is not available;

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

The packs are commanded ON if any of the following conditions occur: – Thrust lever reduction below TO/GA; – The airplane is taking off with two engines operating 500 ft above takeoff field altitude; – The airplane is above 9700 ft, for takeoff fields at 8000 ft or below and one engine inoperative; – The airplane is above 15000 ft, for takeoff fields above 8000 ft and one engine inoperative;

AOM-1502-003

– The airplane is above 9700 ft during go around, in case one engine is inoperative.

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REVISION 18

Air Conditioning System

Page 9

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

AIRPLANE OPERATIONS MANUAL

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Air Conditioning System

REVISION 18

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

CABIN PRESSURE CONTROL SYSTEM GENERAL The Cabin Pressure Control System (CPCS) controls cabin pressurization and provides maximum safety and comfort during every segment of flight and ground operations. The CPCS operates in automatic and manual modes. Normal operation of the CPCS is automatic. The system consists of:

• • • • •

Cabin pressure controller (CPC). One cabin outflow valve (OFV). One negative pressure relief valve (NPRV). One positive pressure relief valve (Safety valve). Static Pressure Port.

SYSTEM COMPONENTS CABIN PRESSURE CONTROLLER (CPC) The basic function of the controller is to control cabin pressure by commanding the outflow valve to modulate airflow through the valve from the pressurized airplane volume to the surrounding environment. The CPC has two fully independent automatic channels, which are alternated following each flight. Both channels provide a manual function as backup, enabling the crew to control cabin pressure by directly actuating the outflow valve (OFV) position.

OUTFLOW VALVE (OFV)

AOM-1502-003

The outflow valve modulates airflow from the pressurized cabin into surrounding environment. It can be modulated automatically or manually.

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REVISION 21

Pressurization System

Page 1

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

AIRPLANE OPERATIONS MANUAL

NEGATIVE PRESSURE RELIEF VALVE (NPRV) The negative pressure relief valve is a spring loaded check valve that works without any electrical power, and is independent of the CPCS. Its function is to protect the airplane structure against damages due to a negative differential pressure. The negative pressure relief valve opens if differential pressure between cabin and surrounding environment exceeds-0.5 psi.

POSITIVE PRESSURE RELIEF VALVE (SAFETY VALVE) The positive pressure relief valve is a spring loaded check valve that works without any electrical power, and is independent the CPCS. Its function is to protect the airplane’s structure against damage due to positive overpressure. In case of outflow valve failure, the positive pressure relief valve opens if the pressure differential between cabin and surrounding environment exceeds 8.6 psi.

STATIC PRESSURE PORT The static pressure port senses the environmental static pressure and mechanically transmits it to the positive pressure relief valve in order to allow the overpressure relief device to work.

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Pressurization System

REVISION 21

AOM-1502-003

The static port is electrically heated to assure there are no obstructions of sensing orifices due to ice accumulation.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

OPERATING MODES The CPCS can be operated in automatic and manual mode.

AUTOMATIC MODE The CPCS automatic operation uses different information inputs from the airplane to control the cabin altitude, the differential pressure and the cabin altitude rate of change. In the automatic mode the information required for the CPCS operation can be retrieved from the FMS or, if the FMS data is not available, it can be manually set by the pilot. The CPCS internal logic is divided in flight modes to better control the cabin altitude change rate in accordance with the flight phase. A high altitude takeoff and landing is also supported automatically by the system. The automatic mode incorporates logic for dumping the airplane pressure with a minimal pilot workload. AUTOMATIC OPERATION WITH FMS DATA AVAILABLE The CPCS uses the gross weight, the cruise altitude set by the pilot and the landing field elevation retrieved from the FMS data base to schedule the target cabin altitude and the cabin pressure variation rate. – LANDING FIELD ELEVATION: It is retrieved from the FMS data base after the input of a destination on the active flight plan. In this case the landing field elevation is shown green on EICAS. – CRUISE ALTITUDE: It is set on PERFORMANCE INIT page 3/3 > INIT CRZ ALT. Changing the cruise altitude in flight requires an update on FMS cruise altitude to readjust the pressurization schedule of operation. – GROSS WEIGHT: The airplane gross weight is retrieved after the confirmation of the inputs on the PERFORMANCE INIT page 3/3. AUTOMATIC OPERATION WITH FMS DATA NOT AVAILABLE

AOM-1502-003

If any FMS data is not available, the CPCS is still capable of automatic operation: – LANDING FIELD ELEVATION:

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REVISION 21

Pressurization System

Page 3

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

AIRPLANE OPERATIONS MANUAL

If not available from the FMS data base, LFE must be manually selected on the pressurization panel by the pilot. In this case the landing field elevation is shown in cyan. A default value of 8000 ft is used if no input is made on LFE. – CRUISE ALTITUDE: If it is not possible to enter the cruise altitude on the FMS, the cabin pressure schedule is calculated based on the ambient pressure. – GROSS WEIGHT: If the gross weight is not available from the FMS the CPCS uses a default value to determine the CABIN ALTITUDE RATE OF VARIATION. DIFFERENTIAL PRESSURE SCHEDULE Two nominal differential pressures are provided by the CPCS: – If the FMS cruise flight level is set below 37000 ft the nominal differential pressure of up to 7.8 psi is used. – If either the FMS cruise flight level is set higher than 37000 ft or the airplane is actually flying above 37000 ft the nominal differential pressure switches to up to 8.4 psi. NOTE: The nominal differential pressure of up to 7.8 psi was specified in order to reduce fatigue and structural stress during flight. Selecting a cruise altitude in the FMS higher than the actual airplane altitude may unnecessarily stress the airplane structure with a higher differential pressure. HIGH ALTITUDE OPERATION The CPCS automatically identifies when the airplane is operating in airports above 8000 ft. If the operation is at an airport above 9400 ft , the “CABIN ALTITUDE HI” EICAS message trigger point is automatically adjusted to a plus of 500 ft AGL. There is no special procedure for the high altitude operation. DUMP FUNCTION This function is used in the event of emergency evacuation, smoke evacuation or for fast cabin depressurization. The DUMP function is activated pushing in the DUMP button on the pressurization panel.

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Page 4

Pressurization System

REVISION 21

AOM-1502-003

MODE ACTIVATION

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

SYSTEM OPERATION The CPCS system automatically: – Sets the ECS packs and recirculation fans to OFF; – Controls the OUT FLOW VALVE to maintain the cabin altitude rate of climb at 2000 ft/min up to 12400 ft. – When the cabin altitude reaches 12400 ft it commands the OUT FLOW VALVE full closed. From this point the cabin altitude rises by natural leak. If the cabin altitude is above 12400 ft when the dump is activated, the cabin altitude may be rising due to a normal leak. To achieve a higher rate of climb the manual mode can be used. DUMP MODE DEACTIVATION Pushing out the DUMP button commands the system back to normal operation opening the ECS packs and turning on the recirculation fan.

MANUAL MODE MODE ACTIVATION The manual mode is activated rotating the pressurization mode selector knob to the MAN position. When manual mode is selected, both channels of the CPCS controller revert to standby state, but only one channel performs the manual operation. The channel selection is automatic. SYSTEM OPERATION With the pressurization system in manual mode the pilot is responsible to open or close the OUT FLOW VALVE to maintain the desired cabin altitude. NOTE: In manual mode there is no automatic depressurization on the ground (after landing).

cabin

AOM-1502-003

The Dump Function is not available in Manual Mode. However, if the associated push button is pushed in, both recirculation fan and packs are turned to off.

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REVISION 21

Pressurization System

Page 5

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIR MANAGEMENT SYSTEM

CPCS FLIGHT MODES The CPCS automatic mode splits a typical flight into different CPCS flight modes. Information from engine N2, landing gear status, FADEC, ADC and FMS are used within the cabin pressure controller to determine the current flight mode. The system calculates a target cabin pressure from the outside pressure, the maximum differential pressure limiter and a corresponding pressure rate of variation data for each of the following CPCS flight modes: • GROUND

• • • • • • •

TAXI TAKEOFF CLIMB CRUISE DESCENT GROUND ABORT.

The CPCS sequences the flight modes in the order presented here. During flight mode transitions, or thrust lever transitions, higher rates of pressure change might occur for a few seconds. During these transitions, the cabin pressure rate might be approximately twice as defined at each flight mode, for a maximum of 5 s, but still being under comfort recommendations.

GROUND MODE MODE ACTIVATION: – Weight on wheels status on ground and; – Engines running below the takeoff thrust. SYSTEM OPERATION – OFV - is set fully open;

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Page 6

Pressurization System

REVISION 21

AOM-1502-003

– CABIN PRESSURE - is set to 0.01 psid lower than ambient pressure (causing a permanent command to position the OFV in the fully open position);

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

– CABIN ALTITUDE CHANGE RATE - the system internal range is between 500 ft/min and -300 ft/min.

TAXI MODE MODE ACTIVATION: This mode is a sequence from the GROUND mode. Starting the engines with the doors closed cause the CPCS to activate momentarily the GROUND mode and switch to TAXI mode. – Weight on wheels status on ground; – Doors closed and; – Engines running at 60% N2 or higher. SYSTEM OPERATION During the TAXI mode, the CPCS starts the first pre-pressurization step, increasing the differential pressure. – CABIN PRESSURE - is set to the ambient pressure plus an offset of 0.11 psid. – CABIN ALTITUDE CHANGE RATE - the system internal range is ±300 ft/min.

TAKEOFF MODE MODE ACTIVATION – Weight on wheels status on ground and; – Engines running at takeoff thrust. SYSTEM OPERATION – CABIN PRESSURE - is set to 0.15 psid above the ambient pressure.

AOM-1502-003

– CABIN ALTITUDE CHANGE RATE - the system internal range is 500 ft/min and -400 ft/min.

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REVISION 21

Pressurization System

Page 7

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

AIRPLANE OPERATIONS MANUAL

CLIMB MODE MODE ACTIVATION – Weight on wheels status in flight. SYSTEM OPERATION The Climb mode operation varies depending on the availability of the cruise flight level in the FMS:

•

CRUISE FLIGHT LEVEL DATA AVAILABLE IN THE FMS: – CABIN ALTITUDE CHANGE RATE - The CPCS calculates the most comfortable rate of climb according to the cruise altitude set in the FMS. The rate of climb is calculated depending on the airplane gross weight and the ambient pressure at the takeoff field. The system internal range is limited to +750 ft/min for increasing cabin altitude and constant at -600 ft/min for decreasing cabin altitude. In case a step climb is performed, the cabin altitude will continuously increase even at the level off altitude until the airplane reaches the target cruise altitude set in the FMS.

•

CRUISE FLIGHT LEVEL DATA NOT AVAILABLE IN THE FMS: – CABIN ALTITUDE CHANGE RATE - The target cabin altitude is calculated depending on the ambient pressure. The system internal range is +750 ft/min and -500 ft/min constant rates. In case a step climb is performed, the cabin altitude will stop increasing during level off and it will continue increasing after climb is resumed.

CRUISE MODE MODE ACTIVATION The CRUISE mode is set when the airplane reaches the cruise flight level set in the FMS or, if no flight level is set in the FMS, when the airplane stops climbing. SYSTEM OPERATION CABIN PRESSURE – If the FMS cruise altitude is set below 37000 ft the nominal differential pressure is set to a maximum of 7.8 psid and at 37000 ft the cabin altitude will be 8000 ft.

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Pressurization System

REVISION 21

AOM-1502-003

•

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

– If either the FMS cruise altitude is set higher than 37000 ft or the airplane is actually flying above 37000 ft the nominal differential pressure is set to a maximum of 8.4 psid. According to the CPCS logic, when transitioning to a cruise altitude above 37000 ft, the differential pressure adjustment to a maximum of 8.4 psid may cause the cabin altitude to decrease below 8000 ft so that it will reach 8000 ft when the airplane is at a cruise altitude of 41000 ft. If no cruise flight level is available on the FMS the target cabin altitude depends on the ambient pressure and the differential pressure from climb mode.

•

CABIN ALTITUDE CHANGE RATE - the system internal range is +500 ft/min and -300 ft/min.

DESCENT MODE MODE ACTIVATION The DESCENT mode is set when the airplane starts a descent after CRUISE mode activation. – CABIN PRESSURE - the target cabin altitude during descent mode is the Landing Field Elevation. It can be automatically retrieved from the FMS data base or manually set by the pilot.

AOM-1502-003

– CABIN ALTITUDE CHANGE RATE - the altitude rate of change depends on the airplane descent rate, cabin pressure, landing field pressure and ambient pressure. The systems internal range is -200 ft/min and -750 ft/min. If the cabin altitude is below the landing field altitude the increase rate depends on the cabin pressure, landing field pressure and ambient pressure and is calculated within the range of +300 ft/min and +750 ft/min.

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REVISION 21

Pressurization System

Page 9

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

AIRPLANE OPERATIONS MANUAL

ABORT MODE MODE ACTIVATION The ABORT mode is set when:

•

The airplane stops climbing and immediately starts descending (no cruise mode activated).

•

Pressure altitude is less than 10000 ft or the airplane is less than 5000 ft above takeoff field elevation.

SYSTEM OPERATION – CABIN PRESSURE - the cabin altitude is scheduled back to the takeoff altitude.

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Pressurization System

REVISION 21

AOM-1502-003

– CABIN ALTITUDE CHANGE RATE - the climb mode is used in reverse direction. The system internal range is +500 ft/min and -600 ft/min.

AOM-1502-003

REVISION 21

Pressurization System

EM170AOM140374D.DGN

· LANDING GEAR EXTENDED · NO TAKEOFF THRUST

GROUND

· DOORS CLOSED · BOTH ENGINES N2 ABOVE 60%

TAXI

CPCS FLIGHT MODES

· LANDING GEAR EXTENDED · TAKEOFF THRUST

TAKEOFF

· LANDING GEAR RETRACTED

CLIMB

· CRUISE FLIGHT LEVEL · STOP CLIMBING

CRUISE

· START DESCENT (AFTER CRUISE)

DESCENT

AIRPLANE OPERATIONS MANUAL SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

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14-02-20

Page 11

Page 12

Pressurization System

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14-02-20

REVISION 21

AOM-1502-003

EM170AOM140375C.DGN

· DOORS CLOSED · BOTH ENGINES N2 ABOVE 60%

TAXI

· LANDING GEAR EXTENDED · TAKEOFF THRUST

TAKEOFF

· LANDING GEAR RETRACTED

CLIMB

· START DESCENT (BEFORE CRUISE) · BELOW 10000 ft · UP TO 5000 ft TAKEOFF FIELD

ABORT

AIR MANAGEMENT SYSTEM

· LANDING GEAR EXTENDED · NO TAKEOFF THRUST

GROUND

CPCS ABORT MODE

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

EICAS MESSAGES TYPE

WARNING

AOM-1502-003

CAUTION

MESSAGE CABIN ALTITUDE HI

MEANING Cabin altitude is 9700 ft or higher, or if cabin altitude is higher than +500 ft above LFE for LFE higher than 9400 ft. AMS CTRL FAIL Both AMS controller channels have failed. AMS controller is not in control BLEED 1 (2) FAIL A bleed failure has been detected. Bleed is no longer available. BLEED 1 (2) LEAK An overheat condition has been detected at the associated bleed system or pack. BLEED APU LEAK An overheat condition has been detected in the APU bleed or both APU overheat detection system loops have failed. BLEED 1 (2) An overpressure condition OVERPRESS has been detected at the associated bleed system or pack. CABIN DIFF PRESS FAIL Cabin differential pressure is higher than 8.5 psid or lower than -0.3 psid.

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REVISION 18

EICAS Messages

Page 1

AIR MANAGEMENT SYSTEM

TYPE

AIRPLANE OPERATIONS MANUAL

MESSAGE CENTER E-BAY FANS FAIL CRG FWD VENT FAIL

FWD E-BAY FANS FAIL PACK 1 (2) FAIL

CAUTION PACK 2 LEAK

PRESN AUTO FAIL

PRESN MAN FAIL

RECIRC SMK DET FAIL RECIRC SMOKE

MEANING Center E-BAY fans have failed. Forward cargo fan has failed ON or if the cargo shutoff valve is failed OPEN associated with smoke detected in the cargo compartment. Forward e-bay fans have failed. Associated pack is no longer available. For airplanes equipped with Ram Air Inlet Door (RAID): when the RAID fails when it is more than 90% CLOSED. An overheat condition has been detected at the pack 2 optional trim air ducts. Both pressurization controller channels have failed in the automatic mode. Both pressurization controller channels have failed in the manual mode. Smoke detector has failed. Smoke has been detected in the recirculation bay.

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Page 2

EICAS Messages

REVISION 18

AOM-1502-003

SYSTEMS DESCRIPTION

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL TYPE

MESSAGE AMS CTRL FAULT

BLEED 1 (2) OFF PACK 1 (2) OFF PRESN AUTO FAULT

RAM AIR FAULT

ADVISORY

XBLEED FAIL

XBLEED SW OFF

AOM-1502-003

STATUS

BLEED APU VLV OPEN

AIR MANAGEMENT SYSTEM

MEANING One of the two AMS controller channels has failed. Associated bleed is turned off. Associated pack is off in flight. Loss of automatic mode redundancy. One CPCS controller channel has failed. Forward emergency ram valve has failed closed. For airplanes equipped with Ram Air Inlet Door (RAID): on ground, when the RAID fails when it is more than 10% OPEN, or more than 90% CLOSED. Either bleed isolation valve has failed closed and cross bleed is no longer available, or the bleed isolation valve failed open and engine is the source for the right side bleed (Bleed 2). Bleed isolation button has been pushed out. APU bleed valve is commanded open.

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REVISION 18

EICAS Messages

Page 3

SYSTEMS DESCRIPTION AIR MANAGEMENT SYSTEM

AIRPLANE OPERATIONS MANUAL

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Page 4

EICAS Messages

REVISION 18

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

SECTION 14-03 AUTOMATIC FLIGHT TABLE OF CONTENTS

AOM-1502-003

Block

Page

General Description............................................. 14-03-01 .... GENERAL DESCRIPTION..................................... 14-03-01 ....

1 1

Controls and Indications..................................... 14-03-05 .... GUIDANCE PANEL................................................ 14-03-05 .... LATERAL GUIDANCE CONTROLS...................... 14-03-05 .... VERTICAL GUIDANCE CONTROLS..................... 14-03-05 .... AFCS GUIDANCE CONTROLS............................ 14-03-05 .... SPEED AND MODE CONTROLS......................... 14-03-05 .... AUTOPILOT/FD TCS BUTTON............................. 14-03-05 .... AUTOPILOT QUICK DISCONNECT BUTTON...... 14-03-05 .... AUTOTHROTTLE DISCONNECT AND GO AROUND BUTTONS....................................... 14-03-05 .... AUTOTHROTTLE ANNUNCIATIONS ON FMA..... 14-03-05 .... AUTOPILOT ANNUNCIATIONS ON FMA............. 14-03-05 .... LATERAL MODE ANNUNCIATIONS ON FMA...... 14-03-05 .... VERTICAL MODE ANNUNCIATIONS ON FMA.... 14-03-05 .... APPROACH STATUS ANNUNCIATIONS ON FMA.................................................................. 14-03-05 ....

1 1 2 4 6 8 9 10 11 12 13 14 15 16

Flight Guidance Control System........................ 14-03-10 .... 1 AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS)............................................................. 14-03-10 .... 1 FLIGHT DIRECTOR (FD)...................................... 14-03-10 .... 1 AUTOPILOT (AP)................................................... 14-03-10 .... 2 YAW DAMPER....................................................... 14-03-10 .... 4 AFCS INDICATIONS ON PFD............................... 14-03-10 .... 6 FGCS LATERAL MODES...................................... 14-03-10 .... 8 FGCS VERTICAL MODES.................................... 14-03-10 .... 11 ILS APPROACH..................................................... 14-03-10 .... 27 PREVIEW FEATURE............................................. 14-03-10 .... 34

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REVISION 20

Table of Contents

Page 1

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

Block Page Thrust Management............................................. 14-03-20 .... 1 THRUST MANAGEMENT SYSTEM...................... 14-03-20 .... 1 AUTOTHROTTLE.................................................. 14-03-20 .... 1 TLA TRIM............................................................... 14-03-20 .... 7 THRUST RATING SELECTION............................. 14-03-20 .... 8 1 1

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Page 2

Table of Contents

REVISION 20

AOM-1502-003

EICAS Messages.................................................. 14-03-30 .... EICAS MESSAGES............................................... 14-03-30 ....

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

GENERAL DESCRIPTION

AOM-1502-003

The Automatic Flight Control System (AFCS) is an integrated system that processes inputs from several airplane systems and sensors. The AFCS supplies this data to the Flight Guidance Control System (FGCS) and Thrust Management System (TMS), thus enabling their operation and producing visual and aural information.

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REVISION 9

General Description

Page 1

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

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Page 2

General Description

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AUTOMATIC FLIGHT

GUIDANCE PANEL The Guidance Panel (GP) provides means for selecting functions and modes as follows: – Lateral Guidance Control. – AFCS Management Control. – Vertical Guidance Control. The GP contains two independent channels (A and B), each one providing independent communication to the FGCS.

GLARESHIELD PANEL

VS FD

NAV

HDG

AP

CRS

APP

HDG

YD

A/T

ALT

FPA

ALT SEL

FPA SEL

VNAV

DN

VS

FD

SPEED MAN

CRS

FLCH BANK PUSH DIR

SRC PUSH FT−M

PUSH SYNC

AOM-1502-003

PUSH IAS−MACH

UP

PUSH DIR

EM170AOM140055.DGN

FMS

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REVISION 21

Controls and Indications

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AUTOMATIC FLIGHT

LATERAL GUIDANCE CONTROLS MAIN PANEL

1 2 NAV

HDG

APP

HDG SEL

3 4

BANK PUSH SYNC

EM170AOM140262.DGN

5

1 - NAV BUTTON According to the presentation selected for the CDI the NAV Button engages: – LOC: if the CDI is selected V/L (Green) and the source ILS frequency is tuned. – LNAV: if the CDI is selected FMS (Magenta). Pressing NAV with LOC or LNAV engaged reverts the lateral guidance to ROLL. 2 - HDG BUTTON – Selects and deselects the heading select mode.

– Manually selects the desired heading.

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Page 2

Controls and Indications

REVISION 21

AOM-1502-003

3 - HDG SELECTOR KNOB

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

– Pressing this knob synchronizes the heading select to the current heading. 4 - BANK BUTTON !Pre-mod MAU load 27.1

– Enables and disables bank angle limit of 17° used by the Heading Mode. "

5 - APP BUTTON – Arms, activates, or deactivates approach modes based on the navigation source displayed on the respective PFD. For example, the following lateral and vertical mode annunciations are displayed on the FMA after the APP button is pressed: – LOC and GS for the ILS approach mode.

AOM-1502-003

– LNAV and GP for theVGP approach mode. The Autopilot Approach Status Annunciator displays the engaged approach mode.

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REVISION 21

Controls and Indications

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AUTOMATIC FLIGHT

VERTICAL GUIDANCE CONTROLS MAIN PANEL

3

4

5

6

7

2 VS VNAV

ALT

FPA

ALT SEL

FPA SEL

DN

VS

EM170AOM140260.DGN

FLCH

1

UP

PUSH FT−M

8

1 - FLCH BUTTON – Selects and deselects the Flight Level Change mode. 2 - VNAV BUTTON – Selects and deselects the VNAV mode (FMS vertical navigation). 3 - ALT BUTTON – Selects and deselects the altitude holding mode (ALT). 4 - ALT SELECTOR KNOB – Selects the desired altitude.

– Counter clockwise rotation: decreases the altitude target.

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Page 4

Controls and Indications

REVISION 21

AOM-1502-003

– Clockwise rotation: increases the altitude target.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

– Pressing this knob displays on the PFD the following altitudes, in meters: – The selected altitude, above the selected altitude readout window. – The actual airplane altitude, above the altitude rolling digits readout window. 5 - FPA BUTTON – Selects and deselects the Flight Path Angle mode. 6 - FPA SELECTOR KNOB – Manually selects the desired Flight Path Angle. 7 - VS BUTTON – Selects and deselects the Vertical Speed mode. 8 - VS THUMB WHEEL SELECTOR – The thumb wheel selector manually selects the desired vertical speed rate. – Rolling the wheel upward selects the desired rate of descent.

AOM-1502-003

– Rolling the wheel downward selects the desired rate of climb.

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REVISION 21

Controls and Indications

Page 5

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AUTOMATIC FLIGHT

AFCS GUIDANCE CONTROLS MAIN PANEL

1

FD

2

3

A/T

AP

CRS

1

FD

EM170AOM140261A.DGN

YD

SRC

PUSH DIR

5

6

4

1 - FD BUTTON – Turns ON and OFF the Flight Director presentation on PFD. – If the AP is engaged it is not possible to turn off the FD presentation on the PFD being used as source for the AP. !Airplanes Pre-Mod MAU load 23.1

NOTE: This button does not engage nor disengage any Flight Director Mode. " !MAU load 23.1 and on

NOTE: Pressing the FD button on the coupled side with AP disengaged, the Flight Director Modes are disengaged.

2 - AP BUTTON

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Controls and Indications

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

– Engages or disengages the Autopilot. 3 - A/T BUTTON – Engages or disengages the Autothrottle. 4 - YD BUTTON – Engages or disengages the Yaw Damper/Turn Coordination function. 5 - SRC BUTTON – Alternates between the lefthand or righthand FMA modes as source for the autopilot. A green arrowhead on the FMA indicates the respective source selected. 6 - CRS BUTTON – Manually sets the desired course on CDI as described below: – CDI displaying FMS: sets preview course. – CDI displaying V/L: sets CDI course.

AOM-1502-003

– Pressing this knob indicates the course to the station.

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REVISION 21

Controls and Indications

Page 7

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

SPEED AND MODE CONTROLS

MAIN PANEL

SPEED MAN

EM170AOM140259.DGN

FMS

1 PUSH IAS−MACH

1 - SPEED SELECTOR KNOB FMS: MAN:

Selected airspeed readout is controlled by the FMS logic. Selected airspeed readout is controlled manually.

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Page 8

Controls and Indications

REVISION 21

AOM-1502-003

– Pressing this knob alternates the speed presentation on PFD selected airspeed readout window between IAS and MACH.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AUTOPILOT/FD TCS BUTTON

N

D

MIC P

U

P T T

O F F

HO T M

A

P T RI

D I SC

A

P FD

T C S

EM170AOM140056.DGN

1

1 - TOUCH CONTROL STEERING BUTTON (TCS) The AP/FD button has authority over the autopilot and flight director. Flight director interface with the AP/FD button: – Press and Hold the TCS: – Synchronizes the Flight Director with the current airplane attitude. – Release the TCS: – The Flight Director returns to the lateral and vertical selection when the TCS was pressed. – With Roll/VS/FPA modes the FD maintains the airplane attitude when the TCS is released. AOM-1502-003

Autopilot interface with the AP/FD button:

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REVISION 21

Controls and Indications

Page 9

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AUTOMATIC FLIGHT

If the AP is engaged, pressing and holding the TCS will momentarily override the AP. Releasing the TCS, the AP resumes airplane control.

AUTOPILOT QUICK DISCONNECT BUTTON

MI P T T

O F F

OT

1

AP

SC

S

EM170AOM140263.DGN

A

P

1 - AP/TRIM DISCONNECT BUTTON Autopilot – Normal means of disengaging the autopilot. – Pressing once disengages the Autopilot. – Second press cancels the Autopilot aural alarm and FMA AP Warning. Trim

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Controls and Indications

REVISION 21

AOM-1502-003

– Refer to Flight Control.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION

AUTOTHROTTLE DISCONNECT AROUND BUTTONS

AUTOMATIC FLIGHT

AND

GO

1

1

AOM-1502-003

EM170AOM140057.DGN

2

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REVISION 21

Controls and Indications

Page 11

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AUTOMATIC FLIGHT

1 - AUTOTHROTTLE DISCONNECT BUTTON – Disengages the autothrottles. 2 - TAKEOFF AND GO AROUND BUTTON – Selects the TO, GA or Windshear Flight Director Modes.

AUTOTHROTTLE ANNUNCIATIONS ON FMA

HOLD TO

3

2

EM170AOM140054B.DGN

PFD

AT 1

The AT mode annunciations displayed on the Flight Mode Annunciation display (FMA) are the following: – SPDT – SPDE – TO – GA – HOLD – LIM – OVRD – RETD 1 - AUTOTHROTTLE ENGAGEMENT ANNUNCIATION

GREEN: Autothrottle engaged.

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Page 12

Controls and Indications

REVISION 21

AOM-1502-003

– Color:

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AMBER: Autothrottle failed. 2 - AUTOTHROTTLE ARMED MODE – Color: WHITE. 3 - AUTOTHROTTLE ACTIVE MODE – Color: GREEN: Autothrottle active mode. AMBER: LIM is displayed to indicate that vertical speed and target speed are incompatible with thrust rating available.

AUTOPILOT ANNUNCIATIONS ON FMA PFD

2

AP

EM170AOM140052B.DGN

1

1 - AUTOPILOT ENGAGED ANNUNCIATION – Color: GREEN: Autopilot engaged. RED: Autopilot failed. NOTE: Pressing and holding the TCS button, the “AP” annunciator on the FMA is replaced by “TCS” (green). Releasing the TCS button, “AP” is again displayed. 2 - FLIGHT DIRECTOR SOURCE ANNUNCIATOR

AOM-1502-003

– A green arrow indicated the selected AFCS source. NOTE: This annunciator is not displayed if the flight director fails.

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REVISION 21

Controls and Indications

Page 13

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

LATERAL MODE ANNUNCIATIONS ON FMA

ROLL HDG 2

1

EM170AOM140053B.DGN

PFD

The lateral mode annunciations displayed on the FMA are the following: – ROLL – HDG – – – –

LNAV LOC BC TRACK

1 - FGCS LATERAL ACTIVE MODE – Color: GREEN: manually commanded on the GP. MAGENTA: FMS commanded. 2 - FGCS LATERAL ARMED MODE – Color: WHITE.

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Controls and Indications

REVISION 21

AOM-1502-003

NOTE: If the FGCS fails the respective mode annunciation is removed.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

VERTICAL MODE ANNUNCIATIONS ON FMA

ALT GS 2

1

EM170AOM140302B.DGN

PFD

The vertical mode annunciations displayed on the FMA are the following: – ALT – ASEL – FLCH – FPA – GA – GS – OVSP – TO – GP – PTH – VS – WSHR 1 - FGCS VERTICAL ACTIVE MODE – Color: GREEN: manually commanded on the GP. MAGENTA: FMS commanded.

AOM-1502-003

2 - FGCS VERTICAL ARMED MODE

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REVISION 21

Controls and Indications

Page 15

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

– Color: WHITE. NOTE: If the FGCS fails the respective mode annunciation is removed.

APPROACH STATUS ANNUNCIATIONS ON FMA

PFD

2

APPR2 AP SPD T AT

APPR1 GS LOC

EM170AOM140415B.DGN

1

The approach annunciations displayed on the FMA are the following: – APPR 2 – APPR 1 – APPR 1 ONLY 1 - ARMED STATUS – Color: WHITE: Approach mode is armed.

RED: Warning condition.

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Controls and Indications

REVISION 21

AOM-1502-003

AMBER: Alert condition.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

2 - ENGAGED STATUS – Color:

AOM-1502-003

GREEN: Non-FMS commanded approach mode is engaged.

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REVISION 21

Controls and Indications

Page 17

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

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Controls and Indications

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

AUTOMATIC (AFCS)

FLIGHT

SYSTEMS DESCRIPTION

CONTROL

AUTOMATIC FLIGHT

SYSTEM

The Automatic Flight Control System (AFCS) provides flight guidance to the PFD Display and the Autopilot. The AFCS includes: – Flight Director (FD); – Autopilot (AP) with coupled Go-Around (GA) and – Yaw Damper (YD).

FLIGHT DIRECTOR (FD) The flight director provides lateral and vertical guidance on both PFD′s from the FMS commands and through pilot selections on the guidance panel.

FLIGHT DIRECTOR PRESENTATION A magenta diamond displayed on the Primary Flight Display (PFD) represents the FD. REMOVAL OF FLIGHT DIRECTOR PRESENTATION Pressing the FD button on the display control panel removes the flight director presentation on the PFD under the following conditions: – AP engaged: the Flight Director presentation can be removed by pressing the FD button on the non-coupled display control panel side. On the coupled side it is not possible to remove the FD from the PFD. – AP disengaged: the Flight Director presentation can be removed from both PFD′s by pressing the FD button on the respective display control panel.

FLIGHT DIRECTOR MODES ACTIVATION The FD automatically turns on under the following conditions: – TO/GA button actuation or; – Manual selection of any vertical or lateral mode or;

AOM-1502-003

– Autopilot engagement or; – Windshear detection.

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REVISION 21

Flight Guidance Control System

Page 1

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

FLIGHT DIRECTOR MODES DE-ACTIVATION !Airplanes Pre-Mod MAU load 23.1

Pressing the FD button does not deactivate the current lateral and vertical modes. " !MAU load 23.1 and on

Pressing the FD button on the coupled side with AP disengaged, the Flight Director Modes are disengaged (FD cue is removed from both PFDs, FD modes are removed from both FMAs and AT mode changes to SPDt tracking the airspeed target). "

To turn off the flight director, press the FPA button on the guidance panel when the active vertical mode is FPA. If any other vertical mode is active, press FPA button once to activate the FPA mode and then press it again to turn off the Flight Director.

AUTOPILOT (AP) The E-JETS have a single autopilot with a dual channel configuration. One channel is active while the other works as a hot spare. The system alternates the channel automatically in case of a failure of the active channel and also after each landing. The autopilot has one servo for pitch control, one for roll control and one or two optionally for rudder control. As the AP servos are connected to the controls, the AP commands may be observed by the movement of the control column, control wheel or rudder to keep pilots aware of any AP input.

AP ENGAGEMENT/DISENGAGEMENT ENGAGEMENT Autopilot engagement is inhibited on the ground. In flight the autopilot is engaged pushing the AP button on the guidance panel. The AP engagement is verified on the FMA on both PFD′s.

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Flight Guidance Control System

REVISION 21

AOM-1502-003

With the confirmation of the AP label on the FMA the autopilot is controlling the airplane pitch, roll and yaw according to the flight director selections.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

DISENGAGEMENT NORMAL DISENGAGEMENT The autopilot is normally disengaged by pressing the quick disconnect PB on either control wheel. Pressing the button once: – Disengages the autopilot; – Triggers the aural warning “AUTOPILOT”; – The FMA “AP” annunciation blinks in red. Pressing the button the second time cancels the aural warning and the FMA annunciation. The autopilot may be momentarily overridden by pressing the TCS button on the control wheel. Releasing the TCS, the autopilot resumes airplane control. NON-NORMAL DISENGAGEMENT The autopilot also disengages if one of the following conditions occurs: – AP button is pressed on the guidance panel; – Either manual pitch trim switch is actuated; – Either stick shaker is activated. – Windshear escape guidance is activated. ABNORMAL DISENGAGEMENT The following events cause an autopilot disconnect and EICAS message: – Reversion of the fly-by-wire system to direct mode. – Either the aileron or elevator control system is disconnected. – A pilot input contrary to the autopilot is made on the controls with a long time light force or a short time stronger force. – Internal monitor failure.

AOM-1502-003

After Non-Normal or Abnormal Disengagement, pressing either AP disconnect button once cancels the flashing “AP” on the FMA and silences the aural alarm. NOTE: AP disengagement by application of force on control column, through the forward and after movement, and control wheel, lateral movement, is indicated in red on FMA. The AP

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REVISION 21

Flight Guidance Control System

Page 3

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

disengagement by application of force only on control wheel may be indicated in red on FMA and AP FAIL message may be displayed on the EICAS.

YAW DAMPER

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Flight Guidance Control System

REVISION 21

AOM-1502-003

The yaw damper is automatically engaged after power-up of either hydraulic system 1 or 3. The yaw damper is automatically disengaged after shutdown of both hydraulic system 1 and 3. The yaw damper may also be disengaged/engaged by pressing the YD button on the AFCS guidance control panel.

E

REVISION 21

Flight Guidance Control System

HDG

33O

6

O79

E

1O

1O

NAV1 118 O3 119 O3

KPHX H 5OO NM 23 MIN

OO5

DTK

3OO KT

GSPD

4

1 2

1OOO

2 1

4

4OOO

E

1 / 2

Q

V

P

U

O

T

Y

S

X

Z

K

N

J

D

M

I

C

B

H

A

TA/RA

W

R

L

F

7

4

1

0

8

5

2

IDENT

TCAS/XPDR

STBY

116 . 8

N 123 XPDR 1471

NAV1 114 . 8 DME H PXR 115 . 6

NAV2 117 . 4

118 . 600

COM2

123 . 200

118 . 600

FMS AUTO

SQ

RADIO

123 . 200

COM1

MCDU 1

APP WPT VPTH MSG HDGINT

1O

29.92 IN

25OOO

OM

255OO

247OO

G

12

ASEL

EM170AOM140817A.DGN

VHF1 118 O25 119 O25

VOR1 VOR2

1O

1O

VOR

VAPP FLARE

9

6

3

/

+/ −

Map

33

[ 1OO ]

FL118

ZUN

NEXT DEST

PROGRESS

TCAS

[ -9.9 ] A WX/R/T S STAB/TGT LX/OFF

WEATHER

O.O NM O MIN

FMS1

5O GUP FL11O

Fuel

DME1 65.3 NM LAX

15 SAT ^C 25 TAT ^C 3OO TAS KTS

FLO9O

GUP44

hPa

BRG

HSI

WX

FPR

PREV

9O.O

3OO

F

TRIMS

DOWN

YAW

-5 -5 -64.6 12OO

1OO %

ROLL

ALT RATE P LFE

CABIN

APU

DOWN

LANDING GEAR

ASCB−D

S/F

2

3 4

81 ^

SPDBRK

LP HP

TEMP

PRESS PSI 64

12OO

FQ LB

IGN A

^C

DOWN

22

UP

PITCH

FT FPM PSI FT

1O2O

BARO

PUSH DIR

CRS

FD

BANK

APP

NAV

PUSH SYNC

HDG

HDG

SRC

YD

AP

TOGA

A/T SPEED

PUSH CHG

AUTO

MAN

FLCH

VNAV

PUSH FT/M

ALT SEL

ALT

VS VS

FD

PUSH DIR

CRS

IN

PUSH STD

BARO SET hPa

BRG

HSI WX

FPR

PREV

TCS

V/L

FMS

MAU 2

DIST ETE FUEL 55.6 O1+32 11.4 95 O2+52 1O.4

3

TCAS

92

Weather

Gain

DME1 LAX 65.3 NM

TA ONLY FLT LVL EXPANDED

TCAS

236

E

555 M

Q V

P U

O T Y

X Z

K

S

E

N

J

D

M

I

C

B H

A

TA/RA

W

R

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F

FMS AUTO

SQ

RADIO

G

STBY

TCAS/XPDR

NAV1 114 . 8 DME H PXR 115 . 6

118 . 600

123 . 200

COM1

7

4

1

0

8

5

2

IDENT

N 123 XPDR 1471

116 . 8

NAV2 117 . 4

118 . 600

123 . 200

COM2

1 / 2

MCDU 2

VHF1 118 O25 119 O25

VOR2

VOR1

KPHX 55 .6 NM 23 MIN

FMS1

GSPD 3OO KT

18O

19O

R

9

6

3

33O

HDG

AP

RF

2

2OO

24O

1

22O

26O

/

+/ −

1OO

5.O

6

1O

1O

AP B AT B

O.2 R

KPHX

KLVS

KFLG

O79

1O

1O

VOR

12

5

O24

DTK

ASEL

VAPP FLARE

MAU 3

4

1 2

1OOO

2 1

4

4OOO

NAV1 118 O3 119 O3

CHR O8: 12

29.92 IN

25OOO

OM

255OO

247OO

ROLL CONTROL FEEDBACK

Checklist

TURB

ACT

VAR Gain

TGT RCT

STAB Off

Off

Fuel 15 SAT ^C 25 TAT ^C 3OO TAS KTS

LX Clear

5

Systems

STBY

BARO

MINIMUMS

ZUN

O.O5 L

SECT

LX

WPT ZUN GUP

GUP

GUP44

PUMPS

N

Plan

O1O

GMAP

WX

NEXT DEST

PROGRESS

1OO

33

FSBY OVRD

5.3 A WX/R/T S STAB TGT LX/OFF

WEATHER

PUSH TEST

RA

Map

ZUN 55. 6 NM 23 MIN

FMS1

TOGA

CHANNEL B

UP

DN

ASCB−D

FPA SEL

FPA

GUIDANCE PANEL GP−750 MINIMUMS

PUSH TEST

RA

S

3 3

25 ^

12

9OO

REV

8O.O

96.O

1OO7 ^

FF PPH 1OOO

N2

9O.O 1OOO

ITT

N1

FLEX TO-2 ATTCS 39 ^

1OO7 ^

REV

8O.O

CHANNEL A

V/L

FMS

VIB

OIL

IGN A

96.O

AP DISCONNECTED SWITCHES

TCS

PUSH STD

BARO SET

MAU 1

IN

1OO

FL13O

PUM

TA ONLY FLT LVL EXPANDED

TCAS

Checklist

[ 1OO ]

3

5

Systems

DIST ETE FUEL 55.6 O1+32 11.4 95 O2+52 1O.4

O.O5 L

N

Weather

WPT ZUN GUP

Plan

OO O

E

FMS1

5.O

AP B AT B

6

CHR O7:12

555 M

18O

19O

R

AP

RF

2

2OO

24O

22O

1

3O

W

236

3O

26O

6

3

E 3

AOM-1502-003

AILERONS SMART SERVO

CAPTAIN LOAD FEEL

CAPTAIN CONTROL WHEEL

ELEVATORS SMART SERVO

FIRST OFFICER LOAD FEEL

FIRST OFFICER CONTROL WHEEL

AIRPLANE OPERATIONS MANUAL SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

Copyright © by Embraer. Refer to cover page for details.

14-03-10

Page 5

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

AFCS INDICATIONS ON PFD FLIGHT MODE ANNUNCIATIONS (FMA) The Flight Mode Annunciation display, also referred as FMA, is located on the top of the PFD and it displays annunciations for autothrottle, autopilot, approach status, lateral and vertical modes. The FMA color code for normal operation is as follows: – Magenta: FMS commanded active/engaged mode. – Green: Non-FMS commanded active/engaged mode. – White: Armed mode. – Amber: Alert condition. – Red: Abnormal condition.

PFD

HOLD TO AT ARMED MODE

AP AT

HDG LOC

AT ENGAGEMENT STATUS

FD ACTIVE VERTICAL MODE

FPA GS FD ARMED MODES

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Flight Guidance Control System

REVISION 21

AOM-1502-003

FD SOURCE

FD ACTIVE LATERAL MODE

EM170AOM140414B.DGN

AP ENGAGEMENT STATUS

AT ACTIVE MODE

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

APPROACH STATUS ANNUNCIATIONS The Approach Status Annunciations are displayed at the top of the FMA upon pressing the APP button on the guidance panel. The annunciator on the left side is either the armed status (white) or a discrepancy (amber) and on the right side is the current engaged status (green). The BARO/RA window on the PFD 1 and on the PFD 2 must be on the same selection (BARO-BARO or RA-RA). If there is a discrepancy the BARO/RA window on the side selected to RA will flash amber. The system will not indicate discrepancy in selected values between PFD 1 and PFD 2. The terminology used for the system capability levels are: – APPROACH 2 (APPR 2) – ILS CAT II capable. – APPROACH 1 (APPR 1) – ILS CAT I capable.

PFD

APPR1 ONLY

AOM-1502-003

EM170AOM140835A.DGN

APPR2

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REVISION 21

Flight Guidance Control System

Page 7

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

FGCS LATERAL MODES The FGCS pilot selectable lateral navigation modes are: – Roll Hold (ROLL). – Heading Select (HDG). – Lateral Navigation (LNAV). – Localizer (LOC). – Back-course (BC). Pilot non-selectable mode is: – Track Hold (TRACK).

ROLL HOLD (ROLL) This is the basic lateral mode and does not provide any airplane guidance. Depending on the airplane bank angle at the moment of ROLL activation, the autopilot will maintain the following bank angles until another lateral mode is selected: – Bank angle at 6° or below: AP levels the wings. – Bank angle above 6° and below 35°: AP holds present bank angle. – Bank angle at 35° or above: AP maintains bank angle at 35°. ROLL MODE ACTIVATION: The ROLL Mode is activated under any of the following conditions: – Pressing TOGA button while on the ground and IAS is below 100 kt; – There is no lateral mode active and a vertical mode is selected; – Deselecting an active lateral mode;

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Flight Guidance Control System

REVISION 21

AOM-1502-003

– COURSE TO INTERCEPT on the FMS is activated.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

ROLL MODE DE-ACTIVATION: – The ROLL Mode is de-activated when another lateral mode becomes active.

HEADING SELECT (HDG) This mode provides airplane lateral guidance through the HDG SEL knob. Pressing the center of the HDG selector knob synchronizes the heading bug to the current heading. The FD follows the selected heading and respects the direction in which the turn on the HDG SEL knob was commanded, regardless if the turn being commanded is greater than 180°. HDG MODE ACTIVATION – HDG button is pressed on the Guidance Panel. HDG MODE DE-ACTIVATION – HDG button is pressed on the Guidance Panel. – When another lateral mode becomes active.

LATERAL NAVIGATION (LNAV) The LNAV engages when: – LNAV mode is armed, LNAV will automatically engage when passing through 200 ft during a climb. – The airplane is above 200 ft and the NAV button is pressed.

AOM-1502-003

The FMS becomes the source for lateral navigation providing guidance through the Flight Director.

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REVISION 21

Flight Guidance Control System

Page 9

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

LOCALIZER (LOC) The LOC mode is selected via the APP button on the GP. The FD automatically manages the LOC and Back-Course according to Localizer frequency, PFD information and airplane’s position. The FD is capable of intercepting the LOC when there is no GS signal. Other vertical navigation modes such as FPA or VS can be used for vertical navigation. The FD opens the bank angle command limit to 35° during Localizer capture.

BACK-COURSE (BC) The FD will automatically select a BC approach on the PFD. The FGCS provides commands for capture and tracking of BC localizer indicated on the selected PFD.

TRACK HOLD (TRACK) The track select mode is used to intercept and maintain an inertial derived airplane track from the IRS. This mode is used for Takeoff and Go-Around. TAKEOFF The automatic transition from ROLL to TRACK during takeoff occurs when: – IAS is greater than 100 kt and; – Bank angle is at 3° or below for more than 10 s. GO AROUND TRACK ACTIVATION – TOGA button is pressed for go-around. TRACK DE-ACTIVATION

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Flight Guidance Control System

REVISION 21

AOM-1502-003

– Another lateral mode is selected.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

Canceling the vertical mode of GA does not disengage the TRACK lateral mode.

FGCS VERTICAL MODES The FGCS vertical navigation modes are: – Flight Path Angle (FPA). – Takeoff (TO). – – – –

Altitude Select (ASEL). Flight Level Change (FLCH). Altitude Hold (ALT). Vertical Speed (VS).

– Vertical Navigation (VNAV). – Overspeed (OVSP). – Glide Slope (GS). – Go around (GA). – VGP (VGP).

FLIGHT PATH ANGLE (FPA) The FPA is the basic vertical mode (except for the TO). The FPA can be used for vertical navigation by selecting a higher or lower altitude on the ALTSEL and then pressing the FPA button. The flight path reference line (FPR) is displayed when the FPA is active. Pressing the FPR button in the display controller panel displays the FPR line, regardless of vertical mode active. Flight path angle (± 9.9°) is selected in the FPA SEL selector knob on the guidance panel. FPA ACTIVATION: – When the autopilot is engaged and no FD mode is active; – Pressing the FPA button on the guidance panel. – A lateral mode is activated and there is no vertical mode active.

AOM-1502-003

– Deselecting the current vertical mode.

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REVISION 21

Flight Guidance Control System

Page 11

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

TAKEOFF (TO)

!MAU load 17.5 and on AND previous than load 19.3 OR SB 0170-31-0017 AND PRE-MOD SB 0170-31-0019;

The takeoff mode is a FD only mode and is represented by crossbars on PFD. TO mode commands the airplane to maintain a pitch attitude reference. In takeoff the autopilot engagement is not accept and FPA mode is inhibited. Lateral mode changes are allowed. FPA indication (green symbol on the ADI) is inhibited for 30 s after lift-off when taking off with flight director OFF (no active mode on the FD).

1O

1O

1O

1O

EM170AOM140413B.DGN

Pressing the TOGA button activates the TO mode. Following a landing, the TO mode can be enabled after 5 seconds on ground (main gear weight on wheels).

PFD TAKEOFF MODE CROSSBAR

The TO mode is deactivated when: – Another vertical mode is selected. – AP/FD TCS button is pressed.

The TO mode initial guidance is the flap-pitch based guidance:

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Flight Guidance Control System

REVISION 21

AOM-1502-003

– AP is activated.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

– FLAP 1 – pitch 11º. – FLAP 2 – pitch 10º. – FLAP 4 – pitch 12º. When airborne and IAS is greater than speed target, the guidance will be speed target according to the following: – All engines operating: V2 + 10 kt. – One engine inoperative: – Engine failure below V2: guides V2. – Engine failure between V2 and V2 + 10 kt: guides present speed. – Engine failure above V2 + 10 kt: guides V2 + 10 kt. The V2 is inserted on the MCDU (PERF > PERF INDEX > PERF DATA > TAKEOFF page). If speed target is not valid, the airplane guides to a fixed pitch according to the flaps in use. In TO mode the pitch is limited to a minimum of 8° and a maximum of 18°. The maximum speed target is Vfe - 5 kt and minimum speed target is Vshaker + 10 kt for all engines operating. For one engine inoperative the minimum speed target is Vshaker + 3 kt.

AOM-1502-003

"

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REVISION 21

Flight Guidance Control System

Page 13

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

TAKEOFF (TO)

!MAU load 19.3 and on OR POST-MOD SB 170-31-0019

1O

1O

1O

1O

EM170AOM140413B.DGN

The takeoff mode is represented by crossbars and is used during the takeoff phase to maintain a pitch attitude based on flap selection, airplane weight and V2 speed.

PFD TAKEOFF MODE CROSSBAR

TO MODE ACTIVATION – TOGA button is pressed on ground. TO MODE DE-ACTIVATION – When another vertical mode is selected. !!Pre-mod MAU load 27.1

– If the AP is engaged TO mode is canceled and FPA becomes the active vertical mode.

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Flight Guidance Control System

REVISION 21

AOM-1502-003

""

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AUTOMATIC FLIGHT

TO PITCH ANGLE CALCULATION To calculate the TO pitch angle the FMS uses the actual airplane weight and the following information inserted in the MCDU TAKEOFF page: !!Pre-mod MAU load 27.1

– Flap position (page 2/3). – V2 speed (page 3/3).

TAKEOFF

3/3

V1 1L

124

1R

2L

VR 125

2R 3R

4L

VFS 180

5L

LANDING

6L

DEP SPD

4R T/O

PITCH 10.5 CLIMB

5R 6R

EM170AOM140803A.DGN

3L

V2 132

""

TO pitch will be dashed if necessary information is not inserted. TO PITCH ANGLE LOGIC The system will guide the Pitch initially to the calculated angle. When airborne and IAS is greater than speed target, the guidance will be as follows: – All engines operating: V2 + 10 kt.

AOM-1502-003

– One engine inoperative: – Engine failure below V2: guides V2.

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REVISION 21

Flight Guidance Control System

Page 15

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

– Engine failure between V2 and V2 + 10 kt: guides present speed. – Engine failure above V2 + 10 kt: guides V2 + 10 kt. In TO mode the pitch is limited to a minimum of 8° and a maximum of 18°. The maximum speed target is Vfe - 5 kt and minimum speed target is Vshaker + 10 kt for all engines operating. For one engine inoperative the minimum speed target is Vshaker + 3 kt. NOTE: If actual flap selection does not agree with FMS selection, the aural warning “NO TAKE OFF FLAPS” will be triggered whenever the airplane is on ground and take off thrust is applied or Take off configuration button is pressed. "

ALTITUDE SELECT (ASEL) The altitude select mode captures and levels off at the selected altitude. A green ASEL is displayed on the FMA while altitude select mode captures the pre-selected altitude, followed by a green ALT display when level off at the selected altitude. NOTE: Altitude select is automatically armed whenever a vertical FD mode is used to fly towards the desired altitude.

FLIGHT LEVEL CHANGE (FLCH) FLCH provides commands to Climb or Descend to the altitude selected (ALTSEL) according to the speed selected. During FLCH the speed selected will be controlled via pitch changes through elevator inputs, and the FMA will show SPDE. FLCH ACTIVATION: – Pressing the FLCH button. FLCH DE-ACTIVATION: – Pressing the FLCH button.

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Page 16

Flight Guidance Control System

REVISION 21

AOM-1502-003

– When another vertical mode is selected.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

FLCH LOGIC: The FLCH mode can be FMS (magenta) or non-FMS (green). During a FLCH descent, selecting an altitude above the current airplane altitude will command the airplane to climb. The airplane will not reach the altitude selected if AT is disengaged and sufficient thrust to climb is not available. During a climb, selecting an altitude below the current airplane altitude will command the airplane to descend. The rate of descent is a result of the amount of engine thrust being used. TRANSITION FROM MACH / IAS The selected speed is displayed in the box on the top of the speed tape. When the altitude is approximately 29000 ft the display switches from IAS to Mach readout during climb and from Mach to IAS readout during descent.

ALTITUDE HOLD (ALT) The ALT mode indication on the FMA indicates the altitude hold mode and the altitude selected is being maintained. ALT MODE DISENGAGEMENT: The ALT mode can be disengaged by selecting a different altitude via ALTSEL knob and activating a new vertical mode. This logic is valid for all vertical modes except for Glide Slope (GS) and VGP. Switching from ALT mode to GS or VGP mode occurs without change in ALT SEL selection. ALTITUDE HOLD BUTTON (ALT)

AOM-1502-003

Pressing the ALT button on the GP engages the altitude hold mode. The altitude hold mode maintains the altitude displayed on the Altimeter at the moment the ALT button is pressed.

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SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

VERTICAL SPEED (VS) The VS mode maintains a vertical speed rate. The VS mode is activated by pressing the VS button on the GP. Vertical speed is selected rotating the vertical speed thumbwheel on the GP. The vertical speed command range goes from -8000 ft/min to +6000 ft/min. The increments of the Vertical Speed target value are: 50 ft/min (below 1000 ft) and 100 ft/min (above 1000 ft).

OVERSPEED PROTECTION (OVSP) The AFCS provides overspeed detection and protection in order to maintain the speed below Vmo/Mmo limits. When the autopilot and/or the autothrottle are engaged, pitch and/or thrust will be adjusted to prevent overspeed. When the FD is disengaged, only aural warning “HIGHSPEED” will be triggered requiring pilot input to avoid overspeeds. When the OVSP protection activates, an amber OVSP indication displays on the FMA. The previous active mode is displayed as armed (white) and becomes active again when OVSP protection is no longer active.

GLIDE SLOPE (GS) The GS approach mode allows the ILS approach mode functions. The GS mode arms when the APP button is pressed and activates when the glide slope is captured.

GO-AROUND (GA) The go-around mode automatically provides go-around guidance and thrust by pressing the TOGA switch. The TRACK HOLD mode is engaged when TOGA is pressed. GA MODE ACTIVATION:

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Flight Guidance Control System

REVISION 21

AOM-1502-003

– Pressing TOGA switch when inflight.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

GA MODE DE-ACTIVATION: – When another vertical mode is selected. GA LOGIC: The GA mode first guidance sets pitch at 8°. When IAS is greater than the speed target, the guidance will be the speed target according to the following: – All engines operating: VREF + 20 kt. – One engine inoperative: VAC (approach climb). The VREF and VAC are inserted on the MCDU (PERF > LANDING page). If speed target is not valid, the airplane guides to pitch 8°. In GA mode the pitch is limited to a minimum of 8° and a maximum of 18°. The maximum speed target is Vfe - 5 kt and minimum speed target is Vshaker + 10 kt for all engines operating. For one engine inoperative the minimum speed target is Vshaker + 3 kt.

WINDSHEAR (WSHR) This mode provides FD escape guidance in case of Windshear detection below 1500 ft AGL. The system provides flight path guidance angle limited to stick shaker, commands wings level and provides aural alerts. The label “WSHR” is displayed when the Windshear Guidance mode is activated. The autopilot is disengaged when the Windshear Guidance mode becomes active. Windshear alerts are associated with vertical winds and rapidly changing horizontal winds and are divided as follows: WINDSHEAR CAUTION:

AOM-1502-003

– Associated with increasing head wind and severe up drafts. A detection of a caution level Windshear is indicated by amber WSHEAR on the PFD and aural alert “CAUTION WINDSHEAR”.

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REVISION 21

Flight Guidance Control System

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SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

WINDSHEAR WARNING: – Associated with decreasing head wind (or increasing tail wind) and severe vertical down drafts. A detection of a warning level Windshear is indicated by a red WSHEAR on the PFD and aural alert “WINDSHEAR, WINDSHEAR, WINDSHEAR”. WINDSHEAR GUIDANCE MODE ACTIVATION: – Windshear warning or caution condition is detected and TOGA switch is pressed. – Windshear Warning condition is detected and thrust lever is set to TO/GA position. – Automatically when windshear warning condition is detected and the FD mode is in TO or GA. A green WSHR annunciation is displayed on the FMA when the Windshear guidance mode is activated.

VERTICAL NAVIGATION (VNAV) The VNAV engages when: !Pre-mod MAU load 27.1

– VNAV mode is armed, VNAV automatically engages when passes through 400 ft during a climb. – The airplane is above 400 ft and the VNAV button is pressed. "

According to the required vertical profile the VNAV automatically selects its sub-modes. VARM SUB-MODE When VNAV is selected on the GP, the initial mode is VARM. The FMS remains in VARM mode until the appropriate vertical mode to be used is determined.

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Flight Guidance Control System

REVISION 21

AOM-1502-003

While in the VARM mode the previous AFCS vertical mode remains engaged.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

VFLCH SUB-MODE VFLCH is VNAV Flight Level Change and can be automatically selected by the FMS or manually by the flight crew for climb or descent. During climbs the VNAV sub mode will always be VFLCH. VFLCH engages when the Alt Selector is set to an altitude different than the current airplane altitude, VNAV is engaged and the FLCH button is pressed. VASEL SUB-MODE VASEL is the VNAV altitude capture mode. It captures the Alt Selector altitude or the FMS waypoint altitude constraint. VALT SUB-MODE Maintains the altitude commanded by the FMS or the Alt Selector. VGP SUB-MODE The VNAV Glide Path (VGP) mode is an FMS based non-precision approach mode created to provide a constant final approach descent path. In this mode, the FMS flies a constant glide path approach from the Final Approach Fix (FAF) to the Missed Approach Point (MAP) regardless the Alt Selector altitude which may be set to the missed approach altitude. !Airplanes Pre-mod MAU load 21.4

Temperature compensation calculated by the FMS does not compensate for VNAV temperature deviations to follow the desired geometric glide path when performing VGP approaches. Thus, if the outside air temperature is above ISA, the VGP flight path is higher than the geometric glide path and, if the outside air temperature is below ISA, the VGP flight path is lower.

AOM-1502-003

"

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REVISION 21

Flight Guidance Control System

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SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

VGP ACTIVATION The VGP mode can be armed by pressing the APP button on the Guidance Panel when within 30 nm radial distance from the FAF, and a non-localizer based approach with a published constant glide path angle is selected in the FMS. The VGP mode is engaged when the airplane is within 5 NM from the FAF along track distance or at any distance within 30 NM from the destination whenever using ACTIVATE VECTORS and the first approach waypoint is the FAF. The VGP does not engage if any change in the vertical procedure profile is made. NOTE: – If the glide path is below the current aircraft position and the APP button is pressed the VGP will engage and command a descend to intercept final approach path. – If performing HOLD PATTERN the VGP should be armed only after exiting the HOLD, otherwise the VGP may intercept the final approach descent path during the HOLD track. VGP DE-ACTIVATION – Selecting another vertical mode.

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Flight Guidance Control System

REVISION 21

AOM-1502-003

– Pressing the APP button on the GP after engagement.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AUTOMATIC FLIGHT

PFD

SPD T 125

LNAV PATH GP

AP AT

16O

35 OO 4OOO 4

15O

2O

2O

14O

1O

1O

2 1

125

35OO

11O 1OO 9O

1O

2O

2O

CRS

HDG

SPD T 125

LNAV

AP AT

CHR

GP

40 OO

16O

1OOO

4OOO 4

15O

2O

2O

14O

1O

1O

125

2 1

30OO

1000

-3.O

11O 1OO 9O GSPD

3OOO 4 30.16 IN

M

GSPD

19O

1 2

1O

1O

2O

2O

1 2

3OOO 4 30.16 IN

M

CRS

HDG

CHR

EM170AOM140686A.DGN

19O

1O

AOM-1502-003

VGP ARMED AND ENGAGED

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REVISION 21

Flight Guidance Control System

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SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

VPATH SUB-MODE The VPATH is a VNAV sub mode used for constant geometric path descents downwards to an waypoint constraint. The FMS path angle can be defined by pilot entries, procedures within the database or by default. By default the FMS path angle is 3°. When required it can be manually varied from 1 to 6 degrees. VPATH LOGIC Flying VPATH (fixed descent angle) speed changes are accomplished through thrust variations. An amber LIM on the FMA indicates that insufficient thrust variation is available to maintain or to reach the required speed. VPATH SPEED/ALTITUDE LIMIT LOGIC In order to comply with Speed/Altitude limit protection selected on the PERF INIT page when the speed limit is exceeded by more than 5 kt, the system reverts to VALT or VASEL momentarily leveling the airplane thus reducing the speed. Once the desired speed is reached the system returns to VFLCH which is maintained until reaching the altitude selected in the ALTSEL window. When the autothrottle is not engaged the FMS may continue the descent through the speed/altitude limit. In this case, manual speed control is necessary to meet the speed/altitude limit. Speed/Altitude Limit protection is also given during VFLCH descents. Under these conditions, the FMS slows the airplane by thrust variation to the speed limit when approaching the altitude associated with it.

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Flight Guidance Control System

REVISION 21

AOM-1502-003

The deletion of SPD/ALT LIM from the FMS will dash the field and FMS will understand that no Speed/Altitude Limit applies.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

VNAV APPROACH TEMPERATURE COMPENSATION !MAU load 21.4 and on

The VNAV temperature compensation technique function adjusts all FMS waypoint altitude constraints for the defined approach, approach transitions, and missed approach segments of the flight plan for non-standard day temperatures. TEMP COMP MODES The flight crew configures the FMS for three modes of VNAV approach temperature compensation on the TEMP COMP page: – OFF: assumes standard day temperature. – COLD: applies temperature compensation only when approach is flown in COLD conditions. – HOT/COLD: applies temperature compensation when approach is flown in any temperature. TEMP COMP REQUIREMENTS – One of its modes (COLD or HOT/COLD) enabled. – An arrival procedure loaded on the active flight plan. – An outside temperature for the destination airport is entered on the LANDING page. TEMP COMP ACTIVATION Since all requirements described above are met the TEMP COMP feature may be activated on the TEMP COMP page. The TEMP COMP page is accessible pressing the TEMP COMP prompt on the LANDING page or on the ACTIVE FLIGHT PLAN page when within 30 NM from destination. Pressing the prompt a MOD FLIGHT PLAN with the proposed altitudes is shown. The flight plan must be activated to incorporate the compensated altitude constraints. NOTE: The temperature compensation is applied only to the altitude constraints from the navigation database. No changes are applied to the pilot-entered constraints.

AOM-1502-003

It is possible to remove the compensated altitudes by selecting the REMOVE prompt on the TEMP COMP page. TEMP COMP PRESENTATION

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REVISION 21

Flight Guidance Control System

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SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

The compensated altitudes for each of the arrival flight plan constraints are displayed in reverse video on the MCDU and VSD. TEMP COMPENSATED MDA (DA) The TEMP COMP page displays the compensated MDA (DA). If the procedure installed in the database does not contain a waypoint that corresponds to the MDA (DA) then four dashes are displayed in its place. Values can be entered or deleted by the flight crew to find out what is the compensated MDA (DA) for temperature inserted in the LANDING page. "

SPEED CONTROL Speed control can be manual or automatic depending on the selection on the Speed Selector Knob. The FMS selection allows the FMS to send its internally defined speeds as target speeds for FGCS. MANUAL SPEED CONTROL If the Speed Selector Knob is set to MANUAL the pilot is responsible for controlling the speed during all flight phases. FMS SPEED CONTROL In this mode the speed command is sent to the AFCS by the FMS. The departure, climb, cruise, descent, approach and go-around speeds are set in the PERFORMANCE INITIALIZATION. If a new schedule is desired, these settings can be modified in flight. SPEED PROTECTION The FMS incorporates speed reversion (transition from VPATH to VFLCH) and latched speed protection. Transition from VPATH to VFLCH: Speed reversion is active when the descent is too steep and it is not possible to maintain the selected speed. In this case, the FMS transitions to VFLCH, which maintains the speed within limits. The transition from VPATH to VFLCH automatically occurs if:

– FMS passes through a speed/altitude limit with a speed greater than 5 kt. In this case, the command is to level off until the speed deviation is below + 2 kt. Afterwards, the FMS commands VFLCH down to the Alt Selector altitude;

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– The speed exceeds VMO/MMO + 10 kt during VPATH descents;

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

– Landing Gear/Flap speed limit is exceeded by more than 10 kt; – In VPATH and the speed is less than VREF – 10 kt. NOTE: If the Auto Throttle is not engaged the pilot is responsible for maintaining the speed.

ILS APPROACH The ILS approach is a non-FMS navigation. The automatic transition from FMS navigation into an ILS approach is done through the use of the preview mode. The transition can also be manually done by pressing the V/L button on the guidance panel. ILS APPROACH ACTIVATION – Pressing the APP button on the GP when an ILS frequency is tuned. ILS APPROACH CAPABILITY The FMA shows current system capability based on the intended approach to be flown. The intended approach capability is determined by the selection of the (RA/BARO) on the Guidance Panel. All other operational conditions must be met in order for the capability to be validated. Selecting BARO indicates APPR 1 capability for an ILS CAT I approach. Selecting RA indicates APPR 2 capability for an ILS CAT II approach. The Altitude (BARO) or Height (RA) inserted in the BARO/RA window on the PFD through the Minimums Knob on the guidance panel determines the EGPWS callouts for the minimums (MDA or DA). Selecting the RA/BARO to off (setting minimums to 0 ft) disables the EGPWS minimums call outs. The system will not indicate discrepancy in selected values between PFD1 and PFD2. CAPABILITY REQUIREMENTS

AOM-1502-003

When ILS modes are requested via the APP button, the system arms for the highest capability available as long as all conditions are satisfied, according to the following:

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REVISION 21

Flight Guidance Control System

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SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

APPR 1 The APPR 1 is the flight director mode used for ILS CAT I approaches. The requirements to engage APPR 1 are: – RA/BARO selector set to BARO. – NAV frequency set to the correct LOC frequency in the MCDU. – V/L or preview selected. These selections are necessary only on the PFD where the FD source is pointing. When APP button is pressed, the system attempts to arm to the highest capability available, this case APPR 1. APPR 2 The APPR 2 is the flight director mode used for ILS CAT II approaches. The requirements to engage APPR 2 are: – Both RA/BARO selector knobs set to RA. – Radio altitude between 800 ft and 1500 ft. – Minimums displayed on both PFDs are valid. – Both NAV frequencies set to correct LOC frequency in the MCDU. – Both PFDs set to correct LOC inbound course (V/L or Preview). – SLAT/FLAP 5. These selections above are necessary on both PFDs. The BARO/RA window on the PFD 1 and on the PFD 2 must be on the same selection (RA-RA) for CAT II approaches. If there is a discrepancy the BARO/RA window on the non coupled side will flash amber upon crossing 1500 ft when APPR mode is selected. An EICAS message APPR 2 NOT AVAILABLE is presented inflight if the required items to engage are not met or a system failure exists.

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REVISION 21

AOM-1502-003

If the flap setting is the only remaining condition to be satisfied for CAT II, the armed status will remain displayed down to 800 ft RA, suggesting there is still one pilot’s action pending.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

CAT II WARNINGS LOCALIZER, GLIDE SLOPE AND RADIO ALTITUDE COMPARATORS WARNINGS A comparison between the localizer, glide slope and radio altitude deviation indications are performed when the following conditions are met: – On-side radio altitude valid and below 1500 ft. – APR mode selected on Flight Guidance Panel. – SLAT/FLAP 5. – CAT II Decision Height setting on both Display Control Panels. – On-side VOR/LOC active course valid. – Cross-side data valid. – Go-around not selected on either side. – No back course selected. For localizer, the following additional condition is required: – Both LOC signals tuned and valid for at least 15 s. If LOC indications differ by values above approximately 1/2 dot, an amber LOC annunciator will appear flashing (for 10 s). Refer to ADI/HSI Miscompares in 14-09-05 for details. For glide slope, the following additional condition is required: – Both glide slope signals valid and both LOC signals tuned and valid for at least 15 s. If GS indications differ by values above approximately 2/3 dot, an amber GS annunciator will appear flashing (for 10 s). Refer to ADI/HSI Miscompares in 14-09-05 for details. For radio altitude, the following additional condition is required: – Both radio altimeters signals valid and on scale.

AOM-1502-003

If radio altimeters indications differ more than a set point, an amber RA annunciator will appear flashing (for 10 s). Refer to ADI/HSI Miscompares in 14-09-05 for details.

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REVISION 21

Flight Guidance Control System

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SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

EXCESSIVE WARNINGS

AIRPLANE OPERATIONS MANUAL

LOCALIZER

AND

GLIDE

SLOPE

DEVIATIONS

The on-side localizer and glide slope excessive deviations are compared to the CAT II limits and displayed when the following conditions are met: – APR mode selected on Guidance Panel. – SLAT/FLAP 5. – CAT II Decision Height setting on Guidance Panel. – VOR/LOC is the active course is valid. – On-side radio altitude between 500 and 80 ft. – On-side localizer tuned and valid. – On-side glide slope valid. – No back course selected. – Go-around not selected on either side. Localizer excessive deviation: If a localizer deviation greater than approximately 1/3 dot is detected, the excessive lateral deviation pointer will change from green to amber, the lateral deviation scale will change from white to amber, and flash. Refer to ADI Indications in 14-09-05 for details. NOTE: The on-side excessive deviation warning is also displayed when the cross-side system has detected an excessive deviation. Glide slope excessive deviation: If a glide slope deviation greater than approximately one dot is detected, the GS pointer will change from green to amber, the GS scale will change from white to amber, and flash. Refer to ADI Indications in 14-09-05 for details.

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Flight Guidance Control System

REVISION 21

AOM-1502-003

NOTE: The on-side excessive deviation warning is also displayed when the cross-side system has detected an excessive deviation.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

ILS APPROACH CHECK POINTS – 1500 ft RA – system starts trying to engage highest capability available.

AOM-1502-003

– 800 ft RA – system “freezes” highest capability available, no longer allowing approach “upgrades”.

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REVISION 21

Flight Guidance Control System

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SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

APPROACH SEQUENCE – CAT II HDG LOC

ALT GS

AP/AT ENGAGED IN HDG/ALT. AP HOLDING SELECTED HEADING AND ALTITUDE. AUTOTHROTTLE HOLDING SELECTED SPD. APP PUSHBUTTON ON GP PRESSED ARMING LOC/GS MODES. AP APPROACH STATUS ANNUNCIATOR SHOWS APPR2 ARMED.

APPR2 AP AT

LOC

APPR2 AP AT

LOC

SPD T

SPD T

SPD T

ALT GS

LOCALIZER CAPTURE.

GS GLIDESLOPE CAPTURE.

AP AT

APPR2 GS LOC

1500 ft · BETWEEN 1500 ft AND 800ft WHEN FLAP IS SET TO 5 WITH RA MINIMUMS SET TO CAT II, AP APPROACH STATUS ANNUNCIATOR SHOWS APPR2 IN GREEN. 800 ft

EM170AOM140417B.DGN

APPR2 AP SPD T AT

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Flight Guidance Control System

REVISION 21

AOM-1502-003

CAT II APPROACH

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

APPROACH SEQUENCE – CAT I APPR1 AP AT

SPD T

GS

LOC

GLIDESLOPE CAPTURE

SPD T 1500 ft

AP AT

APPR1 GS LOC

EM170AOM140418B.DGN

· BELOW 1500 ft WITH RA/BARO SET TO BARO, AP APPROACH STATUS ANNUNCIATOR SHOWS APPR1, ALLOWING CAT I APPROACH.

AOM-1502-003

CAT I APPROACH

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REVISION 21

Flight Guidance Control System

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SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

APPROACH SEQUENCE – CAT I (RA/BARO SET RA) Example: – Either BARO/RA window incorrectly set to RA. APPR1 ONLY AP AT

SPD T

APPR1 ONLY AP AT

GS

LOC

APPR1 GS LOC

SPD T

GLIDESLOPE CAPTURE

BELOW 1500 ft SINCE APPR2 IS NOT AVAILABLE DUE RA/BARO IS INCORRECTLY SET TO RA, AP APPROACH STATUS ANNUNCIATOR SHOWS APPR 1 ONLY AMBER IN BOTH FMAs (ASSOCIATED WITH BARO MIN DIGITAL READOUT AT PFD) AND APPR 1, IN GREEN.

1500 ft

SPD T 2O

2O

1O

1O

1O

1O

2O

2O

AP AT

APPR1 GS LOC

RA 26O

RA 26O

EM170AOM140416D.DGN

800 ft

APPR II NOT AVAILABLE

PREVIEW FEATURE The preview feature provides a transition from FMS navigation into ILS approach course (V/L). When FMS is selected as the primary navigation source the system automatically selects the ILS frequency and Localizer course when: !Airplanes Pre-Mod MAU load 23.1

– The airplane is within 25 NM from destination; " !Pre-mod MAU load 27.1

– The airplane is within 30 NM from destination;

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Flight Guidance Control System

REVISION 21

AOM-1502-003

"

– The PREV function is used;

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

– AUTO tuning is enabled on the MCDU radio page; – An ILS or BCprocedure is part of the active flight plan in the FMS. The PFD will automatically display the Localizer course if the PREVIEW MODE is selected with the ILS frequency already autotuned.

AOM-1502-003

NOTE: Depending on certain conditions of LOC interception, such as interception angle and speed, the FMS may inhibit LOC capture.

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REVISION 21

Flight Guidance Control System

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SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

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Flight Guidance Control System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

THRUST MANAGEMENT SYSTEM The thrust management system (TMS) interfaces with the flight guidance control system (FGCS) to control airplane speed and thrust. The TMS helps reduce fuel consumption and increase engine service life by limiting thrust, speed, and temperatures required for different phases of flight. The TMS consists of the following subfunctions: – autothrottle (AT) – thrust rating system (TRS) – thrust lever angle (TLA) trim.

AUTOTHROTTLE The autothrottle system (AT) moves the thrust levers to maintain the desired airspeed or thrust according to the appropriate mode. It has AT has various modes of operation to help maintain the airplane operation within the normal operational envelope. The AT is designed to operate in single engine condition with the same modes as in the dual engine condition. AUTOTHROTTLE OPERATION The AT sets the correct engine thrust with the synchronized N1 for its various operating modes. AUTOTHROTTLE ENGAGEMENT The AT engages on ground when all of the following conditions occur: – no AT active failures. – AT button pressed on the guidance panel. – both thrust levers above 50° TLA. The AT engages in flight when all of the following conditions occur: – no AT active failures. – AT button pressed on the guidance panel. – airplane at or above 400 ft AGL.

AOM-1502-003

NOTE: In order to maintain AT engaged, the thrust levers misalignment must be within the range equivalent to half of a thrust lever head diameter.

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REVISION 20

Thrust Management

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AUTOMATIC FLIGHT

LOW SPEED PROTECTION When engaged, the AT provides low speed protection according to the following logic: Altitude

Flaps 0 2% over amber Low Above 30000 ft Speed Awareness tape (LSA) Linear interpolation Between 20000 ft and between 1.2 Vs and 30000 ft 2% over LSA Below 20000 ft 1.2 Vs

Flaps 1 to Full

1.2 Vs

AUTOTHROTTLE NORMAL DISENGAGEMENT Normal AT disengagement is accomplished by pressing any of the AT disconnect buttons on the thrust levers. Alternatively, the AT is normally disengaged by pressing the AT button on the guidance panel. The AT is also automatically disengaged when one of the following conditions occurs: – after airplane touchdown – thrust levers beyond the TO/GA position – reverse thrust operation during RTO. NORMAL DISENGAGEMENT ANNUNCIATION – AURAL The aural alarm “THROTTLE” sounds when the AT is disengaged in flight. The aural alarm is cancelled by pressing the AT disconnect button on the thrust levers again. – FMA

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Thrust Management

REVISION 20

AOM-1502-003

The AT annunciation on the FMA flashes in green for 5 s.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AUTOTHROTTLE NON NORMAL DISENGAGEMENT The AT disengages when any of the following conditions occurs: – difference in TLA greater than 8° – autothrottle failure. NON NORMAL DISENGAGEMENT ANNUNCIATION – AURAL The “AUTOTHROTTLE” aural alarm sounds in flight. The aural alarm is cancelled by pressing any of the AT disconnect buttons on the thrust levers again. – FMA The AT annunciation on the FMA flashes in red. – EICAS The EICAS message AT FAIL is displayed. AUTOTHROTTLE MODES The AT modes are described as follows: – takeoff mode (TO) – takeoff hold mode (HOLD) – speed on thrust mode (SPDT) – Speed on Elevator (SPDE) – go-around mode (GA) – retard mode (RETD) – limited thrust (LIM) – override (OVRD). TAKEOFF MODE (TO) The TO mode is armed on ground pressing the AT button on the guidance panel.

AOM-1502-003

It engages when the thrust levers are beyond 50° of TLA.

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REVISION 20

Thrust Management

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AUTOMATIC FLIGHT

TAKEOFF HOLD MODE (HOLD) The HOLD mode prevents undesired thrust levers movement during the takeoff phase of flight. HOLD mode is engaged at or above 60 KIAS during the takeoff roll. The AT servos are de-energized and thrust lever movements are not commanded up to 400 ft AGL. SPEED ON THRUST MODE (SPDT) In this mode the system controls the selected airspeed adjusting the engine thrust by moving the thrust levers. The flight director vertical modes related to SPDT mode are: – flight path angle (FPA) – vertical speed (VS) – glide slope (GS) – VNAV path (PTH) – VGP (GP) – altitude hold (ALT) – altitude select (ASEL). The SPDT is also the AT mode when the FD is turned OFF (no active modes on FMA). SPEED ON ELEVATOR MODE (SPDE) The AT maintains a fixed thrust setting, and the flight director adjusts the pitch attitude to maintain the selected airspeed. For small altitude changes the AT commands only the necessary thrust in order to maintain a comfortable predetermined schedule based on vertical speed. For large altitude changes the AT commands: – idle thrust for descent – maximum thrust limited by the N1 target chevron. The vertical modes related to SPDE mode are: – overspeed (OVSP)

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Page 4

Thrust Management

REVISION 20

AOM-1502-003

– flight level change (FLCH)

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

– VNAV flight level change (FLCH magenta). NOTE: With the AT mode in SPDE and the AP disengaged, deviating from the flight director commands may lead to an undesired airspeed as the AT keeps the engine thrust at maximum or at idle and the pitch attitude change controls the airspeed. In this case, turn the flight director OFF to revert the AT to SPDT. This procedure is to have engine thrust controlling airspeed. GUST COMPENSATION

!MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

Gust compensation mode maintains a minimum of up to 5 kt above 1.2 Vs in gusty conditions with the AT engaged and slat/flap out of the ZERO position. "

GO-AROUND MODE (GA) The Go-Around thrust mode (GA) advances the thrust levers to the TO/GA position. RETARD MODE (RETD) The Retard mode reduces the thrust levers to the idle during flare on landing. The Retard mode arms when all of the following conditions occur: – radio altimeter with valid information – autothrottle engaged – slat/flap lever position at 5 or FULL and landing gear down – radio altitude below 150 ft AGL. Retard mode engages at or below 30 ft. In a normal flare, the Retard mode is scheduled to reduce thrust levers to idle so that idle thrust is achieved upon airplane touch down. LIMITED THRUST (LIM) Limited Thrust (LIM) is displayed on the FMA when the auto throttle authority is not sufficient to achieve or maintain the selected airspeed.

AOM-1502-003

LIM is associated with Speed on Thrust mode (SPDT).

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REVISION 20

Thrust Management

Page 5

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

OVERRIDE (OVRD) The AT can be overridden by moving the thrust levers in any direction without causing its disengagement. If the AT is overridden by a pilot, a green annunciation “OVRD” is displayed on the FMA. When the thrust levers are released the AT will once again return the thrust levers to their commanded position. AT SINGLE ENGINE OPERATION The AT deactivates the respective thrust lever when an engine failure occurs. The operating engine’s thrust lever remains active for AT operation.

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Thrust Management

REVISION 20

AOM-1502-003

Reducing the thrust lever to simulate an engine failure will cause AT disengagement due to a split in thrust lever position.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

TLA TRIM The TLA trim function synchronizes the engine N1 when the AT is disengaged.

AOM-1502-003

The TLA trim function is accessed through the THRUST RATING SELECT page on the MCDU. TLA trim default is ON whenever the AT system is disengaged.

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REVISION 20

Thrust Management

Page 7

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

THRUST RATING SELECTION The TRS determines the appropriate thrust rating upper limit based on the flight phase when in automatic rating mode or based on pilot selection when in manual rating mode. The selected thrust rating and thrust rating values are displayed on the EICAS. Automatic rating or one of the manual ratings are selected through the THRUST RATING SELECT page on the MCDU. The thrust ratings computed by the TRS are the following: – takeoff (TO) – go-around (GA) – climb 1 (CLB-1) – climb 2 (CLB-2) – cruise (CRZ) – continuous (CON).

TRS AUTO

TRS KEY

EM170AOM140385B.DGN

TRS MANUAL RATING SELECTION

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Thrust Management

REVISION 20

AOM-1502-003

THRUST RATING SELECT PAGE

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AUTOMATIC OPERATION On the THRUST RATING SELECT page, AUTO is the default mode after power up. When in this mode, the TRS determines the flight phase, the airplane configuration and the number of engines operative and automatically sets the appropriate thrust rating. At the right side of the AUTO label, the system shows between brackets which TRS mode is active according to system logic. The current thrust rating label is displayed on the EICAS between both engine N1 indicators.

AOM-1502-003

The resultant maximum N1 is displayed above the N1 indicators, and a chevron on each N1 dial provides the analog indication.

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REVISION 20

Thrust Management

Page 9

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AUTOMATIC FLIGHT

TAKEOFF THRUST RATING (TO) The TO thrust rating is set on the TO DATASET MENU page on the MCDU.

T/O DATASET MENU __K_

1/1

ATTCS

TO-1

OFF ON

__K_

REF ECS

__K_

REF A/I

TO-2

OFF ON

TO-3

OFF ENG ALL

TO TEMP

FLEX T/O

23 C

EM170AOM140845A.DGN

OFF ON

FLEX TEMP

39 C

ENTER

THRUST RATING SEL

TO DATA SET MENU PAGE

During takeoff, it is not possible to switch to another TRS mode on the MCDU until the airplane reaches 400 ft AGL. Below this altitude it is only possible to activate the RSV mode either automatically by the TRS or manually by setting the thrust levers to MAX position. CLIMB THRUST RATING (CLB) There are 2 climb modes labeled CLB 1 with highest thrust and CLB 2 with reduced thrust. The CLB 1 and CLB 2 logic is the following: – Climb 1 (CLB 1) is the default mode after the airplane power up.

This logic is to prevent the system from increasing thrust instead of reducing it during transition from TO to CLB after the takeoff.

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Thrust Management

REVISION 20

AOM-1502-003

– If the CLB 1 thrust is higher than the selected takeoff thrust (TO-X), the system automatically selects CLB 2 as the default until the next power down/power up.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

On the THRUST RATING SELECT page it is possible to switch from CLB 1 to CLB 2 with the system in automatic mode by selecting the desired mode on line select key 2R. On the ground this selection is only possible if the selected takeoff thrust (TO-X) is higher than CLB 1. Otherwise, only CLB 2 is available. During takeoff with flight director ON, the CLB mode is engaged when all of the following conditions occur: – landing gear retracted – airplane altitude above 400 ft AGL – any change in the flight director vertical mode. During takeoff with flight director OFF, the CLB mode is engaged when all of the following conditions occur: – landing gear retracted – airplane altitude above 3000 ft AGL. In flight, the CLB mode is engaged when the altitude preselector is set to an altitude higher than the current airplane altitude. CRUIZE THRUST RATING (CRZ) The CRZ mode is engaged when all of the following conditions occur: – Airplane is leveled at the altitude set on the altitude preselector for 90 s. !Airplanes Pre-Mod MAU load 23.1

– Airspeed is within 1 kt from the preselected airspeed. " !MAU load 23.1 and on

– Airspeed is within 5 kt (or 0.01 M) from the preselected airspeed.

AOM-1502-003

"

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REVISION 20

Thrust Management

Page 11

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

GO-AROUND THRUST RATING (GA) The GA mode is activated in flight whenever the landing gear and flaps are down. CONTINUOUS THRUST RATING (CON) During takeoff, the automatic transition from TO mode to CON only happens at 3000 ft AGL when in single engine condition.

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Thrust Management

REVISION 20

AOM-1502-003

In flight, anytime a single engine condition is recognized the TRS automatically sets CON mode.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

EICAS MESSAGES TYPE

MESSAGE AP FAIL AP PITCH MISTRIM

AP PITCH TRIM FAIL AP ROLL MISTRIM

AT FAIL AT NOT IN HOLD CAUTION

FD LATERAL MODE OFF FD VERT MODE OFF SHAKER ANTICIPATED

AOM-1502-003

STALL PROT FAIL

MEANING Autopilot function is inoperative. Pitch trim and autopilot commanding pitch trim control in opposite directions. Autopilot stabilizer trim is no longer operative. Roll trim and autopilot commanding roll trim control in opposite directions. Both AT have failed. Selected AT function is unavailable. AT not in TO Hold following the transition above 60 kt during TO roll and until the airplane transitions 400 ft AGL and GA. Disconnected lateral mode due to invalid conditions. Disconnected vertical mode due to invalid conditions. Indication that Shaker activation angles have been advanced to conservative settings. Stall Warning function and Stall Protection functions are inoperative.

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REVISION 10

EICAS Messages

Page 1

AUTOMATIC FLIGHT

TYPE

AIRPLANE OPERATIONS MANUAL

MESSAGE AFCS FAULT AFCS PANEL FAIL AFCS PANEL FAULT AP FAULT AP PITCH TRIM FAULT AP RUDDER NOT AVAIL APPR 2 NOT AVAIL

AT FAULT AUTOLAND 1 NOT ADVISORY AVAIL ENG TLA TRIM FAIL

FD FAIL FD FAULT HUD LVTO NOT AVAIL SHAKER 1 (2) FAIL STALL PROT FAULT

MEANING AFCS has detected a fault. Both channels of the GP have failed. A single channel of the GP has failed. The AP has one channel failed. The AP pitch trim has one channel failed. Autopilot rudder control is not available. The AP is not capable of a CAT II precision approach. The AT has one channel failed. System not capable to perform Autoland. Selected Sync function is unavailable due to an internal or required input failure.AT function is available. FD is inoperative. A single FD channel is inoperative. The HGS is not receiving the selected ILS system. Stall warning function has failed. AOA Miscompare Monitor (Stall Warning Subsystem) has failed.

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Page 2

EICAS Messages

REVISION 10

AOM-1502-003

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

TYPE

MESSAGE STALL PROT ICE SPEED

ADVISORY YD FAIL YD FAULT

AOM-1502-003

YD OFF

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

MEANING The reference speed has changed. Set reference speed to ice speed. Once the ice condition is detected, the system latches the ice condition active until 30 seconds after WOW becomes valid. Yaw damper function is inoperative. The yaw damper has one channel failed. Yaw damper function is off.

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REVISION 10

EICAS Messages

Page 3

SYSTEMS DESCRIPTION AUTOMATIC FLIGHT

AIRPLANE OPERATIONS MANUAL

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Page 4

EICAS Messages

REVISION 10

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUXILIARY POWER UNIT

SECTION 14-04 AUXILIARY POWER UNIT TABLE OF CONTENTS

AOM-1502-003

Block

Page

General Description............................................. 14-04-01 .... GENERAL DESCRIPTION..................................... 14-04-01 ....

1 1

Controls and Indications..................................... 14-04-05 .... APU CONTROL PANEL......................................... 14-04-05 .... EICAS INDICATION............................................... 14-04-05 ....

1 1 2

APU System Description..................................... 14-04-10 .... APU FUEL SUPPLY............................................... 14-04-10 .... APU BLEED........................................................... 14-04-10 .... APU OPERATION.................................................. 14-04-10 ....

1 1 1 1

EICAS Messages.................................................. 14-04-15 .... EICAS MESSAGES............................................... 14-04-15 ....

1 1

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REVISION 9

Table of Contents

Page 1

SYSTEMS DESCRIPTION AUXILIARY POWER UNIT

AIRPLANE OPERATIONS MANUAL

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Page 2

Table of Contents

REVISION 9

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUXILIARY POWER UNIT

GENERAL DESCRIPTION The Auxiliary Power Unit (APU) is a gas turbine engine located in the airplane tailcone, which provides pneumatic and electrical AC power. The pneumatic power is used for engine starting and to supply bleed air to the air conditioning packs of the Environmental Control System (ECS). An electrical AC generator supplies 115 V 40 kVA to the electrical system. The APU is automatically monitored and controlled through a dedicated Full Authority Digital Electronic Control (FADEC) unit.

AIR COOLER INLET BLEED DUCT AFT FIREWALL

APU ENGINE APS2300

APU AIR INLET SILENCER

EM170AOM140045.DGN

EXHAUST

AOM-1502-003

APU LOCATION

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REVISION 9

General Description

Page 1

SYSTEMS DESCRIPTION AUXILIARY POWER UNIT

AIRPLANE OPERATIONS MANUAL

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General Description

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUXILIARY POWER UNIT

APU CONTROL PANEL OVERHEAD PANEL

APU CONTROL 2 ON

EMER STOP

START

MASTER

EM170AOM140049.DGN

OFF

1

1 - APU SELECTOR KNOB (ROTARY ACTION) OFF: ON: START:

initiates normal APU shutdown. normal position when the APU is running. (momentary action) initiates the APU start cycle. When released, the switch moves to the ON position.

2 - APU EMERGENCY STOP BUTTON (GUARDED) closes the APU fuel shutoff valve, shutting down the APU with no cooldown period. A white striped bar illuminates on the lower half of the button. PUSH OUT: normal position, with the fuel shutoff valve open.

AOM-1502-003

PUSH IN:

NOTE: When an APU fire is detected, the upper half of the button illuminates red.

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REVISION 11

Controls and Indications

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AUXILIARY POWER UNIT

EICAS INDICATION

1 APU

1OO %

45O

C

2

EM170AOM140050.DGN

EICAS

1 - APU RPM INDICATION – Displays the APU RPM (%). GREEN: normal operating range. AMBER: cautionary operating range. RED: operating limit exceeded. 2 - APU EGT (EXHAUST GAS TEMPERATURE) INDICATION – Displays the APU temperature in degrees Celsius (°C). GREEN: normal operating range. AMBER: cautionary operating range.

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Page 2

Controls and Indications

REVISION 11

AOM-1502-003

RED: operating limit exceeded.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUXILIARY POWER UNIT

APU FUEL SUPPLY When only DC power is available, the DC fuel pump, located in the right wing tank, provides fuel to the APU. If AC power is available and the engine is not running, fuel will be provided by the AC fuel pump. When the engine is running, the ejector fuel pump provides fuel to the APU from the right wing tank. However, it is also possible to provide fuel to the APU from the left wing tank via a crossfeed valve.

APU BLEED The APU supplies bleed air on the ground or inflight. However, it is used primarily as a ground pneumatic source for the air conditioning packs (ECS) and engine starting. The Air Management System (AMS) controls the operation of the APU and engine bleed valves. For logic details refer to Section 14-02 (AMS).

APU OPERATION A dedicated Full Authority Digital Electronic Control (FADEC) monitors and controls the start/shutdown sequence, fault detection and APU status. The flight crew controls the normal APU start/shutdown sequence, using the APU selector knob. In an abnormal condition, the flight crew can shut down the APU through a dedicated emergency stop button. The APU is able to supply: – Electrical AC power up to 33000 ft. – Bleed air for engine starting up to 21000 ft. – Bleed air for air conditioning and pressurization up to 15000 ft.

AOM-1502-003

Maximum altitude for APU start is 30000 ft.

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REVISION 18

APU System Description

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AUXILIARY POWER UNIT

APU START Rotating the APU master switch to ON powers the FADEC and APU fuel shutoff valve opens. The APU indication on the EICAS changes from OFF to the APU control parameters (speed and EGT). NOTE: To avoid unsuccessful attempt start it is recommended to wait 30 s after the EICAS is energized to start the APU. Rotating the APU selector knob from ON to START (momentary position), initiates the APU automatic starting cycle. During the automatic starting cycle the FADEC commands the electronic starter controller to energize the brushless starter generator, initiating APU rotation. Three seconds after APU speed has reached 95%, electrical and pneumatic loading are available. If the APU does not reach proper speed or acceleration rate within the starting cycle time, the APU will automatically shut down. GROUND START The FADEC initiates ignition at approximately 6% rpm and the fuel flow after 0.5 s. The battery #2 energizes the electronic starter controller. After a light off occurs, the FADEC commands the starter to cutout at approximately 50% rpm. IN FLIGHT START The FADEC initiates ignition at approximately 7% to 17% rpm and the fuel flow after 0.5 s. After a light off occurs, the FADEC commands the starter to cutout at approximately 50% rpm.

APU SHUTDOWN NORMAL APU SHUTDOWN

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Page 2

APU System Description

REVISION 18

AOM-1502-003

Rotating the APU selector knob from ON to OFF initiates a normal APU shutdown, which is monitored and controlled by the FADEC. During a normal shutdown sequence, the APU pneumatic power is removed immediately and the electrical power is removed at the end of a 2 minutes cooldown period. The EICAS message APU SHUTTING DOWN disappears at the end of that period.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

AUXILIARY POWER UNIT

!APU FADEC 02.00 and on OR POST-MOD SB 170-49-0003

The cooldown period is 1 minute, followed by a spooldown period. The EICAS message APU SHUTTING DOWN disappears at the end of spooldown period. "

NOTE: Turning the APU selector knob back to ON position during the shutdown sequence cancels the shutdown. EMERGENCY APU SHUTDOWN In the event the APU emergency stop button has been selected, the APU fuel shutoff valve closes and the APU shuts down without a two-minute cooldown period.

APU PROTECTION The FADEC provides automatic APU shutdown protection on ground and in flight as follows. The appropriate EICAS message is displayed for each situation.

AOM-1502-003

On the ground Overspeed Underspeed FADEC critical fault APU fire APU EGT overtemperature APU high oil temperature APU low oil pressure Sensor fail

In flight Overspeed Underspeed FADEC critical fault -

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REVISION 18

APU System Description

Page 3

SYSTEMS DESCRIPTION AUXILIARY POWER UNIT

AIRPLANE OPERATIONS MANUAL

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Page 4

APU System Description

REVISION 18

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION AUXILIARY POWER UNIT

EICAS MESSAGES TYPE

MESSAGE APU FAIL

APU FAULT

APU OIL HI TEMP

CAUTION

APU OIL LO PRESS

AOM-1502-003

APU ALTITUDE EXCEED (Post-Mod. Load 21.2)

MEANING APU automatic shutdown has occurred. APU cannot be restarted, except if the automatic shutdown occurred during the starting cycle and according to the restriction defined in the AFM. APU automatic shutdown inhibited in-flight. An anomaly has been detected. Maintenance action is required. APU automatic shutdown inhibited in-flight. Oil temperature is above maximum limit. APU automatic shutdown inhibited in-flight. Oil pressure is below minimum limit. APU operational ceiling has been exceeded. For non-ETOPS airplanes, the airplane is flying at or above 33500 ft with the APU running. For ETOPS airplanes, the airplane is flying with the APU running at or above 37500 ft or above the maximum associated temperature for altitudes between 33000 ft and 37000 ft. Refer to APU limitations block 2-00-38.

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REVISION 9

EICAS Messages

Page 1

AUXILIARY POWER UNIT

TYPE

AIRPLANE OPERATIONS MANUAL

MESSAGE APU SHUTTING DOWN

STATUS

MEANING A normal APU shutdown has been commanded via the APU selector knob.

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Page 2

EICAS Messages

REVISION 9

AOM-1502-003

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

SECTION 14-05 ELECTRICAL TABLE OF CONTENTS Block

Page

General Description............................................. 14-05-01 .... GENERAL DESCRIPTION..................................... 14-05-01 ....

1 1

AOM-1502-003

Controls and Indications..................................... 14-05-05 .... 1 ELECTRICAL POWER CONTROLS AND INDICATIONS.................................................. 14-05-05 .... 1 ELECTRICAL AC POWER..................................... 14-05-05 .... 2 ELECTRICAL DC POWER.................................... 14-05-05 .... 4 RAM AIR TURBINE DEPLOYMENT HANDLE...... 14-05-05 .... 6 ELECTRICAL SYNOPTIC PAGE ON MFD........... 14-05-05 .... 7 STATUS PAGE ON MFD....................................... 14-05-05 .... 12 AC System............................................................ 14-05-10 .... AC ELECTRICAL POWER DESCRIPTION........... 14-05-10 .... AC COMPONENTS AND OPERATION................. 14-05-10 ....

1 1 2

DC System............................................................ 14-05-15 .... DC ELECTRICAL POWER DESCRIPTION.......... 14-05-15 .... DC COMPONENTS AND OPERATION................ 14-05-15 ....

1 1 2

Electrical Power Distribution and Control........ 14-05-20 .... ELECTRICAL POWER DISTRIBUTION AND CONTROL........................................................ 14-05-20 .... INTEGRATED CONTROL CENTER (ICC)............ 14-05-20 .... SECONDARY POWER DISTRIBUTION ASSEMBLIES (SPDA)..................................... 14-05-20 ....

1

Circuit Breakers................................................... 14-05-30 .... CIRCUIT BREAKERS (CB)................................... 14-05-30 .... CIRCUIT BREAKER PANEL.................................. 14-05-30 .... REMOTE CBS....................................................... 14-05-30 ....

1 1 1 5

Electrical Loads Distribution.............................. 14-05-35 .... AC/DC BUSSES LOAD DISTRIBUTION............... 14-05-35 ....

1 1

1 1 2

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REVISION 21

Table of Contents

Page 1

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

Block Page Electrical Distribution and System Configuration................................................. 14-05-40 .... 1 ELECTRICAL DISTRIBUTION AND SYSTEM CONFIGURATION........................................... 14-05-40 .... 1 1 1

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Page 2

Table of Contents

REVISION 21

AOM-1502-003

EICAS Messages.................................................. 14-05-45 .... EICAS MESSAGES............................................... 14-05-45 ....

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

GENERAL DESCRIPTION The Electrical System generates and distributes both AC and DC power to airplane systems. The AC system is composed of: • Two integrated drive generators (IDGs). • One auxiliary power unit (APU) generator. • One inverter.

• •

One ram air turbine (RAT). One AC external power unit.

The DC system is composed of: • Two NiCd batteries. • Three transformer rectifier units (TRU)s. • One DC external power input. Normal operation of the electrical system is automatic.

AOM-1502-003

Two independent networks provide complete segregation for electrical fault isolation purposes. In the event of a power-generating source failure, bus ties automatically connect between the networks with no significant operational degradation nor additional workload.

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REVISION 9

General Description

Page 1

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

14-05-01 Copyright © by Embraer. Refer to cover page for details.

Page 2

General Description

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ELECTRICAL INDICATIONS

POWER

ELECTRICAL

CONTROLS

AND

OVERHEAD PANEL

ELECTRIC AC POWER IDG 1

IDG 2

AUTO

AUTO

OFF

OFF

DISC

DISC

AC POWER

AC BUS 1

AC BUS 2 AC BUS TIES

GPU

APU GEN 1 OPEN

AVAIL

AUTO

2 OPEN

IN USE

DC POWER TRU 1

TRU 2 AUTO

OFF

OFF DC ESS BUS

DC BUS 2

BATT 1 ON OFF

DC BUS TIES AUTO

AUTO OFF

OFF AOM-1502-003

DC POWER

BATT 2 EM170AOM140064.DGN

DC BUS 1

TRU ESS AUTO

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REVISION 21

Controls and Indications

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ELECTRICAL

ELECTRICAL AC POWER

OVERHEAD PANEL

1

ELECTRIC AC POWER IDG 1

IDG 2

AUTO

AUTO

OFF

OFF

DISC

DISC

AC BUS 1

AC BUS 2 AC BUS TIES

GPU

APU GEN

AVAIL

AUTO

2 OPEN

IN USE

4

3

2

EM170AOM140235.DGN

1 OPEN

1 - IDG 1 AND IDG 2 SELECTOR KNOB allows automatic operation of the electrical system. opens the IDG contactor isolating the IDG from the respective AC BUS.

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Page 2

Controls and Indications

REVISION 21

AOM-1502-003

AUTO: OFF:

AIRPLANE OPERATIONS MANUAL DISC:

SYSTEMS DESCRIPTION ELECTRICAL

must be held in this position for one second to mechanically disconnect the IDG.

NOTE: The IDG fault indication LED associated with the EICAS message IDG 1 (2) OIL illuminates indicating to the flight crew which IDG must be disconnected. The LED extinguishes after IDG disconnection. 2 - APU GENERATOR BUTTON PUSH IN: allows automatic operation of the electrical system. PUSH OUT: opens the APU generator contactor and isolates the APU generator from the AC BUS TIE. 3 - AC BUS TIES SELECTOR KNOB 1 OPEN: AUTO: 2 OPEN:

opens the Bus Tie Contactor (BTC) 1, segregating AC BUS 1 from AC BUS 2. This position controls the operation of the BTCs, according to system operational logic. opens the Bus Tie Contactor (BTC) 2, segregating AC BUS 2 from AC BUS 1.

4 - GROUND POWER UNIT (GPU) BUTTON connects the AC GPU to the AC system, according to the source priority. PUSH OUT: isolates the AC GPU from the system. AVAIL: illuminates inside the button when the AC GPU is connected to the airplane and AC power quality requirements (voltage/amperage/frequency) are satisfied. IN USE: illuminates inside the button when the AC GPU is powering the airplane AC electrical system.

AOM-1502-003

PUSH IN:

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REVISION 21

Controls and Indications

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ELECTRICAL

ELECTRICAL DC POWER

OVERHEAD PANEL

1

DC POWER TRU 1

TRU ESS

TRU 2

AUTO

AUTO

OFF

OFF

2

2

DC ESS BUS

DC BUS 2

BATT 1 OFF

BATT 2 DC BUS TIES AUTO

AUTO

OFF

5

3

OFF

4

14-05-05 Copyright © by Embraer. Refer to cover page for details.

Page 4

Controls and Indications

REVISION 21

AOM-1502-003

ON

EM170AOM140234.DGN

DC BUS 1

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

1 - TRU ESS TOGGLE SWITCH AUTO: OFF:

allows automatic operation of the electrical system. isolates the TRU ESS from the ESS BUS 3.

2 - TRU 1 AND TRU 2 TOGGLE SWITCH AUTO: OFF:

allows automatic operation of the electrical system. isolates the TRU from the respective DC BUS.

3 - BATTERY 2 SELECTOR KNOB AUTO: OFF:

allows automatic operation of the electrical system. the battery supply power to the HOT BATT BUS 2 only and is no longer connected to the airplane electrical system.

4 - DC BUS TIE TOGGLE SWITCH AUTO: OFF:

allows automatic operation of the electrical system. opens both essential tie contactors (ETCs) and a DC tie contactor (DCTC).

5 - BATTERY 1 SELECTOR KNOB

AOM-1502-003

ON: OFF:

the battery is connected to the DC ESS BUS 1. the battery supply power to the HOT BATT BUS 1 only and is no longer connected to the airplane electrical system.

14-05-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 5

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

1

EM170AOM140351.DGN

RAM AIR TURBINE DEPLOYMENT HANDLE

1 - RAM AIR TURBINE DEPLOYMENT HANDLE

14-05-05 Copyright © by Embraer. Refer to cover page for details.

Page 6

Controls and Indications

REVISION 21

AOM-1502-003

– Manually deploys the Ram Air Turbine.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ELECTRICAL

ELECTRICAL SYNOPTIC PAGE ON MFD The electrical synoptic page provides a visual representation of the electrical system operation and parameters, and can be selected for viewing by the flight crew on either MFD.

MFD

2

Plan

Map

1 15V 4OO Hz 4O KVA

9

3

IDG 1

Systems

1 15V 4OO Hz 6O KVA

AC BUS 1

1 15V 4OO Hz 4O KVA

TRU 1

8

TRU ESS

TRU 2

DC ESS 3

DC ESS 2

APU START

BATT 2

IN USE BATT 1

DC GPU

7

AOM-1502-003

28 . O V 6O A

DC BUS 2

DC ESS 1

4

28 . O V 6O A

DC BUS 1

28 . O V 6O ° C

AC BUS 2

AC ESS AC STBY

1 15V 4OO Hz 4O KVA

1 15V 4OO Hz

RAT

28 . O V 6O A

IDG 2

APU

AC GPU

Elec

6

28 . O V 6O ° C

5

EM170AOM140061A.DGN

1

14-05-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 7

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

1 - IDG (INTEGRATED DRIVE GENERATOR) – The IDG icon and its outputs (voltage/frequency/amperage) are always displayed, even when readings are zero. If an output is invalid or out of range, the digits are replaced by three amber dashes. – IDG icon: GREEN: IDG available and the IDG selector knob in AUTO position. WHITE: IDG available and the IDG selector knob in OFF position, or the engine is not running. AMBER DASHED: invalid information. – IDG parameters (voltage, frequency and amperage): GREEN: for valid information. AMBER DASHED: for invalid information or a value out of the valid range. When IDG oil pressure drops below 140 psi ± 25 psi, or the IDG oil temperature reaches 335°F ± 10°F (168°C ± 5°C), the EICAS message IDG 1 (2) OIL is displayed and an amber led illuminates near the IDG selector knob on the overhead panel. This LED indicates which IDG must be disconnected. Manual IDG disconnection is achieved by selecting and holding the respective IDG knob to the DISC position for one second. NOTE: Do not hold IDG knob to the DISC position for more than three seconds. After IDG disconnection: – The EICAS message IDG 1 (2) OIL is displayed while the engine oil pressure or temperature are not within limits.

– The IDG fault indication LED extinguishes. The LED illuminates again after airplane power-down-power-up and engine start. In this case, repeat the disconnection procedure to extinguish the IDG fault indication LED.

14-05-05 Copyright © by Embraer. Refer to cover page for details.

Page 8

Controls and Indications

REVISION 21

AOM-1502-003

– The EICAS message IDG 1 (2) OFF BUS is displayed. This message extinguishes when the engine is turned off and it is displayed after the next engine start.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

2 - AC EXTERNAL POWER (AC GPU) – The AC GPU icon and its outputs (voltage/frequency/amperage) are displayed only when the AC GPU is connected and available. If any output is invalid or out of range, the digits are replaced by three amber dashes. – AC GPU icon: GREEN: AC GPU connected and the GPU button is pushed in. WHITE: AC GPU connected and the GPU button is pushed out. AMBER DASHED: invalid information. – AC GPU parameters: GREEN: AC GPU is available and the information is valid. AMBER DASHED: invalid information. 3 - APU – The APU icon and its outputs (voltage/frequency/amperage) are not displayed until the APU is available (3 seconds after 95% rpm). If any output is invalid or out of range, the digits are replaced by three amber dashes. – APU icon: GREEN: APU available and the APU GEN button pushed in. WHITE: APU available and the APU GEN button pushed out. AMBER DASHED: invalid information. NOTE: Whenever the EICAS CAUTION message APU FAIL is displayed, the APU icon will be white beneath an amber cross. – APU parameters (voltage/frequency/amperage): GREEN: for valid information. AMBER DASHED: for invalid information or a value out of the valid range.

AOM-1502-003

4 - ELECTRICAL BUSES – The electrical bus icons are always displayed.

14-05-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 9

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ELECTRICAL

– BUS icons: GREEN: energized bus. WHITE: de-energized bus. AMBER DASHED: invalid information. 5 - TRU (TRANSFORMER RECTIFIER UNIT) – The TRU icon and its outputs (voltage/amperage) are always displayed. – TRU icon: GREEN: TRU available, and the associated toggle switch is in AUTO position. WHITE: TRU available, and the associated toggle switch is in OFF position. AMBER DASHED: invalid information. NOTE: Whenever the EICAS CAUTION message TRU 1 (2) FAIL is displayed, the TRU icon will be white beneath an amber cross. – TRU parameters (voltage/amperage): GREEN: for valid information. AMBER DASHED: for invalid information or a value out of the valid range. 6 - BATTERIES – Battery icons and their outputs (voltage/temperature) are always displayed. – BATTERY icons: GREEN: voltages are greater than 18 V. WHITE: voltages are less than 18 V. AMBER DASHED: invalid information or a value out of the valid range.

GREEN: for valid information.

14-05-05 Copyright © by Embraer. Refer to cover page for details.

Page 10

Controls and Indications

REVISION 21

AOM-1502-003

– BATTERY parameters (voltage/temperature):

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

AMBER DASHED: for invalid information. 7 - DC EXTERNAL POWER (DC GPU) – The DC GPU icon is displayed only when the DC GPU is connected and available. – DC GPU icon: GREEN: DC GPU connected and available. AMBER DASHED: invalid information. NOTE: A white IN USE indication is displayed, centered above the DC GPU icon, whenever the DC GPU is connected and supplying power to the airplane electrical system. 8 - ELECTRICAL FLOW LINE – Flow line icons illustrate voltage sensing. – FLOW LINE icon: GREEN: voltage is sensed. WHITE: voltage is not sensed. AMBER DASHED: invalid information. 9 - RAT (RAM AIR TURBINE) – The RAT icon and its output (voltage and frequency) are displayed only when the RAT is deployed. – RAT icon: GREEN: RAT is deployed and operating. AMBER DASHED: invalid information. – RAT parameter (voltage and frequency): GREEN: for valid information.

AOM-1502-003

AMBER DASHED: for invalid information or a value out of the valid range.

14-05-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 11

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

STATUS PAGE ON MFD Batteries voltage is displayed on the synoptic status page. It can be selected by flight crew on either MFDs.

MFD

BATT1 28.O V 1

BATT2 28.O V

EM170AOM140494A.DGN

ELEC

1 - BATTERIES VOLTAGE INDICATION – Displays batteries 1 and 2 voltage. GREEN: valid battery voltage.

14-05-05 Copyright © by Embraer. Refer to cover page for details.

Page 12

Controls and Indications

REVISION 21

AOM-1502-003

AMBER DASHED: invalid information.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

AC ELECTRICAL POWER DESCRIPTION AC electrical power is the main source for airplane systems and comprises: • Two integrated drive generators (IDGs). • An auxiliary power unit (APU) generator. • A ram air turbine (RAT).

•

A static inverter (AC/DC inverter).

Both IDGs and the APU generator are rated at 40 kVA, 115 VAC, 400 Hz, three-phase. On ground, the APU AC generator or AC ground power unit (AC GPU) can supply power to all AC BUSES. The APU generator may also be used in flight, as a replacement to an IDG, according to the APU operational envelope. In flight, the RAT is used as an emergency generator, supplying power to the ESS BUSES when both AC BUSES 1 and 2 are not powered.

AC GPU

IDG 1

IDG 2 GROUND POWER UNIT

AC POWER

APU GEN

AOM-1502-003

30/40 kVA 115/200 VAC 400 Hz 3−phase

RAT

AC/DC INVERTER 250 VA

15 kVA 115/200 VAC 400 Hz 3−phase

EM170AOM140060.DGN

30/40 kVA 115/200 VAC 400 Hz 3−phase

14-05-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

AC System

Page 1

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

AC COMPONENTS AND OPERATION INTEGRATED DRIVE GENERATOR (IDG) Each engine has an IDG monitored and controlled by a dedicated generator control unit (GCU). When an engine starts, the IDG will automatically come on line, powering the respective AC BUS. The previous power source is disconnected from that AC BUS. For automatic operation of the electrical system, the IDG selector knob must be set to the AUTO position. Moving the selector knob to OFF position, the generator line contactor opens, tripping off-line and de-exciting the selected IDG. When the IDG oil pressure drops below 140 psi ± 25 psi, or the IDG oil temperature reaches 335°F ± 10°F (168°C ± 5°C), the EICAS message IDG 1 (2) OIL is displayed and an amber led illuminates near the IDG selector knob on the overhead panel. This led indicates which IDG must be disconnected and extinguishes after the IDG disconnection. Manual IDG disconnection is achieved by selecting the respective IDG knob to the DISC position and holding for one second. NOTE: Do not hold IDG knob to the DISC position for more than three seconds. Automatic IDG disconnection occurs when manual disconnection is not performed, and the IDG oil temperature reaches 366°F (185.6°C). In both cases, the disconnection is mechanical and the flight crew cannot reconnect the IDG.

APU GENERATOR Before engine starting, when the APU becomes available, the APU generator automatically connects to the AC BUS TIES, disconnecting the AC GPU.

14-05-10 Copyright © by Embraer. Refer to cover page for details.

Page 2

AC System

REVISION 20

AOM-1502-003

During the APU starting cycle, BATT 2 is isolated from the network, powering the APU START BUS exclusively. In flight, the APU can be started up within operational limits, and replaces any IDG sources with no operational degradation.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

AC EXTERNAL POWER SOURCE (AC GPU) The AC GPU button, located on the electrical system panel, controls the AC external power. Once the AC GPU is connected to the airplane and power quality requirements (voltage/amperage/frequency) are within accepted limits, an AVAIL light illuminates on the GPU button. The AC GPU has priority over the batteries to power the electrical system. Pushing the AC GPU button in connects external power to the AC BUS TIE, according to AC source priority. The AVAIL light extinguishes and an IN USE light illuminates. When the APU is started, the system operational logic automatically isolates the GPU from the AC BUS TIE. In this case, the IN USE light extinguishes and an AVAIL light illuminates on the GPU button. NOTE: Before disconnecting the AC GPU from the airplane, the flight crew must push out the AC GPU pushbutton, even if the IN USE light has already extinguished. The AC GPU pushbutton has to be pushed out for the next connection. Ground staff can connect the GPU directly to the AC/DC GND SVC BUSES for ground maintenance and flight preparation, by pushing the respective button located on the front ramp panel or on the flight attendant panel at the forward right galley.

INVERTER The static inverter (AC/DC inverter) converts 28 V DC power from batteries to 115 V AC power to supply the STANDBY AC BUS when an AC power source is not available.

RAM AIR TURBINE (RAT)

AOM-1502-003

The RAT is an AC electrical device installed in the airplane nose section, which converts the kinetic energy of airflow across the turbine into AC power. The electrical power produced is rated at 15 kVA, 115 V AC, 400 Hz, three-phase. Whenever AC power sources are not powering AC buses, the RAT is automatically deployed, and after 8 s, supplies power to the AC ESS BUS. Once deployed it will create a very loud noise due to the high rotation speed, and cannot be stowed back in flight, even if normal electrical power is reestablished. DC ESS BUSES are powered through the ESS TRU. To avoid total loss of power during this 8 s period, batteries are used as backup to power the DC ESS BUSES and the STANDBY AC BUS.

14-05-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

AC System

Page 3

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

The RAT electrical power drives the AC Motor-driven Pump (ACMP 3A) for primary flight control tasks. These include high lift system actuation and power for essential avionics, communication and battery recharging. In flight, there is no altitude restriction for RAT deployment. 130 kt is required to ensure the RAT continues supplying AC/DC ESS BUSES. At speeds below this, the RAT may only supply the AC ESS BUS, and the batteries will automatically provide electrical power to the DC ESS BUSES and the STANDBY AC BUS through the static inverter (AC/DC inverter). As airspeed decreases, load shedding occurs and the AC ESS BUS is no longer powered.

EM170AOM140063.DGN

In case of automatic RAT deployment failure, a deployment handle is provided to manually deploy the RAT.

14-05-10 Copyright © by Embraer. Refer to cover page for details.

Page 4

AC System

REVISION 20

AOM-1502-003

RAM AIR TURBINE

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

NO BREAK POWER TRANSFER (NBPT) The E-Jets Electrical System has a protection feature, the NBPT, which avoids electrical transient in case of power transfer when the airplane is on the ground. The NBPT allows the momentary paralleling between two AC power sources: the IDGs, GPU and the APU generator, at any possible combination.

AOM-1502-003

After achieving the auto-parallel condition, the system is able to parallel the sources for a short period (milliseconds). If the system does not achieve the auto-parallel requirements within the allowed time delay, the transfer will be concluded with a break-transfer of minimum power interruption.

14-05-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

AC System

Page 5

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

14-05-10 Copyright © by Embraer. Refer to cover page for details.

Page 6

AC System

REVISION 20

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

DC ELECTRICAL POWER DESCRIPTION The DC electrical system consists of: • Three transformer rectifier units (TRU)s; • Two batteries. On ground, a DC ground power unit (DC GPU) can be connected to the airplane supplying power to only the APU START BUS. The TRU, rated at 300 A, are used as a primary source of the DC electrical system, converting AC power from the AC BUSES into DC power. In certain conditions, batteries #1 and #2 are used to backup all DC ESS BUSES and the AC STBY BUS. Battery #2 also supplies the APU START BUS, during APU starting.

TRU 2

TRU 1

BATT 1

TRU ESS BATT 2

DC POWER

DC GPU

AOM-1502-003

GROUND POWER UNIT

BATTERIES 22.8 VDC 27 Ah

EM170AOM140059A.DGN

TRANSFORMER RECTIFIER UNIT

14-05-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

DC System

Page 1

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

DC COMPONENTS AND OPERATION TRANSFORMER RECTIFIER UNIT (TRU) Three TRUs convert 115 VAC power into 28 VDC. Each TRU works in isolation. If one of them fails, the BUSES automatically powers by the remaining TRUs, as long as the DC BUS TIES toggle switch is selected to AUTO. TRU 1 provides DC power to DC BUS 1, DC ESS BUS 1, DC GND SVC BUS, HOT BATT BUS 1 and battery #1 charging. TRU 2 provides DC power to DC BUS 2, DC ESS BUS 2, HOT BATT BUS 2 and battery #2 charging. TRU ESS provides DC power to DC ESS BUS 3.

BATTERIES Two NiCd 22.8 VDC, 27 A batteries power up the airplane and are also used as a backup for the DC essential electrical system. The batteries charges constantly by any AC source through the TRUs, including the AC GPU and the RAT. In an ELECTRICAL EMERGENCY, while the RAT is not fully deployed and also if RAT stall speed is reached, batteries supply essential loads for 10 min. Whenever the battery temperature reaches 70°C for at least 2 s, the associated indication becomes red and the EICAS WARNING message BATT 1 (2) OVERTEMP is triggered. The minimum battery #2 operating temperature for APU is -20°C.

14-05-15 Copyright © by Embraer. Refer to cover page for details.

Page 2

DC System

REVISION 20

AOM-1502-003

On ground, if the airplane is powered only by the batteries for more than 5 min, a horn sounds to alert the ground personnel.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

DC EXTERNAL POWER SOURCE (DC GPU) When DC GPU is connected during the APU starting cycle, the DC external power source, and not battery #2, provides 28 VDC power to the APU START BUS. The DC GPU is used when the battery is no longer available or the battery #2 temperature is below -20°C.

AOM-1502-003

A suitable DC GPU should be able to supply the APU start with at least 24 VDC and no more than 32 VDC, when in use. The voltage may be checked on the synoptic page on MFD.

14-05-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

DC System

Page 3

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

14-05-15 Copyright © by Embraer. Refer to cover page for details.

Page 4

DC System

REVISION 20

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

ELECTRICAL CONTROL

POWER

SYSTEMS DESCRIPTION ELECTRICAL

DISTRIBUTION

AND

Four Integrated Control Centers (ICCs) and two Secondary Power Distribution Assemblies (SPDAs) provide distribution and control of the electrical power, and interface with other systems.

INTEGRATED CONTROL CENTER (ICC) The ICC is an electrical-electronic integrated device, providing power distribution and protection for the airplane electrical loads, the secondary power distribution assemblies (SPDAs) and the circuit breakers that are located on the cockpit sidewall panels. A total of four ICCs are implemented in the electrical system. • Left Integrated Control Center (LICC).

• • •

Right Integrated Control Center (RICC). Emergency Integrated Control Center (EICC). Auxiliary Integrated Control Center (AICC).

Each ICC, installed in the electronics bay, incorporates thermal circuit breakers (CBs), line replaceable units (LRUs), line replaceable modules (LRMs) and AC/DC electrical buses. The LRUs and LRMs allow quick access and easy replacement of electrical components, thereby minimizing any delays due to maintenance servicing. AC/DC electrical buses are the primary source of electrical power distribution. These buses are located inside the respective ICCs: LICC

RICC

EICC

AICC

AC BUS 1

AC BUS 2

AC ESS BUS

HOT BATT BUS 2

AC GND SVC BUS

DC BUS 2

STBY AC BUS

APU START BUS

DC GND SVC BUS

DC ESS BUS 2

DC BUS 1

DC ESS BUS 1 DC ESS BUS 3

AOM-1502-003

HOT BATT BUS 1

14-05-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Electrical Power Distribution and Control

Page 1

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

SECONDARY POWER ASSEMBLIES (SPDA)

DISTRIBUTION

An SPDA is an electrical load management unit, which receives power from the ICC AC/DC electrical buses and distributes it to the airplane systems, according to system distribution logic. Two independent SPDAs replace thermal circuit breakers (CBs) and electromechanical relays used in other airplanes, thereby reducing the amount of electrical hardware as well as flight crew workload. SPDAs also have the advantage of integrating protection, logic/control and power supply. Each SPDA has a specific number of slots, into which different electronic modules are plugged. Each module has an associated function such as providing communication, data processing and power distribution. Communication modules use ARINC 429 to integrate SPDAs, ICCs and multi-function control units (MCDUs). Four independent DC BUSES power the SPDAs providing redundancy and ensuring system segregation:

• • • •

DC DC DC DC

SPDA1 BUS 1 ESS BUS 1 ESS BUS 2 GND SVC

SPDA2

• • • •

DC DC DC DC

BUS 2 ESS BUS 1 ESS BUS 2 GND SVC

SPDA 1 is located at the forward electronics bay and SPDA 2 is located at the center electronics bay. Each SPDA incorporates ELECTRONIC CBs (solid state power controllers - SSPC), which protect load distribution to the following systems. AMS Electrical Fuel Hydraulic Anti-ice Lighting

• • • • •

Oxygen Engine ignition and starting Water APU Fire protection

14-05-20 Copyright © by Embraer. Refer to cover page for details.

Page 2

Electrical Power Distribution and Control

REVISION 9

AOM-1502-003

• • • • • •

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

CIRCUIT BREAKERS (CB) Circuit Breakers are classified as either thermal or electronic CBs. Some thermal CBs are located on the cockpit sidewall panels and others inside the ICCs in the electronics bays. The electronic CBs are located inside the SPDAs, in the electronics bays. All CBs situated in the electronics bays are considered remote CBs. The flight crew can visually monitor all circuit breakers located inside the cockpit and, via MCDUs, the remote CBs in the electronics bays. The ICC remote thermal CBs can only be reset by maintenance personal when the airplane is on ground. The flight crew can reset the SPDA remote electronic CBs via the MCDU.

LOCATION Remote Non remote

Circuit breakers types and location TYPE THERMAL ELECTRONIC ICCs SPDAs Cockpit ------------

CIRCUIT BREAKER PANEL Columns and rows on the CB panel are identified through an alphanumeric naming convention.

AOM-1502-003

NOTE: Only the standard CB panel configuration is presented herein as an illustrative example.

14-05-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 16

Circuit Breakers

Page 1

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

LEFT COCKPIT CONSOLE

CIRCUIT BREAKER PANEL

14-05-30 Copyright © by Embraer. Refer to cover page for details.

Page 2

Circuit Breakers

REVISION 16

AOM-1502-003

CIRCUIT BREAKER PANEL

EM170AOM140289.DGN

RIGHT COCKPIT CONSOLE

AOM-1502-003

REVISION 16

Circuit Breakers

1

SMK DET CARGO AFT 1

5

2

SATCOM AMPL

3

WSHLD WIPER 2

LIGHT DOME

AC BUS 1

MISC SEAT ADJUST PILOT

5

1O

AMPL

PAX ADDRESS

5

CABIN INPH

5

FIREX CARGO PBA LT

PRESN CPCS CTRL 1B

DC ESS BUS 3

5

5

5

1O

LG TOWING LT PWR 2

FIREX

ENG 1A

4

ICE DET 1

5

DC COURTESY CEILING LIGHTS

ENGINE OIL LEVEL 1

5

ENG 2A

HYDR SOV SYS 1 HOT BATT BUS 1

5

FUEL ENG SOV 1

5

P-ACE 3 LWR RUD SEC

5

FBW BCK BATT

EM170AOM140233.DGN

G

F

E

D

C

B

A

G

F

E

D

C

B

A

G

F

E

D

C

B

A

5

5

5

6

FWD 1

5

5

5

8

9

1O

11

1O

7

LG

5

SYS 2 PWR 1

5

IRS 1 PWR 1

5

AUDIO 1

5

12

CPCS CTRL 2A

PRESN

CPCS CTRL 2B

5

SYS 1 PWR 1

5

MISC OXY MASK DEPLOY 2

BRK OUTBD

5

ENG 1 T2 HEATER

5 COMPASS

5

ENG 1 IGNITION

5

5 DME 1 NAV

VHF 1 COMM

1O

ELEC RAT BIT

LAV FWD

5

ENGINE

1A

5 ADF 1

MRC 1

5

5

FADEC

VOR/ILS 1

5

ELEC EDP PUMP SYS 2 SYS 3A HYDR

5

5 CLOCK

DISPLAY/ CONTROL

15 EICAS

5

G

F

E

D

C

B

5

G

F

E

D

C

B

5

5

EMER FWD BATT HTR

AP SERVOS

1

ROLL

5

PRESS IND SYS 2

5

CUST I/O 1B MAU 1

13

AIRCOND LOW LIMIT 1

5

14

ENG 1 A-I WIPER PRESS IND 2 ICE/RAIN PROT

5

PAX SIGNS

5

YAW 1

5

CTRL I/O 1

5 A

PITCH TRIM 1

A

5 1 SEC

FCM

5 4 PRI

CUST I/O 1A

LH OUTBD UPR RUD SEC ELEV PRI P-ACE 1 FLIGHT CONTROLS DC ESS BUS 1

FUEL QTY 1

FWD 2 CARGO SMK DET

5

5

CHAN A1

2A

AFCS

ENG 1 OIL PRESS

5

CHAN A2

5

MASTER AURAL WRN 1 CAUT 1 ALERTS

2O PWR 1 MAU 1

2O PWR 2

5 P-ACE 3 RH OUTBD ELEV PRI

5 FLAP ACE 1

5

5

5

5

MCDU 1

ELEC PUMP SYS 2

AIRSTAR MISC

15

IND

5

PRESN

5 STATIC PORT

5

16

ACTR

17

5

5

2 SEC FCM

18

PRINTER

1O

CHART

5

ADS 1 PROBE 1A-2A

5

COMM AUDIO 3

5

NAV

5

5

ADS FC PROBE 1B-2B

5

PFD 1

15

3 PRI

15

5

ENGINE THRUST CTRL 1

5

IRS 2 PWR 2

5

MFD 2

19

2O

FUEL REFUELING 1

5

FAN AIR BLEED 1 INLET AUX RLY DOOR 1 BLEED

CCD 2 DISPLAY/CONTROL

MAIN PNL

MLS 1

DCU 2

5

LH INBD RH INBD ELEV PRI ELEV SEC P-ACE 2 FLIGHT CONTROLS DC BUS 1

FLASH FWD PEDESTAL CHARGER LIGHTS

5

PITCH 1

5

HYDR

PTU

5

PWR 3

2O

SLAT ACE 1

AIRPLANE OPERATIONS MANUAL SYSTEMS DESCRIPTION ELECTRICAL

LEFT STANDARD CB PANEL

Copyright © by Embraer. Refer to cover page for details.

14-05-30

Page 3

Page 4

Circuit Breakers

Copyright © by Embraer. Refer to cover page for details.

14-05-30

REVISION 16

AOM-1502-003

5

5

5

21

22

REFUELING DEFUELING 2 FUEL

5

FAN AIR BLEED 2 INLET DOOR 2 AUX RLY BLEED

5

MLS 2

23

GALLEY 1 CTRL

5

FLOOD/ OVHD PNL STORM LIGHTS

5

AIRSTAIR

5

ADS 2 PROBE 4A NAV

5

HF RX/EX

IRS 2 PWR 1

HF COUPLER COMM

5

EM170AOM140290.DGN

G

F

E

D

15

DISPLAY PFD 2

FCM

5

24

GALLEY 2 CTRL

READING

5

25

DMU

2O

5

SMK DET RECIRC FAN

5

TOWING LT PWR 1 LG

5

PITCH 2

PRESS IND SYS 1

5

PWR 2 PRI

26

5

5

27

AIRSTAIR ACTR BKUP

IRS 1 PWR 2

5

COMM AUDIO 2

5

5

5

28

AIRCOND LOW LIMIT 2

G

F

G

F

29

PRESN CPCS CTRL 1A

5

5 E

15 MFD 1

SYS 2 PWR 2

E

D

C

B

A

5 3 SEC

ENGINE THRUST CTRL 2

D

C

B

A

5

YAW 2

ENG 2 A-1 WIPER PRESS IND 1 ICE/RAIN PROT

5

NWS

5 CUST I/O 2B

MAU 3

ROLL 2 AP SERVOS

PWR 2

2O

5 PEDAL ADJUST

5 VENTRAL AIR BRAKE

PRA/MUSIC MISC

AUTOBRAKE

5

AFCS PANEL PWR 2

5

SYS 1 SYS 3B ELEC PUMP HYDR

5

2O

PWR 1 MAU 2

5

CTL I/O 2

DC BUS 2

P-ACE 1 FLIGHT CONTROLS

5

UPR RUD PRI

LG

FCM

5

5

5

3O

FUEL QTY 2

5

SYS 1 PWR 2

31

BRK INBD

5

ENG 2 T2 HEATER

5

32

FIREX

NAV

APU

ELT

ENGINE

ENG 2 1B FADEC

5

33

FUEL SOV

5

TX

AFCS

5

5

ENG 2 OIL PRESS

5

CHAN B2

5

MAU 2 PWR 2 SEC

2O

PITCH TRIM 2

34

35

FWD 3 AFT 2 CARGO SMK DET

5

2B

CHAN B1

5

HYDR EDP SYS 1

MASTER WRN CAUT 2

AURAL 2

5

5

PWR 1

2O

5

PROBE PROBE 3B 4B ADS 3/STBY NAV

5

5 CUST I/O 2A MAU 3

5 SLAT ACE 2

5 ALERTS

INTREGATED STBY

5

FLIGHT CONTROLS DC ESS BUS 2

5 P-ACE 3 LWR RUD PRI

5 RH INBD ELEV PRI

P-ACE 2

5 LH INBD ELEV SEC

MCDU CCD 2 1 DISPLAY/CONTROL

5

2 PRI

G G

F F

E E

D D

C C

B B

A A

5

36

CMC

5

ENG 2B

37

ICE DET 2

FIREX

ENGINE OIL LEVEL 2

5

ENG 1B

FUEL ENG SOV 2 HOT BATT BUS 2

5

5 UPR RUD PRI

5 RH INBD ELEV PRI

38

5

39

PC OUTLET

MISC

NAV

HYDR PRESS IND SYS 3

AC BUS 2

WSHLD WIPER 1

5

4O

SEAT ADJUST COPILOT

PROBE 3 HEATER PWR

25

LIGHTS ANNUN TEST

P-ACE3 RH OUTBD ELEV SEC FLIGHT CONTROLS DC ESS BUS 3

OXY MASC DEPLOY 1

1O

ADS 2 PROBE 3A

5

LG EXT OVRD

5

FLAP ACE 2

5

BACKUP HOT BATT BUS FCS

LH OUTBD ELEV SEC

ELECTRICAL

C

B

A

5

LH OUTBD ELEV SEC

5

4 SEC

5

1 PRI

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

RIGHT STANDARD CB PANEL

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

REMOTE CBS The flight crew can visually monitor remote circuit breakers located inside the electronics bays through the MCDU CB page by pressing the CB function key on the MCDU. Regardless of the page currently displayed on the MCDU, the page OUT/LOCK displays. CB MENU status page is achieved when the line select key 6L is pressed. The following options are presented:

• •

OUT/LOCK (1L): displays all OUT or LOCKED CBs.

•

CB BY BUS (3L): displays the status of CBs associated with the selected BUS.

• •

FUSE (4L): displays fuse status.

CB BY SYS (2L): displays the status of CBs associated with the selected system.

MAINT (5L): maintenance page.

The CB MENU page displays “NEW TRIP” on line select key 6R when a CB/SSPC trip occurs. Pressing the key (6R) displays the tripped CB/SSPC on the OUT/LOCK page. Pressing the line select key on left side of respective tripped remote CB/SSPC, sets the CB/SSPC condition to acknowledged and extinguishes the EICAS message REMOTE CB TRIP.

AOM-1502-003

NOTE: CB menu status page is for CB status monitoring only. Report maintenance when a CB trip occurs.

14-05-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 16

Circuit Breakers

Page 5

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

OUT/LOCK

NO CBS OUT/LOCKED

CB MENU

CB MENU

1 / 1

OUT/LOCK CB BY SYS CB BY BUS

MAINT

EM170AOM140514A.DGN

FUSE

14-05-30 Copyright © by Embraer. Refer to cover page for details.

Page 6

Circuit Breakers

REVISION 16

AOM-1502-003

CB MENU PAGE ON MCDU

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

AC/DC BUSSES LOAD DISTRIBUTION The following list identifies the electrical buses and the equipment powered by them. An asterisk (*) precedes optional equipment. DC BUS 1 ACMP 2B COMMAND AFT ENTRANCE LIGHTS AFT FLASH LIGHTS CHARGER / AFT LAV LIGHTS *

AIRSTAIR ACTUATOR COCKPIT CHART LIGHTS COCKPIT MAIN PANEL LIGHTING COCKPIT PEDESTAL LIGHTING COPILOT CURSOR CONTROL DEVICE COPILOT MFD CURSOR CONTROL DEVICE 2 DIGITAL AUDIO CONTROL PANEL 3

*

EFB 1 (Canadian Marconi Company - CMC)

*

EFB 1 or EFB 2 (Goodrich) EMERGENCY LIGHTS POWER UNITS (ELPU) ENGINE 1 THRUST QUADRANT ENGINE 1 THRUST REV LEVER SW ENGINE 1 NACELLE ANTI-ICE VALVE FWD FLASH LIGHT CHARGER / WARDROBE LIGHT FWD LAV LIGHTS FWD LAV / RECIRCULATION FWD / MAIN ENTRANCE LIGHTS

*

GALLEY AREA LIGHTS

*

GALLEY G3 CONTROL GASPER VALVE GUIDANCE PANEL 2 (DISPLAY CONTROLLER 2) HS-ACE CH 1 LEFT IDLE LOCK SOLENOID LH FLIGHT ATTND READING LT 1 COMMAND LH FLIGHT ATTND READING LT 2 COMMAND LH FLIGHT ATTND SEAT READING LT

AOM-1502-003

MAU 1 FCM 1 PWR B

14-05-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Electrical Loads Distribution

Page 1

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

DC BUS 1 MAU 1 FCM 2 PWR B MAU 1 PWR SUPPLY 3 MICRO IRU 2 (PWR 2) *

MLS RECEIVER 1 OXYGEN DEPLOY 1 P-ACE #2-1 LEFT INBOARD ELEVATOR (P) P-ACE #2-2 RIGHT INBOARD ELEVATOR (S) PASSENGER SIGNS PILOT MCDU PILOT PFD PITOT / STATIC / AOA1 HEATER PWR PITOT / STATIC / AOA1 SENSOR PITOT / STATIC / AOA2 HEATER PWR PITOT / STATIC / AOA2 SENSOR

*

PRINTER RADIO ALTIMETER 1 READING LIGHTS AFT LEFT READING LIGHTS FWD LEFT REFUEL 1 RH FLIGHT ATTND SEAT READING LT

*

SATCOM SF-ACE 1 SLAT CH 1 DC FEED SPDA 1 PWR SUPPLY FEED 1 TAT 1 HEATER PWR

*

VHF COMM MOD 3 WATER AND WASTE SYSTEM CONTROLLER PWR 2 WEATHER RADAR CONTROL 1 WEATHER RADAR RECEIVER / TRANSMITTER (WEATHER RADAR / ANTENNA) WINDSHIELD HEATER 2 CONTROL WINDSHIELD WIPER 2 CONTROL

14-05-35 Copyright © by Embraer. Refer to cover page for details.

Page 2

Electrical Loads Distribution

REVISION 21

AOM-1502-003

WING INSPECTION LIGHTS

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

DC BUS 2 ACMP 1B COMMAND ACMP 3B COMMAND *

ADF MODULE 2

*

AIRSTAIR LIGHTS

*

AUTO-BRAKE MODULE CARGO SOV COCKPIT FLOOD / STORM LIGHTS COCKPIT OVERHEAD PANEL LIGHTING COCKPIT READING LIGHTS COPILOT PFD DEFUEL DME MODULE 2

*

DMU

*

EFB 2 (Canadian Marconi Company - CMC) ENGINE 2 THRUST quadrant ENGINE 2 THRUST REV LEVER SW ENGINE 2 NACELLE ANTI-ICE VALVE COMMAND FDR / CVR 1 (DVDR 1)

*

GALLEY G1 CONTROL

*

GALLEY G2 CONTROL GUIDANCE PANEL 2 (GP2) HF RECEIVER / EMITTER (Single HF) HF RECEIVER / EMITTER 2 (Dual HF)

*

INFLIGHT ENTERTAINMENT LOGOTYPE LIGHTS MAU 2 PWR 2 PRIMARY MAU 2 PWR SUPPLY 1 MAU 3 FCM 3 PWR B MAU 3 FCM 4 PWR B MAU 3 PWR SUPPLY 2 MICRO IRU 2 (PWR 1)

*

MLS RECEIVER 2 MODE S DIVERSITY TRANSPONDER MOD 2

AOM-1502-003

NAVIGATION MODULE 2 NOSEWHEEL STEERING

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REVISION 21

Electrical Loads Distribution

Page 3

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

DC BUS 2 OXYGEN DEPLOY 2 P-ACE #1-1 LEFT OUT ELEVATOR (S) P-ACE #1-2 UPPER RUDDER (P) PEDALS ADJUSTMENTS PITOT / STATIC / AOA4 HEATER PWR PITOT / STATIC / AOA4 SENSOR *

PRE-RECORDED ANNOUNCEMENT

*

RADIO ALTIMETER 2 READING LIGHTS AFT RIGHT READING LIGHTS FWD RIGHT REFUEL 2 RIGHT IDLE LOCK SOLENOID ROLL TRIM SMOKE DET RECIRC FAN SPDA 2 PWR SUPPLY FEED 1 TAT 2 HEATER PWR TCAS VHF COMM MOD 2 WINDSHIELD HEATER 1 CONTROL

14-05-35 Copyright © by Embraer. Refer to cover page for details.

Page 4

Electrical Loads Distribution

REVISION 21

AOM-1502-003

WINDSHIELD WIPER 1 CONTROL

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

DC ESS BUS 1 ACMP 3A COMMAND ADF MODULE 1 AFT CARGO BAY BOTTLE 1 ELECTRO-EXPLOSIVE DEVICE FEED 2 FWD CARGO BAY BOTTLE 1 ELECTRO-EXPLOSIVE DEVICE FEED 2 AFT CARGO BAY BOTTLE 2 ELECTRO-EXPLOSIVE DEVICE FEED 2 FWD CARGO BAY BOTTLE 2 ELECTRO-EXPLOSIVE DEVICE FEED 2 AFT FLIGHT ATTND PANEL INDICATION LEDS APU FADEC AFCS CH 1A (AIOP 1A) AFCS CH 2A (AIOP 2A) BRAKE CONTROL MODULE 1 BRAKE CONTROL SOV OUTBOARD MOD1 BRAKE SOV SWITCHED OUTBOARD CABIN PRESSURIZATION CONTROL SYSTEM CONTROLLER 2A CABIN PRESSURIZATION CONTROL SYSTEM CONTROLLER 2B CLOCK COMPASS DC APU / ENGINE PUMP COMMAND DIGITAL AUDIO CONTROL PANEL 1 DME MODULE 1 *

DOOR SILL HEATER COMMAND EICAS ENGINE 1 EXCITER 1A COMMAND ENGINE 1 START VALVE ENGINE 1 T2 HEATER ENGINE 1 OIL PRESSURE FADEC 1 CH A FEED 1 & FEED 2 FADEC 2 CH A FEED 1 & FEED 2 FDR ACCELEROMETER FUEL QUANTITY 1

*

FWD GALLEY HEATER COMMAND

AOM-1502-003

FWD LAV SMOKE DETECTOR *

GALLEY 2 FEED 1 COMMAND

*

GALLEY 3 FEED 4 COMMAND GUIDANCE PANEL 1 (GP1)

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REVISION 21

Electrical Loads Distribution

Page 5

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

DC ESS BUS 1 IDG1 DISCONNECT SOLENOID INTEGRATED STANDBY INVERTER DC FEED LANDING GEAR SYS 1 PWR 1 LANDING GEAR SYS 2 PWR 1 MAU 1 FCM 1 PWR A MAU 1 FCM 2 PWR A MAU 1 PWR SUPPLY 1 MAU 1 PWR SUPPLY 2 MICRO IRU 1 (PWR 1) MODE S DIVERSITY TRANSPONDER MOD 1 NAVIGATION MODULE 1 P-ACE #1-1 LEFT OUT ELEVATOR (P) P-ACE #1-2 UPPER RUDDER (S) P-ACE #3-1 RIGHT OUT ELEVATOR (P) PAX OXY DEPLOY 1 (MANUAL) PILOT MASTER WRN / CAUTION 1 PITOT / STATIC / AOA4 COMMAND RAT BIT RAT DEPLOY SOLENOID RIGHT SMOKE DET F1-CARGO BAY RIGHT SMOKE DET F2-CARGO BAY SF-ACE 1 FLAP CH 1 DC FEED SPDA 1 PWR SUPPLY FEED 3 SPDA 2 PWR SUPPLY FEED 3

14-05-35 Copyright © by Embraer. Refer to cover page for details.

Page 6

Electrical Loads Distribution

REVISION 21

AOM-1502-003

VHF COMM MOD 1

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

DC ESS BUS 2 AC FUEL PUMP 1 COMMAND AC FUEL PUMP 2 COMMAND ADS 3 / STBY PROBE 4B *

AFT FLIGHT ATTND PANEL GALLEY MASTER SW OUT

*

AFT GALLEY HEATER COMMAND AFT LAV SMOKE DET APU FIRE DETECTION APU FIRE EXTINGUISH APU FUEL SOV AFCS CH 1B (AIOP 1B) AFCS CH 2B (AIOP 2B) BRAKE CONTROL SOV INBOARD MOD 2 BRAKE CONTROL MODULE 2 BRAKE SOV SWITCHED INBOARD CABIN PRESSURIZATION CONTROL SYSTEM CONTROLLER 1A COPILOT MASTER WRN / CAUTION 2 COPILOT MCDU CURSOR CONTROL DEVICE 1 DC APU / ENGINE PUMP DIGITAL AUDIO CONTROL PANEL 2

*

EFB 1 or EFB 2 (Goodrich)

*

ELT (TRANSMITTER)

*

ELT NAV UNIT ENGINE 2 EXCITER 2A COMMAND ENGINE 2 START VALVE ENGINE 2 T2 HEATER ENGINE 2 OIL PRESSURE FADEC 1 CH B FEED1 & FEED2 FADEC 2 CH B FEED1 & FEED2 FDR / CVR 2 (DVDR 2) FUEL QUANTITY 2 GUIDANCE PANEL 1 (DISPLAY CONTROLLER 1) HS-ACE CH 2

AOM-1502-003

HS-ACE CH 2 PWR INTEGRATED STANDBY

14-05-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Electrical Loads Distribution

Page 7

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

DC ESS BUS 2 LEFT SMOKE DET A2-CARGO BAY LEFT SMOKE DET F3-CARGO BAY LANDING GEAR SYS 1 PWR 2 LANDING GEAR SYS 2 PWR 1 MAU 2 PWR SUPPLY 2 MAU 3 FCM 3 PWR A MAU 3 FCM 4 PWR A MAU 3 PWR SUPPLY 1 MICRO IRU 1 (PWR 2) P-ACE #2-1 LEFT INBOARD ELEVATOR (S) P-ACE #2-2 RIGHT INBOARD ELEVATOR (P) P-ACE #3-2 LOWER RUDDER ACT (P) PILOT CURSOR CONTROL DEVICE PILOT MFD PITOT / STATIC / AOA1 AND AOA2 COMMANDS PITOT / STATIC / AOA3 HEATER PWR PITOT / STATIC / AOA3 SENSOR RAM AIR DOOR 1 SF-ACE 2 SLAT CH 2 DC FEED SMOKE DET TEST SPDA1 PWR SUPPLY FEED 2 SPDA2 PWR SUPPLY FEED 2

14-05-35 Copyright © by Embraer. Refer to cover page for details.

Page 8

Electrical Loads Distribution

REVISION 21

AOM-1502-003

VALVE APU FEED MOTOR OPERATED SHUTOFF FUEL

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

DC ESS BUS 3 ADS 2 PROBE 3A CABIN INTERPHONE (PA HANDSET) CABIN PRESSURIZATION CONTROL SYSTEM CONTROLLER 1B COCKPIT DOME LIGHTS COCKPIT PUSH BUTTON LIGHTS CROSS FEED VALVE FIREX SWITCHES AFT CARGO BAY BOTTLE 1 ELECTRO-EXPLOSIVE DEVICE FEED 1 FWD CARGO BAY BOTTLE 1 ELECTRO-EXPLOSIVE DEVICE FEED 1 AFT CARGO BAY BOTTLE 2 ELECTRO-EXPLOSIVE DEVICE FEED 1 FWD CARGO BAY BOTTLE 2 ELECTRO-EXPLOSIVE DEVICE FEED 1 HF RECEIVER / EMITTER 1 (Dual HF) IDG 2 DISCONNECT SOLENOID LANDING GEAR LEVER LOCK LANDING GEAR OVERRIDE SWITCH MID EMERG FAN COMMAND P-ACE #3-1 RIGHT OUT ELEVATOR (S) P-ACE #3-2 LOWER RUDDER ACT (S) PAX OXY DEPLOY 2 (OVRD COMMAND) PROBE 3 HEATER PWR 2 RAM AIR DOOR 2 RIGHT SMOKE DET A1-CARGO BAY RUDDER TRIM SEAT 1 ADJUSTMENT SEAT 2 ADJUSTMENT

AOM-1502-003

SF-ACE 2 FLAP CH 2 DC FEED

14-05-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Electrical Loads Distribution

Page 9

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

DC GND SVC AFT CARGO COMPARTMENT LIGHTS AFT CARGO LOADING LIGHTS AFT ENTRANCE LIGHTS AFT FLASH LIGHTS CHARGER / AFT LAV LIGHTS AFT LAV LIGHT COURTESY LIGHTS FWD CARGO LIGHTS FWD LAV LIGHTS FWD / MAIN ENTRANCE LIGHTS *

GALLEY AREA LIGHTS SERVICE COMPARTMENT LIGHTS AFT / FWD SPDA 1 PWR SUPPLY FEED 4 SPDA 2 PWR SUPPLY FEED 4

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Page 10

Electrical Loads Distribution

REVISION 21

AOM-1502-003

WATER AND WASTE SYSTEM CONTROLLER PWR1

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

DC HOT BAT BUS 1 BATTERY 1 COURTESY / SERVICE LIGHTS FWD DC CEILING LIGHTS ENGINE 1 OIL LEVEL INDICATION ENGINE 1A FIRE EXTINGUISH ENGINE 2A FIRE EXTINGUISH ENGINE FUEL SOV 1

AOM-1502-003

HYD SYS SOV 1

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REVISION 21

Electrical Loads Distribution

Page 11

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

DC HOT BAT BUS 2 BATTERY 2 CMC ENGINE 1B FIRE EXTINGUISH ENGINE 2 OIL LEVEL INDICATION ENGINE 2B FIRE EXTINGUISH ENGINE FUEL SOV 2 HYD SYS SOV 2 PANEL REFUEL 3

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Page 12

Electrical Loads Distribution

REVISION 21

AOM-1502-003

WATER AND WASTE SYSTEM CONTROLLER PWR 3

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

APU BUS

AOM-1502-003

APU START

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REVISION 21

Electrical Loads Distribution

Page 13

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

AC BUS 1 AC FUEL PUMP 1 ACMP 2B ENGINE 1 EXCITER 1B *

FAN CARGO BAY

*

GALLEY 2 FEED 1 (COFFEE MAKER)

*

GALLEY 3 FEED 4 (STEAM OVEN) GREEN / WHITE STBY POSITION LT’S RIGHT ICE DET 1 LEFT LANDING LIGHT LEFT RECIRC FAN LEFT TAXI LIGHT RED BEACON LIGHT UPPER / LOWER RED / WHITE STBY POSITION LT’S LEFT SF-ACE 1 SLAT CH 1 AC FEED WINDSHIELD HEATER 2 PWR

14-05-35 Copyright © by Embraer. Refer to cover page for details.

Page 14

Electrical Loads Distribution

REVISION 21

AOM-1502-003

WINDSHIELD WIPER 2 PWR

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

AC BUS 2 ACMP 1B ACMP 3B *

AFT DOOR SILL HEATER

*

AFT GALLEY HEATER

*

COCKPIT LAPTOP AC OUTLETS ENGINE 2 EXCITER 2B FAN 2 FWD BAY FAN 2 MID BAY

*

FWD DOOR SILL HEATER

*

GALLEY 2 FEED 3 (STEAM OVEN 1)

*

GALLEY 3 FEED 1 (COFFEE MAKER)

*

GALLEY 3 FEED 2 HOT JUG OR WATER BOILER

*

GALLEY 3 FEED 5 (CHILLER) GREEN / WHITE MAIN POSITION LT’S RIGHT ICE DET 2 RED / WHITE MAIN POSITION LT’S LEFT RIGHT LANDING LIGHT RIGHT TAXI LIGHT SF-ACE 2 FLAP CH 2 AC FEED STROBE LIGHTS WHITE LH / RH WINDSHIELD HEATER 1 PWR

AOM-1502-003

WINDSHIELD WIPER 1 PWR

14-05-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Electrical Loads Distribution

Page 15

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

AC ESS BUS AC FUEL PUMP 2A ACMP 3A SF-ACE 1 FLAP CH 1 AC FEED

14-05-35 Copyright © by Embraer. Refer to cover page for details.

Page 16

Electrical Loads Distribution

REVISION 21

AOM-1502-003

SF-ACE 2 SLAT CH 2 AC FEED

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

AC GND SVC AC OUTLET PWR1 AC OUTLET PWR2 CEILING LIGHTS DRAIN MAST AFT DRAIN MAST FWD FAN 1 FWD BAY FAN 1 MID BAY *

GALLEY 1 FEED 2 (AC OUTLET)

*

GALLEY 3 FEED 2 (AC OUTLET) NOSE LANDING LIGHT NOSE TAXI LIGHT RAT HEATER SIDEWALL LIGHTS VACUUM MOTOR GEN WATER COMPRESSOR WATER HEATER AFT LAV

AOM-1502-003

WATER HEATER FWD LAV

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REVISION 21

Electrical Loads Distribution

Page 17

SYSTEMS DESCRIPTION ELECTRICAL

AIRPLANE OPERATIONS MANUAL

STBY AC BUS ENGINE 1 EXCITER 1A

14-05-35 Copyright © by Embraer. Refer to cover page for details.

Page 18

Electrical Loads Distribution

REVISION 21

AOM-1502-003

ENGINE 2 EXCITER 2A

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

ELECTRICAL DISTRIBUTION AND SYSTEM CONFIGURATION The electrical system normal and some abnormal operations are automatic.

ELECTRICAL SYSTEM BASIC DISTRIBUTION ELECTRICAL POWER GENERATORS The electrical power generated from the IDG, APU, GPU or batteries is directed to the electrical buses. SPDA From the electrical buses the power is directed to the airplane systems and components through the SPDA. The SPDA works as circuit breaker or relay interfacing the electrical buses with the airplane systems and components. MAU The airplane systems that require a complex logic for the normal operation are connected to the MAUs which have the ability to process various inputs and define either ON / OFF or OPEN / CLOSE status for a specific system. Some airplane components have an alternate direct connection with the electrical buses allowing normal operation even in the event of a SPDA or MAU failure.

ELECTRICAL SYSTEM BUSES POWER SOURCE

ELECTRICAL BUS AC BUS 1 AC BUS 2

AOM-1502-003

AC ESS

ELECTRICAL POWER SOURCE NON-NORMAL NORMAL SOURCE SOURCE IDG 1, APU or AC AC BUS 2 GPU on ground. IDG 2, APU or AC AC BUS 1 GPU on ground. AC BUS 1 AC BUS 2 RAT (electrical emergency)

14-05-40 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Electrical Distribution and System Configuration

Page 1

SYSTEMS DESCRIPTION ELECTRICAL

ELECTRICAL POWER SOURCE NON-NORMAL NORMAL SOURCE SOURCE AC ESS INVERTER AC BUS 1 or AC N/A GPU on ground. TRU 1 via AC BUS 1 DC BUS 2 TRU 2 via AC BUS 2 DC BUS 1 DC BUS 1 DC ESS 3 DC BUS 2 DC ESS 3 TRU ESS through the DC ESS 1 or DC AC ESS ESS 2 BATTERY 2 N/A BATTERY 1 N/A BATTERY 2 N/A TRU 1 through the N/A AC GPU.

ELECTRICAL BUS AC STBY AC GND SVC DC DC DC DC

AIRPLANE OPERATIONS MANUAL

BUS 1 BUS 2 ESS 1 ESS 2

DC ESS 3 APU START BUS HOT BATT 1 HOT BATT 2 DC GND SVC

ELECTRICAL SYSTEM NORMAL OPERATION After the initial power up the electrical system is design to operate in automatic mode provided all switches on the electrical panel are in AUTO or ON position. The source priority order for powering the airplane is:

• • • •

Respective IDG. APU generator. GPU (on ground without APU). Opposite IDG.

If required the DC GPU can be used for the APU start.

ELECTRICAL SYSTEM ABNORMAL OPERATION

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Page 2

Electrical Distribution and System Configuration

REVISION 9

AOM-1502-003

If a power-generating source fails, the electrical system redirects power from another available source according to the priority order.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

AC BUSES If one of the AC power sources fails, both AC electrical networks are automatically connected by bus tie contactors (BTCs). One AC power source is sufficient to supply the whole system without significant degradation or additional workload. LOAD SHED For overload protection whenever the electrical load increases beyond the system limit the SPDA commands the load shedding protection. The components turned off by the load shedding are:

• •

Galleys and; Right windshield heating.

When possible the electrical system restores the electrical power to deprived components. TRU FAILURE In case of a TRU failure the respective DC BUS is automatically powered connected to the DC electrical network through both essential tie contactors (ETCs) and a DC tie contactor (DCTC) according to the system logic. TOTAL AC POWER SOURCE FAILURE In the event of a total loss of AC power the RAT is automatically deployed and it powers all ESS BUSES.

SYSTEM CONFIGURATIONS

AOM-1502-003

The following are some important examples of electrical load distribution achieved by the system logic.

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REVISION 9

Electrical Distribution and System Configuration

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ELECTRICAL

ELECTRICAL NETWORK UNPOWERED IDG 1

IDG 2

APU GEN

AC GPU

LICC

RICC BTC2

BTC1 AC BUS 1

AC BUS 2 RAT GEN EICC

AC GND SVC TRU1

TRU2

AC ESS BUS

DC GND SVC AC STBY BUS

TRU ESS

DCTC DC BUS 1

DC BUS2

ETC1

ETC2

DC ESS BUS1

DC ESS BUS3

DC ESS BUS2

AICC

+

APU START BUS

−

HOT BATT BUS 2

+

BATT 1 TO APU START

−

BATT 2

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Page 4

Electrical Distribution and System Configuration

REVISION 9

AOM-1502-003

DC INVERTER 250VA AC

DC GPU

EM170AOM140065A.DGN

HOT BATT BUS1

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

BATTERIES ONLY/APU START IN PROGRESS IDG 1

IDG 2

APU GEN

AC GPU

LICC

RICC BTC2

BTC1 AC BUS 1

AC BUS 2 RAT GEN EICC

AC GND SVC TRU1

TRU2

AC ESS BUS

DC GND SVC AC STBY BUS

TRU ESS

DCTC DC BUS2

DC BUS 1

ETC1

ETC2 DC ESS BUS3

DC ESS BUS1

DC ESS BUS2

AICC

AOM-1502-003

DC INVERTER 250VA AC

+

DC GPU

APU START BUS

−

HOT BATT BUS 2

+

BATT 1 TO APU START

−

BATT 2

EM170AOM140066A.DGN

HOT BATT BUS1

14-05-40 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Electrical Distribution and System Configuration

Page 5

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ELECTRICAL

AC GPU IDG 1

IDG 2

APU GEN

AC GPU

LICC

RICC BTC2

BTC1 AC BUS 1

AC BUS 2 RAT GEN EICC

AC GND SVC TRU1

TRU2

AC ESS BUS

DC GND SVC AC STBY BUS

TRU ESS

DCTC DC BUS2

DC BUS 1

ETC1

ETC2

DC ESS BUS1

DC ESS BUS3

DC ESS BUS2

AICC

+

APU START BUS

−

HOT BATT BUS 2

+

BATT 1 TO APU START

−

BATT 2

14-05-40 Copyright © by Embraer. Refer to cover page for details.

Page 6

Electrical Distribution and System Configuration

REVISION 9

AOM-1502-003

DC INVERTER 250VA AC

DC GPU

EM170AOM140067C.DGN

HOT BATT BUS1

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

APU POWER IDG 1

IDG 2

APU GEN

AC GPU

LICC

RICC BTC2

BTC1 AC BUS 1

AC BUS 2 RAT GEN EICC

AC GND SVC TRU1

TRU2

AC ESS BUS

DC GND SVC AC STBY BUS

TRU ESS

DCTC DC BUS2

DC BUS 1

ETC1

ETC2 DC ESS BUS3

DC ESS BUS1

DC ESS BUS2

AICC

AOM-1502-003

DC INVERTER 250VA AC

+

DC GPU

APU START BUS

−

HOT BATT BUS 2

+

BATT 1 TO APU START

−

BATT 2

EM170AOM140068C.DGN

HOT BATT BUS1

14-05-40 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Electrical Distribution and System Configuration

Page 7

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ELECTRICAL

GROUND SERVICE MODE IDG 1

IDG 2

APU GEN

AC GPU

LICC

RICC BTC2

BTC1 AC BUS 1

AC BUS 2 RAT GEN EICC

AC GND SVC TRU1

TRU2

AC ESS BUS

DC GND SVC AC STBY BUS

TRU ESS

DCTC DC BUS2

DC BUS 1

ETC1

ETC2

DC ESS BUS1

DC ESS BUS3

DC ESS BUS2

AICC

+

APU START BUS

−

HOT BATT BUS 2

+

BATT 1 TO APU START

−

BATT 2

14-05-40 Copyright © by Embraer. Refer to cover page for details.

Page 8

Electrical Distribution and System Configuration

REVISION 9

AOM-1502-003

DC INVERTER 250VA AC

DC GPU

EM170AOM140069A.DGN

HOT BATT BUS1

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

TWO IDG POWER IDG 1

IDG 2

APU GEN

AC GPU

LICC

RICC BTC2

BTC1 AC BUS 1

AC BUS 2 RAT GEN EICC

AC GND SVC TRU1

TRU2

AC ESS BUS

DC GND SVC AC STBY BUS

TRU ESS

DCTC DC BUS2

DC BUS 1

ETC1

ETC2

DC ESS BUS1

DC ESS BUS3

DC ESS BUS2

AICC

AOM-1502-003

DC INVERTER 250VA AC

+

DC GPU

APU START BUS

−

HOT BATT BUS 2

+

BATT 1 TO APU START

−

BATT 2

EM170AOM140070B.DGN

HOT BATT BUS1

14-05-40 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Electrical Distribution and System Configuration

Page 9

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ELECTRICAL

IDG FAILED AND APU GENERATOR IN USE IDG 1

IDG 2

APU GEN

AC GPU

LICC

RICC BTC2

BTC1 AC BUS 1

AC BUS 2 RAT GEN EICC

AC GND SVC TRU1

TRU2

AC ESS BUS

DC GND SVC AC STBY BUS

TRU ESS

DCTC DC BUS2

DC BUS 1

ETC1

ETC2

DC ESS BUS1

DC ESS BUS3

DC ESS BUS2

AICC

+

APU START BUS

−

HOT BATT BUS 2

+

BATT 1 TO APU START

−

BATT 2

14-05-40 Copyright © by Embraer. Refer to cover page for details.

Page 10

Electrical Distribution and System Configuration

REVISION 9

AOM-1502-003

DC INVERTER 250VA AC

DC GPU

EM170AOM140071B.DGN

HOT BATT BUS1

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

IDG FAILED AND APU GENERATOR NOT IN USE IDG 1

IDG 2

APU GEN

AC GPU

LICC

RICC BTC2

BTC1 AC BUS 1

AC BUS 2 RAT GEN EICC

AC GND SVC TRU1

TRU2

AC ESS BUS

DC GND SVC AC STBY BUS

TRU ESS

DCTC DC BUS2

DC BUS 1

ETC1

ETC2

DC ESS BUS1

DC ESS BUS3

DC ESS BUS2

AICC

AOM-1502-003

DC INVERTER 250VA AC

+

DC GPU

APU START BUS

−

HOT BATT BUS 2

+

BATT 1 TO APU START

−

BATT 2

EM170AOM140072C.DGN

HOT BATT BUS1

14-05-40 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Electrical Distribution and System Configuration

Page 11

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ELECTRICAL

RAT POWER IDG 1

IDG 2

APU GEN

AC GPU

LICC

RICC BTC2

BTC1 AC BUS 1

AC BUS 2 RAT GEN EICC

AC GND SVC TRU1

TRU2

AC ESS BUS

DC GND SVC AC STBY BUS

TRU ESS

DCTC DC BUS2

DC BUS 1

ETC1

ETC2

DC ESS BUS1

DC ESS BUS3

DC ESS BUS2

AICC

+

APU START BUS

−

HOT BATT BUS 2

+

BATT 1 TO APU START

−

BATT 2

14-05-40 Copyright © by Embraer. Refer to cover page for details.

Page 12

Electrical Distribution and System Configuration

REVISION 9

AOM-1502-003

DC INVERTER 250VA AC

DC GPU

EM170AOM140073C.DGN

HOT BATT BUS1

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

TRU FAILED IDG 1

IDG 2

APU GEN

AC GPU

LICC

RICC BTC2

BTC1 AC BUS 1

AC BUS 2 RAT GEN EICC

AC GND SVC TRU1

TRU2

AC ESS BUS

DC GND SVC AC STBY BUS

TRU ESS

DCTC DC BUS 1

DC BUS2

ETC1

ETC2

DC ESS BUS1

DC ESS BUS3

DC ESS BUS2

AICC

AOM-1502-003

DC INVERTER 250VA AC

+

DC GPU

APU START BUS

−

HOT BATT BUS 2

+

BATT 1 TO APU START

−

BATT 2

EM170AOM140074B.DGN

HOT BATT BUS1

14-05-40 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Electrical Distribution and System Configuration

Page 13

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ELECTRICAL

AC BUS OFF IDG 1

IDG 2

APU GEN

AC GPU

LICC

RICC BTC2

BTC1 AC BUS 1

AC BUS 2 RAT GEN EICC

AC GND SVC TRU1

TRU2

AC ESS BUS

DC GND SVC AC STBY BUS

TRU ESS

DCTC DC BUS2

DC BUS 1

ETC1

ETC2

DC ESS BUS1

DC ESS BUS3

DC ESS BUS2

AICC

+

APU START BUS

−

HOT BATT BUS 2

+

BATT 1 TO APU START

−

BATT 2

14-05-40 Copyright © by Embraer. Refer to cover page for details.

Page 14

Electrical Distribution and System Configuration

REVISION 9

AOM-1502-003

DC INVERTER 250VA AC

DC GPU

EM170AOM140075B.DGN

HOT BATT BUS1

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

DC BUS OFF IDG 1

IDG 2

APU GEN

AC GPU

LICC

RICC BTC2

BTC1 AC BUS 1

AC BUS 2 RAT GEN EICC

AC GND SVC TRU1

TRU2

AC ESS BUS

DC GND SVC AC STBY BUS

TRU ESS

DCTC DC BUS 1

DC BUS2

ETC1

ETC2

DC ESS BUS1

DC ESS BUS3

DC ESS BUS2

AICC

AOM-1502-003

DC INVERTER 250VA AC

+

DC GPU

APU START BUS

−

HOT BATT BUS 2

+

BATT 1 TO APU START

−

BATT 2

EM170AOM140076B.DGN

HOT BATT BUS1

14-05-40 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Electrical Distribution and System Configuration

Page 15

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ELECTRICAL

DC ESS BUS OFF

IDG 1

IDG 2

APU GEN

AC GPU

LICC

RICC BTC2

BTC1 AC BUS 1

AC BUS 2 RAT GEN EICC

AC GND SVC TRU1

TRU2

AC ESS BUS

DC GND SVC AC STBY BUS

TRU ESS

DCTC DC BUS2

DC BUS 1

ETC1

ETC2 DC ESS BUS3

DC ESS BUS1

DC ESS BUS2

AICC

+

−

HOT BATT BUS 2

+

BATT 1 TO APU START

−

BATT 2

14-05-40 Copyright © by Embraer. Refer to cover page for details.

Page 16

Electrical Distribution and System Configuration

REVISION 9

AOM-1502-003

DC INVERTER 250VA AC

APU START BUS

EM170AOM140077B.DGN

HOT BATT BUS1

DC GPU

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ELECTRICAL

EICAS MESSAGES MESSAGE MEANING BATT 1 (2) OVERTEMP Associated battery temperature is above 70°C. BATT 1-2 OFF Battery #1 and #2 are isolated from the electrical network. BATT DISCHARGING Batteries are discharging in WARNING an electrical emergency with no RAT assistance, or on ground when the battery is the only power source supplying the airplane. ELEC EMERGENCY In flight, AC main buses are de-energized. AC BUS 1 (2) OFF Associated AC BUS is de-energized. AC ESS BUS OFF AC ESS BUS is de-energized. AC STBY BUS OFF AC STBY BUS is de-energized. APU GEN OFF BUS APU generator failure or APU GEN button is pushed out. CAUTION BATT 1 (2) Associated battery is DISCHARGING discharging due to electrical system automation failure, or when battery is the only source supplying the system. BATT 1 (2) OFF Associated battery is isolated from the electrical network. BATT 1 (2) TEMP SENS A discrepancy between FAULT battery sensors has been detected.

AOM-1502-003

TYPE

14-05-45 Copyright © by Embraer. Refer to cover page for details.

REVISION 10

EICAS Messages

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

TYPE

MESSAGE DC BUS 1 (2) OFF DC ESS BUS 1 (2) (3) OFF GPU CONNECTED

IDG 1 (2) OFF BUS CAUTION

IDG 1 (2) OIL

INVERTER FAIL

RAT FAIL

TRU 1 (2) (ESS) FAIL LOAD SHED REMOTE CB TRIP ADVISORY SPDA FAIL

MEANING Associated DC BUS is de-energized. Associated DC ESS BUS is de-energized. AC or DC GPU connected (AVAIL or IN USE indication turned on) and parking brake released. IDG failure or IDG control knob is turned OFF. High oil temperature or low oil pressure has been detected. An inverter failure has been detected during power up built-in test. A failure was detected during power up built-in test in a RAT system component. An associated TRU failure has been detected. Load shed automatically commanded. A remote thermal or electronic CB has been tripped. A significant failure has been detected.

14-05-45 Copyright © by Embraer. Refer to cover page for details.

Page 2

EICAS Messages

REVISION 10

AOM-1502-003

ELECTRICAL

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ENGINE

SECTION 14-06 ENGINE TABLE OF CONTENTS Block

Page

General Description............................................. 14-06-01 .... GENERAL DESCRIPTION..................................... 14-06-01 ....

1 1

AOM-1502-003

Controls and Indications..................................... 14-06-05 .... 1 CONTROL PEDESTAL.......................................... 14-06-05 .... 1 FIRE HANDLE....................................................... 14-06-05 .... 2 ENGINE CONTROL PANEL.................................. 14-06-05 .... 3 EICAS INDICATION............................................... 14-06-05 .... 5 STATUS PAGE....................................................... 14-06-05 .... 11 MCDU INDICATION............................................... 14-06-05 .... 11 Engine Fuel System............................................. 14-06-10 .... ENGINE FUEL SYSTEM....................................... 14-06-10 .... FUEL PUMP........................................................... 14-06-10 .... FUEL/OIL HEAT EXCHANGER............................. 14-06-10 .... FUEL METERING UNIT......................................... 14-06-10 .... FUEL FILTER......................................................... 14-06-10 .... VARIABLE GEOMETRY ACTUATOR.................... 14-06-10 .... FUEL INJECTORS................................................. 14-06-10 .... FUEL SCHEMATIC................................................ 14-06-10 ....

1 1 1 1 1 1 1 2 3

Lubrication System.............................................. 14-06-15 .... LUBRICATION SYSTEM....................................... 14-06-15 .... OIL TANK............................................................... 14-06-15 .... OIL PUMPS............................................................ 14-06-15 .... OIL FILTER............................................................ 14-06-15 .... LUBRICATION SCHEMATIC................................. 14-06-15 ....

1 1 1 1 1 2

Start and Ignition System................................... 14-06-20 .... STARTING AND IGNITION SYSTEMS................. 14-06-20 .... IGNITION SYSTEM............................................... 14-06-20 .... STARTER OPERATION......................................... 14-06-20 ....

1 1 1 1

14-06-TOC Copyright © by Embraer. Refer to cover page for details.

REVISION 16

Table of Contents

Page 1

SYSTEMS DESCRIPTION ENGINE

AIRPLANE OPERATIONS MANUAL

Block Page GROUND START................................................... 14-06-20 .... 2 IN FLIGHT START................................................. 14-06-20 .... 2 AUTO RELIGHT..................................................... 14-06-20 .... 2 Thrust Reverser.................................................... 14-06-25 .... THRUST REVERSER SYSTEM............................ 14-06-25 .... THRUST REVERSER OPERATION...................... 14-06-25 ....

1 1 1

Engine Control System....................................... 14-06-30 .... ENGINE CONTROL SYSTEM............................... 14-06-30 .... FULL AUTHORITY DIGITAL ELECTRONIC CONTROL (FADEC)........................................ 14-06-30 .... AUTOMATIC TAKEOFF THRUST CONTROL SYSTEM (ATTCS)........................................... 14-06-30 .... FLEXIBLE TAKEOFF............................................. 14-06-30 .... ENGINE THRUST RATINGS................................. 14-06-30 .... ENGINE PROTECTION......................................... 14-06-30 ....

1 1

EICAS Messages.................................................. 14-06-35 .... EICAS MESSAGES............................................... 14-06-35 ....

1 1

1

14-06-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 16

AOM-1502-003

2 5 5 9

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ENGINE

GENERAL DESCRIPTION Two wing-mounted General Electric CF34-8E engines produce power to the airplane. The General Electric CF34-8E is a high-bypass and dual rotor turbofan, fully integrated with a nacelle and thrust reverse. The N1 and N2 rotors are mechanically and independently operated. The engine is controlled via a dual channel FADEC system providing flexible engine operation and reduced workload. Engine indications and alerts are displayed on the Engine Indication and Crew Alerting System (EICAS).

AGB MODULE FAN (N1 ROTOR SPEED)

HPT MODULE

COMBUSTION LINER AND STAGE 1 NOZZE ASSEMBLY COMPRESSOR (N2 ROTOR SPEED)

LPT MODULE

EM170AOM140078.DGN

COLD SECTION MODULE

AOM-1502-003

CF34-8E ENGINE

14-06-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 16

General Description

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ENGINE

OVRD 115 VAC

OVRD 115 VAC

EXCITER A

ENG 2 EXCITER 1A RLY STAT

EXCITER B

SOV ENG 1 EXCITER 1A RLY STAT

EDP

ENG 1 EXCITER A CMD

IGNITERS

ENGINE 1 CF34−8E

SPDA 1

ENG 2 EXCITER A CMD

ATS

ENG 1 FADEC IGNITION CHANNEL A

SCV

START/STOP RUN START

STOP

ASCB

ENG 2 FADEC IGNITION CHANNEL A

28 VDC

FADEC 1 CH A

BLEED SYSTEM

EICC

IGNITION AUTO OVRD

OFF

MAU 1 ARINC 429

FADEC 1 CH B

FADEC 2 CH A

IGNITION AUTO OVRD

MAU 3

OFF FADEC 2 CH B 28 VDC

MAU 2

SCV

START/STOP RUN START

STOP

ENG 1 FADEC IGNITION CHANNEL B

ATS

ENG 2 FADEC IGNITION CHANNEL B

SOV EDP IGNITERS

SPDA 2

ENGINE 2

ENG 1 IGNITION EXCITER 1B PHASE A

CF34−8E EXCITER B

115 VAC

ENGINE 2 IGNITER EXCITER 2B PHASE A ENG 2 START VALVE ENG 1 START VALVE

EM170AOM140250A.DGN

EXCITER A

115 VAC

14-06-01 Copyright © by Embraer. Refer to cover page for details.

Page 2

General Description

REVISION 16

AOM-1502-003

ENGINE SCHEMATIC

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ENGINE

CONTROL PEDESTAL

1

EM170AOM140084.DGN

2

1 - THRUST LEVER DETENTS MAX:

AOM-1502-003

TO/GA:

provides the maximum thrust rating available for dual or single engine operation. selects takeoff, maximum continuous, and go-around mode settings.

14-06-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 19

Controls and Indications

Page 1

SYSTEMS DESCRIPTION ENGINE

AIRPLANE OPERATIONS MANUAL

IDLE:

selects flight idle, approach idle, final approach idle and ground idle thrust settings. MIN REV: provides minimum reverse thrust. MAX REV: provides maximum reverse thrust. The thrust lever must be pulled against a spring to achieve the MAX REV position. If the thrust lever is released it goes back to MIN REV position. NOTE: Positioning the thrust lever between the thrust control quadrant detents selects intermediate thrust settings. 2 - THRUST REVERSER TRIGGER – Pulling the thrust reverser trigger allows reverser activation on the ground and REV thrust commands from IDLE to MAX REV. For TOGA and A/T DISC buttons descriptions, refer to Section 14-03 – Automatic Flight.

FIRE HANDLE

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Page 2

Controls and Indications

REVISION 19

AOM-1502-003

The Fire Handle, located on the Fire Protection Control Panel, enables emergency engine shutdown. For further information on fire protection system controls, refer to Section 14-07 − Fire Protection.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ENGINE

ENGINE CONTROL PANEL CONTROL PEDESTAL

POWERPLANT START/STOP

RUN

RUN STOP

START

STOP

START

1

2

1 IGNITION

AUTO OVRD

OFF

OFF

OVRD

2

1

2

EM170AOM140085.DGN

AUTO

1 - START/STOP SELECTOR KNOB STOP:

RUN: START:

commands the FADEC to shut down the engine, provided the associated thrust lever is in the IDLE position. NOTE: For airplanes Post-Mod FADEC 5.40, normal engine shutdown on ground is possible with the associated thrust lever at maximum 5° above the IDLE position. However, the EICAS message ENG 1(2) TLA NOT IDLE is displayed. normal position for engine operation. (momentary action) initiates the engine start sequence.

AOM-1502-003

2 - IGNITION SELECTOR KNOB

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REVISION 19

Controls and Indications

Page 3

SYSTEMS DESCRIPTION

OFF: AUTO: OVRD:

AIRPLANE OPERATIONS MANUAL

deactivates the ignition system. On ground, fuel flow is inhibited. FADEC disregards OFF position in flight. FADEC automatically controls the ignition system, depending on engine requirements. enables FADEC to continuously activate both exciters when the engine is running.

14-06-05 Copyright © by Embraer. Refer to cover page for details.

Page 4

Controls and Indications

REVISION 19

AOM-1502-003

ENGINE

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ENGINE

EICAS INDICATION

EICAS

4

5

7

FLEX TO-2 ATTCS 39

96.O 3 FAIL OO.O

6

96.O 8 4

2 N1

9

FAIL INDICATION

8O.O

8O.O

N1

REV

OFF

10

REV

11 OO.O

12

OFF INDICATION

1

WML

7OO

ITT

1O.O

N2

WINDMILLING INDICATION

IGN A

FUEL QTY

7OO

ITT

9O.O

13

N2

9O.O

14

5OOO

FF PPH 5OOO

15

55OO

FQ LB

16

55OO

17

11OOO OIL

IGN A

9O.O

FIRE 7OO

7OO

18

ITT

12

N2

16O

TEMP

3.O 3.O

LP HP

PRESS PSI 64

81

VIB

9OO 9O.O

3.O 4.2

ITT N2

AOM-1502-003

ITT OVERTEMPERATURE

EM170AOM140306B.DGN

FIRE INDICATION

ENGINE INDICATION - EICAS

14-06-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 19

Controls and Indications

Page 5

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ENGINE

1 - THRUST REVERSER INDICATION – Indicates the thrust reverser position. – Label: REV GREEN: fully deployed. AMBER: in transition. RED: discrepancy between selected and actual reverser positions. 2 - N1 INDICATION – Digital Indication. – Displays the percentage of N1 rpm. GREEN: normal operating range. RED: operating limit exceeded. AMBER DASHED: invalid information or value out of displayable range. – Quantity Scale/Pointer. – The pointer on the scale indicates a value equal to that shown on the digital readout. – Scale: GREEN: normal operating range. RED: operating limit exceeded. – The amber boxed FAIL indication is displayed on the center of the N1 dial when an engine has flamed out or shut down without pilot action. The cyan OFF indication is displayed when the engine is shut down in- flight by pilot action. 3 - N1 WING ANTI-ICE CYAN LINE – Displayed only in icing conditions during final approach (radio altimeter below 1200 ft) with landing gear down or flaps extended.

4 - N1 TARGET INDICATION

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Page 6

Controls and Indications

REVISION 19

AOM-1502-003

– Indicates the minimum thrust level (N1 value) to meet bleed requirements.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ENGINE

– Maximum N1 for the engine thrust rating mode indicated on EICAS. – If the requested value is invalid, the digits will be removed from the display. – A cyan V-shaped bug represents the N1 target on the dial indicator. – Digits: CYAN: normal indication. AMBER DASHED: invalid information or value out of displayable range. 5 - THRUST RATING MODE INDICATION – Indicates the current thrust-rating mode. Indications are displayed in cyan. – Label: TO-1, TO-2, TO-3, TO-1 RSV, TO-2 RSV, TO-3 RSV, FLEX TO-1, FLEX TO-2, FLEX TO-3, CLB-1, CLB-2, CON, CRZ, GA or GA-RSV. 6 - ATTCS INDICATION – An ATTCS indication is displayed to indicate the Automatic Takeoff Thrust Control System status. – Label: ATTCS GREEN: engaged. WHITE: armed. BLANK: not selected. 7 - ASSUMED TEMPERATURE INDICATION – Displays the temperature set on the MCDU. This indication is also used as a reference for flexible thrust.

AOM-1502-003

8 - N1 REQUEST INDICATION – Indicates the momentary difference (transient) between actual N1 and requested N1 applied by thrust lever position (TLA).

14-06-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 19

Controls and Indications

Page 7

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ENGINE

9 - MAXIMUM N1 INDICATION – Green tick-mark. – Indicates the maximum allowable N1 (maximum thrust) for the current thrust rating and operating conditions. If the thrust lever is set to MAX position, the N1 Request value will be equal to the Maximum N1 value. 10 - N1 RED LINE – Indicates the N1 limit. – The digital and dial readout colors change if this value is exceeded. 11 - INTERTURBINE TEMPERATURE (ITT) INDICATION – Quantity Scale/Pointer. – The pointer on the scale indicates a value equal to that shown on the digital readout. – Scale: GREEN: normal operating range. RED: operating limit exceeded. – AMBER dashes will display on digital readout when invalid information or a value out of displayable range is available. – A red fire warning indication is displayed on the center of ITT dial to indicate engine fire condition. 12 - ITT RED/AMBER LINE – Maximum allowable ITT for the current flight phase. – Limits thrust, thereby avoiding the maximum allowable ITT to be exceeded. – The red line will change to amber after the end of the takeoff phase. The red line will be shown in flight if the ITT goes above the CON thrust rating limit.

– Indicates the enabled ignition channel.

14-06-05 Copyright © by Embraer. Refer to cover page for details.

Page 8

Controls and Indications

REVISION 19

AOM-1502-003

13 - IGNITION CHANNEL INDICATION

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ENGINE

– Colors: GREEN: IGN A, IGN B or IGN AB. CYAN: IGN OFF. – A WML icon is displayed whenever the FADEC has detected an engine flameout and the auto re-light system is actuating to restart the engine. 14 - N2 INDICATION – Digital Indication. – Displays the percentage of N2 rpm. GREEN: normal operating range. RED: operating limit exceeded. AMBER DASHED: invalid information or value out of displayable range. 15 - FUEL FLOW INDICATION – Indicates fuel flow in kilograms per hour (KPH) or pounds per hour (PPH). – Digit colors: GREEN: normal indication. AMBER DASHED: invalid information or value out of displayable range. 16 - OIL PRESSURE INDICATION – Indicates the engine oil pressure. – Digit colors: GREEN: normal operating range. AMBER: cautionary operating range.

AOM-1502-003

RED: operating limit exceeded. A zero (0) value may be an indication of Oil Pressure Transducer failure. AMBER DASHED: invalid information or value out of displayable range.

14-06-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 19

Controls and Indications

Page 9

SYSTEMS DESCRIPTION ENGINE

AIRPLANE OPERATIONS MANUAL

17 - OIL TEMPERATURE INDICATION – Indicates the engine oil temperature. – Digit colors: GREEN: normal operating range. AMBER: cautionary operating range. AMBER DASHED: invalid information or value out of displayable range. 18 - ENGINE VIBRATION INDICATION – Indicates low-pressure (LP) and high-pressure (HP) vibration levels for both engines. – Digit colors: GREEN: normal operating range (0 to 3.9). AMBER: cautionary operating range (4.0 to 5.0). AMBER DASHED: invalid information or value out of displayable range.

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Page 10

Controls and Indications

REVISION 19

AOM-1502-003

NOTE: Transient LP or HP high vibration indication without any other abnormal engine parameter indication may be considered normal according to the engine manufacturer.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ENGINE

STATUS PAGE MFD

ENG OIL LEVEL

6.5 QT 2.4

EM170AOM140087C.DGN

1

ENGINE OIL LEVEL INDICATION ON MFD

1 - OIL LEVEL INDICATION – Indication colors: GREEN: normal operating range. AMBER: cautionary operating range. – AMBER dashes will display on digital readout when invalid information or a value out of displayable range is available. NOTE: The limit indication of amber line changes according to the engine status (running/shutdown).

MCDU INDICATION All the inputs required by the FADEC for the takeoff N1 computations are made through the T/O DATASET MENU, on the MCDU. The T/O dataset is performed according to the sequence: – Press TRS (mode button).

AOM-1502-003

– Press TO DATA SET (LSK 6R) on THRUST RATING SELECT page.

14-06-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 19

Controls and Indications

Page 11

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ENGINE

T/O DATASET MENU __K_

1/1

ATTCS

TO-1

OFF ON

__K_

REF ECS

__K_

REF A/I

TO-2 TO TEMP

23 C

ENTER

OFF ENG ALL FLEX T/O

OFF ON

FLEX TEMP

39 C

THRUST RATING SEL

EM170AOM140845A.DGN

TO-3

OFF ON

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Page 12

Controls and Indications

REVISION 19

AOM-1502-003

T/O DATASET MENU PAGE

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ENGINE

ENGINE FUEL SYSTEM GENERAL The engine fuel system provides fuel pressurization, filtering, heat exchange and operation of bleed valves and variable geometric actuators.

FUEL PUMP Fuel supplied by the airplane fuel tanks flows to the engine fuel pumps. Upon exiting the tanks, the fuel flows through the low-pressure pump and then divides into two paths. One flows through the high-pressure fuel pump and returns to the fuel tank as motive flow. The second flows through the fuel/oil heat exchanger to the fuel filter. Once filtered, the flow leaves the FMU and passes through the high-pressure fuel pump, before returning to the FMU.

FUEL/OIL HEAT EXCHANGER The fuel-cooled oil cooler (FCOC) maintains the oil temperature within an acceptable range and heats the engine fuel to prevent freezing.

FUEL METERING UNIT The FMU, controlled by the FADEC, meters and distributes the proper amount of fuel for combustion to the injectors under all operating conditions. The FMU controls the shutoff valve used during all normal shutdowns and provides overspeed protection.

FUEL FILTER The fuel filter removes contaminants from the engine fuel. The impending bypass switch indicates fuel filter blockage and an imminent bypass condition.

VARIABLE GEOMETRY ACTUATOR

AOM-1502-003

The Variable Geometry Actuator consists of two fuel driven actuators controlled by the FADEC via FMU. The purpose of the actuators is to optimize the position of the compressor stators as a function of corrected N2 to provide optimum compressor efficiency.

14-06-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 11

Engine Fuel System

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ENGINE

FUEL INJECTORS

14-06-10 Copyright © by Embraer. Refer to cover page for details.

Page 2

Engine Fuel System

REVISION 11

AOM-1502-003

The fuel injectors atomize the fuel from the FMU and direct it into the combustion chamber.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ENGINE

FUEL SCHEMATIC

EJECTOR FUEL PUMP

FUEL TANK

LOW PRESSURE PUMP

HEAT EXCHANGER

HIGH PRESSURE PUMP

FUEL FILTER FUEL METERING UNIT

FUEL INJECTORS EM170AOM140079A.DGN

HIGH PRESSURE PUMP

AOM-1502-003

FUEL SYSTEM SCHEMATIC

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REVISION 11

Engine Fuel System

Page 3

SYSTEMS DESCRIPTION ENGINE

AIRPLANE OPERATIONS MANUAL

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Page 4

Engine Fuel System

REVISION 11

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ENGINE

LUBRICATION SYSTEM GENERAL Each engine has an independent lubrication system. The oil system lubricates and cools the turbine engine main shaft bearings and the accessory gearbox. Oil is pressurized in the lubrication pump, it then passes through the filter, the fuel-oil heat exchanger and is then divided into several circuits to lubricate the engine.

OIL TANK Oil quantity indication is provided for each engine oil tank and is displayed on the MFD. Oil quantity sensors in the tank detect low oil quantity and trigger the low oil level caution at a specific level.

OIL PUMPS The pump provides oil flow any time the core engine is turning. The pump contains one supply and four scavenge pumping elements. The lube and scavenge pumps deliver oil under pressure to the engine bearings and gears, and then recovers the oil to the tank for reuse.

OIL FILTER The oil filter module incorporates a filter bypass and cold start relief valve. The oil filter bypass valve permits oil flow if the filter becomes clogged. The filter impending bypass switch monitors the differential pressure at the filter.

AOM-1502-003

The filter module has a relief valve to bypass high viscosity oil during cold start conditions.

14-06-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Lubrication System

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ENGINE

LUBRICATION SCHEMATIC BYPASS VALVE

OIL RESERVOIR

FUEL/OIL HEAT EXCHANGER

DEAERATOR OIL OIL FILTER

CHIP DETECTOR

FUEL

A

SCAVENGE SCREENS

A SUMP (BEARINGS #1, #2, AND #3)

B SUMP (BEARING #4)

C SUMP (BEARING #5)

EM170AOM110009A.DGN

B

AIR/OIL SEPARATOR

C

LUBE

PUMP

AGB

AGB

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Page 2

Lubrication System

REVISION 9

AOM-1502-003

LUBRICATION SYSTEM SCHEMATIC

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ENGINE

STARTING AND IGNITION SYSTEMS STARTING SYSTEM The engine starting system consists of: – Air Turbine Starter (ATS). – Starter control valve (SCV). The pneumatic system provides bleed air to the ATS to rotate the rotor speed and start the engine. The FADEC opens the Starter Control Valve (SCV), providing bleed air from the APU, a ground source, or the opposite engine. The Air Turbine Starter (ATS) is a turbine that accelerates the engine to a self-sustaining rpm level. The FADEC closes the SCV when the starter cutout speed is reached.

IGNITION SYSTEM The ignition system provides an electrical spark for fuel combustion during ground/in-flight start attempts and for automatic re-light. The FADEC energizes one igniter for on-ground engine starts and both igniters for in-flight engine starts. When the ignition selector knob is placed on the OVRD position, both igniters on each engine are energized. Igniters 1B and 2B are connected to SPDA 2. In case of SPDA 2 failure, setting the selector knob to OVRD energizes at least the igniter A. NOTE: The frequent use of ignition selector knob at the OVRD position causes the significative reduction of ignitor’s lifetime.

STARTER OPERATION

AOM-1502-003

The engine starter is controlled via the engine start selector knob on the powerplant control panel. For on ground starts, the SCV opens providing bleed air to the ATS to increase rotor speed for engine start.

14-06-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Start and Ignition System

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ENGINE

GROUND START The FADEC initiates ignition at approximately 7% N2 and the fuel flow (metering valve opens) at approximately 20% N2. FADEC will automatically switch to the other ignitor if no light off is detected within 15 s after initiation of fuel flow. The start should be aborted if no light off is detected within 30 s after initiation of fuel flow. After a light off occurs, the FADEC commands the starter to cutout at approximately 50% N2, and commands the FMU fuel metering valve to accelerate the engine to ground idle speed.

IN FLIGHT START Engine cross-bleed air, APU bleed air, or windmilling can be used for in flight engine starts. An in flight cross-bleed start is identical to an on ground start, but the FADEC automatically controls fuel flow to initiate (Metering valve opens) if N2 has not reached 20% after 15 s. For windmill starting, the SCV configures the pneumatic system. The engine start is controlled by the START/STOP selector knob and the FADEC commands ignition at 7% N2 and fuel flow at a minimum of 7.2% N2, or after 15 s, whichever occurs first. The FADEC has no protection for hot starts, hung starts or failure to light off for in flight engine starts. If no light off is detected within 30 s after fuel flow is started, the start should be manually aborted.

AUTO RELIGHT The FADEC monitors N2 and automatically turns on both igniters and schedules the relight fuel flow in the event of an engine flameout. In addition a WML icon is displayed next to the respective engine N2 and represents an auto relight actuation during the engine auto relight attempts. If the engine relight does not occur within 30 s or N2 falls below 7.2%, the automatic relight can be considered unsuccessful and should be manually terminated by moving the START/STOP selector knob to the STOP position.

During ground operations, auto relight attempts are terminated and fuel

14-06-20 Copyright © by Embraer. Refer to cover page for details.

Page 2

Start and Ignition System

REVISION 18

AOM-1502-003

For in flight auto relight, the FADEC has no protection for hot starts, hung starts or failure to light off.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ENGINE

AOM-1502-003

is shutoff if the engine rpm falls below 52 percent N2.

14-06-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Start and Ignition System

Page 3

SYSTEMS DESCRIPTION ENGINE

AIRPLANE OPERATIONS MANUAL

14-06-20 Copyright © by Embraer. Refer to cover page for details.

Page 4

Start and Ignition System

REVISION 18

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ENGINE

THRUST REVERSER SYSTEM The Thrust Reverser System is hydraulically actuated and controlled from the cockpit via the thrust lever.

FORWARD THRUST

FORWARD THRUST

REVERSE THRUST

REVERSE THRUST

EM170AOM140083.DGN

Thrust reverses 1 & 2 operate independently, and are actuated by the respective hydraulic system.

THRUST REVERSER ACTUATION

The FADEC provides an interlock function to protect against inadvertent thrust reverser deployment and also to protect against inadvertent thrust reverser stowing. A locking system consists of two actuator locks and the independent cowl lock. The cowl lock prevents inadvertent deployment of the thrust reverser.

THRUST REVERSER OPERATION Moving the thrust lever to IDLE position enables the lifting of the thrust reverser trigger. Thrust reverser deployment is commanded when the associated thrust lever is moved to the reverse positions (MIN REV or MAX REV).

AOM-1502-003

Thrust reverser deployment occurs only if the airplane is on ground. The thrust reverser trigger can be lifted within 30 seconds after an engine inoperative condition is detected. After this time, the thrust reverse trigger is not released, and the respective thrust lever cannot be moved to the reverse positions. Idle reverse thrust is commanded while the thrust reverser cowls are in transit. After total deployment of the thrust reverser cowls, maximum reverse thrust is commanded if the thrust levers are held in MAX REV position.

14-06-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Thrust Reverser

Page 1

SYSTEMS DESCRIPTION ENGINE

AIRPLANE OPERATIONS MANUAL

In case one thrust reverser fails, when selecting both TLA to MAX REV position, the operative thrust reverser provides minimum reverse thrust only. Selecting only the operating thrust reverser TLA to MAX REV position enables maximum reverse thrust on this engine.

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Page 2

Thrust Reverser

REVISION 18

AOM-1502-003

The thrust reverser is not designed to operate in flight. In case of uncommanded thrust reverser deployment, the engine thrust is limited to idle.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ENGINE

ENGINE CONTROL SYSTEM GENERAL The engine control system performs engine control and thrust management, provides information to the cockpit, maintenance reporting and engine condition monitoring. The engine control system consists of the FADEC, thrust lever, T2 and N1 sensors. The FADEC uses inputs from the airplane and engine to monitor and manage the engine control system. The thrust lever receives the inputs of the desired thrust from the pilots or from the autothrottle. The T2 sensor monitors the engine inlet air temperature for use in FADEC control calculations. The N1 sensor provide fan speed data for the FADEC and airplane vibration monitoring system.

FULL AUTHORITY CONTROL (FADEC)

DIGITAL

ELECTRONIC

The FADEC is the main component of the engine control system. Its functions include: • Engine protection;

• •

Control of the requested and max N1; Control of the ATTCS.

The FADEC has two identical but isolated channels. One operates as the in-control channel and the other as a standby. The standby channel constantly processes all the data and is always ready to take control of the engine in case the active channel fails. The FADEC in-control channel is switched on every engine start.

FADEC ELECTRICAL POWER

AOM-1502-003

Above approximately 50% N2 the FADEC is powered by the Permanent Magnet Alternator (PMA). Below this value or in case the PMA becomes inoperative; the airplane’s electrical system provides the backup power.

14-06-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Engine Control System

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ENGINE

FADEC INTERFACES The FADEC receives data from all engine control system sensors and the airplane air data system to control the operation and performance characteristics of the engine, exercising control over the:

• • • • •

Engine fuel metering unit to adjust the fuel flow;

•

Engine starting to optimize the temperatures, start up time and to provide the available protections;

•

Ignition for engine start and automatic dry motoring, to prevent engine flame out during operation.

Variable geometry valve to improve N1 efficiency; Bleed valve to set the engine bleed extraction; T2 sensor heater to prevent ice accumulation; Thrust reverser actuation to adjust and control N1 values and allowances;

AUTOMATIC TAKEOFF THRUST CONTROL SYSTEM (ATTCS) The ATTCS is controlled by the FADEC and is available on takeoff and go around. TAKEOFF The ATTCS can be selected ON or OFF for takeoff. By default, ATTCS will be selected ON. The selection is made on the MCDU - TAKEOFF DATA SET MENU page and the indication is displayed on the EICAS as follows: • ATTCS label in white - system is armed; • ATTCS label in green - system is engaged. The engagement only happens when the thrust levers reach the TO/GA set position. The selection from ON to OFF must be in accordance with the performance calculations. GO AROUND

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Page 2

Engine Control System

REVISION 18

AOM-1502-003

In flight the ATTCS is automatically armed anytime the thrust rate mode is GA making the GA RSV possible whenever activation criteria are met.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ENGINE

ATTCS ACTIVATION LOGIC The ATTCS automatically commands RSV whenever it is engaged, thrust levers are at TOGA position, and one of following conditions occurs: – Difference between both engine N1 values is greater than 15%; – One engine failure during takeoff; – One engine failure during go-around; – Windshear detection. The RSV mode is manually activated by moving the thrust levers to MAX position whenever the ATTCS is engaged.

AOM-1502-003

Whenever the ATTCS is activated, the green ATTCS indication on the EICAS disappears and the cyan thrust mode will be displayed with an additional “RSV” indication.

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REVISION 18

Engine Control System

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ENGINE

ATTCS LOGIC TABLE Phase of Flight

Condition

ATTCS Status ATTCS ON

One Engine Failure

Takeoff ATTCS OFF Go-Around

ATTCS ON ATTCS ON

Takeoff ATTCS OFF

Windshear Go-Around

ATTCS ON ATTCS ON

Thrust Lever Set TOGA MAX TOGA MAX TOGA MAX TOGA MAX TOGA MAX TOGA MAX TOGA MAX

Takeoff All Engines Operative

ATTCS OFF

TOGA MAX

Go-Around

ATTCS ON

TOGA MAX

(1)

FADEC sets go around reserve thrust, regardless the label is presented on the EICAS, when: • Windshear is detected during takeoff phase, and • TLA is MAX.

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Page 4

Engine Control System

REVISION 18

AOM-1502-003

NOTE:

Engine Thrust TO-x RSV TO-x RSV No Thrust Increase TO-x GA RSV GA RSV TO-x RSV GA RSV (1) No Thrust Increase GA RSV (1) GA RSV GA RSV No Thrust Increase TO-x RSV No Thrust Increase TO-x No Thrust Increase GA RSV

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ENGINE

FLEXIBLE TAKEOFF Flexible takeoff is a reduced takeoff thrust based on assumed temperature. All takeoff modes are eligible for a flexible takeoff. The assumed temperature must be higher than the TO TEMP and is set on the MCDU TAKEOFF DATA SET MENU page. The indication FLEX TO-1, FLEX TO-2 or FLEX TO-3 will be displayed on the EICAS for the respective flexible takeoff thrust. The minimum flex takeoff thrust is limited to 75% maximum rated takeoff thrust or CLB-2 + 0.5% N1, whichever is higher. Flexible takeoff is possible with ATTCS ON or OFF. When flexible takeoff mode is used, moving the thrust levers to MAX position resets the assumed temperature and sets the maximum thrust available (refer to the Thrust Ratings Table).

ENGINE THRUST RATINGS The FADEC calculates the maximum N1 for each thrust rate mode adjusted for altitude, temperature and airspeed and displays both digital and analogical readings on the N1 indicator. The thrust rate modes are the following: • Takeoff (TO-1, TO-2, TO-3)

• • • • • • •

Takeoff Reserve (TO-1 RSV, TO-2 RSV, TO-3 RSV) Go-Around (GA) Go Around Reserve (GA-RSV) Maximum Continuous Thrust (CON) Maximum Climb (CLB-1, CLB-2) Maximum Cruise (CRZ) Idle

TAKEOFF (TO-1, TO-2, TO-3) TO-x is the thrust used for a normal takeoff.

AOM-1502-003

Based on the inputs made on MCDU – TAKEOFF DATA SET MENU page the FADEC calculates the maximum N1 for the given conditions. The takeoff N1 is only achieved when the thrust levers are set to TO/GA position.

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REVISION 18

Engine Control System

Page 5

SYSTEMS DESCRIPTION ENGINE

AIRPLANE OPERATIONS MANUAL

MAXIMUM TAKEOFF RESERVE (TO-1 RSV, TO-2 RSV, TO-3 RSV) Whenever the ATTCS is triggered, TO-x RSV automatically becomes the maximum N1, as long as the thrust levers are set to TO/GA. The TO-x RSV can be manually activated by setting the thrust lever to MAX position, given that the ATTCS is ON and TO-x mode is active.

GO-AROUND (GA) The go around mode is activated in flight whenever the landing gear and flaps are down. The GA mode can also be set from CRZ, CON or CLB by pressing the TOGA switch. The go around thrust can be achieved anytime in flight when the thrust rate mode is other than takeoff and the thrust levers are set to TO/GA. In this situation, the engine thrust mode label on EICAS is not modified.

GO-AROUND RESERVE (GA-RSV) The GA RSV is the highest engine thrust possible and it is to be used in extreme situations where extra thrust is required when maneuvering for landing.

MAXIMUM CONTINUOUS RATING (CON) The maximum continuous thrust is to be used on emergency situation where thrust higher than usual is required. It is the highest thrust the engines can operate continuously without reducing the time between overhauls.

MAXIMUM CLIMB RATING (CLB-1, CLB-2) During aircraft power up, CLB-1 is the default mode setting. Whenever the selected takeoff thrust is lower than CLB-1 the CLB-2 mode becomes the default until the next airplane power down / power up. Manual switching between the climb modes is possible anytime in flight on the MCDU - TRS page.

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Page 6

Engine Control System

REVISION 18

AOM-1502-003

On ground the CLB-1 mode is inhibited if the take off thrust selected is lower than CLB-1 thrust.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ENGINE

MAXIMUM CRUISE RATING (CRZ) The CRZ mode is the maximum N1 that can be used for a normal cruise flight.

IDLE The IDLE modes are automatically adjusted by the FADEC in order to maintain the minimum thrust necessary to provide the required bleed pressure to the airplane. Flight Idle N1 varies with altitude and can change as a function of ECS and anti-ice bleed requirements. The idle mode selections are the following:

• • • •

Flight Idle. Approach Idle. Final Approach Idle. Ground Idle.

IDLE THRUST IN ICE CONDITIONS Whenever ICE CONDITION is sensed the N1 for the FLIGHT IDLE and APPROACH IDLE is automatically increased to maintain the minimum bleed pressure required for the ANTI ICE system operation. With the FINAL APPROACH IDLE there is no N1 automatic increase but a cyan dash is displayed on both EICAS N1 dial to show the minimum thrust required to maintain the bleed pressure required by the ANTI ICE system. FLIGHT IDLE The flight idle mode is active anytime in flight when the approach idle is not selected. APPROACH IDLE Approach Idle is used in flight to enable rapid acceleration to go-around thrust. Approach idle is activated as follows:

AOM-1502-003

• • •

In flight; Altitude less than 15000 ft; and Flaps 1 or greater or landing gear down.

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REVISION 18

Engine Control System

Page 7

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ENGINE

FINAL APPROACH IDLE Final Approach Idle is active as follows:

• • •

Altitude lower than 1200 ft AGL; Landing flaps; Landing gear down.

GROUND IDLE Ground Idle is the minimum thrust setting. Ground Idle provides the minimum stable engine thrust level for ground operations.

MINIMUM REVERSE Min reverse is idle thrust with the thrust reverser cowl opened.

MAX REVERSE Max reverse is the maximum thrust available with the thrust reverser opened.

Ratings Thrust Mode T/O-1 T/O-2 T/O-3

CF34-8E5A1

CF34-8E5

CF34-8E2

Thrust (lbf)

Thrust (lbf)

Thrust (lbf)

ATTCS

All Engine Oper.

One Engine Inop.

All Engine Oper.

One Engine Inop.

All Engine Oper.

One Engine Inop.

ON

13800

14200

13000

14200

11800

13000

OFF

13800

13800

13000

13000

11800

11800 –

ON

13000

14200

11800

13000

–

OFF

13000

13000

11800

11800

–

–

ON

11800

13000

–

–

–

–

OFF

11800

11800

–

–

–

–

GA

ON

13000

14200

13000

14200

11700

13000 11700

CON

–

12800

12800

12800

12800

11700

CLB-1

–

12400

–

12400

–

11200

–

CLB-2

–

11100

–

11100

–

–

–

CRZ

–

10400

–

10400

–

10000

–

NOTE: Thrusts values for sea level and ISA conditions.

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Page 8

Engine Control System

REVISION 18

AOM-1502-003

THRUST RATINGS TABLE

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ENGINE

DERATED TAKEOFF ITT LIMITS During the initial takeoff run the ITT red line marks the temperature limit for the actual thrust rating, changing according to the takeoff mode selected. After V1 - 15 KIAS however, the ITT red line will mark the temperature limit for maximum takeoff thrust rating (TO-1 RSV), assuring that the engine has enough ITT margin to achieve maximum rated thrust.

ENGINE PROTECTION FADEC ENGINE PROTECTION The FADEC provides engine start protection on the ground as follows: – Hung start. – Hot start. – No light-off

OVERSPEED PROTECTION Whenever N2 reaches 102% the FADEC automatically commands an engine shutdown. In the event of three consecutive overspeed detection events within 30 s the FADEC will not relight the engine.

OVERTEMPERATURE PROTECTION The FADEC controls the ITT limits for engine start and throughout engine operation. ITT limit is variable according to the engine operation phase. ITT OVER LIMIT PROTECTION

AOM-1502-003

During engine start if the ITT reaches its limit the FADEC automatically shuts off the fuel flow aborting the start sequence. In this case the start control valve is not automatically closed. Pilot intervention is needed to close the SCV by selecting the START/STOP switch to STOP.

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REVISION 18

Engine Control System

Page 9

SYSTEMS DESCRIPTION ENGINE

AIRPLANE OPERATIONS MANUAL

ENGINE START HIGH ITT PREVENTION To improve the ITT control on engine ground starts the FADEC will not allow fuel flow if ITT is above 120°C.

14-06-30 Copyright © by Embraer. Refer to cover page for details.

Page 10

Engine Control System

REVISION 18

AOM-1502-003

In this case when the pilot sets the START/STOP selector to START the start control valve is commanded open but the fuel flow only starts when the ITT drops below 120°C.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ENGINE

EICAS MESSAGES TYPE

WARNING

AOM-1502-003

CAUTION

MESSAGE ENG 1 (2) OIL LO PRESS

MEANING Engine 1 (2) oil pressure is low. Thrust reverser deployed unexpectedly, or not ENG 1 (2) REV stowed when DEPLOYED commanded to stow or thrust reverse position is undetermined. Thrust modulation is ENG 1 (2) CONTROL disabled. OBV has FAULT failed open or engine will respond slowly. FADEC ENG 1 (2) FADEC overtemperature has OVERTEMP been detected. Engine 1 (2) ENG 1 (2) FAIL shutdown has occurred. ENG 1 (2) FUEL IMP Fuel filter impending BYPASS bypass. Engine 1 (2) Fuel ENG 1 (2) FUEL LO pressure low. Airplane PRESS backup fuel pump is active. ENG 1 (2) NO No dispatch condition DISPATCH detected by FADEC. ENG 1 (2) OIL LO Engine 1 (2) oil level LEVEL is below minimum. Thrust Reverser is ENG 1 (2) REV FAIL not available.

14-06-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 19

EICAS Messages

Page 1

ENGINE

TYPE

AIRPLANE OPERATIONS MANUAL MESSAGE ENG 1 (2) REV PROT FAULT ENG 1 (2) REV TLA FAIL ENG 1 (2) START VLV OPEN ENG 1 (2) T2 HEAT FAIL ENG 1 (2) TLA FAIL ENG EXCEEDANCE

CAUTION ENG NO TAKEOFF DATA

ENG REF A-I DISAG

ENG REF ECS DISAG

MEANING Reverser fault detected, operation not inhibited. Respective reverser solenoid protection has failed. Start valve not closed while engine running. T2 heater failed. Dual thrust lever angle sensor failure. Engine limit exceedance detected. Takeoff data not entered successfully. Discrepancy between information entered in FMS for engine 1 and 2 detected. Ice protection mode selector knob set to the ON position with OFF or ENG in the take-off data set (TDS) menu. Discrepancy between REF. ECS input and actual ECS bleed configuration.

14-06-35 Copyright © by Embraer. Refer to cover page for details.

Page 2

EICAS Messages

REVISION 19

AOM-1502-003

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL TYPE

CAUTION

AOM-1502-003

ADVISORY

SYSTEMS DESCRIPTION ENGINE

MESSAGE

MEANING Discrepancy between maximum thrust ENG THR RATING rating of engines 1 DISAG and 2. Possible asymmetric engine thrust. TLA not at TOGA position during takeoff ENG TLA NOT TOGA and/or go-around phases One FADEC channel ENG 1 (2) FADEC no longer sending FAULT data. Fuel pressure switch ENG 1 (2) FUEL SW indicates pressure is FAIL not low while all fuel pumps are off. ENG 1 (2) OIL IMP Oil filter impending BYPASS bypass. ENG 1 (2) OIL SW Oil pressure switch FAIL failure detected. Short-time dispatch ENG 1 (2) SHORT fault condition DISPATCH detected by FADEC.

14-06-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 19

EICAS Messages

Page 3

ENGINE

TYPE

STATUS

AIRPLANE OPERATIONS MANUAL MESSAGE ENG 1 (2) REV INHIBIT

ENG 1 (2) TLA NOT IDLE

ENG TDS REF A-I ALL

MEANING Reverser inhibited by maintenance action. TLA not set to IDLE during either engine start or engine shutdown. A thrust higher than the expected will be reached if the TLA is above idle during engine start. Set TLA to IDLE within 30 s to shut down the engine. If the 30 s period is exceeded, cycle the START/STOP selector knob to RUN then to STOP to reset the time and shutdown the engine. For airplanes Post-Mod FADEC version 5.40, this message is also displayed during normal engine shutdown on ground with TLA at maximum 5° above IDLE. REF A-I ALL is selected on take-off data set page on MCDU.

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Page 4

EICAS Messages

REVISION 19

AOM-1502-003

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL TYPE

AOM-1502-003

STATUS

MESSAGE

ENG TDS REF A-I ENG

SYSTEMS DESCRIPTION ENGINE

MEANING Ice protection mode selector knob set to the AUTO position and REF A-I ENG is selected on take-off data set page on MCDU.

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REVISION 19

EICAS Messages

Page 5

SYSTEMS DESCRIPTION ENGINE

AIRPLANE OPERATIONS MANUAL

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Page 6

EICAS Messages

REVISION 19

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FIRE PROTECTION

SECTION 14-07 FIRE PROTECTION TABLE OF CONTENTS

AOM-1502-003

Block

Page

General Description............................................. 14-07-01 .... GENERAL DESCRIPTION..................................... 14-07-01 ....

1 1

Controls and Indications..................................... 14-07-05 .... FIRE PROTECTION CONTROL PANEL............... 14-07-05 ....

1 1

Engine Fire Protection......................................... 14-07-10 .... ENGINE FIRE PROTECTION SYSTEM............... 14-07-10 .... ENGINE FIRE DETECTION.................................. 14-07-10 .... ENGINE FIRE EXTINGUISHING........................... 14-07-10 .... ENGINE FIRE PROTECTION SYSTEM SCHEMATIC.................................................... 14-07-10 ....

1 1 1 2

APU Fire Protection............................................. 14-07-15 .... APU FIRE PROTECTION SYSTEM...................... 14-07-15 .... APU FIRE DETECTION......................................... 14-07-15 .... APU FIRE EXTINGUISHING................................. 14-07-15 .... APU FIRE PROTECTION SYSTEM SCHEMATIC.. 14-07-15 ....

1 1 1 2 3

Cargo Compartment Fire Protection.................. 14-07-20 .... CARGO COMPARTMENT FIRE PROTECTION SYSTEM.......................................................... 14-07-20 .... CARGO COMPARTMENT SMOKE DETECTION.. 14-07-20 .... CARGO COMPARTMENT FIRE EXTINGUISHING............................................. 14-07-20 ....

1

Lavatory Fire Protection...................................... 14-07-25 .... LAVATORY FIRE PROTECTION SYSTEM........... 14-07-25 .... LAVATORY SMOKE DETECTION......................... 14-07-25 .... LAVATORY FIRE EXTINGUISHING...................... 14-07-25 .... LAVATORY DETECTORS AND EXTINGUISHERS LOCATION......................... 14-07-25 ....

1 1 1 1

3

1 1 2

1

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REVISION 18

Table of Contents

Page 1

SYSTEMS DESCRIPTION FIRE PROTECTION

AIRPLANE OPERATIONS MANUAL

Block Page Fire Detection System Test................................. 14-07-30 .... 1 FIRE DETECTION SYSTEM TEST....................... 14-07-30 .... 1 1 1

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Page 2

Table of Contents

REVISION 18

AOM-1502-003

EICAS Messages.................................................. 14-07-35 .... EICAS MESSAGES............................................... 14-07-35 ....

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FIRE PROTECTION

GENERAL DESCRIPTION The fire protection system provides fire detection and extinguishing capabilities for: • Engines

• • •

APU Cargo Compartments Lavatories

In addition, portable fire extinguishers are located in the cockpit and cabin.

AOM-1502-003

In the event of fire protection system component failure, an EICAS message will be displayed.

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REVISION 9

General Description

Page 1

SYSTEMS DESCRIPTION FIRE PROTECTION

AIRPLANE OPERATIONS MANUAL

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Page 2

General Description

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FIRE PROTECTION

AOM-1502-003

FIRE PROTECTION CONTROL PANEL

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REVISION 11

Controls and Indications

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FIRE PROTECTION

OVERHEAD PANEL

1

2

3

3

FIRE EXTINGUISHER CARGO SMOKE FWD

AFT

1

2

APU TEST

PULL TO SHUTOFF

ROTATE TO EXTING

ROTATE TO EXTING

PULL TO SHUTOFF

4

FIRE EXTINGUISHER CARGO SMOKE FWD

AFT

APU

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Page 2

Controls and Indications

REVISION 11

AOM-1502-003

EM170AOM140091.DGN

TEST

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FIRE PROTECTION

1 - ENGINE FIRE EXTINGUISHER HANDLE PULL: ROTATE (left/right):

closes the associated engine bleed air, fuel and hydraulic shutoff valves. discharges fire extinguisher bottles into the associated engine.

2 - APU FIRE EXTINGUISHER BUTTON (GUARDED) Momentary action pushbutton: – Closes the APU fuel shutoff valve and discharges the APU fire extinguisher bottle. 3 - CARGO FIRE (GUARDED)

DETECTION/EXTINGUISHER

BUTTON

Momentary action pushbutton: – According to the system logic, discharges the high and low-rate cargo extinguisher bottles of the associated cargo compartment when the button is lit. – Pressing the pushbutton when it is not illuminated arms the associated extinguisher bottle and the button illuminates red. 4 - FIRE DETECTION SYSTEM TEST BUTTON Momentary action button: – Tests the cargo smoke, engine and APU fire detection systems.

AOM-1502-003

– If the button is pressed for more than 10 seconds the APU automatically shuts down.

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REVISION 11

Controls and Indications

Page 3

SYSTEMS DESCRIPTION FIRE PROTECTION

AIRPLANE OPERATIONS MANUAL

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Page 4

Controls and Indications

REVISION 11

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FIRE PROTECTION

ENGINE FIRE PROTECTION SYSTEM The Engine Fire Protection System is designed to provide: – Engine fire detection; – Engine fire extinguishing and; – Continuous Built-In Tests to detect internal faults.

SYSTEM ELECTRICAL SUPPLY The electrical power is supplied by: – Engine fire detection: MAU 1 (DC ESS BUS 1) and MAU 3 (DC ESS BUS 2). – Engine fire extinguishing: HOT BATT BUS 1 and HOT BATT BUS 2.

ENGINE FIRE DETECTION The Engine Fire Detection System is monitored by two detector loops. When a fire condition is detected the signal goes to the MAU which generates the associated EICAS messages and alarms.

ENGINE FIRE EICAS MESSAGES AND ALARMS When a fire is detected the following EICAS messages and alarms are triggered: AURAL – aural warning; LIGHTS – the fire extinguisher handle illuminates; – the master WARNING lights illuminate; EICAS MESSAGES – the FIRE warning light on the respective ITT indicator illuminates;

AOM-1502-003

– the EICAS WARNING message ENG 1 (2) FIRE is displayed.

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REVISION 11

Engine Fire Protection

Page 1

SYSTEMS DESCRIPTION FIRE PROTECTION

AIRPLANE OPERATIONS MANUAL

ENGINE FIRE EXTINGUISHING The Engine Fire Extinguishing System is comprised of: – two fire handles and; – two fire-extinguishing bottles.

ENGINE FIRE HANDLE Anytime the fire handle is pulled it commands the following shutoff valves to close: – the engine fuel shutoff valve; – the engine hydraulic shutoff valves and; – the engine bleed air shutoff valve. Each fire handle is associated with one engine.

ENGINE EXTINGUISHER BOTTLE A total of two fire extinguisher bottles named A and B are installed in the airplane to serve either or both engines.

OPERATION Once the FIRE HANDLE has been pulled the extinguisher bottles can be operated. Rotating the FIRE HANDLE counter clockwise discharges extinguisher bottle A into the associated engine. Rotating clockwise discharges extinguisher bottle B into the same engine.

14-07-10 Copyright © by Embraer. Refer to cover page for details.

Page 2

Engine Fire Protection

REVISION 11

AOM-1502-003

NOTE: When an engine fire extinguishing bottle is discharged, fire handle illumination may be lost. In this case if the CAS message is still active the fire condition persists.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ENGINE FIRE SCHEMATIC

FIRE PROTECTION

PROTECTION

SYSTEM

FIRE EXTINGUISHER CARGO SMOKE FWD

AFT

1

2

APU TEST

PULL TO SHUTOFF

ROTATE TO EXTING

SHOT B

PULL TO SHUTOFF

SHOT A

ROTATE TO EXTING

SHOT B

SHOT A

BOTTLE A

BOTTLE B

TO ENGINE 1

EICAS

TO ENGINE 2

DOUBLE CHECK TEE

DOUBLE CHECK TEE

EM170AOM140088.DGN

EICAS

ENGINE FIRE PROTECTION SCHEMATIC

SYSTEM CONTINUOUS SELF MONITORING

AOM-1502-003

Except for illumination of the button, all system components are continuously monitored. In case of an internal failure a CAS message is generated to alert the crew of the failed condition.

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REVISION 11

Engine Fire Protection

Page 3

SYSTEMS DESCRIPTION FIRE PROTECTION

AIRPLANE OPERATIONS MANUAL

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Page 4

Engine Fire Protection

REVISION 11

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FIRE PROTECTION

APU FIRE PROTECTION SYSTEM The APU Fire Protection System is designed to provide: – APU fire detection; – APU fire extinguishing and; – Continuous Built-In Test to detect internal faults.

SYSTEM ELECTRICAL SUPPLY The electrical power is supplied by: – APU fire detection: MAU 1 (DC ESS BUS 1) and MAU 3 (DC ESS BUS 2). – APU fire extinguishing: DC ESS BUS 2.

APU FIRE DETECTION The APU Fire Detection System is comprised of two detectors loops. When a fire condition is detected the signal goes to the MAU which generates the associated EICAS messages and alarms.

APU FIRE EICAS MESSAGES AND ALARMS When a fire is detected the following EICAS messages and alarms are triggered: AURAL – aural warning; LIGHTS – the red stripped bar of the APU emergency stop button illuminates; – the master WARNING lights illuminate; EICAS MESSAGES – the EICAS WARNING message APU FIRE is displayed.

AOM-1502-003

All alarms and indications cease when fire conditions are no longer present.

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REVISION 16

APU Fire Protection

Page 1

SYSTEMS DESCRIPTION FIRE PROTECTION

AIRPLANE OPERATIONS MANUAL

APU FIRE EXTINGUISHING The APU Fire Extinguishing System is comprised of: – one pushbutton; – one fire extinguisher bottle.

APU FIRE EXTINGUISHER PUSHBUTTON When the APU FIRE EXTINGUISHER button is pressed the system: – discharges the APU fire bottle. – shuts down the APU through the APU FADEC. – closes the APU fuel shutoff valve (SOV). – displays an EICAS ADVISORY message APU FIREX BTL DISCH.

APU EXTINGUISHER BOTTLE One fire extinguisher bottle is installed in the rear fuselage.

OPERATION As soon as the APU EMER STOP pushbutton is pressed, the red striped bar is replaced by the white striped bar, indicating that the APU has shut down. After the APU EMER STOP pushbutton is pressed, the APU fire extinguisher pushbutton illuminates entirely red. Pressing the pushbutton, discharges the extinguishing bottle. The APU fire extinguisher pushbutton illumination turns OFF when the fire input from the APU fire detectors disappears. In case of fire and 1 min has passed without APU EMER STOP pushbutton has been pressed, the APU fire extinguisher pushbutton illuminates. Pressing the APU fire extinguisher pushbutton, discharges the extinguisher bottle, shuts down the APU and turns OFF the red striped bar on the APU EMER STOP pushbutton.

APU AUTO SHUTDOWN

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Page 2

APU Fire Protection

REVISION 16

AOM-1502-003

On ground, the APU will automatically shut down 10 seconds after the fire condition is present.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FIRE PROTECTION

APU FIRE PROTECTION SYSTEM SCHEMATIC FIRE EXTINGUISHER CARGO SMOKE FWD

AFT

APU

EICAS APU BOTTLE

TO APU

EM170AOM140236A.DGN

TEST

AOM-1502-003

APU FIRE PROTECTION SYSTEM SCHEMATIC

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REVISION 16

APU Fire Protection

Page 3

SYSTEMS DESCRIPTION FIRE PROTECTION

AIRPLANE OPERATIONS MANUAL

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Page 4

APU Fire Protection

REVISION 16

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FIRE PROTECTION

CARGO COMPARTMENT FIRE PROTECTION SYSTEM The forward and aft cargo compartments on the E-JETS are class C. Both cargo compartments are protected by the CARGO SMOKE DETECTION SYSTEM and CARGO FIRE PROTECTION SYSTEM. Both systems can generate EICAS messages to alert for malfunctions.

CARGO COMPARTMENT SMOKE DETECTION Each cargo compartment has an independent smoke detection system. The forward cargo compartment has three smoke detectors. The aft cargo compartment has two smoke detectors. The system is monitored by a periodic built-in test, generating the associated alarms and EICAS messages. After smoke detection in the forward compartment, the air circulation fan in the forward compartment automatically turns off and the ventilation outflow valve closes.

SYSTEM INDICATIONS AURAL – Aural warning. LIGHTS – The master WARNING lights flashing. – The associated cargo compartment extinguishing button illuminates. EICAS – CRG AFT SMOKE;

AOM-1502-003

– CRG FWD SMOKE.

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REVISION 20

Cargo Compartment Fire Protection

Page 1

SYSTEMS DESCRIPTION FIRE PROTECTION

AIRPLANE OPERATIONS MANUAL

SYSTEM AUTOMATION FORWARD CARGO COMPARTMENT Because of the capability to carry live animals in the forward cargo compartment a ventilation system is installed and must be turned off in case of smoke or fire inside the forward cargo compartment. After fire or smoke is detected in the forward cargo compartment the following actions are automatically commanded by the system: – Air circulation fan is turned off; – The high-rate fire extinguishing bottle is armed and; – The forward cargo compartment ventilation outflow valve is commanded closed. AFT CARGO COMPARTMENT After fire or smoke is detected in the aft cargo compartment the following action is automatically commanded by the system: – The high-rate fire extinguishing bottle is armed.

CARGO COMPARTMENT FIRE EXTINGUISHING The Cargo Fire Extinguishing System is comprised of: – One high-rate extinguisher bottle and; – One low-rate extinguisher bottle. Both extinguisher bottles are installed in the center avionics bay and used in either forward or aft cargo compartment.

ANNUNCIATED FIRE EXTINGUISHING After the annunciation of smoke detection in the cargo compartment, pressing the associated cargo compartment button causes: – the high-rate fire-extinguishing bottle to discharge immediately into the selected cargo compartment.

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Page 2

Cargo Compartment Fire Protection

REVISION 20

AOM-1502-003

– the EICAS ADVISORY message CRG FIREX HI DISCH to display.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FIRE PROTECTION

One minute later, the second fire-extinguishing bottle discharges automatically at a reduced flow rate and the agent remains in the selected cargo compartment for 75 minutes for airplanes with 60-minute diversion time allowed. NOTE: – Pressing the associated pushbutton before the one-minute period immediately discharges the low-rate extinguishing bottle. – In case of fire on ground, the low-rate fire-extinguishing bottle is not automatically discharged. The flight crew must push the cargo fire-extinguishing pushbutton once again to discharge the low-rate bottle. – After a discharge event, when the airplane is on ground, the message CRG FWD (AFT) SYS FAIL may display on EICAS. CARGO COMPARTMENT FIRE EXTINGUISHING - WITH MESSAGE Bottle Discharge High-rate Bottle Low-rate Bottle Automatic after 1 In-flight Push the button once minute On-ground Push the button once Push the button once

NON-ANNUNCIATED FIRE EXTINGUISHING The system can be used even without a cargo smoke warning. In this case, the high-rate bottle is armed by pushing the respective cargo fire extinguisher button and is indicated by the red button light and the associated EICAS message. If the button is pushed again within the next two minutes, the high-rate bottle is discharged. At this time the low-rate bottle is armed. In case the flight crew does not push the button within the next two minutes, the system is reset and the high-rate bottle will not discharge. NOTE: After a discharge event, when the airplane is on ground, the message CRG FWD (AFT) SYS FAIL may display on EICAS.

AOM-1502-003

In flight, the second bottle will automatically discharge after one minute. On ground, the automatic timer feature for discharge of FIREX LO is disabled, however FIREX LO remains armed and can be manually discharged by depressing the appropriate button.

14-07-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Cargo Compartment Fire Protection

Page 3

SYSTEMS DESCRIPTION FIRE PROTECTION

AIRPLANE OPERATIONS MANUAL

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Page 4

Cargo Compartment Fire Protection

REVISION 20

AOM-1502-003

CARGO COMPARTMENT FIRE EXTINGUISHING - WITHOUT MESSAGE Bottle Discharge High-rate Bottle Low-rate Bottle Automatic after 1 In-flight Push the button twice minute On-ground Push the button twice Push the button once

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FIRE PROTECTION

LAVATORY FIRE PROTECTION SYSTEM The Lavatory Smoke Detection and Fire Extinguishing Systems protect the forward and aft lavatories. Each lavatory has a dedicated fire protection system.

LAVATORY SMOKE DETECTION The Lavatory Smoke Detection System consists of one smoke sensor installed on each lavatory ceiling. If – – –

smoke is detected in either lavatory: the master WARNING lights illuminate. the EICAS WARNING message LAV SMOKE is displayed. in the lavatory where the smoke has been detected an alarm sounds and the smoke detector light comes on. – a flashing orange light on the respective attendant lights panel (rainbow lights) illuminates.

LAVATORY FIRE EXTINGUISHING The Fire Extinguishing System consists of one fire-extinguisher bottle installed on each lavatory waste container. When the temperature inside the waste container exceeds a certain limit, the system automatically discharges the extinguishing agent. If required, the flight attendant can suppress the fire by using a portable fire extinguisher.

AOM-1502-003

LAVATORY DETECTORS AND EXTINGUISHERS LOCATION

14-07-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Lavatory Fire Protection

Page 1

SYSTEMS DESCRIPTION FIRE PROTECTION

AIRPLANE OPERATIONS MANUAL

POWER INDICATOR LIGHT

INTERRUPT SWITCH

SELF−TEST SWITCH

SENSOR

ALARM INDICATOR LIGHT

ALARM HORN

FIRE EXTINGUISHER BOTTLE

PRESSURE GAUGE

AUTO DRAIN VALVE

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Page 2

Lavatory Fire Protection

REVISION 18

AOM-1502-003

EM170AOM140238A.DGN

MANUAL SHUTOFF VALVE

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

POWER INDICATOR LIGHT

FIRE PROTECTION

INTERRUPT SWITCH

SELF−TEST SWITCH

SENSOR

ALARM INDICATOR LIGHT

ALARM HORN

FIRE EXTINGUISHER BOTTLE

AOM-1502-003

MANUAL SHUTOFF VALVE

AUTO DRAIN VALVE

EM170AOM140237B.DGN

PRESSURE GAUGE

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REVISION 18

Lavatory Fire Protection

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FIRE PROTECTION

!Airplanes equipped with lavatory smoke photoelectric detector HORN CANCEL SWITCH

POWER INDICATOR LIGHT

ALARM HORN SELF−TEST SWITCH

FIRE EXTINGUISHER BOTTLE

PRESSURE GAUGE

AUTO DRAIN VALVE

EM170AOM141095B.DGN

MANUAL SHUTOFF VALVE

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Page 4

Lavatory Fire Protection

REVISION 18

AOM-1502-003

"

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FIRE PROTECTION

!Airplanes equipped with lavatory smoke photoelectric detector HORN CANCEL SWITCH

POWER INDICATOR LIGHT

ALARM HORN SELF−TEST SWITCH

FIRE EXTINGUISHER BOTTLE

MANUAL SHUTOFF VALVE

AUTO DRAIN VALVE

EM170AOM141096B.DGN

PRESSURE GAUGE

AOM-1502-003

"

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REVISION 18

Lavatory Fire Protection

Page 5

SYSTEMS DESCRIPTION FIRE PROTECTION

AIRPLANE OPERATIONS MANUAL

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Page 6

Lavatory Fire Protection

REVISION 18

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FIRE PROTECTION

FIRE DETECTION SYSTEM TEST The fire detection test button on the control panel provides a manual test for the following systems: – Engine fire detection; – APU fire detection; – Cargo smoke detection. When the TEST button on the fire protection panel is pressed, it initiates the following: AURAL – The fire aural warnings sound. LIGHTS – The master WARNING lights flash. – The fire extinguisher handles illuminate steady. – The cargo fire-extinguishing buttons illuminate steady. – The APU fire-extinguishing button and the upper half of the APU emergency stop button to illuminate. EICAS MESSAGES – – – – –

ENG 1 FIRE; ENG 2 FIRE; APU FIRE; CRG AFT SMOKE; CRG FWD SMOKE.

EICAS INDICATIONS – The FIRE warning light on the ITT indicators illuminate. SYSTEM CONFIGURATIONS – The forward cargo compartment fan turns off – The cargo compartment ventilation outflow valve closes – only when bleed air is being provided by the engines or the APU.

AOM-1502-003

CAUTION: IF THE FIRE DETECTION TEST BUTTON IS PRESSED FOR 10 SECONDS, THE APU WILL SHUTDOWN.

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REVISION 11

Fire Detection System Test

Page 1

SYSTEMS DESCRIPTION FIRE PROTECTION

AIRPLANE OPERATIONS MANUAL

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Page 2

Fire Detection System Test

REVISION 11

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FIRE PROTECTION

EICAS MESSAGES TYPE

WARNING

AOM-1502-003

CAUTION

MESSAGE

MEANING A fire condition has been APU FIRE detected in the APU. Smoke has been detected CRG AFT (FWD) SMOKE in the associated cargo compartment. A fire condition has been ENG 1 (2) FIRE detected in the associated engine. Smoke has been detected LAV SMOKE in the lavatory. APU fire detection system APU FIRE DET FAIL has failed. APU fire-extinguisher APU FIREX FAIL bottle has failed. All smoke detectors have failed in the associated compartment, or Pressure in any CRG AFT (FWD) FIRE extinguisher bottle is low SYS FAIL and the cartridges are intact, or any of the cartridge circuits are opened. ENG 1 (2) FIRE DET Engine fire detection FAIL system has failed. Lavatory smoke detection LAV SMOKE DET FAIL system has failed.

14-07-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

EICAS Messages

Page 1

FIRE PROTECTION

TYPE

AIRPLANE OPERATIONS MANUAL

MESSAGE APU FIREXBTL DISCH

CRG FIRE PROT FAULT

ADVISORY

CRG FWD (AFT) FIREX HI ARM CRG FWD (AFT) FIREX LO ARM ENG 1 (2) FIREXBTL A (B) FAIL ENG FIREXBTL A (B) DISCH

STATUS

CRG FIREX HI (LO) DISCH

MEANING APU fire-extinguisher bottle has been discharged. Failures of smoke detectors in a Cargo Compartment or any SPDA internal failure, which does not render the smoke detection completely inoperative. High rate Cargo Firex system armed either automatically or manually. Low rate Cargo Firex system armed after High rate bottle discharged. Associated fire-extinguisher bottle has failed. Associated fire-extinguisher bottle has been discharged. Cargo high-rate (low-rate) discharge fire-extinguisher bottle has been discharged.

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Page 2

EICAS Messages

REVISION 9

AOM-1502-003

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

SECTION 14-08 FLIGHT CONTROLS TABLE OF CONTENTS Block

Page

General Description............................................. 14-08-01 .... GENERAL DESCRIPTION..................................... 14-08-01 ....

1 1

AOM-1502-003

Controls and Indications..................................... 14-08-05 .... 1 CONTROL WHEEL................................................ 14-08-05 .... 1 SLAT/FLAP SELECTOR LEVER........................... 14-08-05 .... 2 SPEED BRAKE LEVER......................................... 14-08-05 .... 4 TRIM PANEL.......................................................... 14-08-05 .... 5 FLIGHT CONTROL MODE PANEL....................... 14-08-05 .... 7 DISCONNECT HANDLE........................................ 14-08-05 .... 8 FLIGHT CONTROLS SYNOPTIC PAGE ON MFD.. 14-08-05 .... 9 EICAS INDICATION............................................... 14-08-05 .... 13 FCS Description................................................... 14-08-10 .... FLY BY WIRE COMPONENTS.............................. 14-08-10 .... ACTUATOR CONTROL ELECTRONICS (ACE). . . 14-08-10 .... FLIGHT CONTROL MODULES (FCMs)................ 14-08-10 .... MODES OF OPERATION...................................... 14-08-10 .... FCM, P-ACE AND AIRPLANE LEVEL COMMUNICATION.......................................... 14-08-10 .... POWER UP BUILT IN TEST (PBIT)...................... 14-08-10 .... FLY BY WIRE (FBW) BACKUP BATTERY............ 14-08-10 ....

1 1 1 2 3

Pitch Control......................................................... 14-08-15 .... PITCH CONTROL.................................................. 14-08-15 .... ELEVATOR CONTROL SYSTEM.......................... 14-08-15 .... HORIZONTAL STABILIZER CONTROL SYSTEM.. 14-08-15 .... STABILIZER TRIM................................................. 14-08-15 ....

1 1 1 6 7

Roll Control........................................................... 14-08-20 .... ROLL CONTROL................................................... 14-08-20 .... AILERON CONTROL SYSTEM............................. 14-08-20 ....

1 1 3

4 7 9

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REVISION 17

Table of Contents

Page 1

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

Yaw Control.......................................................... 14-08-25 .... YAW CONTROL..................................................... 14-08-25 .... RUDDER CONTROL SYSTEM............................. 14-08-25 .... RUDDER TRIM SYSTEM...................................... 14-08-25 ....

1 1 1 3

Slat/Flap System.................................................. 14-08-30 .... SLAT/FLAP SYSTEM............................................. 14-08-30 .... SLAT/FLAP PROTECTION LOGIC........................ 14-08-30 .... SLAT/FLAP SYSTEM INTERLOCKS..................... 14-08-30 ....

1 1 4 4

Spoiler System..................................................... 14-08-35 .... SPOILER SYSTEM................................................ 14-08-35 .... GROUND OPERATION......................................... 14-08-35 .... IN-FLIGHT OPERATION........................................ 14-08-35 ....

1 1 3 3

EICAS Messages.................................................. 14-08-45 .... EICAS MESSAGES............................................... 14-08-45 ....

1 1

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Page 2

Table of Contents

REVISION 17

AOM-1502-003

Block Page MULTIFUNCTION SPOILER CONTROL SYSTEM.. 14-08-20 .... 4 ROLL TRIM............................................................ 14-08-20 .... 5

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

GENERAL DESCRIPTION The Flight Control System is comprised of the primary and the secondary flight control systems and their associated system components. The primary flight control system consists of: • Ailerons and the multi function roll spoilers for roll axis control. • Elevators for pitch axis control. • Rudder for yaw axis control. The secondary flight control system consists of: • Horizontal stabilizer. • Flaps and Slats. • The multi-function spoiler (when used as speed brakes or ground spoilers). • Dedicated ground spoilers. Hydraulic actuators control the respective flight control surfaces. These are referred to as Power Control Units (PCUs). The ailerons are commanded by conventional control cables that run from each control wheel back to a pair of hydro-mechanical actuators. Elevators, rudders, roll spoilers as well as all secondary flight control systems, including the horizontal stabilizer, flaps and slats, ground spoilers and speed brakes, are controlled electronically using Fly-by-Wire (FBW) technology. The primary flight control electronics include two complementary parts: • The Primary Actuator Control Electronics (P-ACE). • The Flight Control Module (FCM).

AOM-1502-003

Primary Actuator Control Electronics (P-ACE) and/or Flight Control Modules (FCM) are employed to operate the respective electro-hydraulic or electro-mechanical actuators.

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REVISION 9

General Description

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT CONTROLS

AILERON

SLATS

ELEVATOR FLAPS

HORIZONTAL STABILIZER GROUND SPOILERS

MULTI−FUNCTION SPOILERS

EM170AOM140092.DGN

RUDDER

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Page 2

General Description

REVISION 9

AOM-1502-003

CONTROL SURFACE LOCATION

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT CONTROLS

CONTROL WHEEL

N

D

MIC

P T T

O F F

C

U

A

P TRI

R

ONO

T − ST O P

−R

M

D

ST

HO T A

HR

SE T

P

E

1

I S C

AP

FD

T C S

EM170AOM140108A.DGN

2

1 - PITCH TRIM SWITCH (SPRING-LOADED TO NEUTRAL) – Trims the airplane when the autopilot is not engaged. – If only half of the switch is actuated for more than 7 s, the switch will be automatically deactivated. – Manual pilot trim commands are limited to 3 s. NOTE: Captain’s pitch trim switch actuation has priority over the first officer’s. 2 - AP/TRIM DISCONNECT BUTTON Trim

AOM-1502-003

– Disables both HS-ACE channels when the switches remain pressed, thus disconnecting the autopilot and stopping any active trim command. – Releasing the button will activate the channel again.

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REVISION 18

Controls and Indications

Page 1

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

Autopilot – Refer to Automatic Flight.

SLAT/FLAP SELECTOR LEVER CONTROL PEDESTAL

UP

0

0

1

1

SLAT / FLAP

FULL

FULL DOWN

EM170AOM140106.DGN

5

5

Lever position 0 1 2 3 4

Slat position 0° 15° 15° 15° 25°

Flap position 0° 5° 10° 20° 20°

Detent/Gated Detent/Stop Detent Detent Detent Gated/Stop

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Page 2

Controls and Indications

REVISION 18

AOM-1502-003

– Selects slat/flap position by unlatching the lever and lifting a trigger below the head. – Intermediate positions are not enabled. If lever is left at an intermediate position, flaps/slats remain in the last selected position. Position 4 is gated for normal Go Around and Takeoff. Position 5 is used for landing.

AIRPLANE OPERATIONS MANUAL

AOM-1502-003

Lever position 5 Full

Slat position 25° 25°

SYSTEMS DESCRIPTION

Flap position 20° 35°

FLIGHT CONTROLS

Detent/Gated Detent Detent/Stop

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REVISION 18

Controls and Indications

Page 3

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

SPEED BRAKE LEVER CONTROL PEDESTAL

CLOSE 0

0

FULL

FULL OPEN

EM170AOM140105.DGN

1/2

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Page 4

Controls and Indications

REVISION 18

AOM-1502-003

– Symmetrically deploys the multi-function panels. All multi function spoiler panels deploy at the same angle in response to the speed brake lever position.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT CONTROLS

TRIM PANEL

CONTROL PEDESTAL

TRIM PITCH

ROLL

BACKUP SW

2

DN LWD

RWD

4 UP

YAW LEFT

SYS 1 CUTOUT

5

SYS 2 CUTOUT

RIGHT EM170AOM140107.DGN

1

AOM-1502-003

3

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REVISION 18

Controls and Indications

Page 5

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

1 - YAW TRIM KNOB (SPRING-LOADED TO NEUTRAL) – Actuates the yaw trim to left or right. – Manual pilot trim commands are limited to 3 s. 2 - ROLL TRIM SWITCH (SPRING-LOADED TO NEUTRAL) – Actuates the roll trim to left or right. – Manual pilot trim commands are limited to 3 s. 3 - PITCH TRIM NEUTRAL)

BACK-UP

SWITCH

(SPRING-LOADED

TO

– Operation of the switch while the autopilot is engaged causes the autopilot to disengage. – Manual pilot trim commands are limited to 3 s. 4 - PITCH TRIM SYS 1 CUTOUT BUTTON (GUARDED) PUSH IN: disables the HS-ACE channel 1. PUSH OUT: enables the HS-ACE channel 1. 5 - PITCH TRIM SYS 2 CUTOUT BUTTON (GUARDED)

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Page 6

Controls and Indications

REVISION 18

AOM-1502-003

PUSH IN: disables the HS-ACE channel 2. PUSH OUT: enables the HS-ACE channel 2.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT CONTROLS

FLIGHT CONTROL MODE PANEL

CONTROL PEDESTAL

FLIGHT ELEVATORS

CONTROLS RUDDER

STALL

MODE SPOILERS

WARNING

SHAKER 1 CUTOUT

SHAKER 2 CUTOUT

EM170AOM140345A.DGN

1

1 - FLIGHT CONTROL MODE BUTTON (GUARDED)

AOM-1502-003

PUSH IN: places the associated flight system into direct mode. PUSH OUT: places the associated flight system into normal mode.

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REVISION 18

Controls and Indications

Page 7

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

DISCONNECT HANDLE

EM170AOM140347.DGN

2

1

1 - ELEVATOR DISCONNECT HANDLE PULL: isolates the Captain and First Officer’s control columns for elevator control. 2 - AILERON DISCONNECT HANDLE

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Page 8

Controls and Indications

REVISION 18

AOM-1502-003

PULL: isolates the Captain and First Officer’s control wheel for aileron control.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT CONTROLS

FLIGHT CONTROLS SYNOPTIC PAGE ON MFD The flight controls synoptic page provides a visual representation of the flight controls system operation and parameters, and can be selected by the flight crew for viewing on either MFD.

1

7

Systems Flt Ctrl

Plan

Map

2

ELEC PBIT 16 HYDR PBIT 04

3 STATUS HYD SYS

MODE

RUDDER

3

NORMAL

ON

STBY

ELEV LH

1

DIRECT

ON

STBY

FAIL

ELEV RH

6

AOM-1502-003

ACTUATORS

5

4

EM170AOM140304D.DGN

SURFACE

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REVISION 18

Controls and Indications

Page 9

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT CONTROLS

B

C

D

G

F

H

E

EM170AOM140852A.DGN

A

1 - AIRPLANE GRAPHIC – A static display that shows the location of flight control surfaces, status of the flight control actuators and flight controls mode of operation.

A.

RETRACTED: a green line aligned with the wings, elevator or rudder.

B.

DEPLOYED: a green line and the surface with green stripes. A white dashed box is shown only for surface position greater than 50% of its deflection.

C.

FAILED RETRACTED: an amber line, a white dashed box and an amber cross.

D.

FAILED DEPLOYED: white dashed box, surface with amber stripes and amber cross.

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Page 10

Controls and Indications

REVISION 18

AOM-1502-003

2 - SURFACE POSITION STATUS

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

E.

NOT AVAILABLE WITH NO FAIL INDICATION: shows a white dashed box for surfaces with deflection in one direction (e.g. spoilers) and two white dashed box for surfaces with deflection in two directions (e.g. ailerons).

F.

NOT AVAILABLE WITH FAILURE INDICATION: shows a white dashed box and an amber cross for surfaces with deflection in one direction (e.g. spoilers) and two white dashed box and two amber crosses for surfaces with deflection in two directions (e.g. rudder).

G.

DIRECT MODE: shows the surface with amber stripes. A white dashed box is shown only for surface position greater than 50% of its maximum deflection. As for flap zero the maximum surface deflection is about 50% of the full deflection, the white dashed box may not be shown, due to system tolerances.

H.

FULL DEPLOYED: solid green box.

3 - FLIGHT CONTROL SYSTEM STATUS ANNUNCIATIONS – The status annunciations are shown in a table format for three surfaces. Three surfaces are listed in a column labeled SURFACE: RUDDER, ELEV LH, and ELEV RH. 4 - ACTUATOR STATUS ANNUNCIATION – The rudder has two actuators, upper and lower. Each left and right elevator surfaces have two actuators, inboard and outboard. – NORMAL/ACTIVE: a green ON annunciation inside a green rectangle box. – NORMAL/STANDBY: a white STBY annunciation inside a white rectangle box. – DIRECT/STANDBY: a white STBY annunciation inside a white rectangle box.

AOM-1502-003

– DIRECT/ACTIVE: an ON annunciation presented in an amber rectangle box background. – FAIL: a “—“ annunciation displayed in an amber rectangle box background.

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REVISION 18

Controls and Indications

Page 11

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

5 - AXES MODE ANNUNCIATION – Axes mode annunciations are shown for the rudder, the left and the right elevator. It is presented as NORMAL, DIRECT, FAIL or “-“, which indicates an invalid axes mode. 6 - HYDRAULIC SYSTEM SOURCE ANNUNCIATION – Hydraulic system source annunciations are shown for the rudder, the left and the right elevator. It is presented as 1, 2, 3 or “-“, which indicates an invalid source. 7 - PBIT REMAINING TIME READOUT – A digital remaining time readout displays the hours until the electrical and hydraulic PBIT expire.

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Page 12

Controls and Indications

REVISION 18

AOM-1502-003

– If the value of the PBIT remaining time readout is higher or equal to 5, the numbers will be displayed in green, otherwise will be cyan. Invalid data will be represented by 2 dashes (″- -″) in amber.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT CONTROLS

EICAS INDICATION SLAT/FLAP/SPEEDBRAKE INDICATION ON EICAS EICAS

3

SPDBRK

S

F

1 2 S/F

1

2

EM170AOM140110.DGN

SLAT/FLAP/SPDBRK

1 - SLAT/FLAP POSITION – Displays the slat/flap position. If the information is invalid, the indication will be removed from the display. GREEN: real-time surface position. – The cyan pointers show the slat/flap commanded position and the green slat/flap depictions show actual slat/flap position. The flap scale has tic marks at each end, representing positions at 0° and 35° while the slat scale has tic marks at each end, representing positions at 0° and 25°. 2 - SLAT/FLAP READOUT – Displays the slat/flap surface position. If the information is invalid, the indication will be removed from the display. GREEN DASHES: slat/flap in transit.

AOM-1502-003

NOTE: In case of slat/flap surface jamming, an additional box will be displayed in amber, as well as the readout. Whenever two boxes are displayed the possible values are 0, 3 or FULL for the slats and 0, 1, 2, 4 or FULL for the flaps based on the value of the surface angle. 3 - SPEEDBRAKE INDICATION

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REVISION 18

Controls and Indications

Page 13

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

– Displays a white SPDBRK annunciation when the airplane is in air. AMBER BOXED: in case of failure. NOTE: An OPEN and GREEN speedbrake position indication and a white GND SPLR annunciation display on EICAS after airplane touchdown when one of the Ground Spoiler panels open.

EICAS

SLAT/FLAP/SPDBRK

2 S/F

EM170AOM940017A.DGN

GND SPLR

S

NOTE: For SLAT/FLAP/SPDBRK position 0 the legend and arrows will be removed from the display as presented below:

EICAS

S/F

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Page 14

Controls and Indications

REVISION 18

AOM-1502-003

O

EM170AOM140109.DGN

SLAT/FLAP/SPDBRK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

!Airplanes Pre-Mod MAU load 23.1

NOTE: If SLAT/FLAP surface stops in an intermediate position, amber dashes are displayed on EICAS. !MAU load 23.1 and on

"

NOTE: If SLAT/FLAP surface stops in an intermediate position, the SLAT/FLAP READOUT will display the more retracted surface position. As an example, if flap fails between positions 2 and 3, the EICAS will indicate position 2. The FLAPS or SLATS indication 0 in amber indicate the surface may be between 0 and 1. Thus maximum altitude for flaps extended (20000 ft) must be respected.

AOM-1502-003

"

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REVISION 18

Controls and Indications

Page 15

SYSTEMS DESCRIPTION FLIGHT CONTROLS

SLAT/FLAP/SPDBRK

SPDBRK

S

3

AIRPLANE OPERATIONS MANUAL

SLAT/FLAP/SPDBRK

SPDBRK

S

F

O

3

S/F

F

FULL S/F

FLAP FAIL IN 0

FLAP FAIL IN FULL

SLAT/FLAP/SPDBRK

SPDBRK

S

3

SLAT/FLAP/SPDBRK

SPDBRK

S

F

1

O

S/F

F

-S/F

FLAP DATA INVALID OR UNAVAILABLE WHEN SLAT/ FLAP LEVER IS IN ZERO POSITION

FLAP FAIL IN 1

SLAT/FLAP/SPDBRK

SPDBRK

S

3

SLAT/FLAP/SPDBRK

SPDBRK

S

F

2

3

F

-S/F

S/F

FLAP DATA INVALID OR UNAVAILABLE WHEN SLAT/ FLAP LEVER IS NOT IN ZERO POSITION

FLAP FAIL IN 2

SLAT/FLAP/SPDBRK

SPDBRK

S

FULL

F

5

EM170AOM140111C.DGN

S/F FLAP FAIL IN 5

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Page 16

Controls and Indications

REVISION 18

AOM-1502-003

OVERALL DISPLAY SITUATIONS

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

ROLL/PITCH/YAW TRIM INDICATION ON EICAS

TRIMS

ROLL

PITCH UP

1

YAW

O.O

2

EM170AOM140364A.DGN

EICAS

1 - ROLL/PITCH/YAW TRIM SCALE – Trim position configuration is indicated by a solid green pointer in the scale. – There are five tic marks displayed along the roll and yaw scale, positioned at –100%, –50%, 0%, 50%, 100%. – There are five tic marks displayed along the pitch trim scale, positioned at 2° and 1.75° DOWN, 5.5°, 9.25°, and 13° UP. There is a green takeoff band on the scale extending from 1° DOWN to 6° UP, corresponding to the allowable pitch trim position for takeoff. 2 - PITCH TRIM DIGITAL READOUT – Digital indication of the horizontal stabilizer trim position in tenths of a degree increments.

AOM-1502-003

– An UP or DN indication displays above or below the readout according to the trim set. AMBER DASHES: pitch trim information is invalid.

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REVISION 18

Controls and Indications

Page 17

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

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Page 18

Controls and Indications

REVISION 18

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

FLY BY WIRE COMPONENTS Fly-by-wire is an electronic system designed to operate the flight controls replacing the control cables of a conventional airplane. The EMBRAER FBW system is composed of a set of nine Actuator Control Electronics (ACEs) and four Flight Control Modules (FCMs): – Three Primary-ACEs (P-ACE). – Two Slat/Flap ACEs (SF-ACE). – One Horizontal Stabilizer ACE (HS-ACE). – Three Spoiler ACEs (S-ACE). – Four Flight Control Modules (FCM).

ACTUATOR CONTROL ELECTRONICS (ACE) The ACE units connect the control column electronically to the respective control surface, providing direct analog control of the surface. There are four different ACE units:

PRIMARY CONTROL ELECTRONICS (P-ACE) The P-ACE units control the rudder and the elevator surfaces. There are three P-ACE units, two installed in the forward electronics bay and one installed in the aft electronics bay. Each P-ACE has two channels one is the active and the other is the standby.

SLAT/FLAP (SF-ACE)

ACTUATOR

CONTROL

ELECTRONICS

The SF-ACE units control the slat and flaps surface. There are two SF-ACE units installed in the middle electronics bay.

AOM-1502-003

Each SF-ACE has two channels one channel for flap and one channel for slat.

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REVISION 21

FCS Description

Page 1

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

HORIZONTAL STABILIZER ELECTRONICS (HS-ACE)

ACTUATOR

CONTROL

The HS-ACE unit controls the horizontal stabilizer surface. The Horizontal Stabilizer ACE (HS-ACE) is installed in the aft electronics bay. The HS-ACE has two channels one is the active and the other is the standby.

SPOILER ACTUATOR CONTROL ELECTRONICS (S-ACE) The S-ACE resides within the FCMs and is used to control the multifunction spoilers. Each FCM controls one pair of multi-function spoiler. FCM #1, FCM #3 and FCM #4 have wiring to control spoilers. FCM #2 does not control any spoiler pair.

FLIGHT CONTROL MODULES (FCMs) The FCMs provide software-based assistance to the P-ACE and is required for normal-mode operation of the flight controls system. The FCM units are connected to the P-ACE via the Controller Area Network Bus (CAN BUS), providing digital inputs to the P-ACE, which are combined with pilot inputs. This is used to augment pilot inputs for different airspeeds, and provides other high-level functions such as Angle-of-attack (AOA) limiting to the P-ACE units.

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Page 2

FCS Description

REVISION 21

AOM-1502-003

FCM 1 and 2 are located in the Modular Avionics Units # 1 (MAU 1) and FCM 3 and 4 are located in the Modular Avionics Unit # 3 (MAU 3).

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT CONTROLS

NORMAL MODE FCM AIRCRAFT SYSTEMS: ADS, IRS, FLAP & SLAT, FADEC, AFCS ...

FLIGHT CONTROL MODULE (HIGH LEVEL CONTROL, INTERFACING AND SIGNAL PROCESSING)

DIRECT MODE DIGITAL SIGNALS FLIGHT CONTROL SURFACE

ACE ANALOG SIGNALS

ACTUATOR CONTROL ELECTRONICS (CONTROL LIMITS SET BY HARDWARE AND AUGMENTED SOFTWARE FROM FCM)

ANALOG SIGNALS

EM170AOM140301A.DGN

COCKPIT CONTROL INPUTS

FLY-BY-WIRE SCHEMATIC

MODES OF OPERATION The Flight Control System provides two basic modes of operation: – NORMAL MODE: The Flight Control Module (FCM) provides software based airspeed gain schedules and control limits to the P-ACE, as well as high level functions such as: – Elevator control laws scheduling with airspeed. – Auto-thrust compensation with elevator. – Angle-of-Attack (AOA) limiting with elevator offset. – Rudder airspeed gain scheduling and stroke limiting. – Yaw damper and turn coordination via AFCS. – Rudder flight authority.

AOM-1502-003

– Roll spoiler scheduling with airspeed and speedbrake deployment.

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REVISION 21

FCS Description

Page 3

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

– Configuration change compensation with horizontal stabilizer due to speed brakes actuation. – DIRECT MODE: The FCM is removed from the control loop (for instance, due to loss of airspeed data) and the control limits default to values set by hardware in the P-ACE. – Direct mode of operation is primarily the result of loss of data from all FCM (no airspeed input) or; multiple ACE failures. – Operation is defaulted to fixed control laws configuration. – Control input provided by Captain and First Officer’s sensors is sent directly to the surface.

NORMAL MODE vs DIRECT MODE SELECTION The mode selection is automatic when a channel failure is detected or manually selected by using a “Mode Select” switch on the Flight Control Panel. The “Mode Selection” switch provides the capability to the flight crew to reset the system to Normal Mode in case of the system defaulting to Direct Mode, or to manually default the flight control system to Direct Mode in case of a wrong gain computed by the FCMs being transmitted to the P-ACEs or S-ACEs. In this case the “Mode Selection” switch toggles the Normal Channel of the active P-ACE to the Direct Channel of the standby P-ACE. The pilot always has supreme control authority of the airplane since the FCMs cannot override a pilot input.

FCM, P-ACE AND COMMUNICATION

AIRPLANE

LEVEL

The Controller Area Network BUS (CAN BUS) is the communication link between the FCMs and the P-ACE units while the Avionics Standard Communication Bus (ASCB) provides data exchange between all FCMs, and with other components of the avionic system. The following systems provide data to the flight controls system: – Smart probes and the Air Data Application (ADA) modules provide air data for various airspeed augmentation commands.

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Page 4

FCS Description

REVISION 21

AOM-1502-003

– The IRS provides airplane attitude and accelerations to the FCMs used for AOA limiting function computation.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

– The Proximity Sensor Electronic Module (PSEM) provides Weight-On-Wheels (WOW) and ground spoiler position data to the FCMs. – Brake Control Modules (BCM) provide wheel speed signals used for ground spoiler deployment.

AOM-1502-003

– The FADEC provide Thrust Lever Angle (TLA) to the FCMs used for elevator thrust compensation, and the Automatic Flight Control System (AFCS) provides autopilot commands. – Data is shared for the EICAS to display warnings, cautions, advisory and system status and also provided to the central maintenance computer (CMC) for system diagnostics.

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REVISION 21

FCS Description

Page 5

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT CONTROLS

FLT CTL PANEL

STATUS − ELECTRONIC − ACTUATION − MODE SURFACE POSITION

ASCB DATA BUS

WARNINGS

MAU FBW CONTROL SURFACES

PCU

P−ACE

CAN BUS

CAUTIONS

FCM

ADVISORIES EICAS

PCU

SYSTEM SYNOPTICS

ASCB

FCM (ELEVATOR, RUDDER, MULTI− FUNCTIONS SPOILERS)

P−ACE

MAU

CMC

FCM

PRIMARY CAN DATA BUS

ADC

(SECONDARY NOT SHOWN)

EM170AOM140096B.DGN

FCM CAN BUS

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Page 6

FCS Description

REVISION 21

AOM-1502-003

AIRPLANE COMMUNICATION INTERFACE

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

POWER UP BUILT IN TEST (PBIT) The Power Up Built in Test (PBIT) reduces the flight control system exposition to latent faults, ensuring that the system components remain capable of executing their functions. The PBIT is provided for both the Electrical and Hydraulic systems. !MAU load 21.2 and on OR POST-MOD SB 170-31-0028

The PBIT expires after 50 hours (elapsed time) since the last successful PBIT. Once the PBIT is expired, FLT CTRL BIT EXPIRED EICAS CAUTION message is displayed. This EICAS CAUTION message is provided for both Electrical PBIT and Hydraulic PBIT. The message remains displayed on EICAS until a new Electrical or Hydraulic PBIT is successfully performed. No action is required if the PBIT expires in-flight, as the EICAS CAUTION message will only be displayed after landing. "

ELECTRICAL POWER UP BUILT IN TEST The Electrical PBIT provides detection of out-of-tolerance conditions and failures in the FCMs, P-ACEs and SF-ACEs. The Electrical PBIT is automatically performed during power up after the airplane is powered by any AC source and takes approximately 3 min to complete. If the FLT CTRL BIT EXPIRED message is displayed, the electrical built in test must be performed. The FLT CTRL TEST IN PROG Status message is displayed while electrical PBIT is in progress. If the airplane is already powered up, the crew may check the PBIT REMAINING TIME READOUT before starting the taxi out procedure. If the remaining time is sufficient for the taxi and takeoff, the crew may elect to reset the PBIT on the next flight.

AOM-1502-003

The Electrical PBIT will be interrupted if any electric hydraulic pump is turned ON, if the FCP switches are cycled or if AC power is interrupted while the test is running.

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REVISION 21

FCS Description

Page 7

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT CONTROLS

HYDRAULIC POWER UP BUILT IN TEST The Hydraulic PBIT provides functional test of the flight control actuators. The Hydraulic PBIT is performed automatically, only on the ground when all three hydraulic systems are pressurized. The test takes 1 minute to complete and will be interrupted if any flight control surface is moved while the test is in progress. !MAU load 21.2 and on OR POST-MOD SB 170-31-0028

The FLT CTRL TEST IN PROG Status message is displayed while hydraulic PBIT is in progress. " !MAU load 21.4 and on

The Hydraulic PBIT is not performed if the temperatures within the hydraulic reservoir are lower than 50°F (10°C). When FLT CTRL BIT EXPIRED is set the temperature-based inhibition is removed. The Hydraulic PBIT does not unintentionally re-run in case of momentary loss of hydraulic validity or hydraulic pressure on a single hydraulic system. To re-run the Hydraulic PBIT all three hydraulic systems must be depressurized and then pressurized. "

FLIGHT CONTROLS CONFIGURATION

ODD

EVEN

DAY

ENGAGE

For the rudder, elevator and stabilizer control surfaces which have two controlling channels, the flight control system has a function to select which set of channels would be the active channels for a particular day. This function, called the ‘Odd-Even Day Engage’ configuration is implemented to reduce the latency in the flight control system and to allow for even wear of the flight control system components.

Rudder

Odd Upper Channel Hydraulics 1

Even Lower Channel Hydraulics 3

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Page 8

FCS Description

REVISION 21

AOM-1502-003

The ‘Odd-Even Day Engage’ function provides the following selection grouping for the rudder, elevator and horizontal stabilizer surfaces which can be view in the flight controls synoptic page on either MFD.

AIRPLANE OPERATIONS MANUAL

Left Elevator Right Elevator

Odd Inboard Channel Hydraulics 2 Outboard Channel Hydraulics 3

SYSTEMS DESCRIPTION FLIGHT CONTROLS

Even Outboard Channel Hydraulics 1 Inboard Channel Hydraulics 2

During normal operation, the Odd-Even Day Engage function may engage in a different configuration from that shown above. If this scenario occurs, no maintenance action will be required to release the airplane for service unless there is a CAS message related to the flight controls system.

FLY BY WIRE (FBW) BACKUP BATTERY In case of an extremely improbable failure that would render complete loss of normal and emergency electrical power to the FBW, the backup power system, with no pilot intervention, keeps the appropriate number of elevator and rudder actuators operating for at least 15 min. There is no dedicated message to indicate the failure of this system; therefore there is no flight crew action required if this happens. This backup system is comprised by a dedicated battery, distribution bus and circuit breakers. The backup battery is charged by the DC ESS 3 bus during normal operation and consists of sealed lead acid cells with built-in-test (BIT) capability and an internal heater that guarantees the minimum battery temperature.

AOM-1502-003

Although the battery is connected to the airplane buses, the use of an internal rectifier keeps it from powering back the buses, assuring isolation in case of failure in the main electrical power system.

14-08-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

FCS Description

Page 9

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

14-08-10 Copyright © by Embraer. Refer to cover page for details.

Page 10

FCS Description

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

PITCH CONTROL Pitch axis control is by means of electro-hydraulic commanded elevators and an electro-mechanical horizontal stabilizer.

ELEVATOR CONTROL SYSTEM Pilot’s inputs to the elevators are through the cockpit control columns in normal or direct mode. The elevators can be automatically controlled through the FCM via the autopilot.

ELEVATOR CONTROL SYSTEM COMPONENTS A total of four P-ACE channels are used to independently control each of the four PCUs, providing the analog elevator control functions implemented in the P-ACE units. Four independent FCM units, located in the MAU 1 and 3, provide high-level system augmentation to the P-ACE units, such as gain scheduling as a function of airspeed, elevator thrust compensation and AOA limiting.

ELEVATOR CONTROL SYSTEM OPERATION MODE NORMAL MODE: With the elevator control system operating in normal mode, the elevator moves according to gain scheduling as a function of airspeed, reducing elevator movement with increasing airspeeds. In the event of loss of airspeed information, the FCM is removed from the control loop, and the associated P-ACE reverts to direct mode. FCM functions and AOA limiting are then no longer available. DIRECT MODE: When the FCM is removed from the control loop the elevator system is reverted to direct mode automatically and the operation is defaulted to fixed control laws configuration.

AOM-1502-003

Elevator high level functions as well as the auto pilot are no longer available.

14-08-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Pitch Control

Page 1

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

POWER CONTROL UNIT (PCU) The elevator surfaces are hydraulically actuated through the PCU units. The hydraulic systems responsible for powering the actuators are: – Hydraulic System 1: left outboard actuator. – Hydraulic System 2: left & right inboard actuators. – Hydraulic System 3: right outboard actuator. Since the actuators on each surface operate on active/standby mode, the P-ACE automatically alternates the active actuator every time the elevator system is powered up. The loss of hydraulic supply forces the standby PCU to become active.

ELEVATOR JAM If a jam in one of the elevator actuator is detected, the respective elevator surface will remain fixed at the position where the jam occurred. The pilot will be able to control the airplane using the remaining elevator.

ELEVATOR FLIGHT CONTROL PANEL BUTTON A dedicated button on the Flight Control Mode panel provides the capability to the pilots to reset the elevator system to Normal Mode in case of the system defaulting to Direct Mode, or to manually default the elevator system to Direct Mode. When the flight control panel elevator button is pushed in, it commands all four elevator channel to change from Normal to Direct mode. In addition, pushing the button also results in the active elevator channels transitioning to the standby state, and the channels that were previously in standby would become active. This feature is also included to allow the system to transition away from the present controlling channels.

14-08-15 Copyright © by Embraer. Refer to cover page for details.

Page 2

Pitch Control

REVISION 17

AOM-1502-003

When the flight control panel elevator button is pushed out, the system reverts to the Normal Mode.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

ELEVATOR THRUST COMPENSATION FUNCTION (ETC) This function helps to reduce the pilot workload by applying elevator commands to reduce the pitching moment produced by increasing or decreasing engine thrust. The ETC function is computed in the FCM as a function of N1, mach and pressure altitude. Elevator command is limited to plus or minus 5°, and is applied proportional to the amount of engine thrust above or below the reference thrust setting. If one or more sensors required to perform the ETC function fail, the function is no longer available and the respective message will be displayed on the EICAS. For long term control, ETC commands are off-loaded in order to transfer the elevator offset to the stabilizer. This function termed ‘ETC Off-load’ allows the elevator to retain full authority, while providing elevator control to maintain flight path condition in the presence of thrust changes.

ARTIFICIAL FEEL UNITS (AFU) With no mechanical connection between the control column and the elevator surfaces, two independent feel units provide artificial feel and centering to the control columns, which increase as a function of control column displacement. The feel units consist of a preloaded spring, which returns the columns to the neutral position. There is one feel unit attached to each torque tube, in case of separation of the control columns commands, the feel system is still active for the non-jammed column. With the columns disconnected or with a single AFU disconnected, the feel loads on the column are reduced to one half of the normal loads.

DISCONNECT MECHANISM (JAMMED COLUMN) A disconnect mechanism is provided to allow separation of the First Officer and Captain’s control columns. In the event of a jam in one of the control columns, the disconnect mechanism can be actuated by pilots through the disconnect handle in the cockpit.

AOM-1502-003

Following a disconnection, the pilot of the non-jammed side retains pitch control by means of the on-side elevator. The system will remain disconnected for the remainder of the flight and ground maintenance is required to reset the disconnected unit.

14-08-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Pitch Control

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

PCU

EM170AOM140348.DGN

COCKPIT CONTROL SYSTEM

P−ACE

FCM OTHER AIRCRAFT SYSTEMS DISCONNECT MECHANISM

COCKPIT CONTROL SYSTEM

FCM

P−ACE

PCU

LEFT ELEVATOR SURFACE

RIGHT ELEVATOR SURFACE

FLIGHT CONTROLS

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Page 4

Pitch Control

REVISION 17

AOM-1502-003

ELEVATOR SYSTEM SCHEMATIC

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT CONTROLS

MODULAR AVIONICS UNITS

MAU − ASCB

FCM 1

AIR DATA SYSTEM A

FCM 2 B

A

FCM 3 B

A

AUTOMATIC FLIGHT CONTROL SYSTEM

FCM 4 B

A

B

CAN BUS RIGHT COLUMN LVDTs

RIGHT ELEVATOR SURFACE

P−ACE 3−1

P−ACE 2−2

LEFT COLUMN LVDTs

P−ACE 2−1

LEFT ELEVATOR SURFACE

EM170AOM140097B.DGN

P−ACE 1−1

AOM-1502-003

ELEVATOR SYSTEM INTERFACE

14-08-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Pitch Control

Page 5

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

HORIZONTAL STABILIZER CONTROL SYSTEM Control of the horizontal stabilizer is by means of an electromechanical system commanded by either: – The manual selection of the Captain or First Officer’s wheel main trim switches or pedestal mounted backup trim switches which directly control an electrical servo motor coupled to the Horizontal Stabilizer Actuator (HSA). – Or the Flight Control Module (FCM) for autopilot trim and speed brake auto trim which actuate the electrical servo-motor coupled to the Horizontal Stabilizer Actuator (HSA).

HORIZONTAL STABILIZER SYSTEM COMPONENTS Horizontal Stabilizer Actuator Control Electronics (HS-ACE) and one Horizontal Stabilizer Actuator (HSA) are used to move the control surface.

HORIZONTAL STABILIZER ACTUATOR

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Page 6

Pitch Control

REVISION 17

AOM-1502-003

The HSA is a single electrical-mechanical actuator. Two DC motors drive the actuator in an active/standby configuration. Stabilizer position is provided to the HS-ACE and is used for monitoring and EICAS indication.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

HORIZONTAL STABILIZER

N

D

MIC P

U

P T T

O F F

HO T

D

P T RI

M

A

AP

I S C

FD

T C S

TRIM PITCH

COCKPIT CONTROL SYSTEM

HS−ACE

BACKUP SW

ACTIVE HSA STANDBY

DN RWD

UP SYS 2

OTHER AIRCRAFT SYSTEMS

HORIZONTAL STABILIZER

FCM

EM170AOM140473A.DGN EM170AOM140473B.DGN

SYS 1

STABILIZER TRIM MANUAL TRIM The manual trim is commanded through switches installed on the control columns or a backup switch located on the main pedestal. Signals from either the control columns switches or the backup switch controls the electric trim motor.

AOM-1502-003

The backup trim switch and the control wheel trim switches are dual split switches which have a 7 s time limitation when actuated separately. If only one half of the switch is actuated for more than 7 s, that switch is automatically deactivated. The aural warning “TRIM” triggers for 7 s when the control wheel trim or backup trim switches have failed or when only half of switch is pressed. If the failure persists for more than 7 s, the aural message is deactivated and the applicable advisory pitch trim switch fail message is displayed on EICAS. In order to avoid a possible pitch trim runaway condition, manual pilot trim commands are limited to 3 s. After the control wheel trim or backup

14-08-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Pitch Control

Page 7

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

trim switches have both halves pressed for more than 3 s, the timer stops the horizontal stabilizer control surface movement and if the switch remains pressed, the aural warning “TRIM” triggers. When the switch is no more pressed, the aural warning stops. In case of stick shaker activation, the HS-ACE is prevented from responding to any pitch trim commands by a stick shaker signal from the AFCS. Stabilizer Trim priority Logic The HS-ACE responds to all trim commands with the following priority: 1.

Backup switches.

2.

Captain.

3.

First Officer.

4.

FCM (auto-trim) commands.

AUTOPILOT TRIM The autopilot can directly operate the electric trim motor when the autopilot is engaged. If the autopilot trim function is inoperative, the autopilot cannot be engaged. If this function is lost during autopilot operation, the autopilot will disengage. Autopilot trim function will be active only if: – Autopilot is engaged. – Configuration trim is operational. – Manual electric trim is not active. – On-side autopilot channel is priority. NOTE: In case of an electrical failure, followed by RAT deployment, the trim function will work at half speed operation, for either manual trim or autopilot trim.

ELECTRICAL EMERGENCY

14-08-15 Copyright © by Embraer. Refer to cover page for details.

Page 8

Pitch Control

REVISION 17

AOM-1502-003

In the event of an electrical emergency, only the HS-ACE channel 2 is operational at low rate. A loss of airspeed data from the FCM also results in low rate operation of the horizontal stabilizer, providing structural protection for the surface.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

ROLL CONTROL Lateral control system includes both conventional ailerons and the fly by wire multi function spoilers witch provides the roll axis control.

FWD TORQUE TUBES

AFT TORQUE TUBES

MULTIFUNCTION SPOILERS AILERON

FBW SYSTEM

AOM-1502-003

CABLE

EM170AOM140472A.DGN

MULTIFUNCTION SPOILERS AILERON

14-08-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 11

Roll Control

Page 1

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

LH CONTROL CABLE

RH CONTROL CABLE

EM170AOM140914A.DGN

RH CONTROL CABLE (REF.)

LH CONTROL CABLE (REF.)

14-08-20 Copyright © by Embraer. Refer to cover page for details.

Page 2

Roll Control

REVISION 11

AOM-1502-003

AILERON CABLES SCHEMATIC

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AILERON CONTROL SYSTEM Aileron control is accomplished through a conventional cable system, which transmits control wheel and autopilot inputs to the ailerons power control units. The power control units are driven by the following hydraulic systems: – Hydraulic System 2: left & right inboard PCU. – Hydraulic System 3: left & right outboard PCU. AILERONS JAM The aileron control system is divided into left and right half systems. The two halves are designed to tolerate single-point jams without loss of lateral control. In the event of a jam, the left and right sub-systems may be disconnected, thereby allowing command movements in the functional half-system. The jammed half of the aileron system can be disconnected by pulling the aileron disconnect handle located in the cockpit. Following a disconnect, the system remains separated for the remainder of the flight. Maintenance action is required to reconnect the disconnect device.

RIGHT AILERON JAM The First Officer’s half of the system is jammed. The Captain retains control of the left aileron and the pair #5 of multi-function spoilers will remain available with normal artificial feel.

LEFT AILERON JAM The Captain’s half of the system is jammed.

AOM-1502-003

The First Officer retains control of the right aileron without artificial feel and roll trim since the feel mechanism is attached to Captain’s half of the system, the pair #4 of multi-function spoilers will remain available.

14-08-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 11

Roll Control

Page 3

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

PCU DISCONNECT In the event of a disconnection of one aileron PCU from the surface or wing structure, the other PCU attached to the surface will operate normally, but the force authority will be halved. Hence the aileron PCUs normally share air-loads during flight, if the FCM detects a difference in load sharing from the actuators, a message will be displayed on the EICAS.

MULTIFUNCTION SPOILER CONTROL SYSTEM The multifunction spoiler control system consists of 6 panels numbered from inboard to outboard as: – L3, L4, L5 (left wing) and – R3, R4, R5 (right wing). The roll spoiler function drives all six multifunction spoiler panel deployment asymmetrically as a function of control wheel position.

MULTIFUNCTION SPOILER OPERATION MODE – NORMAL MODE: The Flight Control Module (FCM) provides software based airspeed gain schedules and control limits to the S-ACE, the spoiler deploys as a function of airspeed, reducing spoiler deployment with increasing airspeeds. – DIRECT MODE: In the event of a FCM failure, the spoiler associated with the FCM turns to the direct mode. The other spoilers remain in the normal mode.

ROLL CONTROL SURFACES POSITION

14-08-20 Copyright © by Embraer. Refer to cover page for details.

Page 4

Roll Control

REVISION 11

AOM-1502-003

AILERON

EM170AOM140098.DGN

MULTI−FUNCTION SPOILERS

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

ROLL TRIM The aileron control system is manually trimmed by using the roll trim switch on the trim control panel, located in the cockpit on the center pedestal. The trim system is operated via the roll trim switch on the trim control panel, commanding the actuator to move, and repositioning neutral feel position of the aileron system. The actuator is equipped with a timer, limiting a single trim command to three seconds. A quick disconnect switch, located on the control wheels, disables the roll trim actuator by interrupting DC power to the trim motor, as long as the switch remain depressed.

AILERON TRIM SERVO FAILURE In the event of a runaway of the aileron trim servo, the control wheel neutral point will shift and the pilot will be required to hold a constant force to maintain neutral lateral control. The pilot will retain full lateral control authority albeit with asymmetrical control forces.

AOM-1502-003

In the event a disconnection of the trim actuator occurs the feel and centering for the lateral control will be lost.

14-08-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 11

Roll Control

Page 5

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

14-08-20 Copyright © by Embraer. Refer to cover page for details.

Page 6

Roll Control

REVISION 11

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

YAW CONTROL Yaw control is performed by means of an electronic control system that commands electrohydraulic actuators of the rudders.

RUDDER CONTROL SYSTEM The rudder control system is controlled either by the pilots and FCM high-level functions. Additionally, it is controlled by autopilot in airplanes equipped with Autoland. The rudder control system moves a single rudder surface attached to the vertical stabilizer. Two actuators, or PCUs, electrically commanded and hydraulically powered, are connected to the rudder control surface, receiving signals from the rudder control’s Fly By Wire system (FBW). Either the upper or the lower rudder actuator can control the rudder surface. The Captain commands only the upper actuator and the First Officer commands only the lower actuator. The rudder actuators operate in an active/standby configuration, hence the P-ACEs alternate between the active PCU every time the rudder system is powered-up. The hydraulic systems responsible for actuating the actuators are: Hydraulic System 1: upper actuator, or PCU. Hydraulic System 3: lower actuator, or PCU.

RUDDER CONTROL SYSTEM COMPONENTS Two independent P-ACE modules drive the upper and lower PCU, providing the analog rudder control functions implemented in the P-ACE hardware.

AOM-1502-003

Four independent FCM units, located in MAU 1 and 3, provide highlevel system augmentation on the P-ACE units, such as yaw damping, turn coordination, as well as gain scheduling as a function of airspeed.

14-08-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Yaw Control

Page 1

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

RUDDER FLIGHT CONTROL PANEL BUTTON A dedicated button on the Flight Control Mode panel provides the capability to the pilots to alternate from Normal mode to Direct mode and vice-versa. PUSHED IN When the flight control panel rudder button is pushed in, it commands both rudder channels to change from Normal to Direct mode. It also results in the active rudder channels transitioning to the standby state, and the channels that were previously in standby would become active. This feature also allows the system to transition away from the current controlling channels to the standby channels. PUSHED OUT When the flight control panel rudder button is pushed out, the system recovers the Normal Mode.

RUDDER CONTROL SYSTEM OPERATION MODE Normal Mode: In the normal mode, the FCMs add further high-level functions to the pilot pedal inputs. With increasing airspeed, rudder gain is reduced by the FCM in order to compensate for the increase in rudder effectiveness, and providing structural protection to the rudder surface. Direct Mode: In the event of loss of airspeed information to the flight control system, the P-ACEs will revert to Direct mode using a fixed gain. There are two Direct mode fixed gains that are selected as a function of flaps/slats positions. LOW-SPEED FIXED GAIN Is selected for Flaps/Slats extended. The rudder is set at the maximum authority to ensure that the pilot has sufficient authority to control the aircraft during the approach and landing.

14-08-25 Copyright © by Embraer. Refer to cover page for details.

Page 2

Yaw Control

REVISION 17

AOM-1502-003

HIGH SPEED FIXED GAIN Is selected for flaps/slats retracted. Ensures that the rudder movement is limited at high speeds, providing structural protection.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

RUDDER JAM PEDAL JAMMED In case of pedal assemblies jammed, the rudder remains active and will be actuated by high-level functions (yaw dumping and turn coordination). PCU JAMMED In case of a jammed PCU actuator the rudder will be hydraulically locked at the current position. Aircraft control will be established through the ailerons and roll spoilers.

RUDDER TRIM SYSTEM

AOM-1502-003

Rudder trim function is limited to three seconds. If further displacement of the trim system is required the command must be released and reapplied. Position indication of the trim actuator is provided on the EICAS.

14-08-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Yaw Control

Page 3

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

MODULAR AVIONICS UNITS

MAU − ASCB

AIR DATA SYSTEM

FCM’s

LEFT PEDAL LVDT’S

AUTOMATIC FLIGHT CONTROL SYSTEM

AIR DATA SYSTEM

P−ACE 3−2 RIGHT PEDAL LVDT’S

RUDDER SURFACE

EM170AOM140230.DGN

P−ACE 1−2

14-08-25 Copyright © by Embraer. Refer to cover page for details.

Page 4

Yaw Control

REVISION 17

AOM-1502-003

RUDDER SYSTEM INTERFACE

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

SLAT/FLAP SYSTEM The high lift control system consists of flaps and slats. The slat system controls eight slat surfaces on the leading edge of the wing (four per wing) and the flap system controls four double slotted flap surfaces on the trailing edge (two per wing). Surface position commands are given to the Slat/Flap-ACE (SF-ACE) via a Slat/Flap control lever installed on the center pedestal in the cockpit.

SLAT INBOARD

SLAT OUTBOARD

FLAP OUTBOARD

EM170AOM140099.DGN

FLAP INBOARD

SLAT/FLAP PANEL LOCATION

AOM-1502-003

There are seven slat/flap control lever positions. Slat and flap motion is sequenced such that slats extend first and flaps retract first when the motion command requires both surfaces to move. The system uses electrical power to move the surfaces.

14-08-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 13

Slat/Flap System

Page 1

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

SLAT/FLAP SYSTEM COMPONENTS Deployment of both slats and flaps surfaces is commanded by two SF-ACEs and electrically operated using Power Driver Units (PDUs). Each SF-ACE is a dual channel unit, with one channel for flap control and one channel for slat control.

14-08-30 Copyright © by Embraer. Refer to cover page for details.

Page 2

Slat/Flap System

REVISION 13

AOM-1502-003

A total of four flap actuators per side provide the actuation force to extend and retract the flap panels mounted on the trailing edge of each wing. The double-slotted flap consists of a main flap panel and an aft flap panel for both inboard and outboard flaps.

AIRPLANE OPERATIONS MANUAL

SLAT/FLAP SELECTOR LEVER

SYSTEMS DESCRIPTION FLIGHT CONTROLS

UP

0

0

1

1

SLAT / FLAP 5

5

FULL

FULL DOWN

SLATS

SLATS

SLAT PDU

FLAPS

SF−ACE 2

FLAP PDU

FLAPS

EM170AOM140100B.DGN

SF−ACE 1

AOM-1502-003

SLAT/FLAP SYSTEM SCHEMATIC

14-08-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 13

Slat/Flap System

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT CONTROLS

SLAT/FLAP PROTECTION LOGIC SKEW PROTECTION Electronic skew sensors monitor differential movement between neighboring panels of flap (slat). If differential movement of a panel exceeds acceptable limits, the SF-ACES shuts down the flap (slat) system and the FLAP (SLAT) FAIL message displays on EICAS. The SLAT-FLAP LEVER DISAG may appear if the respective surface has not reached the position selected on the Slat/Flap Lever. The affected surface is inoperative for the remainder of the flight whereas the non-affected surface operates normally (i.e., in case of FLAP FAIL the Slats operates normally and vice-versa).

STRIKE PROTECTION The SF-ACE monitors PDU load and if an excessive load is detected it stops the electrical power to the respective PDU for further movement to the selected direction. The FLAP (SLAT) FAIL message displays and the SLAT-FLAP LEVER DISAG also displays, as the affected surface has not reached the selected position. In such cases, the affected surface can be commanded in the opposite direction (i.e., for FLAP FAIL during retraction, the Flap can be commanded for extension and vice-versa). When the strike protection actuates, the affected surface can be commanded in both directions if it is returned to the previously selected position. SF-ACE allows two attempts in addition to the first applied command that originated the excessive PDU load. After two unsuccessful attempts to select a position, the affected surface is de-energized since the strike protection cuts the PDU power for both directions.

SLAT/FLAP SYSTEM INTERLOCKS OPERATING WITH RAM AIR TURBINE (RAT)

If the Ram Air Turbine RAT is the only source of electric power, the flaps and slats operate in half speed, as only one channel remains available. Additionally, when RAT is the only source of electrical power, the SF-ACE prevents deployment of slats and flaps beyond position three to assure adequate airspeed for the RAT.

14-08-30 Copyright © by Embraer. Refer to cover page for details.

Page 4

Slat/Flap System

REVISION 13

AOM-1502-003

The SF-ACE has two independent channels that are powered by different electrical power sources.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

SLAT OR FLAP FAILURE In case of a Flap or Slat failure, when the affected surface is de-energized, the SF-ACE still commands the non-affected surface upon S/F Lever movement. This allows improved landing performance even in the event of failure by selecting a more appropriate position of the non-affected surface. However, there are some slat/flap combinations that are automatically protected by the system, as they would induce poor airplane controllability. Thus, the SF-ACE does not command the Flaps beyond 10° (S/F Lever on position 2) with the Slats below 15°. In this failure scenario, if the S/F Lever is commanded beyond the position 2, the SF-ACE limits the Flap deflection to 10° and the SLAT-FLAP LEVER DISAG message displays.

AOM-1502-003

The slat/flap interlock is disabled on ground allowing either surface be extended or retracted to any valid position regardless of the position of the other surface.

14-08-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 13

Slat/Flap System

Page 5

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

14-08-30 Copyright © by Embraer. Refer to cover page for details.

Page 6

Slat/Flap System

REVISION 13

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

SPOILER SYSTEM The spoiler control system consists of ten spoiler panels numbered inboard to outboard as follows: – L1, L2, L3, L4, L5 (left wing) and – R1, R2, R3, R4, R5 (right wing).

AOM-1502-003

Panels L3, R3, L4, R4, L5 and R5 are called multifunction spoilers and have three modes of operation: – Roll Control: deployed asymmetrically for roll augmentation as commanded by the pilots control wheel. Displacement angle is proportional to control wheel displacement. – Speed Brakes: deployed symmetrically during flight by speed brake handle to increase aerodynamic drag to reduce airspeed or increase rate of descent. Panel displacement is proportional to speed brake handle position. – Ground Spoilers: deployed symmetrically during landing roll to increase wheel braking efficiency and aerodynamic drag to reduce the stopping distance. Panels are fully and automatically extended when ground spoiler deployment conditions are met.

14-08-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Spoiler System

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

EM170AOM140102.DGN

FLIGHT CONTROLS

SPOILERS LOCATION

HYDRAULIC ACTUATOR

SYSTEM

ASSOCIATED

WITH

EACH

The hydraulic systems responsible for actuating the multi function PCUs are: – Hydraulic System 1: left and right inboard and middle PCUs (L3, R3, L4, R4). – Hydraulic System 2: left and right outboard PCUs (L5, R5). The hydraulic systems responsible for actuating the dedicated ground spoilers PCUs are: – Hydraulic System 1: left and right outboard PCUs (R2, L2).

14-08-35 Copyright © by Embraer. Refer to cover page for details.

Page 2

Spoiler System

REVISION 20

AOM-1502-003

– Hydraulic System 2: left and right inboard PCUs (R1, L1).

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

GROUND OPERATION The spoiler control system provides automatic ground spoiler deployment to increase wheel-braking efficiency reducing the lift generated by each wing and to reduce the stopping distance producing aerodynamic drag. During ground operation, all spoiler panels function as ground spoilers and are commanded to the fully extended or fully retracted positions. The ground spoiler function drives all ten spoiler’s panels to the limit deflection of the actuators.

MULTI-FUNCTION DEPLOYMENT

AND

GROUND

SPOILERS

After touchdown the FCM will command all multifunction spoiler surfaces to the 40° extended position and the ground spoiler surfaces to 60° when the following conditions are simultaneously met: – Weight on wheels on ground. – Wheel speed is above 45 kt or airspeed is above 60 KIAS. – Thrust Lever Angle (TLA) below 26°. Following rollout, the spoilers will automatically retract when wheel speed is below 45 kt for at least 5 s. If the throttles are moved beyond 35° (TLA) after landing, the spoiler panels will automatically retract. In a bounced landing, the FCM holds the “on ground” signal for 5 s after the WOW signals indicate “in air”. However, if the pilot commands TLA greater than 24° the ground spoilers are retracted. NOTE: In the direct mode, ground spoilers are not available.

IN-FLIGHT OPERATION ROLL SPOILERS The roll spoiler function drives the multifunction spoiler panels asymmetrically as a function of control wheel position.

AOM-1502-003

For further information on the roll spoilers operation, refer to AOM 14-08-20.

14-08-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Spoiler System

Page 3

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

SPEED BRAKES When actuating as speed brakes, the spoiler control system deploys all six multi function spoiler panels symmetrically up to the in-flight limit of 30 degrees following speed brake handle position. If extended during approach, the speed brakes will automatically retract upon selection of slat/flap 2 or above. Speed brakes will not be deployed if airspeed is below 180 KIAS, and will also automatically retract if airspeed decreases below this threshold. In order to prevent inadvertent operation during a go-around maneuver the speed brakes will automatically retract anytime the thrust levers are advanced beyond Thrust Lever Angle (TLA) 70 degrees. In the event of a disagreement of the speed brake handle position with actual surface position, the EICAS advisory message SPDBRK LEVER DISAG is displayed on the EICAS.

14-08-35 Copyright © by Embraer. Refer to cover page for details.

Page 4

Spoiler System

REVISION 20

AOM-1502-003

NOTE: In the direct mode, speed brakes are not available.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT CONTROLS

EICAS MESSAGES TYPE

WARNING

AOM-1502-003

CAUTION

MESSAGE ELEV (RUDDER) (SPOILER) NML MODE FAIL

MEANING Normal mode of the associated system is no longer operative. One of the ground spoiler surfaces has GROUND SPOILERS extended FAIL inadvertently or has failed to extend when commanded. Stall protection AOA LIMIT FAIL function has failed. One or more sensors required to perform Elevator Thrust ELEV THR COMP Compensation FAIL function have failed and the function is no longer available. Left and right elevator control system has ELEVATOR FAULT reverted to direct mode. Left (right) elevator ELEVATOR LH (RH) control system is no FAIL longer available. Both flaps electronic control channels are inoperative and the flaps system is no FLAP FAIL longer available or there is a jam in the mechanical portion that precludes the flaps from moving.

14-08-45 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

EICAS Messages

Page 1

FLIGHT CONTROLS

TYPE

AIRPLANE OPERATIONS MANUAL

MESSAGE

FLT CTRL BIT EXPIRED

FLT CTRL NO DISPATCH

PITCH TRIM FAIL CAUTION RUDDER FAIL

RUDDER FAULT

RUDDER LIMITER FAIL

SLAT FAIL

MEANING (Pre-Mod. Load 21.2) 20 hours or more has passed since the last time PBIT was activated. (Post-Mod. Load 21.2) 50 hours or more has passed since the last time PBIT was activated. One of the components associated with the flight control system has failed to a No-Go condition. Pitch trim function is no longer available. Active and standby rudder channels have failed or rudder has jammed. Indicates that the rudder control system has reverted to direct mode. Indicates that rudder ground authority is retained after take-off. Both slats electronic control channels are inoperative and the slats system is no longer available or there is a jam in the mechanical portion that precludes the slats from moving.

14-08-45 Copyright © by Embraer. Refer to cover page for details.

Page 2

EICAS Messages

REVISION 21

AOM-1502-003

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

TYPE

CAUTION

AOM-1502-003

ADVISORY

SYSTEMS DESCRIPTION FLIGHT CONTROLS

MESSAGE

MEANING Difference between SLAT-FLAP LEVER commanded position DISAG and surface position. Airspeed gain scheduling has failed in one or more pairs of multifunction SPOILER FAULT spoilers, and the system(s) has defaulted to a fixed gain. The mechanical device, which locks the horizontal STAB LOCK FAULT stabilizer, has failed. Direct mode is not allowed. Steep approach Mode STEEP APPR FAIL is failed. Indicates that the left (right) aileron is no longer available or AILERON LH (RH) there is a mechanical FAIL disconnection in the left (right) aileron surface. Pitch Trim Auto AUTO CONFIG TRIM Configuration function FAIL is inoperative. One of the flaps electronic control channels is FLAP LO RATE inoperative and the flap system is still available but running at low speed.

14-08-45 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

EICAS Messages

Page 3

FLIGHT CONTROLS

TYPE

AIRPLANE OPERATIONS MANUAL

MESSAGE

FLT CTRL FAULT

ADVISORY

PITCH CONTROL DISC PITCH TRIM BKUP FL (Pre-Mod Load 25.1.0.1) PITCH TRIM BKUP FAIL (Post-Mod Load 25.1.0.1) PITCH TRIM SW 1 FAIL PITCH TRIM SW 2 FAIL PITCH TRIM LO RATE ROLL CONTROL DISC

MEANING One of the components associated with the flight control system has failed. Control columns are disconnected.

Backup pitch trim switch is inoperative.

Captain’s pitch trim switch is inoperative. First Officer’s pitch trim switch is inoperative. Pitch trim system can only operate at a low rate. Control wheels are disconnected.

14-08-45 Copyright © by Embraer. Refer to cover page for details.

Page 4

EICAS Messages

REVISION 21

AOM-1502-003

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

TYPE

ADVISORY

AOM-1502-003

STATUS

SYSTEMS DESCRIPTION FLIGHT CONTROLS

MESSAGE

MEANING One of the Slats electronic control channels is SLAT LO RATE inoperative and the slat system is still available but in low speed. SPDBRK FAIL SPEED BRAKE (Post-Mod Load 27.1) function has failed. A mismatch exists between the SPDBRK LEVER speedbrake handle DISAG position and the multifunction spoiler surfaces. STEEP APPR NOT Steep Approach AVAIL Mode is not available. Electrical and FLT CTRL TEST IN hydraulic PBIT in PROG progress.

14-08-45 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

EICAS Messages

Page 5

SYSTEMS DESCRIPTION FLIGHT CONTROLS

AIRPLANE OPERATIONS MANUAL

14-08-45 Copyright © by Embraer. Refer to cover page for details.

Page 6

EICAS Messages

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

SECTION 14-09 FLIGHT INSTRUMENTS/COMM/NAV/FMS TABLE OF CONTENTS Block

Page

General Description............................................. 14-09-01 .... GENERAL DESCRIPTION..................................... 14-09-01 ....

1 1

AOM-1502-003

Controls and Indications..................................... 14-09-05 .... 1 FLIGHT INSTRUMENTS....................................... 14-09-05 .... 1 COMMUNICATION................................................ 14-09-05 .... 60 Flight Instruments................................................ 14-09-10 .... AIR DATA SYSTEM............................................... 14-09-10 .... RADAR ALTIMETER SYSTEM.............................. 14-09-10 .... INTEGRATED ELECTRONIC STANDBY SYSTEM.......................................................... 14-09-10 .... CLOCK................................................................... 14-09-10 .... STANDBY MAGNETIC COMPASS........................ 14-09-10 ....

1 1 5

Communication.................................................... 14-09-15 .... GENERAL.............................................................. 14-09-15 .... RADIO COMMUNICATION SYSTEM.................... 14-09-15 .... INTERPHONE SYSTEM........................................ 14-09-15 .... AUDIO CONTROL PANEL..................................... 14-09-15 .... DIGITAL VOICE DATA RECORDER (DVDR) SYSTEM.......................................................... 14-09-15 .... COMMUNICATION MANAGEMENT FUNCTION (CMF)............................................................... 14-09-15 ....

1 1 2 13 16

7 8 9

16 17

Navigation............................................................. 14-09-20 .... 1 INERTIAL REFERENCE SYSTEM (IRS).............. 14-09-20 .... 1 GLOBAL POSITIONING SYSTEM (GPS)............. 14-09-20 .... 4 RADIO NAVIGATION SYSTEM............................. 14-09-20 .... 12 MISSED APPROACH PREVIEW........................... 14-09-20 .... 25 WEATHER RADAR SYSTEM................................ 14-09-20 .... 26

14-09-TOC Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Table of Contents

Page 1

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

Block Page Flight Management System................................ 14-09-25 .... 1 FLIGHT MANAGEMENT SYSTEM........................ 14-09-25 .... 1 FLIGHT PLANNING............................................... 14-09-25 .... 1 VERTICAL FLIGHT PLAN..................................... 14-09-25 .... 2 FMS SPEED PLAN................................................ 14-09-25 .... 5 DATA BASE............................................................ 14-09-25 .... 7 FUNCTIONS.......................................................... 14-09-25 .... 9 FMS ANNUNCIATORS.......................................... 14-09-25 .... 10 PREFLIGHT........................................................... 14-09-25 .... 13 PROGRESS........................................................... 14-09-25 .... 79 DIRECT-TO............................................................ 14-09-25 .... 87 PATTERNS............................................................. 14-09-25 .... 91 CROSSING POINTS.............................................. 14-09-25 .... 103 ARRIVAL................................................................ 14-09-25 .... 119 LANDING............................................................... 14-09-25 .... 123 1 1

14-09-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 21

AOM-1502-003

EICAS Messages.................................................. 14-09-35 .... EICAS MESSAGES............................................... 14-09-35 ....

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

GENERAL DESCRIPTION The airplane is equipped with a complete set of Communication and Navigation functions. The main interface for the system is done through the Audio Control Panel (ACP) and the Multi-function Control Display Unit (MCDU). The MCDUs provide radio frequency and mode control. The frequencies can also be selected on the Primary Flight Displays (PFDs) through the Cursor Control Devices (CCDs). The system provides a backup tuning page that may be used when a failure is detected. This backup page is displayed on MCDU 2 and enables tuning for COM 1, NAV 1 and Transponder (XPDR) 1. The audio system is controlled via three individual ACPs that are available to the captain, first officer and observer, and also provides interface with the Passenger Address (PA), Aural Warning, and Digital Voice and Data Recorder (DVDR) systems. Optional communications equipment includes a third VHF COM, HF and Selcal systems.

AOM-1502-003

Navigation may be performed using only the navigation radio sensors or Flight Management System (FMS) resources. The FMS uses the standard navigation radio sensors, Global Positioning System (GPS) and Inertial Reference System (IRS) for positioning and navigation.

14-09-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 10

General Description

Page 1

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-01 Copyright © by Embraer. Refer to cover page for details.

Page 2

General Description

REVISION 10

AOM-1502-003

INTENTIONALLY BLANK

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

FLIGHT INSTRUMENTS AIRSPEED TAPE INDICATIONS

PFD

1

14O 2

16O 17

3

14O 13O 16

1 25

FS F 2

6 7

9

12O

11O

11O

R AP RF

1OO

1

15

9O

19O M

9O 14 13

5

AC

12O

1OO

4

19O M

GSPD 13O KT

4O

8

10

1OO 12O 13O 14O

11 12

1 R 2 FS

18

EM170AOM140266A.DGN

15O

1 - SELECTED AIRSPEED/MACH READOUT – Displays speed/mach values.

AOM-1502-003

MAGENTA: automatically set by the FMS. CYAN: manually entered by the flight crew.

14-09-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 1

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

AMBER DASHED: invalid information. 2 - SELECTED AIRSPEED BUG – Displayed when the FMS/AFCS commanded speed is in the displayed range of speed tape. MAGENTA: automatically set by the FMS. CYAN: manually entered by flight crew. 3 - VFS SPEED (FS) – Takeoff final segment speed. 4 - FLAP RETRACTION SPEED REFERENCE (F) – Flap retraction speed reference for both dual engine and single engine takeoffs. 5 - V2 SPEED (2) – Takeoff V2 speed. 6 - AIRSPEED TREND VECTOR – Shows the airspeed which the airplane will be within 10 s, if the present acceleration/deceleration rate is maintained. 7 - VAC SPEED (AC) – Approach Climb Speed. 8 - VR SPEED (R) – Indicates rotation speed. 9 - VAP SPEED (AP) – Indicates approach speed.

– Indicates reference speed.

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Page 2

Controls and Indications

REVISION 21

AOM-1502-003

10 - VREF SPEED (RF)

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

11 - GREEN DOT !MAU load 21.2 and on OR POST-MOD SB 170-31-0028

– Indicates the driftdown speed when Slat/Flap is UP and the ideal Slat/Flap extension speed for the current airplane weight. It provides a minimum margin of 1.3 g over stick shaker speed, or 40° of bank angle, for wings leveled condition during any flight phase and Slat/Flap setting. Altitude, Speed in Mach, Slat/Flap position and Weight from the FMS (resolution in increments of 500 kg/1100 lb) are used to compute the Green Dot. The Green Dot is calculated in Mach and then converted into IAS to be displayed on the PFD. In case of loss of IAS, loss of Slat/Flap position or position disagreement, the Green Dot is removed from the PFD. " !MAU Load 21.2 up to Load 25.4 - Pentium M or Load 25.3 - Pentium II

NOTE: – The green dot does not account for ice accretion. Therefore, when flying in icing conditions, if the EICAS message STALL PROT ICE SPEED is displayed, it is recommended to add 10 kt to the green dot. – In case the EICAS message STALL PROT FAIL is displayed, the green dot is removed from the PFD. – The green dot is temporarily removed from the PFD during SLAT/FLAP transition. – The green dot logic does not account for speed brakes actuation. " !MAU Load 25.5.0.1 and on

NOTE: – The green dot accounts for ice accretion. – In case the EICAS message STALL PROT FAIL is displayed, the green dot is removed from the PFD. – The green dot logic does not account for speed brakes actuation.

AOM-1502-003

"

14-09-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 3

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

!MAU LOAD 25.5.0.1 OR MAU LOAD 25.6

NOTE: If STALL PROT ICE SPEED is displayed, do not use the green dot speed reference for driftdown. In this case use the driftdown tables with ice accretion presented in QRH and AOM. "

12 - V1 SPEED (1) – Decision Speed. 13 - GROUND SPEED – Displays IRS-based ground speed. 14 - MACH AIRSPEED READOUT – Displays the actual airplane Mach number. Mach shall be displayed when aircraft speed is 0.450 M or greater and remains displayed until the aircraft airspeed falls below 0.400 M. GREEN: normal range. AMBER: airspeed is reaching an overspeed or it is at or below shaker speed and above stall speed. RED INVERSE VIDEO: airspeed at or above overspeed or, at or below stall speed. AMBER DASHED: invalid information. NOTE: When selected airspeed information is invalid, the digital display and label are removed. 15 - LOW SPEED AWARENESS TAPE (LSA) – Indicates the margin to the stick shaker speed. It rises from the bottom of the speed tape and has two colored ranges: AMBER: from K VS1G down to Vshaker. K ranges from 1.054 to 1.13 depending on speed and airplane type. The lower the speed, the higher the K factor.

14-09-05 Copyright © by Embraer. Refer to cover page for details.

Page 4

Controls and Indications

REVISION 21

AOM-1502-003

RED: at or below Vshaker.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– The LSA is a function of Airspeed in Mach, Slat/Flap position, Angle of Attack, Spoiler position, Landing Gear position and Icing conditions (EICAS message STALL PROT ICE SPEED displayed). – When EICAS messages SHAKER ANTICIPATED or STALL PROT ICE SPEED are displayed, the top of LSA tape is repositioned upwards to match the new Vshaker. – When the airspeed indication or Angle of Attack data is invalid, the LSA tape is removed. 16 - AIRSPEED ROLLING DIGITS – Displays the indicated airspeed (IAS), above 30 kt. GREEN: normal range. AMBER: airspeed trend vector (when displayed) is reaching the VMO/Mmo or it is at amber low speed awareness tape or the actual airspeed is at amber low speed awareness tape. RED INVERSE VIDEO: airspeed trend vector (when displayed) or actual airspeed is at red low speed awareness tape or at VMO/Mmo barber pole. – The airspeed trend vector when displayed has the priority over actual airspeed to define the airspeed rolling digits color. 17 - VMO/Mmo BARBER POLE – Displayed when the VMO/Mmo is within the viewable range, and covers speeds at or above VMO/Mmo (red and white). 18 - SPEED DIGITAL READOUT

AOM-1502-003

– Preview readout for takeoff bugs.

14-09-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 5

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

VERTICAL SPEED INDICATIONS PFD

35OO 35OO

1

2OOO 4

2 3 4

2 1

3OOO

5

1OOO

6

25OO

EM170AOM140382.DGN

1 2 4

29.92 IN

1 - SELECTED VERTICAL SPEED DIRECTION ARROW – Indicates either up or down direction. Used in conjunction with the selected vertical speed readout. 2 - SELECTED VERTICAL SPEED READOUT – Displays selected climb or descent rate. 3 - VERTICAL SPEED SCALE – Extends from -4000 ft/min to 4000 ft/min, with an expanded scale between 1000 ft/min and -1000 ft/min. – From 0 ft/min to ±500 ft/min: One tick mark at every 100 ft/min.

4 - SELECTED VERTICAL SPEED BUG

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Page 6

Controls and Indications

REVISION 21

AOM-1502-003

– From ±1000 ft/min to ±4000 ft/min: One tick mark at every 1000 ft/min.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– Displays selected climb or descent rate on the vertical speed scale. 5 - VERTICAL SPEED POINTER – Displays the actual vertical speed if within the viewable range; parks at the limit if beyond viewable range. – If the current rate is greater than ±9999 ft/min, or the altitude data received is not valid, the vertical speed pointer is removed. 6 - VERTICAL SPEED READOUT – Displayed when the vertical speed increases above 550 ft/min or decreases below -550 ft/min. – Removed when the vertical speed decreases below 500 ft/min or increases above -500 ft/min. GREEN: normal range.

AOM-1502-003

AMBER DASHES: invalid information.

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REVISION 21

Controls and Indications

Page 7

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

ALTITUDE TAPE INDICATIONS PFD

8

1O67 M

7

35OO

6

35OO

2OOO 1

4 2 1

2

914 M

5

3OOO

1OOO

3

25OO 4

EM170AOM140381.DGN

1 2 4

29.92 IN

1 - ALTITUDE TAPE – Indicates actual airplane altitude. The altitude tape is labeled with tick marks every 100 ft and single or double-lined chevrons at 500 ft or 1000 ft intervals, respectively. 2 - METRIC ALTITUDE READOUT – Indicates actual airplane altitude in meters, with a resolution of 5 m. – Displayed when selected in the altitude selector knob. – A green hashed box appears on the left side of the numeric digits when altitude is below 10000 m. – A minus (-) symbol appears on the left side of the numeric digits when altitude is below sea level.

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Page 8

Controls and Indications

REVISION 21

AOM-1502-003

3 - ALTITUDE ROLLING DIGITS READOUT

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– Indicates actual airplane altitude in feet. Digits are displayed with a resolution of 20 ft. – A green hashed box appears on the left side of the numeric digits when altitude is below 10000 ft. – A minus (-) symbol appears on the left side of the numeric digits when altitude is below sea level. 4 - BAROMETRIC CORRECTION – Displays the barometric correction as selected. 5 - ALTITUDE TREND VECTOR – Indicates the projected altitude, which the airplane will be within 6 seconds, based on the current vertical speed. – This vector is displayed along the left edge of the altitude tape as a wide white line. 6 - SELECTED ALTITUDE BUG – Positioned at the selected altitude. CYAN: manually entered by the flight crew. AMBER: actual airplane altitude is between 1000 and 200 ft from the preselected altitude. An audio alert is sounded after the airplane has captured the altitude and departs more than 200 ft from the selected altitude. 7 - SELECTED ALTITUDE READOUT – Displays digital selected altitude in feet. CYAN: manually entered by the flight crew.

AOM-1502-003

AMBER: actual airplane altitude is between 1000 and 200 ft from the preselected altitude. An audio alert is sounded after the airplane has captured the altitude and departs more than 200 ft from the selected altitude.

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REVISION 21

Controls and Indications

Page 9

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

8 - METRIC SELECTED ALTITUDE READOUT – Displays digital selected altitude in meters.

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Page 10

Controls and Indications

REVISION 21

AOM-1502-003

– Displayed when selected in the altitude selector knob.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

ADI INDICATIONS PFD

5

6

4

7

8

2O

2O

1O

1O

9

10 FMS VERTICAL DEVIATION, NO PREVIEW

12

3 -3.O

11

11

2 1O

2O

2O

ILS VERTICAL DEVIATION, NO PREVIEW

ILS LATERAL DEVIATION, NO PREVIEW

15

FMS LATERAL DEVIATION, NO PREVIEW

13

14

FMS AND PREVIEW MODE ACTIVE

13

EXPANDED/EXCESSIVE LATERAL DEVIATION

AOM-1502-003

FMS AND PREVIEW MODE ACTIVE

EM170AOM140468A.DGN

1

1O

14-09-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 11

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

PFD

2O

2O

1O

1O 16

1O

1O

2O

2O

5O

4O

4O

3O

3O

2O

2O

1O

1O

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Page 12

Controls and Indications

REVISION 21

AOM-1502-003

5O

EM170AOM140469C.DGN

17

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

1 - FLIGHT PATH REFERENCE LINE/READOUT (FPR) – Indicates a selected path angle for reference, when the FPR button is pressed. 2 - AIRPLANE SYMBOL – Fixed and used with the pitch tape to reflect airplane pitch attitude in relation to the horizon line. 3 - FLIGHT PATH VECTOR SPEED ERROR TAPE – Indicates the difference between actual and the selected airspeed. – Down/Up Tape indicates current airspeed is less/greater than the selected airspeed. 4 - FPA ACCELERATION POINTER – Provides an indication of acceleration and deceleration rates along the flight path. – Moves upward/downward for increasing/decreasing values of flight path acceleration. 5 - PITCH LIMIT INDICATOR (PLI) – Pitch based indication of the margin (in degrees) between stick shaker Angle of Attack and airplane’s Angle of Attack displayed against the airplane pitch attitude, using the Airplane Symbol as zero degrees. GREEN: from 1.2 of VS1G down to K of VS1G. K ranges from 1.054 to 1.13 depending on speed and airplane type. The lower the speed, the higher the K factor. AMBER: from K.VS1G down to Vshaker. K ranges from 1.054 to 1.13 depending on speed and airplane type. The lower the speed, the higher the K factor. RED: at or below Vshaker. AOM-1502-003

– The PLI is removed when the airspeed exceeds 1.2 of VS1G.

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REVISION 21

Controls and Indications

Page 13

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

– The PLI is a function of Airspeed in Mach, Slat/Flap position, Angle of Attack, Spoiler position, Landing Gear position and Icing conditions (EICAS message STALL PROT ICE SPEED displayed). – When EICAS messages SHAKER ANTICIPATED or STALL PROT ICE SPEED are displayed, the PLI is displayed on lower angles due to reduction of the margin between stick shaker Angle of Attack and airplane’s Angle of Attack. – When the airspeed indication, Angle of Attack data is invalid, the PLI is removed. 6 - SLIP/SKID INDICATOR – Indicates slip or skid if flight is not coordinated. 7 - ROLL SCALE/LOW BANK LIMIT ARC – Indicates the current airplane roll attitude. The scale has tick marks at 10, 20, 30 and 60 degrees and inverted triangles at 0 and 45 degrees. !Pre-mod MAU load 27.1

– A low bank limit arc helps the pilot to fly with low bank angles during turns (0° up to 17°). "

8 - ROLL POINTER – Indicates the current airplane roll attitude. 9 - FLIGHT PATH ANGLE (FPA) – Indicates the current flight path in reference to the horizon line (green). 10 - FLIGHT DIRECTOR – Shows lateral and vertical FD guidance cue.

– Pointer: indicates current glide slope position.

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Page 14

Controls and Indications

REVISION 21

AOM-1502-003

11 - ILS GLIDE SLOPE DEVIATION

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

GREEN: when neither FMS nor preview mode is in use. CYAN: when the preview mode is selected. AMBER: when the deviation from the APPR 2 vertical approach path becomes out of range of the normal scale. – Scale: indicates deviation position: WHITE: indicates normal deviation from the vertical path. AMBER FLASHING: when the deviation from the APPR 2 vertical approach path becomes out of range of the normal scale. 12 - FMS VERTICAL DEVIATION – Pointer: indicates current vertical path (magenta). Displayed in trapezoidal form when no ILS is in use. Otherwise it is presented in diamond format. – Scale: indicates deviation (white). 13 - ILS/VOR LATERAL DEVIATION – Pointer: indicates current localizer position. GREEN: when neither FMS nor preview mode is in use. Also displayed in the expanded mode for APPR 2 operations. CYAN: when the preview mode is selected. AMBER: when the deviation from the APPR 2 lateral approach path becomes out of range of the normal scale. – Scale: indicates deviation position. WHITE: indicates normal deviation from the lateral path or expanded scale for APPR 2 operation. AMBER FLASHING: when the deviation from the APPR 2 lateral approach path becomes out of range of the expanded scale.

AOM-1502-003

14 - FMS LATERAL DEVIATION – Pointer: indicates current lateral path (magenta). Displayed in trapezoidal format when no ILS is in use. Otherwise, it is presented in diamond format.

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REVISION 21

Controls and Indications

Page 15

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

– Scale: indicates deviation (white). 15 - PITCH TAPE – Provides a pitch angle indication between the airplane symbol and the horizon line or an angle indication for the flight path angle. 16 - TAKEOFF CROSSBAR – In the takeoff mode, the takeoff crossbar is displayed. The horizontal line moves vertically along the center of the Airplane Symbol to provide vertical guidance. The vertical line moves horizontally along the center of the Airplane Symbol to provide horizontal guidance. 17 - EXCESSIVE PITCH CHEVRON ANNUNCIATION

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Page 16

Controls and Indications

REVISION 21

AOM-1502-003

– Displayed whenever excessive pitch attitude is detected.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

ADI ANNUNCIATIONS PFD

7

FLO9O

ADS1 IRS1

6

2O

2O VTA

1O

1O

1O

1O

2O

2O

8 9

1 EICAS

MIN

5OO BARO 4OO

AOM-1502-003

4

2O

2O

1O

1O

1O

1O

2O

2O

2

3

O M

I

EM170AOM140474E.DGN

5

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REVISION 21

Controls and Indications

Page 17

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

1 - RADAR ALTITUDE INDICATION – Displays actual radar altitude. GREEN: normal operation. AMBER: failure of one of the radar altimeters, in a dual system installation. 2 - MINIMUMS SELECTED READOUT – Displays the selected minimum barometric or radar altitude. WHITE: BARO/RA label. CYAN: radar or barometric altitude readout. 3 - MARKER BEACON ANNUNCIATIONS – Displays I for inner, M for the middle or O for outer marker annunciations. 4 - MINIMUM ANNUNCIATION – Advises that the airplane is near or at the minimum altitude preselected by the pilot. 5 - MONITOR ANNUNCIATIONS – Displayed whenever the EICAS message list from both monitor warnings (MW 1 and MW 2) do not match or an ADI/HSI miscompare is detected. 6 - ATTITUDE SOURCE ANNUNCIATION – Displays IRS1 or IRS2 to indicate that a system other than the on-side system (normal operation) is providing the data, or that both sides are using the same system. 7 - AIR DATA SOURCE ANNUNCIATION

8 - VNAV ALTITUDE CONSTRAINT ANNUNCIATION

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Page 18

Controls and Indications

REVISION 21

AOM-1502-003

– Displays ADS1, ADS2 or ADS3 to indicate that a system other than the on-side system (normal operation) is providing the data, or that both sides are using the same system.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– Annunciates a VNAV waypoint constraint. – Altitude constraints are displayed as follows: – At constraint: a bar is displayed above and below the altitude. – At or above constraint: a bar is displayed below the constraint value. – At or below constraint: a bar is displayed above the constraint value. – Constraint window: a bar is displayed above upper altitude and a bar is displayed below lower altitude. 9 - VERTICAL TRACK ALERT ANNUNCIATION

AOM-1502-003

– Annunciates the transition from climbing or descending to level flight and from level flight to climbing or descending during VNAV operations.

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REVISION 21

Controls and Indications

Page 19

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

HSI INDICATIONS PFD

3

4

6

5

4

7

8

9

10

11

2

15O

21O

21O

LOC1

S

21

CHR

O8:12

1O

24

12

W

15

1

CRS

HDG

GSPD 3OO KT

E

6

VHF1 118 5O 119 25

3

14

13

N

VOR1 VOR2

33

15

3O

12

16

NAV1 119 1O 119 15

14

FULL COMPASS MODE

18

HDG

MAG1

33O

27

FMS1 LOC1

26

KPHX

DTK

6

E 12

55.6 NM

CHR O7:12

21 DME1

H

LRX

65.3 NM 2O MIN

22

RNP 1.1O

3

23 MIN

CRS

O7O O9O 1O 5

O8O

VOR1 VOR2

MSG DR APPR

VHF1 118 5O 119 25

NAV1 119 1O 119 15

25

ARC MODE

23 24

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Page 20

Controls and Indications

REVISION 21

AOM-1502-003

GSPD

3OO KT

20

19

EM170AOM140380E.DGN

17

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

PFD

GSPD

HDG

3OO KT

33O

MAG1

36 O 1O

PUMPS

N

FMS1

33

GUP44

CHR O7:12

3

ZUN

55.6 NM

23 MIN

RNP 1.1O

GUP

VHF1 118 5O 119 25

NAV1 119 1O 119 15

O.4 R

31

30

28

EM170AOM140512D.DGN

ZUN 1OO

29

1 - PRIMARY NAVIGATION SOURCE ANNUNCIATION – Displays the selected navigation source. GREEN: onside V/L navigation source is selected. AMBER: cross-side navigation or cross-side FMS navigation source is selected. MAGENTA: FMS navigation source is selected. 2 - GROUND SPEED READOUT – Displays Ground speed based on IRS information. 3 - SELECTED HEADING READOUT – Displays the selected airplane heading.

AOM-1502-003

CYAN: valid information. AMBER DASHES: invalid information.

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REVISION 21

Controls and Indications

Page 21

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

4 - BEARING POINTERS – Displays up to two bearing pointers. CYAN: indicates bearing for ADF1, VOR1 or FMS1 (circle head). WHITE: indicates bearing for ADF2, VOR2 or FMS2 (diamond head). 5 - COURSE SELECT POINTER – Displays the selected course anytime the primary navigation source is a VOR or localizer, controlled by the CRS knob on the guidance panel. GREEN: onside navigation source is selected. AMBER: cross-side navigation source is selected. CYAN: preview course pointer. MAGENTA: FMS navigation source is selected. 6 - HEADING READOUT – Displays the actual airplane heading. GREEN: valid information. AMBER DASHES: invalid information. – When an invalid information occurs a label HDG FAIL is also displayed. 7 - LATERAL DEVIATION INDICATOR – Displays the deviation from the intended course. Indicates whether the airplane is flying left or right of the selected navigation reference. – Incorporates the to/from pointer that indicates if the airplane is flying to or away from the selected navigation reference. GREEN: onside navigation source is selected. AMBER: cross-side navigation source is selected.

8 - DRIFT ANGLE BUG

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Page 22

Controls and Indications

REVISION 21

AOM-1502-003

MAGENTA: FMS navigation source is selected.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– Displays the actual airplane ground track. Its offset relative to the top mark is the drift angle, that is, difference between ground track and heading. 9 - WIND DISPLAY – Indicates wind magnitude and direction. – Direction can be displayed as a single arrow (default) or as parallel and perpendicular arrows. 10 - COURSE SELECT/DESIRED TRACK POINTER – Displays the selected course, controlled by the CRS knob on the guidance panel or the selected track according to data from the FMS. – The word CRS is displayed anytime the primary navigation source is a VOR or localizer. GREEN: onside V/L navigation source is selected. MAGENTA: onside FMS navigation source is selected. AMBER: cross-side navigation source is selected. CYAN: preview course. AMBER DASHES: invalid information. 11 - CHRONOMETER READOUT – Displays chronometer. – Information removed after 30 seconds of inactivity (chronometer in stop or reset). 12 - NEXT TARGET COURSE !Pre-mod MAU load 27.1

– Unavailable "

AOM-1502-003

13 - LATERAL DEVIATION DOTS 14 - SECONDARY RADIO TUNING

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REVISION 21

Controls and Indications

Page 23

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

– Always displayed in left and right boxes and shows VHF NAV/COMM frequencies, when radio data is valid. – The multifunction control display unit (MCDU) is the primary means for radio tuning, while the control cursor device (CCD) and display unit (DU) are the secondary means of radio tuning. GREEN: active frequency. WHITE: standby frequency. AMBER DASHES: radio data invalid. 15 - BEARING SOURCE ANNUNCIATIONS – Display the bearing pointer sources. CYAN (circle): displays the related VOR1, ADF1 or FMS1 source selected. WHITE (diamond): displays the related VOR2, ADF2 or FMS2 source selected. 16 - SELECTED HEADING BUG – Displays the airplane selected heading on both the full compass and arc modes controlled by the heading selector knob on the guidance panel. 17 - PREVIEW NAVIGATION SOURCE ANNUNCIATION – Displays the preview VOR or localizer navigation. 18 - HEADING SOURCE ANNUNCIATION – Indicates a non-normal source condition (e.g., Captain side is using IRS 2), a same source condition (e.g., both Captain and First Officer using IRS 1) or the selection of True heading reference. 19 - COURSE SELECT PREVIEW POINTER

20 - DESIRED TRACK READOUT

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Page 24

Controls and Indications

REVISION 21

AOM-1502-003

– Displays the selected course preview (VOR or LOC) anytime the primary navigation source is a FMS, controlled by the CRS knob on the guidance panel.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– Displays the selected track according to data from the FMS. MAGENTA: onside navigation source is selected. AMBER: cross-side navigation source is selected. AMBER DASHES: invalid information. 21 - DISTANCE DATA BLOCK INDICATIONS – Display DME source, identifier, distance and time to the selected station. – H label is displayed whenever the DME is in hold. 22 - RNP DATA BLOCK INDICATIONS – Displayed when the FMS required navigation precision is the primary navigation source. 23 - MCDU ANNUNCIATIONS – MSG label is displayed whenever a caution message appears in the MCDU. – DR label is displayed whenever the FMS is operating in dead reckoning mode. – DGRAD label is displayed whenever the FMS is operating in degrade mode. 24 - FMS MODE ANNUNCIATOR – APPR label indicates Approach Sensitivity mode. – TERM label indicates Terminal Approach mode. – WPT label indicates Waypoint Alert. – OFFSET indicates Lateral Offset. 25 - COURSE SELECT/DESIRED TRACK POINTER

AOM-1502-003

– Displays the selected course controlled by the CRS knob on the guidance panel or the selected track according to data from the FMS.

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REVISION 21

Controls and Indications

Page 25

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

– The word CRS is displayed anytime the primary navigation source is a VOR or localizer. – GREEN: onside V/L navigation source is selected. – MAGENTA: onside FMS navigation source is selected. – AMBER: cross-side navigation source is selected. – CYAN: preview course. – AMBER DASHES: invalid information. 26 - WAYPOINT DATA BLOCK INDICATIONS – Display the identifier, distance and time to the next waypoint. 27 - SELECTED HEADING OUT OF VIEW ARROW – Displayed on arc mode when the selected heading is not within the viewable range, and shows which way is shortest to the selected heading. 28 - FMS LATERAL DEVIATION INDICATION – Indicates airplane’s lateral deviation from the desired track. – R/L label indicates right/left deviation. 29 - WAYPOINT DISPLAY – Indicates waypoint symbol. – If selected, also indicates waypoint identifier. MAGENTA: next waypoint. WHITE: other waypoints. Up to five waypoints shall be displayed on the HSI Display subject to the range considerations. 30 - HORIZONTAL TRACK LINE – Connects waypoints.

WHITE: connects other waypoints.

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Page 26

Controls and Indications

REVISION 21

AOM-1502-003

MAGENTA: connects with next waypoint.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

31 - RANGE SELECTION – Displayed only in MAP mode, provides the selected half-ring range. – Once selected by the CCD touchpad the knob icon is displayed, indicating that the range is set and changeable by turning the CCD knob. – The possible range values are from 2.5 up to 1000 NM.

AOM-1502-003

NOTE: It is not possible to change the range when the weather overlay is active.

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REVISION 21

Controls and Indications

Page 27

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

HSI WEATHER RADAR INDICATIONS PFD

2

DTK

HDG

33O

36 O

FMS1 KPHX 55 .6 NM 23 MIN

33

N

CHR O8: 12

O2O

5

WX

1 VHF1 118 5O 119 25

.

1OO

O.2R

-9 A WX/R/T S STAB TGT

4

3

NAV1 119 1O 119 15

EM170AOM140291A.DGN

GSPD

3OO KT

1 - WEATHER RADAR RETURNS – Displays target in colors. – WX mode: the color indicates rain intensity in order of increasing ‘intensity: green, yellow, red and magenta. – RCT mode: attenuation is too high, hiding possible severe weather areas (cyan). – GMAP mode: color indicates surface information: black, cyan, yellow and magenta. – TURB mode: areas of potentially hazardous turbulence (white). 2 - ANTENNA POSITION INDICATOR – Indicates that antenna scan is active.

– First line:

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Page 28

Controls and Indications

REVISION 21

AOM-1502-003

3 - WEATHER RADAR ANNUNCIATIONS

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– CCD inner knob icon: tilt angle is modifiable. – Tilt angle readout: displays the tilt angle. – ACT annunciation: ACT is an active submode. – Fault code data (entire line): fault has been detected. – Second line: – Weather radar mode annunciation: GREEN (WX): normal WX. GREEN (WX/R): normal WX with RCT. GREEN (WX/T): normal WX with TURB. GREEN (WX/R/T): normal WX with RCT and TURB. GREEN (WX/TX): Weather transmitting, but not selected for display on the PFD or MFD, when the airplane is in air. GREEN (GMAP): GMAP mode. GREEN (FSBY): forced standby. GREEN (TEST): test mode and no faults. AMBER (WX/TX): Weather transmitting, but not selected for display on the PFD or MFD, when the airplane is on ground. AMBER (WX CTRL): invalid WX control bus. AMBER (FAIL): failure is detected. AMBER (OVRNG): MAP range greater than 300 NM. WHITE (WX OFF): WX is OFF. WHITE (WAIT): power up. WHITE (STBY): normal standby. WHITE (S): slave mode is active. – Third line: – Stabilization annunciation: radar stabilization is inhibited. – Target and gain mode annunciation. GREEN (TGT): TGT selected.

AOM-1502-003

FLASHING AMBER (TGT): TGT selected and alert condition. AMBER (VAR): variable gain selected.

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REVISION 21

Controls and Indications

Page 29

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

4 - WEATHER RADAR VIDEO ANNUNCIATION

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Page 30

Controls and Indications

REVISION 21

AOM-1502-003

– Indicates weather radar video failure.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

ADI/HSI MISCOMPARES PFD

3

AP AT

OVRD

125

SPD E

C A16O S

15O

2

PIT

14O

LOC

GS

VOR

ASEL

2O

2O

1O

1O

4

35 OO

2 1

FPA

125 1 9

5

35OO -3.O

11O 1OO CAS MSG

9O

19O

1OOO

A 4OOO L 4 T

1O

1O

2O

2O

RA

1 2

GS

3OOO 4 29.92 IN

M

GSPD 3OO KT

6

CRS

HDG

33O

21O

ILS1

HDG

CHR

O8:12 7

1O

21

15

S

21O

NAV1 119 1O 119 15

EM170AOM140272A.DGN

E

12 AOM-1502-003

6

VHF1 118 5O 119 25

3

VOR1 VOR2

8

LOC

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REVISION 21

Controls and Indications

Page 31

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

1 - RADIO ALTITUDE MISCOMPARE ANNUNCIATION – Displayed whenever the radio altimeter has failed or the difference between the Captain and First Officer’s radio altitude is greater than a set point. 2 - PITCH, ROLL AND ATTITUDE MISCOMPARE ANNUNCIATION – Displayed whenever a pitch, roll or attitude miscompare is detected. – The miscompare annunciators and triggering limits are: – PIT: Pitch > 5° – ROL: Rol > 6° – ATT: ATT - Both Monitors Tripped 3 - AIRSPEED MISCOMPARE ANNUNCIATION – Displayed whenever airspeed miscompare is detected. – The miscompare annunciator and triggering limit are: – IAS: > 5 KIAS NOTE: The IAS monitor is inhibited if both airspeed indicators show below 100 KIAS. 4 - ALTITUDE MISCOMPARE ANNUNCIATION – Displayed whenever altitude miscompare is detected. – The miscompare annunciator and triggering limit are: – ALT: > 200 ft 5 - FLIGHT PATH ANGLE MISCOMPARE ANNUNCIATION – Displayed whenever miscompare is detected for FPA. – The miscompare annunciator and triggering limit are: – FPA: > 2° SYSTEM

MISCOMPARE

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Page 32

Controls and Indications

REVISION 21

AOM-1502-003

6 - VERTICAL ORIENTATION ANNUNCIATION

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– GS flag displays whenever glideslope/glidepath miscompare is detected. – The miscompare annunciator and triggering limit are: – GS: > 2/3 dot 7 - HEADING MISCOMPARE ANNUNCIATION – Displayed whenever a heading miscompare is detected. – The miscompare annunciator and triggering limit are: – HDG: > 6° NOTE: The HDG mode is inhibited if one of the HDG indicators is set to a different mode. 8 - LATERAL ORIENTATION ANNUNCIATION

SYSTEM

MISCOMPARE

– Displayed whenever localizer miscompare is detected. – The miscompare annunciator and triggering limit are: – LOC: > 1/2 dot NOTE: The LOC monitor is inhibited if both navigation sources are not set to LOC. 9 - EICAS MESSAGE MISCOMPARE ANNUNCIATION – Displayed whenever the EICAS message list from both monitor warnings (MW 1 and MW 2) do not match. – The miscompare annunciators are: – EICAS: A Graphics Data Test Monitor failure is detected and is annunciated on the EICAS.

AOM-1502-003

– CAS MSG: CAS miscompare monitoring is performed continuously on all valid sources of CAS data. If a miscompare is detected it will be annunciated on each available PFD.

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REVISION 21

Controls and Indications

Page 33

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

ADI/HSI FAILS PFD

125

OVRD SPD E

AP AT

LOC

3

VOR

ASEL

GS

4

35 OO

1OOO

ATT FAIL

2

5

6

--GSPD

--- KT

---- IN

CRS

HDG

---

---

---

CHR

--:--

FMS1 HDG FAIL

7

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Page 34

Controls and Indications

REVISION 21

AOM-1502-003

EM170AOM140470A.DGN

1

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

1 - HDG FAIL – An ‘x’ appears whenever HDG indication is lost. It is still possible to revert the HDG source from IRS 1 to IRS 2, in case of a PFD 1 Heading Indication failure, and the opposite in case of HDG 2 failure. 2 - AIRSPEED ANNUNCIATION FAIL – Airspeed Indication disappears and an ‘x’ displays. 3 - ATTITUDE INDICATION FAIL – Attitude indication disappears and a message ATT FAIL displays on PFD. 4 - ALTITUDE INDICATION FAIL – Altitude Indication disappears and the message ALT FAIL displays on PFD. The barometric pressure correction appears dashed. 5 - VERTICAL SPEED INDICATION FAIL – Vertical Indication disappears and an ‘x’ displays. 6 - ILS/FMS VERTICAL DEVIATION INDICATION FAIL – Vertical Deviation indication disappears and an ‘x’ displays. 7 - LATERAL DEVIATION INDICATION FAIL

AOM-1502-003

– Lateral Deviation Indication disappears and an ‘x’ displays.

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REVISION 21

Controls and Indications

Page 35

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

HORIZONTAL PROFILE INDICATIONS MFD

2

3

FMS1

36 O

ZUN 55.6 NM 23 MIN

5

PUMPS

N

33

15 SAT ^C 25 TAT ^C 3OO TAS KTS

DME1 LAX 65.3 NM 2O MIN

3

GUP44

3O

14

13

WEATHER

5 A WX/R/T S STAB TGT LX

9

1OO

1OO O.O5 L

PROGRESS

NEXT DEST

WPT ZUN GUP

DIST ETE FUEL 55.6 O1+32 11.4 95 O2+52 1O.4

11

E

W

ZUN

12

7

8

6

GUP

6

10 EM170AOM140270A.DGN

1

5

4

1 - WAYPOINT DATA BLOCK INDICATIONS – Display the identifier, distance and time to the next waypoint. 2 - FMS SOURCE INDICATION – Displays the selected FMS source. MAGENTA: onside FMS is selected. AMBER: cross-side FMS is selected. 3 - HEADING READOUT – Displays airplane’s actual heading. GREEN: valid information. AMBER DASHES: invalid information.

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Page 36

Controls and Indications

REVISION 21

AOM-1502-003

4 - DRIFT ANGLE BUG

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– Displays airplane’s actual ground track. Its offset relative to the top mark is the drift angle, that is, difference between ground track and heading. 5 - WIND DISPLAY – Indicates wind magnitude and direction of the wind. – Direction can be displayed as a single arrow (default) or as parallel and perpendicular arrows. 6 - AIR DATA SYSTEM INDICATIONS – Information not available when: – Temperature indication of either TAT 1 or TAT 2 is above 60°C, or; – Airplane is on ground and any engine is running. – Indicates static air temperature (SAT), total air temperature (TAT) and true air speed (TAS), sourced by the selected Air Data System. GREEN: all operating ranges. AMBER DASHED: invalid information or ADS failure, TAT and SAT may be different. 7 - DME DATA BLOCK INDICATIONS – Display DME source, identifier, distance and time to the selected station. – H label is displayed whenever the DME is in hold. 8 - HORIZONTAL TRACK LINE – Connects waypoints. MAGENTA: connects with next waypoint. WHITE: connects other waypoints.

AOM-1502-003

9 - RANGE SELECTION

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REVISION 21

Controls and Indications

Page 37

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

– Displayed when MAP mode is selected, as an outer compass ring and an inner half-range ring. The half-range ring is labeled with the half-range distance. – The Plan format displays only a half-range ring, which is labeled with the range distance. – Both range labels are shown with the knob icon, indicating that the range is set and changed by turning the CCD knob. – The possible values for range are 2.5 NM to 1000 NM. NOTE: It is not possible to change the range when the on-side weather virtual controller is selected to OFF and the slave mode is active. 10 - FMS LATERAL DEVIATION INDICATION – Indicates airplane’s lateral deviation from the desired track. – R/L label indicates right/left deviation. 11 - FMS PROGRESS WINDOW – Data contained in the box is arranged in two rows. The upper row lists data for the next waypoint (NEXT) and the lower row lists data for the destination (DEST). The following information is displayed: waypoint name, distance to go, estimated time enroute and fuel remaining at the waypoint. 12 - SELECTED HEADING OUT OF VIEW ARROW – Displayed when the selected heading is not within the viewable range, and shows which way is shortest to the selected heading. 13 - SELECTED HEADING BUG

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Page 38

Controls and Indications

REVISION 21

AOM-1502-003

– Displays the airplane selected heading controlled by the heading select knob on the guidance panel.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

14 - WAYPOINT DISPLAY – Indicates waypoint symbol. – If selected, also indicates waypoint identifier. MAGENTA: next waypoint.

AOM-1502-003

WHITE: other waypoints.

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REVISION 21

Controls and Indications

Page 39

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

VERTICAL PROFILE INDICATIONS MFD

1

360 00

5

4

FMS1 [ 5O ]

XTRACK

1OO

6

340 00

GUP44

320 00

FL320

300 00

9

8

7

EM170AOM140293B.DGN

380 00

3

2

1 - FMS SOURCE INDICATION – Displays the selected FMS source. MAGENTA: on-side FMS is selected. AMBER: cross-side FMS is selected. 2 - CROSS TRACK ANNUNCIATION – Indicates a significant deviation from the planned horizontal flight path. – The vertical track line from the left of the vertical profile window to the next waypoint changes to a dashed amber line. 3 - AIRPLANE TRAJECTORY LINE

4 - HALF/FULL CURL ICON INDICATION

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Page 40

Controls and Indications

REVISION 21

AOM-1502-003

– Shows the vector trend of the airplane along the vertical axis, based on the current flight path angle.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– Can be changed using the CCD outer knob. 5 - HALF/FULL RANGE INDICATIONS – Show the selected horizontal ranges. 6 - WAYPOINT DISPLAY – Indicates waypoint symbol. – If selected, also indicates waypoint identifier with altitude and, if applicable, a HOLD label that indicates a holding pattern. MAGENTA: next waypoint. WHITE: other waypoints. 7 - VNAV ALTITUDE CONSTRAINT INDICATION – Indicates a VNAV waypoint constraint. – Altitude constraints are displayed as follows: – At an altitude: a bar is displayed above and below the constraint value. – At or above an altitude: a bar is displayed below the constraint value. – At or below an altitude: a bar is displayed above the constraint value. – Altitude window: a bar is displayed above the upper constraint value and a bar is displayed below the lower constraint value. 8 - SELECTED ALTITUDE INDICATION – Indicates the selected altitude in the guidance panel. 9 - VERTICAL TRACK LINE – Connects waypoints. MAGENTA: connects with next waypoint. WHITE: connects other waypoints.

AOM-1502-003

DASHED AMBER: airplane has significantly deviated from the planned horizontal flight path.

14-09-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 41

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

MFD WEATHER RADAR MFD

FMS1

O1O

ZUN 55. 6 NM 23 MIN

5

PUMPS

15 SAT ^C 25 TAT ^C 3OO TAS KTS

N

DME1 LAX 65.3 NM 2O MIN

GUP44

33

1

3O

GUP ZUN

1OO

WEATHER

15

A 5 WX/R/T S STAB TGT LX

O.O5 L

PROGRESS

NEXT DEST

14

WPT ZUN GUP

TCAS

DIST ETE FUEL 55.6 O1+32 11.4 95 O2+52 1O.4

TA ONLY FLT LVL EXPANDED

FSBY OVRD SECT

TGT

LX

GMAP

STAB Off

RCT

CLR TST

11

STBY

VAR Gain

ACT

Off

Gain

TURB

92

10

9

8

7

6

5

4

3

2

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Page 42

Controls and Indications

REVISION 21

AOM-1502-003

WX

12

EM170AOM140131B.DGN

13

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

1 - WEATHER RADAR RETURNS – Displays target in colors. – WX mode: the color indicates rain intensity. In increasing order of intensity: green, yellow, red and magenta. – RCT mode: attenuation is too high, hiding possible severe weather areas (cyan). – GMAP mode: color indicates surface information: black, cyan, yellow and magenta. – TURB mode: areas of potentially hazardous turbulence (white). 2 - TARGET ALERT CHECKBOX – Enables and disables the radar target feature. Can only be selected in the WX mode and at selected ranges of 200 NM or less. 3 - RAIN ECHO ATTENUATION COMPENSATION TECHNIQUE CHECKBOX – Enables REACT function in all modes, except GMAP. 4 - ALTITUDE COMPENSATED TILT CHECKBOX – Enables automatic adjustment of the antenna tilt in relation to the altitude and selected range. 5 - TURBULENCE DETECTION CHECKBOX – Enables the turbulence function only in the WX mode and at selected ranges of 50 NM or less. 6 - GAIN INDICATION DISPLAY – Indicates receiver sensitivity level from 0 to 100. 7 - RECEIVER GAIN CHECKBOX

AOM-1502-003

– Enables manual variation of the receiver sensitivity. 8 - ANTENNA STABILIZATION CHECKBOX

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REVISION 21

Controls and Indications

Page 43

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

– Enables/disables automatic antenna stabilization. – An amber STAB label is displayed within the weather box when automatic antenna stabilization is disabled. 9 - SECTOR SCAN CHECKBOX – Enables the sector scan function for both pilots’ displays. 10 - OFF MODE – Turns off the weather mode, provided OFF is selected in both weather radar virtual controllers. – In flight only, a single virtual controller selected to OFF operates in SLAVE mode. 11 - STANDBY MODE – Selects the radar system into a standby mode, provided STBY is selected in both weather radar virtual controllers. – A green FSBY label is displayed within the weather box when forced standby is active, on the ground. 12 - GROUND MAPPING MODE – Enables ground mapping mode. 13 - RADAR MODE – In flight, activates the radar mode. 14 - FORCED STANDBY OVERRIDE – Enables WX on the ground, when selected on both pilots’ virtual control panel. NOTE: Selection of Antenna Stabilization checkbox (STAB OFF) 4 times in less than 3 seconds enables the forced Standby Override function (FSBY OVRD). 15 - WEATHER RADAR ANNUNCIATIONS

– CCD inner knob icon: tilt angle is modifiable.

14-09-05 Copyright © by Embraer. Refer to cover page for details.

Page 44

Controls and Indications

REVISION 21

AOM-1502-003

– First line:

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– Tilt angle readout: displays the tilt angle. – ACT annunciation: ACT is active. – Fault code data (entire line): fault has been detected. – Second line: – Weather radar mode annunciation: GREEN (WX): normal WX. GREEN (WX/R): normal WX with RCT. GREEN (WX/T): normal WX with TURB. GREEN (WX/R/T): normal WX with RCT and TURB. GREEN (GMAP): GMAP mode. GREEN (FSBY): forced standby. GREEN (TEST): test mode and no faults. AMBER (WX CTRL): invalid WX control bus. AMBER (FAIL): failure is detected. AMBER (OVRNG): MAP range greater than 300 NM. WHITE (WX OFF): WX is OFF. WHITE (WAIT): power up. WHITE (STAB): STAB OFF function selected. WHITE (STBY): normal standby. WHITE (S): slave mode is active. – Third line: – Stabilization annunciation: radar stabilization is inhibited. – Target and gain mode annunciation. GREEN (TGT): TGT selected. FLASHING AMBER (TGT): TGT selected and alert condition.

AOM-1502-003

AMBER (VAR): variable gain selected.

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REVISION 21

Controls and Indications

Page 45

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

MCDU CONTROLS CONTROL PEDESTAL

1L

1R

2L

2R

3L

3R

4L

4R

5L

5R

6L

6R

1

1

7 2 6 3

A

B

C

D

E

F

G

H

I

J

K

L

1

2

3

+/ −

M

N

O

P

Q

R

4

5

6

/

S

T

U

V

W

7

8

9

X

Y

Z

4 EM170AOM140136A.DGN

5

0

5

1 - LINE SELECT KEYS – Data is selected to a line from the scratchpad or vice-versa. – Selects a page if the line shows an index display (arrow).

– Controls display brightness.

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Page 46

Controls and Indications

REVISION 21

AOM-1502-003

2 - BRIGHTNESS CONTROL BUTTON

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– A control bar will be displayed in the scratchpad. 3 - TUNING KNOB – Rotating this knob selects frequencies or other numeric values. 4 - ALPHANUMERIC BUTTONS – Enter alphanumeric inputs. – Space key (SP) is used to insert a space. – A toggle plus/minus key inserts the corresponding signal. 5 - PREV/NEXT AND CLR/DEL BUTTONS – Previous (PREV): Changes the current page to the previous page. – Next (NEXT): Changes the current page to the next page. – Clear (CLR): Clears alphanumeric entries or messages in the scratchpad. – Delete (DEL): Works together with line select buttons in order to delete waypoints and other items displayed. This button is inhibited when a message is displayed. 6 - FUNCTION BUTTONS – Menu (MENU): Displays the menu page. – Data link (DLK): Displays ACARS main menu page. – Radio (RADIO): Displays the radio page. – Circuit breaker (CB): Displays the circuit breaker page. – Thrust Rating Selection (TRS): Display the engine thrust ratings for various flight phases. – Performance (PERF): Displays the performance page (FMS function). – Navigation (NAV): Displays the navigation page (FMS function).

AOM-1502-003

– Flight plan (FPL): Displays the flight plan page (FMS function). – Progress (PROG): Displays the progress page (FMS function).

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REVISION 21

Controls and Indications

Page 47

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

– Route (RTE): Display the route page (FMS function). 7 - SCRATCHPAD – It is the working area, located on the bottom line of the display, where the pilot can enter data and/or verify data before line selecting the data into its proper position. – Data is retained on the scratchpad throughout all mode and page changes.

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Page 48

Controls and Indications

REVISION 21

AOM-1502-003

– The scratchpad also provides advisory and alerting messages to be displayed.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

DISPLAY CONTROLLER PANEL GLARESHIELD PANEL

HSI

BARO SET IN

2

WX

3

FMS

hPa

MINIMUMS RA

PREV

11

BARO

V/L

BRG

PUSH STD

5 FPR

10

9

4

8

7

6

EM170AOM140122A.DGN

1

1 - HORIZONTAL SITUATION INDICATOR (HSI) BUTTON – Selects between full compass, arc or map mode for the on-side PFD. 2 - WEATHER RADAR (WX) BUTTON – Displays WX Radar information on PFD (HSI in arc or map mode only). 3 - FMS SELECTION/FMS SOURCES – Selects FMS as the primary navigation source for the on-side PFD and toggles between FMS1 and FMS2. 4 - RA OR BARO MINIMUMS SELECTOR KNOB (OUTER) – RA: sets radio altimeter minimums. AOM-1502-003

– BARO: sets barometric minimums.

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REVISION 21

Controls and Indications

Page 49

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

5 - DECISION HEIGHT OR MINIMUM DESCENT (INNER) – Selects decision height (DH), decision altitude or minimum descent altitude based on position of RA/BARO selector knob. 6 - VOR/LOC BUTTON (V/L) – Selects VOR or LOC as the primary navigation source for the on side PFD and toggles between VOR/LOC1 and VOR/LOC2. 7 - PREVIEW BUTTON (PREV) – Selects the preview mode when the FMS is the primary navigation source. The course and the lateral/vertical deviation can be previewed. – Pressing the first time: enables the on-side VOR/LOC preview. – Pressing a second time: enables the opposite side VOR/LOC preview. – Pressing a third time: disables the preview mode. – The previewed navigation source will automatically transition as the primary navigation source when capture on LOC mode. 8 - FLIGHT PATH REFERENCE (FPR) BUTTON – Commands the flight path reference line and the flight path digital readout. 9 - BEARING SOURCES (BRG) BUTTONS – CIRCLE (ο): allows VOR1, ADF1 or FMS1 selection for the on-side PFD display. – DIAMOND (◊): allows VOR2, ADF2 or FMS2 selection for the on-side PFD display. 10 - BAROMETIC CORRECTION CONTROL (INNER) – Sets barometric altimeter correction.

11 - BAROMETIC CORRECTION SELECTOR KNOB (OUTER)

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Page 50

Controls and Indications

REVISION 21

AOM-1502-003

– Pushing this control knob sets barometric correction to standard.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– IN: sets barometric correction format to inches of mercury.

AOM-1502-003

– HPA: sets barometric correction format to hectopascals.

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REVISION 21

Controls and Indications

Page 51

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

INTEGRATED ELECTRONIC STANDBY SYSTEM (IESS) 3

5

4

6

7

8

2

ILS

9

STD 8199 M

1013 hPa

ILS1

10

340

+

28000 320

10 11 2O

2

269 OO

28 O 280

−

10

26000

260

500

.57 M 18

IRS1

CAGE 17

12

13

BARO

16

14 15

EM170AOM140124A.DGN

1

1 - BRIGHTNESS ADJUSTMENT BUTTONS – Adjust brightness. 2 - AIRSPEED ROLLING DIGITS – Indicates actual calibrated airspeed. – In case of failure the airspeed tape and the pointer will be removed and replaced by a red cross. 3 - VMO/Mmo BARBER POLE – Displayed when VMO/Mmo is within the viewable range, and covers speeds at or above VMO/Mmo (red and white).

4 - ILS BUTTON

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Page 52

Controls and Indications

REVISION 21

AOM-1502-003

– An amber VMO Flag being displayed on the IESS means that the maximum speed indication is lost, because flap/slat information is unavailable to the standby system.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– Selects the display of ILS 1 deviations and the label LOC 1 is annunciated on the left top corner. In case of failure, a red cross replaces the annunciation. 5 - ROLL INDICATION – Indicates the bank angle of the airplane. 6 - REFERENCE BAROMETRIC PRESSURE INDICATION – Indicates the barometric pressure as set by the barometric rotary knob. 7 - STANDARD BUTTON – Sets the barometric pressure to standard atmospheric pressure. 8 - SLIP/SKID INDICATION – Indicates slip or skid angle if flight is not coordinated. 9 - METER ALTITUDE INDICATION – Indicates the actual altitude in meters. – A green hashed box appears on the left side of the numeric digits when altitude is below 10000 m. – A minus (-) symbol appears on the left side of the numeric digits when altitude is below sea level. 10 - BRIGHTNESS CELL – Automatically adjusts the instrument brightness according to the ambient lighting. 11 - ALTITUDE INDICATION – Indicates actual altitude, with graduated scale of 20 ft.

AOM-1502-003

– A NEG indication is displayed vertically in white in case of negative altitude. – In case of failure the altitude tape will be removed and replaced by a red cross, and an ALT flag is displayed.

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REVISION 21

Controls and Indications

Page 53

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

– A green hashed box appears on the left side of the numeric digits when altitude is below 10000 ft. – A minus (-) symbol appears on the left side of the numeric digits when altitude is below sea level. 12 - PITCH ANGLE SCALE – Provides a pitch angle indication between the airplane symbol and the horizon line. 13 - VERTICAL SPEED – Indicates the actual vertical speed in feet per minute (ft/min). – An arrow indicates climb or descent. – In case of failure the corresponding pointer and scale will be removed. 14 - BARO ROTARY KNOB – Allows barometric settings. 15 - ILS DEVIATIONS – Vertical scale: green diamond indicates glide slope position. – Horizontal scale: green diamond indicates localizer position. – Vertical and horizontal scales are not displayed when ILS is not selected. – In case of failure, the pointer and the scale are removed from view and replaced by a red cross. 16 - CAGE BUTTON – Resets attitude to zero, eliminating accumulated drift when the button is pressed for more than two seconds.

– When pressed, an amber CAGE flag is displayed on the upper right corner of the IESS.

14-09-05 Copyright © by Embraer. Refer to cover page for details.

Page 54

Controls and Indications

REVISION 21

AOM-1502-003

– Not operational during the initialization mode and must be used with wings leveled on stabilized flight conditions.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

17 - MACH NUMBER INDICATION – Displayed whenever Mach increases above 0.45 and will be removed when Mach decreases below 0.40. 18 - AIRPLANE SYMBOL

AOM-1502-003

– Reference for airplane attitude indication.

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REVISION 21

Controls and Indications

Page 55

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

CLOCK/CHRONOMETER MAIN PANEL MAIN PANEL

CHR

RST MIN

2

CHR

3

SEC

UTC

GPS INT

SET HR/MO

MIN/DY

SEC/Y

1

AUTO RST

5 HR

6

ET

MIN

EM170AOM140273.DGN

DATE

4

SET

MAIN PANEL CHRONOMETER

1 - DATE/SET KNOB/BUTTON – Allows time setting when GPS/INT/SET selector is in the SET position. Repeated pressings of the SET button causes the selector to cycle between minute, hour, year, month and day. The desired digits flashes and the setting is obtained by rotating the DATE/SET button clockwise to increase and counter-clockwise to decrease. – Selects the date to be displayed on the associated indicator, when GPS/INT/SET selector is in GPS or INT. 2 - RESET BUTTON – Reset the chronometer to zero if chronometer is stopped.

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Page 56

Controls and Indications

REVISION 21

AOM-1502-003

– LCD display is blanked when the RST button is pressed and the chronometer is running.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

3 - CHRONOMETER BUTTON – Starts/stops the chronometer. 4 - GPS/INT/SET SELECTOR – GPS: synchronizes with UTC and DATE from GPS. – INT: displays information from the internal clock. – SET: allows date and time to be set by the DATE/SET KNOB/BUTTON. 5 - ELAPSED TIME SELECTOR – AUTO: automatically starts the chronometer on liftoff. – RST (spring loaded): resets the elapsed time if WOW is present. 6 - CLOCK/CHONOMETER DISPLAY – Displays chronometer, time/date and elapsed time. – If no GPS signal is detected, the clock will display dashes and only the positions INT and SET on the GPS/INT/SET selector will be available.

AOM-1502-003

– The chronometer display is blanked in the non-operating mode.

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REVISION 21

Controls and Indications

Page 57

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

CONTROL WHEEL

1 MI

HR

O

SE T

C

P T T

O F F

E

OT A

TOP

P

S C

−R

AP

EM170AOM140515A.DGN

S

CONTROL WHEEL CHRONOMETER

1 - CHRONOMETER BUTTON – Starts/stops/resets the chronometer displayed on PFD.

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Page 58

Controls and Indications

REVISION 21

AOM-1502-003

– Independent information/functioning for each control wheel.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AOM-1502-003

EM170AOM140323.DGN

STANDBY MAGNETIC COMPASS

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REVISION 21

Controls and Indications

Page 59

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

COMMUNICATION CONTROL WHEEL 1 MI

HR

O

SE T

C

P T T

O F F

E

OT A

TOP

P

S C

−R

AP

EM170AOM140144.DGN

S

1 - CONTROL WHEEL COMMUNICATIONS SWITCH – PTT (momentary): allows VHF transmissions, as well as voice communications to passengers. – HOT: allows communication between crewmembers and between crewmembers and ramp station.

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Page 60

Controls and Indications

REVISION 21

AOM-1502-003

– OFF: allows only audio reception.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

GLARESHIELD COMMUNICATION MAIN PANEL

1

1

PTT

CONTROL PEDESTAL

AOM-1502-003

PA

EM170AOM140145.DGN

2

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REVISION 21

Controls and Indications

Page 61

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

1 - GLARESHIELD PTT BUTTON – Allows VHF transmissions and voice communications to passengers. 2 - PASSENGER ADDRESS PTT BUTTON – Allows voice communications to passengers, regardless of any selection in the audio control panel. While selected, it deactivates the microphone selector button (audio control panel), and in this case no radio transmission occurs since there is no VHF/HF/SATCOM microphone selection.

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Page 62

Controls and Indications

REVISION 21

AOM-1502-003

– When selected for more than 2 min, the communication is automatically deactivated.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

HAND MICROPHONE CONTROLS

PILOT AND COPILOT CONSOLES

1

EM170AOM140146.DGN

1

1 - HAND MIC PTT BUTTON

AOM-1502-003

– Allows transmission through the ACP, as well as communication to passengers.

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REVISION 21

Controls and Indications

Page 63

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

CAPTAIN AND FIRST OFFICER JACK PANELS

1

MIC

PHONE BOOM MIC

14-09-05 Copyright © by Embraer. Refer to cover page for details.

Page 64

Controls and Indications

REVISION 21

AOM-1502-003

1

EM170AOM140147.DGN

ANR HDST

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

1 - CAPTAIN AND FIRST OFFICER JACKS

AOM-1502-003

– Allows plugging in headphone (PHONE), headset (ANR HDST), hand microphone (HAND MIC) and boom microphone (BOOM MIC).

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REVISION 21

Controls and Indications

Page 65

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

OBSERVER JACK PANEL

OBSERVER STATION

OBSERVER JACKS MICROPHONE BOOM

HDPH

ANR

HOT PTT HDST

2

1

EM170AOM140294.DGN

OFF

1 - OBSERVER JACKS – Allows plugging in headphone (HDPH), headset (ANR HDST) and boom microphone (BOOM).

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Page 66

Controls and Indications

REVISION 21

AOM-1502-003

2 - OBSERVER COMMUNICATIONS SWITCH

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– PTT (momentary): allows VHF and voice communications with passengers. – HOT: allows communication between crewmembers and between crewmembers and ramp station.

AOM-1502-003

– OFF: allows only audio reception.

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REVISION 21

Controls and Indications

Page 67

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

RAMP STATION 1

MAINTENANCE PANEL CKPT CALL

LAN

R A M P

GCU / EPM

MIC/PHONE I

N P H

2

1 STEERING

RAMP INPH

2

CKPT CALL

AC GPU GROUND SERVICE SW

LAN

MIC/PHONE

AVAIL IN USE

1

CKPT CALL

R A M P MIC/PHONE I

N P H

1

2

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Page 68

Controls and Indications

REVISION 21

AOM-1502-003

G P U O/ V RLY

EM170AOM140252.DGN

PWR

D C

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

1 - COCKPIT CALL BUTTON (momentary action) – When pressed, generates a single HI/LO tone chime and the RAMP annunciator button flashes on the audio control panel. 2 - MICROPHONE/HEADPHONE JACK – Allow ground personnel to plug in a headphone and a microphone equipped with a PTT button.

AOM-1502-003

NOTE: Ground personnel panel is linked to the hot mic once the ramp button is selected.

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REVISION 21

Controls and Indications

Page 69

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

AUDIO CONTROL PANEL (ACP)

CONTROL PEDESTAL

OBSERVER STATION

1

3

2

4

MIC

VHF1

VHF2

VHF3

HF

SAT

NAV1

NAV2

NAV3

ADF1

ADF2

DME1

DME2

MKR

PA

AUD

EMER

SPKR

INPH

CAB

HDPH

VOL

MIC

VHF1: 47 NORM BKUP

12

11

AUTO

MASK

10

9

8

7

6

5

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Page 70

Controls and Indications

REVISION 21

AOM-1502-003

BKUP

RAMP

EM170AOM140151A.DGN

SELCAL

ID

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

1 - MICROPHONE SELECTOR BUTTONS – Related communication channel is enabled for transmission and reception. – When selected, a green bar illuminates inside the button. 2 - AUDIO CONTROL BUTTONS – Related audio channel is enabled for reception. – Automatically activated when a transmission channel is selected. – More than one audio channel may be selected at the same time. – When selected, a green dot illuminates inside the button. 3 - SATCOM CONTROL BUTTON – UNAVAILABLE. 4 - PASSENGER ADDRESS CONTROL BUTTON – Enables PA announcements. It deactivates the microphone selector button and in this case no radio transmission occurs since there is no VHF/HF/SATCOM microphone selection. – When selected, a green bar illuminates on the transmission button and a green dot illuminate on the reception button. – If PTT (from Yoke, Glareshield or Hand Microphone) remains pressed for more than 2 min, after PA is selected, the communication is automatically deactivated. 5 - SERVICES INTERPHONE CONTROL BUTTONS

AOM-1502-003

– EMER: enables communication with flight attendants during emergency situations (emergency mode). A triple HI/LO tone chime sounds through the PA system and illuminates a red light at ceiling of the flight attendant station. When selected, a green bar flashes on button until the flight attendant picks up the call. Once the flight attendant picks up the call the green bar flashes faster. Pressing the button again, the light becomes steady and the communication with the flight attendant is enabled.

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REVISION 21

Controls and Indications

Page 71

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

– RAMP: enables communication with ground personnel. For an incoming call, the ramp annunciator flashes and remains steady on when active. A single HI/LO tone chimes. A microphone selector button can be selected while RAMP is active. In this case, the RAMP button remains illuminated. Communication through the ramp interphone remains active unless PTT or PA PTT is activated for radio transmission or passenger announcements and resumes when PTT or PA PTT is released. – CAB: enables communication with flight attendants during normal situations (normal mode). A single HI/LO tone chime sounds through the PA system and illuminates a green light at ceiling of the flight attendant station. When selected, a green bar flashes on button until the flight attendant picks up the call. Once the flight attendant picks up the call the green bar flashes faster. Pressing the button again, the light becomes steady and the communication with the flight attendant is enabled. A microphone selector button can be selected while CAB is active. In this case, the CAB button remains illuminated. Communication through the cabin interphone remains active unless PTT or PA PTT is activated for radio transmission or passenger announcements and resumes when PTT or PA PTT is released. NOTE: The RAMP and CAB control buttons can be selected at the same time. Also, one microphone selector button can be selected together with cabin or ramp buttons. CAB cannot be selected while EMER is active as selection of EMER deselects CAB and transfers audio communication to the EMER channel. 6 - MASTER VOLUME CONTROL KNOB – Allows adjustment of the most recently selected audio. 7 - ID FILTER BUTTON – Activates a filter that eliminates voice on VOR and ADF audio so the identification can be heard.

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Page 72

Controls and Indications

REVISION 21

AOM-1502-003

8 - AUDIO SELECTION BUTTONS

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– Enables the respective audio to be summed into the output on the headphone (HDPH), interphone (INPH) or cockpit speaker (SPKR). – When selected, a green dot illuminates inside the button. 9 - ACP DISPLAY – Displays the selected transmission channel and digital volume information. 10 - AUTO/MASK MICROPHONE SWITCH – AUTO (PUSH IN): allows audio communication via oxygen masks. – MASK (PUSH OUT): activates oxygen masks microphone when auto mode fails. – Oxygen mask stowage box doors must be closed and reset in order to enable hand or headset microphone booms after using the oxygen mask microphone. 11 - BACKUP VOLUME CONTROL BUTTON/KNOB – NORM (PUSH IN): normal operation mode. – BKUP (PUSH OUT): restores VHF communication in case of digital audio system failure. – While in BKUP position (PUSH OUT), minimum volume is at the extreme counterclockwise position and the maximum volume is at the extreme clockwise position. – The VHF 1 is the radio available for Captain ACP and VHF 2 is the radio available for the First Officer ACP. 12 - SELCAL ANNUNCIATOR BUTTON

AOM-1502-003

– UNAVAILABLE.

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REVISION 21

Controls and Indications

Page 73

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

DIGITAL VOICE-DATA RECORDER !Airplanes equipped with Honeywell or L3 DVDR OVERHEAD PANEL

DVDR CONTROL PANEL

FWD CVR DVDR ERASE TEST

4

HEADPHONE

3

2

1

EM170AOM140125.DGN

AFT

1 - SELECTOR SWITCH – Selects forward and afterward DVDR switch to set the source of the headphone audio for the aural indication when the DVDR test is successful (to maintenance task only). 2 - HEADPHONE JACK – Monitors tone transmission during test or to monitor playback of voice audio. 3 - TEST BUTTON – Simultaneously tests all CVR and FDR functions on both DVDR.

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Page 74

Controls and Indications

REVISION 21

AOM-1502-003

4 - CVR ERASE BUTTON

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– Erases the recorded audio information, provided that the airplane is on the ground and parking brake is set. "

DIGITAL VOICE-DATA RECORDER !Airplanes equipped with Universal DVDR OVERHEAD PANEL

1

2

3

PASS/ FAIL

PASS/ FAIL

FDR 2 CVR 1

EVENT

HEADPHONE

TEST

ERASE

CVR 2

AUDIO

6

7

5

4

EM170AOM141102B.DGN

FDR 1

1 - FDR PASS/FAIL INDICATOR – GREEN: the associated FDR works properly. – AMBER: the associated FDR is failed or not installed. 2 - HEADPHONE JACK – Monitors tone transmission during test. 3 - CVR PASS/FAIL INDICATOR – GREEN: the associated CVR works properly. AOM-1502-003

– AMBER: the associated CVR is failed or not installed.

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REVISION 21

Controls and Indications

Page 75

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

4 - AUDIO INDICATOR – GREEN: an audio signal at a minimum level is detected in any of the four CVR channels during the self-test. 5 - CVR ERASE BUTTON – Erases the recorded audio information, provided that the airplane is on the ground and parking brake is set. 6 - TEST BUTTON – Simultaneously tests all CVR and FDR functions on both DVDR. 7 - EVENT BUTTON – Not used in this configuration.

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Controls and Indications

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIR DATA SYSTEM The E-JETS are equipped with 5 independent ADSs. Each ADS receives and computes the data collected by its components to provide air data information to the following systems: – Airspeed indicator; – Altimeter; – Vertical speed indicator; – Side slip indicator; – Flight controls; – IESS airspeed indicator; – IESS altitude indicator; – IESS vertical speed indicator; – Static air temperature; – Total air temperature; Each ADS is composed by a specific set of sensors. The following list shows the structure of each system: – ADS 1: TAT 1, ADSP 1/2 and ADA 1. – ADS 2: TAT 2, ADSP 3/4 and ADA 2. – ADS 3: TAT 1, ADSP 3/4 and ADA 3. – ADS 4: ADSP 3/4 and IESS. The ADS 5 sends information to the flight control system. SYSTEM COMPONENTS The ADS components are: – Air Data Smart Probes (ADSP); – Total Air Temperature (TAT) probes and

AOM-1502-003

– Air Data Applications (ADA).

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REVISION 21

Flight Instruments

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIR DATA SMART PROBES AND TAT PROBES The E-JETS are equipped with four air data smart probes (ADSP). The ADSP are composed of: – Multi function probes and – Air data computer. The ADSP/TAT will sense and transmit static pressure, total pressure, angle of attack and TAT to the Air Data System. The angle of attack is calculated based on an interface between the static pressure of the smart probes. – ADSP 1 interfaces with ADSP 2. – ADSP 3 interfaces with ADSP 4. Each ADSP and TAT are heated to provide protection for icing build up maintaining continued sensor accuracy in icing conditions.

ADSP

TAT MFP

TOTAL PRESSURE STATIC PRESSURE AOA TAT

EM170AOM140318A.DGN

ADC

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Page 2

Flight Instruments

REVISION 21

AOM-1502-003

TAT AND ADSP

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIR DATA APPLICATION (ADA) The ADA computes final air data (altitude, airspeed, etc.) and transmits this information to the appropriate airplane systems (PFD, stall protection system, flight controls system, etc). NORMAL OPERATION During normal operation, air data readouts are as follows: – Left PFD - ADS 1. – Right PFD - ADS 2. – IESS – ADS 4. ABNORMAL OPERATION ADS FAILURE If a failure occurs on ADS 1 or ADS 2, the affected PFD loses all air data information and a red cross is shown over the failed indication and an EICAS message is generated alerting the crew of the failure. SENSOR FAILURE If a single sensor failure occurs, like the static air pressure or total air pressure the affected indication will be lost or unreliable. In case of unreliable information the indicator presentation looks normal but the information will be incorrect when compared to the other similar indicators and a flag may be presented on the PFD indicating a split between similar indicators. In case of lost information a red flag is displayed over the failed indicator. ABNORMAL OPERATION LOGIC If a failure of the ADS occurs the failed ADS automatically revert to ADS 3 or the pilot can manually revert to any available ADS to recover the information on the affected PFD. After manual or automatic reversion, the selected source is displayed on a flag on the affected PFD and a stripe bar illuminates on the affected side reversionary button.

AOM-1502-003

The reversionary logic cycle for the left and right PFDs are as follows:

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REVISION 21

Flight Instruments

Page 3

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL Reversionary Logic

Captain First Officer

Normal Operation ADS 1 ADS 2

1st reversion

2nd reversion

ADS 3 ADS 3

ADS 2 ADS 1

ADSP 4

ADSP 3

TAT 2

TAT 1

ADSP 1 EM170AOM140118.DGN

ADSP 2

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Page 4

Flight Instruments

REVISION 21

AOM-1502-003

PROBE LOCATION

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

RADAR ALTIMETER SYSTEM The radar altimeter function measures the airplane height above terrain and sends this information to be displayed on the PFD and to be used by the other airplane systems. To determine the height the radar altimeter transmits a signal to the ground and processes the time it takes to receive the signal return converting it into radio altitude. The radar altimeter range of operation is -20 ft to 2500 ft. When the airplane is parked at the gate or nearby, in the presence of irregular surfaces (i.e. tools, tool carts, stairs, cables, etc), the radar altimeter altitude measurements may be affected. As a result, the miscompare RA may be displayed on both PFDs and the EICAS message APPR 2 NOT AVAIL may be triggered. RADAR ALTIMETER INTERFACE The system interfaces with the TCAS, which uses the radio altitude information to inhibit descend resolution advisories. The system also interfaces with the modular avionics unit (MAU), for data distribution and integrity checking. In addition, other interfaces are performed such as with the EGPWS, to determine airplane sink rate variation, with the DVDR system, in order to record mandatory parameters. DUAL INSTALLATION NORMAL OPERATION In a dual system installation, the PFD 1 displays the system 1 radio altitude and the PFD 2 displays the system 2 radio altitude. ABNORMAL OPERATION If a difference between both radio altitudes occurs a flag RA in amber above the radio altitude box will be displayed.

AOM-1502-003

If one radar altimeter is lost in a dual installation the remaining radar altimeter provides the radio altitude information for both PFDs. In this case the radio altitude readout is shown in amber and an EICAS message is posted indicating the failed system.

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REVISION 21

Flight Instruments

Page 5

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

RADAR ALTIMETER TEST The system has a self test that may be performed by the pilot on the MENU page on the MCDU performing the following steps: – Push the LSK 1L (MISC); – Push the LSK 4R (TEST); – On the TEST page 2/2, push the LSK 3L (RAD ALT) and check the MCDU showing RAD ALT test ON and the radar altitude indication showing 50 ft ± 5 ft on PFD 1 and PFD 2.

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Page 6

Flight Instruments

REVISION 21

AOM-1502-003

– Push the LSK 3L (OFF) to stop the test.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

INTEGRATED ELECTRONIC STANDBY SYSTEM The IESS computes and displays the primary flight information: – Attitude (pitch and roll). – Standard or barometric-corrected altitude and associated barometric pressure. – Calibrated airspeed. In addition, the IESS provides the following secondary functions or displays: – Calibrated Mach number. – VMO/Mmo. – Side slip indication. – Vertical speed. – Localizer and glide slope presentation from the NAV 1 ILS frequency. – Barometric pressure. – Altitude in meters. NORMAL OPERATION The IESS is powered as soon as the airplane battery 1 is selected to ON and airplane battery 2 is selected to AUTO. Then, the IESS starts its alignment phase. The initial IESS alignment takes about 90 seconds to be completed and can be identified on the screen by the “INIT 90 s” flag. NOTE: The airplane must not be moved during the first 90 seconds after power-up, while the IESS is undergoing alignment. Moving the airplane during this period can cause in-flight attitude indication errors that may not be noticeable on ground. ABNORMAL OPERATION

AOM-1502-003

In case of failure, attitude display information (e.g. brown and blue background, pitch scale, roll scale and roll pointer) is removed and replaced by a black background and a red cross, and an ATT flag is displayed. In case of a loss of data, an OUT OF ORDER page is displayed.

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REVISION 21

Flight Instruments

Page 7

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

CLOCK The electronic clock provides the following information: – Chronometer (CHR) – Universal time coordinated (UTC) – Date (day/month and year) – Elapsed time (ET). NORMAL OPERATION The electronic clock displays time information from either the GPS or the internal clock. GPS TIME With the switch set to GPS the system receives the UTC time from the GPS automatically as long as the GPS is receiving a satellite signal. INTERNAL TIME The clock can be set to operate without the GPS. To adjust the internal time proceed as follows: – Turn the GPS – INT switch to SET position; – Rotate the SET switch to adjust the blinking field; – Press the SET switch to move to another clock field; – Repeat the process until all clock field are as desired; – Turn the GPS – INT switch to INT to start the clock internal operation. ELAPSED TIME The elapsed time starts automatically when the airplane is airborne and stops when the airplane returns to the ground state. There is no automatic reset between flights. To reset the counter set the AUTO - RST switch to RST and release it. CHRONOMETER The CHR switch starts and stops the chronometer.

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Page 8

Flight Instruments

REVISION 21

AOM-1502-003

The RST switch resets the chronometer when it is stopped.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

STANDBY MAGNETIC COMPASS The illuminated magnetic compass has a rotating compass card marked with white legend on black background, with the cardinal points appropriately marked as “N”, “S”, “E”, and “W”. Each 30-degree line, except the cardinals, is identified by numerals representing degrees. Headings are read against a vertical lubber line engraved and filled white on the inside surface of the bowl. Two calibration cards are supplied for the compass, one for normal operational condition (pitots on and windshield heating off) installed above the compass, and one for electrical emergency condition, installed on the main panel left corner.

AOM-1502-003

NOTE: Magnetic compass reading shall always be done considering conditions written in applicable calibration cards.

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REVISION 21

Flight Instruments

Page 9

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

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Page 10

Flight Instruments

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

GENERAL

AOM-1502-003

The communication system comprises the radio communication (VHF), interphone, audio control panels and digital data voice recorder.

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REVISION 21

Communication

Page 1

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

RADIO COMMUNICATION SYSTEM VERY HIGH FREQUENCY The VHF digital radios (VDR) 1 and 2 are located in the Modular Radio Cabinets (MRC). VDR 1 and 2 interfaces with the audio system through the audio/microphone busses, and with the MCDU/PFD through the ASCB. VDR channels 1 and 2 are for voice communication only. VDR 3 interfaces with audio system and MCDU/PFD indirectly via MRC 2 and directly to MAU 1 to data transmission. The VHF radio 3 is located on a separated radio Mini Cabinet. VDR 3 provides voice communication as well as data communications through ACARS (Aircraft Communication Addressing and Reporting System) applications. The VHF frequency is tuned/activated through the MCDU (primary means) or CCD (PFD). A tuning backup is available in MCDU 2 in case of loss of both MAUs. In the same way, if the audio bus is lost there are audio backups. The flight crew may tune the VHF frequency on the MCDU as follows: VHF 1/2 – Press RADIO button on the MCDU to go to RADIO page 1/2. RADIO PAGE 1/2: – The frequency is changed using either the scratchpad or the tuning knob on the MCDU; – To change a frequency value with the scratchpad, use the keypad to enter the new frequency value, and then push the LSK next to the frequency to be modified. This transfers the value from the scratchpad to the selected frequency;

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Page 2

Communication

REVISION 21

AOM-1502-003

– To change a frequency value with the MCDU tuning knob, the standby frequency must prior be boxed pressing the LSK 2L/2R. Tune the frequency. With the cursor around the standby frequency and the swap icon displayed, push the LSK to swap the standby and active frequencies.

AIRPLANE OPERATIONS MANUAL

RADIO SQ

COM1

SQ

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

1 / 2 COM2

TX

123 . 200 118 . 600 FMS AUTO

NAV1 114 . 80 DME H PXR 115 . 60

FMS AUTO

116 . 8 W123456

TCAS/XPDR

XPDR 1471 IDENT IDENT

TA/RA

EM170AOM140325B.DGN

STBY

NAV2 117 . 4

RADIO PAGE 1/2

COM 1 (2) PAGE 1/1: – Press the respective standby frequency twice if not boxed, otherwise press once, to go to COM page 1; – On the COM page it is possible to capture a frequency tuned in memory. Press LSK 3L to box the memory tune and use the tuning knob to cycle the stored frequencies. Press the active frequency to capture the selected memory tune; – Press LSK 1R to cycle to the squelch on or off; – Press LSK 3R to cycle to the frequency spacing: 8.33: frequency has three decimal places. 25: frequency has two decimal places.

AOM-1502-003

– Press LSK 6L to go to COM MEMORY page 1/2.

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REVISION 21

Communication

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

1 / 1

COM1

SOUELCH

ACTIVE

ON OFF MODE

123 . 200 PRESET 118 . 000

FREO

MEM TUNE 1 KDVT TWR 118.400

EM170AOM140839A.DGN

8 . 33 25

RADIO 1 / 2

MEMORY

COM PAGE 1/1

The VHF frequency selection through the CCD is as follows: – Select the PFD through the CCD. The left and right format location buttons select respectively pilot’s and copilot’s PFDs; – Through the touch pad move the cursor to the navigation frequency window; – Tune the standby frequency through the tuning knob;

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Page 4

Communication

REVISION 21

AOM-1502-003

– Activate the standby frequency by pressing the enter key.

W 24

RNP 1O.1

12 15

5

21

COM1 18O 55 119 4O

FLIGHT INSTRUMENTS/COMM/NAV/FMS

E

VOR1 VOR2

SYSTEMS DESCRIPTION

NAV1 115 6O 119 O3

EM170AOM140893A.DGN

AIRPLANE OPERATIONS MANUAL

COM MEMORY PAGES:

AOM-1502-003

– On the COM MEMORY page it is possible to capture a frequency tuned in memory or store a frequency/identification. To capture a frequency press the respective memory frequency to box it and press 1L to activate the frequency. To store a frequency or its identification use the alphanumeric keys and press the respective memory line select key. Additionally the frequency can also be stored pressing the receptive memory line select key and rotating the tuning knob.

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REVISION 21

Communication

Page 5

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

1 /2

COM MEMORY COM 1 123 . 722 1 - KDVT TWR 118 . 400 2 - KDVT GND 121 . 800 3 - MEMORY

MEMORY - 4 MEMORY - 5 MEMORY - 6

RADIO 1 / 2

EM170AOM140840A.DGN

COM 1

COM MEMORY PAGES

VHF 3 RADIO PAGE 2/2: – To bring up the RADIO PAGE 2/2, with the radio PAGE 1/2 displayed, press the NEXT button; – On RADIO page 2/2 it is possible to tune and activate the VHF 3 frequencies for voice mode. Press LSK 6L twice to go to COM 3 page 1/1, and then press LSK 2R to cycle the operational mode (data or voice). It is possible to tune a radio frequency in the same manner as VHF 1 and 2;

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Page 6

Communication

REVISION 21

AOM-1502-003

– The frequencies for data transmission are selected on a specific ACARS page. With data mode selected, the indication ‘DATA’ displays, otherwise VHF 3 active and standby frequencies display.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

RADIO

2 / 2

1L

ADF1 230 . 0

1R

2L

365 . 0

2R

3L

3R

4L

5R

6L

6R

EM170AOM140490A.DGN

5L

4R

COM3 DATA

AOM-1502-003

RADIO PAGE 2/2 (DATA MODE)

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REVISION 21

Communication

Page 7

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

RADIO

2 / 2

SQ

ADF1

ADF2

230 . 0

235 . 5

365 . 0

360 . 0

HF1 8 . 8550

UV

10 . 0960 EM170AOM140326.DGN

COM3 121 . 7 118 . 5

RADIO PAGE 2/2 (VOICE MODE)

COM 3 PAGE 1/1:

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Page 8

Communication

REVISION 21

AOM-1502-003

– The COM 3 page provides the same options as COM 1 (2) pages, except that is possible to select the transmission mode for VHF 3. The transmission mode is selected by pressing LSK 2R to cycle the operational mode (data or voice).

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

COM 3

2L 3L 4L

ACTIVE

SQUELCH

123.200

ON

118.000 MEM

OFF MODE

PRESET

DATA

VOICE

TUNE

FREQ

8.33

1 - KDVT TWR 118.400

25

2R 3R 4R

5L 6L

1R

5R MEMORY

RADIO

2/2

6R

EM170AOM140491B.DGN

1L

1/1

AOM-1502-003

COM 3 PAGE 1/1

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REVISION 21

Communication

Page 9

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

BACKUP RADIO PAGE: – The BACKUP RADIO page provides means for tunning COM 1, VHF NAV 1 and XPDR 1 (ALT OFF mode) in case of loss of primary and secondary tuning means (tuning using MCDU and CCD). In such cases, radio access is done via backup connection available on MCDU 2; – The BACKUP RADIO page is available by pressing the MENU function button on the MCDU and then LSK 4L on Menu page. The BACKUP RADIO page displays automatically on MCDU 2 for some failure conditions.

MENU 1R

MISC

2L

2R

3L

3R

4L

< BKUP RADIO

4R

5L

MCDU MAINT >

5R

6L

MCDU STAT >

6R

EM170AOM140516A.DGN

1L

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Communication

REVISION 21

AOM-1502-003

MENU PAGE 1/1

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

1L

COM1 123 . 2OO

1R

2L

365 . 0

2R

3L

NAV1 114 . 8O

3R

4L

11O . 6O

4R

XPDR 1471

5L 6L

STBY

ALT-OFF

IDENT

5R 6R

EM170AOM140511A.DGN

BACKUP RADIO

AOM-1502-003

BACKUP RADIO PAGE 1/1

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REVISION 21

Communication

Page 11

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

LAN

TUNNING BACKUP

MCDU 1

CCD 1

MAU 1

MAU 3

CMF 2 CMC

CMF 1

CCD 2

MFD 1

PFD 1

MFD 2

MCDU 2

PFD 2

MAU 2

ASCB

AUDIO BACKUP

ANTENNAS

MRC 2

MRC 1

VHF 2 XPDR 2 ADF 2

VHF 1 XPDR 1 ADF 1

ANTENNAS

AUDIO / MICROPHONE BUS

AUDIO PANEL 2

AUDIO PANEL 3

AUDIO PANEL 1

EM170AOM140481B.DGN

VHF 3

AUDIO BACKUP

ANTENNA

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Page 12

Communication

REVISION 21

AOM-1502-003

NAVIGATION AND COMMUNICATION SYSTEM SCHEMATIC

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

INTERPHONE SYSTEM The interphone system provides communication between the flight crew, flight attendants and ramp personnel. The flight attendants communicate between flight attendant stations or with the flight crew using any of the attendant handsets. Communication between flight crew and flight attendants may be done through the ACP. Call chimes are annunciated at the beginning of the call from the cockpit to the flight attendants and vice-versa.

PASSENGER ADDRESS (PA) The PA system allows flight crew in the cockpit and flight attendants to make announcements to the passengers. Announcements are heard through speakers located in the cabin and in the lavatories. The pilots can make announcements using a hand microphone, headset boom or oxygen mask microphones. The flight attendants can use the PAPA handset located at their stations. Pre-recorded announcements may be provided as well as recorded music for passenger entertainment. PA system use is prioritized. Cockpit announcements have first priority and override all others. Flight attendant announcements override the pre-recorded announcements which override the music system.

ATTENDANT CALL The call system is used as a mean for crewmembers to gain the attention of other crewmembers and to indicate that interphone communication is desired.

AOM-1502-003

Attention is gained through the use of lights and aural signals (chimes or horn). The cockpit may be called from either flight attendant station or by the ground personnel. The ground personnel may only be called from the cockpit. Flight attendants may be called from the cockpit through interphone buttons on the ACPs or flight attendant call button on the overhead panel, the other attendant station, or from any passenger seat (PSU) or lavatory. Call lights in the passenger cabin identify the source of incoming calls to the attendants. Call system chime signals low, high, or high/low tones are audible in the passenger cabin through the PA system speakers. The PA speakers

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REVISION 21

Communication

Page 13

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

also provide an alerting chime signal whenever one of the following conditions occur: – NO SMOKING, FASTEN SEAT BELT, or RETURN TO SEAT (in the lavatory) signs illuminate or extinguish – STERILE COCKPIT light illuminates.

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Page 14

Communication

REVISION 21

AOM-1502-003

The attendant call lights located on the forward and aft main ceiling panel areas provide a visual indication to attendant when there is a call from the flight crew or passengers.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

ATTENDANT CALL TABLE Calling originator

Called position

Visual signal at called position Green light

Attendant Station Cockpit

Cockpit (lateral console) Cockpit (Overhead Panel)

Red light

Amber sterile cockpit light No smoking or Passenger cabin, fasten belt signs lavatories and illuminate/ galleys extinguish

Aural signal at called position Single high/low tone chime Triple high/low tone chime Single high tone chime Single low tone chime

Ramp station

-

Horn in the nose wheel well

Attendant station

-

Single high/low tone chime

AOM-1502-003

Single or triple CAB or EMERG high/low tone annunciator Cockpit chime for CABor button flashes Attendant EMERG, on the ACP station respectively Single high/low Attendant station tone chime RAMP annunciator Single high/low Ramp station Cockpit button flashes tone chime on the ACP Single high tone Lavatory Attendant station Orange light chime Passenger Single high tone Attendant station Blue PSU chime

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REVISION 21

Communication

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

AUDIO CONTROL PANEL There are three Audio Control Panels (ACP), located at the control pedestal and observer station. Each panel controls an independent crew station audio system and allows the flight crew to select the desired radios, navigation aids, interphones and PA systems for monitoring and transmission. The audio panel receives inputs from all audio communication channels and aural warnings. Audio warning for altitude alert, ground proximity warning system (GPWS), traffic collision avoidance system (TCAS), and windshear among others, are also heard through the speakers and headsets. These warnings cannot be controlled or turned off by the flight crew. Audio from each ACP is monitored using a headset, headphone or the related speaker, except for the observer speaker.

DIGITAL VOICE DATA RECORDER (DVDR) SYSTEM !Airplanes equipped with Honeywell or L3 DVDR

The digital voice data recorder system (DVDR) combines a flight data recorder (FDR) and a cockpit voice recorder (CVR) in a single unit. Two DVDR units are installed. DVDR 1 is installed in the forward electronic bay, and the DVDR 2 in the aft electronic bay. Each unit receives, records and preserves all required data parameters and voice recordings from the cockpit crew and area microphones. The DVDR unit is capable of recording the last 120 min of audio information from cockpit area microphone and primary crew microphones and 25 h of flight data. The DVDR automatically starts recording audio information as soon as power up is performed and continues until the power down. The flight data begins to be recorded when the first engine is started. The DVDRs FDR data is available through the MCDU for maintenance purposes only. If the DVDR power system fails, an EICAS message is generated to indicate the failure. All DVDR EICAS messages are advisory and some of them are inhibited in critical phases of flight, such as takeoff.

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Communication

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

!Airplanes equipped with Universal DVDR

The digital voice data recorder system (DVDR) combines a flight data recorder (FDR) and a cockpit voice recorder (CVR) in a single unit. Two DVDR units are installed. DVDR 1 is installed in the forward electronic bay, and the DVDR 2 in the aft electronic bay. Each unit receives, records and preserves all required data parameters and voice recordings from the cockpit crew and area microphones. Additionally, the DVDR 1 is equipped with an internal RIPS (Recorder Independent Power Supply) which supplies power to the CVR whenever there is an airplane power loss. The DVDR unit is capable of recording the last 120 min of audio information from cockpit area microphone and primary crew microphones, 120 min of datalink data and 25 h of flight data. The DVDR automatically starts recording audio information as soon as power up is performed. Flight data recording begins when the first engine is started. After power down, the DVDR continues recording audio information for 10 min. During this time, the FDR1, FDR2, and CVR2 PASS FAIL lights illuminate steady in amber on the DVDR Control Panel. The DVDRs FDR data is available through the MCDU for maintenance purposes only. If the DVDR power system fails, an EICAS message is generated to indicate the failure. All DVDR EICAS messages are advisory and some of them are inhibited in critical phases of flight, such as takeoff. "

COMMUNICATION MANAGEMENT FUNCTION (CMF) The Communication Management Function (CMF) is an airborne communications router that supports communication between airplane datalink applications and their corresponding ground service providers. The following functionalities are available through the CMF: – Character-oriented communication through the Aircraft Communications Addressing and Reporting System (ACARS) network;

AOM-1502-003

– Communication between different devices in the airplane.

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REVISION 21

Communication

Page 17

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

SYSTEM INTERFACES The CMF has the following interfaces: – Multifunction Control Display Unit The MCDU is the primary flight crew interface with the CMF functions, which are accessed through the ACARS MAIN MENU by pressing the DLK function key. Alternative access to the CMF functions is performed by pressing the MENU function key on the MCDU, entering the MISC page and selecting the ACARS prompt. Further access to other pages is provided through the line select keys (LSK) on the MCDU. Crew alerting and advisory messages are displayed on the MCDU scratchpad. Alerting messages are displayed regardless of whether CMF is active on the MCDU, while advisory messages are displayed only when the CMF is active on the MCDU. If it is the first access to the CMF pages since power up, the CMF ACARS MAIN MENU is displayed. If it is not the first access since power up and there are new messages, the NEW MESSAGES page is displayed. If it is not the first access since power up and there are no new messages, the last CMF page accessed is displayed. – Printer The CMF uses the Local Area Network (LAN) to interface with an optional Printer. CMF data may be printed from an MCDU by using the print prompt displayed on an active CMF page. – Central Maintenance Computer The CMC receives fault and event reports from the CMF and allows communication between the CMF and an optional Printer.

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Communication

REVISION 21

AOM-1502-003

– Primary Flight Display The amber “MSG” annunciation is displayed on the PFD when uplink messages are received from ground Datalink Service Providers. Also, this annunciation is displayed following an alerting message on the MCDU scratchpad.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

SPD T

APPR1 LOC GS

AP AT

115

FLIGHT INSTRUMENTS/COMM/NAV/FMS

3O OO

16O

4OOO 4

15O

FS

14O

2O

2O

1O

1O

2 1

AC

125

35OO

AP

1OOO

-3.O RF

1OO

1O

1O

9O

2O

2O

1 2

M

GSPD 3OO KT

3OOO 4

BARO 4OO

29.92 IN

CRS

HDG

21O

21O

21O

ILS1

21

3O

12

W

E

33

VOR1 VOR2

N

3

VHF1 118 5O 119 25

1O

24

15

S

CHR

O8:12

MSG NAV1 119 1O 119 15

EM170AOM141231A.DGN

11O

19O

1OOO

6

MSG ANNUNCIATION ON PFD

– Engine Indication and Crew Alerting System The following EICAS messages are related to CMF. Refer to AOM 14-09-35 for messages description. !Airplanes with CMF installed, Post-Mod MAU Load 25.1.0.1

– DATALINK 1 FAIL. AOM-1502-003

"

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REVISION 21

Communication

Page 19

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

!Airplanes equipped with CMF and Pre-Mod MAU load 25.1.0.1

– CMF 1 FAIL. "

– Aural Warning System When an Air Traffic Services (ATS) message is received, a voice message “ATS MESSAGE” sounds once. – Flight Management System The CMF serves only as a router to allow communication of data messages processed by the FMS, such as flight plan update requests, flight plan updates, performance data, etc. – Digital Voice Data Recorder The optional CMF interface with DVDR provides the capability to record datalink message traffic between the airplane and the ground stations.

CMF PAGES ON MCDU There are pages for Airline Operational Communication (AOC) applications, which are accessed on the ACARS MAIN MENU. Pages and messages format for AOC applications may be customized by the airline through an AMI (Airline Modifiable Information) database. The AMI pages are identified by “ACARS” on the upper left corner of each page. There are pages for Air Traffic Service (ATS) applications. These pages are accessed through the ATS MENU option on the ACARS MAIN MENU. ATS pages are also defined in the Honeywell Generated Information (HGI) database and can not be customized by the airline.

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Communication

REVISION 21

AOM-1502-003

There are System Pages, which are primarily accessed through the SYS MENU option on the ACARS MAIN MENU. The System Pages are defined in the Honeywell Generated Information (HGI) database and can not be customized by the airline. Pages defined in the HGI database are identified by “CMU” on the upper left corner of each page.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRCRAFT COMMUNICATIONS ADDRESSING AND REPORTING SYSTEM (ACARS) ACARS is a datalink system that allows real time communication between ground stations and the airplane. Using the ACARS the airline is able to: – Monitor fuel consumption and fuel cost in real time; – Receive a report on the airplane position; – Manage delays and passenger connections; – Receive weather information and ATC clearance on board the airplane; – Transmit and receive messages from and to the airplane. The messages exchanged are divided in two groups: – Addressed to or by crew members: datalink requests or free text reports; – Automatically sent: reports of flight data, performance data and routine events. Communication with ground stations is made through the VHF Data Radio (VDR) 3 channel.

AOM-1502-003

Applications that operate through ACARS are defined as Airline Operational Communications (AOC) and Air Traffic Services (ATS).

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REVISION 21

Communication

Page 21

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

AIRLINE OPERATIONAL COMMUNICATIONS (AOC) APPLICATIONS The AOC applications supported by the CMF are character-oriented applications that are designed to be transmitted through the ACARS network. The AOC applications format and their location on the ACARS MAIN MENU may be customized by the airline through an Airline Modifiable Information (AMI) database, except the ATS MENU option. Examples of AOC applications are: – Flight Initialization; – Crew Identification; – Free Text; – Weather Request; – OOOI Reports. Out, Off, On and In (OOOI) reports are automatic messages sent by the CMF when events associated with gate departure or arrivals have occurred. Both reports and trigger events may be customized by the airline. Examples are: – Out – doors closed and parking brake released; – Off – takeoff (landing gear retraction); – On – landing (landing gear extension); – In – gate arrival (parking brakes set and doors open). The AOC applications required by most airlines and which are described in this section are: – ACARS MAIN MENU; – PRE-FLIGHT; – INITIALIZATION; – DEPARTURE DELAY REPORT; – WEATHER REQUEST; – VHF VOICE (VOX) CONTACT REQUEST;

– IN-FLIGHT;

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Communication

REVISION 21

AOM-1502-003

– VHF VOICE CONTACT UPLINK;

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– ENROUTE DELAY REPORT; – ARRIVAL DELAY REPORT; – ESTIMATED TIME OF ARRIVAL (ETA) REPORT; – DIVERSION REPORT; – POST-FLIGHT; – FREE TEXT; – FLIGHT TIMES; – NEW MESSAGES LOG; – MESSAGES SEND LOG; – MESSAGE RECEIVED LOG; – STATUS; – SENSOR STATUS; – ASCB DATA;

AOM-1502-003

– PORT ACTIVITY.

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REVISION 21

Communication

Page 23

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

ACARS MAIN MENU

MAIN MENU

1L

< PRE FLT

2L

NEW MSGS >

1R

< IN FLT

MSGS SENT >

2R

3L

< POST FLT

MSGS RCVD >

3R

4L

< FREE TEXT

STATUS >

4R

5L

< FLT TIMES

6L

< SYS MENU

5R ATS MENU >

6R

EM170AOM140479D.DGN

ACARS

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Communication

REVISION 21

AOM-1502-003

ACARS MAIN MENU

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

PRE FLIGHT The PRE FLT option allows access to the PRE-FLIGHT page, which may be used to send information related to pre-flight activities. This page is also used to perform system initialization and it is available during all flight phases. After initialization, the crew receives a message to confirm that the flight has been recognized as an ACARS flight. The ACARS system uses the VHF COM 3 when in DATA mode. INITIALIZE

ACARS

PRE-FLIGHT

1L

< INITIALIZE

2L

< DEP DELAY

2R

3L

< FREE TEXT

3R

4L

< WX REQUEST

4R

5L 6L

1R

VOX CONTACT >

5R

ATS MENU >

6R

< MAIN MENU

EM170AOM140855B.DGN

NEW MSGS >

The initialization display provides flight number, departure and destination stations, and crew member information that are used by the AOC applications. When the initialization is performed, some information is directly transferred from the FMS to the INITIALIZE page and some information is to be inserted by the flight crew. – XPDR FLT ID: XPDR Flight ID (source: XPDR); – FLT NO: Flight Number (source: CMF); AOM-1502-003

– DEP: Departure (source: FMS);

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REVISION 21

Communication

Page 25

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

– FUEL QTY: Fuel Quantity (source: fuel gauges); – CAP ID: Captain ID (source: flight crew); – F/O ID: First Officer ID (source: flight crew); – SKED DAY: Schedule Day (source: flight crew); – DEST: Destination (source: FMS); – BD FUEL: Boarded Fuel (source: flight crew); – Crew 3 ID and Crew 4 ID (source: flight crew).

ACARS

INITIALIZE

FLT NO

2L

DEP SBSJ

3L

FUEL QTY 9.6

SKED DAY XPDR FLT ID ABC123

CYPE

5L

F/O ID CHLS

6L

< RETURN

1R 2R

BD FUEL -----

3R

CREW-3 ID

CAPT ID 4L

24 DEST SBCT

LANA

4R

CREW-4 ID CECI DATALINK

5R

AUTO INIT

*

6R

EM170AOM140856B.DGN

1L

0123

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Communication

REVISION 21

AOM-1502-003

INITIALIZE PAGE

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

DEPARTURE DELAY The DEP DELAY option allows access to the DEPARTURE DELAY page, which may be used to inform the AOC of a departure delay.

ACARS

DEPARTURE DELAY

EST OFF

2L

CODE ---

12:40 REASON ATC

1R 2R

3L

REMARKS DELAY DUE TO HEAVY TRAFFIC

3R

4L

----------------------------------

4R

5L

----------------------------------

5R

DATALINK 6L

< RETURN

REPORT

*

6R

EM170AOM140857B.DGN

1L

AOM-1502-003

DEPARTURE DELAY PAGE

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REVISION 21

Communication

Page 27

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

WEATHER REQUEST The WX REQUEST option allows access to the WEATHER REQUEST page, which may be used request weather information. After selecting the desired information, it is necessary to insert the station ICAO code in the respective line select key (1R to 4R).

ACARS

WEATHER REQUEST STA1

1L

* METAR

2L

* TAF

3L

* FCST-14HS

4L

* ACT

SBCT STA2

1R

-----

2R

STA3 ----STA4 -----

& FCST

5L

3R 4R

6L

< RETURN

REQUEST

*

6R

EM170AOM140858A.DGN

5R DATALINK

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Communication

REVISION 21

AOM-1502-003

WEATHER REQUEST PAGE

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

VOX CONTACT The VOX CONTACT option allows access to the VOX CONTACT REQ page, which may be used by the flight crew to downlink a request to the AOC on the selected frequency. The flight crew needs to access the radio page to tune the desired frequency, which is displayed as VOX FREQ adjacent to line select keys 4L or 4R, depending on the VHF bandwidth selected on line select keys 2L or 2R.

ACARS

REQ

VOX CONTACT

1L 2L

1R

*8.33

KHZ

25 KHZ

*

3L

2R 3R

VOX FREQ 4L

131.80

5L

4R

6L

< RETURN

REQUEST

*

6R

EM170AOM140871B.DGN

5R DATALINK

AOM-1502-003

VOX CONTACT REQ PAGE

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REVISION 21

Communication

Page 29

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

IN FLIGHT The IN FLT option allows access to the IN FLIGHT page, which may be used to send information related to in-flight activities. It is available during all flight phases.

ACARS

IN FLIGHT

2L

NEW MSGS >

1R

< ARR DELAY

ETA >

2R

3L

< FREE TEXT

DIVERSION >

3R

4L

< WX REQUEST

5L 6L

4R VOX CONTACT >

5R

ATS MENU >

6R

< MAIN MENU

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Communication

REVISION 21

AOM-1502-003

< ENRT DELAY

EM170AOM140859B.DGN

1L

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

ENROUTE DELAY The ENRT DELAY option allows access to the ENROUTE DELAY page, which may be used to inform the AOC of an enroute delay.

ACARS

ENROUTE DELAY CODE

EST IN

2L

---

13:12 REASON ATC

1R 2R

3L

REMARKS ----------------------------------

3R

4L

----------------------------------

4R

5L

----------------------------------

5R

DATALINK 6L

< RETURN

REPORT

*

6R

EM170AOM140860B.DGN

1L

AOM-1502-003

ENROUTE DELAY PAGE

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REVISION 21

Communication

Page 31

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

ARRIVAL DELAY The ARR DELAY option allows access to the ARRIVAL DELAY page, which may be used to inform the AOC of an arrival delay.

ACARS

ARRIVAL DELAY CODE

EST IN

2L

---

14:12 REASON ATC

1R 2R

3L

REMARKS ----------------------------------

3R

4L

----------------------------------

4R

5L

----------------------------------

5R

DATALINK 6L

< RETURN

REPORT

*

6R

EM170AOM140861B.DGN

1L

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Page 32

Communication

REVISION 21

AOM-1502-003

ARRIVAL DELAY PAGE

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

ESTIMATED TIME OF ARRIVAL (ETA) The ETA option allows access to the ETA REPORT page, which may be used to inform the AOC of the estimated time of arrival.

ACARS

ETA REPORT

ETA

2L 3L 4L 5L

14:12

1R

REMARKS WE ARE ARRIVING LATER THAN EXPECTED

----------------------------------------------------------------------------------------------------

2R 3R 4R 5R

DATALINK 6L

< RETURN

REPORT

*

6R

EM170AOM140862A.DGN

1L

AOM-1502-003

ETA REPORT PAGE

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REVISION 21

Communication

Page 33

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

DIVERSION The DIVERSION option allows access to the DIVERSION page, which may be used to inform the AOC of a diversion to another airport.

ACARS

DIVERSION REPORT

REVISED ETA 1L

16:12

1R

2L

ALT AIRPORT SBCT

2R

3L

REMARKS ----------------------------------

3R

4L

----------------------------------

4R

----------------------------------

5R

DATALINK 6L

< RETURN

REPORT

*

6R

EM170AOM140863A.DGN

5L

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Page 34

Communication

REVISION 21

AOM-1502-003

DIVERSION REPORT PAGE

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

VOX CONTACT The VOX CONTACT option allows access to the VOX CONTACT REQ page, which may be used by the flight crew to downlink a request to the AOC on the selected frequency. The flight crew needs to access the radio page to tune the desired frequency, which is displayed as VOX FREQ adjacent to line select keys 4L or 4R, depending on the VHF bandwidth selected on line select keys 2L or 2R.

ACARS

REQ

VOX CONTACT

1L 2L

1R

*8.33

KHZ

25 KHZ

*

3L

2R 3R

VOX FREQ 4L

131.80

5L

4R

6L

< RETURN

REQUEST

*

6R

EM170AOM140871B.DGN

5R DATALINK

AOM-1502-003

VOX CONTACT REQ PAGE

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REVISION 21

Communication

Page 35

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

POST FLIGHT The POST FLT option allows access to the POST-FLIGHT page, which may be used to send information related to post-flight activities. It is available during all flight phases.

ACARS

POST-FLIGHT

1L

< FLT TIMES

2L

< ARR DELAY

2R

3L

< FREE TEXT

3R

4L

< POST FLT REPORT

4R

6L

1R

VOX CONTACT >

5R

ATS MENU >

6R

< MAIN MENU

EM170AOM140864B.DGN

5L

NEW MSGS >

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Communication

REVISION 21

AOM-1502-003

POST-FLIGHT PAGE

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

POST-FLIGHT REPORT The POS FLT REPORT option allows access to the POST FLT RPT page, which may be used to inform flight data to the AOC. This display is only accessible from the ON event until the end of the flight. Refer to the definition of the OOOI reports in the previous pages.

POST FLT RPT

OUT

BLK TIME

15:11

IN

01:33

OFF 2L

1 / 2 16:44 ON

1R

16:42 AUTOLAND

2R

FLT TIME

15:49

00:53

PILOT LNDG 3L

CYPE

4L

CAT LNDG CAT I

3R

NO

4R

5L

READY PRINT

*

5R

6L

NO COMM REPORT

*

6R

< RETURN

EM170AOM140865B.DGN

1L

ACARS

AOM-1502-003

POST FLT RPT PAGE

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REVISION 21

Communication

Page 37

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

ACARS

AIRPLANE OPERATIONS MANUAL

POST FLT RPT

2 / 2

1L

----------------------------------

1R

2L

----------------------------------

2R

3L

----------------------------------

3R

4L

---------------------------------READY

4R

5L

PRINT

*

5R

*

6R

NO COMM 6L

< RETURN

REPORT

EM170AOM140866B.DGN

REMARKS

FREE TEXT

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Page 38

Communication

REVISION 21

AOM-1502-003

The FREE TEXT page may be used to send a free text message to the AOC.

AIRPLANE OPERATIONS MANUAL

ACARS

FREE TEXT

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

1 / 2

TEXT LINES 1L 2L

----------------------------------

2R

3L

----------------------------------

3R

4L

---------------------------------READY

4R

5L

PRINT

*

5R

*

6R

DATALINK 6L

< RETURN

REPORT

EM170AOM140867B.DGN

1R

AOM-1502-003

FREE TEXT PAGE

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REVISION 21

Communication

Page 39

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

FLIGHT TIMES The FLT TIMES option allows access to the FLIGHT TIMES page. This page allows the flight crew to obtain flight statistics on the flight phases. It displays flight number, flight day and the ACARS times for OOOI events. Refer to the definition of OOOI reports in the previous pages. The current and previous flight times information is displayed on two pages. At the end of a flight event, all the parameters on the current flight times page are copied to the previous flight times page and the parameters on the current flight times page are cleared.

ACARS

1 / 2

FLIGHT TIMES CURRENT FLIGHT

3L

15:11/ 9.7 IN/FUEL

5L

* * * * */* * * * * BLOCK * * * * */* * * * *

6L

< RETURN

4L

DEP/DEST SBSJ/SBCT OFF/FUEL

* * * * */* * * * *

1R 2R 3R

ON/FUEL

* * * * */* * * * * FLIGHT * * * * */* * * * * 1534.6

4R 5R 6R

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Communication

REVISION 21

AOM-1502-003

2L

FLT NO/DAY 0123 /24 OUT/FUEL

EM170AOM140868B.DGN

1L

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

NEW MESSAGES The NEW MSGS option allows access to the NEW MESSAGES page. This page lists up to 30 messages received that have not been viewed by the crew. When the log file reaches 28 messages, a “RESPOND TO UPLINKS” scratchpad message is displayed and continues to be displayed until 30 messages are stored in the log. If a 31st message is received, the message can not be stored in the log file. The “RESPOND TO UPLINKS” message is again displayed and the uplink message is discarded once it is acknowledged by the CMF as received.

1250Z

1 / X

1L

MESSAGE 1235Z

NEW FREE TEXT > NEW

1R

2L

MESSAGE

TWIP REQUEST >

2R

3L

3R

4L

4R

5L

5R

6L

< RETURN

DELETE LOG

*

6R

EM170AOM140869B.DGN

NEW MESSAGES

CMU

AOM-1502-003

NEW MESSAGES PAGE

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REVISION 21

Communication

Page 41

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

MESSAGES SENT The MSGS SENT option allows access to the MSG SEND LOG page. This page lists all messages that have been sent by the flight crew. The Airline Modifiable Information (AMI) database may define up to 8 log files for AOC messages, each one capable of holding up to 100 messages. Each log has a DELETE LOG.

1 / X

MSG SEND LOG

1L

1301Z FREE TEXT

,

2L

1259Z WEATHER REQUES

,

3L

1259Z INITIALIZE

,

SENDING , , >

1R

,

SENT , >

2R

,

SENT , >

3R

4L

4R

5L

5R

6L

< RETURN

DELETE LOG

*

6R

EM170AOM140870B.DGN

HHMMZ

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Communication

REVISION 21

AOM-1502-003

MSG SEND LOG PAGE

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

MESSAGES RECEIVED The MSGS RCVD allows access to the MSG RCVD LOG pages. These pages list all uplink messages that have been received and viewed by the crew. Each log has a DELETE LOG.

MSG RCVD LOG

1250Z

1 / 1

1L

MESSAGE 1235Z

DISPLAYED FREE TEXT > DISPLAYED

1R

2L

MESSAGE

TWIP REQUEST >

2R

3L

3R

4L

4R

5L

5R

6L

< RETURN

DELETE LOG

*

6R

EM170AOM140885B.DGN

ACARS

AOM-1502-003

MSG RCVD LOG PAGE

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REVISION 21

Communication

Page 43

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

STATUS The STATUS option allows access to the STATUS MENU page, which may be used to obtain information about sensors and FMS displays.

ACARS

STATUS MENU

1L

< SENSORS

2L

< ASCB DATA

2R

3L

< PORT ACTIVITY

3R

1R

4L

4R

5L

5R

6L

< MAIN MENU

ATS MENU >

6R

EM170AOM140872A.DGN

NEW MSGS >

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Communication

REVISION 21

AOM-1502-003

STATUS MENU PAGE

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

SENSORS The SENSOR option allows access to the SENSOR STATUS page, which may be used to obtain information about sensors status, including doors, engine, fuel quantity and brakes sensors.

SENSOR STATUS

1L

ID/REG UV/PP-XJB

2L

DOORS < CLOSED

3L

BRAKE SET

4L

AIRBORNE NO /GND ICAO ADDR

5L

71000324

E190

ENGS ON NO

1R

FUEL QTY 9.6

2R

FLT PHASE ON GND

3R

OOOI STATE OUT XPDR ADDR

4R

71000324

5R

24APR08 6L

1535.5

< RETURN

6R

EM170AOM140873B.DGN

ACARS

AOM-1502-003

SENSORS STATUS PAGE

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REVISION 21

Communication

Page 45

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

ASCB DATA The ASCB DATA allows access to the ASCB DATA page, which may be used to obtain ASCB-related information.

1 / 2

FLIGHT ID ABC123 DEST APT

TIME 13:35:50 DATE

2L

SBSJ ORING APT

24APR08 FOB

2R

3L

SBCT GND SPEED

9.6 AIRSPEED

3R

4L

0.0 ALTITUDE

10.5 DIST TO GO

4R

5L

2949

1.3

5R

FUEL UNITS KILOGRAMS

6R

1L

6L

< RETURN

1R

EM170AOM140874B.DGN

ASCB DATA

ACARS

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Communication

REVISION 21

AOM-1502-003

ASCB DATA PAGE

ACARS 1L 2L 3L

ASCB DATA

MACH .017 HEADING

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

2 / 2

AIR TEMP +23.5 STATIC TEMP

274.6 DRIFT ANGLE .0 LATITUDE

+23.5 WIND SPEED

*****

1R 2R 3R 4R

5L

S25 31.91’ LONGITUDE W 49 10.52’

6L

< RETURN

6R

4L

5R EM170AOM140875A.DGN

AIRPLANE OPERATIONS MANUAL

AOM-1502-003

ASCB DATA PAGE

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REVISION 21

Communication

Page 47

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

PORT ACTIVITY The PORT ACTIVITY option allows access to the PORT ACTIVITY page, which may be used to obtain information about the state of operation for some systems.

ACARS

1 / 2

PORT ACTIVITY

MCDU 1

FMC 1

1L

ACTIVE

ACTIVE

2L

ACTIVE

ACTIVE NOT INSTLD

NOT INSTLD

3R

OFFSIDE CMU

CMC

4L

2R

MCDU 3

FMC 3

3L

1R

MCDU 2

FMC 2

ACTIVE

ACTIVE

4R

5L

ACTIVE

5R

6L

< RETURN

6R

EM170AOM141232A.DGN

PRINTER

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Communication

REVISION 21

AOM-1502-003

PORT ACTIVITY PAGE

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ACARS

FLIGHT INSTRUMENTS/COMM/NAV/FMS

2 / 2

PORT ACTIVITY

HFDR 1

VDR 1

NOT INSTLD

NOT INSTLD

2L

NOT INSTLD

NOT INSTLD INACTIVE

ACTIVE NOT INSTLD

NOT INSTLD

5L 6L

3R

SDU 2

CABIN 1

4L

2R

SDU 1

VDR 3

3L

1R

HFDR 2

VDR 2

4R 5R

< RETURN

6R

EM170AOM141233A.DGN

1L

AOM-1502-003

PORT ACTIVITY PAGE

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REVISION 21

Communication

Page 49

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

MAIN MENU LSK 6R

SYS MENU LSK 6L

INITIALIZE LSK 1L

DEP DELAY LSK 2L

FREE TEXT LSK 3L

WX REQUEST LSK 4L

NEW MSGS LSK 1R

VOX CONTACT LSK 5R

ENRT DELAY LSK 1L

ARR DELAY LSK 2L

FREE TEXT LSK 3L

WX REQUEST LSK 4L

NEW MSGS LSK 1R

ETA LSK 2R

DIVERSION LSK 3R

VOX CONTACT LSK 5R

FLT TIMES LSK 1L

ARR DELAY LSK 2L

FREE TEXT LSK 3L

POST FLT RPT LSK 4L

NEW MSGS LSK 1R

VOX CONTACT LSK 5R

SENSORS LSK 1L

ASCB DATA LSK 2L

PRE FLT LSK 1L

ATC MENU LSK 5R

ATS MENU LSK 6R

IN FLT LSK 2L

FREE TEXT LSK 4L

FLT TIMES LSK 5L

NEW MSGS LSK 1R

MSGS SENT LSK 2R

MSGS RCVD LSK 3R

STATUS LSK 4R PORT ACTIVITY LSK 3L

NEW MSGS LSK 1R

EM170AOM140480B.DGN

POST FLT LSK 3L

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Communication

REVISION 21

AOM-1502-003

AOC PAGES ACCESS

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIR TRAFFIC SERVICE (ATS) APPLICATIONS The Air Traffic Service (ATS) applications supported by the CMF are character-oriented applications that are designed to be transmitted through the ACARS network as a substitute for voice communication. The CMF supports the following ATS applications: – ATIS (Air Traffic Information Service) application: this application provides terminal information reports. The flight crew may send a downlink message requesting an uplink report that may be specific airport information or enroute information; – Pushback Clearance application: this application may be used to request pushback clearance from the ground system; – TWIP (Terminal Weather Information for Pilots): this application may be used to request weather reports from the ground system; – Expected Taxi Clearance application: this application may be used to request taxi clearance from the ground system; – Departure Clearance application: this application may be used to request departure clearance from the ground system; – Oceanic Clearance application: this application may be used to request oceanic clearance from ground system;

AOM-1502-003

– Flight System Message: this is an uplink only message. It is a supplementary message when the application requesting information does not have the necessary range of responses available to fully serve the request.

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REVISION 21

Communication

Page 51

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

ATS MENU The ATS MENU option on the ACARS MAIN MENU allows access to all ATS applications.

ATS MENU

1L

< TWIP REQ

NEW MSGS >

1R

2L

< ATIS REQ

ATS LOG >

2R

3L

< DCL REQ

3R

4L

< OCEANIC REQ

4R

5L

< PUSHBACK REQ

6L

< MAIN MENU

TAXI REQ > SYS MENU >

5R 6R

EM170AOM140876A.DGN

CMU

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Communication

REVISION 21

AOM-1502-003

ATS MENU PAGE

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

TWIP REQUEST The TWIP REQ option allows access to the TWIP REQUEST page, which may be used to send a downlink request for a TWIP uplink report.

CMU

TWIP REQUEST

AIRPORT

2L

SBCT

1R 2R

MODE

3L

* NORMAL

4L

* AUTO

5L

* TERMINATE

6L

3R

UPDATE

4R

AUTO

5R DATALINK

*

< RETURN

REQUEST

6R

EM170AOM140877A.DGN

1L

AOM-1502-003

TWIP REQUEST PAGE

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REVISION 21

Communication

Page 53

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

ATIS REQUEST The ATIS REQ option allows access to the ATIS REQUEST page, which may be used to send a downlink request for an ATIS uplink report.

1L

ATIS REQUEST

AIRPORT SBCT

1R

2L

* ARRIVAL

3L

* AUTO

UPDATE

3R

4L

* AUTO

ENROUTE

4R

5L

* TERMINATE

6L

DEPART

*

AUTO

5R DATALINK

*

< RETURN

2R

REQUEST

6R

EM170AOM140878A.DGN

CMU

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Communication

REVISION 21

AOM-1502-003

ATIS REQUEST PAGE

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

DEPARTURE CLEARANCE REQUEST The DCL REQ option allows access to the DCL REQUEST page, which may be used to send a downlink request for a departure clearance uplink message.

CMU

DCL REQUEST

FLT ID ABC123

DEP SBSJ

1R

STAND R11

2R

DEST SBCT

3R

4L

---------------------------------

4R

5L

--------------------------------DATALINK

5R

6L

< RETURN

6R

1L

ATIS 2L

O

3L

REQUEST

*

EM170AOM140879C.DGN

REMARKS

AOM-1502-003

DCL REQUEST PAGE

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REVISION 21

Communication

Page 55

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

OCEANIC CLEARANCE REQUEST The OCEANIC REQ option allows access to the OCEANIC CLX REQ page, which may be used to send a downlink request for an Oceanic Clearance uplink message.

CMU

OCEANIC CLX REQ

1L

ENTRY FIX 53 . 00 N 015 . 00W

2L

MACH .75

3L

ATC FACILITY EGCC

REQ TIME 01 : 10 ALTITUDE FL350 FLT ID ABC123

1R 2R 3R

4L

--------------------------------

4R

5L

-------------------------------DATALINK < RETURN REQUEST

5R

6L

*

6R

EM170AOM140880D.DGN

REMARKS

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Communication

REVISION 21

AOM-1502-003

OCEANIC CLX REQ PAGE

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

PUSHBACK CLEARANCE REQUEST The PUSHBACK REQ option allows access to the PUSHBACK CLX REQ page, which may be used to send a downlink request for a pushback clearance uplink message.

PUSHBACK CLX REQ

CMU 1L

FLT ID ABC123

2L

DEPT SBSJ

3L

STAND R 11

SKED

DAY/ TIME 12/12 : 55 DEST SBCT

1R 2R 3R

4L

--------------------------------

4R

5L

-------------------------------DATALINK < RETURN REQUEST

5R

6L

*

6R

EM170AOM140881C.DGN

REMARKS

AOM-1502-003

PUSHBACK CLX REQ PAGE

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REVISION 21

Communication

Page 57

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

TAXI CLEARANCE REQUEST The TAXI REQ option allows access to the TAXI CLX REQUEST page, which may be used to send a downlink request for a taxi clearance uplink message.

TAXI CLX REQUEST

CMU 1L

FLT ID ABC123

2L

DEPT SBSJ

3L

STAND R11

SKED

DAY/ TIME 15 / 16 : 35 DEST SBCT

1R 2R 3R

4L

--------------------------------

4R

5L

-------------------------------DATALINK < RETURN REQUEST

5R

6L

*

6R

EM170AOM140882C.DGN

REMARKS

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Communication

REVISION 21

AOM-1502-003

TAXI CLX REQUEST

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

ATS LOG The ATS LOG option allows access to the ATS LOG page. This page displays all uplink and downlink ATS messages.

CMU

ATS

LOG

1 / 1

1217Z KSLX

.

TWIP

.

1216Z 2L

TWIP

.

>

1R

SENT REQUEST

.

.

.

>

2R

3L

3R

4L

4R

5L

5R READY

6L

< RETURN

PRINT

ATS

LOG

*

6R

EM170AOM140884A.DGN

1L

DISPLAYED

ATS LOG PAGE

AOM-1502-003

There are also Flight System Message pages, which display unsolicited uplink messages providing additional information that the Departure and Oceanic Clearance uplink messages did not provide.

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REVISION 21

Communication

Page 59

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

ATC STAT MSG

CMU 1L

O113

2L

UA1234 ERROR

99O21O

3L

REVERT TO VOICE PROCEDURES

EGGX

1R

RCL REJECTED IN MESSAGE

2R 3R

4L

4R

5L 6L

< RETURN

PRINT

*

6R

EM170AOM140883B.DGN

5R READY

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Page 60

Communication

REVISION 21

AOM-1502-003

FLIGHT SYSTEM MESSAGE PAGE

AIRPLANE OPERATIONS MANUAL

MAIN MENU LSK 6L

ATS MENU LSK 6R

ATS LOG LSK 2R

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

NEW MSGS LSK 1R

TWIP REQ LSK 1L

TWIP Report

ATIS REQ LSK 2L

ATIS Report

DCL REQ LSK 3L

DCL Report

OCEANIC REQ LSK 4L

OCEANIC Report

PUSHBACK REQ LSK 5L

PUSHBACK Report

TAXI REQ LSK 5R

TAXI Report

ATC STAT MSG

EM170AOM141234A.DGN

SYS MENU LSK 6L

AOM-1502-003

ATS PAGES ACCESS

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REVISION 21

Communication

Page 61

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

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Communication

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

INERTIAL REFERENCE SYSTEM (IRS) The inertial system computes airplane position, ground speed, heading and attitude. The main component of the IRS is the Inertial Reference Unit (IRU), which interfaces with the Modular Avionic Unit (MAU), Global Positioning System (GPS) and the Air Data Computer (ADC). The IRU provides output data to the PFD, weather radar, Multifunction Control Display Unit (MCDU), Flight Management System (FMS) and reversionary panel. Primary source for the Captain′s PFD is the IRS 1 and for the First Officer′s PFD is IRS 2. In case of mode failure, power loss or loss of one IRU, the affected station can source select the other side station by means of the IRS reversionary panel button. An automatic power up (on ground) and alignment is provided. The alignment on ground (up to 17 min) must be performed with the airplane not in movement and position manually entered primarily via MCDU or obtained automatically from the GPS. In flight alignment is also possible to recover navigation capability using data from the GPS. The alignment time can be checked on the IRS STATUS PAGE 1/1 on the MCDU.

IRS I STATUS 1L

1 / 1

STATIONARY ALIGNMENT IAS POSITION

1R

2L

N09.59.9 E009.00.0

2R

3L

TIME TO NAV 0.9MIN

3R

4L

4R SET MAG HOG

AOM-1502-003

6L

POS SENSOR

5R 6R

EM170AOM140894A.DGN

---*

5L

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REVISION 21

Navigation

Page 1

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

IRU outputs digital data including the following: – Primary airplane attitude in pitch and roll; – Magnetic and true heading; – – – –

Body linear acceleration; Body angular rate; Inertial velocity; Navigation Position;

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Page 2

Navigation

REVISION 21

AOM-1502-003

– Wind Data; – Calculated data.

AIRPLANE OPERATIONS MANUAL

WEATHER RADAR

MCDU 1

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

ASCB

IRU 1 MAU 1

ADSP 1/ 2

MAU 2

PFD 1/ 2

ADSP 3/4

MAU 3

WEATHER RADAR

EM170AOM140126A.DGN

IRU 2

MCDU 2

IRS SCHEMATIC

The position can be entered on MCDU as follows: – Press NAV button on the MCDU to go to NAV INDEX page 1/2.

AOM-1502-003

NAV INDEX PAGE 1/2: – Press line select key 1L or 4L to go respectively to NAV IDENT or POS SENSORS page 1/1. NAV IDENT or POS SENSORS page 1/1: – Press line select key 6R to go to POSITION INIT page 1/1.

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REVISION 21

Navigation

Page 3

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

POSITION INIT PAGE 1/1: – The POSITION INIT page will list positions that can be line-selected for initialization of the FMS using the LOAD line select key. Any of the positions listed can be used for the initialization. The pilot may also enter the appropriate latitude/longitude or reference waypoint using the alphanumeric keys and pressing the line select key 2L.

POSITION INIT

1/ 1

LAST POS

N33 26.8 W112 01.5 LOAD KPHX REF

WPT

N33 26.2 W112 00.5 LOAD GPS 1 POS

POS SENSORS

EM170AOM140127.DGN

N33 26.9 W112 01.2 LOAD

FLT PLAN

MCDU POSITION INIT PAGE

GLOBAL POSITIONING SYSTEM (GPS) The Global Positioning System (GPS) is a satellite navigation sensor, which receives satellite signals from an active antenna in order to compute airplane position, velocity and time.

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Page 4

Navigation

REVISION 21

AOM-1502-003

The baseline GPS module is contained within MAU 1, located in the forward fuselage avionics bay. If the optional second GPS is installed, it is contained in MAU 3.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

TIME

IRU 1

POSITION

CLOCK

GPS 1 POSITION MAU 1

ELT/NAV

POSITION TIME VELOCITY

MCDU 1

POSITION TIME VELOCITY

IRU 2

POSITION

GPS 2 MAU 3

EM170AOM140319.DGN

MCDU 2

GPS SCHEMATIC

AOM-1502-003

The performance of both GPS system is monitored (GPS 1(2) STATUS 1/2 and 2/2) by selecting the MCDU NAV button and selecting the POS SENSOR pages.

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REVISION 21

Navigation

Page 5

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

GPS 1 STATUS 1L

N34

GPS POSITION

04.6

GRD SPD = 318 2L 3L

N302 KT

E68

W111

KT

1 / 2

08.2

1R

14999

2R

GPS ALT

MILES FR FMS POS

N0.1

W4.4

TOTAL 4.4

3R

4L

4R

5L

5R

6L

POS SENSORS

PRED RAIM

6R

EM170AOM140774B.DGN

FLIGHT INSTRUMENTS/COMM/NAV/FMS

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Navigation

REVISION 21

AOM-1502-003

GPS 1 STATUS PAGE 1/2

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

GPS altitude displayed is the World Geodetic System 1984 (WGS–84) height above the ellipsoid (geoid height + height above MSL). The GPS altitude is not relative to pressure altitude but is referenced to an earth–centered earth–fixed (ECEF) coordinate system. Pressure altitude is not relative to the same reference frame, but relative to the standard pressure or local pressure settings. Therefore, significant differences can be seen between GPS altitude and pressure altitude.

GPS ALTITUDE

HEIGHT ABOVE ELLIPSOID EARTH’S SURFACE

WGS−84 ELLIPSOID

EM170AOM140775A.DGN

HEIGHT ABOVE MSL

GPS ALTITUDE

AOM-1502-003

The GPS 1(2) STATUS PAGE 2/2 displays information about receiver autonomous integrity monitor (RAIM), figure of merit (FOM), horizontal dilution of precision (HDOP), vertical dilution of precision (VDOP), time (UTC) and date, operating mode and satellites tracked.

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REVISION 21

Navigation

Page 7

FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

GPS 1 STATUS 1L 2L 3L

2 / 2

RAIM = 0.10 NM FOM = 0.05 NM HDOP = 2 UTC 1730 VDOP = 2 DATE 21AUG94 MODE = NAVIGATION SATELLITES TRACKED = 7

1R 2R 3R

4L

4R

5L

5R

6L

POS SENSORS

PRED RAIM

6R

EM170AOM140776B.DGN

SYSTEMS DESCRIPTION

GPS 1 STATUS PAGE 2/2

RAIM and FOM indicate current uncertainty of position expressed in nautical miles. HDOP and VDOP are numbers that rate current satellite geometry in the horizontal and vertical axis with 1 being the best geometry. Normally, HDOP and VDOP numbers are below 10. The fifth line displays the operational mode of the GPS. Possible operational modes are displayed as SELF–TEST, INITIALIZATION, ACQUISITION, NAVIGATION, DIFFERENTIAL, ALTITUDE AIDING, VELOCITY AIDING, FAILED. The acquisition mode is used to acquire satellites after power is applied. The GPS tracks four satellites to acquire its position. After being in the navigation mode, altitude aiding is the mode entered when fewer than four satellites are being tracked. In this mode, the GPS uses altitude from the digital air data computer (ADS) to aid in determining position.

The last line of the GPS STATUS page indicates the number of satellites that are being tracked and used by the GPS.

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Navigation

REVISION 21

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NOTE: If the GPS is operated inside a hangar or other areas where signals cannot be received, the GPS can detect this as a failure. In this case, cycling the power is necessary to restart the GPS.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

Any faults within the GPS module will be reported on the MCDU. The Message (“MSG”) indicator on the PFD will illuminate, and “GPS 1 FAILED” or “GPS 2 FAILED”, as appropriate, will be displayed in the scratchpad area.

RECEIVER AUTONOMOUS INTEGRITY MONITOR (RAIM) The GPS module executes a RAIM test to insure the integrity of the data transmitted by the satellite. RAIM is a software function that supplies an alert to the cockpit when the integrity limit exceeds a flight phase dependant threshold. The GPS has RAIM outputs for the current position and time in the form of horizontal and vertical integrity limit (HIL and VIL) at some future place and time. In order to compute RAIM, the GPS must have a minimum of five satellite signals. The FMS does not accept GPS data unless a valid RAIM figure is available. The FMS produces an alert for the flight crew on the MCDU when the GPS has lost integrity: “GPS RAIM ABOVE LIMITS”. Also an alert is generated by the FMS when the integrity will exceed the limit: “RAIM WILL EXCEED LIMIT”. A third alert will be generated by the FMS when RAIM is not available: “GPS RAIM UNAVAILABLE”.

PREDICTIVE RAIM (PRAIM) The GPS also has a predictive RAIM function that provides the following types of RAIM predictions: Destination and Alternate waypoint (Pilot Select). Predictive RAIM uses an almanac function that is updated whenever the GPS is tracking satellites. Satellites can be manually deselected or enabled for destination and alternate waypoint prediction. This function calculates whether the satellite geometry is acceptable for approach at the expected destination at the estimated time of arrival (ETA). On ground, in order for an ETA to be computed, the pilot must enter an ETD (ORIGIN/ETD) in line select key 1L on the initial FLT PLAN page.

AOM-1502-003

The predictive RAIM page is accessed by selecting the PRED RAIM prompt from any GPS STATUS page. When selected, the PREDICTIVE RAIM page is displayed. YES indicates RAIM is predicted to be within approach criteria. NO indicates RAIM is predicted to be unacceptable or unavailable.

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FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

PREDICTIVE RAIM 1L 2L

1 / 1

DEST

FROM GPS 1 PILOT SEL

KLAX

KPHX

0953Z

< -TIME- >

1521Z

YES

< -RAIM- >

NO

1R 2R

3L

3R

4L

4R

5L

5R

6L

POS SENSORS

RETURN

6R

EM170AOM140777B.DGN

SYSTEMS DESCRIPTION

PREDICTIVE RAIM PAGE

The FMS uses the high priority GPS for predictive RAIM. The priority order for FMS 1 is GPS 1, GPS 2. The priority order for FMS 2 is GPS 2, GPS 1. If only a single GPS is available, both FMSs use it for predictive RAIM. Should the GPS fail or the interface between the FMS and GPS not work properly, the FMS displays the message PREDICTIVE RAIM UNAVAILABLE on the PREDICTIVE RAIM page. Predictive RAIM is calculated using GPS almanac information. The almanac within the GPS is automatically updated whenever the GPS is on and tracking satellites. The almanac within the GPS is set invalid if it is older than 3.5 days. Should this occur, the message ALMANAC EXPIRED is displayed on the PREDICTIVE RAIM page. The almanac takes approximately 12–25 minutes to update once the GPS is tracking satellites. RAIM predictions are not possible with an expired almanac.

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REVISION 21

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Selecting the DEST prompt from the PREDICTIVE RAIM page displays DESTINATION RAIM page 1/2.

AIRPLANE OPERATIONS MANUAL

DESTINATION RAIM

2L 3L

FLIGHT INSTRUMENTS/COMM/NAV/FMS

1 / 2

RAIM@TIME

KLAX

NO 0953Z

RAIM@TIME

RAIM@TIME

YES 0938Z

NO 0958Z

YES 0943Z

NO 1003Z

NO

NO 1008Z

0948Z

1R 2R 3R

4L

4R

5L

5R

6L

POS SENSORS

PRED RAIM

6R

EM170AOM140780B.DGN

PLACE 1L

SYSTEMS DESCRIPTION

DESTINATION RAIM PAGE 1/2

AOM-1502-003

DESTINATION RAIM page 2/2 supports satellite deselection. From this page, the pilot selects which GPS satellites are to be excluded from the DESTINATION RAIM predictions. The pilot enters the Pseudo–Random Noise (PRN) code for the satellite that is scheduled to be out of service according to published GPS NOTAMs.

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FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

DESTINATION RAIM

2 / 2

SATELLITE DESELECT BY PRN NUMBER

1L

1R

2L

4

--

2R

3L

--

--

3R

4L

4R

5L

5R

6L

POS SENSORS

PRED RAIM

6R

EM170AOM140781B.DGN

SYSTEMS DESCRIPTION

DESTINATION RAIM PAGE 2/2

The satellite deselection can also be done in the PILOT SELECT RAIM page 2/2.

RADIO NAVIGATION SYSTEM The radio navigation equipment is located in the Modular Radio Cabinet (MRC). The interface with the audio is through the audio/microphone bus, and with the MCDU/PFD/MFD through the ASCB. The main components are: – Very-high-frequency Omni-directional Range (VOR). – Automatic Direction Finder (ADF). – Distance Measuring Equipment (DME). – Instrument Landing System (ILS). The MCDU is the primary means for radio tuning (RADIO PAGE and PROGRESS PAGE), while the CCD and PFD are the secondary means.

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– Transponder System (XPDR).

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

A tuning backup is available in MCDU 2 in case of loss of both MAUs. If the audio bus is lost there are audio backups also.

VOR/ILS RADIO PAGE 1/2: – The frequency is changed using either the scratchpad or the tuning knob on the MCDU. – To change a frequency value with the scratchpad, use the keypad to enter the new frequency value, and then push the LSK next to the frequency to be modified. This transfers the value from the scratchpad to the selected frequency. – To change a frequency value with the MCDU tuning knob, the standby frequency must be boxed prior to pressing the LSK 4L/4R. Tune the frequency with the cursor around the standby frequency and the swap icon displayed, push the LSK to swap the standby and active frequencies.

RADIO SQ

COM1

SQ

1 / 2 COM2

TX

123 . 200 118 . 600 NAV1 114 . 80 DME H PXR 115 . 60

FMS AUTO

FMS AUTO

116 . 8 W123456

TCAS/XPDR

XPDR 1471 IDENT IDENT

TA/RA

EM170AOM140325B.DGN

STBY

NAV2 117 . 4

RADIO PAGE 1/2

AOM-1502-003

PROGRESS PAGE 1/3

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SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

– It is possible to tune the NAV radio using either the identifier or the frequency. – Enter the identifier or the frequency value into the scratchpad and then push the LSK 5L or 5R. The FMS tunes the NAV radio on the PROGRESS PAGE.

PROGRESS 1L

PAYSO

21.8

00+05

2L

ABQ

282

3L

KMS

1076

4L 5L 6L

NEXT DEST

1/3

ETE

FUEL

10.0

1R

00+56

9.0

2R

02+38

7.0

3R

DMEDME RNP = 2.00 EPU = 8.23

TFD 114.80 NAV 1

INW 112.60

NAV 2

4R 5R 6R

EM170AOM140895A.DGN

DIST

TO

NAV PAGE 1/1: – Press the respective standby frequency twice if it is not boxed, otherwise press once, to go to NAV page 1. – Pushing LSK 1L swaps the active and preset frequencies (when the cursor is on field 2L). – On the NAV page is possible to capture a frequency tuned in memory. Press 4L to box the memory tune and use the tuning knob to cycle the stored frequencies. Press the active frequency to capture the selected memory tune.

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REVISION 21

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– Press LSK 2R to cycle DME hold on or off.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– Press LSK 5R to toggle the FMS autotune feature ON and OFF for the selected VHF NAV radio. Autotune is indicated by the magenta NAV active frequency on the PFD and it can be only selected ON when the primary navigation source is FMS.

1 / 1

NAV I ACTIVE

2L 3L 4L

114.80 PRESET 117.40

1R

DME HOLD ON OFF

MEN TUNE 1 114.80

TEST ON OFF FMS AUTO

TFD

5L 6L

ON MEMORY

OFF

RADIO 1 / 2

2R 3R 4R 5R 6R

EM170AOM140896A.DGN

1L

The VOR/ILS frequency selection through the CCD is as follows: – Select the PFD through the CCD. The left and right format location buttons select respectively pilot’s and copilot’s PFDs. – Through the touch pad move the cursor to the navigation frequency window. – Tune the standby frequency through the tuning knob.

AOM-1502-003

– Activate the standby frequency by pressing the enter key.

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Page 15

24

RNP 1O.1

12 15

5

21

COM1 18O 55 119 4O

E

VOR1 VOR2

AIRPLANE OPERATIONS MANUAL

W

FLIGHT INSTRUMENTS/COMM/NAV/FMS

NAV1 115 6O 119 O3

EM170AOM140893A.DGN

SYSTEMS DESCRIPTION

ADF RADIO PAGE 2/2: The frequency is changed using either the scratchpad or the tuning knob on the MCDU. To change a frequency value with the scratchpad, use the keypad to enter the new frequency value, and then push the LSK next to the frequency to be modified. This transfers the value from the scratchpad to the selected frequency.

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REVISION 21

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To change a frequency value with the MCDU tuning knob, the standby frequency must be boxed prior to pressing the LSK 4L/4R. Tune the frequency. With the cursor around the standby frequency and the swap icon displayed, push the LSK to swap the standby and active frequencies.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

RADIO

2 / 2

SQ

ADF1

ADF2

230 . 0

235 . 5

365 . 0

360 . 0

HF1 8 . 8550

UV

10 . 0960 EM170AOM140326.DGN

COM3 121 . 7 118 . 5

ADF PAGE 1/1: – Press the respective standby frequency twice if it is not boxed, otherwise press once, to go to ADF page 1. – Pushing LSK 1L swaps the active and preset frequencies (when the cursor is on field 2L). – On the ADF page is possible to capture a frequency tuned in memory. Press LSK 4L to box the memory tune and use the tuning knob to cycle the stored frequencies. Press the active frequency to capture the selected memory tune.

AOM-1502-003

– Press LSK 5R to cycle ADF mode: ADF - receives static signal and computes bearing to station. ANT - receives ADF static signal only. BFO - adds a beat frequency oscillation for reception of signals. VOICE - permits voice to be received and transmitted over radio speakers.

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SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

1 / 1

ADF 1 ACTIVE

2L 3L 4L

1299.5 PRESET 600.0 MEN TUNE 3

SDL

1R 2R

NDB

TEST

224.0

5L

ADF

6L

MEMORY

ON

3R

OFF MODE

4R

ANTENNA BFO VOICE

5R

RADIO 2 / 2

6R

EM170AOM140897A.DGN

1L

NAV/ADF MEMORY PAGES:

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REVISION 21

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– On the NAV/ADF MEMORY pages it is possible to capture a frequency tuned in memory or store a frequency/identification. To capture a frequency press the respective memory frequency to box it and press 1L to activate the frequency. To store a frequency or its identification use the alphanumeric keys and press the respective memory line select key. Additionally the frequency can also be stored pressing the receptive memory line select key and rotating the tuning knob.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

NAV MEMORY

1 / 2

NAV 1

2L 3L

108.70 1 - TFD 114.80 2 - MEMORY

1R

MEMORY - 4 2R

MEMORY - 5

116.50 3 - MEMORY

3R

MEMORY - 6

4L

4R

5L

NAVA 1

5R

6L

RADIO 1 / 2

6R

EM170AOM140898A.DGN

1L

TRANSPONDER The transponders are located in the Modular Radio Cabinet (MRC). Each transponder provides conventional ATC functions. The dual Mode S XPDR system enables secondary surveillance by transmission of airplane identification information, altitude (barometric) and coded message data to ATC ground stations and TCAS installations on other airplane. The transponder code is entered/activated through the MCDU. A tuning backup is available in MCDU 2 in case of loss of both MAUs.

AOM-1502-003

The transponder receives and transmits altitude information from the ADS of the coupled side. Flight ID information is provided by the FMS, or it can be entered by the pilot. The XPDR also receives the ICAO address programmed into the airplane personality module (APM) and the pilot enters the squawk code.

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

!Airplanes equipped with Enhanced Transponder or ADS-B Out Radar Area

The installed transponder system is able to respond to interrogations in Modes A, C and S. It is fully compliant with the requirements in EU 1207/2011, Annex II, Part A and Part C. "

The system is not capable to transmit the Track Angle Rate parameter. The following table presents the XPDR and TCAS modes of operation:

STANDBY ALT-OFF ALT-ON

XPDR Modes None A and S A, C and S

TA

A, C and S

Yes

TA/RA

A, C and S

Yes

MODE

Replies Altitude No No Yes

TCAS Disabled Disabled Disabled Traffic Advisory only Traffic Advisory/ Resolution Advisory

On ground, and in any mode except Standby, the XPDR only replies to discretely addressed mode S interrogations. The replies in mode A and mode C will occur when the airplane is airborne and the XPDR/TCAS mode is not set to Standby or ALT-OFF. The flight crew may enter the transponder code on the MCDU as follows: – Press radio button on the MCDU to go to RADIO page 1/2. RADIO PAGE 1/2: – On RADIO page 1/2 it is possible to enter the transponder code. The entering can be accomplished using the tuning knob or the numeric buttons. If the tuning knob will be used the transponder field must be boxed prior to pressing its respective line select key. In case of the numeric keys, enter the transponder code and press the respective line select key. – Press LSK 5L to go to TCAS/XPDR page 1/2.

– Press LSK 6R to select identification mode.

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REVISION 21

AOM-1502-003

– Press LSK 6L to alternately select STBY or the selected active mode. The active mode can be set on TCAS/XPDR page 2/2.

AIRPLANE OPERATIONS MANUAL

RADIO SQ

COM1

SQ

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

1 / 2 COM2

TX

123 . 200 118 . 600 FMS AUTO

FMS AUTO

116 . 8 W123456

TCAS/XPDR STBY

NAV2 117 . 4

XPDR 1471 IDENT IDENT

TA/RA

EM170AOM140325B.DGN

NAV1 114 . 80 DME H PXR 115 . 60

TCAS/XPDR PAGE 1/2: – On TCAS/XPDR page 1/2 is possible to enter and activate the transponder code. The entering can be accomplish using the tuning knob or the numeric buttons. If the tuning knob will be used, the standby code must be boxed prior to pressing its respective line select key. In case of the numeric keys use, enter the standby code and press the respective line select key. To activate the standby code, press the respective active code. – Press LSK 5L to cycle the transponder selection 1 or 2.

AOM-1502-003

– Press NEXT button to go to TCAS/XPDR page 2/2.

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

1 / 2

TCAS/XPDR

2L

PRESSURE ALT

1471 PRESET 1200

41000

1R

FLT

ID

N123

3L 4L 5L

2R 3R 4R

XPDR SEL XPDR 1 XPDR 2

IDENT RADIO 1 / 2

6L

5R 6R

EM170AOM140899A.DGN

1L

ACTIVE

TCAS/XPDR PAGE 2/2:

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REVISION 21

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– Press LSK 1L to cycle the transponder mode: TA/RA. TA. ALT-ON. ALT-OFF.

AIRPLANE OPERATIONS MANUAL

TCAS/XPOR

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

2 / 2

TCAB/XPDR MIDE

2L

*

TA/RA TR ALT-ON ALT-OFF ALT RANGE

1R 2R

3L

3R

4L

4R

5L

5R RADIO 1 / 2

6L

AUTOMATIC DEPENDENT BROADCAST (ADS-B) OUT

6R

SURVEILLANCE

EM170AOM140900A.DGN

1L

-

!Airplanes equipped with ADS-B Out

ADS-B Out is a function of the transponder that allows broadcast of information such as airplane identification, position, altitude and velocity. It is enabled through the Airplane Personality Module (APM). Transponder Mode S 1090 Extended Squitter acquires necessary data to support ADS-B Out over the existing Network Interface Module (MRC NIM) and GPS units.

AOM-1502-003

The use of ADS-B provides accurate information and frequent updates to airspace users and controllers. It supports improved use of airspace, reduced ceiling/visibility restrictions, improved surface surveillance, and enhanced safety through the conflict management. The ADS-B Out is automatically turned on during airplane power up. The ADS-B Out is automatically turned off after airplane power down or after transponder turned off. When the ADS-B Out is deselected the XPDR operates as Mode S Enhanced Transponder.

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

An additional label ADS-B is added to the MCDU RADIO page 1/2. The following color code for the ADS-B label should be observed: – Green: ADS-B is selected ON, ADS-B information is valid and XPDR is ON. – White: ADS-B is selected ON, ADS-B information is valid and XPDR is in STBY. – Amber: ADS-B is selected ON and ADS-B information is invalid. Information is valid when the XPDR accepts the GPS information (number of satellites tracked, accuracy and integrity) as acceptable for the ADS-B function. Therefore, flight crew must be aware that after power up, with ADS-B selected ON, the ADS-B label is displayed in amber while the GPS is acquiring satellites data. The label ADS-B OFF is displayed in white when ADS-B is selected OFF.

RADIO

1 / 2

123 . 200

COM2 123 . 200

118 . 600

118 . 600

NAV1 114 . 80

NAV2 117 . 40

115 . 60

116 . 80

TCAS/XPDR STBY

W123456 ADS - B

XPDR1 1471 IDENT IDENT

TA/RA

EM170AOM141078A.DGN

SQ

COM1

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REVISION 21

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The ADS-B Out function may be manually selected ON or OFF on the MCDU TCAS/XPDR page 1/2.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

1 / 2

TCAS/XPDR 1L 2L

ACTIVE

PRESSURE ALT

1471 PRESET 1200

41000

1R

FLT

ID N123

3L

2R 3R

TEST

5L

ON OFF

XPDR SEL XPDR 1 XPDR 2 ADS - B

6L

IDENT RADIO 1 / 2

ON OFF

4R 5R 6R

EM170AOM141079B.DGN

4L

"

MISSED APPROACH PREVIEW

AOM-1502-003

The MFDs MAP menu has the option to select the preview of the Missed Approach procedure on the MFD. The presentation is in cyan and follows the flight plan sequence.

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

WEATHER RADAR SYSTEM The airplane can be equipped with WU-660 or WU-880 weather radar system models. The system is designed primarily for detection and analysis of the weather during flight and for ground mapping. The MFD handles the display of radar data and, in addition provides virtual controllers for weather radar control. Weather data is displayed on both MFDs, as well as on the PFDs. When operating in ground mapping prominent landmarks are displayed which allow identification of coastlines, hilly or mountainous regions, cities or even, large structures. The weather radar system consists of an integrated Receiver Transmitter Antenna unit (RTA) and two virtual weather radar controllers. The RTA is mounted in the nose of the airplane, whereas the virtual controllers consist of the CCDs and the weather mode information displayed on the MFDs below the weather information.

CCD 2

CCD 1

PFD 1

MFD 1

MFD 2

PFD 2

IRS VIRTUAL WX CONTROLLER

VIRTUAL WX CONTROLLER

ASCB

MAU 1

MAU 3 GUIDANCE PANEL

EM170AOM140130.DGN

RTA

Display of weather data is available on the MFDs and PFDs. Selection of weather data display is accomplished via CCD actuating in the MFD using a soft key to select MAP menu. This act will enable weather

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REVISION 21

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WEATHER RADAR SCHEMATIC

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

information and virtual controller on the MFD. Five modes and ten functions are available. Each one will be discussed in the following sections.

WX RADAR MODES RADAR WEATHER DETECTION MODE (WX) The WX mode is used to detect areas of severe weather. This will allow the pilots to avoid areas of dangerous weather conditions and possible turbulence. If WX is selected before the initial RTA warm-up period is over (approximately 90s), WAIT is displayed in the mode field. In the wait mode, the transmitter and antenna scan are inhibited.

GROUND MAPPING MODE (GMAP) This mode is used to alert the flight crew about hazards caused by ground targets. This is especially useful in areas of rapidly changing terrain, such as hilly mountainous areas. The selection of preset gain will generally provide the desired mapping display, however the gain can also be manually operated. It is possible to have one pilot working the GMAP while the other is using the WX mode.

AOM-1502-003

It is not intended to be used or relied for ground proximity warning.

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

STANDBY (STBY)/FORCED STANDBY (FSBY) MODE The weather radar remains in a ready state, with the antenna scan motionless and stowed in a tilt-up position. In addition, the transmitter is inhibited and the display memory is erased. The following table shows the RTA modes for each WX radar configuration: LEFT RIGHT CONTROLLER CONTROLLER

LEFT SIDE

RIGHT SIDE

RTA MODE

OFF

OFF

OFF

OFF

OFF

Standby

Slave Standby

Standby

Standby

Standby

OFF

Standby

Slave Standby

Standby

OFF

ON

Slave ON

ON

ON

OFF

ON

OFF

ON

Slave ON

ON

Standby

ON

Standby

ON

ON

ON

Standby

ON

Standby

ON

ON

ON

ON

ON

ON

Standby

Standby

Standby

Standby

Standby

FSBY is displayed when the airplane is on the ground. The RTA is in forced standby mode when the airplane is on the ground, the transmitter and antenna scan are both inhibited, display memory is erased, and FSBY is displayed in the mode field. Overriding the forced standby requires that both pilots select the FSBY OVRD menu item on the respective weather controllers or one pilot selects the Antenna Stabilization checkbox (STAB OFF) 4 times in less than 3 seconds enabling the WX mode on ground.

OFF MODE

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REVISION 21

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Turns the radar off, provided OFF is selected on both virtual controllers. The system is no longer radiating power and the antenna is stowed.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

SLAVE MODE One controller is in OFF position whereas the other controller is in an operating mode. The operating one is in control of both sweeps.

TURBULENCE DETECTION (TURB) FUNCTION The radar processes return signals in order to determine if a turbulence signature is present. Areas of moderate, severe, or extreme turbulence are displayed in soft white. TURB may only be engaged in the WX mode and at selected ranges of 50 NM or less. NOTE: – It may occur that the Turbulence function annunciation in MFD and PFD to remain displayed for ranges above 50 NM even though the function is deactivated. – Range selections of 200 NM or greater always clear Turbulence function annunciation.

ANTENNA STABILIZATION FUNCTION The antenna is stabilized in pitch and roll using attitude information from the IRU. Momentarily selecting the STAB OFF checkbox disables antenna stabilization and causes an amber STAB to be displayed.

RECEIVER GAIN (GAIN) FUNCTION The GAIN control varies the RTA receiver gain. There are two modes: variable and calibrated. The normal preset is calibrated mode and is used for weather avoidance. The system will be forced into calibrated gain when RCT or TGT are selected. The variable mode is useful for additional weather analysis and for ground mapping. In WX mode, variable gain can increase receiver sensitivity over the calibrated level to show weak targets or it can be reduced below the calibrated level to eliminate weak returns.

RANGE FUNCTION

AOM-1502-003

The range can be manually set (CCD) to a desirable value (10 NM, 25 NM, 50 NM, 100 NM, 200 NM, 300 NM). The label OVRG is shown whenever the Map range is greater than 300 NM.

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AIRPLANE OPERATIONS MANUAL

TARGET ALERT (TGT) FUNCTION The TGT function monitors for weather beyond the selected range and 7.5° on each side of the airplane heading. If such weather is detected within the monitored heading, outside the selected range until a range of 200 NM , the TGT annunciation changes from a green-armed condition to an amber alert condition on the MFD. This annunciation advises the flight crew that potentially hazardous weather lies directly in front and outside of the selected range. When this warning is received, the flight crew should select longer ranges to view the questionable target. Note that TGT is inactive when hazards are within the selected range. Selecting the TGT function forces the system to preset gain and turns off variable gain mode. Selections of ranges of 200 NM or greater automatically turns off TGT function and allows variable gain mode. It can only be selected in the WX mode. NOTE: – The TGT annunciation on MFD may occur when the range is increased to 200 NM or greater, even though the function is deactivated. – In such cases, system logic follows the TGT function annunciation, and gain is automatically preset. – Selection of 1000 NM range always clears TGT annunciation.

SECTOR SCAN (SECT) FUNCTION The normal radar sweep is ± 60 degrees from the airplane nose, at a rate of 12 sweeps per minute. Selecting the SECT pushbutton reduces the angle of sweep to ± 30 degrees and increases the sweep rate to 24 sweeps per minute.

TILT FUNCTION

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The inner knob on the CCD provides tilt control giving the pilot manual control of the antenna tilt angle. The CCD inner knob is a dedicated tilt knob if VAR Gain is not active. Tilt can be varied between 15 degrees up (clockwise rotation) and 15 degrees down (counterclockwise rotation).

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

ALTITUDE COMPENSATED TILT (ACT) FUNCTION Automatically adjusts the antenna tilt according to the altitude and selected range. The TILT knob can be used for fixed offset corrections of up to 2.0 degrees.

RAIN ECHO ATTENUATION TECHNIQUE (REACT) FUNCTION

COMPENSATION

Used in WX mode to compensate for attenuation of the radar signal as it passes through a storm. It does this by increasing the gain of the receiver as weather is detected. The cyan field indicates areas where further compensation is not possible. This is a warning indicating that attenuation is hiding possible severe weather and should be considered dangerous. The REACT compensation is active in all modes except GMAP mode. The REACT compensation can be active in all modes except GMAP mode.

TEST FUNCTION The test function is selected on MCDU avionics test page. The test is used to select a special test pattern to allow verification of system operation. If fault codes are detected they will be displayed at the same location where tilt angle is displayed in the Weather mode field.

AOM-1502-003

NOTE: Output power is radiated in test mode, unless the WX radar is in FSBY mode.

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REVISION 21

Navigation

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

FLIGHT MANAGEMENT SYSTEM The Flight Management System (FMS) manages navigation sensors to produce the airplane position. The system provides data for the cockpit displays and flight control system. The FMS serves as aid to flight planning, navigation, performance, database and redundancy management. The system may be installed in a single or dual configuration. For additional information on functions and operation, refer to the manufacturer’s manual. For additional information on limitations, refer to the Supplemental Flight Management System Limitations of this manual (Chapter 2). The FMS 1 and 2 reside respectively in MAU 2 and MAU 3. The FMS interfaces with the followings systems and equipment: • GPS: the FMS uses inputs from the GPS to calculate airplane position and perform navigation functions. • IRS: the FMS uses inputs from the IRS to obtain airplane position and perform navigation functions.

• • •

MFD and PFD: the FMS provides data for display navigation guidance on the PFD and navigation map data on the MFD. VOR/DME: the FMS uses inputs from the VOR/DME to perform navigation functions. MCDU: the Multifunction Control Display Unit, located on the control pedestal, provides control functions management and operating modes for proper FMS operation. It is the interface between the FMS and the flight crew.

FLIGHT PLANNING In general, flight plans may be divided in four categories: active, stored, lateral or vertical.

ACTIVE FLIGHT PLAN

AOM-1502-003

This is the flight plan currently being flown. The active flight plan can be entered waypoint by waypoint, loaded from an external source, or recalled from storage. At a minimum, active flight plans must contain a “FROM” waypoint (possibly the origin), a “TO” waypoint, and a destination. A flight plan is considered “closed” when the last waypoint is the destination.

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STORED FLIGHT PLAN The flight plan is stored when it is saved in the computer’s memory and can be recalled later and become an active flight plan. When entering a flight plan to store, the flight plan must have a departure and destination airport, and both must be database waypoints. When recalling a flight plan, entering the name of the flight plan results in the flight plan becoming active. If the name of the flight plan can not be found, the flight crew can enter the departure and destination airports. If any are found, the FLIGHT PLN LIST page is displayed to allow selection of a flight plan.

LATERAL FLIGHT PLAN The lateral flight plan begins at the origin. The default origin in the active flight plan is the nearest airport to the present aircraft position that is within three miles, but it may be changed by the flight crew. The flight plan ends at the destination, which must be entered by the pilot as there is no default destination. The flight plan is built by inserting waypoints or strings of waypoints between the departure and destination airports. Examples of strings of waypoints are standard instrument departure procedures (SIDs), airways, standard terminal arrival procedures (STARs), and approach transitions.

VERTICAL FLIGHT PLAN Vertical navigation (VNAV) is a FMS function that calculates a vertical profile, based on performance initialization data, and defines vertical modes to the FGCS. Once the FMS has generated a vertical profile, VNAV information can be accessed any time via PROG < PROGRESS 2/3 < VNAV DATA. Moreover, FMS VNAV sends inputs for display on the PFD and MFD.

GENERAL RULES FOR VNAV OPERATION – In order to use the VNAV function, the FMS Performance Initialization must be completed and confirmed. – VNAV never exceeds the set altitude in the Altitude Selector.

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– The airplane climbs whenever the FMS VNAV is in the climb phase, and the altitude set in the Altitude Selector is above the present airplane altitude.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– The airplane descends whenever the FMS VNAV is in the descent phase and the altitude set in the Altitude Selector is below the present airplane altitude. – A Vertical Track Alert (VTA) is issued 60 seconds before the FMS commands a climb or a descent, or 1000 ft before the level off altitude. There is no VTA if leveling-off is based on the altitude set in the Altitude Selector. – VNAV, whenever existing constraints allows it, defines constant climb or descent paths.

NORMAL OPERATION Climb: VNAV performs all climb profiles contained in the VFLCH mode. If the FMS levels-off at an altitude constraint defined over a waypoint, it resumes the climb automatically upon sequencing the waypoint. If the FMS levels-off at an altitude set on the Altitude Pre Selector, after setting the Altitude Pre Selector to a higher altitude, the FLCH button must be pressed on the guidance panel in order for the VNAV to transition from VALT to VFLCH. Cruise: The FMS will transition to cruise phase when reaching the initial cruise altitude set in the PERF INIT page. If the airplane levels at an altitude lower than the initial cruise altitude, the FMS does not transition to cruise. If the ALT SEL is set to an altitude higher than the FMS cruise altitude, after few seconds, the cruise altitude in the PERF INIT page is reset to match with the ALT SEL selection. NOTE: To reset the FMS cruise altitude to an altitude lower than the current FMS cruise altitude, it may be necessary to delete the current cruise altitude in the FMS CRUISE PAGE 1/1 prior to insert the new altitude. To leave cruise level to either climb or descent, the altitude selector must be set to an altitude higher or lower than the present altitude and a vertical DIRECT-TO or VFLCH must be commanded. When TCS is used to exit a leveled altitude, the command logic is to return to the original altitude when the change is less than 50 ft. For changes greater than 50 ft, the new achieved altitude is maintained.

AOM-1502-003

TOD: The Top of Descent is calculated using the values inserted in the PERF INIT page and is displayed in the VNAV page and on the PFD/MFD.

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!MAU load 21.2 and on OR POST-MOD SB 170-31-0028

The DES NOW prompt is displayed on the FMS DESCENT, FLIGHT PLAN and ROUTE pages providing an easy command to start the descent when the airplane is 50 NM or less from the calculated TOD. When selected, the Flight Director commands the airplane to descent according to the airplane position relative to the predicted TOD. – Early Descent: selecting the DES NOW prompt before the TOD is reached enables the Early Descent mode, where the FD commands a 1000 FPM descent up to the point where the planned descent path or the next altitude constraint is intercepted. – Late Descent: selecting the DES NOW prompt after the planned TOD is reached enables the Late Descent mode, where the FD commands a descent angle 1.5° steeper than the planned descent angle to intercept the planned path. NOTE: If this descent angle is not enough to intercept the previously planned path a UNABLE PATH INTERCEPT scratchpad message is displayed. "

Descent: One minute prior to the TOD, a vertical track alert is given. When reaching the TOD, the FMS automatically starts the descent in VFLCH or VPATH if the altitude selector is set to a lower altitude. – VFLCH Descents – The descent is in VFLCH mode if there is no altitude constraint down to 1500 ft/10 NM prior to the destination airport. VFLCH also complies with the speed/altitude limit. After an intermediate level-off at the altitude selector altitude, the next descent must be initiated selecting the altitude selector to a lower altitude and pressing FLCH on the GP.

Vertical DIRECT-TO: This operation is similar to the lateral DIRECT-TO. It is performed selecting the desired altitude from the scratch pad to the line adjacent to the desired waypoint.

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– VPATH Descents – The descent is in VPATH anytime an altitude constraint exists in the descent path and the airplane is within the capture logic of VPATH mode. FMS must be the navigation source and LNAV must be engaged in order the VPATH to become available. When the FMS passes through the last altitude constraint waypoint, it reverts to VFLCH to complete the descent. During VPATH descents, significant modifications of the flight plan may result the VPATH mode to drop to FPA mode.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

!MAU load 21.2 and on OR POST-MOD SB 170-31-0028

The FMS calculates the predicted altitudes at which the airplane should pass the waypoints and then applies the altitude constraints to these altitudes, if necessary. "

VNAV and HOLDING PATTERNS: The following applies: – If descending on VFLCH and a holding pattern is entered, the active mode remains VFLCH; – If a PPOS holding is entered while in VPATH, the active mode changes to VFLCH; – If a hold is entered while in VPATH descent, the command changes to VALT.

FMS SPEED PLAN FMS Speed Plan is a function that calculates speeds for a specified navigation based on performance initialization data, and sends speed targets to the FGCS. Once the performance is initialized and confirmed, FMS speeds can be accessed in the ACTIVE FLT PLAN pages.

SPEED COMMAND FLIGHT PHASES In order to perform the speed calculations and to define the FGCS targets in automatic mode, the FMS divides the flight in flight phases as follows: Takeoff: The FMS speed control does not provide guidance while in the Take Off mode. However, it sends inputs to the PFD to show the V2, until V2 is reached, then it ramps to V2 + 10 kt until the vertical mode is changed.

AOM-1502-003

Departure: Speed command is the one selected on the DEP/APP speeds page. The default departure speed is 200 kt for 4 NM below 2500 ft. Climb: Following departure, the command is the speed restriction set on the PERF INIT page 3/3. The default limit is 250 kt below 10000 ft. After clearing the limitation, the FMS commands the lower value between MACH or CAS set on the climb schedule. The default climb schedule is 280 kt/0.73 M. During step climbs the FMS commands climb speed

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schedule if the difference between the current and the intended level is more than 5000 ft, otherwise it remains in cruise speed schedule. Cruise: When in VALT or ALT and the present altitude is equal to the cruise altitude selected on the PERF INIT, the speed command is the cruise schedule selected. If the airplane levels-off at an altitude lower than the Initial Cruise altitude, the speed command continues on the climb schedule. Descent: The default descent speed schedule is 290 kt/0.76 M/3.0°. During step descents, the descent speed schedule will be the default speed commanded by the FMS. After level off FMS commands cruise speed schedule if the aircraft is before 50 NM from the TOD or descend speed schedule if it is within this range. Approaching the set limitation in the Speed/Altitude limit of the PERF INIT page 3/3, the FMS commands a speed reduction to comply with any existing the speed constraint. Approach: The transition to approach speeds is at 15 flight plan nautical miles from the destination or 5 NM from the first approach fix. This selection is made on the DEP/APP speeds pages. When the flaps are set to position 1, the FMS commands speeds for the next flap. These speeds are calculated by the FMS for the actual airplane weight. !MAU load 21.2 and on OR POST-MOD SB 170-31-0028

The approach speed limit activation logic considers the distance to destination airport and altitude AGL (default values are 15.0 NM and 3000 ft AGL). "

Waypoint Speed Constraints – If a speed is set in a flight plan waypoint, the FMS guides the AFCS to comply with this speed. During a climb, the FMS commands the speed set in the speed constraint waypoint for all previous waypoints. After passing the speed constraint waypoint, the FMS reverts to the speed schedule set in the initialization up to the TOC.

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Go-around – When the flight director is set to G/A the FMS speeds schedule changes for go-around as defined in the PERF INIT. If a new approach is set while in go-around speed schedule the FMS reverts to approach speeds. While in go-around, if a new destination is set, the FMS transitions to climb schedule speeds.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

During cruise and descent, the FMS commands the AFCS to cross the waypoint at the selected speed and applies this speed for the subsequent waypoints.

DATA BASE The FMS has three databases in its memory, a navigation database, a custom database, and an aircraft database.

NAVIGATION DATABASE The FMS retrieves information from the navigation database about waypoints and procedures used in flight planning, and to tune NAVAIDs for position determination. The navigation database is updated in cycles of 28 days, and the last two cycles are displayed as ACTIVE NDB or NON-ACTIVE on the MCDU NAV IDENT page. If the airplane is on ground and after a power up is performed, the FMS automatically sequences to a new database cycle at 0900Z on the date the new cycle becomes effective. Therefore, the older cycle is effective for 9 hours beyond the last day of that cycle, and the new cycle is not effective until 0900Z of its first day. Active flight plans are cleared when the active database cycle changes.

AOM-1502-003

If the system is powered up at or after 0900Z on the date the new cycle becomes effective, the new cycle indication changes from amber to green and is displayed as ACTIVE NDB. The old cycle indication changes from green to amber and is displayed as NON-ACTIVE NDB.

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

NAV IDENT 1L 2L 3L

DATE

1/1

ACTIVE NDB

1R

NON-ACTIVE NDB

2R

18JAN 14FEB/13

25JAN13 UTC

21DEC 17JAN/13

1855 Z SW

NDB V3.01 16M

EMBRAER-302

NZ7.1.2

3R

4L

4R

5L

5R MAINTENANCE

POS INIT

6R EM170AOM141328A.DGN

6L

If the system is powered up before 0900Z on the date the new cycle becomes effective, the old cycle indication is displayed in green and as ACTIVE NDB. The new cycle indication is displayed in amber and as NON-ACTIVE NDB. NOTE: The green indication does not reflect the actual date. It is only related to the effectiveness of the navigation base and it takes into account the 9 hours difference in the effectiveness time. The active database may be manually selected. If the pilot selects the new database cycle before 0900Z on the date the new cycle becomes effective, the new cycle is displayed in amber and as the ACTIVE NDB. The old cycle is displayed in green and as the NON-ACTIVE NDB. For this scenario, if takeoff and landing occur before 0900Z, the old database cycle returns to ACTIVE NDB before the Flight Complete logic.

When both cycles are displayed in amber, either the date is wrong or both navigation databases are expired.

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NOTE: The FMS always follows the database cycle selected as ACTIVE NDB, regardless of the color (green or amber).

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

Depending on the location, the database cycle date may not agree with the current local date. Most FMSs are configured so the time displayed on the MCDU NAV IDENT page is synchronized with the GPS date and time.

CUSTOM DATABASE The custom database contains information entered by the pilot. This is where the pilot can create and store flight plans and waypoints. This database is not updated on a scheduled basis.

AIRCRAFT DATABASE The airplane database contains all airplane-specific performance parameters. The performance learning function within the FMS, known as SmartPerf, has the ability to “learn” performance characteristics based on information gathered on previous flights. This performance learning requires no pilot action. Therefore, all performance data (learned and fixed) is contained in the file.

FUNCTIONS PERFORMANCE (PERF) This function gives access to performance related pages including performance initialization, climb, cruise, descent, wind, fuel management and takeoff and landing data. In addition, permits the initialization of stored flight plans and execute performance computations.

NAVIGATION (NAV) This function gives access to Index providing access to position sensor data, stored flight plans, FIX INFO, selection of waypoints and maintenance pages. In addition, in this page is possible to perform data loading using a remote terminal or DMU.

FLIGHT PLAN (FPL)

AOM-1502-003

This function Provides flight plan data for each leg in the planned (active) flight plan, including course, distance and FPA/altitude constraints. It is also possible to create a flight plan, select a stored flight plan and loading of a flight plan from a disk.

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

PROGRESS (PROG) This function summarizes important dynamic flight parameters and the airplane relationship with the active flight plan, such as Estimated Time Enroute (ETE), distance to go, fuel information, current NAV mode, number of long range NAVs used, NAVAIDS that are presently tuned, FMS navigation mode, closest NAVAIDS, and air data information (current speed, altitude and temperature).

COMPANY ROUTE (RTE) Route planning allows a quicker flight planning by the pilot. It can be performed either by selecting a company route from the database or by entering flight plan legs and procedures using Air Traffic Control (ATC) language, saving time during the preflight phase. This function displays the active route with origin, destination, runway and company route identifier information.

FMS ANNUNCIATORS Annunciators are displayed on the electronic display system (EDS). Magenta indicates an advisory annunciator and amber indicates an alerting annunciators. – Dead Reckoning (DR) - DR is an alerting (amber) annunciator. This annunciator is displayed or lit when operating in the DR mode. The FMS enters DR mode after loss of required navigation performance (see DGRAD) and loss of radio updating and all other position sensors (IRS and GPS) for greater than 2 minutes. – Degraded (DGRAD) - DGRAD is an alerting (amber) annunciator. This annunciator is displayed or lit when the FMS loses required navigation performance (RNP). This is accompanied by the UNABLE RNP scratchpad message. The DGRAD annunciator is displayed on the HSI and LNAV display when FMS is the selected airplane navigation source on EDS and any of the following conditions exist: – FMS EPU is greater than RNP.

– GPS is not available and GPS is required for the selected flight plan procedure.

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– FMS position integrity estimate is greater than the integrity alarm limit (this can occur when EPU is slightly less than RNP).

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

If the DR annunciator is displayed or lit when the DGRAD annunciator is displayed or lit, the DGRAD annunciator is removed or turned off. – Message (MSG) - MSG is an alerting (amber) annunciator. This annunciator is displayed when a message is shown in the MCDU scratchpad. The annunciator is removed or turned off after the message(s) has been cleared from the scratchpad. Messages are displayed in the MCDU scratchpad at various times. They inform or alert the pilot as to system status. Messages are divided into the following two major groups: – ADVISORY MESSAGES - Advisory messages are usually the result of a pilot action on the MCDU (e.g., making an entry with the incorrect format). These messages do not turn on The MSG annunciator. – ALERTING MESSAGES - Alerting messages alert the pilot to the FMS status, assuming the pilot is not looking at the MCDU (e.g., a message annunciating a sensor failure). Messages are stacked for display in priority order on a first in, last out basis. In cases where there are multiple messages stacked, the message annunciator remains displayed or lit until all messages are cleared. Only one message can be cleared per CLR key push. – Approach (APPR) - APPR is an advisory (magenta) annunciator. The annunciator indicates the FMS is in the approach mode of operation. In this mode, the EDS deviation sensitivity and FMS tracking gains are increased. The approach annunciator is displayed if ALL of the following conditions are valid: – The FMS is the selected airplane navigation source on EDS. – A non–precision instrument approach must have been activated from the navigation database. If no approach, or an ILS, LOC, LOC-BC, LDA), simplified directional facility (SDF), or MLS approach is selected, the APPR annunciator does not light. – The airplane position is between 2 NM outside the final approach fix (FAF) and the missed approach point (MAP). – The DGRAD annunciator must be removed or turned off.

AOM-1502-003

– When the approach requires the use of GPS, GPS navigation mode must be valid.

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

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– Terminal (TERM) - TERM is an advisory (Magenta) annunciator. TERM indicates the FMS is in the terminal area and that required navigation accuracy has increased. – Lateral Track Alert (WPT) - WPT is an advisory (magenta) annunciator. FMS gives a WPT 30 seconds prior to sequencing a waypoint. – Vertical Track Alert (VTA) - VTA is an advisory (magenta) annunciator. A vertical track annunciation is given to warn of an impending FMS vertical track command change. A VTA is issued for the following conditions: – The airplane is within 1000 ft of capturing an altitude constraint that is not collocated with the altitude preselect. – In CRUISE, one minute prior to TOD. – One minute prior to resuming a climb or descent from a constrained waypoint. – Prior to resuming a VNAV flight level change (VFLCH) descent due to a speed limit altitude level-off. – In CRUISE, one minute prior to executing a step Climb. The VTA is also issued as an audible annunciation. – Lateral Offset (OFFSET) - OFFSET is an advisory (magenta) annunciator. FMS gives the capability to define and fly a parallel offset of up to 30 NM on any TF or CF leg that is not included in a SID, STAR, Approach or Hold. A parallel offset can also be flown to a DF leg following the final turn. – Altitude Alert - The altitude alert generated by the FMS is used by EDS in a fashion similar to that used to alert the flight crew of the impending altitude preselect target (i.e., amber speed tape display).

The APPR annunciator must turn on 2 NM before the final approach fix. It remains lit for the remainder of the approach. This is a positive cue to the flight crew that the sensor configurations is correct and sensor integrity is within limits for the approach. The approach annunciator is not lit during localizer based approaches since the FMS is not authorized to be coupled during localizer approaches. The DGRAD annunciator must be off throughout the approach. If DGRAD annunciator turns on, the FMS should not be used for the remainder of the approach. The

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– Required Navigation Performance (RNP) - RNP is an advisory (magenta) annunciator.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

flight crew can continue the approach using raw data or perform the missed approach procedure.

PREFLIGHT A preflight procedure for a normal flight can be accomplished on the ground with the following steps: – Radios page. – Navigation identification. – Position initialization. – Route selection. – Departure. – Performance initialization. – Performance data check. – Takeoff. – Preflight status verification.

AOM-1502-003

In order to clarify the steps required in the preflight procedure a navigation example is considered.

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

!MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

AVIONICS POWER

NAVIGATION IDENTIFICATION

POSITION INITIALIZATION

ROUTE SELECTION

PERFORMANCE INITIALIZATION

PERFORMANCE DATA CHECK

TAKEOFF

PREFLIGHT STATUS VERIFICATION

FLY !

EM170AOM140466B.DGN

DEPARTURE

"

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PREFLIGHT FLOW CHART

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

!MAU load 19.3 and on OR POST-MOD SB 170-31-0019

AVIONICS POWER

RADIOS PAGE PUSH FMS FUNCTION KEY BUTTON

NAVIGATION IDENTIFICATION

POSITION INITIALIZATION

OPTION

MAINTENANCE AND SYSTEM CONFIGURATION

ROUTE SELECTION

PERFORMANCE INITIALIZATION

PERFORMANCE DATA CHECK

TAKEOFF

ACTIVE FLIGHT PLAN

PROGRESS

FLY !

EM170AOM140728A.DGN

DEPARTURE

AOM-1502-003

PREFLIGHT FLOW CHART

"

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SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

SBBV

UA300

SBEG

MAN

UZ6

BRS

PCL

SBSJ

EM170AOM140467C.DGN

UW2

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NAVIGATION EXAMPLE

AIRPLANE OPERATIONS MANUAL

NAVIGATION IDENTIFICATION INITIALIZATION

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AND

POSITION

!MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

1 - After power up the RADIO page will be displayed as default. Press NAV button to enter the NAV INDEX 1/2 page. 2 - Press LSK 1L (NAV IDENT) to go to NAV IDENT 1/1 page. The following items must be checked on NAV IDENT 1/1 page: – Date and time: This data comes from the GPS. If the GPS is failed or the data is not valid, date and time can be changed. – Navigation data base: Active data base and alternate period dates. – Worldwide coverage. 3 - Press LSK 6L (MAINTENANCE) to go to FMS MAINTENANCE 1/3 page. Check if active mode is dual. In case of not operating in dual mode the navigation must be entered in both MCDUs. 4 - Press LSK 6R to go back to NAV IDENT 1/1 page. 5 - On NAV IDENT 1/1 page press LSK 6R (POS INIT). 6 - The POSITION INIT 1/1 page presents a maximum of 3 options to be loaded as initial position pressing respectively 1R, 2R or 3R: – Last position: The FMS stores the last position when the airplane is powered down. – Reference waypoint: Displays the closest ramp x or airport reference point within 3 NM of the last position. Additionally the pilot may type a waypoint or coordinates on the scratchpad through alphanumeric keys, and enter it pressing LSK 2L.

AOM-1502-003

– GPS position.

14-09-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 17

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 18

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

!!MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

RADIO 1L

NAV INDEX

1/2

2

COM1

COM2

118.15

121.60

1L

1R

DATE

NAV IDENT WPT LIST

DATALINK

3L

112.80

111.50

3R

3L

FPL LIST

FLT SUM

4L

110.30

110.80

4R

4L

POS SENSORS

2L

121.30

121.85

NAV1

2R

1

NAV2

5L

TCAS/XPDR

6L

STBY

2L

XPD1

4436

5R

5L

IDENT

6R

6L

NAV IDENT

1/2

FIX INFO DEPARTURE

1R

1L

2R

2L

3R

3L

09OCT03 UTC

1708z

04

SW

4R

4L

HOLD

5R

5L

ARRIVAL

6R

6L

1/1

ACTIVE NDB 02 OCT 29OCT/03

SEP

NDB

NZ7. 0

01 OCT/03 V3.01

5M

YY5-310

1R 2R 3R 4R 5R

MAINTENANCE

POS INIT

6R

3

FMS 2 MAINTENANCE

NAV IDENT

1/3

ACTIVE MODE

1L

DATE

DUAL

1L

1R

SELECTED MODE

2L

DUAL

2L

2R

09OCT03 1708z SW

3L

3R

3L

4L

4R

5L

5R DATA LOAD

NAV IDENT

POSITION INIT LAST POS

1L

S23

13.7

SBSJ REF

2L

S23

3L

S23

GPS

13.7 1

13.7

W045 WPT

W045

POS

W045

SEP

NDB

01 OCT/03 V3.01

5M

YY5-310

2L

2R

S23

13.7

SBSJ REF

S23

GPS

S23

13.7 1

13.7

W045 WPT

W045

POS

W045

52.3 LOAD

1R

52.3 LOAD

2R

52.3 LOAD

3R

3R

3L

4L

4R

4L

4R

5L

5R

5L

5R

6L

MAINTENANCE

POS INIT

5

6R

6L

POS SENSORS

FLT PLAN

52.3 LOAD

6R

52.3 LOAD

1R 2R

(LOADED)

52.3 LOAD

3R 4R

5L

5R POS SENSORS

6

1/1

4L

6L

6R

NZ7. 0

04

LAST POS

1L

1R

1/1

EM170AOM140438C.DGN

6L

4

ACTIVE NDB 02 OCT 29OCT/03

UTC

POSITION INIT

1/1

FLT PLAN

6R

AOM-1502-003

NAVIGATION IDENTIFICATION AND POSITION INITIALIZATION

14-09-25

"" "

Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 19

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 20

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

NAVIGATION IDENTIFICATION INITIALIZATION

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AND

POSITION

!MAU load 19.3 and on OR POST-MOD SB 170-31-0019

1 - After power up the RADIO page will be displayed as default. Press NAV button to enter the NAV IDENT 1/1 page. 2 - On NAV IDENT 1/1 page the following items must be checked: – Date and time: This data comes from the GPS. If the GPS is failed or the data is not valid, date and time can be changed. – Navigation data base: Active data base and alternate period dates. – Worldwide coverage. 3 - Press LSK 6R (NAV IDENT) to go back to NAV IDENT 1/1 page. 4 - On NAV IDENT 1/1 page press LSK 6R (POS INIT). 5 - The POSITION INIT 1/1 page presents a maximum of 3 options to be loaded as initial position pressing respectively 1R, 2R or 3R: – Last position: The FMS stores the last position when the airplane is powered down. – Reference waypoint: Displays the closest ramp x or airport reference point within 3 NM of the last position. Additionally the pilot may type a waypoint or coordinates on the scratchpad through alphanumeric keys, and enter it pressing LSK 2L.

AOM-1502-003

– GPS position.

14-09-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 21

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 22

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

!!MAU load 19.3 and on OR POST-MOD SB 170-31-0019

RADIO COM1

1L 2L

COM2

118.15

121.60

121.30 NAV1

121.85 FMS AUTO

3L

112.80

4L

110.30

5L

TCAS/XPDR

6L

STBY

FMS AUTO

NAV IDENT

1/2

1R

1L

2R

2L

1

NAV2

FMS 1 MAINTENANCE

1/1

ACTIVE MODE

ACTIVE NDB

DATE UTC

2L

2R

21DEC 17JAN/07

SW

DUAL

1R

SELECTED MODE

NON-ACTIVE NDB

1855 Z

1L

1R

18JAN 14FEB/07

25JAN07

1/3

NDS V3.01 16M

DUAL

2R

111.50

3R

3L

3R

3L

3R

110.80

4R

4L

4R

4L

4R

4436

5R

5L

5R

5L

5R

IDENT

6R

6L

6R

6L

WORLD3-301

NZ7.02

XPD1

MAINTENANCE

POS INIT

DATA LOAD

NAV IDENT

3

6R

2

NAV IDENT 1L 2L 3L

DATE

25JAN07 UTC

1855 Z SW

POSITION INIT

1/1

ACTIVE NDB

18JAN 14FEB/07 NON-ACTIVE NDB

21DEC 17JAN/07 NDS V3.01 16M

LAST POS

1R

1L 2L

2R

S23

13.7

SBSJ REF

S23

GPS

S23

13.7 1

13.7

W045 WPT

W045

POS

W045

POSITION INIT

1/1

52.3 LOAD 52.3 LOAD 52.3 LOAD

LAST POS

1L

1R 2R

5

2L

S23

13.7

SBSJ REF

S23

GPS

S23

13.7 1

13.7

W045 WPT

W045

POS

W045

1/1

52.3 LOAD

1R

52.3 LOAD

2R

LOADED

52.3 LOAD

3R

3L

3R

3L

4L

4R

4L

4R

4L

4R

5L

5R

5L

5R

5L

5R

6R

6L

MAINTENANCE

WORLD3-301

POS INIT

6R

4

6L

POS SENSORS

RTE

POS SENSORS

RTE

3R

6R EM170AOM140715B.DGN

6L

N27.02

AOM-1502-003

NAVIGATION IDENTIFICATION AND POSITION INITIALIZATION

14-09-25

"" "

Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 23

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 24

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

ROUTE SELECTION - CREATING A FLIGHT PLAN !MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

1 - On POSITION INIT 1/1 page press LSK 6R (FLT PLAN). On FLT PLAN 1/1 page it is possible to create/store a flight plan or load a flight plan from the memory. 2 - Enter the flight plan name in the scratchpad through alphanumeric keys and press LSK 3R. 3 - If the initialization coordinates are within 3 NM of the airport data base the origin airport is already loaded, otherwise enter the origin airport in the scratchpad through alphanumeric keys and press LSK 1L. 4 - Enter the destination airport in the scratchpad through alphanumeric keys and press LSK 2R. 5 - Enter the waypoints in the scratchpad through alphanumeric keys and press LSK correspondent to VIA.TO: – In case of waypoints entries, enter the airway identifier followed by the last desired waypoint of the airway. Both must be separated by a period. – If a waypoint entry corresponds to more than one option in the memory, all options are displayed and selection of the desired one is made by pressing the respective LSK. – When entering a waypoint and no VIA.TO is displayed press NEXT button until VIA.TO is displayed. 6 - When entry of all waypoints is finished, press LSK correspondent to DEST and press LSK correspondent to VIA.TO to close the flight plan. Verify the flight plan created by pressing NEXT button. Press LSK 6R (FPL SEL) to go to FPL PLAN SELECT 1/1 page.

AOM-1502-003

7 - Insert the flight plan by pressing LSK 1R (INSERT). 8 - On FLT PLAN page press LSK 6R (ACTIVATE) to activate the flight plan.

14-09-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 25

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 26

Flight Management System

REVISION 21

AOM-1502-003

9 - Access the last page (ALTERNATE FPL) by pressing the NEXT button.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

!!MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

POSITION INIT LAST POS

1L

S23

13.7

SBSJ REF

2L

S23

3L

S23

13.7

W045 WPT

W045

52.3 LOAD 52.3 LOAD

ORIGIN/ETD

1L

1R 2R

2L

3R

3L

4L

4R

5L

5R

GPS

6L

1

13.7

POS

W045

POS SENSORS

1L 2L

SBSJ

SBSJ

SBSJ-SBEG

1/1

DLK FPL

ORIGIN

FPL

2R

@

211

SBEG

VIA . TO

5R

5L

5R

6R

6L

FPL LIST

PERF INIT

SBSJ 355

2L 3L

4L

4R

4L

PCLNB

DIST/ETE 1467/06+57

@

GS 211

00+26

1L

1R

SBSJ

DIST/ETE 1507/07+08

355

92.0NM

007

44.9NM

PCLNB

2R

2L

3R

3L

KERBO

4R

4L

ARX

DEST

SBEG

007

PATTERN

FPL SEL

5L

6R

6L

PATTERN

FPL SEL

5R

5L

6R

6L

6R

1/2 @

GS 211

1R 2R

00+26

3R

00+13 86,8NM

4R

00+25

005

5R

FPL SEL

SBSJ-SBEG FPL ORIGIN

92.0NM

VIA.TO

PATTERN

1/1

4

2R

5L

3R

6L

1R

3R

3L

5L

211

4R

1L

5

@

DEST

3L

SBSJ-SBEG FPL

2R

GS

1465/06+56

4L

ORIGIN

1R

SBSJ

4R

GS DEST

VIA . TO

1/1

4L

6L

6R

2

2L

FPL

DIST/ETE

3R

RECALL OR CREATE FPL NAMED

1/1

DIST/ETE 1465/06+56

1

1L

1R

DEST

(LOADED)

52.3 LOAD

FLT PLAN

SBSJ-SBEG ORIGIN

5

FLT PLAN

1/1

100NM

VALDI

5R

00+29 FPL SEL

PATTERN

6R

5

1L

CRISE 007

2L

5

BRS

VIA.TO

3L

FPL

SBSJ-SBEG FPL

2/2

95.0NM

007

1R

00+27

1L

40.1NM

CRISE 007

2R

00+11

2L

DEST

SBEG

BRS

335

399NM

EROG

3R

3L 4L

NABOL

5L

5R

5L

TAROP

6R

6L

334

6L

PATTERN

FPL SEL

PATTERN

2L

2R

00+11 40.1NM

4R

1L

1R

40.1NM

335

4L

SBSJ-SBEG FPL

2/3

95.0NM 00+27

00+11 01+53

333

250NM 01+11

333

197NM

332

40.1NM

VIBOT EGAP

3R

3L

MAN

4R

4L

VIA . TO

5R

5L

3/3 1R 2R

00+56

3R

00+11 DEST

SBEG

125NM 00+36 FPL SEL

6R

5

6L

4R 5R

PATTERN

FPL SEL

(CONTINUE)

6R

EM170AOM140439C.DGN

SBSJ-SBEG 007

AOM-1502-003

CREATING A FLIGHT PLAN 1/2

""

14-09-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 27

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

!!MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

SBSJ-SBEG FPL 333

1L

VIBOT

250NM 01+11

2L

EGAP

00+56

333

SBEG

1L

197NM

00+11

PATTERN

2R

2L

INVERT/INSERT

2R

3R

3L

STORED FPL PERF

3R

0260

4R

4L

4R

5L

5R

6

6L

6R

FPL SEL

FLT PLAN

5R

SBSJ 335

2L

PCLNB

3L

KERBO

007

ACTIVE FLT PLAN

007

ARX

005

6L

VALDI CANCEL

1L

2R

2L

PCLNB

/

3R

3L

KERBO

335

86.8NM 00+25

/

4R

4L

/

5R

5L

ACTIVATE

6R

100NM 00+29

SBSJ

1R /

44.9NM 00+13

6R

LIST

ALTERNATE FPL

1/5

5/5

ORIGIN/ETD

92.6NM 00+26

FPL

1/5

ORIGIN/ETD

5L

7 1R

DEST

SBEG

4L

INSERT

4.5NM 00+01

5L

1L

SBSJ-SBEG

40.1NM

106

6L

1R

1/1

PLAN

44.9NM

007

86.8NM

005

8

6L

00+26

007

ARX

VALDI

1L

1R 92.6NM

00+13 00+25

/

2R

/

9

1R ALTERNATE

2L

2R

3R

3L

3R

/

4R

4L

4R

/

5R

5L

5R

PERF INIT

6R

6L

100NM 00+29

DEPARTURE

DEPARTURE

PERF INIT

6R

CREATING A FLIGHT PLAN 2/2

14-09-25

"" "

Copyright © by Embraer. Refer to cover page for details.

Page 28

Flight Management System

REVISION 21

AOM-1502-003

MAN

4L

FLT

EM170AOM140440C.DGN

332

3L

FLT PLAN SELECT

3/3

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

ROUTE SELECTION - CREATING A FLIGHT ROUTE !MAU load 19.3 and on OR POST-MOD SB 170-31-0019

1 - On POSITION INIT 1/1 page press LSK 6R (RTE). On RTE 1/1 page it is possible to create/store a flight plan or load a flight plan from the memory. 2 - If the initialization coordinates are within 3 NM of the airport data base the origin airport is already loaded, otherwise enter the origin airport in the scratchpad through alphanumeric keys and press LSK 1L. 3 - Enter the destination airport in the scratchpad through alphanumeric keys and press LSK 1R. 4 - Press NEXT key to go to RTE 2/3 page. 5 - Enter the waypoints in the scratchpad through alphanumeric keys and press LSK correspondent to VIA.TO: – In case of waypoints entries, enter the airway identifier followed by the last desired waypoint of the airway. Both must be separated by a period. – If a waypoint entry corresponds to more than one option in the memory, all options are displayed and selection of the desired one is made by pressing the respective LSK. – When entering a waypoint and no VIA.TO is displayed press NEXT button until VIA.TO is displayed. 6 - When entry of all waypoints is finished, press LSK correspondent to DEST and press LSK correspondent to VIA.TO to close the flight plan. 7 - On RTE page press LSK 6R (ACTIVATE) to activate the flight plan.

AOM-1502-003

8 - Access the last page (ALTERNATE RTE) by pressing the NEXT button.

14-09-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 29

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 30

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

!!MAU load 19.3 and on OR POST-MOD SB 170-31-0019

POSITION INIT LAST POS

1L

S23

2L

S23

W045

13.7

SBSJ REF GPS

S23

WPT

W045

13.7 1

POS

13.7

W045

1/1

RTE

2 ORIGIN/ETD

SBSJ

52.3 LOAD

1R

1L

52.3 LOAD

2R

2L

52.3 LOAD

3R 4R

4L

5L

5R

FPL REQST

FPL REPORT

CALL SIGN

POS SENSORS

RTE

RTE 1L 2L

DEST

SBSJ

SBFL CO ROUTE

SBSJ-SBFL

3L 4L 5L 6L

1

2R

2L

3

DEST

SBSJ

1R CO ROUTE

RUNWAY

6L

6R

FPL LIST

PERF INIT

RTE

2R

FPL REQST

FPL REPORT

CALL SIGN

FLIGHT ID

FPL LIST

PERF INIT

DATA LINK UNAVAILABLE

3L 4L

5R

5L

6R

6L

1R

SBFL

2R

2L

3R

3L

3R

4R

4L

4R

5L

5R

6L

6R

DEPARTURE

CALL SIGN

FLIGHT ID

FPL LIST

PERF INIT

2R

PERF INIT

5

6R

4R 5R

SBFL

6R

2/4

VIA

DEST

4

FPL REPORT

RTE

TO

1L

5R

3R FPL REQST

2/3

VIA 1R

3R 4R

FLIGHT ID

5L

1/3

ORIGIN/ETD

RUNWAY

1L

LOADED

4L

6L

1/1

ORIGIN/ETD

1R CO ROUTE

RUNWAY

3L

3L

RTE

1/1 DEST

TO

*ALT03

1R

1L

DIRECT

2L

TORUK.RDE

RDE

2R

3L

DIRECT

NIBGA

3R

4L

DIRECT

BROCK

4R

5L

DIRECT

CLARO

5R

6L

CANCEL

ACTIVATE

6R

6

VIA 1L

DIRECT

TO

SBFL DEST

2L

RTE

4/5 VIA 1R

1L

DIRECT

ALTERNATE RTE

4/5 TO

SBFL DEST

1R

1L

2R

2L

2R

3L

3R

4L

4R

5L

5R

2R

2L

3L

3R

3L

3R

4L

4R

4L

4R

5L

5R

5L

5R

6L

SBFL

CANCEL

ACTIVATE

6R

7

6L

SBFL

DEPARTURE

3/3

PERF INIT

8

6R

6L

ALTERNATE

DEPARTURE

PERF INIT

1R

6R

EM170AOM140716A.DGN

RTE

AOM-1502-003

CREATING A FLIGHT ROUTE

14-09-25

"" "

Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 31

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 32

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

ROUTE SELECTION - LOADING A FLIGHT PLAN 1 - Press Flight Plan (FPL key to go to FLT PLN 1/1 page. On this page it is possible to create/store a flight plan or load a flight plan from the memory. 2 - Press LSK 6L (FP LIST) or enter the flight plan name in the scratchpad through alphanumeric keys to access the FLIGHT PLAN LIST page. 3 - In the FLIGHT PLAN LIST page, select the desired flight plan by pressing the respective LSK flight plan that appears in the scratch pad. 4 - Press LSK 1L (SHOW FPL). Verify the loaded flight plan by pressing NEXT button to scroll on the pages. 5 - Press LSK 6R (FPL SEL) to go to FLIGHT PLAN SELECT 1/1 page. 6 - On FLIGHT PLAN SELECT 1/1 page press LSK 1R (INSERT) to insert the flight plan. 7 - On FLT PLAN page press LSK 6R (ACTIVATE) to activate the flight plan.

AOM-1502-003

8 - Access the last page (ALTERNATE FPL) by pressing the NEXT key.

14-09-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 33

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 34

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLT PLAN

2

ORIGIN/ETD

1L

SBSJ

2R

2L

GPS-CAB02

SBSJ-SBEG

2R

3R

3L

SBGP-SBGP

SBSJ-SEG

3R

4L

4R

4L

SBGP-SDJL

SBSJ-SBGA

4R

5L

5R

5L

SBGP-SBSJ

SBSJ-SBMA

5R

6R

6L

FPL SEL

6R

RECALL OR CREATE FPL NAMED

FPL LIST

1L

SBSJ 007

44.9NM

PCLNB

GPS-CAB02

SBSJ-SBEG

2R

2L

3L

SBGP-SBGP

SBSJ-SEG

3R

3L

KERBO

4L

SBGP-SDJL

SBSJ-SBGA

4R

4L

ARX

007

005

SBGP-SBSJ

SBSJ-SBEG

SBSJ-SBMA

5R

5L

FPL SEL

6R

6L

FLT PLAN

2L

SBSJ

92.6NM

007

44.9NM

PCLNB

3L

KERBO

4L

ARX

007

005

5L 6L

VALDI CANCEL

00+26 00+13

1L

SBSJ

00+25

SBSJ-SBEG

INSERT

6 1R

2R

2L

INVERT/INSERT

2R

3R

3L

STORED FPL PERF

3R

4R

4L

4R

100NM 5R

00+29 FPL SEL

5

5L 6L

6R

5R 6R

FPL LIST

ALTERNATE FPL

1/5

5/5

92.6NM

007

44.9NM

PCLNB

2R

2L

3R

3L

KERBO

/

4R

4L

ARX

007

005

/ ACTIVATE

5R 6R

7

5L 6L

VALDI

1L

1R

355

/

100NM 00+29

1L

86.8NM

PATTERN

/

86.8NM 00+25

00+13

1R

1/1

ORINGIN/ETD 1R

355

211

00+26

ACTIVE FLT PLAN

1/5

ORINGIN/ETD 1L

VALDI

@

FLT PLAN

3

00+26 00+13

8

1R ALTERNATE

/

2R

2L

2R

/

3R

3L

3R

/

4R

4L

4R

/

5R

5L

5R

6R

6L

86.8NM 00+25 100NM 00+29

DEPARTURE

PERF INIT

DEPARTURE

PERF INIT

6R

EM170AOM140441D.DGN

6L

GS

1514/07+10 92.0NM

FLT PLAN SELECT

1/3

DIST/ETE

355

2L

5L

PERF INIT

ORIGIN 1R

1R

DEST

SBSJ-SBEG FPL

1/2

ORG/DEST

1L

1/2

ORG/DEST

1L

6L

FLIGHT PLAN LIST

FLIGHT PLAN LIST SHOW FPL 1R

3L

SHOW FPL

DLK FPL

2L

1

4

1/1

FLIGHT INSTRUMENTS/COMM/NAV/FMS

AOM-1502-003

LOADING A FLIGHT PLAN

14-09-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 35

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 36

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

CREATING AN ALTERNATE FLIGHT PLAN !MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

1 - On ALTERNATE FPL page enter the alternate airport in the scratchpad through alphanumeric keys and press LSK 2R. 2 - Enter the waypoints in the scratchpad through alphanumeric keys and press LSK correspondent to VIA.TO: – In case of waypoints entries, enter the airway identifier followed by the last desired waypoint of the airway. Both must be separated by a period. – If a waypoint entry corresponds to more than one option in the memory, all options are displayed and selection of the desired one is made by pressing the respective LSK. – When entering a waypoint and no VIA.TO is displayed press NEXT button until VIA.TO is displayed. 3 - When entry of all waypoints is finished, press LSK correspondent to DEST and press LSK correspondent to VIA.TO to close the flight plan.

AOM-1502-003

4 - Activate the alternate flight plan by pressing the LSK 6R (ACTIVATE).

14-09-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 37

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 38

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

!!MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

ALTERNATE FPL

2

5/5

1L

1R ALTERNATE

ALTERNATE FPL 1L

1

SBEG

MOD ALTERNATE FPL

5/5 1R

1L

SBEG MAN

ALTN

VIA.TO -----

SBBV

2L

2R

2L

2R

2L

3L

3R

3L

3R

3L

4L

4R

4L

4R

5R

5L

6R

6L

5L 6L

DEPARTURE

PERF INIT

ACTIVATE

CANCEL

2

286

5/5 1R

4.5NM /

00+01

VIA.TO

ALTN

SBBV

4L

5R

5L

6R

6L

2R 3R 4R 5R

CANCEL

ACTIVATE

6R

3

MOD ALTERNATE FPL 1L

SBEG 286

2L

MAN

UBUME

4L

EDRIP

008

007

5L 6L

008

FELIX

1L

1R 4.5NM 00+01

008

3L

MOD ALTERNATE FPL

5/6

BVI

VIA.TO

00+06

/

1R

1L

2R

2L

3R

3L

ALTN

SBBV

/

2R

/

3R

3L

/

4R

4L

4R

4L

5R

5L

5R

5L

6R

6L

6R

6L

2

2L

40.2NM 00+06

MOD ALTERNATE FPL

6/6

40.2NM

008

BVI

40.2NM 00+06

220

SBBV

0.7NM 00+00

/

1R / 0280 ALTN

SBBV

143NM 00+20

6/6

2R 3R 4R

132NM /

00+18

ACTIVATE

CANCEL

CANCEL

ACTIVATE

5R CANCEL

ACTIVATE

6R

4

ALTERNATE FPL

2L

BVI

40.2NM 00+07

220

SBBV

0.7NM 00+00

6/6 /

1R / 0280 ALTN

SBBV

3L

2R 3R

4L

4R

5L

5R

6L

DEPARTURE

PERF INIT

EM170AOM140442C.DGN

1L

008

6R

AOM-1502-003

ALTERNATE FLIGHT PLAN

14-09-25

"" "

Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 39

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 40

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

CREATING AN ALTERNATE FLIGHT ROUTE !MAU load 19.3 and on OR POST-MOD SB 170-31-0019

1 - On ALTERNATE RTE page enter the alternate airport in the scratchpad through alphanumeric keys and press LSK 2R. 2 - Enter the waypoints in the scratchpad through alphanumeric keys and press LSK correspondent to VIA.TO: – In case of waypoints entries, enter the airway identifier followed by the last desired waypoint of the airway. Both must be separated by a period. – If a waypoint entry corresponds to more than one option in the memory, all options are displayed and selection of the desired one is made by pressing the respective LSK. – When entering a waypoint and no VIA.TO is displayed press NEXT button until VIA.TO is displayed. 3 - When entry of all waypoints is finished, press LSK correspondent to DEST and press LSK correspondent to VIA.TO to close the flight plan.

AOM-1502-003

4 - Activate the alternate flight route by pressing the LSK 6R (ACTIVATE).

14-09-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 41

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 42

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

!!MAU load 19.3 and on OR POST-MOD SB 170-31-0019

2

ALTERNATE RTE

ALTERNATE RTE

3/3

1L

1R

VIA

1L

1

ALTERNATE

ALTERNATE RTE

3/3 TO ALTN

1R

1L

2L

2R

2L

2R

2L

3L

3R

3L

3R

3L

4L

4R

4L

4R

4L

5R

5L

5R

5L

6R

6L

6R

6L

5L CANCEL

6L

ACTIVATE

SBCT

SBCT

CANCEL

ACTIVATE

PONCA

3/3

VIA

TO

DIRECT

PONCA

1R 2R

ALTN

SBCT

3R 4R 5R

CANCEL

ACTIVATE

SBCT

6R

3

ALTERNATE RTE 1L 2L 3L

VIA

TO

DIRECT

PONCA

DIRECT

SBCT ALTN

SBCT

4L 5L

1R

1L

2R

2L

3R

3L

4R

4L

5R CANCEL

ACTIVATE

6R

4

VIA

3/3 TO

DIRECT

PONCA

DIRECT

SBCT ALTN

SBCT

5L 6L

1R 2R 3R 4R 5R

DEPARTURE

PERF INIT

6R

EM170AOM140729A.DGN

6L

ALTERNATE RTE

3/3

AOM-1502-003

ALTERNATE FLIGHT ROUTE

14-09-25

"" "

Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 43

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 44

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

PERFORMANCE INITIALIZATION 1 - On ALTERNATE FPL or ALTERNATE RTE page press LSK 6R (PERF INIT) to enter in the PERFORMANCE INIT page. The following items must be checked: – Aircraft type. – Tail number. 2 - Select the performance mode by pressing LSK 2R to enter in the PERF MODE page. Press the respective LSK performance mode and LSK 1R (RETURN). Three modes are available for selection: – Full performance: The performance is based according to pilot selections. The following pages/datas are only available in full performance: – PERF DATA pages. – CLIMB pages. – CRUISE pages. – DESCENT pages. – Point of no return page. – Equal time point page. – Optimum and maximum altitude. – Cruise speed schedules: long range cruise, maximum speed, maximum endurance and maximum range. In order to calculate the performance data the following entries are required: – Zero Fuel Weight.

AOM-1502-003

– Current groundspeed and fuel flow: The performance is based according to current groundspeed and fuel flow. On the ground a default value for groundspeed is used, once airborne the current value is used. The fuel flow can be overridden by a pilot entry. – Speed schedules and cruise fuel flow: The performance is based according to pilot entered speed schedules and cruise fuel flow.

14-09-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 45

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

3 - Enter the climb speed in the scratchpad through alphanumeric keys and press LSK 3L. The entry can be CAS, MACH or both CAS/MACH (separated by a slash). The active speed is the one that provides the lowest TAS. Entering “delete” returns the default values. Selection can also be provided by pressing LSK 3R and entering the CLIMB MODES page. On CLIMB MODES page select the respective LSK climb mode and LSK 1R (RETURN). 4 - Enter the cruise speed in the scratchpad through alphanumeric keys and press LSK 4L. The entry can be CAS, MACH or both CAS/MACH (separated by a slash). The active speed is the one that provides the lowest TAS. Entering “delete” returns the default values. Selection can also be provided by pressing LSK 4R and entering the CRUISE MODES page. On CRUISE MODES page select the respective LSK cruise mode and LSK 1R (RETURN). Four cruise mode are available: – Long range cruise. – Maximum speed. – Maximum endurance. – Maximum range speed. If long range cruise or maximum speed are selected, the active speed at high altitudes is MACH and at low altitudes is CAS. For maximum endurance always CAS is the active speed. 5 - Enter the descent speed and angle in the scratchpad through alphanumeric keys and press LSK 3L. The entry can be CAS, MACH, ANGLE, both CAS/MACH or CAS/MACH/ANGLE (separated by slashes). The active speed is the one that provides the lowest TAS. Entering “delete” returns the default values.

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 46

Flight Management System

REVISION 21

AOM-1502-003

Selection can also be provided by pressing LSK 5R and entering the DESCENT MODES page. On DESCENT MODES page select the respective LSK climb mode and LSK 1R (RETURN).

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

6 - Press the LSK 6L to enter in the DEP/APP SPD pages. On the DEPARTURE SPEED 1/3, it is possible to set the speed restriction during the departure as well as the altitude and the distance where the departure speed limit applies. 7 - Press the NEXT button to go to APPROACH SPEEDS 2/3 page. On this page it is possible to enter the approach speeds depending the flap setting. It is also possible to enter the approach speed limit. The FMS logic is to command the speed for the next flap up to flaps full. In the LSK 4L, it is possible to access the radial distance in nautical miles where FMS begins the approach schedule. In the LSK 5R or 5L it is possible to select if the approach speed schedule is to be initiate at further out distance than the one set in 4L or not. !MAU load 21.2 and on OR POST-MOD SB 170-31-0028

In the LSK 4L it is also possible to access the altitude AGL in feet and in the LSK 4R it is possible to access the radial distance in nautical miles. "

8 - Press the NEXT button to go to GO-AROUND SPEEDS 3/3 page. On this page it is possible to set go around speeds depending on flap settings. Press the RETURN prompt at 1R to go back to PERFORMANCE INIT 1/3. 9 - Press NEXT button to go to PERFORMANCE INIT 2/3 page. 10 - On PERFORMANCE INIT 2/3 page it is possible to enter the data below. The entry is accomplished in the scratchpad through alphanumeric keys and pressing the respective LSK.

AOM-1502-003

– Step climb increment (unavailable).

14-09-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 47

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

– Fuel reserve. Additionally fuel reserve can also be entered by pressing LSK 2R to access FUEL RESERVE page. On FUEL RESERVE page it is possible to enter the fuel reserve in kilograms or in minutes. The entry is accomplished in the scratchpad through alphanumeric keys and pressing the respective LSK. Press LSK 1R (RETURN) to go back to PERFORMANCE INIT page. The fuel reserve applies at destination or at the alternate destination if one has been entered. – Fuel allowance for takeoff and landing. – Contingency fuel. 11 - Press NEXT button to enter in the PERFORMANCE INIT page 3/3. On this page it is possible to enter the data below. The entry is accomplished in the scratchpad through alphanumeric keys and pressing the respective LSK. – Transition altitude. – Initial cruise altitude. Altitudes above the transition altitude are displayed as flight levels and below in feet. The cruise altitude must be equal to or greater than the Altitude Selector, otherwise the message RESET ALT SEL? is displayed. If the full performance mode is selected the initial cruise altitude is displayed as OPTIMUM. – Average cruise wind and corresponding altitude. – Zero fuel weight. – Speed limits associated with altitudes. – Temperature deviation.

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 48

Flight Management System

REVISION 21

AOM-1502-003

– Fuel weight. If the maximum gross weight is exceeded the message EXCEEDS MAX GROSS WEIGHT is displayed.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ALTERNATE FPL 008

1L

BVI

40.2NM 00+07

2L

SBBV

00+00

220

PERFORMANCE INIT

6/6

ACFT TYPE

/

1R

1L

E170-C2

2R

2L

FULL PERF

0.7NM / 0280 ALTN

SBBV

3L

MAN

PILOT SPD/FF

3R

LRC

OR

FULL PERF (ACT)

4R

290/.77M/3.0

OR

5R

5L

5R

ACFT DB

6R

6L

6R

5L 6L

DEP/APP SPD

PERFORMANCE INIT ACFT TYPE

1L

E170-C2

2L

FULL PERF

PERF MODE

CLIMB

3L

MAN

290/.70M

CRUISE

DESCENT

CLIMB MODES

1/3

# PP-XJI

TAIL

SPD

CRUISE

1R

1L

OR

2R

2L

OR

3R

3

2R

3L

5R 6R

CURRENT GS/FF

4L

5L PERF INIT

2L

2 1R

RETURN

3R

4L

DEPARTURE

SPD

2

2R

1L

4R

3L

4R

6L

OR

1R

OR

290/.70M

3R

4L

1

1/1

TAIL

PERF MODE

CLIMB

PERF MODE

1/3

# PP-XJI

FLIGHT INSTRUMENTS/COMM/NAV/FMS

MANUAL 290/.70M

1/1 RETURN

290/.70M (ACT)

PERFORMANCE INIT

3

ACFT TYPE

1R

1L

E170-C2

2R

2L

FULL PERF

3R

3L

PERF MODE

CLIMB

3L

MAN

290/.70M

1/3

# PP-XJI

TAIL

SPD

CRUISE

1R

OR

2R

OR

3R

4L

LRC

OR

4R

4L

4R

4L

LRC

OR

4R

5L

290/.77M/3.0

OR

5R

5L

5R

5L

290/.77M/3.0

OR

5R

6L

DEP/APP SPD

ACFT DB

6R

6L

6R

6L

DEP/APP SPD

ACFT DB

6R

DESCENT

DESCENT

4

(CONTINUE)

1L

1/1

RETURN

PERFORMANCE INIT

4

ACFT TYPE

1R

1L

E170-C2

2L

FULL PERF

3L

2L

LRC (ACT)

2R

3L

MAX SPD

3R

PERF MODE

CLIMB

MAN

290/.70M

DESCENT MODES

1/3

# PP-XJI

1/1

TAIL

SPD

CRUISE

1R

1L

OR

2R

2L

MANUAL 290/.77M/3.0

OR

3R

3L

290/.77 M/3.0

4L

VMO/MMO/3.0

RETURN

1R 2R

(ACT)

3R

4L

MAX END

4R

4L

LRC

OR

4R

5L

MXR SPD

5R

5L

290/.77M/3.0

OR

5R

5L

5R

6R

6L

DEP/APP SPD

ACFT DB

6R

6L

6R

6L

DESCENT

5

4R

EM170AOM140443C.DGN

CRUISE MODES MANUAL 290/.78M

AOM-1502-003

PERFORMANCE INITIALIZATION 1/2

14-09-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 49

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

PERFORMANCE INIT ACFT TYPE

1L 2L

E170-C2

PERF MODE

FULL PERF MAN

CLIMB

3L

290/.70M

DEPARTURE SPEED

1/3

# PP-XJI

TAIL

OR

SPD

CRUISE

1R 2R

1L

SPEED LIMIT 200

2L

AGL < 2500

APPROACH SPEEDS

1/3

RETURN LIMIT

>MN 4.0

1R 2R

7

1L

200

2L

180

FLAPS 5

FLAPS 3

FLAPS 6

160

3R

3L

3R

3L

4L

4R

4L

3000 YES

AGL
NM

FIRST APP WPT

OR

15.0

4R

NO

5R 6R

6

8

GO_AROUND SPEEDS

3/3

CLEAN

1L 2L 3L

200

RETURN

FLAPS 1

FLAPS 3

FLAPS 2

FLAPS 4

180

140

160

120

PERFORMANCE INIT

9 1R 2R

ACFT TYPE

1L 2L

E170-C2

PERF MODE

FULL PERF CLIMB

MAN

PERFORMANCE

1/3

# PP-XJI

TAIL

OR

SPD

INIT-KG

2/3

STEP INCREMENT

1L

1R 2R

10

4000

1R

FUEL RESERVE

2L

800 KG

2R

OR

TO/LDG FUEL

OR

3R

3L

LRC

OR

4R

4L

290/.77M/3.0

OR

5R

5L

5R

ACFT DB

6R

6L

6R

290/.70M

3R

3L

4L

4R

4L

5L

5R

5L

6L

6R

6L

DEP/APP SPD

CRUISE

DESCENT

110/70 KG

3R

CONTINGENCY FUEL

300 KG

4R

11

PERFORMANCE

12

INIT-KG

PERFORMANCE INIT

2/3

STEP INCREMENT

1L 2L 3L

RETURN

1R

1L

4000

AT DEST OR

ALTN IF ENTERED

2R

2L

800 KG

1L

1R

FUEL RESERVE

800 KG (ACT)

OR

2R

13

2L

TO/LDG FUEL

3R

3L

4L

4R

4L

5L

5R

6L

6R

MIN

TRANS ALT

5000

INIT CRZ ALT

OPTIMUM

CRZ WINDS

110/70 KG

3R

3L

4R

4L

5L

5R

5L

6L

6R

6L

CONTINGENCY FUEL

300T/30 ZFW

300 KG

25000

3/3

SPD/ALT LIM

250/10000 +0 C

2R

AT ALTITUDE

FL100

FUEL (GAUGE) (5000) 5000 GROSS WT

30000

PERF PLAN

1R

ISA DEV

CONFIRM INIT

3R 4R 5R 6R

PERFORMANCE INITIALIZATION 2/2

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 50

Flight Management System

REVISION 21

AOM-1502-003

1/1

EM170AOM140444F.DGN

FUEL RESERVE

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

PERFORMANCE DATA CHECK 1 - On PERFORMANCE INIT 3/3 page press LSK 6R (CONFIRM INIT). On the PERF DATA page the following data displays for destination and alternate: – Cruise and ceiling altitudes. – Step increments. – Estimated time enroute. – Estimated time arrival. – Distance. – Fuel requirement. – Fuel figure of merit (accuracy of the fuel required). – Fuel remaining. – Gross weight. The cruise altitude and step increments can be changed by entering in the scratchpad through alphanumeric keys and pressing respectively LSK 1L or LSK 1R. 2 - Press NEXT button to go to PERF DATA 2/3 page. On this page the following information is displayed: – Average cruise wind. – Preflight fuel remaining. – Latest estimated fuel remaining. – Difference between preflight and estimated fuel remaining. 3 - Press NEXT button to go PERF DATA 3/3 page. On this page the following information is displayed: – Required fuel reserve. – Predicted fuel remaining. AOM-1502-003

– Updated plan (most recent of the fuel remaining).

14-09-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 51

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 52

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

PERFORMANCE INIT TRANS ALT 1L 2L

250/10000

OPTIMUM 300T/30 25000

6L

FL400/FL408

+0 C

2R

2L

13+35


2.0

> >

25.7

TAKEOFF

PERF INIT

4R

0.7 5R 6R

2

1L

PERF DATA

2/3 >

AVG WIND

HW 00

1L

1R

PREFLIGHT PLAN UPDATE PLAN

3L

DIFFERENCE

800 KG 0.0

5L PERF INIT

2R

3

2.1 +2.1

4L

6L

1R

AT ALTN

DEST FUEL REMAINING 2L

3/3

FUEL RESERVE

TAKEOFF

2L

REQ/PLAN

0.8/0.0

UPDATE PLAN

3R

3L

4R

4L

5R

5L

6R

6L

2R

0.7 +0.7

DIFFERENCE

3R 4R 5R

PERF INIT

TAKEOFF

6R

EM170AOM140445C.DGN

PERF DATA CRZ < 300T/16

AOM-1502-003

PERFORMANCE DATA CHECK

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

TAKEOFF

!MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

1 - On PERF DATA page press LSK 6R (TAKEOFF) to enter in the TAKEOFF 1/3 page. On TAKEOFF 1/3 page the following information is displayed: – Runway number and ICAO identifier. – Runway heading. – Runway length. – Outside air temperature. – Surface wind. – Pressure altitude. – Baro settings. – Runway elevation. Temperature, surface wind, and baro settings can be entered. The entry is accomplished in the scratchpad through alphanumeric keys and pressing the respective LSK. 2 - Press NEXT button to go to TAKEOFF 2/3 page. The following information is displayed: – Runway slope. – Runway threshold. – Runway stopway. – Headwind/tailwind and crosswind. – Density altitude. With exception of density altitude the others information can be entered. The entry is accomplished in the scratchpad through alphanumeric keys and pressing the respective LSK.

AOM-1502-003

3 - Press NEXT button to go to TAKEOFF page 3/3. Enter with V1, VR, V2 and VFS. The entry is accomplished in the scratchpad through alphanumeric keys and pressing the respective LSK.

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REVISION 21

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AIRPLANE OPERATIONS MANUAL

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

!!MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

PERF DATA

TAKEOFF

3/3

FUEL RESERVE 1L

RUNWAY

1L

1R

AT ALTN 800 KG

2L

REQ/PLAN UPDATE PLAN

3L

0.8/0.0

2L

2R

0.7 3R

3L

4R

4L

5L

5R

6L

PERF INIT

+0.7

TAKEOFF

LENGTH

155

9843

6R

1

+31

C/+88

F

---

2031/29.92

5L 6L

SLOPE

/---

1L

1R

OAT WIND

P ALT/B SET

4L

DIFFERENCE

HDG

15 SBSJ

TAKEOFF

1/3

2R

2

2L

ELEV

2031

2/3 THRSHLD

0.9%

STOPWAY

0

WIND

1066

1R 2R

DENSITY ALT

4218

3R

3L

4R

4L

4R

DEPARTURE

5R

5L

5R

CLIMB

6R

6L

PERF DATA

3R

PERF DATA

CLIMB

6R

3

TAKEOFF V1

---

---

3L

---

3/3 VFS

V1

1R

1L

110

2R

2L

120

3R

3L

140

4L

4R

4L

4R

5L

5R

5L

5R

6R

6L

---

VR

V2

6L

180

1R

VR 2R

V2

PERF DATA

CLIMB

3R

CLEAR

CLIMB

3

6R

EM170AOM140447C.DGN

1L 2L

TAKEOFF

3/3 VFS

AOM-1502-003

TAKEOFF

14-09-25

"" "

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REVISION 21

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AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

TAKEOFF

!MAU load 19.3 and on OR POST-MOD SB 170-31-0019

1 - On PERF DATA page press LSK 6R (TAKEOFF) to enter in the TAKEOFF 1/3 page. On TAKEOFF 1/3 page the following information is displayed: – Runway heading. – Takeoff weight. – Static air temperature. – Surface wind. – Pressure altitude. – Baro settings. – Runway slope. – Headwind/tailwind and crosswind. – Runway elevation. – Runway condition. Takeoff weight, temperature, surface wind, baro settings and runway condition can be entered. The entry is accomplished in the scratchpad through alphanumeric keys and/or pressing the respective LSK. NOTE: – If no departure runway is selected on the FMS or the runway heading is manually inserted by the pilot on the TAKEOFF page, the scratchpad will present the EXCEEDS P ALTITUDE LIMIT message every time the airplane climbs through 15000 ft. – The information entered on RWY CONDITION is not used for FMS computations. 2 - Press NEXT button to go to TAKEOFF 2/3 page. The following information is displayed: – Flaps.

AOM-1502-003

– Takeoff mode. – ATTCS.

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

The entry of the information is accomplished in the scratchpad through the respective LSK.

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REVISION 21

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3 - Press NEXT button to go to TAKEOFF page 3/3. Enter with V1, VR, V2, VFS and crosscheck the takeoff pitch angle. The entry is accomplished in the scratchpad through alphanumeric keys and pressing the respective LSK.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

!!MAU load 19.3 and on OR POST-MOD SB 170-31-0019

PERF DATA

TAKEOFF

3/3

FUEL RESERVE 1L 30 MIN REQ/PLAN

2L

*

RWY HDG

AT ALTN 5000

*

1R

1L

155 OAT
WIND ELEV 2031 WIND

2R

T/O LANDING

C/ +51

FLAPS

WGT

P ALT/B SET 2031/1013 RWY SLOPE 1.0X RWY CONDITION

1R

VR V2

SURFACE

3/3

V1

3L

5L

1

6R

1/3 T.O.

AOM-1502-003

TAKEOFF

14-09-25

"" "

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REVISION 21

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

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AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

DEPARTURE

!MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

1 - On TAKEOFF 3/3 page press NEXT button to go to TAKEOFF 1/3 page and press LSK 5R (DEPARTURE). 2 - On the DEPARTURE RUNWAYS page selects the runway by pressing the respective LSK. 3 - On SIDs page selects the SID by pressing the respective LSK. 4 - On the DEPARTURE TRANS page selects the departure transition by pressing the respective LSK. 5 - On PROCEDURE page press LSK 6R (INSERT).

AOM-1502-003

6 - Activate the flight plan by pressing the LSK 6R (ACTIVATE) on MOD FLT PLAN page. Check if there is no discontinuity between waypoint scrolling with the next button.

14-09-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

!!MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

TAKEOFF RUNWAY

1L

15 SBSJ

HDG

155

9843

+31

3L

2031/29.92

C/+88

F

P ALT/B SET

---

5L PERF DATA

1L

3L

SBSJ

1R

1L

SBSJ RW15

1R

2R

2L

15

2R

2L

CACI

MIDO

2R

3R

3L

33

3R

3L

CACO

MOCA

3R

4R

4L

4R

4L

FAME

OREN

4R

5R

5L

LUSO

6R

6L

1

DEPARTURE

5R

5L

CLIMB

6R

6L

TAKEOFF

PROCEDURE

1/1

SBSJ RW15 OREN

SBSJ RW15 OREN.PCL

1R

1L

PCL

2R

2R

2L

VGH

3R

3L

3R

3L

IJNB

4R

4L

4R

4L

OREN

5R

5L 6L

5R REVIEW

INSERT

6R

5

5L 6L

1R

0.9NM 00+00

CLB /2520 A

2R

8.0NM 00+01

/

3R

355

10.0NM 00+02

/

4R

355

11.4NM 00+02

155

F

*ALT02 R005

6R

1/6

RW15 SBSJ

1L

INSERT

5R 6R

3

ORIGIN/ETD

2L

5L

PINO INSERT

MOD FLT PLAN

1/1

1R

REVIEW

1/2

/---

4L

6L

1L

SIDs

1/1

2031

DEPARTURE TRANS

2L

2

ELEV

4L

4

1R

OAT WIND

2L

6L

DEPARTURE RUNWAYS

1/3 LENGTH

BGC30

CLB /FL085 A ACTIVATE

CANCEL

5R 6R

6

ACTIVE FLT PLAN

1/6

ORIGIN/ETD

RW15 SBSJ

CLB /2520 A

2R

8.0NM 00+01

/

3R

355

10.0NM 00+02

/

4R

355

11.4NM 00+02

F

*ALT02 R005

3L

IJNB

4L

OREN

5L 6L

1R

0.9NM 00+00

155

BGC30

DEPARTURE

CLB /FL085 A PERF INIT

5R 6R

EM170AOM140446D.DGN

1L 2L

AOM-1502-003

DEPARTURE

14-09-25

"" "

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REVISION 21

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AIRPLANE OPERATIONS MANUAL

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

DEPARTURE

!MAU load 19.3 and on OR POST-MOD SB 170-31-0019

1 - The DEPARTURE page can be selected either on NAV INDEX or RTE pages by pressing the respective LSK. 2 - On the DEPARTURE RUNWAYS page selects the runway by pressing the respective LSK. 3 - On SIDs page selects the SID by pressing the respective LSK. 4 - On the DEPARTURE TRANS page selects the departure transition by pressing the respective LSK. 5 - On PROCEDURE page press LSK 6R (INSERT).

AOM-1502-003

6 - Activate the flight route by pressing the LSK 6R (ACTIVATE) on the MOD RTE page. Check if there is no discontinuity between waypoint scrolling with the next button.

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REVISION 21

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

!!MAU load 19.3 and on OR POST-MOD SB 170-31-0019

RTE 1L

DEPARTURE RUNWAYS

4/5

VIA

TO

DIRECT

SBFL DEST

1R

2

1L

SBSJ

SIDs

1/1 1R

1L

1/2

SBSJ RW15

1R

2R

2L

15

2R

2L

CACI

MIDO

2R

3L

3R

3L

33

3R

3L

CACO

MOCA

3R

4L

4R

4L

4R

4L

FAME

TORUK

4R

5R

5L

5R

5L

LUSO

6R

6L

6R

6L

2L

SBFL

5L 6L

DEPARTURE

PERF INIT

TAKEOFF

XUXIT

5R

INSERT

6R

3

1

DEPARTURE TRANS 4

1L

SBSJ RW15 TORUK

2L

RDE

3L

SAT

PROCEDURE

1/1 1R

1L

2R

2L

MOD RTE

1/1 VIA

SBSJ RW15 TORUK.RDE

1R

1L

2R

2L

3R

3L

3R

3L

4L

4R

4L

4R

4L

5L

5R

5L

5R

6R

6L

6L

REVIEW

INSERT

REVIEW

*ALT15

DIRECT TORUK.RDE

RDE

DIRECT

6L

CANCEL

1R 2R

SBFL

3R

DEST

4R

SBFL

5L

5

6R

INSERT

2/3 TO

ACTIVATE

5R 6R

6

ACT RTE 1L 2L 3L

DIRECT TORUK.RDE DIRECT

4L

*ALT15

1R 2R

RDE

SBFL

3R

DEST

4R

SBFL

5L 6L

2/3 TO

DEPARTURE

PERF INIT

5R 6R

EM170AOM140731A.DGN

VIA

AOM-1502-003

DEPARTURE

14-09-25

"" "

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REVISION 21

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

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AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

LANDING SPEEDS

!MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

1 - Press Perf button to go to PERF INDEX 1/2 page. 2 - Press LSK 4R (LANDING) to go to LANDING 1/3 page. 3 - Access the LANDING 3/3 page by pressing the NEXT button twice.

AOM-1502-003

4 - Enter with VREF, VAP, VAC and VFS for the departure runway. The entry is accomplished in the scratchpad through alphanumeric keys and pressing the respective LSK.

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REVISION 21

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

!!MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

PERF INDEX

LANDING

1/2 RUNWAY

1L

PERF DATA

PERF INIT

1L

1R

10 SBEG

LENGTH

103

8858

OAT < --- SURFACE --- >

1

2L

PERF PLAN

3L

CLIMB

4L

DESCENT

5L

INIT

6L

INIT

TAKEOFF

2R

2L 3L

CRUISE

3R

LANDING

4R

4L

DATA

5R

5L

DATA

6R

6L

2

---

C/---

F

--- /--ELEV

1L

1R

0.1%

0

1R

WIND 2R

3

2L

DENSITY ALT

2R

3R

3L

3R

4R

4L

4R

ARRIVAL

5R

5L

5R

FPL PLAN

6R

6L

0252

DESCENT

2/3 THRSHLD

SHOPE

WIND

P ALT/B SET 0252/29.92

LANDING

1/3

HDG

DESCENT

FLT PLAN

6R

3

LANDING

3/3 VFS

1L

VREF

1L

1R VAP

120

3/3 VFS

180

1R

VAP

2R

2L

130

3L

3R

3L

140

4L

4R

4L

4R

5L

5R

5L

5R

6R

6L

2L

VAC

6L

DESCENT

2R

VAC

FLT PLAN

CLEAR

3R

FLT PLAN

EM170AOM140448B.DGN

LANDING VREF

6R

4

AOM-1502-003

LANDING SPEEDS

14-09-25

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REVISION 21

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AIRPLANE OPERATIONS MANUAL

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

LANDING SPEEDS

!MAU load 19.3 and on OR POST-MOD SB 170-31-0019

1 - Press Perf button to go to PERF INDEX 1/2 page. 2 - Press LSK 4R (LANDING) to go to LANDING 1/2 page. NOTE: The information entered on APPROACH FLAP, LANDING FLAP, ICE and APPROACH TYPE are not used for FMS computations. 3 - Access the LANDING 2/2 page by pressing the NEXT button.

AOM-1502-003

4 - Enter with VREF, VAP, VAC and VFS for the departure runway. The entry is accomplished in the scratchpad through alphanumeric keys and pressing the respective LSK.

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REVISION 21

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AIRPLANE OPERATIONS MANUAL

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

!!MAU load 19.3 and on OR POST-MOD SB 170-31-0019

PERF INDEX

LANDING

1/2

1/2

RWY OAT

1

1L

PERF INIT

2L

PERF PLAN

3L

CLIMB

4L

DESCENT

5L

INIT

6L

INIT

LND WGT

PERF DATA

1R

1L

+15 C/+59 F

TAKEOFF

2R

2L

APPROACH FLAP FLAP-2 LANDING FLAP

CRUISE

3R

3L

FLAP-FULL ICE

LANDING

4R

4L

NO

DATA

5R

5L

DATA

6R

6L

2

LANDING

21975LB

1R

OR FLAP-4

2R

OR FLAP-5

3R

OR

YES

4R

OR

5R

DATA

6R

APPROACH TYPE CAT-1 PERF DATA

T.O.

LANDING

2/2

VREF 1L 2L

1R VAP 2R VAC

1L

1R

2L

VAP 130

2R 3R 4R

3L

4L

4R

4L

VFS 180

5L

5R

5L

6R

6L

3R

4

VFS

DESCENT

FLT PLAN

5R PERF DATA

FLT PLAN

6R

EM170AOM140732A.DGN

6L

2/2

VREF 120

VAC 140

3L

3

AOM-1502-003

LANDING SPEEDS

14-09-25

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AIRPLANE OPERATIONS MANUAL

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

PROGRESS 1 - Press PROG button to go to PROGRESS 1/3 page. On PROGRESS 1/3 page the following information is displayed for the to, next and destination waypoints: – Distance to go. – Estimated time enroute. – Estimated fuel remaining. – Primary navigation source. – Required navigation performance (RNP) value. – Estimated position uncertainty (EPU) value. If EPU becomes greater than RNP the message UNABLE RNP is displayed. – Tuned navigation radios frequencies. Any active waypoint entry is permitted. The entry is accomplished in the scratchpad through alphanumeric keys and pressing the respective LSK (1L or 2L). 2 - Pressing LSK 6L or 6R (NAV 1/NAV 2) enters respectively in the NAV 1 or NAV 2 page. 3 - A list of 10 closest navigation frequencies is displayed. To tune a frequency press the respective LSK or press LSK 6L (PROGRESS) to return to PROGRESS 1/3 page. 4 - Press NEXT button to go to PROGRESS 2/3 page. The following information is displayed: – Current fuel quantity. – Current airplane Gross weight.

AOM-1502-003

5 - Pressing LSK 6L (RNP) enters in the RNP 1/1 page. The following information is displayed: – Manual override RNP value at LSK 1L. If one does not exist, then entry prompts are displayed. Entry of DELETE clears the manual override RNP value.

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

– Departure RNP value at LSK 2L. – Approach RNP value at LSK 2R. – Enroute /remote RNP values at LSK 3L. – Missed approach RNP value at LSK 3R. The default RNP values for each phase of flight are displayed in small characters. The pilot can manually enter new RNP values that are displayed in large characters. The entry is accomplished in the scratchpad through alphanumeric keys and pressing the respective LSK. Entry of DELETE returns the default value. A confirm entry prompt is displayed if the pilot has entered a manual override RNP value that is higher than default. The selection of the YES prompt at LSK 6R accepts the entered value as the new manual override RNP value and the selection of the NO prompt at LSK 6L causes the manual override RNP to return to the original value. A lower RNP value is accepted and gives access to PROGRESS page 2. !Airplanes Pre-Mod MAU load 23.1

NOTE: The default RNP values for the approach phase are displayed on the MCDU when the airplane is at 2 NM outside of the FAF, at the same time of the APPR annunciation on the PFD. " !MAU load 23.1 and on

NOTE: The default RNP values for the approach phase are displayed on the MCDU when the airplane is at the IAF. "

6 - Press LSK 6R (PROGRESS 2) to return to PROGRESS 2/3 page. 7 - Press the LSK 6R to enter the VNAV DATA page. On this page, the following information displays. – VNAV Figure of Merit at LSK 1L.

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AOM-1502-003

– Vertical Deviation at LSK 1R.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

– TOC pseudo waypoint distance/time to go at LSK 2L and TOC altitude at LSK 2R. – TOD pseudo waypoint distance/time to go at LSK 3L and TOD altitude at LSK 3R. – Bottom of Descent (BOD) pseudo waypoint distance/time to go at LSK 3L and BOD altitude at LSK 3R. 8 - Press NEXT button to go to PROGRESS 3/3 page. The following information is displayed: – Cross track error. – Off set entry. – Airplane track. – Airplane drift. – Airplane heading. – Wind. – Ground speed. 9 - Pressing LSK 6L (AIR DATA) enters in the AIR DATA 1/1 page. The following information is displayed: – Pressure altitude. – Barometric altitude. – Vertical speed. – Static air temperature. – ISA deviation. – Total air temperature. 10 - Press LSK 6R (PROGRESS 3) to return to PROGRESS 3/3 page. 11 - Pressing LSK 6R (FLT SUM) entries in the FLIGHT SUMMARY 1/1 page.

AOM-1502-003

The following information is displayed: – Takeoff time.

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SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

– Enroute time. – Landing time. – Fuel used. – Average true air speed/ground speed. – Air distance. – Ground distance.

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REVISION 21

AOM-1502-003

12 - Press LSK 6R (PROGRESS 3) to return to PROGRESS 3/3 page.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

!MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

PROGRESS DIST

TO

1

PCLNB

17.1

00+03

2L

KERBO

62.1

00+09

6.0

3L

SBEG

1438

03+31

1.7

4L 5L 6L

DEST

GPS R---

RNP = 1.00

115.60

NAV 1

6.2

EPU = 0.13 R---

PROGRESS

1/ 1

FUEL

1L

NEXT

NAV 1

1/3

ETE

111.50 NAV 2

DIST

TO

1L

1R

2L

2R 3R

3L

4R

4L

5R

5L 6L

6R

2

ARX 117.00

BHZ 117.70

ULD 116.10

BGC 116.20

TRM 114.70

CPN 112.00

PSN 113.30

LUZ 113.10

CNF 114.40

GOI 112.70

1R 2R

FUEL

1L

PCLNB

17.1

00+03

6.2

1R

2L

KERBO

62.1

00+09

6.0

2R

SBEG

1438

03+31

1.7

3R

3L

4R

4L

5R

5L

6R

6L

PROGRESS

1/3

ETE

NEXT DEST

GPS R---

RNP = 1.00

115.60

NAV 1

3R 4R

EPU = 0.13 R---

111.50

5R

NAV 2

6R

3 4

PROGRESS

RNP

2/3

SPD/ALT CMD 1L

TOC

FUEL QTY

1L

1R

3L

4L

4R

4L

4R

5R

5L

5R

5L

5R

6R

6L

4R

5L VNAV DATA

1R

FUEL QTY

2L

4L

RNP

TOC

2R

3L

6L

1L

1R

3R

2L

3R

CROSS WT

1.00

APPR

DEPARTURE

2/3

SPD/ALT CMD

1.00

2R

31243

TOD

3L

ARRIVAL

0.30

6243

2L

PROGRESS

1/1

MANUAL --.-1.00 ENRT/REMOTE

MISSED APP

2.00/10.00

PROGRESS 2

6

6L

6R

TOD

6243

2R

31243

3R

CROSS WT

RNP

VNAV DATA

6R

5 7

1L

36 FT

+59 FT DIST/ETE

2L

3.5 45.0 15.0

PROGRESS

1/1

/00+01 /00+10 /00+05

PROGRESS

2/3

SPD/ALT CMD

VERT DEV 1R

1L

ALT

TOC

FUEL QTY

1R

6243

2R

31243

3R

8

1L

XTK ERROR 0.00NM

2L

355

3L

000T/1

TRACK

3/3 OFFSET

- --.- NM

DRIFT

HDG

355

0

1R

2R

2L

3R

3L

4L

4R

4L

4R

4L

4R

5L

5R

5L

5R

5L

5R

6R

6L

6R

6L

3L

6L

TOC TOD BOD

PERF INIT

NM NM NM

PROGRESS 2

TOD

RNP

CROSS WT

VNAV DATA

9

WIND

AIR DATA

>

DIRECT-TO

1/5

5R

CLB SPD

2026Z >> DISCONTINUITY

4L

4

ACTIVE FLT PLAN

1/5

.78M/FLP330

2103Z

6L

DES

700 3.0

/ 4000

ACTIVATE

1R 2R 3R 4R 5R 6R

8

EM170AOM980103B.DGN

ACTIVE FLT PLAN

AOM-1502-003

DIRECT-TO

14-09-25

"" "

Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 89

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 90

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

PATTERNS HOLDING 1 - Press NAV button to go to NAV INDEX 1/2 page. 2 - On NAV INDEX 1/2 page press LSK 5R (HOLD). 3 - On ACTIVE FLT PLAN page press the respective LSK correspondent to the desired holding waypoint. If the desired hold waypoint is not displayed press NEXT button until it appears. On the HOLDING PATTERN 1/1 page the following information is displayed: – Hold fix name. – Speed. – Quadrant entry. The possible entries are N, NE, E, SE, S, SW, W or NW. – Entry type. – Leg time. – Inbound course/turn direction. The possible entries are course followed by a slash and then a L (left) or R (right), only the course or only the slash followed by a L (left) or R (right). – Leg distance. – Expected further clearance (EFC) time. When a valid Hold EFC time is inserted and activated, all time and fuel predictions for waypoints beyond the Hold are based on remaining in the hold until the expected clearance time has elapsed. 4 - Press LSK 6R (INSERT).

AOM-1502-003

5 - On MOD FLT PLAN page press LSK 6R (ACTIVATE).

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REVISION 21

Flight Management System

Page 91

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 92

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

3

NAV INDEX 1L

1

2L 3L

FPL LIST POS SENSORS

5L

FIX INFO

FLT SUM

HOLD ARRIVAL

DEPARTURE

HOLD FIX

1L

OREN

355

2L

BGC30

3.0NM 1521Z

CLB 250/FL085A

355

3R

3L

PCLNB

69.5NM 1540Z

1500 .70M/FL267

4R

4L

KERBO

44.9NM 1553Z

900 .70M/FL346

5L

ARX

86.8NM 1617Z

.77M/FL400

6L

DEPARTURE

2R

WPT LIST

2

5R 6R

007

007

PERF PLAN

*HOLD*

HOLDING PATTERN

1/6

1517Z

1R

NAV IDENT

4L

6L

ACTIVE FLT PLAN

1/2

1R 2R

1L 2L

BGC30

QUAD ENTRY DIRECT S INBD CRS/DIR

3R

3L

4R

4L

5R

5L

6R

6L

1/ 1

SPEED 200

1R

LEG TIME 1.5MIN

2R

LEG DIST

355 /R TURN

8.8NM

3R

EFC TIME

1242Z

4R 5R

CLEAR

INSERT

6R

4

1L

OREN

1517Z

355

2L

BGC30 H

2.3NM 1521Z

CLB 250/FL085A

355

3L

PCLNB

69.5NM 1548Z

1500 .70M/FL267

4L

KERBO

44.9NM 1601Z

900 .70M/FL346

5L

ARX

86.8NM 1625Z

.77M/FL400

6L

CANCEL

007

007

ACTIVE FLT PLAN

1/6

ACTIVATE

1L

1R

1/6

OREN

1517Z

355

BGC30 H

2.1NM 1520Z

CLB 250/FL085A

355

2R

2L

3R

3L

PCLNB

69.5NM 1548Z

1500 .70M/FL267

4R

4L

KERBO

44.9NM 1601Z

900 .70M/FL346

5L

ARX

86.8NM 1625Z

.77M/FL400

6L

EXIT

5R 6R

5

007

007

PERF PLAN

1R 2R 3R

EM170AOM140454C.DGN

MOD FLT PLAN

4R 5R 6R

AOM-1502-003

HOLDING

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REVISION 21

Flight Management System

Page 93

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 94

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

FLYOVER The flyover is used to proceed to a waypoint before commencing the turn. 1 - Press NAV button to enter in the NAV INDEX 1/2 page. 2 - Press NEXT button to go to NAV INDEX 2/2 page. 3 - Press LSK 3L (PATTERNS) to enter in the PATTERNS 1/1 page. 4 - Press LSK 2L (FLYOVER).

AOM-1502-003

5 - On ACTIVE FLT PLAN page press the respective LSK correspondent to the desired flyover waypoint. If the desired flyover waypoint is not displayed press NEXT button until it appears.

14-09-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 95

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

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Page 96

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

3

1L 2L 3L

CRISE

1440Z

.76M/FL380

1R

007

39.9NM 00+05

.76M/FL380

2R

335

39.9NM 00+06

.76M/FL380

3R

3L

399NM 00+55

.75M/FL380

4R

4L

POS SENSORS

125NM 00+18

.75M/FL380

5R

5L

FIX INFO

TAKEOFF

6R

6L

DEPARTURE

BRS

EROG

335

4L

NABOL

5L

TAROP

6L

DEPARTURE

334

PATTERNS 4

1L 2L

NAV INDEX

1/4

HOLD FLYOVER

1

1L

NAV IDENT

1R

2L

WPT LIST

2R

1L

1R

2L

2R

CRISE

3L

PATTERNS

6R

6L

6R

ACTIVE FLT PLAN

1/4

.76M/FL380

1R

1L

CRISE

1440Z

.76M/FL380

1R

.76M/FL380

2R

335

39.9NM 00+06

.76M/FL380

3R

399NM 00+55

.75M/FL380

4R

125NM 00+18

.75M/FL380

5R

TAKEOFF

6R

NABOL

125NM 00+18

.75M/FL380

5R

5L

TAROP F

6R

6L

DEPARTURE

TAROP

334

2R

2L

BRS

EROG

335 334

DEPARTURE *FLYOVER*

TAKEOFF

1/4

39.9NM 00+05

3L

.76M/FL380

4R

007

4L

NABOL

3R

ARRIVAL

3R

5L

CROSS PTS

5R

4R

5R

2R

5L

.76M/FL380

5L

MAINTENANCE

5R

.75M/FL380

335

1R

4R

399NM 00+55

EROG

3L

CONVERSION

HOLD

39.9NM 00+06

4L

6L

DATA LOAD

335

BRS

3R

6R

2L

39.9NM 00+05

4R

REVIEW

POS INIT

007

3L

5

1440Z

3R

2

1L

2/2

4L

ACTIVE FLT PLAN

4L

6L

FLT SUM

FPL LIST

1/ 1

PCDR TURN

NAV INDEX

1/2

EM170AOM140465B.DGN

ACTIVE FLT PLAN

AOM-1502-003

FLYOVER

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REVISION 21

Flight Management System

Page 97

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 98

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

PROCEDURE TURN The procedure turn is used to reverse the course during an approach. A procedure turn is only available from approaches in the navigation data base. 1 - Press NAV button to enter in the NAV INDEX 1/2 page. 2 - Press NEXT button to enter in the NAV INDEX 2/2 page. 3 - Press LSK 3L (PATTERNS) to go to PATTERNS 1/1 page. 4 - Press LSK 1R (PCDR TURN) to go to PROCEDURE TURN 1/1 page. 5 - On the PROCEDURE TURN 1/1 page the following information is displayed: – Procedure turn fix. – Boundary distance. – Procedure turn angle. The entry is L (left) or R (right) followed by the turn angle. – Inbound course. – Outbound time. – Outbound distance. The outbound time/distance and procedure turn angle can be changed. The entry is accomplished in the scratchpad through alphanumeric keys and pressing the respective LSK. 6 - Press LSK 6R (ACTIVATE) to go to ACTIVE FLT PLAN page.

AOM-1502-003

7 - After passing the procedure turn fix press LSK 6L (TURN).

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REVISION 21

Flight Management System

Page 99

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 100

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

3

ACTIVE FLT PLAN 329

1L 2L 3L

NAV INDEX

1/3

41.5NM 1125Z

DES 3.0 /2000A

1R

329

2.3NM 1126Z

DES 500 3.0 /1500A

2R

149

3.5NM 1126Z

DES 500 3.0 /1500A

149

3.5NM 1128Z

DES 500 3.1 /0320

103

3.5NM 1128Z

DES 500 3.1 /0320 ARRIVAL

CF10

P

*INTO1 CF10

4L

FF10

5L

RW10

6L

NAV INDEX

1/2

1L

NAV IDENT

1R

1L

POS INIT

2L

WPT LIST

2R

2L

DATA LOAD

3R

3L

FPL LIST

3L

PATTERNS

4R

4L

POS SENSORS

5R

5L

FIX INFO

6R

6L

DEPARTURE

1

FLT SUM

3R

2

2/2

CONVERSION

1R

MAINTENANCE

2R

CROSS PTS

3R

4R

4L

4R

HOLD

5R

5L

5R

ARRIVAL

6R

6L

6R

5

PATTERNS

PROCEDURE TURN

1/ 1

4 1L

HOLD

PCDR TURN

PT

1L

1R

CF10

PT 2R

2L

3L

3R

3L

4L

4R

5L

2L

FLYOVER

ANG(CRS)

REVIEW

PT

1R

1L

TIME

CF10

PT

1/ 1

FIX BOUNDARY DIST 41.5 NM ANG(CRS)

OUTBD

1R

TIME

2R

2L

3R

3L

4L

4R

4L

4R

5R

5L

5R

5L

5R

6R

6L

6R

6L

L45 (185 ) INBD

6L

OUTBD

PROCEDURE TURN

1/ 1

FIX BOUNDARY DIST 41.5 NM 1.0

CRS

OUTBD

050

MIN

DIST 3.5

MIN

DELETE

L30 (185 ) INBD

1.0

CRS

OUTBD

050

MIN

2R

DIST 3.5

MIN

ACTIVATE

3R

6R

6

1L 2L

41.5NM 1125Z

329

2.3NM 1126Z

DES 500 3.0 /1500A

2R

2L

149

3.5NM 1126Z

DES 500 3.0 /1500A

3R

3L

CF10

3.5NM 1128Z

DES 500 3.1 /0320

4R

4L

FF10

3.5NM 1128Z

DES 500 3.1 /0320

5R

5L

RW10

ARRIVAL

6R

6L

TURN

CF10

P

*INTO1

3L

CF10

4L

FF10

5L

RW10

149 103

6L

ACTIVE FLT PLAN

1/3

DES 3.0 /2000A

1L

1R

PROCEDURE TURN

ACTIVE FLT PLAN

1/3 1R

1L

PROCEDURE TURN

329

2.3NM 1126Z

DES 500 3.0 /1500A

2R

2L

149

3.5NM 1126Z

DES 500 3.0 /1500A

3R

3L

CF10

3.5NM 1128Z

DES 500 3.1 /0320

4R

4L

FF10

3.5NM 1128Z

DES 500 3.1 /0320

5R

5L

RW10

ARRIVAL

6R

6L

*INTO1 149 103

1/3 1R

329

2.3NM 1126Z

DES 500 3.0 /1500A

149

3.5NM 1126Z

DES 500 3.0 /1500A

3R

149

3.5NM 1128Z

DES 500 3.1 /0320

4R

3.5NM 1128Z

DES 500 3.1 /0320

5R

ARRIVAL

6R

*INTO1

103

7

2R

EM170AOM140464B.DGN

ACTIVE FLT PLAN 329

AOM-1502-003

PROCEDURE TURN

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REVISION 21

Flight Management System

Page 101

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

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Page 102

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

CROSSING POINTS The crossing points are used to determine some information regarding a waypoint relative to the current airplane position. The following types of crossing points are presented: – Present position direct to a waypoint from the current airplane position. – Crossing radial from a waypoint for the current airplane position. – Equal time point between any two given waypoints. This option is only available when operating in full performance mode. – Latitude/longitude crossing for the current flight plan. – Point abeam a waypoint for current flight plan. – Point of no return from any given waypoint. This option is only available when operating in full performance mode. 1 - Press NAV button to go to NAV INDEX 1/2 page. 2 - Press NEXT button to go to NAV INDEX 2/2 page. 3 - Press LSK 3R (CROSS PTS) to enter in the CROSSING POINTS 1/1 page.

PRESENT POSITION DIRECT 1 - On CROSSING POINTS 1/1 page press LSK 1L (PPOS DIR) to go to PPOS DIRECT 1/1 page. 2 - Enter with the waypoint name. The entry is accomplished in the scratchpad through alphanumeric keys and pressing LSK 1L. After the entry the following information is displayed: – Course to the waypoint. – Distance to the waypoint. – Estimated time enroute.

AOM-1502-003

– Remaining fuel in the waypoint.

14-09-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Flight Management System

Page 103

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

1

NAV INDEX 1L

NAV IDENT

2L

WPT LIST

3L

FPL LIST

4L

POS SENSORS

5L

FIX INFO

6L

DEPARTURE

1/2 1R 2R FLT SUM

3R 4R

HOLD

5R

ARRIVAL

6R

2

NAV INDEX POS INIT

2L

DATA LOAD

3L

CONVERSION

1R

MAINTENANCE

2R

CROSS PTS

3R

PATTERNS

4L

4R

5L

5R

6L

6R

CROSSING POINTS 1L

PPOS DIR

2L

CROSS RADIAL

3L

EQ TIME PT

1/ 1

LAT/LON

1R

PT ABEAM

2R

PT NO RET

3R

4L

3

4R

5L

5R

6L

6R

EM170AOM140451B.DGN

1L

2/2

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Page 104

Flight Management System

REVISION 21

AOM-1502-003

CROSSING POINTS

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

CROSSING POINTS

1/ 1

1 1L

PPOS DIR

2L

CROSS RADIAL

3L

EQ TIME PT

LAT/LON

1R

PT ABEAM

2R

PT NO RET

3R

4L

4R

5L

5R

6L

6R

PPOS DIRECT 2

1/1

WAYPOINT 1R

----

2R

3L

3R

4L

4R

5L 6L

5R CROSS PTS

6R

PPOS DIRECT WAYPOINT

1L 2L 3L

TRM

DIRECT TO

TRM

CRS

049

DIST 168

229/168 ETE FUEL 00+22 5.7

4L

1R 2R 3R 4R

5L 6L

1/1

RAD/DIS FR

5R CROSS PTS

6R

EM170AOM140461B.DGN

1L 2L

AOM-1502-003

PRESENT POSITION DIRECT

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REVISION 21

Flight Management System

Page 105

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

CROSSING RADIAL 1 - On the CROSSING POINTS 1/1 page press LSK 2L (CROSS RADIAL) to go to CROSS RADIAL 1/1 page. 2 - Enter with the waypoint name. The entry is accomplished in the scratchpad through alphanumeric keys and pressing LSK 1L. 3 - Enter with the cross radial. The entry is accomplished in the scratchpad through alphanumeric keys and pressing LSK 1R. After the entry the following information is displayed: – The distance from the waypoint where the airplane will cross the selected radial. – Course to the waypoint. – Distance to the waypoint. – Estimated time enroute.

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Page 106

Flight Management System

REVISION 21

AOM-1502-003

– Remaining fuel in the waypoint.

AIRPLANE OPERATIONS MANUAL

CROSSING POINTS PPOS DIR

2L

CROSS RADIAL

3L

EQ TIME PT

2

WAYPOINT

LAT/LON

1R

1L

PT ABEAM

2R

2L

----

CROSS RADIAL

1/1

WAYPOINT

CROSS RADIAL

---.-

FLIGHT INSTRUMENTS/COMM/NAV/FMS

1R

1L

2R

2L

TRM

1/1

CROSS RADIAL

---.-

3 1R 2R

3R

3L

3R

3L

3R

4L

4R

4L

4R

4L

4R

5L

5R

5L

5R

5L

5R

6L

6R

6L

6R

6L

PT NO RET

CROSS RADIAL WAYPOINT

TRM

2L

TRM/260.0/117

RADIAL DIRECT TO AT CRS

008

DIST 76.7

260.0

117NM

ETE FUEL 00+10 5.8

1R 2R 3R 4R

5L

5R CROSS PTS

6R

1/1

4L

6L

CROSS PTS

CROSS

1L

3L

CROSS PTS

EM170AOM140462B.DGN

1

1L

CROSS RADIAL

1/ 1

SYSTEMS DESCRIPTION

6R

AOM-1502-003

CROSSING RADIAL

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REVISION 21

Flight Management System

Page 107

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

14-09-25 Copyright © by Embraer. Refer to cover page for details.

Page 108

Flight Management System

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

EQUAL TIME POINT 1 - On the CROSSING POINTS 1/1 page press LSK 3L (EQ TIME PT) to go to EQUAL TIME POINT 1/1 page. 2 - On EQUAL TIME POINT 1/1 page the following information is displayed to the waypoints 1/2 and Equal Time Point (ETP): – Distance to the waypoint. – Estimated time enroute. – Remaining fuel in the waypoint. The default waypoints are the departure and destination airports. It is possible to enter other waypoints. The entry is accomplished in the scratchpad through alphanumeric keys and pressing LSK 1L or 1R. If the airplane has passed the ETP the message PAST is displayed. 3 - Pressing LSK 6R (WIND) enters in the CRUISE ALT WIND 1/1 page. Cruise wind entry can be done for the selected waypoints. The entry is accomplished in the scratchpad through alphanumeric keys and pressing the respective LSK (1R or 2R).

AOM-1502-003

4 - Press LSK 6R (EQ TIME PT) to return to EQUAL TIME POINT 1/1 page.

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

CROSSING POINTS

EQUAL TIME POINT

1/ 1

WPT 1

1L 2L 3L

1

PPOS DIR

LAT/LON

CROSS RADIAL

PT ABEAM

1R 2R

1L 2L

SBSJ

ETE

SBEG

WPT 1

1L

1R

FUEL

D>SBSJ

219

00+44

5.3

D>SBEG

1257

03+10

1.8

FP>ETP

544

01+16

4.0

FLIGHT INSTRUMENTS/COMM/NAV/FMS

CRUISE ALT WIND

1/1

WPT 2 DIST

SYSTEMS DESCRIPTION

SBSJ

000T/00

WPT 2

2L

2R

1/1

WIND

1R

WIND

000T/00

SBEG

2R

3R

3L

3R

3L

3R

4L

4R

4L

4R

4L

4R

5L

5R

5L

5R

5L

5R

6L

6R

6L

EQ TIME PT

PT NO RET

CROSS PTS

WIND

6R

2

6L

CROSS PTS

EQ TIME PT

6R

3

EQUAL TIME POINT 1L 2L 3L

SBSJ

1/1

WPT 2 DIST

ETE

SBEG

1R 2R

FUEL

D>SBSJ

219

00+44

5.3

D>SBEG

1257

03+10

1.8

FP>ETP

544

01+16

4.0

3R

4L

4R

5L

5R

6L

CROSS PTS

WIND

EM170AOM140459B.DGN

WPT 1

6R

AOM-1502-003

EQUAL TIME POINT

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AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

LATITUDE/LONGITUDE CROSSING 1 - On the CROSSING POINTS 1/1 page press LSK 1R (LAT/LON) to go to CROSS LAT/LON 1/1 page. 2 - Enter with the latitude and/or longitude. The entry is accomplished in the scratchpad through alphanumeric keys and pressing the respective LSK (1L or 1R). After the entry the following information is displayed: – Course to the waypoint. – Distance to the waypoint. – Estimated time enroute.

AOM-1502-003

– Remaining fuel in the waypoint.

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AIRPLANE OPERATIONS MANUAL

CROSSING POINTS 1L

PPOS DIR

2L

CROSS RADIAL

3L

EQ TIME PT

1/ 1

LAT/LON

1 1R

PT ABEAM

2R

PT NO RET

3R

4L

4R

5L

5R

6L

6R

CROSS LAT/LON LAT 1L

1/1 LON

---- --.-

--- --. -

1R

2L

2R

3L

3R

4L

4R

5L 6L

5R CROSS PTS

6R

CROSS LAT/LON LAT

1L

S18 12.2

2L

S18 12.2

W047 26.8

008

120

3L

1/1 LON

W047 26.8

DIRECT TO CRS

DIST

ETE

FUEL

00+16

4L

3R 4R

5L 6L

5.7

1R 2R

5R CROSS PTS

6R

EM170AOM140460B.DGN

SYSTEMS DESCRIPTION

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LATITUDE/LONGITUDE CROSSING

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

POINT ABEAM 1 - On the CROSSING POINTS 1/1 page press LSK 2R (PT ABEAM) to go to POINT ABEAM 1/1 page. 2 - Enter with the waypoint name. The entry is accomplished in the scratchpad through alphanumeric keys and pressing LSK 1L. After the entry the following information is displayed: – The radial and distance from the waypoint where the airplane will cross the point abeam. – Course to the waypoint. – Distance to the waypoint. – Estimated time enroute.

AOM-1502-003

– Remaining fuel in the waypoint. If no point abeam exists for the current flight plan the message NO CROSSING POINT FOUND is displayed.

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AIRPLANE OPERATIONS MANUAL

CROSSING POINTS 1L

PPOS DIR

2L

CROSS RADIAL

3L

EQ TIME PT

1/ 1

LAT/LON

1R

PT ABEAM

2R

PT NO RET

3R

4L

4R

5L

5R

6L

6R

POINT ABEAM

2

1

1/1

WAYPOINT

-----

1R 2R

3L

3R

4L

4R

5L 6L

5R 6R

CROSS PTS

POINT ABEAM 1L

TRM

2L

TRM/278/111

3L

008

278/111

DIRECT TO CRS

1/1

PT ABEAM

WAYPOINT

DIST

ETE

95.6

00+12

FUEL

4L

3R 4R

5L 6L

5.7

1R 2R

5R CROSS PTS

6R

EM170AOM140450B.DGN

1L 2L

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POINT ABEAM

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

POINT OF NO RETURN 1 - On the CROSSING POINTS 1/1 page press LSK 3R (PT NO RET) to go to POINT OF NO RETURN 1/1 page. 2 - On POINT OF NO RETURN 1/1 page the following information is displayed for the selected waypoint and point of no return: – Distance to the waypoint. – Estimated time enroute. – Remaining fuel in the waypoint. The default waypoint is the origin. It is possible to enter other waypoints and/or cruise wind. The entry is accomplished in the scratchpad through alphanumeric keys and pressing respectively LSK 1L or 1R. If the airplane has passed the point of no return a message PAST is displayed.

AOM-1502-003

If the point of no return is beyond the destination a message BEYOND DEST is displayed.

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FLIGHT INSTRUMENTS/COMM/NAV/FMS

AIRPLANE OPERATIONS MANUAL

CROSSING POINTS 1L

PPOS DIR

2L

CROSS RADIAL

3L

EQ TIME PT

1/ 1

LAT/LON

1R

PT ABEAM

2R

PT NO RET

3R

4L

4R

5L

5R

6L

6R

POINT OF NO RETURN WPT

1/1

CRZ ALT WIND

1L

SBEG

2L

D>SBEG

1250

FP>PNR

BEYOND DEST

DIST

ETE

000T/00 FUEL

03+13

1.3

1R 2R

3L

3R

4L

4R

5L

5R

6L

1

CROSS PTS

6R

EM170AOM140452B.DGN

SYSTEMS DESCRIPTION

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AOM-1502-003

POINT OF NO RETURN

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

ARRIVAL 1 - When the airplane is within 200 NM to the destination the prompt ARRIVAL appears. Press LSK 6R (ARRIVAL) to enter in the ARRIVAL 1/1 page. 2 - On ARRIVAL page select LSK 1L (RUNWAY) to go to RUNWAY page. 3 - On RUNWAY page select the runway by pressing the respective LSK. 4 - On APPROACH page select approach procedure by pressing the respective LSK. 5 - On APROACH TRANS page select the approach transition by pressing the respective LSK. 6 - On STAR page select the STAR by pressing the respective LSK. 7 - On STAR TRANS page select the STAR transition by pressing the respective LSK. 8 - Press LSK 6R (INSERT) to insert the arrival.

AOM-1502-003

9 - On MOD FLT PLAN page press LSK 6R (ACTIVE) to activate the flight plan.

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AIRPLANE OPERATIONS MANUAL

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INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

ACTIVE FLT PLAN 1L

VIBOT

2L

EGAP

3L

SBEG

1/2

1100Z

352 337

29.3NM 1108Z

290/12000

37.0NM 1126Z

500 100/0260 DEST

SBEG

4L 5L 6L

ARRIVAL

SBEG APPROACH

4

ARRIVAL

2

1/1

SBEG

1R

1L

RUNWAY

1R

1L

10

1R

2L

APPROACH

2R

2L

28

2R

3R

3L

STAR

3R

3L

3R

4R

4L

4R

5R

5L

5R

6R

6L

4R

4L

5R

5L

6R

1

>

6L

LANDING

ARRIVAL

1/1 1R

ILS

1L

10 2L

RUNWAY

2R

2L

10 3L

3R

3L

4L

4R

4L

5L

5R

5L

6R

6L

6L

ARRIVAL

SBEG

ILS

STAR

>

INSERT

ARRIVAL

MOD FLT PLAN 1R 2R

APPROACH

REVIEW

APPROACH

1/1 1L

VIBOT

2L

EGAP

RW10

VOR

1/1

2R

AIRPORT 1L

FLIGHT INSTRUMENTS/COMM/NAV/FMS

SBEG RUNWAY

3

AIRPORT

SYSTEMS DESCRIPTION

3R

3L

4R

4L

5R

5L

6R

8

6L

352

1/4

1100Z

1R

19.8NM 1107Z

261/15000

329

41.2NM 1115Z

DES 500 3.0 /2000A

103

2.3NM 1116Z

DES 500 3.0 /1500A

3.5NM 1118Z

DES 500 3.1 /0320

CF10 FF10

103 F

RW10

CANCEL

6R

ACTIVATE

2R 3R 4R 5R 6R

9

ACTIVE FLT PLAN

2L 3L 4L 5L 6L

VIBOT 352

1R

19.2NM 1107Z

261/15000

329

41.2NM 1115Z

DES 500 3.0 /2000A

103

2.3NM 1116Z

DES 500 3.0 /1500A

103 F

3.5NM 1118Z

DES 500 3.1 /0320

EGAP CF10 FF10

RW10

LANDING

2R 3R

EM170AOM140449D.DGN

1L

1/4

1100Z

4R 5R 6R

AOM-1502-003

ARRIVAL

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AIRPLANE OPERATIONS MANUAL

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AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

LANDING !MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

1 - When the airplane is within 200 NM to the destination the prompt LANDING appears. Press LSK 6R (LANDING) to enter in the LANDING 1/3 page. On LANDING 1/3 page the following information is displayed: – Runway heading. – Runway length. – Runway outside air temperature. – Runway wind. – Runway pressure altitude and barometric setting. – Runway elevation. With exception of runway heading and length the other information can be entered. The entry is accomplished in the scratchpad through alphanumeric keys and pressing respective LSK. 2 - Press NEXT button to go to LANDING 2/3 page. The following information is displayed: – Runway slope. – Runway threshold. – Runway density altitude. – Runway wind. 3 - Press NEXT button to go to LANDING 3/3 page. 4 - Enter with VREF, VAP, VAC and VFS. The entry is accomplished in the scratchpad through alphanumeric keys and pressing respective LSK.

AOM-1502-003

5 - Press LSK 6R (FLT PLAN) to go to ACTIVE FLT PLAN 1/4 page.

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AIRPLANE OPERATIONS MANUAL

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INTENTIONALLY BLANK

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

!!MAU load up to 17.5 OR PRE-MOD SB 170-31-0019

ACTIVE FLT PLAN 1L 2L 3L 4L 5L

VIBOT 352

RUNWAY

1100Z 19.2NM 1107Z

261/15000

41.2NM 1115Z

DES 500 3.0 /2000A

103

2.3NM 1116Z

DES 500 3.0 /1500A

103 F

3.5NM 1118Z

DES 500 3.1 /0320

EGAP

329

CF10 FF10

RW10

LANDING

1/4

6L

LANDING

1R

1L

2R

2L

3R

3L

4R

4L

5R

1

P ALT/B SET 0252/29.92

DESCENT

LANDING

1/3 LENGTH 8858

OAT WIND --- C/--- F --- /---

5L 6L

6R

10 SBEG

HDG 103

ELEV 0252

SLOPE

1R

1L

2R

2L

2

2/3 THRSHLD

0.1%

0

1R

WIND

DENSITY ALT

2R

3R

3L

3R 4R

4R

4L

ARRIVAL

5R

5L

FLT PLAN

6R

6L

5R DESCENT

FLT PLAN

6R

3

1L 2L

LANDING

3/3 VFS ---

VAP ---

1L

1R

2L

2R

VAC ---

4

VREF 115

ACTIVE FLT PLAN

3/3 VFS 170

VAP 120

1L

1R

2L

2R

VAC 130

3R

3L

4L

4R

4L

4R

4L

5L

5R

5L

5R

5L

6R

6L

3L

6L

DESCENT

3R

FLT PLAN

3L

CLEAR

FLT PLAN

6R

5

VIBOT 352

1/4

1100Z

1R

19.2NM 1107Z

261/15000

329

41.2NM 1115Z

DES 500 3.0 /2000A

103

2.3NM 1116Z

DES 500 3.0 /1500A

3.5NM 1118Z

DES 500 3.1 /0320

EGAP CF10 FF10

103 F

RW10

6L

LANDING

2R 3R 4R 5R 6R

EM170AOM140458B.DGN

LANDING VREF ---

AOM-1502-003

LANDING

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AIRPLANE OPERATIONS MANUAL

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AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

!MAU load 19.3 and on OR POST-MOD SB 170-31-0019

1 - When the airplane is within 200 NM to the destination the prompt LANDING appears. Press LSK 6R (LANDING) to enter in the LANDING 1/2 page. On LANDING 1/2 page the following information is displayed: – Runway outside air temperature. – Landing weight. – Approach flaps. – Landing flaps. – Ice. – Approach type. For landing, surface temperature is required. With exception to landing weight, all the other information can be entered. The entry is accomplished in the scratchpad through alphanumeric keys and pressing respective LSK. The landing weight displayed in LANDING 1/2 page is based on the following logic: – If time since airborne is less than or equal to 15 min, the landing weight will be the FMS takeoff weight minus the fuel burn allowance. – If time since airborne is greater than 15 min, the landing weight will be the predicted landing gross displayed in PERF DATA 1/3. 2 - Press NEXT button to go to LANDING 2/2 page. If the landing V-Speeds inserted on the LANDING 2/2 page before the takeoff are not being displayed on the PFD, they are deleted on the FMS 15 min after takeoff. 3 - Enter with VREF, VAP, VAC and VFS. The entry is accomplished in the scratchpad through alphanumeric keys and pressing respective LSK.

AOM-1502-003

4 - Press LSK 6R (FLT PLAN) to go to ACTIVE FLT PLAN page.

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AIRPLANE OPERATIONS MANUAL

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AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

!!MAU load 19.3 and on OR POST-MOD SB 170-31-0019

1L 2L 3L

*ALT03

DIRECT TORUK.RDE

RDE

DIRECT

4L

LANDING

DEPARTURE

1L

+15 C/+59 F

2L

APPROACH FLAP FLAP-2 LANDING FLAP

1R 2R VAC

5L

6R

6L

OR FLAP-5

3R

OR

YES

4R

OR

5R

DATA

6R

APPROACH TYPE CAT-1 PERF DATA

T.O.

2

2/2

ACTIVE FLT PLAN

2L

3R 4R

4L

5R

5L

ISKUL

6R

6L

DEPARTURE

3L

VFS 180

5L

5R

5L

6R

6L

1/5

ORIGIN/ETD

VAP 130

4L

3R

1R 2R

1L

4R

3

21975LB

OR FLAP-4

VREF 120

VFS

1R

1L 2L

2R

4

3L

RW15 SBSJ 155

1.9NM

227

00+00 13.7NM

ALT03 TORUK 227

PERF DATA

FLT PLAN

D227S 227

00+03

CLB

218/ 2520 A CLB 218/

7.0NM 00+01 8.0NM 00+01

218/

1R 2R

FL080 B CLB

3R

FL070 A

4R

2400 270/FL158 LANDING

5R 6R

EM170AOM140736A.DGN

FLT PLAN

NO

4L

4L

DESCENT

FLAP-FULL ICE

5R

VAC 140

6L

3L

LANDING

VAP

3L

1

4R

2/2

1L 2L

1R

DEST

VREF

LND WGT

2R

SBFL

PERF INIT

1/2

RWY OAT

3R

SBFL

5L 6L

LANDING

2/3 TO

*

ACT RTE VIA

AOM-1502-003

LANDING

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AIRPLANE OPERATIONS MANUAL

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SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

FLIGHT INSTRUMENTS/COMM/NAV/FMS

VNAV TEMPERATURE COMPENSATION !MAU load 21.4 and on

The FMS provides the capability to create constant angle vertical paths for the final approach segment of the non-precision approaches and vertical descent profiles for transition to the final approach segment based on the altitude constraints in the navigation database. These descent profiles are flown by reference to the indicated barometric altitude. However, barometric altimeters are calibrated to indicate true altitude under ISA conditions of temperature and sea level pressure. The VNAV temperature compensation provides the capability to compensate the altitude constraints for all the waypoints in approach, approach transitions and missed approach segments of the flight plan during non-standard temperature conditions. The temperature compensation configuration feature is presented in FLIGHT CONFIG 2/2 page. This page is accessed through the MAINTENANCE 2/3 page. !!MAU load 21.4 and on

FLIGHT CONFIG FUNCTION KEY PAGING

OFF

OR

2/2

ON

NONE

OR

COLD

OR

TEMP COMP CONFIG

SETUP

EM170AOM140540B.DGN

FLIGHT SUMMARY OUTPUT

AOM-1502-003

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AIRPLANE OPERATIONS MANUAL

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AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

EICAS MESSAGES TYPE

MESSAGE ADS 1 (2) (3) FAIL

ADS 1 (2) (3) (4) HTR FAIL

AVNX ASCB FAULT DISPLAY CTRL FAIL DISPLAY CTRL FAULT

CAUTION

FMS POS DISAG

FMS 1 (2) GPS POS DISAG

FMS-GPS POS DISAG IRS 1 (2) FAIL

AOM-1502-003

IRS EXCESSIVE MOTION

MEANING Associated ADS has failed. At least one of the two smart probes that feed a respective Air Data System has the associated heater failed. One or more ASCB buses have failed. Display controller is no longer operating. Loss of a display controller channel. Maintenance is required. A position disagreement between FMSs was detected. A position disagreement between the associated FMS and GPS was detected. Associated FMS computed position and GPS position do not agree. Associated IRS has failed. Excessive motion of airplane is disturbing associated IRS aligning sequence.

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REVISION 21

EICAS Messages

Page 1

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

CAUTION

MESSAGE MCDU 1 (2) (3) OVHT (Pre-Mod Load 17.5)

MEANING Associated MCDU has suffered an overheat condition. All functions hosted in NAVCOM 1 (2) FAIL associated MRC are unavailable. MRC NIM has NAVCOM 1 (2) OVHT suffered an overheat condition. Top level system part VALIDATE CONFIG number was updated. VHF COM has VHF 1 (2) (3) OVHT suffered an overheat condition. Radio 3 COM and VHF 3 FAIL ACARS functions have failed. XPDR 1 (2) IN STBY Transponder is at (Post-Mod. Load STBY mode in flight. 23.1)

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Page 2

EICAS Messages

REVISION 21

AOM-1502-003

TYPE

AIRPLANE OPERATIONS MANUAL

AIRPLANE OPERATIONS MANUAL TYPE

MESSAGE ADS 1 (2) HTR FAULT ADS 3 (4) SLIPCOMP FAIL ADS-B FAIL (Pre-Mod Load 25.4 Pentium M or Pre-Mod Load 25.3 Pentium II) ADS-B NOT AVAIL (Post-Mod Load 25.4 - Pentium M or Post-Mod Load 25.3 Pentium II)

AOM-1502-003

ADVISORY

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

MEANING The electronics in the MFP heater portion of the ADSP has failed. ADS 3 (4) sideslip compensation function has failed. 2 GPS has failed or GPS signal has degraded.

2 GPS has failed or GPS signal has degraded.

Integrated ADS PROBE 1 (2) (3) Pitot/Static/AOA (4) FAIL sensor 1 (2) (3) (4) has failed. ATC DATALINK 1 (2) FAIL (only for airplanes The respective ATC equipped with function has failed. ATN-CPDLC Pre-Mod Load 27.1) CMC FAIL CMC has failed. CMF 1 FAIL CMF 1 has failed and (Pre-Mod Load Datalink connection 25.1.0.1) was lost. DATALINK 1 FAIL CMF 1 has failed and (Post-Mod Load Datalink connection 25.1.0.1) was lost. DATALINK 2 FAIL (only for airplanes CMF 2 has failed and equipped with Datalink connection ATN-CPDLC Pre-Mod was lost. Load 27.1)

14-09-35 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

EICAS Messages

Page 3

SYSTEMS DESCRIPTION FLIGHT INSTRUMENTS/COMM/NAV/FMS

ADVISORY

MESSAGE

MEANING Respective DVDR CVR AFT (FWD) FAIL CVR function has failed. Respective DVDR FDR AFT (FWD) FAIL FDR function has failed. The electronics in the FLT CTRL ADS FAIL ADC portion of the ADSP has failed. Associated FMS has FMS 1 (2) FAIL failed. GPS 1 (2) FAIL Associated GPS has (Post-Mod Load 27.1) failed. The respective HF has failed. These HF 1 (2) FAIL messages are displayed only for dual installation. Associated IRS is in IRS ALIGNING aligning sequence.

14-09-35 Copyright © by Embraer. Refer to cover page for details.

Page 4

EICAS Messages

REVISION 21

AOM-1502-003

TYPE

AIRPLANE OPERATIONS MANUAL

AIRPLANE OPERATIONS MANUAL TYPE

MESSAGE IRS 1 (2) NAV MODE FAIL

IRS PRES POS INVALID LPV NOT AVAIL (Post-Mod Load 27.1) RALT 1 (2) FAIL

ADVISORY

RNP AR NOT AVAIL (Post-Mod Load 27.1) RNP AR 40 kt > 40 kt

NOT

ENGINE

WSPEED

DETECTED

RUNNING

> 40 kt

DETECTED

ENGINE RUNNING

WSPEED

> 40 kt

-

After takeoff, the settings in the MCDU will be ignored by the airplane and the engine and wing anti-ice valves will open anytime an icing condition is detected, or the Ice Protection Panel Mode Switch is set to ON position.

14-12-10 Copyright © by Embraer. Refer to cover page for details.

Page 8

System Description

REVISION 21

AOM-1502-003

The T/O DATASET MENU page on the MCDU will become available thirty seconds after the airplane touches the ground.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ICE AND RAIN PROTECTION

AOM-1502-003

After landing, the Ice Protection System should be activated if icing conditions exist.

14-12-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

System Description

Page 9

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

ICE AND RAIN PROTECTION

WINDSHIELD HEATING SYSTEM The windshields are electrically heated for anti-icing and anti-fogging purposes.

NORMAL OPERATION The windshield heating button remains pushed in allowing the system to automatically control the windshield temperature to a specific range. Left and right windshields heating are controlled by individual pushbuttons on the overhead panel. The system only operates if there are at least two AC electrical sources. GROUND OPERATION When a single AC power is available (e.g. one IDG) each windshield heating controller performs its standard power-up BIT routine heating the corresponding windshield for 120 seconds. ABNORMAL OPERATION

14-12-10 Copyright © by Embraer. Refer to cover page for details.

Page 10

System Description

REVISION 21

AOM-1502-003

In case of a single AC electrical source in-flight only the left windshield heating is powered. If the left windshield heating system fails, the right windshield heating becomes available.

AIRPLANE OPERATIONS MANUAL

AIR DATA SYSTEM

SMART

SYSTEMS DESCRIPTION ICE AND RAIN PROTECTION

PROBE/TAT

HEATING

The Air Data Smart Probe (ADSP)/TAT normal heating mode is fully automatic. The ADSP heating operation can be manually overridden on ground. A total of four smart and two TAT probes are installed on the nose fuselage section of the airplane. Each probe has a dedicated heater.

AUTO MODE The ADSP and TAT are heated whenever an engine is running or the airplane is airborne.

MANUAL OVERRIDE The ADSP Heater pushbutton is installed on the main control panel to allow the heating of ADSPs with the airplane on the ground. If the ADSP Heater pushbutton is pushed IN, the ADSP heating system will be powered, overriding the system logic on ground. When the batteries are the only electrical source to the airplane, only the ADSP 3 will be heated. The ADSP Heater pushbutton should be pushed OUT with one or both engines running.

WINDSHIELD WIPER SYSTEM This airplane is equipped with two independent wipers operated through dedicated control knobs on the overhead panel.

AOM-1502-003

The windshield wipers will stop if operated on a dry windshield. The system remains inoperative until the wiper control knob is set to one of the three available speeds.

14-12-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

System Description

Page 11

SYSTEMS DESCRIPTION ICE AND RAIN PROTECTION

AIRPLANE OPERATIONS MANUAL

14-12-10 Copyright © by Embraer. Refer to cover page for details.

Page 12

System Description

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ICE AND RAIN PROTECTION

ICE PROTECTION SYSTEM The Ice Protection System Test selector knob provides a manual test for the wing and engine anti-ice systems for maintenance use. The wing anti-ice system tests itself during flight (SAI IBIT) 10 min after takeoff or at 10000 ft AGL, whichever occurs first. At this time the Slat Anti-Ice Valves will be opened (EICAS messages A-I WING VLV OPEN and A-I Synoptic page will indicate that valves have opened). If a failure occurs during IBIT, the message A-I WING FAIL will be displayed.

AOM-1502-003

The SAI IBIT duration is 60 seconds (maximum). The test can be finished earlier if all slat temperature sensors have an increase of 10°F.

14-12-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 12

Ice Protection System

Page 1

SYSTEMS DESCRIPTION ICE AND RAIN PROTECTION

AIRPLANE OPERATIONS MANUAL

14-12-15 Copyright © by Embraer. Refer to cover page for details.

Page 2

Ice Protection System

REVISION 12

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION ICE AND RAIN PROTECTION

EICAS MESSAGES TYPE

MESSAGE

WARNING

A-I WING 1 (2) LEAK

A-I ENG 1 (2) FAIL

A-I LO CAPACITY A-I WING FAIL CAUTION A-I WING NO DISPATCH ICE DETECTOR 1 (2) FAIL

AOM-1502-003

WINDSHIELD 1 (2) HTR FAIL

MEANING An overheating or leakage is detected in the associated wing anti-ice system. Engine anti-ice bleed valve is closed when commanded open, or duct failure detected. Wing anti-ice bleed air pressure and temperature capacity is low. A wing anti-ice system failure has been detected. Wing anti-ice bleed valve has failed open. Maintenance action is required. Associated ice detector has failed. Associated windshield heating system has failed or is overheated.

14-12-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

EICAS Messages

Page 1

SYSTEMS DESCRIPTION ICE AND RAIN PROTECTION

ADVISORY

STATUS

MESSAGE

MEANING Ice protection selector A-I MODE NOT AUTO knob is not in the AUTO position. Ice protection button for A-I SWITCH OFF engine and/or wing anti-ice system is pushed out. An icing condition has ICE CONDITION been detected. Displayed during test if there is loss of the A-I ENG 1 (2) FAULT capacity to monitor the adequate functioning of the system. Indicates leakage in the A-I ENG 1 (2) LEAK internal pipe. Engine anti-ice valve is A-I ENG 1 (2) VLV OPEN open. Wing anti-ice valve is open. Also displayed during test after every A-I WING VLV OPEN takeoff, (crossing 10000 ft or 10 minutes after takeoff, whichever occurs first).

14-12-20 Copyright © by Embraer. Refer to cover page for details.

Page 2

EICAS Messages

REVISION 9

AOM-1502-003

TYPE

AIRPLANE OPERATIONS MANUAL

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

SECTION 14-13 LANDING GEAR AND BRAKES TABLE OF CONTENTS Block

Page

General Description............................................. 14-13-01 .... GENERAL DESCRIPTION..................................... 14-13-01 ....

1 1

AOM-1502-003

Controls and Indications..................................... 14-13-05 .... 1 LANDING GEAR CONTROLS AND INDICATIONS.................................................. 14-13-05 .... 1 BRAKES................................................................. 14-13-05 .... 7 STEERING............................................................. 14-13-05 .... 15 TOWING LIGHTS.................................................. 14-13-05 .... 17 Air/Ground Positioning System.......................... 14-13-10 .... AIR GROUND POSITIONING SYSTEM............... 14-13-10 ....

1 1

Landing Gear Doors............................................ 14-13-12 .... LANDING GEAR DOORS...................................... 14-13-12 ....

1 1

Landing Gear Operation...................................... 14-13-15 .... LANDING GEAR CONTROL SYSTEM................. 14-13-15 .... LANDING GEAR OPERATION.............................. 14-13-15 .... DOWN/UP LOCK SENSORS................................ 14-13-15 .... DOWNLOCK RELEASE BUTTON........................ 14-13-15 .... LANDING GEAR AURAL WARNING..................... 14-13-15 ....

1 1 1 3 3 5

Brakes................................................................... 14-13-20 .... BRAKES................................................................. 14-13-20 .... NORMAL OPERATION.......................................... 14-13-20 .... LOCKED WHEEL PROTECTION.......................... 14-13-20 .... ANTISKID PROTECTION...................................... 14-13-20 .... AUTOMATIC WHEEL BRAKING........................... 14-13-20 .... TOUCHDOWN PROTECTION.............................. 14-13-20 .... EMERGENCY/PARKING BRAKE.......................... 14-13-20 .... FUSIBLE PLUGS................................................... 14-13-20 .... BRAKE WEAR PINS.............................................. 14-13-20 ....

1 1 1 1 2 2 2 2 3 3

14-13-TOC Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Table of Contents

Page 1

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

AIRPLANE OPERATIONS MANUAL

Nosewhell Steering System................................ 14-13-25 .... NOSEWHEEL STEERING SYSTEM..................... 14-13-25 .... OPERATION.......................................................... 14-13-25 .... HANDWHEEL STEERING MODE......................... 14-13-25 .... RUDDER PEDAL STEERING MODE.................... 14-13-25 .... FREE WHEEL STEERING MODE........................ 14-13-25 .... MINIMUM TURNING RADII................................... 14-13-25 ....

1 1 1 1 4 4 6

EICAS Messages.................................................. 14-13-30 .... EICAS MESSAGES............................................... 14-13-30 ....

1 1

14-13-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 18

AOM-1502-003

Block Page AUTOBRAKE......................................................... 14-13-20 .... 6

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

GENERAL DESCRIPTION The landing gear system provides ground-rolling capability to the airplane, thus enabling takeoff, landing, and taxi operations. The airplane is equipped with a retractable tricycle landing gear which is hydraulically operated. It provides structural support and shock absorber functions for safe transmission of landing, taxing, and ground loads from the wheels to the airplane structure. Each landing gear is a conventional dual wheel unit. The nose landing gear incorporates a powered steering system, which performs the airplane directional control on the ground. The brake system is designed to provide manual or automatic (if applicable) airplane deceleration during ground operations.

EM170AOM140165.DGN

The landing gear and brake system parameters and indications are displayed on both MFD synoptic pages. System messages are displayed on the EICAS.

AOM-1502-003

MAIN AND NOSE LANDING GEARS

14-13-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

General Description

Page 1

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

AIRPLANE OPERATIONS MANUAL

14-13-01 Copyright © by Embraer. Refer to cover page for details.

Page 2

General Description

REVISION 18

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

LANDING GEAR CONTROLS AND INDICATIONS LANDING GEAR CONTROL PANEL MAIN PANEL

DN LOCK REL

UP

2

EM170AOM140166.DGN

1

DN

1 - DOWNLOCK RELEASE BUTTON (MOMENTARY ACTION) – Manually releases the landing gear lever lock. 2 - LANDING GEAR LEVER

AOM-1502-003

UP: DOWN:

retracts the landing gear. extends the landing gear.

14-13-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 1

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

AIRPLANE OPERATIONS MANUAL

ALTERNATE GEAR EXTENSION COMPARTMENT

3

2

1

GEAR DOWN

EM170AOM140227B.DGN

NORMAL

1 - ELECTRICAL OVERRIDE SWITCH the landing gear lever performs landing gear retraction and extension. GEAR DOWN: electronically bypasses the PSEM, opens the forward and aft doors and extends the landing gear.

14-13-05 Copyright © by Embraer. Refer to cover page for details.

Page 2

Controls and Indications

REVISION 21

AOM-1502-003

NORMAL:

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

2 - ALTERNATE GEAR EXTENSION LEVER (TWO-POSITION) – When pulled, relieves hydraulic pressure in the landing gear lines and releases all landing gear uplocks. 3 - ALTERNATE GEAR EXTENSION LEVER UNLOCK PUSHBUTTON

AOM-1502-003

– When pressed, releases the handle from the actuated position.

14-13-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 3

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

AIRPLANE OPERATIONS MANUAL

LANDING GEAR WARNING INHIBITION BUTTON MAIN PANEL

GND PROX G/S INHIB

LG WRN INHIB

EM170AOM140168.DGN

1

1 - LANDING GEAR WARNING (GUARDED-MOMENTARY ACTION)

INHIBITION

BUTTON

Inhibits the landing gear aural warning in the event of dual radio altimeter failure. A white striped bar will illuminate when pushed. The white striped bar will extinguish if: – Thrust levers are advanced beyond 45° thrust lever angle (TLA) for two engines or; – Thrust levers are advanced beyond 59° TLA for one engine inoperative or;

14-13-05 Copyright © by Embraer. Refer to cover page for details.

Page 4

Controls and Indications

REVISION 21

AOM-1502-003

– The flap selector lever is set to 5 or full without any landing gear down and locked.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

LANDING GEAR POSITION INDICATION !Airplanes not equipped with Autobrake EICAS

DN DN

DN

1

EM170AOM140169.DGN

LANDING GEAR

" !Airplanes equipped with Autobrake OR POST-MOD SB 170-32-0014 EICAS

DN DN

DN

1

EM170AOM140497A.DGN

LG/AUTOBRAKE

"

1 - LANDING GEAR POSITION INDICATION – DOWN: the green DN label inside a green circle indicates that the respective landing gear is down and locked. – UP: the white UP label inside a white box indicates that the respective landing gear is up and locked. – TRANSIT: the amber cross-hatched box indicates that the respective landing gear is in transit.

AOM-1502-003

– DISAGREEMENT: the indication changes from its previous color to red 20 seconds after the discrepancy is detected. – The red cross-hatched box indicates that the respective

14-13-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 5

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

LANDING GEAR AND BRAKES

landing gear is kept in transit and is not locked in the commanded position. !Pre-mod MAU load 27.1

– The red DN label inside a red circle and the red UP label inside a red box indicate a discrepancy between landing gear lever position and any landing gear position. "

!Pre-mod MAU load 27.1

LANDING GEAR

LANDING GEAR

DN DN

DN

GEAR DOWN

TRANSITION

LANDING GEAR

LANDING GEAR

UP

UP

UP

UP

DN

LOCKED UP

DN

DISAGREE

LANDING GEAR

DN EM170AOM140689B.DGN

DN

DISAGREE

"

14-13-05 Copyright © by Embraer. Refer to cover page for details.

Page 6

Controls and Indications

REVISION 21

AOM-1502-003

LANDING GEAR POSITION INDICATION ON EICAS

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

BRAKES

EM170AOM140761A.DGN

EMERGENCY PARKING BRAKE HANDLE

1

1 - EMERGENCY/PARKING BRAKE HANDLE – Actuates the emergency/parking brake. – The handle will lock when pulled up to the fully actuated position.

AOM-1502-003

– To release the handle from the fully actuated position, the top button must be pressed.

14-13-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 7

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

LANDING GEAR AND BRAKES

EMERGENCY PARKING BRAKE LIGHT

GND PROX TERR INHIB

EMERG/ PRKG BRAKE

ON

1

EM170AOM140173A.DGN

MAIN PANEL

1 - EMERGENCY/PARKING BRAKE LIGHT

14-13-05 Copyright © by Embraer. Refer to cover page for details.

Page 8

Controls and Indications

REVISION 21

AOM-1502-003

– ON: the indicator illuminates when the emergency/parking brake is actuated and there is hydraulic pressure on the brake line.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

LANDING GEAR AND BRAKES

AUTOBRAKE SELECTION

!Airplanes equipped with Autobrake OR POST-MOD SB 170-32-0014 MAIN PANEL

AUTOBRAKE OFF RTO

LO MED

1 EM170AOM140174.DGN

HI

1 - AUTOBRAKE SELECTOR KNOB (ROTARY ACTION) – RTO: Selects RTO deceleration rate. – OFF: Autobrake is deactivated. – LO: Selects the low deceleration rate. – MED: Selects the medium deceleration rate. – HI: Selects the high deceleration rate.

AOM-1502-003

"

14-13-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 9

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

AIRPLANE OPERATIONS MANUAL

AUTOBRAKE EICAS INDICATION

!Airplanes equipped with Autobrake OR POST-MOD SB 170-32-0014

EICAS

LG/AUTOBRAKE

UP A-BRK HI

UP

EM170AOM140176.DGN

UP

1

1 - AUTOBRAKE INDICATION – A-BRK: the white A-BRK label indicates the autobrake is armed. – RTO, HI, MED or LO: green labels indicating the selected autobrake mode.

14-13-05 Copyright © by Embraer. Refer to cover page for details.

Page 10

Controls and Indications

REVISION 21

AOM-1502-003

– AMBER DASHED: indicates that the data is invalid.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

LANDING GEAR AND BRAKES

LG/AUTOBRAKE

LG/AUTOBRAKE

DN

DN

DN

DN

DN

DN

A-BRK RTO AUTOBRAKE RTO

AUTOBRAKE OFF

LG/AUTOBRAKE

LG/AUTOBRAKE

DN

DN

DN

DN

DN

DN

A-BRK LO

A-BRK MED

AUTOBRAKE LO

AUTOBRAKE MED

LG/AUTOBRAKE

LG/AUTOBRAKE

DN DN

DN

A-BRK HI

DN

A-BRK

AUTOBRAKE HI

AUTOBRAKE DATA INVALID OR UNAVAILABLE

EM170AOM140170.DGN

DN DN

AUTOBRAKE EICAS INDICATIONS

AOM-1502-003

"

14-13-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 11

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

LANDING GEAR AND BRAKES

MFD STATUS PAGE INDICATIONS MFD

BRAKES

EMER ACCU PSI

S Y S 1

S Y S 2

1

3OOO

3OOO

OB 2OO

IB 2OO

IB 2OO

OB 2OO

EM170AOM140692A.DGN

TEMP C

1 - EMERGENCY/PARKING BRAKE ACCUMULATOR PRESSURE INDICATION – Digital Pressure GREEN: normal operating range. AMBER: emergency/parking brake effectiveness is degraded. AMBER DASHED: invalid information or a value out of the valid range. – Pressure Scale/Pointer If the value is invalid, the pointer disappears from the display. – Scale: WHITE: normal operating range. AMBER: emergency/parking brake effectiveness is degraded. GREEN (hollow): normal operating range.

14-13-05 Copyright © by Embraer. Refer to cover page for details.

Page 12

Controls and Indications

REVISION 21

AOM-1502-003

– Pointer:

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

LANDING GEAR AND BRAKES

AMBER (solid): emergency/parking brakes effectiveness is degraded. MFD

BRAKES

EMER ACCU PSI

S Y S 1

S Y S 2 3OOO

3OOO TEMP C IB 2OO

IB 2OO

EM170AOM140693A.DGN

OB 2OO

2

OB 2OO

2 - BRAKE TEMPERATURE INDICATION – Digital Temperature Displays brake temperature in degrees Celsius (°C). GREEN: normal operating range. AMBER: cautionary operating range (no takeoff range). AMBER DASHED: invalid information or a value out of the valid range. – Temperature Scale/Pointer If the value is invalid, the pointer will disappear from the display. – Scale: WHITE: normal operating range.

AOM-1502-003

AMBER: cautionary operating range. – Pointer:

14-13-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 13

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

AIRPLANE OPERATIONS MANUAL

GREEN (hollow): normal operating range.

14-13-05 Copyright © by Embraer. Refer to cover page for details.

Page 14

Controls and Indications

REVISION 21

AOM-1502-003

AMBER (solid): cautionary operating range.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

STEERING

EM170AOM140178.DGN

STEERING HANDLE

AOM-1502-003

– The handle must be pushed down (1) to engage the steering system. Releasing the handle will enable rudder pedals mode, keeping it pressed enables handwheel mode. Rotating the handwheel left or right (2) commands steering.

14-13-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 15

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

AIRPLANE OPERATIONS MANUAL

STEERING DISENGAGE SWITCH

NOTE: PILOT’S CONTROL WHEEL SHOWN, VIEWED FROM BEHIND.

EM170AOM140179C.DGN

1

1 - STEERING DISENGAGE SWITCH (MOMENTARY ACTION)

14-13-05 Copyright © by Embraer. Refer to cover page for details.

Page 16

Controls and Indications

REVISION 21

AOM-1502-003

– Disengages the nosewheel steering system.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

EM170AOM140286B.DGN

TOWING LIGHTS

1 - TOWING LIGHTS GREEN: – Steering disengaged through the external steering disengage switch and – Parking brakes not applied and – Main brakes not applied. RED: – External steering disengage switch in the engaged position or – Parking brakes applied or

AOM-1502-003

– Main brakes applied.

14-13-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Controls and Indications

Page 17

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

AIRPLANE OPERATIONS MANUAL

14-13-05 Copyright © by Embraer. Refer to cover page for details.

Page 18

Controls and Indications

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

AIR GROUND POSITIONING SYSTEM Two proximity sensor electronic modules (PSEM) process signals from the six weight-on-wheels (WOW) proximity sensors to determine if the airplane is on ground or in flight. Two WOW sensors are installed on each landing gear. Each PSEM monitors the six WOW proximity sensors. The inputs are logically combined by the PSEMs, and other airplane systems, to provide the overall airplane air/ground (WOW) indication to those systems. If two WOW sensors on the same landing gear leg fail, the PSEMs will activate a logic that prevents the landing gear lever from moving up.

AOM-1502-003

In this case, with the airplane on ground, the LG NO DISPATCH caution message is displayed on the EICAS. In-flight the failure is recognized through the landing gear lever stuck in the DOWN position and the EICAS message LG WOW SYS FAIL may be presented.

14-13-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 9

Air/Ground Positioning System

Page 1

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

AIRPLANE OPERATIONS MANUAL

14-13-10 Copyright © by Embraer. Refer to cover page for details.

Page 2

Air/Ground Positioning System

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

LANDING GEAR DOORS MAIN LANDING GEAR DOORS Each main landing gear (MLG) has three doors: lower, middle, and upper door. The upper door is hinged to a rib of the MLG bay in the wing. Rods attach the upper door to the MLG main fitting. The middle door is not hinged. It is attached by bolts directly to the MLG main fitting. The lower door is hinged to the middle door. When the MLG extends, the lower door opens and provides clearance for the full stroke of the MLG shock absorber.

AOM-1502-003

The MLG doors do not cover the wheel and tire assemblies when the MLG is fully retracted.

14-13-12 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Landing Gear Doors

Page 1

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

AIRPLANE OPERATIONS MANUAL

LOWER DOOR UPPER DOOR

EM170AOM141350A.DGN

MIDDLE DOOR

14-13-12 Copyright © by Embraer. Refer to cover page for details.

Page 2

Landing Gear Doors

REVISION 18

AOM-1502-003

MAIN LANDING GEAR DOORS

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

NOSE LANDING GEAR DOORS The nose landing gear (NLG) bay has four doors: two forward doors and two rear doors. All doors are mechanically actuated by the NLG as it extends or retracts. The rear doors are hinged to the airplane fuselage. The rear doors stay open while the NLG is extended. The forward doors are hinged to the airplane fuselage. These doors open temporarily during NLG extension or retraction, and close after the NLG is fully extended or fully retracted.

AOM-1502-003

If the NLG doors are not properly closed, the message LG NOSE DOOR OPEN is displayed in the EICAS.

14-13-12 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Landing Gear Doors

Page 3

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

AIRPLANE OPERATIONS MANUAL

EM170AOM141348A.DGN

REAR DOORS

FORWARD DOORS

14-13-12 Copyright © by Embraer. Refer to cover page for details.

Page 4

Landing Gear Doors

REVISION 18

AOM-1502-003

NOSE LANDING GEAR DOORS

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

LANDING GEAR CONTROL SYSTEM Normal operation of the landing gear is commanded through the landing gear lever located on the main instrument panel and controlled by the SPDA. In the event of a failure of the landing gear lever, landing gear extension can be performed by the landing gear override switch located on the landing gear free fall lever compartment. Hydraulic pressure is necessary for retraction and normal extension of the landing gear. In the event of a hydraulic pressure failure, landing gear extension is possible through the alternate landing gear lever. The landing gear operation is monitored by the PSEM and the downlock sensors. A landing gear aural warning alerts the crew whenever any landing gear is not down and locked and the system recognizes the intention to land.

LANDING GEAR OPERATION LANDING GEAR RETRACTION Positioning the landing gear lever to the UP position releases hydraulic pressure for the nose and main landing gear locks, and pressurizes the respective actuators to retract the landing gear. When retraction is completed, the landing gear is held in place by uplocks. Whenever the PSEM computes a signal of weight on wheels (airplane on ground status) the SPDA commands the landing gear lever to lock mechanically in the DOWN position.

AOM-1502-003

When the weight on wheels signal is no longer valid (airplane in-flight status) the mechanical lock is released allowing the landing gear lever to move to the UP position. NOTE: – If for any reason the shock absorber of any landing gear does not extend completely the PSEM keeps computing a signal of airplane on ground. – With this condition the landing gear lever is locked down and the LG WOW SYS FAIL EICAS message is displayed. – To prevent structural damage to the airplane the landing gear must be retracted only in case of an emergency that requires climb performance improvement.

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REVISION 21

Landing Gear Operation

Page 1

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

AIRPLANE OPERATIONS MANUAL

LANDING GEAR NORMAL EXTENSION Normal landing gear extension is used when the electrical and hydraulic systems are operating normally and there is no failure in the landing gear lever control box. Setting the landing gear lever DOWN releases hydraulic pressure for the nose and main landing gear uplocks, as well as for the retraction actuators. The landing gear doors are mechanically opened. When extension is completed, the landing gear is locked in the fully extended position by the downlock springs.

ELECTRICAL OVERRIDE EXTENSION When the landing gear lever control box fails the electrical override system is used to extend the landing gear. The electrical override system bypasses the PSEM and commands gear extension in the same sequence as the normal operation.

ALTERNATE GEAR EXTENSION If hydraulic pressure is not available for landing gear operation or the electrical system fails, landing gear extension is performed by the alternate gear extension lever. Pulling up the alternate gear lever releases residual hydraulic pressure in the landing gear lines and opens all landing gear uplocks. The landing gear extends in a free fall with the aid of gravitational and aerodynamic forces. In the unlikely event that one main gear does not lock down, it may be necessary to slip the airplane using aerodynamic drag to lock the affected leg. With the landing gear down and locked the EICAS indication displays the label DOWN.

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Page 2

Landing Gear Operation

REVISION 21

AOM-1502-003

The label will be DOWN with a red color if the landing gear lever is set to UP or in green if set to DOWN.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

DOWN/UP LOCK SENSORS Each landing gear has two uplock sensors and two downlock sensors. In the event of a discrepancy between both uplock or downlock sensors of the same landing gear, the sensor in agreement with the landing gear lever position will be considered valid.

DOWNLOCK RELEASE BUTTON

AOM-1502-003

The downlock release button mechanically bypasses the system protection logic. It should be used only in the event of a landing gear control lever failure or when it is necessary to clear obstacles.

14-13-15 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Landing Gear Operation

Page 3

Page 4

Landing Gear Operation

Copyright © by Embraer. Refer to cover page for details.

14-13-15

REVISION 21

AOM-1502-003

EM170AOM140355B.DGN

UPLOCK

NLG ACT. UNLOCK ACT.

UPLOCK

PSEM

UNLOCK ACT.

UNLOCK ACT.

RETRACT

EXTEND

ALTERNATE GEAR EXTENSION LEVER

MLG ACT.

OR

ES UPLOCK

LG SELECTOR VALVE

FREE FALL SELECTOR VALVE

EXTENSION OVERRIDE SWITCH

MLG ACT.

RS

SUPPLY

RETURN

LANDING GEAR AND BRAKES

LDG CONTROL PANEL

DN

UP DN LOCK REL

STEERING SYSTEM

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

LANDING GEAR OPERATION SCHEMATIC

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

LANDING GEAR AURAL WARNING The landing gear aural logic uses the thrust lever angle, flap setting and radio altimeter to define the intention to land the airplane. The aural warning “LANDING GEAR” is announced and can not be silenced in the following situations:

SLAT/FLAP lever in a landing position (5 or FULL)

•

Regardless of thrust lever position and radio altitude.

SLAT/FLAP lever in the 0, 1, 2, 3 or 4 position

• • •

Radio altitude below 700 ft AGL, and Either thrust lever is set below 45° for two operative engines, or Thrust lever is set below 59° for a one-engine inoperative condition.

Radio Altimeter Fail

AOM-1502-003

•

In the event of dual radio altimeter failure, the warning inhibition button silences the aural warning only if the SLAT/FLAP lever is in the 0, 1, 2, 3 or 4 position.

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REVISION 21

Landing Gear Operation

Page 5

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

AIRPLANE OPERATIONS MANUAL

14-13-15 Copyright © by Embraer. Refer to cover page for details.

Page 6

Landing Gear Operation

REVISION 21

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

BRAKES The brake system employs brake-by-wire rudder pedals located at both pilot stations. Hydraulic system 1 provides pressure to the outboard brakes and hydraulic system 2 provides pressure to the inboard brakes. The Emergency/Parking brake has the ability to stop the airplane if a failure happens simultaneously on both hydraulic systems or if both brake control modules fail. The brake wear can be monitored through the brake wear pins located on each main wheel.

NORMAL OPERATION The system has two brake control modules (BCM) and one optional auto brake control module (ABM). • BCM 1 is connected to DC ESS BUS 1 and controls the outboard brakes.

•

BCM 2 is connected to DC ESS BUS 2 and controls the inboard brakes.

•

ABM is connected to DC BUS 2.

During normal operation the BCM provides protection from skidding and locking of the main wheels. It also has some functions to improve the braking performance. The BCM main functions are: • Locked wheel protection. • Antiskid protection. • Automatic wheel braking. • Touchdown protection.

LOCKED WHEEL PROTECTION Locked wheel protection is active anytime on ground and at wheel speeds above 30 kt.

AOM-1502-003

The system logic compares wheel speed signals between the left and the right inboard brakes or between the left and the right outboard brakes. If a wheel speed is 33% or below its associated paired wheel speed, the brake control module commands zero pressure to the brake of the slower wheel, thus allowing speed equalization. The tolerance between wheel speeds is provided to permit differential braking, for steering purposes.

14-13-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Brakes

Page 1

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

AIRPLANE OPERATIONS MANUAL

ANTISKID PROTECTION Anti skid protection prevents tire skidding and maximizes brake efficiency according to the runway surface. The system controls the amount of hydraulic pressure applied to the brakes and, if necessary, reduces the wheel brake pressure in order to recover wheel speed and prevent tire skidding. For wheel speeds below 10 kt, the anti skid protection is deactivated, thus allowing the pilot to lock and pivot on a wheel for maneuvering. Anti skid protection is not available for the emergency/parking brake system.

AUTOMATIC WHEEL BRAKING Automatic wheel braking prevents the main landing gear from being retracted with the wheels spinning. A dedicated device inside the nose landing gear bay stops the nose landing gear wheels from spinning.

TOUCHDOWN PROTECTION Touchdown protection prevents the airplane from touching down with the main landing gear brakes applied. It is deactivated: • Three seconds after WOW has sensed the ground; or

•

When wheel speed is above 50 kt.

EMERGENCY/PARKING BRAKE The Emergency/Parking brake is operated through a handle located on the pedestal control panel and is powered by hydraulic systems 1 and 2. The emergency/parking brake system has pressure accumulators isolated from both normal hydraulic systems. The accumulators have sufficient pressure to provide six full-brake applications.

PARKING BRAKE OPERATION

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Page 2

Brakes

REVISION 17

AOM-1502-003

When used as a parking brake, the handle must be pulled until it locks at the upper position.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

LANDING GEAR AND BRAKES

EMERGENCY BRAKE OPERATION If both normal brakes fail the handle will actuate as an emergency brake. In this case it has to be pulled carefully and slowly as there is no anti-skid protection while braking with the Emergency/Parking brake. At high speeds, the deflection of the emergency/parking brake handle when the brake indicating light comes ON, provides sufficient pressure to start braking. As speed decreases the required deflection increases to maintain continuous braking.

FUSIBLE PLUGS The fusible plugs are pins attached to the wheels, which melt relieving tire pressure in case of tire overheat.

WHEEL (CUT VIEW)

FUSIBLE PLUG

EM170AOM140471A.DGN

TIRE

BRAKE WEAR PINS

AOM-1502-003

Brake Wear Pins indicate that brakes are worn-out and when the pins are flush with Brake Bracket Outer Face assembly, the brakes need replacement.

14-13-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Brakes

Page 3

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

AIRPLANE OPERATIONS MANUAL

BRAKE ASSEMBLY

14-13-20 Copyright © by Embraer. Refer to cover page for details.

Page 4

Brakes

REVISION 17

AOM-1502-003

BRACKET

EM170AOM140419.DGN

WEAR PIN

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

LANDING GEAR AND BRAKES

!EMBRAER 170/175 airplanes not equipped with autobrake EMERG/ PARKING BRAKE HANDLE PILOT

CO−PILOT

PEDAL TRANSDUCER

CMC / EICAS

THRUST LEVER R IDLE (DISCRETE)

MAU 1 BCM 1

HYD SYS #1 PRESS INDICATION (ASCB) PRESSURE HYDRAULIC SYSTEM 1

THRUST LEVER L IDLE (DISCRETE)

MAU 2 BCM 2

HYD SYS #2 PRESS INDICATION (ASCB) PRESSURE HYDRAULIC SYSTEM 2

SHUTOFF VALVE

1

4

BRAKE CONTROL VALVE

2

3

RETURN HYD FUSE

PRESSURE TRANSDUCER

WHEEL SPEED TRANSDUCER 1

2

3

4

R P

B B

R P

THERMAL RELIEF VALVE

DUAL EMERG/ PARKING BRAKE VALVE

CABLE

EM170AOM140171.DGN

PRESSURE SWITCH

AOM-1502-003

BRAKE SYSTEM SCHEMATIC

"

14-13-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Brakes

Page 5

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

AIRPLANE OPERATIONS MANUAL

AUTOBRAKE The autobrake system provides automatic braking at maximum deceleration rates, which may vary according to runway conditions, for landings and rejected takeoffs. The system modulates hydraulic pressure to the brakes in order to provide a constant deceleration rate corresponding to the level selected. If reverse thrust is actuated, the autobrake system will modulate the brake pressure to maintain the deceleration rate constant. The autobrake system can only be armed if the normal brake system is operational. Anti skid, touchdown and locked wheel protections are provided during autobrake operation. Four autobrake levels of deceleration (RTO, LO, MED, HI) are available via a selector knob on the cockpit main instrument panel. There are two modes of autobrake control: • Landing mode (LO, MED, HI). • Rejected take-off mode (RTO). NOTE: RTO is the selected takeoff mode with the maximum deceleration rate. This deceleration is equivalent to the maximum manual braking.

AUTOBRAKE LANDING AND RTO MODE Autobrake will be armed if the following conditions are met: REJECTED TAKEOFF MODE LO, MED or HI RTO In flight On ground Below 60 kt No faults Not pressed Any Any Idle or REV

LANDING MODE Selector Knob Position WOW Indication Wheel Speed Brake Control System Brake Pedal Position Thrust Levers Position

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Page 6

Brakes

REVISION 17

AOM-1502-003

Autobrake will be applied if the following conditions are met:

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

REJECTED TAKEOFF MODE ARMED LO, MED or HI RTO On ground Above 60 kt No faults Not pressed Idle or REV

LANDING MODE Condition Selector Knob Position WOW Indication (MLG) Wheel Speed Brake Control System Brake Pedal Position Thrust Levers Position

NOTE: For landing mode, the main landing gear WOW must indicate the airplane is on ground for more than 2 seconds to allow autobrake application. Landing and RTO modes will be disarmed if one of the following conditions occurs:

• •

The selector switch is set to the OFF position.

•

Brake control system failure is detected (while wheel speed is below 60 kt if RTO is selected).

•

Either thrust lever is advanced beyond idle during autobrake application. Autobrake will be disarmed if the following conditions are met:

Pedal braking is applied (while wheel speed is above 60 kt if RTO is selected).

REJECTED TAKEOFF MODE Selector Knob Position OFF or RTO OFF, LO, MED or HI WOW Indication In flight Faults detected Brake Control System Faults detected below 60 kt of wheel speed Pressed while Pressed (more than Brake Pedal Position Autobrake is being 20%) applied Above idle while Autobrake is being Thrust Levers Position applied The aural message “AUTOBRAKE” is activated when “armed” condition (LO, MED, HI or RTO) is changed to “disarmed” by

AOM-1502-003

LANDING MODE

14-13-20 Copyright © by Embraer. Refer to cover page for details.

REVISION 17

Brakes

Page 7

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

LANDING GEAR AND BRAKES

autobrake module (ABM) or brake control module (BCM) failure during parking, taxiing, takeoff roll or landing.

!EMBRAER 170/175 airplanes equipped with autobrake

EMERG/ PARKING BRAKE HANDLE

AUTOBRAKE

PILOT

OFF

CO−PILOT LO MED

RTO

HI

PEDAL TRANSDUCER

CMC / EICAS

THRUST LEVER R IDLE (DISCRETE)

MAU 1

PRESSURE HYDRAULIC SYSTEM 1

AUTO BRK

BCM 1

HYD SYS #1 PRESS INDICATION (ASCB)

THRUST LEVER L IDLE (DISCRETE)

MAU 2 BCM 2

HYD SYS #2 PRESS INDICATION (ASCB) PRESSURE HYDRAULIC SYSTEM 2

SHUTOFF VALVE

1

4

BRAKE CONTROL VALVE

2

3

RETURN HYD FUSE

PRESSURE TRANSDUCER

WHEEL SPEED TRANSDUCER 1

2

3

4

P

B B

R P

THERMAL RELIEF VALVE

DUAL EMERG/ PARKING BRAKE VALVE

CABLE

BRAKE SYSTEM SCHEMATIC

14-13-20

"

Copyright © by Embraer. Refer to cover page for details.

Page 8

Brakes

REVISION 17

AOM-1502-003

R

EM170AOM140498A.DGN

PRESSURE SWITCH

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

NOSEWHEEL STEERING SYSTEM The airplane nose landing gear has steer-by-wire control powered by hydraulic system 2 and electronically controlled by the Nosewheel Steering Control Module.

OPERATION To engage the nose wheel steering system: – The hydraulic system 2 needs to be pressurized. – The external steering disengage switch must be in the engaged position. – The handwheel steering must be pressed and released for rudder pedal steering or kept pressed for handwheel steering. NOTE: After a power up, the first steering engagement must be performed with the airplane stopped. If this condition is not met, the hardover test might not be successfully accomplished by the system and STEER FAIL message may be displayed. The nose wheel steering has three modes of operation: the handwheel steering mode, the rudder pedal steering mode and the free wheel steering mode.

HANDWHEEL STEERING MODE The handwheel steering mode is used for low speed control and whenever a wider turn angle is required.

OPERATION

!PRE-MOD SB 0170-32-0034

To operate in handwheel steering mode the handwheel steering must be kept pressed. Steering angle varies from ±76° up to 40 kt decreasing linearly to ±7° at 100 kt.

AOM-1502-003

Upon releasing the handwheel steering, the system reverts to rudder pedal steering mode.

14-13-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Nosewhell Steering System

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

LANDING GEAR AND BRAKES

+/− 76

+/− 7 40

100

WHEEL SPEED [kt]

EM170AOM000246.DGN

MAX STEERING ANGLE [deg]

MAXIMUM STEERING ANGLE

The wheel deflection as function of the handwheel angular deflection is not linear. The steering system is more sensitive at nose wheel deflections above 10°. The pilot will easily notice that small handwheel movements cause a greater deflection of the nose wheel when it is already deflected more than 10°.

WHEEL DEFLECTION

43°

10° 40°

60°

80°

HANDWHEEL ANGULAR DEFLECTION

EM170AOM140694A.DGN

76°

HANDWHEEL GAIN

14-13-25 Copyright © by Embraer. Refer to cover page for details.

Page 2

Nosewhell Steering System

REVISION 20

AOM-1502-003

"

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

LANDING GEAR AND BRAKES

OPERATION

!Airplanes equipped with NWSCM-04 and on or POST-MOD SB 0170-32-0034

To operate in handwheel steering mode the handwheel steering must be kept pressed. The steering handwheel command is limited to a maximum steering angle of ± 76° allowed up to 10 kt. Over around 26 kt the maximum steering deflection is 20°. Over 100 kt the maximum deflection is ± 7°. Upon releasing the handwheel steering, the system reverts to rudder pedal steering mode.

MAX DEFLECTION ANGLE [deg]

+/− 20 +/− 7 10

26.2

89

100

WHEEL SPEED [kt]

EM170AOM141080A.DGN

+/− 76

MAXIMUM STEERING ANGLE

The wheel deflection as function of the handwheel angular deflection is not linear.

AOM-1502-003

The functional characteristic of the steering handwheel angle is divided into separated linear parts with different gradients.

14-13-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Nosewhell Steering System

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

LANDING GEAR AND BRAKES

WHEEL DEFLECTION

EM170AOM141081B.DGN

+76°

+25° +5° 20°

50°

80°

HANDWHEEL ANGULAR DEFLECTION

HANDWHEEL GAIN

"

RUDDER PEDAL STEERING MODE The rudder pedal steering mode is designed to be used on high speed operations on ground or whenever a wider angle turn is not required.

OPERATION Rudder pedal steering is active on ground any time the STEER OFF message is not displayed on EICAS. If in handwheel steering mode, the handwheel steering must be pressed and released to activate rudder pedal steering mode. The maximum steering angle of the rudder pedal is ±7°.

FREE WHEEL STEERING MODE The free wheel steering mode is mostly used for towing or when the normal steering system fails.

OPERATION The steering system can be disengaged reverting to free wheel by means of: – The steering disengage button located on both control wheels.

In the free wheel mode, the airplane steering can be carried out by use

14-13-25 Copyright © by Embraer. Refer to cover page for details.

Page 4

Nosewhell Steering System

REVISION 20

AOM-1502-003

– The external steering disengage switch located on the external power connection access.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

of rudder, differential brake and/or asymmetrical thrust. During taxi, smooth radius turns must be performed. The free wheel mode is automatically selected when: – Failure of the Air/Ground signal occurs. – Nose wheel angle is greater than 76°. – Nose wheel steering system failure is detected.

STEERING

D I S E N G AC GPU GROUND SERVICE SW

CKPT CALL

LAN

MIC/PHONE E N G A G E

EM170AOM140177B.DGN

AVAIL IN USE

RAMP INPH

AOM-1502-003

EXTERNAL STEERING DISENGAGEMENT SWITCH

14-13-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Nosewhell Steering System

Page 5

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

LANDING GEAR AND BRAKES

MINIMUM TURNING RADII !EMBRAER 170 Models

R 15.56M 51ft 0in R 16.55M 54ft 3in

R 5.65M 18ft 6in

76°

16.66M 54ft 8in (RUNWAY MINIMUM WIDTH)

R10.73M 35ft 2in

R 11.01M 36ft 1 in

R 5.13M 16ft 10in

EM170AOM140180.DGN

R 14.85M 48ft 9in

MINIMUM TURNING RADII

14-13-25 Copyright © by Embraer. Refer to cover page for details.

Page 6

Nosewhell Steering System

REVISION 20

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

!EMBRAER 175 Models with wing tip

R 16.58 m 54 ft 4.7 in. R 17.45 m 57 ft 2.8 in. R 5.97 m 19 ft 7 in.

76°

R 11.78 m 38 ft 8 in. 18.04 m 59 ft 2 in. (RUNWAY MINIMUM WIDTH)

R 12.07 m 39 ft 7 in. R 5.45 m 17 ft 11 in.

EM170AOM140674B.DGN

R 15.80 m 51 ft 10 in.

MINIMUM TURNING RADII

AOM-1502-003

"

14-13-25 Copyright © by Embraer. Refer to cover page for details.

REVISION 20

Nosewhell Steering System

Page 7

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

LANDING GEAR AND BRAKES

!EMBRAER 175 Models with enhanced wing tip or POST-MOD SB-170-57-0058

R 17.62 m 57 ft 9.5 in. R 17.45 m 57 ft 2.8 in. R 5.97 m 19 ft 7 in.

76°

R 11.78 m 38 ft 8 in. 18.04 m 59 ft 2 in. (RUNWAY MINIMUM WIDTH)

R 12.07 m 39 ft 7 in. R 5.45 m 17 ft 11 in.

EM170AOM141357B.DGN

R 15.80 m 51 ft 10 in.

MINIMUM TURNING RADII

14-13-25 Copyright © by Embraer. Refer to cover page for details.

Page 8

Nosewhell Steering System

REVISION 20

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

EICAS MESSAGES

!Airplanes not equipped with Autobrake

TYPE WARNING

MESSAGE LG LEVER DISAG

BRK OVERHEAT

BRK LH (RH) FAIL

EMER BRK FAIL

CAUTION

LG NO DISPATCH LG NOSE DOOR OPEN

LG WOW SYS FAIL PRKG BRK NOT RELEASED

AOM-1502-003

STEER FAIL

MEANING A discrepancy between the position of the landing gear control lever and at least one landing gear is detected. Brake temperature has exceeded the cautionary operating range (amber). Loss of both wheel brakes (inboard and outboard) of either the left or right landing gear. Both brake accumulator pressures are low and low pressure of hydraulic systems 1 and 2 is detected. Landing gear dispatchability is affected. Nose landing gear is locked up and nose landing gear door is open. Indicates a failure condition in the WOW indication system. Parking brake not fully released. Indicates a steering system failure condition when the landing gear is down.

14-13-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

EICAS Messages

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

TYPE

MESSAGE

BRK CONTROL FAULT

BRK LH (RH) FAULT ADVISORY BRK PEDL LH (RH) SEAT FAIL

EMER BRK FAULT

LG TEMP EXCEEDANCE STEER FAULT STATUS

STEER OFF

MEANING Comprehends different brake control failures, which may result or not in an airplane performance degradation. In the worst case scenario, the failure leads to a minor (less than 10%) braking performance degradation and no penalty on landing distance is expected. Loss of one wheel brake (inboard or outboard) of either the left or right landing gear. One pedal of the left or right hand seat has failed. Pressure on one brake accumulator is low or the inboard and outboard park brake pressures are in disagreement. Indicates non-dispatch condition related to the landing gear after a brake overheat. Steering system is degraded. Steering is disconnected.

!Airplanes equipped with Autobrake OR POST-MOD SB 170-32-0014

TYPE WARNING

MESSAGE LG LEVER DISAG

"

MEANING A discrepancy between the position of the landing gear control lever and at least one landing gear is detected.

14-13-30 Copyright © by Embraer. Refer to cover page for details.

Page 2

EICAS Messages

REVISION 21

AOM-1502-003

LANDING GEAR AND BRAKES

AIRPLANE OPERATIONS MANUAL

TYPE

MESSAGE AUTOBRAKE FAIL BRK OVERHEAT

BRK LH (RH) FAIL

EMER BRK FAIL CAUTION LG NO DISPATCH LG NOSE DOOR OPEN

LG WOW SYS FAIL PRKG BRK NOT RELEASED

AOM-1502-003

STEER FAIL

SYSTEMS DESCRIPTION LANDING GEAR AND BRAKES

MEANING Autobrake function is no longer available. Brake temperature has exceeded the cautionary operating range (amber). Loss of both wheel brakes (inboard and outboard) of either the left or right landing gear. Both brake accumulator pressures are low and low pressure of hydraulic systems 1 and 2 is detected. Landing gear dispatchability is affected. Nose landing gear is locked up and nose landing gear door is open. Indicates a failure condition in the WOW indication system. Parking brake not fully released. Indicates a steering system failure condition when the landing gear is down.

14-13-30 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

EICAS Messages

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

LANDING GEAR AND BRAKES

TYPE

MESSAGE

BRK CONTROL FAULT

BRK LH (RH) FAULT ADVISORY BRK PEDL LH (RH) SEAT FAIL

EMER BRK FAULT

LG TEMP EXCEEDANCE STEER FAULT STATUS

STEER OFF

MEANING Comprehends different brake control failures, which may result or not in an airplane performance degradation. In the worst case scenario, the failure leads to a minor (less than 10%) braking performance degradation and no penalty on landing distance is expected. Loss of one wheel brake (inboard or outboard) of either the left or right landing gear. One pedal of the left or right hand seat has failed. Pressure on one brake accumulator is low or the inboard and outboard park brake pressures are in disagreement. Indicates non-dispatch condition related to the landing gear after a brake overheat. Steering system is degraded. Steering is disconnected.

14-13-30 Copyright © by Embraer. Refer to cover page for details.

Page 4

EICAS Messages

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION OXYGEN

SECTION 14-14 OXYGEN TABLE OF CONTENTS Block

Page

General Description............................................. 14-14-01 .... GENERAL DESCRIPTION..................................... 14-14-01 ....

1 1

Controls and Indications..................................... 14-14-05 .... MASK STOWAGE BOX AND CREW MASK......... 14-14-05 .... OXYGEN CONTROL PANEL................................. 14-14-05 .... SYNOPTIC PAGE ON MFD.................................. 14-14-05 .... CREW OXYGEN CYLINDER AND REFILL POINT LOCATION........................................... 14-14-05 ....

1 1 3 4

Flight Crew Oxygen System............................... 14-14-10 .... GENERAL.............................................................. 14-14-10 .... OXYGEN CYLINDER............................................. 14-14-10 .... FLIGHT CREW FULL-FACE MASKS.................... 14-14-10 .... PROTECTIVE BREATHING EQUIPMENT (PBE).. 14-14-10 ....

1 1 1 1 3

Passenger Oxygen............................................... 14-14-15 .... PASSENGER OXYGEN SYSTEM......................... 14-14-15 ....

1 1

5

Airplanes equipped with 11 ft3 Portable Oxygen Cylinder

PORTABLE OXYGEN CYLINDER......................... 14-14-15 ....

4

AOM-1502-003

Airplanes equipped with 4.25 ft3 Portable Oxygen Cylinder

PORTABLE OXYGEN CYLINDER......................... 14-14-15 ....

7

EICAS Messages.................................................. 14-14-20 .... EICAS MESSAGES............................................... 14-14-20 ....

1 1

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REVISION 20

Table of Contents

Page 1

SYSTEMS DESCRIPTION OXYGEN

AIRPLANE OPERATIONS MANUAL

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Page 2

Table of Contents

REVISION 20

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION OXYGEN

GENERAL DESCRIPTION The oxygen system provides supplemental oxygen to the flight crew and passengers when a lack of oxygen supply occurs on board. The airplane oxygen system is comprised of two systems and other oxygen devices. Oxygen system parameters and indications are displayed on both MFD synoptic pages. System messages are displayed on EICAS displays.

FLIGHT CREW OXYGEN SYSTEM This system provides supplemental oxygen stored in a rechargeable cylinder and also provides protection to the flight crew in event of smoke and other harmful gases.

PASSENGER OXYGEN SYSTEM This system provides only supplemental chemically generated oxygen to passengers and flight attendants.

PROTECTIVE BREATHING EQUIPMENT (PBE) The PBE provides the crew with positive pressure oxygen for respiratory and visual protection against the effects of smoke and other harmful gases.

PORTABLE OXYGEN CYLINDERS

AOM-1502-003

Portable oxygen cylinders are located throughout the airplane for use by the flight attendants to assist passengers in case of sudden decompression or first aid purposes.

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REVISION 9

General Description

Page 1

SYSTEMS DESCRIPTION OXYGEN

AIRPLANE OPERATIONS MANUAL

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Page 2

General Description

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

OXYGEN

MASK STOWAGE BOX AND CREW MASK PILOT AND COPILOT CONSOLES

2

3

TEST RESET

0 G 10 % ER EM

OXY ON

1

NO RM

SK

P EE SW

AS SY

A E R O S Y S T E M S

−O N

MA 200 0 CRE GEN W OXY

NELLCOR PURITAN BENNETT PURITAN BENNETT AERO SYSTEMS CO.

MASK STOWAGE BOX

4

AOM-1502-003

5

EM170AOM140187B.DGN

6

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REVISION 21

Controls and Indications

Page 1

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

OXYGEN

1 - FLOW INDICATOR – A bright yellow star when visible indicates that oxygen is flowing. 2 - TEST/RESET BUTTON (SPRING LOADED) – Pressing this button with the mask stowed tests the oxygen mask and activates the microphone. The flow indicator star momentarily blinks and oxygen flow will be audible through audio system. – Pressing this button with the mask not stowed and the mask box door closed shuts off the oxygen flow, turns off mask’s microphone and returns the communication from the cockpit speakers to the headsets. 3 - OXY ON FLAG – This flag appears whenever oxygen is supplied to the mask. 4 - PURGE VALVE – This valve allows oxygen flow into the face seal, purging any smoke and fumes. – This valve automatically opens when the oxygen supply control knob is rotated to the emergency mode position. 5 - HARNESS INFLATION CONTROL VALVE – Pressing this valve inflates the harness so that the mask may be donned. Releasing the button deflates the harness securing the mask in place. 6 - OXYGEN SUPPLY CONTROL KNOB (ROTARY ACTION) – Rotating the knob selects the mode of oxygen supply. supplies pure oxygen under positive pressure. supplies pure oxygen at all cabin altitudes. supplies an oxygen/air mixture on demand (the ratio depends on cabin altitude).

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Controls and Indications

REVISION 21

AOM-1502-003

EMERG: 100%: NORM:

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION OXYGEN

OXYGEN CONTROL PANEL OVERHEAD PANEL

1

2

OFF

OVRD

MASK DEPLOYED

ON

MASKS DEPLOY

EM170AOM140188.DGN

PASSENGER OXYGEN AUTO

1 - MASKS DEPLOY SELECTOR KNOB (ROTARY ACTION) OFF: AUTO: OVRD:

disables automatic deployment of passenger oxygen masks. enables automatic deployment of passenger oxygen masks when cabin pressure altitude is above 14000 ft. deploys the passenger oxygen masks regardless of cabin altitude.

2 - MASK DEPLOYED INDICATOR LIGHT

AOM-1502-003

– An ON light illuminates, indicating that the passenger and flight attendant oxygen masks have been deployed.

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REVISION 21

Controls and Indications

Page 3

SYSTEMS DESCRIPTION OXYGEN

AIRPLANE OPERATIONS MANUAL

SYNOPTIC PAGE ON MFD !MAU load 21.2 and on OR POST-MOD SB 170-31-0028

The status synoptic page provides digital oxygen pressure indication.

!!Commercial airplanes equipped with MAU load 21.2 and on OR POST-MOD SB 0170-31-0028

MFD

PSI CREW

171O

1 EM170AOM140801C.DGN

OXY PRESS

""

A difference in pressure indication between the MFD and the oxygen pressure gauge outside the airplane may be observed. The difference occurs due to a temperature correction in the MFD that does not occur on the oxygen pressure gauge. 1 - COCKPIT OXYGEN PRESSURE INDICATION GREEN: normal operating range (minimum for three crew members in the cockpit). CYAN: advisory operating range (minimum for two crew members in the cockpit). AMBER: cautionary operating range (no dispatch). AMBER DASHED: invalid information or a value out of the valid range.

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Controls and Indications

REVISION 21

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION OXYGEN

CREW OXYGEN CYLINDER AND REFILL POINT LOCATION

INDICADOR DE DESCARGA DE OXIGÊNIO OXYGEN DISCHARGE INDICATOR

2

3

0

1000 1500 500 2000

USE NO OIL

PSI

OXYGEN

1 USAR SOMENTE OXIGÊNIO DE AVIAÇÃO

AOM-1502-003

USE AVIATION OXYGEN ONLY

EM170AOM140181A.DGN

SUPPLY PRSSURE MADE IN USA 26

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REVISION 21

Controls and Indications

Page 5

SYSTEMS DESCRIPTION OXYGEN

AIRPLANE OPERATIONS MANUAL

1 - OXYGEN PRESSURE GAUGE – Displays the cylinder static pressure. 2 - OXYGEN RECHARGE VALVE – The valve is used to recharge the cylinder by maintenance personnel. 3 - DISCHARGE INDICATOR DISC

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Page 6

Controls and Indications

REVISION 21

AOM-1502-003

GREEN: normal operating range. The green oxygen cylinder pressure relief disc blows out in the event of an overpressure.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION OXYGEN

GENERAL Flight crew oxygen is provided via a conventional, high-pressure, gaseous-type system in which the oxygen is stored in a rechargeable cylinder.

OXYGEN CYLINDER Oxygen is stored in a 77 ft3 cylinder, pressurized up to 1850 psi at 21°/70°F. The cylinder is installed in the forward cargo compartment and does not need to be removed to recharge. After loss of cabin pressure, sufficient oxygen is provided for all cockpit members to permit emergency descent from 41000 ft to 10000 ft in 22 min with mask regulator on 100% mode and continuing cruise at 10000 ft for 98 min with mask regulator on NORMAL mode.

FLIGHT CREW FULL-FACE MASKS Flight crew and observer full-face, quick donning masks and regulators are stowed in oxygen mask storage boxes near each seat. The masks provide supplemental oxygen and protection from smoke and other harmful gases.

FLIGHT CREW FULL-FACE MASKS TEST The masks are tested utilizing the TEST/RESET button. With the mask stowed and the regulator knob set to 100%, pressing and holding the TEST/RESET button will cause a short blink of flow indicator and an oxygen flow sound will be audible in the speakers. On the radio panel, the SPKR Indicator will illuminate. Once the mask fully pressurizes the indicator must go out showing the system is leak free. Releasing the TEST/RESET button will terminate the test.

FLIGHT CREW FULL-FACE MASKS OPERATION

AOM-1502-003

Opening the stowage box’s mask automatically initiates the oxygen flow. Pressing the harness inflation control valve will inflate the harness, enabling its quick donning. Releasing the button will deflate the harness, firmly fitting it to the head. The mask is designed to be donned within 5 s. The oxygen will flow until the stowage box’s doors are closed.

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REVISION 18

Flight Crew Oxygen System

Page 1

SYSTEMS DESCRIPTION OXYGEN

AIRPLANE OPERATIONS MANUAL

FLIGHT CREW FULL-FACE MASKS COMMUNICATION The mask is also connected to the communications system. When the oxygen mask stowage box door is opened the mask’s microphone is automatically activated and the headset boom microphone is deactivated. The speakers are also automatically activated and the communication reception is possible through the speakers or the headsets. When the oxygen mask stowage box is closed and the TEST/RESET switch is pressed the headset boom microphone is restored and the mask’s microphone is turned off.

FULL FACE MASK OPERATING MODES Normal: Normal Mode provides supplemental oxygen diluted with cabin air according to the cabin pressure altitude until a preset point where the user inhales 100% oxygen. This feature is to conserve the amount of oxygen consumed from the supply source while still maintaining protective physiological levels. 100%: 100% Mode provides non-diluted oxygen to the crew regardless of cabin altitude. Emergency: The “EMER” setting provides non-diluted oxygen regardless of cabin altitude, with a slightly positive pressure. This setting should be used to eliminate condensation or to purge smoke and toxic fumes that may get into the mask.

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Page 2

Flight Crew Oxygen System

REVISION 18

AOM-1502-003

When the mask is on emergency mode, the air pressure and flow make communication more difficult. To avoid communication disruption it is recommended not to use the EMER setting continuously, selecting the mode back to 100% or Normal after the mask is clear of smoke, fumes or condensation.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION OXYGEN

PROTECTIVE BREATHING EQUIPMENT (PBE) !Airplanes equipped with Scott Aviation PBE

The PBE unit is for emergency use only. It is vacuum-sealed in a transparent bag and contained within a carrying plastic case. The carrying case has an inspection window, which allows visualization of a “good condition strap” without opening the case. In case of leakage, the “good condition indicator” will turn from blue to pink, indicating that the unit is unserviceable. In case of a vacuum loss, even with the “good condition indicator” blue, the unit is also unserviceable. The equipment hood isolates the user’s head from the external ambient gases by means of an elastic neck seal. Pulling the chemical oxygen generator actuation ring initiates the oxygen flow. Once the oxygen flow is started, it cannot be stopped. Oxygen will be supplied for at least 15 min. The PBE unit provides the crew with positive pressure oxygen for respiratory and visual protection against the effects of smoke and other harmful gases at altitudes up to 40000 ft. PBE device consists basically of a double layer synthetic material hood and a life support pack, where a chemical reaction produces oxygen.

LIFE SUPPORT PACK

DOUBLE LAYER HOOD

CARRYING CASE

AOM-1502-003

GOOD CONDITION INDICATOR

EM170AOM140422C.DGN

ACTUATION RING

PROTECTIVE BREATHING EQUIPMENT

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Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Flight Crew Oxygen System

Page 3

SYSTEMS DESCRIPTION OXYGEN

AIRPLANE OPERATIONS MANUAL

2

1

REMOVE DEVICE FROM STORAGE CASE.

3

TEAR OFF PULL STRIP AND REMOVE DEVICE FROM PLASTIC PROTECTIVE WRAPPER.

PULL

4

PULL ACTUATION RING IN DIRECTION INDICATED, STARTING OXYGEN FLOW. HEAR THE FLOW NOISE OF OXYGEN.

5

WITH THE SOUND OF OXYGEN FLOWING, HOLD DEVICE WITH LIFE SUPPORT PACK AWAY FROM USER; GRASP HOLE IN NECK SEAL WITH THUMBS.

BEND FORWARD FROM WAIST. INSERT CHIN INTO HOLE AND PULL HOOD ACROSS FACE AND OVER HEAD.

WHILE STANDING UPRIGHT, PULL HOOD DOWN UNTIL HEADBAND FIRMLY ENGAGES FOREHEAD. CLEAR NECK SEAL OF OBSTRUCTIONS AND CHECK NECK SEAL FOR SECURE FIT.

EM170AOM140421.DGN

6

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Page 4

Flight Crew Oxygen System

REVISION 18

AOM-1502-003

PROTECTIVE BREATHING EQUIPMENT USAGE

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION OXYGEN

" !Airplanes equipped with ESSEX PBE

The PBE unit is for emergency use only. It is folded and packaged inside a moisture resistant pouch, and stowed in a protective container. The PBE unit is equipped with a humidity indicator which allows visualization of the unit serviceability. If humidity indicator color is blue the unit is serviceable and if humidity color is pink the unit must be removed from service within 36 h. The loss of vacuum in the inner packaging does not render the PBE unserviceable. Units that have lost vacuum remain serviceable as long as the humidity indicator color is blue. The PBE has two oxygen cylinders, and once the pouch is removed from the container, oxygen flow is initiated by snapping the two cylinders apart, and the hood donned. It will be supplied for at least 15 min. The PBE unit provides the crew with positive pressure oxygen for respiratory and visual protection against the effects of smoke and other harmful gases.

1

OPTIONAL

2 OR

AOM-1502-003

TWO HANDLED POUCH

TEAR OPEN POUCH

EM170AOM140604A.DGN

2

PROTECTIVE BREATHING EQUIPMENT BOX AND POUCHES

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REVISION 18

Flight Crew Oxygen System

Page 5

OXYGEN

1

AIRPLANE OPERATIONS MANUAL

2

3 END OF SERVICE INDICATOR

ACTIVATING THE ESSEX PBE OXYGEN SUPPLY PREPARATORY TO DONNING IT

DONNING THE ACTIVATED ESSEX PBE

OVERALL VIEW OF ESSEX CREWMEMBER PBE (AS WORN)

EM170AOM140605A.DGN

SYSTEMS DESCRIPTION

PROTECTIVE BREATHING EQUIPMENT DESCRIPTION

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Page 6

Flight Crew Oxygen System

REVISION 18

AOM-1502-003

"

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION OXYGEN

PASSENGER OXYGEN SYSTEM Individual chemical oxygen generators supply the passenger oxygen system during an emergency descent in the event of cabin depressurization. The passenger oxygen system provides supplemental oxygen only to the following: passenger service units (PSU), flight attendant stations, lavatories, and galley areas. For airplanes Post-Mod. SB 170-35-0008 or equipped with an equivalent modification factory incorporated, gaseous oxygen supply is provided in the lavatories.

PASSENGER OXYGEN MASKS Passenger oxygen masks are located in the PSUs above the passenger seats. Each PSU contains either two or three masks that supply oxygen only for approximately 12 min (standard), 14 min (optional) or 22 min (optional). The masks does not provide smoke protection and once the system starts supplying oxygen, they cannot be shut off.

OXYGEN SUPPLY To provide the required oxygen level for the user, the mask combines the available ambient air with the air supplied by the supplemental generator. The supplemental generator supplies oxygen according with the scheduled altitude defined on the airplane emergency descent profile.

PASSENGER OXYGEN SYSTEM OPERATION Passenger oxygen mask can be automatically or manually deployed. PASSENGER OXYGEN MASKS AUTOMATIC DEPLOYMENT The masks are automatically deployed when the cabin altitude is between 14000 ft to 14750 ft. PASSENGER OXYGEN MASKS MANUAL DEPLOYMENT

AOM-1502-003

Manual deployment can be performed from the cockpit by positioning the passenger oxygen selector knob to the OVRD position. A manual release tool located near each flight attendant station can be used in case dispensing unit door fails. The flight crew monitors the passenger oxygen mask deployment status through EICASmessages and an indicator light on the overhead panel.

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REVISION 20

Passenger Oxygen

Page 1

SYSTEMS DESCRIPTION OXYGEN

AIRPLANE OPERATIONS MANUAL

PASSENGER MASKS DEPLOY INDICATION The ON light on the overhead OXYGEN PANEL illuminates indicating that the passenger mask doors are commanded open. PASSENGER SIGNS AUTOMATION When the passenger mask doors are automatic or manual commanded open the system automatically turns ON the FASTEN SEAT BELT and the NO SMOKING (NO ELEC DEVICE optional) regardless of the switch position. The switch normal operation is inhibited until the MASKS DEPLOY switch is set to OFF position. PASSENGER MASKS USAGE The oxygen masks are held in a mask retainer. The yellow mask must be pulled out of the retainer. Oxygen flows throughout all masks in the dispensing unit whenever any yellow mask hanging from the dispensing unit is pulled downward.

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Page 2

Passenger Oxygen

REVISION 20

AOM-1502-003

A green, in-line flow indicator is visible in the transparent oxygen hose whenever oxygen is flowing to the masks.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION OXYGEN

DISPENSING UNIT

MASK RETAINER

GREEN IN−LINE FLOW INDICATOR

ACTUATOR PIN DISCONNECTED

MASK RESERVOIR BAG

CORD HOSE

EM170AOM140184C.DGN

ELASTIC STRAP

OXYGEN MASK

AOM-1502-003

DISPENSING UNITS/PASSENGER MASKS

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REVISION 20

Passenger Oxygen

Page 3

SYSTEMS DESCRIPTION OXYGEN

AIRPLANE OPERATIONS MANUAL

PORTABLE OXYGEN CYLINDER

!Airplanes equipped with 11 ft3 Portable Oxygen Cylinder

The portable oxygen cylinders are for flight attendants use to assist passengers in case of sudden cabin decompression or for first aid purposes. The cylinders store 312  (11 ft3) of oxygen, pressurized to 1800 psi. at 21°/70°F.

PORTABLE OXYGEN CYLINDER COMPONENTS The cylinders are fitted with a pressure gauge, a pressure regulator and an ON/OFF valve. A high-pressure frangible safety disk ruptures within a cylinder pressure of 2700 psi to 3000 psi. For airplane dispatchability, the minimum pressure shown on the gauge of portable oxygen cylinder, must be in accordance with the minimum guideline set either for airline or regulatory authority.

PORTABLE OXYGEN CYLINDER USE

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Page 4

Passenger Oxygen

REVISION 20

AOM-1502-003

Two continuous flow outlets are available; one regulates flow at 2  per minute for walk-around use and the second provides flow at 4  per minute for first aid use.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

OXYGEN

HIGH PRESSURE FRANGIBLE SAFETY DISK ON−OFF VALVE

PRESSURE REGULATOR

2 LITERS CONTINUOUS FLOW OUTLET 4 LITERS CONTINUOUS FLOW OUTLET PRESSURE GAUGE

11 cu.ft CYLINDER

ADJUSTABLE CARRYING STRAP

EM170AOM140672A.DGN

CONTINUOUS−FLOW MASK BAG (WITH TWO MASKS)

AOM-1502-003

PORTABLE OXYGEN CYLINDER

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REVISION 20

Passenger Oxygen

Page 5

SYSTEMS DESCRIPTION OXYGEN

AIRPLANE OPERATIONS MANUAL

PRESSURE REGULATOR HI

PRESSURE GAUGE

ON−OFF VALVE

EM170AOM140688A.DGN

LO

"

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Page 6

Passenger Oxygen

REVISION 20

AOM-1502-003

PORTABLE OXYGEN CYLINDER

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION OXYGEN

PORTABLE OXYGEN CYLINDER

!Airplanes equipped with 4.25 ft3 Portable Oxygen Cylinder

The portable oxygen cylinders are for flight attendants use to assist passengers in case of sudden cabin decompression or for first aid purposes. The cylinders store 120  (4.25 ft3) of oxygen, pressurized to 1800 psi at 21°/70°F.

PORTABLE OXYGEN CYLINDER COMPONENTS The cylinders are fitted with a pressure gauge, charging valve, relief valve, mask bag and an ON/OFF valve. A safety plug consists of a frangible safety disk covered by a fusible material. When the cylinder is exposed to temperatures above 71°, the fusible material melts, enabling the rupture of the Frangible Safety Disk, which will occur within a static pressure of 2500 psi to 2775 psi. For airplane dispatchability, the minimum pressure shown on the gauge of portable oxygen cylinder must be in accordance with the minimum guideline set either for airline or regulatory authority.

PORTABLE OXYGEN CYLINDER USE

AOM-1502-003

Two continuous flow outlets are available; one regulates flow at 2  per minute for walk-around use and the second provides flow at 4 per minute for first aid use.

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REVISION 20

Passenger Oxygen

Page 7

SYSTEMS DESCRIPTION OXYGEN

AIRPLANE OPERATIONS MANUAL

VALVE ON/OFF VALVE

2 LITERS CONTINUOUS FLOW OUTLET CHARGING VALVE

RELIEF VALVE

4 LITERS CONTINUOUS FLOW OUTLET

HI

OUTLET

SAFETY PLUG PRESSURE GAUGE

PRESSURE GAUGE

OUTLET

CONTINUOUS−FLOW MASK BAG (WITH TWO MASKS)

"

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Page 8

Passenger Oxygen

REVISION 20

AOM-1502-003

ADJUSTABLE CARRYING STRAP

EM170AOM140420A.DGN

TOP VIEW 4.25 cu.ft CYLINDER

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION OXYGEN

EICAS MESSAGES TYPE

CAUTION

MESSAGE CREW OXY LO PRESS PAX OXY NOT DEPLOYED PAX OXY SW NOT AUTO

AOM-1502-003

ADVISORY

OBSERVER OXY LO PRESS

MEANING Oxygen cylinder pressure is below minimum safety limits, or the pressure sensor has failed. Masks are not deployed after an automatic or manual command. Passenger oxygen selector is set to the OFF position. Oxygen cylinder pressure is below minimum safety limits for 3 crew members, or the pressure sensor has failed.

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REVISION 9

EICAS Messages

Page 1

SYSTEMS DESCRIPTION OXYGEN

AIRPLANE OPERATIONS MANUAL

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Page 2

EICAS Messages

REVISION 9

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION WARNING SYSTEM

SECTION 14-15 WARNING SYSTEM TABLE OF CONTENTS

AOM-1502-003

Block

Page

General Description............................................. 14-15-01 .... GENERAL DESCRIPTION..................................... 14-15-01 ....

1 1

Controls and Indications..................................... 14-15-05 .... GLARESHIELD PANEL......................................... 14-15-05 .... TAKEOFF CONFIG CHECK BUTTON.................. 14-15-05 .... STALL WARNING PANEL...................................... 14-15-05 .... GLARESHIELD EGPWS PANEL........................... 14-15-05 .... CONTROL PEDESTAL EGPWS PANEL............... 14-15-05 .... EGPWS SELECTION ON MFD............................. 14-15-05 .... EGPWS DISPLAY ON MFD.................................. 14-15-05 .... EGPWS DISPLAY ON PFD................................... 14-15-05 .... WINDSHEAR INDICATION ON PFD..................... 14-15-05 .... TCAS MAP OVERLAY FORMAT WINDOW.......... 14-15-05 .... TCAS ZOOM FORMAT WINDOW......................... 14-15-05 .... TCAS INDICATION ON PFD................................. 14-15-05 ....

1 1 2 2 3 5 6 7 9 10 11 13 15

Monitor Warning Function (MWF)...................... 14-15-07 .... MONITOR WARNING FUNCTION (MWF)............ 14-15-07 ....

1 1

Visual Warning..................................................... 14-15-10 .... VISUAL WARNING................................................ 14-15-10 .... WARNING LIGHTS................................................ 14-15-10 .... MESSAGES ON EICAS......................................... 14-15-10 ....

1 1 1 1

Aural Warning....................................................... 14-15-15 .... AURAL WARNING................................................. 14-15-15 .... VOICE MESSAGES............................................... 14-15-15 ....

1 1 3

Takeoff Configuration Warning........................... 14-15-20 .... TAKEOFF CONFIGURATION WARNING............. 14-15-20 ....

1 1

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REVISION 16

Table of Contents

Page 1

SYSTEMS DESCRIPTION WARNING SYSTEM

AIRPLANE OPERATIONS MANUAL

Block Page Stall Protection System....................................... 14-15-25 .... 1 STALL PROTECTION SYSTEM............................ 14-15-25 .... 1 Enhanced Ground Proximity Warning System.. 14-15-30 .... 1 ENHANCED GROUND PROXIMITY WARNING SYSTEM (EGPWS)......................................... 14-15-30 .... 1 EGPWS AURAL WARNINGS................................ 14-15-30 .... 4 TERRAIN MAPPING SELECTION........................ 14-15-30 .... 7 TERRAIN AWARENESS DISPLAY........................ 14-15-30 .... 8 EGPWS MESSAGES............................................. 14-15-30 .... 12 Windshear Detection and Escape...................... 14-15-35 .... GENERAL.............................................................. 14-15-35 .... WINDSHEAR DETECTION................................... 14-15-35 .... WINDSHEAR ESCAPE GUIDANCE MODE......... 14-15-35 .... WINDSHEAR SYSTEM TEST............................... 14-15-35 ....

1 1 1 3 5

Traffic Collision Avoidance System................... 14-15-40 .... TRAFFIC COLLISION AVOIDANCE SYSTEM (TCAS)............................................................. 14-15-40 .... TCAS OPERATION ON THE MCDU..................... 14-15-40 .... TCAS STATUS ANNUNCIATIONS........................ 14-15-40 .... TCAS WARNING INHIBITIONS............................. 14-15-40 ....

1

EICAS Messages.................................................. 14-15-45 .... EICAS MESSAGES............................................... 14-15-45 ....

1 1

14-15-TOC Copyright © by Embraer. Refer to cover page for details.

Page 2

Table of Contents

REVISION 16

AOM-1502-003

1 1 3 8

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION WARNING SYSTEM

GENERAL DESCRIPTION The airplane is provided with a variety of warnings to notify crew on systems status, malfunctions, and abnormal airplane configurations. Alarm lights provide indication of a system status. An Engine Indication and Crew Alerting System (EICAS) provides the flight crew with a four-level alert messaging system. A fifth level is provided for maintenance purposes only. Besides the five displays in the main panel, two displays are provided through the Multi-function Control Display Unit (MCDU). Some of the more critical messages also generate an aural warning. Sensitive warning is available through the Stall Protection System (SPS), which shakes the control column if an impending stall is verified.

AOM-1502-003

To aid navigation and approach procedures, an Enhanced Ground Proximity Warning System (EGPWS), Traffic Alert and Collision Avoidance System (TCAS), and a Windshear Detection and Escape Guidance System are also provided.

14-15-01 Copyright © by Embraer. Refer to cover page for details.

REVISION 10

General Description

Page 1

SYSTEMS DESCRIPTION WARNING SYSTEM

AIRPLANE OPERATIONS MANUAL

14-15-01 Copyright © by Embraer. Refer to cover page for details.

Page 2

General Description

REVISION 10

AOM-1502-003

INTENTIONALLY BLANK

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION WARNING SYSTEM

GLARESHIELD PANEL MAIN PANEL

WARN

2 EM170AOM140197.DGN

1

CAUT

1 - MASTER WARNING PUSHBUTTON – A red light blinks inside the button when a new warning message is displayed on the EICAS. – Acknowledges the warning messages and extinguishes the associated blinking. 2 - MASTER CAUTION PUSHBUTTON – An amber light blinks inside the button when a new caution message is displayed on the EICAS.

AOM-1502-003

– Acknowledges the caution messages and extinguishes the associated blinking.

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REVISION 10

Controls and Indications

Page 1

SYSTEMS DESCRIPTION WARNING SYSTEM

AIRPLANE OPERATIONS MANUAL

TAKEOFF CONFIG CHECK BUTTON CONTROL PEDESTAL

CONFIG EM170AOM140199.DGN

T/O

1 - TAKEOFF CONFIGURATION CHECK BUTTON – Checks the takeoff configuration.

STALL WARNING PANEL CONTROL PEDESTAL

CONTROLS RUDDER

STALL

MODE SPOILERS

WARNING

SHAKER 1 CUTOUT

SHAKER 2 CUTOUT

1

EM170AOM140201.DGN

FLIGHT ELEVATORS

1 - SHAKER CUTOUT BUTTON

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Page 2

Controls and Indications

REVISION 10

AOM-1502-003

– When pushed in, cuts out the associated shaker channel.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION WARNING SYSTEM

GLARESHIELD EGPWS PANEL EGPWS TERRAIN SYSTEM OVERRIDE MAIN PANEL

EM170AOM140213.DGN

GND PROX TERR INHIB

GROUND PROXIMITY TERRAIN INHIBIT PUSHBUTTON

AOM-1502-003

– When pushed in, inhibits EGPWS and thus avoids unwanted terrain alerts in airports not covered by EGPWS database.

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REVISION 10

Controls and Indications

Page 3

SYSTEMS DESCRIPTION WARNING SYSTEM

AIRPLANE OPERATIONS MANUAL

EGPWS GLIDESLOPE CANCELLATION

MAIN PANEL

EM170AOM140214A.DGN

GND PROX G/S INHIB

GROUND PROXIMITY GLIDESLOPE INHIBIT – Momentary pushbutton annunciator used to manually cancel glideslope alerts.

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Page 4

Controls and Indications

REVISION 10

AOM-1502-003

– Illuminates when pressed any time below 2000 ft nominal radar altitude and will be automatically reset (light off) by climbing above 2000 ft nominal or descending below 30 ft.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

WARNING SYSTEM

CONTROL PEDESTAL EGPWS PANEL FLAP OVERRIDE SWITCH (GUARDED)

CONTROL PEDESTAL

EM170AOM140216A.DGN

GND PROX FLAP OVRD

AOM-1502-003

– Inhibits triggering flap alerts in case of landings where flap configuration is different from normal landing flap configuration.

14-15-05 Copyright © by Embraer. Refer to cover page for details.

REVISION 10

Controls and Indications

Page 5

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

WARNING SYSTEM

EGPWS SELECTION ON MFD MAIN PANEL

Map Navaids

Plan

Systems

36 O

7

Airports

N

WPT Ident Progress

Status 15 SAT ^C 25 TAT ^C 3OO TAS KTS DME1 LAX 65.3 NM 2O MIN

3

Vert Prof

Weather Terrain

X 1OO

Off

O.O5 L

E

TERRAIN SELECTION

EM170AOM140379B.DGN

6

TCAS

EGPWS MAP MENU FUNCTION – The TERRAIN mode enables the EGPWS terrain depiction to be displayed on the map overlay format window in solid or lower density colors including the sea level (0 ft MSL).

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Page 6

Controls and Indications

REVISION 10

AOM-1502-003

– The ranges allowed are: 5 NM, 10 NM, 25 NM, 50 NM, 100 NM, 200 NM, 300 NM, 500 NM and 1000 NM.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

WARNING SYSTEM

EGPWS DISPLAY ON MFD MAIN PANEL

Plan

Map

FMS1

MAGI 1

PXR 3O. O NM 5 MIN

3 4O 33

3

Systems

8

DME1 BXK 6O.O NM

N

3O

Fuel SAT +22 ^C TAT +24 ^C TAS 32O KTS

KELS

3

6

EM170AOM140378C.DGN

W

PXR

1OO

1

O.37 L

TERRAIN

TERRAIN

2

11O / O9O

1 - TERRAIN ANNUNCIATION Labels and colors: – TERRAIN GREEN: EGPWS is scanning the terrain. AMBER: system failure. – TERRAIN INHIBIT WHITE: terrain inhibit button is pressed in approach mode. – TERRAIN N/A

AOM-1502-003

AMBER: terrain awareness not available due to position accuracy degradation.

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REVISION 10

Controls and Indications

Page 7

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

WARNING SYSTEM

– TERRAIN TEST WHITE: self- test activated. 2 - TERRAIN DIGITAL DISPLAY – Displays the highest and lowest terrain/obstacle. 3 - TERRAIN INDICATION – Displays images of surrounding terrain. Different colors and their intensity represent the terrain elevation. – Colors: Solid red: warning terrain threat area. Solid yellow: caution terrain threat area. High-density red dots: terrain more than 2000 ft above airplane altitude. High-density yellow dots: terrain between 1000 ft and 2000 ft above airplane altitude. Low-density yellow dots: terrain between 500 ft (250 ft with gear down) below and 1000 ft above airplane altitude. Solid green: the highest terrain is not within 500 ft (250 ft with gear down) of airplane altitude. It may be displayed with dotted yellow when the airplane altitude is near than 500 ft (250 ft with gear down) of terrain. High-density green dots: terrain between 1000 ft and 500 ft below the airplane altitude. Low-density green dots: terrain between 2000 ft and 1000 ft below the airplane altitude.

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Page 8

Controls and Indications

REVISION 10

AOM-1502-003

Low-density cyan dots: sea level.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION WARNING SYSTEM

EGPWS DISPLAY ON PFD PFD

2O

2O

1O

1O

1O

1O

2O

2O

1 GND PROX

EM170AOM140376.DGN

-3.O

1 - GROUND PROXIMITY/PULL UP ANNUNCIATIONS – Label and colors: – GND PROX - Color: amber.

AOM-1502-003

– PULL UP - Color: red.

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REVISION 10

Controls and Indications

Page 9

SYSTEMS DESCRIPTION WARNING SYSTEM

AIRPLANE OPERATIONS MANUAL

WINDSHEAR INDICATION ON PFD

1

2

WSHR

1O

1O

1O

1O

2O

2O

EM170AOM140274A.DGN

2O WSHEAR 2O

1 - WINDSHEAR INDICATION (WSHEAR) – Indicates that a windshear has been detected. – Color: AMBER: caution windshear. RED: warning windshear. 2 - FLIGHT GUIDANCE ESCAPE MODE ENGAGEMENT

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Page 10

Controls and Indications

REVISION 10

AOM-1502-003

– Indicates the FGCS Windshear Escape Mode engagement.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

WARNING SYSTEM

TCAS MAP OVERLAY FORMAT WINDOW 3

2

Map Navaids

Plan

Systems

36O

7

Airports

N

WPT Ident

+1O

Vert Prof

DME1 LAX 65.3 NM 2O MIN

+5

4

5

6

X -O2

Weather

6 -O1

Terrain

O.O5 L

E

5O

Off

TCAS

TA/LA REL EXPD

EM170AOM140277B.DGN

TCAS

15 SAT ^C 25 TAT ^C 3OO TAS KTS

3

Progress

1

Status

1 - TCAS SELECTION IN MAP MENU – Actives the TCAS information to be displayed on the map overlay format window. 2 - RESOLUTION ADVISORY (RA) INDICATION – Symbol: Solid square. – Color: Red. 3 - TRAFFIC ADVISORY (TA) INDICATION – Symbol: Solid circle.

AOM-1502-003

– Color: Amber.

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REVISION 10

Controls and Indications

Page 11

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

WARNING SYSTEM

4 - PROXIMATE TRAFFIC INDICATION – Symbol: Solid diamond. – Color: Cyan. 5 - OTHER TRAFFIC INDICATION – Symbol: Hollow diamond. – Color: Cyan. 6 - TCAS MODE – Annunciates the TCAS operating mode. – Labels and Colors: TCAS FAIL: amber. TCAS TEST: green. TCAS OFF: amber. TA ONLY: green. TCAS TA/RA: green.

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Page 12

Controls and Indications

REVISION 10

AOM-1502-003

NOTE: The TA ONLY flashes amber when it is the active mode and a RA condition is detected.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

WARNING SYSTEM

TCAS ZOOM FORMAT WINDOW

1

2

3

4

NO BRG

TA O1ONM -98 TA O1ONM -98

5

TCAS

9 Range

8

+1O

ABS NRM/

TA ONLY REL EXPD

-O2

+5 /

/

7

OO

TCAS

O

Weather

6

EM170AOM140278.DGN

-O1

+O1

1 - RESOLUTION ADVISORY (RA) INDICATION – Symbol: Solid square. – Color: Red. 2 - TRAFFIC ADVISORY (TA) INDICATION – Symbol: Solid circle. – Color: Amber. 3 - PROXIMATE TRAFFIC INDICATION – Symbol: Solid diamond.

AOM-1502-003

– Color: Cyan.

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REVISION 10

Controls and Indications

Page 13

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

WARNING SYSTEM

4 - OTHER TRAFFIC INDICATION – Symbol: Hollow diamond. – Color: Cyan. 5 - NO BEARING INDICATION – TCAS temporarily unable to determine the bearing of other airplanes when a steep bank angle masks the directional antenna. 6 - TCAS MODE – Annunciates the TCAS operating mode. – Labels and Colors: TCAS FAIL: amber. TCAS TEST: green. TCAS OFF: amber. TA ONLY: green. TCAS TA/RA: green. NOTE: The TA ONLY flashes amber when it is the active mode and a RA condition is detected. 7 - MODE SELECTION – Selects the vertical mode to be displayed on TCAS. 8 - ABS SELECTION – Selects the absolute altitude mode to be displayed on TCAS. Deselecting this item enables the relative altitude mode. Absolute altitude mode will be replaced by relative altitude mode in the following situations: – An RA or TA intruder is displayed; – Deselection of the mode; or

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Page 14

Controls and Indications

REVISION 10

AOM-1502-003

– 15 seconds after being selected.

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

WARNING SYSTEM

9 - RANGE SELECTION – Enable the selection of the range to be displayed. The selection is changed through the selector knob in the CCD.

TCAS INDICATION ON PFD MAIN PANEL

2

AP

16O

LOC

GS

19O

1

4OOO 1OOO 25OO

18O 1O

17O

4 2 1

1O

15O

2OOO AC

13O

AP

12O

RF

1O

11O

1 2

1O

BARO 4OO

3OO M

15OO

4

29.92 IN

EM170AOM140390B.DGN

FS

The commands provide pitch guidance information to the flight crew to recommend or prohibit a maneuver and prevent hazardous encounters with other airplane. The vertical speed scale is used to display TCAS resolution advisories. The red range is the avoidance zone and the green range is the fly-to-zone. 1 - AVOIDANCE ZONE

AOM-1502-003

– Symbol: Trapezoid. – Color: Red.

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REVISION 10

Controls and Indications

Page 15

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

WARNING SYSTEM

2 - FLY-TO ZONE – Symbol: Rectangle.

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Page 16

Controls and Indications

REVISION 10

AOM-1502-003

– Color: Green.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION WARNING SYSTEM

MONITOR WARNING FUNCTION (MWF) Two monitor warning function computers in separate modular avionics units (MAUs) continually monitor the status of various airplane and avionics systems. One MWF has priority and alerts the flight crew by generating alert messages in the CAS display window. Some warnings also have sounds (voice and/or tone). The other MWF is a backup. If the priority MWF fails, the display computer automatically selects and uses the data from the backup MWF. Alert messages are prioritized and color-coded for display. The MWF also controls message timing, flight crew acknowledgement, and the scrolling of the CAS messages in the CAS display window. CAS SOURCE SELECTION The CAS List Message Comparison Annunciation is shown on both PFDs to indicate that the CAS lists from the two monitor warning systems do not match. The annunciation consists of the letters ″CAS MSG″ displayed inside a cutout box. If the two CAS message lists are continuously different for 20 s, a miscompare indication is annunciated. The CAS MSG source can be visualized or manually changed on the MCDU avionics SETUP page through LSK 2R from CAS 1 to CAS 2 or vice versa.

AOM-1502-003

CAS SOURCE SELECTION options are only enabled on the MCDU SETUP page 1/1 when a miscompare is detected between CAS 1 and CAS 2 lists, otherwise just the label CAS SOURCE SELECTION is displayed.

14-15-07 Copyright © by Embraer. Refer to cover page for details.

REVISION 18

Monitor Warning Function (MWF)

Page 1

SYSTEMS DESCRIPTION WARNING SYSTEM

AIRPLANE OPERATIONS MANUAL

SETUP PILOT XY

1 / 1

WIND

VECTOR

COPILOT XY

VECTOR

MT / YD / AP / FD B A AT / ETTS B A TRS CHANNEL B A PFD RADIO SETUP

MISC MENU

EM170AOM140523A.DGN

CAS SOURCE SELECTION CAS 1 CAS 2 AUTO

14-15-07 Copyright © by Embraer. Refer to cover page for details.

Page 2

Monitor Warning Function (MWF)

REVISION 18

AOM-1502-003

MCDU AVIONICS SETUP PAGE

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION WARNING SYSTEM

VISUAL WARNING Visual warnings are provided through illuminated warning buttons, displays indications and EICAS messages.

WARNING LIGHTS Master warning and caution lights are installed on the glareshield panel and blink when any warning or caution message shows on the EICAS or triggered by the Aural Warning Unit. It alerts to conditions that require action or caution related to the operation of the airplane.

MESSAGES ON EICAS EICAS MESSAGES MNEMONICS CAS messages mnemonic are generally presented in three elements, as shown in the example: General Header or System ENGINE

Specific Nature of the Subsystem or Problem location

CAS Message Mnemonic

Left side

Fire detected

ENG 1 FIRE

FUEL SOV

Left side

Valve is closed

FUEL SOV CLOSED

ADS

Third system

ADS standby failed

ADS 3 FAIL

AOM-1502-003

NOTE: – The above format may not be applicable for all CAS messages. Therefore, although the standard is desirable, it shall be subordinated to a clear statement of the nature of the problem. – Throughout the manual, number 1 is used to identify the left side, number 2 to identify the right side and number 3 for triple systems (usually for backup and standby systems).

14-15-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Visual Warning

Page 1

SYSTEMS DESCRIPTION WARNING SYSTEM

AIRPLANE OPERATIONS MANUAL

EICAS MESSAGES CATEGORIZATION There are four message priority levels: – Warning. – Caution. – Advisory. – Status. WARNING (red): indicates an emergency or airplane system condition that requires immediate corrective or compensatory crew action. CAUTION (amber): indicates an abnormal operational or airplane system conditions that require immediate crew awareness and should require a subsequent corrective or compensatory action. ADVISORY (cyan): indicates operational or airplane conditions that require crew awareness. Subsequent or future crew action may be required. STATUS (white): indicates information/status messages. The pilot can use the system efficiently when the appropriate action is accomplished. A fifth level is provided for maintenance and is not available during flight operation. It is accessed only on ground. Messages with the higher priority precede other messages when shown simultaneously. The EICAS displays up to 15 messages simultaneously. The MCDU displays some messages in the event of a failure of both MFD and the EICAS.

STATUS LINE The CAS window is selected by a CCD when a cyan curl with arrow icon (meaning knob adjustable data) is displayed, and the alert window border changes from gray to cyan. In case of an overflow (exceeding the display capacity – 15 messages), turning the active CCD scroll knobs scrolls the alert message stack list under the CAS window. The status line indicates the number (count) and type (color) of messages out of the CAS window, and if they are located above or below the window.

Warning messages are not scrolled out of the window.

14-15-10 Copyright © by Embraer. Refer to cover page for details.

Page 2

Visual Warning

REVISION 21

AOM-1502-003

The out-of-view message display (digits and arrows) flashes continuously when there are unacknowledged messages out of view.

AIRPLANE OPERATIONS MANUAL

SYSTEMS DESCRIPTION WARNING SYSTEM

O3

O3

O8

O6

EM170AOM140904A.DGN

EICAS

ROOT EICAS MESSAGES Some single failures may trigger more than one EICAS message at a time. In the event of multiple EICAS messages, identifying the true nature of the failure and taking the appropriate corrective action is an important role. EICAS messages which may generate more messages with them are called Root EICAS messages and they are highlighted by a preceding chevron “>”. In most cases the corrective action will be to perform only the procedure associated with the ROOT EICAS message, but some situations may require additional actions. The pilot must always review all messages displayed on the EICAS and check if they are associated to the root EICAS message and take additional actions if required. ROOT EICAS message procedures do not necessarily have to be performed first. If more than one root message is displayed at the same time or displayed together with a WARNING message, the priority order to be evaluated is: – WARNING messages; – ELECTRICAL BUSES and;

AOM-1502-003

– MAU.

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REVISION 21

Visual Warning

Page 3

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

WARNING SYSTEM

Below is the list of all the ROOT EICAS messages: CENTER EBAY FANS FAIL FWD EBAY FANS FAIL AVNX MAU 1A FAIL AVNX MAU 1B FAIL AVNX MAU 2A FAIL AVNX MAU 2B FAIL AVNX MAU 3A FAIL AVNX MAU 3B FAIL AC BUS 1 OFF AC BUS 2 OFF AC ESS BUS OFF

DC BUS 1 OFF DC BUS 2 OFF DC ESS BUS 1 OFF DC ESS BUS 2 OFF DC ESS BUS 3 OFF ELEC EMERGENCY LG WOW SYS FAIL HYD 1 LO PRESS HYD 2 LO PRESS HYD 3 LO PRESS

EICAS MESSAGES INHIBITION Some EICAS messages are inhibited on takeoff or approach and landing to prevent it from being a nuisance.

CODE K1 K2a K2b K3 K4

AFTER Electrical Power ON 1st Engine Started TLA > TO Power 80 kt 400 ft (takeoff)

K5

200 ft (landing)

BEFORE 1st Engine Started

DESCRIPTION A/C parked

TLA > TO Power 80 kt 400 ft (takeoff) 200 ft (landing)

A/C taxiing TO Roll Takeoff Climb, cruise, approach Landing

30 seconds after touchdown and wheelspeed below 30 kt.

14-15-10 Copyright © by Embraer. Refer to cover page for details.

Page 4

Visual Warning

REVISION 21

AOM-1502-003

Inhibition logic considers the following k-codes to inhibit the messages:

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

WARNING SYSTEM

EICAS MESSAGE INHIBITION SCHEMATIC

IN AIR A/C PARKD

A/C TAXING

TO ROLL

K1 POWER ON

K2a

ONE ENGINE STARTED

K2b

K3 80 kt

TLA >TO POWER

K4 400 ft

TAKEOFF

K5 200 ft

CLIMB / CRUISE APPROACH

LANDING

EM170AOM140300.DGN

ON GROUND

ON GROUND

EICAS MESSAGES PRESENTATION The messages are grouped and presented in a chronological order accordingly to its category. The Warning category is placed at the top of the EICAS display. Below this category the system presents the Caution, Advisory and Information/Status category, in this order. When new Warning, Caution and Advisory alert messages are displayed, they are presented flashing in inverse video for crew acknowledgment. The warning and caution alert messages shall remain flashing in inverse video until manual crew acknowledgment via Master Warning or Caution button (respectively) is pressed. Advisory messages will automatically revert from inverse to normal video after 5 seconds they started to be displayed. After the acknowledgment, the new message shall remain in steady normal video, at the top of its category on the EICAS display, until a new message belonging to that group appears. The EICAS messages cannot be cancelable. They shall remain active as long as its activation condition exists. The following table presents all EICAS messages. The type column indicates the message priority level: – (W) Warning. – (C) Caution.

AOM-1502-003

– (A) Advisory. – (S) Status.

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REVISION 21

Visual Warning

Page 5

SYSTEMS DESCRIPTION WARNING SYSTEM

AIRPLANE OPERATIONS MANUAL

14-15-10 Copyright © by Embraer. Refer to cover page for details.

Page 6

Visual Warning

REVISION 21

AOM-1502-003

The INHIBITION column indicates the k-codes.

AIRPLANE OPERATIONS MANUAL SECTION TYPE

W

SYSTEMS DESCRIPTION

MESSAGE

WARNING SYSTEM

INHIBITION

DOOR CRG AFT (FWD) OPEN

K3, K5

DOOR EMER LH (RH) OPEN

None

DOOR PAX AFT (FWD) OPEN DOOR SERV AFT (FWD) OPEN APM FAIL APM MISCOMP

K3, K5 K2b, K3, K4, K5

AVNX MAU 1 (2) (3) A (B) FAIL AVNX MAU 1 (2) (3) A (B) OVHT

K3, K5

AVNX MAU 1 (2) (3) FAN FAIL CMS FAIL

K2b, K3, K4, K5

DOOR CENTER (FWD) EBAY OPEN

K3, K5

DOOR HYD OPEN C

None

EICAS OVHT

K3, K5

EMER LT NOT ARMED

14-01 AIRPLANE GENERAL

EMER LT ON

A

AOM-1502-003

EICAS FAULT

K2b, K3, K5

MFD 1 (2) FAULT

None

MFD 1 (2) OVHT

K3, K5

PFD 1 (2) FAULT

None

PFD 1 (2) OVHT

K3, K5

SYS CONFIG FAIL

K2a, K2b, K3, K4, K5

APM FAULT

K2b, K3, K4, K5

AVNX DB MODULE FAIL

K2a, K2b, K3, K4, K5

AVNX MAU 1 (2) (3) A (B) FAULT

K2b, K3, K4, K5

AVNX MAU 1 (2) (3) FAN FAULT

K2b, K3, K4, K5

CCD 1 (2) FAULT

K2b, K3, K5

CMS FAULT

K2b, K3, K4, K5

CRG AFT ACCESS OPEN

None

DOOR FUELING OPEN

K2b, K3, K4, K5

DOORS NOT STOWED

K1, K2b, K3, K5

EMER LT BATT FAULT

K2b, K3, K4, K5

14-15-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Visual Warning

Page 7

SYSTEMS DESCRIPTION WARNING SYSTEM

SECTION TYPE W

AIRPLANE OPERATIONS MANUAL MESSAGE

CABIN ALTITUDE HI

INHIBITION K1, K2a, K2b, K3, K5

AMS CTRL FAIL BLEED 1 (2) FAIL BLEED 1 (2) LEAK BLEED 1 (2) OVERPRESS BLEED APU LEAK CABIN DIFF PRESS FAIL CENTER EBAY FANS FAIL CRG FWD VENT FAIL C

K2b, K3, K5

FWD EBAY FANS FAIL PACK 1 (2) FAIL PACK 1 (2) LEAK PAX OXY LO PRESS (only for 190 ECJ model)

14-02 AMS

PRESN AUTO FAIL PRESN MAN FAIL RECIRC SMK DET FAIL

K2a, K2b, K3, K5

RECIRC SMOKE

K2b, K3, K5

AMS CTRL FAULT

K2a, K2b, K3, K4, K5

BLEED 1 (2) OFF CRG AFT VENT FAIL (only for 190 ECJ model) A

K2b, K3, K5

PACK 1 (2) OFF PRESN AUTO FAULT XBLEED FAIL XBLEED SW OFF

S

BLEED APU VLV OPEN

K2b, K3, K4, K5 K2b, K3, K5 K2b, K3, K5

14-15-10 Copyright © by Embraer. Refer to cover page for details.

Page 8

Visual Warning

REVISION 21

AOM-1502-003

RAM AIR FAULT

AIRPLANE OPERATIONS MANUAL SECTION TYPE

C

SYSTEMS DESCRIPTION

MESSAGE

K2b, K3, K5

AP PITCH MISTRIM

K3

AP PITCH TRIM FAIL

K2b, K3, K5

AP ROLL MISTRIM

K3

AT FAIL

K3, K5

AT NOT IN HOLD

None

FD VERT MODE OFF SHAKER ANTICIPATED

AOM-1502-003

K3 K2b, K3, K5

STALL PROT FAIL

K2b, K3

AFCS FAULT

K2b, K3, K4, K5

AFCS PANEL FAIL

K3, K5

AFCS PANEL FAULT

K2a, K2b, K3, K4, K5

AP FAULT AP PITCH TRIM FAULT AP RUDDER NOT AVAIL APPR 2 NOT AVAIL AT FAULT

A

INHIBITION

AP FAIL

FD LATERAL MODE OFF

14-03 AUTOMATIC FLIGHT

WARNING SYSTEM

K2b, K3, K4, K5 K2b, K3 K2b, K3, K4, K5

AUTOLAND 1 (2) NOT AVAIL

K2b, K3

ENG TLA TRIM FAIL

K2b, K3, K5

FD FAIL

K3, K5

FD FAULT

K2b, K3, K4, K5

HUD LVTO NOT AVAIL

K2b, K3, K4, K5

MACH TRIM FAIL

K2b, K3, K5

MACH TRIM FAULT

K2b, K3, K4, K5

SHAKER 1 (2) FAIL

K2b, K3, K5

STALL PROT FAULT

K2b, K3, K4, K5

STALL PROT ICE SPEED

K2b, K3, K5 and inhibited 5 minutes after weight-on-wheels off.

YD FAIL

K2b, K3, K5

YD FAULT

K2b, K3, K4, K5

YD OFF

None

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REVISION 21

Visual Warning

Page 9

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

WARNING SYSTEM

SECTION TYPE 14-03 AUTOMATIC FLIGHT

14-04 AUXILIARY POWER UNIT

S

C

MESSAGE

INHIBITION

AUTOLAND OFF

K2b, K3

APU ALTITUDE EXCEED

K1, K2A, K2B, K3, K5

APU FAIL APU FAULT APU OIL HI TEMP

K2b, K3, K5

APU OIL LO PRESS S

APU SHUTTING DOWN

K2b, K3, K5

BATT 1 (2) OVERTEMP W

BATT 1-2 OFF BATT DISCHARGING

None

ELEC EMERGENCY AC BUS 1 (2) OFF AC ESS BUS OFF AC STBY BUS OFF

K3, K5

APU GEN OFF BUS

14-05 ELECTRICAL

C

BATT 1 (2) OFF

K3, K5

BATT 1 (2) TEMP SENS FAULT

K2a, K2b, K3, K4, K5

DC BUS 1 (2) OFF DC ESS BUS 1 (2) (3) OFF GPU CONNECTED IDG 1 (2) OFF BUS IDG 1 (2) OIL INVERTER FAIL RAT FAIL TRU 1 (2) FAIL TRU ESS FAIL

A

None

K3, K5 K3, K4, K5 K3, K5 K2a, K2b, K3, K4, K5 K3, K5

LOAD SHED

K3, K4, K5

REMOTE CB TRIP

K2b, K3, K4, K5

SPDA FAIL

K3, K5

14-15-10 Copyright © by Embraer. Refer to cover page for details.

Page 10

Visual Warning

REVISION 21

AOM-1502-003

BATT 1 (2) DISCHARGING

AIRPLANE OPERATIONS MANUAL SECTION TYPE W

SYSTEMS DESCRIPTION WARNING SYSTEM

MESSAGE

INHIBITION

ENG 1 (2) OIL LO PRESS

K3, K5

ENG 1 (2) REV DEPLOYED

None

ENG 1 (2) CONTROL FAULT ENG 1 (2) FADEC OVERTEMP ENG 1 (2) FAIL ENG 1 (2) FUEL IMP BYPASS ENG 1 (2) FUEL LO PRESS

K3, K5 K3 K3, K5

ENG 1 (2) NO DISPATCH

K2b, K3, K4, K5

ENG 1 (2) OIL LO LEVEL (Post-Mod Load 25.1.0.1)

K2b, K3, K4, K5

ENG 1 (2) OIL LO LEVEL (Pre-Mod Load 25.1.0.1) ENG 1 (2) REV FAIL

K3, K4, K5

ENG 1 (2) REV PROT FAULT

C 14-06 ENGINE

ENG 1 (2) REV TLA FAIL (Post-Mod Load 25.1.0.1)

K2b, K3, K5

ENG 1 (2) REV TLA FAIL (Pre-Mod Load 25.1.0.1) ENG 1 (2) START VLV OPEN

K3, K5

ENG 1 (2) T2 HEAT FAIL ENG 1 (2) TLA FAIL ENG EXCEEDANCE

K2b, K3, K4, K5

ENG NO TAKEOFF DATA

K3, K4, K5

ENG REF A-I DISAG

K1, K3, K4, K5

ENG REF ECS DISAG (Pre-Mod Load 23.1)

K3, K4, K5

ENG REF ECS DISAG (Post-Mod Load 23.1)

K2b, K3, K4, K5

ENG THR RATING DISAG

K3, K4, K5

ENG TLA NOT TOGA

None

ENG 1 (2) FADEC FAULT

K3, K4, K5

ENG 1 (2) FUEL SW FAIL

AOM-1502-003

A

ENG 1 (2) OIL IMP BYPASS

K3, K5

ENG 1 (2) OIL SW FAIL

K3, K4, K5

ENG 1 (2) SHORT DISPATCH

K2b, K3, K4, K5

14-15-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Visual Warning

Page 11

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

WARNING SYSTEM

SECTION TYPE 14-06 ENGINE

S

MESSAGE

INHIBITION

ENG 1 (2) REV INHIBIT

K3, K5

ENG 1 (2) TLA NOT IDLE

None

ENG TDS REF A-I ALL ENG TDS REF A-I ENG

K3, K4, K5

APU FIRE CRG AFT (FWD) SMOKE W

ENG 1 (2) FIRE CABIN SMOKE (only for 190 ECJ model)

K3, K5

LAV SMOKE

K2b, K3, K5

APU FIRE DET FAIL APU FIREX FAIL C 14-07 FIRE PROTECTION

None

K3, K5

CRG AFT (FWD) FIRE SYS FAIL

K2b, K3, K5

ENG 1 (2) FIRE DET FAIL

K3, K5

IFE RACK SMOKE

K2b, K3, K5

LAV SMOKE DET FAIL

K2a, K2b, K3, K4, K5

APU FIREX BTL DISCH

A

CRG FIRE PROT FAULT CRG FWD (AFT) FIREX HI ARM CRG FWD (AFT) FIREX LO ARM ENG 1 (2) FIREXBTL A (B) FAIL ENG FIREXBTL A (B) DISCH

S

CRG FIREX HI (LO) DISCH

K3, K5 K2a, K2b, K3, K4, K5 K2b, K3, K5 K3, K5 K2b, K3, K5

14-15-10 Copyright © by Embraer. Refer to cover page for details.

Page 12

Visual Warning

REVISION 21

AOM-1502-003

CABIN SMOKE DET FAIL (only for 190 ECJ model)

AIRPLANE OPERATIONS MANUAL SECTION TYPE W

SYSTEMS DESCRIPTION

MESSAGE

INHIBITION

GROUND SPOILERS FAIL

None

ELEV (RUDDER) (SPOILER) NML MODE FAIL

K1, K2a, K2b, K3, K5

AOA LIMIT FAIL

K2b, K3, K5

ELEV THR COMP FAIL

K3, K5

ELEVATOR FAULT ELEVATOR LH (RH) FAIL

C

WARNING SYSTEM

K3

FLAP FAIL

K3, K5

FLT CTRL NO DISPATCH

K2b, K3, K4, K5

FLT CTRL BIT EXPIRED

K2a, K2b, K3, K4, K5

PITCH TRIM FAIL

K3, K5

RUDDER FAIL RUDDER FAULT

K3

RUDDER LIMITER FAIL SLAT FAIL 14-08 FLIGHT CONTROLS

K3, K5

SLAT-FLAP LVR DISAG

SPOILER FAULT

(Pre-Mod. Load 21.2) K2b, K3 (Post-Mod. Load 21.2) K1, K2a, K2b, K3

STAB LOCK FAULT

K3, K5

STEEP APPR FAIL

K1, K2a, K2b, K3

AILERON LH (RH) FAIL AUTO CONFIG TRIM FAIL

K3, K5

FLAP LO RATE FLT CTRL FAULT

K3, K4, K5

PITCH CONTROL DISC A

PITCH TRIM BKUP FL (Pre-Mod. Load 25.1.0.1) PITCH TRIM BKUP FAIL (Post-Mod. Load 25.1.0.1)

K3, K5

PITCH TRIM LO RATE

AOM-1502-003

PITCH TRIM SW 1 (2) FAIL ROLL CONTROL DISC

14-15-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Visual Warning

Page 13

WARNING SYSTEM

SECTION TYPE

AIRPLANE OPERATIONS MANUAL MESSAGE

SLAT LO RATE SPDBRK LEVER DISAG

A 14-08 FLIGHT CONTROLS

S

INHIBITION K3, K5

SPDBRK FAIL (Post-Mod. Load 27.1)

K2b, K3, K5

TAILSTRIKE PROT FAIL (Pre-Mod. Load 23.1)

K1

TAILSTRIKE AVOID FAIL (Post-Mod. Load 23.1)

K1

STEEP APPR NOT AVAIL

K2b, K3, K5

FLT CTRL TEST IN PROG

(Pre-Mod. Load 21.2) K2a, K2b, K3, K4, K5 (Post-Mod. Load 21.2) K2b, K3, K4, K5

14-15-10 Copyright © by Embraer. Refer to cover page for details.

Page 14

Visual Warning

REVISION 21

AOM-1502-003

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL SECTION TYPE

14-09 FLIGHT INSTRUMENTS, COMM, NAV & FMS

SYSTEMS DESCRIPTION

MESSAGE

INHIBITION

ADS 1 (2) FAIL

K3, K5

ADS 3 FAIL

K2b, K3, K5

ADS 1 (2) HTR FAIL

K5

ADS 3 (4) HTR FAIL

K2b, K3, K5

AVNX ASCB FAULT

K2b, K3, K4, K5

DISPLAY CTRL FAIL

K3, K5.

DISPLAY CTRL FAULT

K2b, K3, K4, K5

FMS 1 (2) GPS POS DISAG

K1, K2a, K2b, K3, K5

FMS POS DISAG

K1, K2a, K2b, K3, K5

HF 1 (2) FAIL IRS 1 (2) FAIL C

WARNING SYSTEM

None

IRS EXCESSIVE MOTION

K2b, K3, K4, K5

MCDU 1 (2) (3) OVHT (Pre-Mod Load 17.5)

K2b, K3, K5

NAV 3 FAIL NAVCOM 1 (2) FAIL

K3, K5

NAVCOM 1 (2) OVHT NO ETOPS SEL (only for airplanes ETOPS configured)

K3, K4, K5

VALIDATE CONFIG

K2b, K3, K4, K5

VHF 1 (2) (3) OVHT VHF 3 FAIL

AOM-1502-003

XPDR 1 (2) IN STBY (Post-Mod. Load 23.1)

K3, K5 K1, K2a, K2b, K3, K5

14-15-10 Copyright © by Embraer. Refer to cover page for details.

REVISION 21

Visual Warning

Page 15

SYSTEMS DESCRIPTION

AIRPLANE OPERATIONS MANUAL

WARNING SYSTEM

SECTION TYPE

MESSAGE ADS 1 (2) HTR FAULT

INHIBITION K3, K4, K5

ADS-B FAIL (Pre-Mod Load 25.4 - Pentium M or K2b, K3, K5 Pre-Mod Load 25.3 - Pentium II)

14-09 FLIGHT INSTRUMENTS, COMM, NAV & FMS

ADS-B NOT AVAIL (Post-Mod Load 25.4 - Pentium M or Post-Mod Load 25.3 - Pentium II)

K2b, K3, K5

ADS 3 SLIPCOMP FAIL

K2b, K3, K5

ADS PROBE 1 (2) (3) (4) FAIL

K2b, K3, K4, K5

ATC DATALINK 1 (2) FAIL (only for airplanes equipped with ATN-CPDLC Pre-Mod Load 27.1)

K3, K5

CMC FAIL

K2a, K2b, K3, K4, K5

CMF 1 FAIL (Pre-Mod Load 25.1.0.1) A

DATALINK 1 FAIL (Post-Mod Load 25.1.0.1) DATALINK 2 FAIL (only for airplanes equipped with ATN-CPDLC Pre-Mod Load 27.1)

K3, K5

EVS FAIL (only for 190 ECJ equipped with EFVS)

K2b, K3, K5

FDR AFT (FWD) FAIL

K3, K5

FLT CTRL ADS FAIL

K2b, K3, K4, K5

FMS 1 (2) FAIL

K3, K5

GPS 1 (2) FAIL (Post-Mod Load 27.1)

K3, K5

HUD 1 (2) FAIL

K2b, K3, K5

IRS 1 (2) (3) NAV MODE FAIL

K1, K2a, K2b, K3, K5

IRS ALIGNING

K2b, K3, K4, K5

IRS PRES POS INVALID

K2a, K2b, K3, K4, K5

14-15-10 Copyright © by Embraer. Refer to cover page for details.

Page 16

Visual Warning

REVISION 21

AOM-1502-003

CVR AFT (FWD) FAIL

AIRPLANE OPERATIONS MANUAL SECTION TYPE

SYSTEMS DESCRIPTION

MESSAGE

A

K3, K5

RALT 1 (2) FAIL

None

RNP AR