A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL The content of this document is the property of Airbus. It is supplied
Views 274 Downloads 35 File size 166MB
A318/A319/A320/A321
FLIGHT CREW OPERATING MANUAL The content of this document is the property of Airbus. It is supplied in confidence and commercial security on its contents must be maintained. It must not be used for any purpose other than that for which it is supplied, nor may information contained in it be disclosed to unauthorized persons. It must not be reproduced in whole or in part without permission in writing from the owners of the copyright. © AIRBUS 2005. All rights reserved.
AIRBUS S.A.S CUSTOMER SERVICES DIRECTORATE 31707 BLAGNAC CEDEX FRANCE REFERENCE: 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
ISSUE DATE: 18 SEP 12
Intentionally left blank
TRANSMITTAL LETTER A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Issue date: 18 SEP 12
This is the FLIGHT CREW OPERATING MANUAL at issue date 18 SEP 12 for the A318/A319/A320/A321 and replacing last issue dated 30 MAY 12
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
TRL P 1/2 18 SEP 12
TRANSMITTAL LETTER A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
TRL P 2/2 18 SEP 12
FILING INSTRUCTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Please incorporate the revision as follow: Localization Subsection Title GEN General Information DSC-21-20-50 Warnings and Cautions DSC-22_10-50 Warnings and Cautions DSC-22_20 - Polar Navigation DSC-22_20-20-40 Alignment of Inertial Reference System DSC-22_20-50-10-25 FMS2 Honeywell DSC-22_20-60 - Polar Navigation DSC-23-10-50 Electrical Supply DSC-24-10-20 Generation Of Electrical Power DSC-24-30 Warnings and Cautions DSC-26-20-20 Controls and Indicators DSC-27-10-20 Architecture DSC-27-20-10-20 Pitch Control DSC-27-20-10-30 Lateral Control DSC-27-20-10-50 Sideslip Target DSC-28-10-60 Fuel Recirculation System DSC-28-30 Warnings and Cautions DSC-31-40 Indications on PFD DSC-31-45 Indications on ND DSC-33-30-10 Description DSC-35-30-10 Description
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Remove
Insert Rev. Date
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL ALL
18 SEP 12
ALL
18 SEP 12
ALL ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
FI P 1/4 18 SEP 12
FILING INSTRUCTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Localization Subsection Title DSC-35-30-20 Controls and Indicators DSC-70-40-50 IDG Cooling System PRO-ABN-24 Electrical PRO-ABN-26 Fire Protection PRO-ABN-27 Flight Controls PRO-ABN-28 Fuel PRO-ABN-34 Navigation PRO-ABN-70 Power Plant PRO-ABN-80 Miscellaneous PRO-NOR-SOP-04 Preliminary Cockpit Preparation PRO-NOR-SOP-05 Exterior Inspection PRO-NOR-SOP-06 Cockpit Preparation PRO-NOR-SOP-18 Precision Approach PRO-NOR-SRP-01-70 Approach PRO-SPO-30 High Altitude Operations PRO-SPO-60 Operations on Narrow Runways PRO-SUP-24 Electrical PRO-SUP-80 Miscellaneous PRO-SUP-91-20 Operations in Windshear or Downburst PRO-SUP-91-40 Operations On Airports Covered With Ash, Sand or Dust PRO-SUP-92-10 Less Paper in the Cockpit
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Remove
Insert Rev. Date
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12 18 SEP 12
FI P 2/4 18 SEP 12
FILING INSTRUCTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Localization Subsection Title LIM-11 Weight and Center of Gravity Limits LIM-12 Environmental Envelope and Airport Operations LIM-22-20 Automatic Approach, Landing and Roll Out LIM-34 Navigation PER-LOD-WBA-FIT-10 FUEL INDEX TABLE PER-TOF-TOC-10-20 TAKEOFF CHART DESCRIPTION PER-FPL-FLP-ALT-10 OPTIMUM AND MAXIMUM ALTITUDES PER-FPL-FLP-ALT-20 OPTIMUM ALTITUDE ON SHORT STAGE PER-LDG-DIS-MAT Runway Condition Assessment Matrix for Landing
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Remove
Insert Rev. Date
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
ALL
18 SEP 12
FI P 3/4 18 SEP 12
FILING INSTRUCTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FI P 4/4 18 SEP 12
PRELIMINARY PAGES
Intentionally left blank
PRELIMINARY PAGES LIST OF EFFECTIVE OPERATIONS ENGINEERING BULLETIN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
Identification
(2)
T
(3)
E
Rev. Date
Title
OEB38 issue 1.0 Criteria: SA Applicable to: ALL OEB40 issue 1.0
R
N
18 MAR 11
Erroneous Radio Altimeter Height Indication
W
Y
18 MAR 11
AIR ENG 1(2) BLEED ABNORMAL PR or AIR ENG 1(2) BLEED FAULT
Criteria: SA Applicable to: ALL OEB41 issue 1.0
W
N
18 MAR 11
Erroneous Alternate Fuel Predictions Upon Modification of a Company Route in the Alternate Flight Plan
Y
21 MAY 12
F/CTL SPOILER FAULT
Y
21 MAY 12
L/G GEAR NOT DOWNLOCKED
Criteria: P10762, P10763 Applicable to: ALL OEB43 issue 3.0 W Criteria: SA Applicable to: ALL OEB44 issue 2.0 W Criteria: SA Applicable to: ALL
(1) Evolution code : N=New, R=Revised, E=Effectivity (2) Type of OEB: R=Red, W=White (3) Affects ECAM: Y=Yes, N=No
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LEOEB P 1/2 18 SEP 12
PRELIMINARY PAGES LIST OF EFFECTIVE OPERATIONS ENGINEERING BULLETIN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LEOEB P 2/2 18 SEP 12
PRELIMINARY PAGES LIST OF EFFECTIVE SECTIONS/SUBSECTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
R
R
R
Localization GEN DSC-20-10 DSC-20-20 DSC-21-10-10 DSC-21-10-20 DSC-21-10-30 DSC-21-10-40 DSC-21-10-50 DSC-21-10-60 DSC-21-10-70 DSC-21-20-10 DSC-21-20-20 DSC-21-20-30 DSC-21-20-40 DSC-21-20-50 DSC-21-20-60 DSC-21-30-10 DSC-21-30-20 DSC-21-30-40 DSC-21-30-50 DSC-21-30-60 DSC-21-30-70 DSC-21-30-80 DSC-21-40-10 DSC-21-40-20 DSC-21-40-30 DSC-21-40-35 DSC-21-40-40 DSC-21-40-50 DSC-22_10-10 DSC-22_10-20 DSC-22_10-30 DSC-22_10-40-05 DSC-22_10-40-10 DSC-22_10-40-20 DSC-22_10-40-30 DSC-22_10-40-40 DSC-22_10-40-50 DSC-22_10-50 DSC-22_10-60 DSC-22_20-10
Subsection Title General Information Introduction General Arrangement General Main Components Temperature and Flow Regulation System Operation under Failure Condition Controls and Indicators Warnings and Cautions Electrical Supply General Main Components System Operation Controls and Indicators Warnings and Cautions Electrical Supply General Avionics Ventilation Battery Ventilation Lavatory and Galley Ventilation Controls and Indicators Warnings and Cautions Electrical Supply General System Operation Controls and Indicators ECAM Cond Page Warnings and Cautions Electrical Supply Description System Interface Diagram FMGS Modes of Operation Management of the Displays MCDU FCU Thrust Levers Primary Flight Display Navigation Display Warnings and Cautions ELECTRICAL SUPPLY General
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Rev. Date 18 SEP 12 29 JUL 11 30 MAY 12 30 MAY 12 30 MAY 12 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 25 NOV 11 25 NOV 11 25 NOV 11 18 SEP 12 29 JUL 11 29 JUL 11 30 MAY 12 29 JUL 11 30 MAY 12 30 MAY 12 29 JUL 11 29 JUL 11 30 MAY 12 29 JUL 11 29 JUL 11 30 MAY 12 29 JUL 11 29 JUL 11 30 MAY 12 29 JUL 11 03 APR 12 29 JUL 11 30 MAY 12 30 MAY 12 30 MAY 12 30 MAY 12 30 MAY 12 18 SEP 12 29 JUL 11 29 JUL 11
PLP-LESS P 1/16 18 SEP 12
PRELIMINARY PAGES LIST OF EFFECTIVE SECTIONS/SUBSECTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
R
R
Localization DSC-22_20-20-05 DSC-22_20-20-10 DSC-22_20-20-20 DSC-22_20-20-30 DSC-22_20-20-40 DSC-22_20-20-50 DSC-22_20-30-05 DSC-22_20-30-10-05 DSC-22_20-30-10-15 DSC-22_20-30-20-05 DSC-22_20-30-20-25 DSC-22_20-40-10 DSC-22_20-40-20 DSC-22_20-40-30 DSC-22_20-50-10-25 DSC-22_20-50-20-35 DSC-22_20-50-30 DSC-22_20-60-10 DSC-22_20-60-20 DSC-22_20-60-30 DSC-22_20-60-40 DSC-22_20-60-50 DSC-22_20-60-60 DSC-22_20-60-70 DSC-22_20-60-80 DSC-22_20-60-90 DSC-22_20-60-100 DSC-22_20-60-110 DSC-22_20-60-120 DSC-22_20-60-130 DSC-22_20-70 DSC-22_20-80 DSC-22_30-10 DSC-22_30-20 DSC-22_30-30 DSC-22_30-40 DSC-22_30-50 DSC-22_30-60 DSC-22_30-70-10 DSC-22_30-70-20 DSC-22_30-70-30
Subsection Title General Position Computation Evaluation of Position Accuracy Radio Navigation Tuning Alignment of Inertial Reference System Navigation Database General General FMS2 HONEYWELL General FMS2 Honeywell Optimization Cost Index Predictions FMS2 Honeywell FMS2 Honeywell MCDU - Data Format List Effect of Baro Reference Setting Clear Key (Clearing Function) How to Execute a Diversion Engine Out Secondary Flight Plan Pilots/Stored Route Function Report Page Closest Airports Time Marker Step ALTS Required Time of Arrival (RTA) Equitime Point MCDU Back Up Navigation AOC Functions Print Functions General Flight Director Autopilot (AP) Speed/Mach Control AP/FD Modes General AP/FD Lateral Modes Principles Climb Mode Open Climb Mode
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Rev. Date 29 JUL 11 30 MAY 12 30 MAY 12 03 APR 12 18 SEP 12 29 JUL 11 29 JUL 11 03 APR 12 30 MAY 12 03 APR 12 30 MAY 12 03 APR 12 29 JUL 11 30 MAY 12 18 SEP 12 30 MAY 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 30 MAY 12 30 MAY 12 03 APR 12 30 MAY 12 03 APR 12 30 MAY 12 03 APR 12 03 APR 12 03 APR 12 30 MAY 12 30 MAY 12 03 APR 12 03 APR 12 30 MAY 12 03 APR 12 29 JUL 11 03 APR 12 29 JUL 11 29 JUL 11 03 APR 12 29 JUL 11
PLP-LESS P 2/16 18 SEP 12
PRELIMINARY PAGES LIST OF EFFECTIVE SECTIONS/SUBSECTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
R
Localization DSC-22_30-70-50 DSC-22_30-70-60 DSC-22_30-70-65 DSC-22_30-70-70 DSC-22_30-70-80 DSC-22_30-75 DSC-22_30-80-10 DSC-22_30-80-20 DSC-22_30-80-30-05 DSC-22_30-80-30-10 DSC-22_30-80-30-20 DSC-22_30-80-40 DSC-22_30-90 DSC-22_30-100 DSC-22_40-10 DSC-22_40-20 DSC-22_40-30 DSC-22_40-40 DSC-22_40-50 DSC-22_45 DSC-22_46 DSC-23-10-10 DSC-23-10-20 DSC-23-10-30 DSC-23-10-50 DSC-23-20-10 DSC-23-20-20 DSC-23-20-30 DSC-23-20-40 DSC-23-20-50 DSC-23-20-60 DSC-23-20-70 DSC-23-30-10 DSC-23-30-20 DSC-23-30-30 DSC-23-40-40 DSC-23-40-50 DSC-23-46-10 DSC-23-46-20 DSC-23-46-30 DSC-23-50
Subsection Title Descent Mode Open Descent Mode Altitude Acquire Mode Altitude Hold Mode Vertical Speed Mode - Flight Path Angle Mode (V/S - FPA) Mode Reversions General Takeoff General Precision Approach Non Precision Approach Go Around (GA) Autothrust Flight Mode Annunciator (FMA) General Yaw Functions Flight Envelope Function Windshear Detection Function Controls and Indicators Auto Flight - AOC Functions Auto Flight - Print Interface General VHF/HF/SELCAL Radio Tuning Electrical Supply General Controls Interphone Systems Call Systems Passenger Address EMER EVAC Electrical Supply DESCRIPTION CONTROLS AND INDICATORS ON OVERHEAD PANEL ELECTRICAL SUPPLY ACARS Functions Electrical Supply General Controls and Indicators ELECTRICAL SUPPLY Warnings and Cautions
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Rev. Date 30 MAY 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 29 JUL 11 29 JUL 11 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 30 MAY 12 03 APR 12 29 JUL 11 29 JUL 11 03 APR 12 29 JUL 11 29 JUL 11 03 APR 12 03 APR 12 29 JUL 11 29 JUL 11 29 JUL 11 18 SEP 12 30 MAY 12 30 MAY 12 29 JUL 11 30 MAY 12 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 03 APR 12 29 JUL 11 03 APR 12 03 APR 12 29 JUL 11 29 JUL 11
PLP-LESS P 3/16 18 SEP 12
PRELIMINARY PAGES LIST OF EFFECTIVE SECTIONS/SUBSECTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
R
R
R
R R R
Localization DSC-24-10-10 DSC-24-10-20 DSC-24-10-30-10 DSC-24-10-30-20 DSC-24-10-30-30 DSC-24-10-30-40 DSC-24-20 DSC-24-30 DSC-25-10-10 DSC-25-10-20 DSC-25-10-30 DSC-25-10-40 DSC-25-10-50 DSC-25-10-60 DSC-25-10-70 DSC-25-10-80 DSC-25-10-100 DSC-25-11-10 DSC-25-11-20 DSC-25-11-40 DSC-25-15-30 DSC-25-40-10-10 DSC-26-10 DSC-26-20-10 DSC-26-20-20 DSC-26-20-30 DSC-26-30-10 DSC-26-30-20 DSC-26-30-30 DSC-26-40-10 DSC-26-40-20 DSC-26-50-10 DSC-26-50-20 DSC-26-50-30 DSC-26-50-40 DSC-26-60 DSC-27-10-10 DSC-27-10-20 DSC-27-20-10-10 DSC-27-20-10-20 DSC-27-20-10-30
Subsection Title General Generation Of Electrical Power General NORMAL CONFIGURATION Abnormal Configurations Distribution Table Controls and Indicators Warnings and Cautions General Cockpit Plan Seats Cockpit Window Pilot's Instrument Panels Pedestal Overhead Panel C/B Panels Electrical Supply Description Cockpit Door Locking System (CDLS) Electrical Supply Electrical Supply Description GENERAL Description Controls and Indicators Warnings and Cautions Description Controls and Indicators Warnings and Cautions Description Warnings and Cautions Smoke Detection Fire Extinguishing Controls and Indicators Warnings and Cautions Electrical Supply GENERAL Architecture General Pitch Control Lateral Control
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Rev. Date 30 MAY 12 18 SEP 12 29 JUL 11 18 SEP 12 18 SEP 12 29 JUL 11 30 MAY 12 18 SEP 12 29 JUL 11 30 MAY 12 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 30 MAY 12 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 25 NOV 11 29 JUL 11 03 APR 12 18 SEP 12 29 JUL 11 30 MAY 12 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 30 MAY 12 30 MAY 12 30 MAY 12 30 MAY 12 29 JUL 11 29 JUL 11 18 SEP 12 30 MAY 12 18 SEP 12 18 SEP 12
PLP-LESS P 4/16 18 SEP 12
PRELIMINARY PAGES LIST OF EFFECTIVE SECTIONS/SUBSECTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
R
R
R
Localization DSC-27-20-10-50 DSC-27-20-20 DSC-27-20-30 DSC-27-20-40 DSC-27-20-50 DSC-27-30-10 DSC-27-30-20 DSC-27-30-30 DSC-27-30-40 DSC-28-10-10 DSC-28-10-20 DSC-28-10-30 DSC-28-10-50 DSC-28-10-60 DSC-28-10-70 DSC-28-10-80 DSC-28-10-90 DSC-28-20 DSC-28-30 DSC-28-40 DSC-29-10-10 DSC-29-10-20 DSC-29-10-30 DSC-29-20 DSC-29-30 DSC-29-40 DSC-30-10-10 DSC-30-20-10 DSC-30-20-20 DSC-30-20-30 DSC-30-20-40 DSC-30-30-10 DSC-30-30-20 DSC-30-30-30 DSC-30-30-40 DSC-30-40-10 DSC-30-40-20 DSC-30-40-30 DSC-30-40-40 DSC-30-50-10 DSC-30-50-20
Subsection Title Sideslip Target Reconfiguration Control Laws Controls and Indicators Warnings and Cautions Electrical Supply Description Controls and Indicators Warnings and Cautions Electrical Supply General Tanks Engine Feed APU Feed Fuel Recirculation System Refueling and Defueling Fuel Quantity Indication and Level Sensing Fuel Tank Inerting System Controls and Indicators Warnings and Cautions ELECTRICAL SUPPLY General Generation Distribution CONTROLS AND INDICATORS Warnings and Cautions ELECTRICAL SUPPLY Description Description Controls And Indicators Warnings And Cautions Electrical Supply Description Controls and Indicators Warnings and Cautions Electrical Supply Description CONTROLS AND INDICATORS WARNINGS AND CAUTIONS ELECTRICAL SUPPLY Description Controls and Indicators
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Rev. Date 18 SEP 12 30 MAY 12 30 MAY 12 03 APR 12 29 JUL 11 29 JUL 11 03 APR 12 29 JUL 11 29 JUL 11 29 JUL 11 30 MAY 12 30 MAY 12 29 JUL 11 18 SEP 12 30 MAY 12 30 MAY 12 25 NOV 11 30 MAY 12 18 SEP 12 29 JUL 11 29 JUL 11 25 NOV 11 29 JUL 11 30 MAY 12 29 JUL 11 29 JUL 11 03 APR 12 30 MAY 12 29 JUL 11 29 JUL 11 29 JUL 11 03 APR 12 03 APR 12 29 JUL 11 29 JUL 11 30 MAY 12 29 JUL 11 29 JUL 11 29 JUL 11 30 MAY 12 29 JUL 11
PLP-LESS P 5/16 18 SEP 12
PRELIMINARY PAGES LIST OF EFFECTIVE SECTIONS/SUBSECTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
R R
Localization DSC-30-50-30 DSC-30-50-40 DSC-30-60-10 DSC-30-60-20 DSC-30-60-30 DSC-30-70-10 DSC-30-70-30 DSC-31-05-10 DSC-31-05-20 DSC-31-05-30 DSC-31-05-40 DSC-31-05-50 DSC-31-05-60 DSC-31-10 DSC-31-15 DSC-31-20 DSC-31-25-10 DSC-31-25-20 DSC-31-27 DSC-31-30 DSC-31-40 DSC-31-45 DSC-31-50 DSC-31-55-10 DSC-31-55-20 DSC-31-60-10 DSC-31-60-20 DSC-31-60-30 DSC-31-70 DSC-31-75 DSC-32-10-10 DSC-32-10-20 DSC-32-10-30 DSC-32-10-40 DSC-32-10-50 DSC-32-10-60 DSC-32-20-10 DSC-32-20-20 DSC-32-20-30 DSC-32-20-40 DSC-32-30-10
Subsection Title Warnings and Cautions Electrical Supply DESCRIPTION CONTROLS AND INDICATORS ELECTRICAL SUPPLY DESCRIPTION ELECTRICAL SUPPLY Introduction Cockpit Arrangement Architecture Controls and Switching Reconfiguring the DMC Reconfiguring DUs Ecam Description Indications on E/WD Indications on SD General Example OEB Reminder ECAM Controls Indications on PFD Indications on ND EFIS Controls GENERAL CONTROLS AND INDICATORS Flight Data Recording System Controls and Indicators Aircraft Integrated Data System Warnings and Cautions Electrical Supply Description Landing Gear System/Interface Interactions between Landing Gear and Aircraft Systems Controls and Indicators Warnings and Cautions Electrical Supply Description Controls and Indicators Warnings and Cautions Electrical Supply Description
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Rev. Date 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 30 MAY 12 03 APR 12 30 MAY 12 29 JUL 11 03 APR 12 30 MAY 12 29 JUL 11 18 SEP 12 18 SEP 12 03 APR 12 29 JUL 11 29 JUL 11 29 JUL 11 30 MAY 12 29 JUL 11 03 APR 12 29 JUL 11 29 JUL 11 30 MAY 12 25 NOV 11 30 MAY 12 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 30 MAY 12
PLP-LESS P 6/16 18 SEP 12
PRELIMINARY PAGES LIST OF EFFECTIVE SECTIONS/SUBSECTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
R
Localization DSC-32-30-20 DSC-32-30-30 DSC-32-30-40 DSC-32-40-10 DSC-32-40-20 DSC-32-40-40 DSC-33-10-10 DSC-33-10-20 DSC-33-10-30 DSC-33-10-40 DSC-33-20-10 DSC-33-20-20 DSC-33-20-30 DSC-33-30-10 DSC-33-30-20 DSC-33-30-30 DSC-33-40-10 DSC-34-10-10 DSC-34-10-20 DSC-34-10-30 DSC-34-10-40 DSC-34-15-10 DSC-34-15-20 DSC-34-15-30 DSC-34-15-40 DSC-34-15-50 DSC-34-20 DSC-34-25 DSC-34-30-10 DSC-34-30-20 DSC-34-30-30 DSC-34-30-40 DSC-34-40-10 DSC-34-40-20 DSC-34-40-30 DSC-34-50-10 DSC-34-50-20 DSC-34-50-50 DSC-34-60-10 DSC-34-60-20 DSC-34-60-30
Subsection Title Controls and Indicators Warnings and Cautions Electrical Supply Description Controls and Indicators Electrical Supply General Description Controls and Indicators Electrical Supply General Controls and Indicators Electrical Supply Description Controls and Indicators Electrical Supply Controls and Indicators Description Controls and Indicators Warnings and Cautions Electrical Supply Description Normal Operation Operation in Case of Failure Warnings and Cautions Electrical Supply Standby Instruments ISIS Tuning Navaids Controls and Indicators Electrical Supply Description Warnings and Cautions Electrical Supply Description Controls and Indicators Electrical Supply Description Controls and Indicators Predictive Windshear System
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Rev. Date 03 APR 12 30 MAY 12 29 JUL 11 29 JUL 11 30 MAY 12 29 JUL 11 29 JUL 11 30 MAY 12 30 MAY 12 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 18 SEP 12 03 APR 12 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 03 APR 12 29 JUL 11 03 APR 12 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 30 MAY 12 30 MAY 12 29 JUL 11 30 MAY 12 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 30 MAY 12 29 JUL 11 29 JUL 11 30 MAY 12 30 MAY 12
PLP-LESS P 7/16 18 SEP 12
PRELIMINARY PAGES LIST OF EFFECTIVE SECTIONS/SUBSECTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
R R
Localization DSC-34-60-40 DSC-34-60-50 DSC-34-70-10 DSC-34-70-20 DSC-34-70-30 DSC-34-70-40 DSC-34-70-50 DSC-34-70-60 DSC-34-80-10 DSC-34-80-20 DSC-34-80-30 DSC-34-80-40 DSC-35-10 DSC-35-20-10 DSC-35-20-20 DSC-35-20-30 DSC-35-30-10 DSC-35-30-20 DSC-35-30-40 DSC-35-40-10 DSC-36-10-10 DSC-36-10-20 DSC-36-10-30 DSC-36-10-40 DSC-36-10-50 DSC-36-10-60 DSC-36-20 DSC-36-30 DSC-36-40 DSC-38-10 DSC-38-20 DSC-45-10 DSC-45-20 DSC-45-25 DSC-45-30 DSC-45-40 DSC-46-10 DSC-46-20 DSC-46-30 DSC-46-40 DSC-46-60
Subsection Title Warnings and Cautions ELECTRICAL SUPPLY Description GPWS Basics Modes EGPWS Functions Controls and Indicators Warnings and Cautions Electrical Supply Description Controls and Indicators Warnings and Cautions Electrical Supply General Description Controls and Indicators Electrical Supply Description Controls and Indicators Electrical Supply Description General Engine Bleed System Apu Bleed Air Supply Crossbleed Leak Detection Operation Following Failures Controls and Indicators Warnings and Cautions Electrical Supply Description ELECTRICAL SUPPLY Description System Operation Data Loading PRINTER ELECTRICAL SUPPLY General ATSU Communications Function AOC Applications CNS/ATM Warnings and Cautions
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Rev. Date 25 NOV 11 29 JUL 11 29 JUL 11 30 MAY 12 29 JUL 11 30 MAY 12 29 JUL 11 29 JUL 11 30 MAY 12 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 30 MAY 12 30 MAY 12 29 JUL 11 18 SEP 12 18 SEP 12 29 JUL 11 30 MAY 12 29 JUL 11 03 APR 12 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 03 APR 12 29 JUL 11 29 JUL 11 29 JUL 11 25 NOV 11 30 MAY 12 29 JUL 11 29 JUL 11 29 JUL 11 30 MAY 12 03 APR 12 25 NOV 11 03 APR 12 29 JUL 11
PLP-LESS P 8/16 18 SEP 12
PRELIMINARY PAGES LIST OF EFFECTIVE SECTIONS/SUBSECTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
R
Localization DSC-46-70 DSC-49-10-10 DSC-49-10-20 DSC-49-20 DSC-49-30 DSC-49-40 DSC-52-10-10 DSC-52-10-20 DSC-52-10-30 DSC-52-10-40 DSC-52-10-50 DSC-52-10-60 DSC-52-10-80 DSC-52-20 DSC-52-30 DSC-52-50 DSC-70-10 DSC-70-20 DSC-70-30-10 DSC-70-30-20 DSC-70-30-30 DSC-70-30-40 DSC-70-40-10 DSC-70-40-20 DSC-70-40-30 DSC-70-40-40 DSC-70-40-50 DSC-70-50 DSC-70-60 DSC-70-70 DSC-70-80-10 DSC-70-80-20 DSC-70-80-30 DSC-70-80-40 DSC-70-90 DSC-70-98 PRO-ABN-01 PRO-ABN-10 PRO-ABN-21 PRO-ABN-22 PRO-ABN-23
Subsection Title Electrical Supply General Main Components Controls and Indicators Warnings and Cautions Electrical Supply General Passenger Doors Emergency Exits Cargo Doors Avionics Compartment Access Door Cockpit Door Escape Slides/Rafts Controls and Indicators Warnings and Cautions ELECTRICAL SUPPLY Engine Fadec General Thrust Levers Thrust Rating Limit Thrust Control General Fuel Pump Unit Shut-Off Valves Hydromechanical Unit IDG Cooling System OIL SYSTEM Airbleed System (CFM) THRUST REVERSER SYSTEM General Architecture Ignition System Engine Starting System Controls and Indicators (CFM) ELECTRICAL SUPPLY Introduction Operating Techniques Air Conditioning / Pressurization / Ventilation Auto Flight Communications
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Rev. Date 30 MAY 12 29 JUL 11 29 JUL 11 30 MAY 12 29 JUL 11 29 JUL 11 30 MAY 12 30 MAY 12 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 03 APR 12 30 MAY 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 18 SEP 12 03 APR 12 30 MAY 12 18 SEP 12 03 APR 12 29 JUL 11 30 MAY 12 30 MAY 12 30 MAY 12 29 JUL 11 30 MAY 12 30 MAY 12 30 MAY 12 30 MAY 12 30 MAY 12
PLP-LESS P 9/16 18 SEP 12
PRELIMINARY PAGES LIST OF EFFECTIVE SECTIONS/SUBSECTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
R R R R
R
R R
R R R
R
Localization PRO-ABN-24 PRO-ABN-25 PRO-ABN-26 PRO-ABN-27 PRO-ABN-28 PRO-ABN-29 PRO-ABN-30 PRO-ABN-31 PRO-ABN-32 PRO-ABN-34 PRO-ABN-36 PRO-ABN-46 PRO-ABN-49 PRO-ABN-52 PRO-ABN-70 PRO-ABN-80 PRO-ABN-90 PRO-NOR-SOP-01 PRO-NOR-SOP-02 PRO-NOR-SOP-03 PRO-NOR-SOP-04 PRO-NOR-SOP-05 PRO-NOR-SOP-06 PRO-NOR-SOP-07 PRO-NOR-SOP-08 PRO-NOR-SOP-09 PRO-NOR-SOP-10 PRO-NOR-SOP-11 PRO-NOR-SOP-12 PRO-NOR-SOP-13 PRO-NOR-SOP-14 PRO-NOR-SOP-15 PRO-NOR-SOP-16 PRO-NOR-SOP-17 PRO-NOR-SOP-18 PRO-NOR-SOP-19 PRO-NOR-SOP-20 PRO-NOR-SOP-21 PRO-NOR-SOP-22 PRO-NOR-SOP-23 PRO-NOR-SOP-24
Subsection Title Electrical Equipment Fire Protection Flight Controls Fuel Hydraulic Ice and Rain Protection Indicating / Recording Systems Landing Gear Navigation Pneumatic Information Systems APU Doors Power Plant Miscellaneous Detailed Cabin / Cockpit Evacuation Procedure General Information Flight Preparation Safety Exterior Inspection Preliminary Cockpit Preparation Exterior Inspection Cockpit Preparation Before Pushback or Start Engine Start After Start Taxi Before Takeoff Takeoff After Takeoff Climb Cruise Descent Preparation Descent Precision Approach Non Precision Approach Visual Approach Landing Go-Around After Landing Parking
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Rev. Date 18 SEP 12 03 APR 12 18 SEP 12 18 SEP 12 18 SEP 12 30 MAY 12 30 MAY 12 30 MAY 12 30 MAY 12 18 SEP 12 30 MAY 12 25 NOV 11 29 JUL 11 29 JUL 11 18 SEP 12 18 SEP 12 03 APR 12 29 JUL 11 03 APR 12 29 JUL 11 18 SEP 12 18 SEP 12 18 SEP 12 03 APR 12 30 MAY 12 30 MAY 12 30 MAY 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 25 NOV 11 30 MAY 12 03 APR 12 18 SEP 12 03 APR 12 30 MAY 12 30 MAY 12 18 SEP 12 03 APR 12 30 MAY 12
PLP-LESS P 10/16 18 SEP 12
PRELIMINARY PAGES LIST OF EFFECTIVE SECTIONS/SUBSECTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
R
R
R
R
Localization PRO-NOR-SOP-25 PRO-NOR-SOP-90 PRO-NOR-SRP-01-05 PRO-NOR-SRP-01-10 PRO-NOR-SRP-01-15 PRO-NOR-SRP-01-20 PRO-NOR-SRP-01-30 PRO-NOR-SRP-01-40 PRO-NOR-SRP-01-50 PRO-NOR-SRP-01-60 PRO-NOR-SRP-01-70 PRO-NOR-SRP-01-80 PRO-SPO-20 PRO-SPO-25-10 PRO-SPO-25-20 PRO-SPO-25-30 PRO-SPO-25-40 PRO-SPO-30 PRO-SPO-35 PRO-SPO-40-10 PRO-SPO-40-20 PRO-SPO-40-30 PRO-SPO-40-40 PRO-SPO-40-50 PRO-SPO-40-60 PRO-SPO-45 PRO-SPO-50 PRO-SPO-51 PRO-SPO-60 PRO-SPO-65 PRO-SPO-85 PRO-SUP-10 PRO-SUP-21 PRO-SUP-22-10 PRO-SUP-22-20-15 PRO-SUP-23 PRO-SUP-24 PRO-SUP-25 PRO-SUP-27-10 PRO-SUP-27-20 PRO-SUP-27-30
Subsection Title Securing the Aircraft Standard Callouts Introduction Cockpit Preparation Before Pushback or Start Taxi Takeoff Climb Cruise Descent Approach Go-Around Flight Without Cabin Pressurization General Limitations Procedures Performance High Altitude Operations Flight Over Mountainous Area General Operational Limitations Dispatch Consideration Diversion During Extended Range Operations Procedures Performance Engine Intermix Operations Reduced Vertical Separation Minimum (RVSM) Required Navigation Performance (RNP) Operations on Narrow Runways Operations at QNH Above 1050 hPa ILS PRM Approach Operating Speeds Definition Air Conditioning / Pressurization / Ventilation FMGS Reset and Other Abnormal Procedures FMS2 Honeywell Specificities Communications Electrical Equipment General Normal Operations Abnormal Operations
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Rev. Date 29 JUL 11 03 APR 12 18 SEP 12 18 SEP 12 30 MAY 12 30 MAY 12 30 MAY 12 03 APR 12 30 MAY 12 30 MAY 12 18 SEP 12 30 MAY 12 03 APR 12 29 JUL 11 25 NOV 11 03 APR 12 30 MAY 12 18 SEP 12 18 SEP 12 25 NOV 11 25 NOV 11 25 NOV 11 25 NOV 11 03 APR 12 03 APR 12 30 MAY 12 30 MAY 12 03 APR 12 18 SEP 12 03 APR 12 29 JUL 11 03 APR 12 29 JUL 11 30 MAY 12 30 MAY 12 03 APR 12 18 SEP 12 03 APR 12 29 JUL 11 25 NOV 11 25 NOV 11
PLP-LESS P 11/16 18 SEP 12
PRELIMINARY PAGES LIST OF EFFECTIVE SECTIONS/SUBSECTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
R
R R N R R
R
R
Localization PRO-SUP-27-40 PRO-SUP-27-50 PRO-SUP-28 PRO-SUP-30 PRO-SUP-31 PRO-SUP-32 PRO-SUP-34 PRO-SUP-46 PRO-SUP-70 PRO-SUP-80 PRO-SUP-90 PRO-SUP-91-10 PRO-SUP-91-20 PRO-SUP-91-30 PRO-SUP-91-40 PRO-SUP-91-50 PRO-SUP-92-10 LIM-10 LIM-11 LIM-12 LIM-13 LIM-21-21_10 LIM-21-21_20 LIM-21-21_30 LIM-22-10 LIM-22-20 LIM-24 LIM-27 LIM-28 LIM-29 LIM-32 LIM-34 LIM-35 LIM-49-10 LIM-49-20 LIM-70 OEB-GEN OEB-38 OEB-40
Subsection Title
Rev. Date
The Protection Systems Aircraft Trimming Fuel Ice and Rain Protection Indicating / Recording Systems Landing Gear Navigation Information Systems Power Plant Miscellaneous One Engine Taxi Severe Turbulence Operations in Windshear or Downburst Cold Weather Operations On Airports Covered With Ash, Sand or Dust Fluid Contaminated Runway Less Paper in the Cockpit General Limitations Weight and Center of Gravity Limits Environmental Envelope and Airport Operations Speed Limitations Air Conditioning Pressurization Ventilation General Automatic Approach, Landing and Roll Out Electrical Flight Controls Fuel Hydraulic Landing Gear Navigation Oxygen General Envelope Power Plant General Description Erroneous Radio Altimeter Height Indication AIR ENG 1(2) BLEED ABNORMAL PR or AIR ENG 1(2) BLEED FAULT
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
29 JUL 11 29 JUL 11 29 JUL 11 30 MAY 12 29 JUL 11 25 NOV 11 30 MAY 12 29 JUL 11 30 MAY 12 18 SEP 12 03 APR 12 30 MAY 12 18 SEP 12 25 NOV 11 18 SEP 12 30 MAY 12 18 SEP 12 29 JUL 11 18 SEP 12 18 SEP 12 30 MAY 12 29 JUL 11 30 MAY 12 29 JUL 11 18 SEP 12 18 SEP 12 30 MAY 12 29 JUL 11 25 NOV 11 29 JUL 11 25 NOV 11 18 SEP 12 25 NOV 11 29 JUL 11 30 MAY 12 03 APR 12 25 NOV 11 29 JUL 11 29 JUL 11
PLP-LESS P 12/16 18 SEP 12
PRELIMINARY PAGES LIST OF EFFECTIVE SECTIONS/SUBSECTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
Localization OEB-41 OEB-43 OEB-44 FCB-10 FCB-FCB2 FCB-FCB5 FCB-FCB7 FCB-FCB8 FCB-FCB9 FCB-FCB11 FCB-FCB12 FCB-FCB13 FCB-FCB15 FCB-FCB16 FCB-FCB17 FCB-FCB18 FCB-FCB20 FCB-FCB22 FCB-FCB23
R
FCB-FCB24 FCB-FCB25 FCB-FCB26 FCB-FCB27 PER-LOD-GEN PER-LOD-CGO PER-LOD-FUL PER-LOD-WBA-LTS PER-LOD-WBA-FIT-10 PER-OPD-GEN PER-OPD-CON-AEO PER-OPD-CON-OEI PER-THR-GEN PER-THR-MTO PER-THR-MGA PER-THR-FLX PER-THR-MCT PER-THR-MCL PER-THR-MCR
Subsection Title
Rev. Date
Erroneous Alternate Fuel Predictions Upon Modification of a Company Route in the Alternate Flight Plan F/CTL SPOILER FAULT L/G GEAR NOT DOWNLOCKED Introduction Operation in Windshear/Downburst Conditions Avoiding Tailstrikes FQI Accuracy Electronic Interference from Portable Equipment carried on by Passengers Thrust Acceleration in A/THR Modes Radio Altimeter Anomalies during Adverse Weather Conditions FMGS Navigation Database Specific Features of the FMGS Full Standard VMO/MMO Determination Operation of Fleets with/without CPIP Characteristic and Protection Speeds Ground Speed Mini Function Publication of some Attendant Information Bulletins EGPWS Database Use of Managed Guidance in Approach and NAV Database Validation Aircraft Handling in Final Approach Use of Rudder on Transport Category Airplanes Yaw Disturbances during the Takeoff Roll Automatic Landing Performance GENERAL CARGO LOADING FUEL LOAD AND TRIM SHEET FUEL INDEX TABLE GENERAL ALL ENGINES OPERATIVE ONE ENGINE INOPERATIVE GENERAL MAXIMUM TAKEOFF MAXIMUM GO AROUND FLEXIBLE TAKEOFF MAXIMUM CONTINUOUS MAXIMUM CLIMB MAXIMUM CRUISE
03 APR 12
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
30 MAY 12 30 MAY 12 29 JUL 11 29 JUL 11 29 JUL 11 25 NOV 11 29 JUL 11 29 JUL 11 29 JUL 11 30 MAY 12 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 03 APR 12 03 APR 12 29 JUL 11 30 MAY 12 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 03 APR 12 03 APR 12 18 SEP 12 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12
PLP-LESS P 13/16 18 SEP 12
PRELIMINARY PAGES LIST OF EFFECTIVE SECTIONS/SUBSECTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
R
Localization PER-TOF-THR-FLX-10 PER-TOF-THR-FLX-20 PER-TOF-THR-FLX-30 PER-TOF-THR-FLX-40 PER-TOF-TOC-05 PER-TOF-TOC-10-10 PER-TOF-TOC-10-20 PER-TOF-TOC-10-30 PER-TOF-TOC-12-10 PER-TOF-TOC-12-30 PER-TOF-TOC-12-40 PER-TOF-TOC-12-50 PER-TOF-TOC-14-10 PER-TOF-TOC-14-20 PER-TOF-TOC-14-30 PER-TOF-TOC-16-10 PER-TOF-TOC-16-20 PER-TOF-TOC-16-30 PER-TOF-TOC-18-10 PER-TOF-TOC-18-20 PER-TOF-TOC-18-30 PER-TOF-TOC-18-40 PER-TOF-TOC-20-10 PER-TOF-TOC-20-20 PER-TOF-TOC-20-30 PER-TOF-TOD-24 PER-TOF-TOD-25-10 PER-TOF-TOD-25-20 PER-TOF-TOD-40-10 PER-TOF-TOD-40-20 PER-TOF-TOD-40-30 PER-TOF-TOD-40-40 PER-TOF-TOD-50 PER-TOF-CTA-10 PER-TOF-CTA-20 PER-TOF-CTA-30 PER-TOF-CTA-40-10 PER-TOF-CTA-40-20
Subsection Title DEFINITION OF FLEXIBLE TAKEOFF USE OF FLEXIBLE TAKEOFF REQUIREMENTS RECOMMENDATION INTRODUCTION TAKEOFF PERFORMANCE TAKEOFF CHART DESCRIPTION ADDITIONAL INFORMATION DETERMINATION OF MAXIMUM TAKEOFF WEIGHT AND SPEEDS EXTRAPOLATION MAXIMUM STRUCTURAL TAKEOFF WEIGHT SUMMARY DETERMINATION OF FLEXIBLE TAKEOFF TEMPERATURE AND SPEEDS FLEXIBLE TAKEOFF NOT POSSIBLE SUMMARY TAKEOFF PERFORMANCE TAKEOFF CHART DESCRIPTION ADDITIONAL INFORMATION DETERMINATION OF MAXIMUM TAKEOFF WEIGHT AND SPEEDS EXTRAPOLATION MAXIMUM STRUCTURAL TAKEOFF WEIGHT SUMMARY DETERMINATION OF FLEXIBLE TAKEOFF TEMPERATURE AND SPEEDS FLEXIBLE TAKEOFF NOT POSSIBLE SUMMARY QNH/BLEEDS CORRECTION SPEEDS LIMITED BY VMC V2 LIMITED BY VMU/VMCA INTRODUCTION USE OF TABLES HOW TO PROCEED QUICK REFERENCE TABLES NET TAKEOFF FLIGHT PATH GENERAL DEFINITIONS OPERATIONAL CONDITIONS TAKEOFF PERFORMANCE TAKEOFF FROM A WET RUNWAY
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Rev. Date 29 JUL 11 29 JUL 11 03 APR 12 29 JUL 11 29 JUL 11 29 JUL 11 18 SEP 12 03 APR 12 03 APR 12 29 JUL 11 29 JUL 11 29 JUL 11 03 APR 12 29 JUL 11 29 JUL 11 29 JUL 11 03 APR 12 03 APR 12 03 APR 12 29 JUL 11 29 JUL 11 29 JUL 11 03 APR 12 29 JUL 11 29 JUL 11 03 APR 12 30 MAY 12 03 APR 12 29 JUL 11 29 JUL 11 03 APR 12 03 APR 12 03 APR 12 29 JUL 11 29 JUL 11 29 JUL 11 29 JUL 11 03 APR 12
PLP-LESS P 14/16 18 SEP 12
PRELIMINARY PAGES LIST OF EFFECTIVE SECTIONS/SUBSECTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
R R
Localization PER-TOF-CTA-40-30 PER-TOF-CTA-40-40 PER-FPL-GEN-INT PER-FPL-GEN-MFR PER-FPL-GEN-FPL PER-FPL-FLP-CAT PER-FPL-FLP-ALT-10 PER-FPL-FLP-ALT-20 PER-FPL-FLP-ICR-10 PER-FPL-FLP-ICR-20 PER-FPL-FLP-ICR-30 PER-FPL-FLP-ICR-40 PER-FPL-FLP-ICR-50 PER-FPL-FLP-ICR-60 PER-FPL-FLP-QFP-10 PER-FPL-FLP-QFP-20 PER-FPL-FLP-QFP-30 PER-FPL-FLP-QFP-40 PER-FPL-FLP-QFP-50 PER-FPL-FLP-ALN-20 PER-FPL-FLP-FTK PER-CLB-GEN PER-CLB-CLT PER-CRZ-ECI-10 PER-CRZ-ALT-10 PER-CRZ-ALT-20 PER-CRZ-ALT-30 PER-CRZ-CRT-10 PER-CRZ-CRT-20 PER-CRZ-CRT-30 PER-CRZ-ICQ-10 PER-CRZ-ICQ-20 PER-CRZ-ICQ-30 PER-CRZ-ICQ-40 PER-CRZ-ICQ-50 PER-HLD-GEN PER-HLD-HLD PER-DES-GEN PER-DES-STD PER-DES-EMG
Subsection Title
Rev. Date
TAKEOFF FROM A CONTAMINATED RUNWAY EXAMPLE INTRODUCTION MINIMUM RECOMMENDED FUEL REQUIREMENTS FLIGHT PLAN CALCULATION TABLES OPTIMUM AND MAXIMUM ALTITUDES OPTIMUM ALTITUDE ON SHORT STAGE GENERAL INTEGRATED CRUISE AT A GIVEN MACH NUMBER INTEGRATED CRUISE AT LONG RANGE CRUISE SPEED CLIMB CORRECTION STEP CLIMB CORRECTION DESCENT CORRECTION INTRODUCTION CORRECTION FOR DEVIATION FROM REFERENCE LANDING WEIGHT EXAMPLE FLIGHT PLANNING AT A GIVEN MACH NUMBER FLIGHT PLANNING AT LONG RANGE SPEED ALL ENGINES OPERATIVE FUEL TANKERING GENERAL CLIMB TABLES OPTIMUM MACH NUMBER OPTIMUM AND MAXIMUM ALTITUDES WIND ALTITUDE TRADE FOR CONSTANT SPECIFIC RANGE OPTIMUM ALTITUDE ON SHORT STAGE GENERAL CRUISE AT M.78 CRUISE AT LONG RANGE GENERAL CORRECTION FOR DEVIATION FROM REFERENCE WEIGHT EXAMPLE IN CRUISE QUICK CHECK M.78 IN CRUISE QUICK CHECK LONG RANGE GENERAL HOLDING TABLES GENERAL STANDARD EMERGENCY
03 APR 12 03 APR 12 29 JUL 11 29 JUL 11 29 JUL 11 03 APR 12 18 SEP 12 18 SEP 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 30 MAY 12 03 APR 12
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 29 JUL 11 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 29 JUL 11 03 APR 12 03 APR 12 25 NOV 11 29 JUL 11 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 29 JUL 11 03 APR 12 03 APR 12
PLP-LESS P 15/16 18 SEP 12
PRELIMINARY PAGES LIST OF EFFECTIVE SECTIONS/SUBSECTIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
R
Localization PER-GOA-GEN PER-GOA-ACG-NOR PER-GOA-ACG-CAT PER-LDG-GEN PER-LDG-CTA-10 PER-LDG-CTA-20 PER-LDG-DIS-MAT PER-LDG-DIS-RLD PER-OEI-GEN-05 PER-OEI-GEN-10 PER-OEI-GEN-15 PER-OEI-GEN-20 PER-OEI-ALT-10 PER-OEI-CRT-10 PER-OEI-CRT-20 PER-OEI-ICQ-10 PER-OEI-ICQ-20 PER-OEI-HLD PER-OEI-DES-10 PER-OEI-DES-15 PER-OEI-DES-20 PER-OEI-DES-30
Subsection Title GENERAL NORMAL CAT II GENERAL GENERAL DEFINITIONS Runway Condition Assessment Matrix for Landing REQUIRED LANDING DISTANCES / MANUAL LANDING GENERAL STANDARD STRATEGY OBSTACLE STRATEGY FIXED SPEED STRATEGIES CEILINGS STANDARD AND OBSTACLE STRATEGIES FIXED SPEED STRATEGIES STANDARD STRATEGIES FIXED SPEED STRATEGIES HOLDING STANDARD STRATEGY OBSTACLE STRATEGY FIXED SPEED STRATEGIES DESCENT TO LANDING
Rev. Date 30 MAY 12 03 APR 12 03 APR 12 30 MAY 12 29 JUL 11 30 MAY 12 18 SEP 12 30 MAY 12 25 NOV 11 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12 03 APR 12
(1) Evolution code : N=New, R=Revised, E=Effectivity, M=Moved
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LESS P 16/16 18 SEP 12
PRELIMINARY PAGES AIRCRAFT ALLOCATION TABLE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
This table gives, for each delivered aircraft, the cross reference between: -
The Manufacturing Serial Number (MSN). The Fleet Serial Number (FSN) of the aircraft as known by AIRBUS S.A.S. The registration number of the aircraft as known by AIRBUS S.A.S. The aircraft model. (1)
M
MSN
FSN
9761
Registration Number
Model
18-CMHE
320-214
(1) Evolution code : N=New, R=Revised
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-AAT P 1/2 18 SEP 12
PRELIMINARY PAGES AIRCRAFT ALLOCATION TABLE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-AAT P 2/2 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION J0006 Applicable to: ALL J0012
Linked SB
Incorp. Date
Title
29 JUL 11
FUEL- INSTALL A CENTRE TANK SYSTEM-
29 JUL 11
Applicable to: ALL J0071
LIGHTS - NAVIGATION LIGHTS - INSTALL A SECOND NAVIGATION LIGHT SYSTEM -
29 JUL 11
Applicable to: ALL J0513
WINGS-WING TIP FENCES-INTRODUCE WING TIPS INCLUDING FENCES-
25 NOV 11
ICE AND RAIN PROTECTION - WING ICE PROTECTION - ETOPS CIRCUIT BREAKERS 1DL AND 2DL - TRANSFER POWER SUPPLY.
29 JUL 11
FUEL - IMPROVE LOW LEVEL WARNING
29 JUL 11
Applicable to: ALL J1255
WINGS - REMOVE LEADING EDGE VENTILATION SYSTEM
29 JUL 11
Applicable to: ALL J1334
FUEL - TANK LEVEL SENSING - INTRODUCE MODIFIED LOW FUEL PRESSURE WARNING CONTROL
29 JUL 11
Applicable to: ALL J1617
LANDING GEAR-MLG-LGCIU-INTRODUCTION OF STANDARD UNIT P/N A4C
29 JUL 11
Applicable to: ALL J2190
FLIGHT CONTROLS-GENERAL- DELETION OF L.A.F. FEATURE FROM A320 A/C (SERIAL SOLUTION)
29 JUL 11
Applicable to: ALL J2257
FUEL - MAIN FUEL PUMP SYSTEM - ADAPT PUMP CONTROL LATCH FOR FLIGHT DECK REFUEL CAPABILITY
29 JUL 11
Applicable to: ALL J2360
FUEL-MANUAL (MAGNETIC) INDICATORS- DELETE ATTIDUDE MONITOR
29 JUL 11
Applicable to: ALL J2361
FUEL - QUANTITY INDICATION - INTRODUCE FUEL LEAK DETECTION
29 JUL 11
FUEL-QUANTITY INDICATION-REMOVE FUEL LEAK DETECTION FUNCTION ASSOCIATED WITH FQIC 13-9 (ANTI-MOD FOR MOD 32650)
Applicable to: ALL J0664 Applicable to: ALL J0689
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 1/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION J2527
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL J2816
FUEL - QUANTITY INDICATING - INSTALL FUEL QUANTITY INDICATING COMPUTER STANDARD 13.10
29 JUL 11
Applicable to: ALL J2879
WINGS - FIXED PARTITION - INTRODUCE A STANDARD OF BOX WITHOUT DRY BAY
29 JUL 11
Applicable to: ALL J2963
INERT GAS SYSTEM - CERTIFY FUEL TANK INERTING SYSTEM AND ACTIVATE MONITORING
29 JUL 11
Applicable to: ALL K0024
WINGS - MAIN STRUCTURE - REDUCE THE QUANTITY OF MAGNETIC LEVEL INDICATORS
29 JUL 11
Applicable to: ALL K0026
DOORS- BULK CARGO COMPARTMENT- INSTALL AN ADDITIONAL DOOR AT FR 60/62-
29 JUL 11
Applicable to: ALL K0035
LIGHTS - EXTERNAL LIGHTS - INSTALL LOGO LIGHTS
29 JUL 11
Applicable to: ALL K0036
FIRE PROTECTION - FWD CARGO COMPARTMENT INSTALL SMOKE DETECTION SYSTEM -
29 JUL 11
Applicable to: ALL K0037
FIRE PROTECTION - AFT CARGO COMPARTMENT INSTALL SMOKE DETECTION SYSTEM -
29 JUL 11
Applicable to: ALL K0052
FIRE PROTECTION - CARGO COMPARTMENT FIRE EXTINGUISHING - INSTALL A SINGLE SHOT SYSTEM -
29 JUL 11
Applicable to: ALL K0064
INDICATING/RECORDING SYSTEMS - INSTALL AN AIRCRAFT INTEGRATED DATA SYSTEM -
29 JUL 11
Applicable to: ALL K0070
LIGHTS - EXTERIOR LIGHTS - INSTALL SYNCHRONIZED STROBE LIGHTS
29 JUL 11
Applicable to: ALL K0071
AIR CONDITIONING - CARGO COMPARTMENT - VENTILATION - INSTALL SYSTEM IN AFT COMPARTMENT -
29 JUL 11
AIR CONDITIONING - AFT CARGO COMPARTMENT INSTALL HEATING SYSTEM
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 2/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION
Incorp. Date
Title
29 JUL 11
Applicable to: ALL K10003
WATER/WASTE- INSTALL VACUUM TOILET SYSTEM -
29 JUL 11
Applicable to: ALL K10009
AIRBORNE AUXILIARY POWER-CONTROL AND MONITORING - INTRODUCE ECB SOFTWARE VERSION 06.00.000
29 JUL 11
Applicable to: ALL K1014
EQUIPMENT/FURNISHINGS - CURTAINS AND PARTITIONS - INSTALL IMPROVED STRIKES FOR COCKPIT DOOR
29 JUL 11
Applicable to: ALL K10359
WATER/WASTE - RELOCATE POTABLE WATER TANK -
29 JUL 11
Applicable to: ALL K10463
LIGHTS- EMERGENCY LIGHTING- DEFINE FLOOR MOUNTED LUFTHANSA TECHNIK 900 SERIES EEPMS
25 NOV 11
Applicable to: ALL K10494
AIR CONDITIONING - PACK TEMPERATURE CONTROL - INSTALL AIR CONDITIONING CONTROLLER P/N 1803B0000-02
29 JUL 11
Applicable to: ALL K10516
AIRBORNE AUXILIARY POWER - GENERAL - INSTALL APIC APS3200 APU AS STANDARD (REPLACES HONEYWELL GTCP36-300)
29 JUL 11
Applicable to: ALL K1119
AIRBORNE AUXILIARY POWER - CONTROL AND MONITORING - INTRODUCE HONEWELL VECB WITH SOFTWARE -04
29 JUL 11
Applicable to: ALL K11694
EQUIPMENT/FURNISHINGS - CARGO COMPARTMENT - REARRANGE COMPARTMENT 4 INTO TWO ZONES -
29 JUL 11
Applicable to: ALL K12405
E/F -MISCELLANEOUS EMERGENCY EQUIPMENTINSTALL ELT (406AFN) WITH RCP IN COCKPIT AND NAV PROVISIONS - HONEYWELL
29 JUL 11
Applicable to: ALL K1245
COMMUNICATIONS - CIDS - INTRODUCE HANDSET SERIES N40A FROM VENDOR HOLMBERG
29 JUL 11
APU - INTRODUCE APU MODE 6 AND ASSOCIATED ECB (GARRETT)
K0082
Linked SB
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 3/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION
Incorp. Date
Title
29 JUL 11
Applicable to: ALL K12825
COMMUNICATIONS - CIDS - INSTALL CIDS AND SDF OBRM SOFTWARE P/N -33A AND CAM UPDATE
29 JUL 11
Applicable to: ALL K1420
COMMUNICATIONS - CIDS - INSTALL CIDS DIRECTOR P/N -333B
29 JUL 11
Applicable to: ALL K1806
DOORS-CARGO COMPT DOORS-MODIFY LOCKING INDICATION
29 JUL 11
Applicable to: ALL K2335
ELECTRICAL POWER-AC/DC ESSENTIAL POWER DISTRIBUTION-PROVIDE PROVISIONS FOR ETOPS-
29 JUL 11
Applicable to: ALL K2938
FIRE PROTECTION - LAVATORY SMOKE DETECTION - INTRODUCE AMBIENT SYSTEM
29 JUL 11
Applicable to: ALL K2962
DOORS-CARGO COMPARTMENT DOOR HYDRAULIC SYSTEM-INTRODUCE MODIFIED DOOR SELECTOR VALVE
29 JUL 11
Applicable to: ALL K3118
HYDRAULIC POWER-BLUE MAIN HYDRAULIC POWER-IMPROVE MAINTENANCE STATUS OF BLUE HYDRAULIC RESERVOIR
29 JUL 11
Applicable to: ALL K3279
AUXILIARY POWER UNIT - CONTROL AND MONITORING - INTRODUCE A NEW ECB
29 JUL 11
Applicable to: ALL K3471
AUXILIARY POWER UNIT - CONTROL AND MONITORING - MODIFY WIRE HARNESSES FOR NEW ECB 817-1
29 JUL 11
Applicable to: ALL K3599
GENERAL - INCREASE DESIGN WEIGHT TO 61T MZFW
29 JUL 11
Applicable to: ALL K3901
AIR CONDITIONING - COCKPIT AND CABIN TEMPERATURE CONTROL - INTRODUCE ZONE TEMPERATURE CONTROLLER -03
29 JUL 11
Applicable to: ALL K4457
COMMUNICATIONS-CIDS-INTRODUCE MODIFIED DIRECTOR POWER SUPPLY PRINCIPLE
29 JUL 11
A.P.U.-POWER PLANT-INTRODUCE ALLIED SIGNAL APU 131-9(A)
K12824
Linked SB
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 4/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION K4574
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL K4726
AIR CONDITIONING-FLOW CONTROL AND INDICATING INTRODUCE MODIFIED AIR CONDITIONING FLOW CONTROL
29 JUL 11
Applicable to: ALL K4787
WATER/WASTE-TOILET SYSTEM-INTRODUCE MODIFIED TOILET ASSY
29 JUL 11
Applicable to: ALL K4793
LIGHTS-INTRODUCE EPSU P/N 54-10 ON A319/A320 A/C
29 JUL 11
Applicable to: ALL K4913
AIR CONDITIONING-AIR COOLING SYSTEMINTRODUCE MODIFIED RAM AIR OUTLET
29 JUL 11
Applicable to: ALL K5059
HYDRAULIC POWER - AUXILIARY HYDRAULIC POWER - INSTALL A319 RAM AIR TURBINE ON A320
29 JUL 11
Applicable to: ALL K5070
COMMUNICATIONS - CIDS - RELOCATE PA IN USE LIGHT IN COCKPIT
29 JUL 11
Applicable to: ALL K5213
COMMUNICATIONS - CIDS - DUAL DIAL CODE ON HANDSET KEYBOARD (A319/A3 21)
29 JUL 11
Applicable to: ALL K5446
AIR CONDITIONING-PACK TEMPERATURE CTRLINTRODUCE MODIFIED PACK TEMPERATURE CONTROLLER
29 JUL 11
Applicable to: ALL K5549
INDICATING/RECORDING SYSTEMS-CFDSINTRODUCE A COMBINED FDIU/DMU
29 JUL 11
Applicable to: ALL K5801
OXYGEN-PASSENGER OXYGEN-INTRODUCE MODIFIED CHEMICAL OXYGEN CONTAINER -15 MINPURITAN
29 JUL 11
Applicable to: ALL K6156
AIR CONDITIONING-PRESSURE CONTROL AND MONITORING-INTRODUCE PRESSURE CONTROLLER P/N 9022-15702-10
29 JUL 11
Applicable to: ALL K6443
AIR CONDITIONING-PACK TEMP.CTRL INTRODUCE MODIFIED PACK TEMP. CTRL P/N 759D0000-02
29 JUL 11
AIR CONDITIONING-AIR COOLING- INSTALL A NEW ECS
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 5/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION K6936
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL K7072
AIRBORNE AUXILIARY POWER (APU) - GENERAL - INCREASE OPERATION ENVELOPE TO 39800 FT FOR GTCP 36-300
29 JUL 11
Applicable to: ALL K7755
LIGHTS-EMERGENCY LIGHTING-MODIFY EPSU LOAD DISTRIBUTION FOR A319/A320
29 JUL 11
Applicable to: ALL K7790
EQUIPMENT FURNISHINGS-CURTAINS AND PARTITIONS-MODIFIED INTRUSION AND PENETRATION RESISTANT COCKPIT DOOR
29 JUL 11
Applicable to: ALL K7847
DOORS-PASSENGER COMPARTMENT FIXED INTERIOR DOORS-INSTALL ELECTRICAL COCKPIT DOOR RELEASE SYSTEM
25 NOV 11
Applicable to: ALL K8400
EQUIPMENT/FURNISHINGS-PASSENGER COMPART SEATS - INTRODUCE ISPSS IN CONJUNCTION WITH INTEGRATED IFE/SPSS
29 JUL 11
Applicable to: ALL K8734
COMMUNICATIONS-CIDS-INTRODUCE ENHANCED CIDS (A318 VERSION) AND RELATED SYSTEMS ON SINGLE AISLE FAMILY
25 NOV 11
Applicable to: ALL K8905
AIR CONDITIONING - AIR COOLING - ADAPT A318 ECS TO A320 A/C
29 JUL 11
Applicable to: ALL K9458
EQUIPMENT/FURNISHINGS-CURTAINS AND PARTITIONS-INSTALL DEADBOLT ON CENTER LATCH OF REINFORCED COCKPIT DOOR
25 NOV 11
Applicable to: ALL K9473
AIR CONDITIONING - PACK TEMPERATURE CONTROL - INSTALL IMPROVED AIR COND. SYSTEM CONTROLLER PN 1803B0000-01
29 JUL 11
Applicable to: ALL K9877
AIR CONDITIONING - PRESSURE CONTROL AND MONITORING - INSTALL RPCU AND WIRING PROVISIONS FOR RPWS
29 JUL 11
EQUIPMENT/FURNISHINGS - CURTAINS AND PARTITIONS - MODIFY DEADBOLT FOR REINFORCED COCKPIT DOOR
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 6/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P0040
NAVIGATION - WEATHER RADAR SYSTEM - INSTALL A 2ND SYSTEM -
29 JUL 11
Applicable to: ALL P0052
EQUIPMENT/FURNISHINGS - FLIGHT COMPARTMENT - INSTALL A 4TH OCCUPANT SEAT -
29 JUL 11
Applicable to: ALL P0063
LANDING GEAR - INSTALL TYRE PRESSURE INDICATING SYSTEM (MESSIER) -
29 JUL 11
Applicable to: ALL P0091
NAVIGATION - INSTALL PROVISION SYSTEM FOR ADF/RMI
29 JUL 11
Applicable to: ALL P0143
OXYGEN - FLIGHT CREW SYSTEM - INSTALL A 77.1 CU/FT BOTTLE IN COMPOSITE MATERIAL -
29 JUL 11
Applicable to: ALL P0147
COMMUNICATIONS - RADIO MANAGEMENT INSTALL A 3RD RMP -
29 JUL 11
Applicable to: ALL P0160
STRUCTURE - REINFORCE STRUCTURE TO ALLOW MTOW 72T-MLW 63T-MZFW 59T DESIGN WEIGHTS
29 JUL 11
Applicable to: ALL P0196
OXYGEN - FLIGHT CREW OXYGEN - INSTALL A 115 CU/FT STEEL OXYGEN CYLINDER -
29 JUL 11
Applicable to: ALL P0197
LANDING GEAR - INSTALL TYRE PRESSURE INDICATING SYSTEM LORAL (GOODYEAR) -
29 JUL 11
COMMUNICATIONS - HF SYSTEM - INSTALL A SINGLE SYSTEM
29 JUL 11
COMMUNICATIONS-INSTALL DATA LINK SYSTEM
29 JUL 11
Applicable to: ALL P0415
NAVIGATION - REPLACE VOR RMI BY A VOR/ADF/RMI
29 JUL 11
Applicable to: ALL P0622
COMMUNICATIONS - PROVIDE "HOT MIKE" RECORDING
29 JUL 11
NAVIGATION - AIR DATA - PROVIDE QFE BARO SETTING
P0031
Applicable to: ALL P0283 Applicable to: ALL P0287
Linked SB
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 7/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P10022
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P10098
ENGINE AND FUEL CONTROL- FADEC SYSTEMINTRODUCE NEW "5BO" ECU SOFTWARE STD ON CFM56-5B ENGINES - CNF CFM 109B
29 JUL 11
Applicable to: ALL P10267
ELECTRICAL POWER - AC ESSENTIAL GENERATION SWITCHING - INSTALL AUTO SWITCHING SYSTEM FOR AC AND DC ESS BUS
29 JUL 11
Applicable to: ALL P10321
NAVIGATION - RADIO MAGNETIC INFORMATION SWITCHING AND INDICATING - RE-INSTALL THALES DDRMI VOR/DME INDICATORS
29 JUL 11
Applicable to: ALL P10383
AUTO FLIGHT - GENERAL - REMOVE AFM LIMITATION ON NON-PRECISION APPROACHES WITH ONE ENGINE OUT ON A320/A318 A/C
29 JUL 11
Applicable to: ALL P10439
INDICATING/RECORDING SYSTEMS - FLIGHT WARNING COMPUTER (FWC) - INSTALL FWC STANDARD H2-F5
29 JUL 11
Applicable to: ALL P10443
AUTO-FLIGHT - FMGC - INSTALL FMGC HNWL STD P1C12 ON CFM A/C
29 JUL 11
Applicable to: ALL P10493
FLIGHT CONTROL - ELAC SYSTEM - INTRODUCE ELAC "L93" SOFTWARE STANDARD
29 JUL 11
Applicable to: ALL P10527
FLIGHT CONTROL - ELAC - ACTIVATE HIGH ALTITUDE UPSETS VMO/MMO OVERSHOOT PROTECTION FUNCTION ON ELAC
29 JUL 11
Applicable to: ALL P10538
INDICATING/RECORDING SYSTEM-ELECTRONIC INSTRUMENT SYSTEM (EIS)-INSTALL DISPLAY MANAGEMENT COMP. SOFTW. EIS2 S8-2
29 JUL 11
Applicable to: ALL P10652
AUTO FLIGHT - AUTOPILOT/FLIGHT DIRECTOR INSTALL WIRING PROVISIONS FOR AP/FD TCAS FUNCTION
29 JUL 11
COMMUNICATIONS - AUDIO MANAGEMENTINSTALL NON SATCOM TEAM ACP3000 P/N ACP2788AD01
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 8/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P10686
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P10694
AUTO-FLIGHT - FMGC - INSTALL HONEYWELL PERFORMANCE DATABASE RELEASE 1A (PS4087592-901)
29 JUL 11
Applicable to: ALL P10762
AUTO-FLIGHT - FMGC - ACTIVATE "MOD NAV GO AROUND" ON FMGC
29 JUL 11
Applicable to: ALL P10777
AUTO FLIGHT - FMGC - INSTALL FMGC HWL H2C12 (RELEASE 1A) ON CFM A/C
29 JUL 11
Applicable to: ALL P1116
AUTO FLIGHT - FAC (FLIGHT AUGMENTATION COMPUTER) - INTRODUCE FAC SOFTWARE STANDARD "BAM0620"
29 JUL 11
Applicable to: ALL P11256
ELECTRICAL POWER - RELOCATE 3 CIRCUIT BREAKERS FROM PANEL 120 VU TO 49 VU -
29 JUL 11
Applicable to: ALL P11473
NAVIGATION - GENERAL - CERTIFY RNP AR CAPABILITY (STEP3) ON A320 AND A318
29 JUL 11
Applicable to: ALL P11592
AUTO FLIGHT- FLIGHT MANAGEMENT SYSTEMACTIVATE BARO RADIO SETTING FUNCTION
29 JUL 11
Applicable to: ALL P11744
COMMUNICATION-COCKPIT VOICE RECORDERSUPPLY THE CVR 28VDC TO COMPLY WITH FAA REGULATION (FAR 25.14.57 (D)(5))
29 JUL 11
Applicable to: ALL P11807
FLIGHT CONTROLS- SEC SYSTEM- INTRODUCE NEW SPOILER ELEVATOR COMPUTER (SEC) SOFTWARE STD 120 WITH HARD B'
03 APR 12
Applicable to: ALL P11856
INDICATING/RECORDING SYSTEM - ELECTRONIC INSTRUMENT SYSTEM (EIS) - INSTALL NEW EIS2 SOFTWARE S9
29 JUL 11
Applicable to: ALL P1302
AUTO FLIGHT- FLIGHT MANAGEMENT SYSTEMACTIVATE NO AP DISCONNECTION BELOW MDA/MDH UNTIL MISSED APPROACH POINT
29 JUL 11
LANDING GEAR-WHEELS AND BRAKES-INSTALL BSCU STD5-
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 9/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P1312
Linked SB
Incorp. Date
Title
29 JUL 11
LIGHTS - PANEL 25VU - INTEGRALLY LIGHTED PLATE - MODIFY WORDING
29 JUL 11
ELECTRCIAL POWER - DC - IMPROVE BCL -
29 JUL 11
Applicable to: ALL P1485
NAVIGATION - ATC MODE "S" - ACTIVATE SELECTIVE INTERROGATION FUNCTION -
29 JUL 11
Applicable to: ALL P1573
ELECTRICAL POWER - DC GENERATION - REVISE "BAT OFF" INDICATION -
29 JUL 11
ENGINE CONTROLS-MODIFY POWER SUPPLY FOR HP FUEL SOLENOID
29 JUL 11
NAVIGATION - MODIFY GPWC WARNING -
29 JUL 11
Applicable to: ALL P1752
AIR CONDITIONING-AVIONICS VENTILATIONINSTALL A NRV AT AIR INLET
29 JUL 11
Applicable to: ALL P1850
HYDRAULIC POWER-MODIFY ELECTRICAL ROUTING OF GREEN LEAKAGE MEASUREMENT ELECTROVALVE CONTROL
29 JUL 11
Applicable to: ALL P1872
FLIGHT CONTROLS - ELAC/EFCS SYSTEM INTRODUCE SOFTWARE L62
29 JUL 11
Applicable to: ALL P1875
AIR CONDITIONING - INSTALL CIRCUIT BREAKER FOR REAR CARGO COMPT VALVE SUPPLY FOR EROPS -
29 JUL 11
Applicable to: ALL P1883
AIR CONDITIONING - PROVIDE EMERGENCY POWER SUPPLY FOR AFT CARGO COMPT HEATING CONTROLLER FOR EROPS -
29 JUL 11
Applicable to: ALL P1906
FLIGHT CONTROLS - FCDC - INSTALL SOFTWARE L45
29 JUL 11
ENGINE FUEL AND CONTROL - EIU/CFM INTRODUCE SOFTWARE 11
29 JUL 11
LANDING GEAR - MLG - INSTALL GOODRICH TPIS
29 JUL 11
COMMUNICATIONS - INSTALL HF1 FOR EROPS
Applicable to: ALL P1390 Applicable to: ALL P1450
Applicable to: ALL P1631 Applicable to: ALL P1669
Applicable to: ALL P1939 Applicable to: ALL P1970 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 10/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P2040
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P2196
OXYGENE - COCKPIT - INSTALL MODIFIED LP OXYGEN SUPPLY SOLENOID VALVE
29 JUL 11
Applicable to: ALL P2205
MINOR IMPROVEMENTS INTRODUCED FROM A/C 268 - AS ZONE
29 JUL 11
Applicable to: ALL P2218
FIRE PROTECTION - DETECTION - INTRODUCE MODIFIED ENGINE AND APU FIRE PANEL
29 JUL 11
Applicable to: ALL P2223
NAVIGATION - TCAS II - INTRODUCE COMPLETE PROVISIONS
29 JUL 11
Applicable to: ALL P2294
NAVIGATION - GPWS - INSTALL GPWC MARK V WITH INTERFACE WITH CFDS
29 JUL 11
ENGINE FUEL AND CONTROL - CFM 56 INTRODUCE EIU VERSION 12 AND ADDITIONAL WIRING
29 JUL 11
AUTO FLIGHT - ACTIVATE WINDSHEAR FUNCTION
29 JUL 11
Applicable to: ALL P2493
ELECTRICAL POWER - DC GENERATION INTRODUCE IMPROVED BCL
29 JUL 11
Applicable to: ALL P2546
EQUIPMENT/FURNISHINGS - COCKPIT SEATS INTRODUCE TYPE A340 SEATS
29 JUL 11
Applicable to: ALL P2547
INDICATING/RECORDING SYSTEMS - CENTRAL WARNING SYSTEM - INSTALL SDAC A320/321 STANDARD
29 JUL 11
Applicable to: ALL P2588
INDICATING RECORDING SYSTEMS - EIS - DEFINE COF A STANDARD FOR A320/A321 DMC
29 JUL 11
Applicable to: ALL P2590
EQUIPMENT/FURNISHINGS - EMERGENCY EQUIPMENT - INTRODUCE PBE DRAEGER IN THE COCKPIT
29 JUL 11
Applicable to: ALL P2814
NAVIGATION - INSTALL A BENDIX TCAS II COLLISION AVOIDANCE SYSTEM
29 JUL 11
LANDING GEAR - WHEELS AND BRAKES INTRODUCE BSCU STD 6
Applicable to: ALL P2316 Applicable to: ALL P2379
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 11/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P2960
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P2963
CERTIFICATION DOCUMENTS - GENERAL CERTIFICATION FOR TAKE-OFF WITH 15 KNOT TAILWIND
29 JUL 11
Applicable to: ALL P3004
AIR CONDITIONING - IMPROVE CABIN PRESSURIZATION CONTROL ON 25VU PANEL.
29 JUL 11
LIGHTS - COCKPIT ILLUMINATION - INTRODUCE IMPROVED COCKPIT LIGHTING
29 JUL 11
AUTO FLIGHT - FMS - PROVIDE FMS CROSS LOAD
29 JUL 11
NAVIGATION - ADIRS - ADAPT SHELVES FOR 4 MCU ADIRS INSTALLATION
29 JUL 11
AUTO FLIGHT - FCU - INTRODUCE FCU M-9 STD
29 JUL 11
Applicable to: ALL P3197
ENGINE FUEL AND CONTROL - CFM 56 - EIU INTRODUCE VERSION 13
29 JUL 11
Applicable to: ALL P3202
GENERAL - OPERATIONS FROM HIGH ALTITUDE AIRPORT (CFM ENGINES) (PRESSURE ALTITUDE LIMIT 9.200 FT)
29 JUL 11
Applicable to: ALL P3204
AUTO FLIGHT - FCU - INTRODUCE FCU STANDARD M10
29 JUL 11
Applicable to: ALL P3277
AUTO FLIGHT-FMS-INTRODUCE FMGC A320/321 B1 STD WITH OPTIONS AND 400 KILOWORDS FOR CFM 56 VERSIONS
29 JUL 11
Applicable to: ALL P3356
MINOR IMPROVEMENTS INTRODUCED FROM A/C 508 (ST2) TO A/C 521 (ST2)
29 JUL 11
Applicable to: ALL P3365
LANDING GEAR - BSCU - TWIN WHEEL - INTRODUCE A320/A321 STD 6 VERSION 60C
29 JUL 11
Applicable to: ALL P3401
ICE AND RAIN PROTECTION-ICE DETECTIONPROVIDE ICE DETECTOR ILLUMINATION
29 JUL 11
AUTO FLIGHT - FLIGHT CONTROL UNIT (FCU) DELETE "EXPEDITE" FUNCTION FROM FCU
Applicable to: ALL P3011 Applicable to: ALL P3044 Applicable to: ALL P3102 Applicable to: ALL P3105
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 12/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P3510 Applicable to: ALL P3511
Linked SB
Incorp. Date
Title
29 JUL 11
NAVIGATION - ADIRS - INTRODUCE STD P/N AC06
29 JUL 11
Applicable to: ALL P3524
AUTO FLIGHT - FAC - INSTALL TWO FACS P/N BAM 0509
29 JUL 11
Applicable to: ALL P3588
ELECTRICAL POWER - AC AUXILIARY GENERATION (APU GENERATOR) - INTRODUCE MODIFIED GENERATOR
29 JUL 11
Applicable to: ALL P3594
LANDING GEAR - A320/A321 TWIN WHEELS INTRODUCE BSCU STANDARD 7 (70B VERSION)
29 JUL 11
Applicable to: ALL P3660
INDICATING/RECORDING SYSTEMS - ELECTRICAL CLOCK - INSTALL A CLOCK SMITHS TYPE 2610
29 JUL 11
FLIGHT CONTROLS -S.E.C. SYSTEM INTRODUCE A320/A321 S.E.C STANDARD P/N BAM0508
Applicable to: ALL P3686 Applicable to: ALL P3694
29 JUL 11
AUTO FLIGHT-FAC-INTRODUCE FAC P/N BAM 510
25 NOV 11
Applicable to: ALL P3737
AUTO FLIGHT-FMGC-A320/321-FG STANDARD FOR A321 CFM CAT III
29 JUL 11
Applicable to: ALL P3756
ENGINE FUEL AND CONTROL-FUNCTIONAL INTERFACE-INTRODUCE EIU VERSION 14 ON CFM56 ENGINES
29 JUL 11
Applicable to: ALL P3790
AUTO FLIGHT - GENERAL - EXTEND CAT III B AUTOMATIC LANDING CAPABILITY (FOR CFM ENGINES)
29 JUL 11
Applicable to: ALL P3812
NAVIGATION-ADIRS-INTRODUCE 4MCU ADIRU HONEYWELL P/N C06
29 JUL 11
Applicable to: ALL P3830
PNEUMATIC-ENGINE BLEED AIR SUPPLYINTRODUCE A BLEED AIR MONITORNG COMPUTER STD6
29 JUL 11
FLIGHT CONTROLS-SEC SYSTEM-"PARTIAL LIFT DUMPING" FUNCTION ACTIVATION
29 JUL 11
FLIGHT CONTROLS-INTRODUCE ELAC STD L69J
Applicable to: ALL P3878 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 13/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P3897
N
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P3924
INDICATING RECORDING SYSTEMS-DMCINTRODUCE D.M.C. V31 STANDARD
29 JUL 11
Applicable to: ALL P3955
LANDING GEAR - MLG - MESSIER - INTRODUCE BRAKES P/N C202253
29 JUL 11
Applicable to: ALL P3964
NACELLES/PYLONS-PYLON STRUCTURE- ADAPT PRIMARY STRUCTURE TO A321-200 VERSION
29 JUL 11
Applicable to: ALL P4054
NAVIGATION-TCAS-INSTALL ATC/TCAS CONTROL PANEL SEXTANT P/N 04-AA01.
29 JUL 11
Applicable to: ALL P4055
AUTOFLIGHT-FCU-INTRODUCE F.C.U. STANDARD M11
18 SEP 12
Applicable to: ALL P4079
AUTOFLIGHT-FCU-INTRODUCE FCU STANDARD M11 WITHOUT EXPEDITE FUNCTION
29 JUL 11
Applicable to: ALL P4087
AUTO FLIGHT - FMGC - PROVIDE ACARS AND PRINTER INTERFACES IN FMS (CFM VERSION)
29 JUL 11
Applicable to: ALL P4089
NAVIGATION-ADIRS-INSTALL HONEYWELL ADIRS WITH GPS PRIMARY NAVIGATION CAPABILITY
29 JUL 11
Applicable to: ALL P4121
AUTO FLIGHT-FMGC-REDUCE VAPP FOR A320 CFM/IAE
29 JUL 11
Applicable to: ALL P4151
EXHAUST-THRUST REVERSER CONTROL AND INDICATING-ACTIVATE ADDITIONAL THRUST REVERSER LOCK CONTROL
29 JUL 11
Applicable to: ALL P4155
INDICATING/RECORDING SYSTEM - INSTALL A PORTABLE DATA LOADER CONNECTOR AND DISK STOWAGE
29 JUL 11
Applicable to: ALL P4170
AUTOFLIGHT - FMGC - ACTIVATE ACARS INTERFACE IN FMS (CFM AND IAE ENGINES)
29 JUL 11
FLIGHT CONTROLS - FCDC SYSTEM - PROVIDE A VISUAL INDICATION FOR SIMULTANEOUS SIDE STICK ACTION
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 14/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P4191
Incorp. Date
Title
29 JUL 11
NAVIGATION - GENERAL - CHANGE EQUIPMENTS TO COMPLY WITH MARCH 95 SPECS.
29 JUL 11
AUTOFLIGHT - FMGC - ACTIVATE PRINTER INTERFACE IN FMS (CFM AND IAE ENGINES)
29 JUL 11
POWER PLANT-GENERAL-INTRODUCE CFM56-5B/P
29 JUL 11
Applicable to: ALL P4281
ICE AND RAIN PROTECTION-WINDSHIELD RAIN PROTECTION-DESACTIVATION OF RAIN REPELLENT SYSTEM
29 JUL 11
Applicable to: ALL P4287
ENGINE FUEL AND CONTROL-CONTROLLINGINTRODUCE ECU SOFTWARE-STANDARD 5BE-1 FOR CFM56-5B (SAC ENGINES)
29 JUL 11
Applicable to: ALL P4319
INDICATING/RECORDING SYSTEMS - FWC DEFINE OEB REMINDER WITHIN FWC STD -E1 AND SUBSEQUENT
29 JUL 11
Applicable to: ALL P4320
AUTO FLIGHT - FCU - DEFINE FLIGHT DIRECTOR ENGAGEMENT IN CROSSED BARS AT GO AROUND
29 JUL 11
Applicable to: ALL P4378
AUTO FLIGHT-GENERAL-ACTIVATE GLOBAL SPEED PROTECTION AND F/D DISENGAGEMENT UPON SPEED CONSTRAINTS
29 JUL 11
Applicable to: ALL P4417
CERTIFICATION - GENERAL - CERTIFICATION FOR HIGH ALTITUDE AIRPORT OPERATION
29 JUL 11
Applicable to: ALL P4495
ELECTRICAL POWER-DC GENERATIONMODIFY TRANSFORMER RECTIFIER OVERHEAT PROTECTION
29 JUL 11
Applicable to: ALL P4497
INDICATING/RECORDING SYSTEMS-DISPLAY MANAGEMENT COMPUTER (DMC)-INTRODCUE DMC V32 STD
29 JUL 11
DOORS EMERGENCY ESCAPE SLIDE RELEASE & OVERPRESS. WARNING SYSTEMS-MODIFY CTRL LOGIC OF THE OVERPRESS. WARNING SYST
Applicable to: ALL P4205 Applicable to: ALL P4230 Applicable to: ALL P4234
E
Linked SB
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 15/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P4502
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P4528
INFORMATION SYSTEM - AIR TRAFFIC AND INFORMATION SYSTEM (ATIMS) - INSTALL ATSU COMPUTER FOR ACARS
29 JUL 11
Applicable to: ALL P4539
ENGINE FUEL AND CONTROL-CONTROLLING INTRODUCE ECU SOFTWARE STD5 BH FOR CFM56-5B -SAC-
29 JUL 11
Applicable to: ALL P4576
AUTOFLIGHT-FLIGHT CONTROL UNIT- (FCU) INTRODUCE SEXTANT MODULAR FCU
29 JUL 11
Applicable to: ALL P4647
LANDING GEAR-ALTERNATE BRAKING- INTRODUCE MODIFIED ALTERNATE BRAKING SYSTEM
29 JUL 11
Applicable to: ALL P4677
NAVIGATION - WEATHER RADAR SYSTEM ACTIVATE COLLINS DUAL PREDICTIVE WINDSHEAR SYSTEM
29 JUL 11
Applicable to: ALL P4707
COM-CVR-INSTALL A SOLID STATE COCKPIT VOICE RECORDER (SSCVR) LORAL FAIRCHILD P/N 200-0012-00 (SFE)
29 JUL 11
Applicable to: ALL P4709
COMMUNICATIONS - SSCVR - INSTALL SSCVR ALLIED SIGNAL P/N 980-6022-001
29 JUL 11
Applicable to: ALL P4770
ADDITIONAL CERTIFICATION ITEMS - LANDING WITH A 15 KNOT TAILWIND
29 JUL 11
Applicable to: ALL P4773
NAVIGATION-WEATHER RADAR SYSTEM- INSTALL FULL PROVISION FOR 2ND TRANSCEIVER
29 JUL 11
Applicable to: ALL P4789
NAVIGATION - ADF - INSTALL A SECOND ADF RECEIVERS
29 JUL 11
Applicable to: ALL P4801
NAVIGATION - ILS - INSTALL ADDITIONAL WIRING PROVISIONS FOR MMR INSTALLATION
29 JUL 11
Applicable to: ALL P4808
ELECTRICAL POWER-GENERAL-DEFINE NEW ELECTRICAL GENERATION CONCEPT FOR SINGLE AISLE A/C
29 JUL 11
LANDING GEAR-WHEELS AND BRAKES- INTRODUCE BSCU COMMON STD
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 16/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P4885
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P4916
NAVIGATION - GPWS - ACTIVATE ENHANCED FUNCTIONS OF THE EGPWS
29 JUL 11
Applicable to: ALL P4954
FLIGHT CONTROL -ELAC SYSTEM- INTRODUCE E.L.A.C. WITH ENHANCED RELAYS
29 JUL 11
Applicable to: ALL P4956
AUTO FLIGHT-FMGC-INTRODUCE FMGC CAM0102 FOR A319 AUTOLAND AND GPS/ACARS FOR CFM ENGINES
29 JUL 11
Applicable to: ALL P4977
FLIGHT CREW PORTABLE DEVICES - COCKPIT PROTECTIVE BREATING EQUIPMENT (PBE) PURITAN BENNETT
29 JUL 11
INDICATING/RECORDING SYSTEMS - FWC PROVIDE NEW SYNTHETIC VOICE "DUAL INPUT"
29 JUL 11
AUTO-FLIGHT-FAC INTRODUCE FAC STD BAM 0513
29 JUL 11
Applicable to: ALL P5138
ICE AND RAIN PROTECTION-WINSHIELD RAIN PROTECTION-ACTIVATION OF RAIN REPELLENT SYS.(FLUID COMPATIBLE WITH OZONE RULES)
29 JUL 11
Applicable to: ALL P5168
FLIGHT CONTROLS-ELAC SYSTEM-INTRODUCE ELAC SOFTWARE "L80"
29 JUL 11
Applicable to: ALL P5228
NAVIGATION - MMR - INSTALL COLLINS MMR PROVIDING ILS AND GPS FUNCTION
29 JUL 11
Applicable to: ALL P5239
INDICATING/RECORDING SYSTEMS-ACTIVATE THE "HI ALT SET" RIGHT MEMO FOR HIGH ALTITUDE AIRPORT OPERATION
29 JUL 11
Applicable to: ALL P5241
NAVIGATION-ATC MODE"S"-INTRODUCE ATC/TCAS CONTROL UNIT P/N C12404AB02
29 JUL 11
Applicable to: ALL P5253
NAVIGATION - WEATHER RADAR SYSTEM - INSTALL COLLINS SINGLE WEATHER RADAR WITH FULL PROVISION FOR A SECOND SYS
29 JUL 11
NAVIGATION - ADIRS - REPLACE ADIRS CDU BY MSU (MODE SELECTOR UNIT)
Applicable to: ALL P4983 Applicable to: ALL P5071
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 17/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P5314
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P5377
AUTO FLIGHT - MULTIPURPOSE CONTROL AND DISPLAY UNIT (MCDU) - INTRODUCE MCDU HONEYWELL 2ND GENERATION (P/N -980)
29 JUL 11
Applicable to: ALL P5429
INFORMATION SYSTEM-AIR TRAFFIC AND INFO MANAGEMENT SYS(ATIMS)-COCKPIT-INTRODUCE SYS PROVISIONS FOR FANS "A"(ATSU-2DCDU)
29 JUL 11
Applicable to: ALL P5451
ENGINE FUEL AND CONTROL-FADEC SYSTEMCFM56-5B-SAC-INTRODUCE ECU SOFTWARE 5BI
29 JUL 11
Applicable to: ALL P5459
ELECTRICAL POWER - GENERAL - AC-DC MAIN DISTRIBUTION - INSTALL AC-DC SHEDDABLE BUSBARS
29 JUL 11
Applicable to: ALL P5465
AIR CONDITIONING - PACK COOLING AIR CONTROL - INTRODUCE LOGIC RELAY FOR CONTROL PACK CLOSURE AT ENGINE START
29 JUL 11
Applicable to: ALL P5518
INDICATING/RECORDING SYSTEMS - ELECTRICAL CLOCK- INSTALL AIR PRECISION P/N APE5100-1 CAPABLE OF GPS TIME
29 JUL 11
Applicable to: ALL P5567
LANDING GEAR-NORMAL BRAKING- INTRODUCE STD 8 BSCU (TWIN VERSION)
29 JUL 11
Applicable to: ALL P5583
INDICATING RECORDING SYSTEM-DMCINTRODUCE DMC V40 STANDARD
29 JUL 11
Applicable to: ALL P5638
NAVIGATION - ADIRS - REDUCE VERTICAL SEPARATION MINIMUM USING ADR1 AND 2 ONLY
29 JUL 11
Applicable to: ALL P5669
NAVIGATION-STANDBY DATA : ALTITUDE AND HEADING - INSTALL INTEGRATED STANDBY INSTRUMENT SYSTEM (ISIS)
29 JUL 11
Applicable to: ALL P5685
NAVIGATION - TCAS - INSTALL ALLIED SIGNAL TCAS COMPUTER P/N 066-50000-2220 (WITH CHANGE 7.0)
29 JUL 11
COMMUNICATIONS - AUDIO MANAGEMENT SYSTEM - INSTALL SATCOM AMU AND ACP
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 18/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P5687
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P5706
COMMUNICATION-SATCOM-ACTIVATE SATCOM AERO-I COLLINS COCKPIT VOICE FUNCTION
29 JUL 11
Applicable to: ALL P5768
INDICATING RECORDING SYSTEM-FWCINTRODUCE FWC STANDARD H2/E3P
29 JUL 11
Applicable to: ALL P5895
ELEC PWR-AC EMERGENCY GENERATIONACTIVATE A319/A321 ELECTRICAL EMERGENCY CONFIGURATION ON A320 A/C
29 JUL 11
Applicable to: ALL P5905
NAVIGATION-GPWS-INTRODUCE EGPWS P/N 206-206 AND INHIBIT AUTOMATIC DEACTIVATION ENHANCED FUNCTIONS
29 JUL 11
Applicable to: ALL P6030
COMMUNICATIONS-SATELLITE COMMUNICATIONINSTALL A COLLINS AERO I SATCOM AVIONIC (6 CHANNELS)
29 JUL 11
Applicable to: ALL P6044
ELECTRICAL POWER - AC GENERATION - INSTALL ELECTRICAL OUTLETS IN COCKPIT
29 JUL 11
Applicable to: ALL P6067
ICE AND RAIN PROTECTION-WINSHIELD- RAIN PROTECTION-INTRODUCE MODIFIED GAGE ASSY -P/N 4020W35-2
29 JUL 11
Applicable to: ALL P6071
LANDING GEAR-NOSE LANDING GEAR WHEELS-REMOVE RUBBING STRIPS
29 JUL 11
Applicable to: ALL P6142
INDICATING/RECORDING SYSTEMS - DMC DISPLAY ALTITUDE IN METRIC UNITS ON THE PRIMARY FLIGHT DISPLAY (PFD)
29 JUL 11
Applicable to: ALL P6146
NAV-STANDBY DATA: ATT AND HDG-INTRODUCE COMPLETE PROV FOR INTEGRATED STANDBY INSTRUMENT SYSTEM ELECTRICAL SUPPLY
29 JUL 11
Applicable to: ALL P6201
INDICATING/RECORDING SYSTEM - FWC INTRODUCE "F/CTL FLAP LVR NOT ZERO" RED WARNING
29 JUL 11
GENERAL-FLIGHT ENVIRONMENTAL ENVELOPEEXTENSION TO 12100 M (39800 FT)
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 19/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P6251
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P6283
ICE AND RAIN PROTECTION-WINDSHIELD RAIN PROTECTION-INTRODUCE MODIFIED GAGE ASSY WITH INPUT VALUE FUNCTION SUPPRESSED
29 JUL 11
Applicable to: ALL P6314
CERTIFICATION DOCUMENTS - GENERAL - CERTIFY LANDING ON WET RUNWAY PORUS FRICTION COURSE TYPE (WITH BSCU STD 8)
29 JUL 11
Applicable to: ALL P6375
AUTO FLIGHT - DEFINE "GUIDED RADAR APPROACH WITH AUTOPILOT ENGAGED" PROCEDURE (MUH 250 FT)
29 JUL 11
Applicable to: ALL P6544
LANDING GEAR-PARKING/ULTIMATE EMERGENCY BRAKING-INTRODUCE A PRESSURE SWITCH
29 JUL 11
Applicable to: ALL P6578
INDICATING/RECORDING SYSTEMS - FWC ACTIVATE SPECIFIC FWC PROCEDURE
29 JUL 11
Applicable to: ALL P6588
INDICATING RECORDING SYSTEMS- EIS-INSTALL DMC, DU AND DISKETTES FOR EIS2
29 JUL 11
Applicable to: ALL P6589
INFORMATION SYSTEM - ATIMS - MODIFY ATSU AIRCRAFT INTERFACE SOFTWARE ACCORDING TO SERVICE PROVIDERS LIST
29 JUL 11
Applicable to: ALL P6624
INDICATING/RECORDING SYSTEMS-CFDIUINTRODUCE CFDIU STANDARD 9B
29 JUL 11
Applicable to: ALL P6630
COMMUNICATIONS - COCKPIT VOICE RECORDER - REINTRODUCE SSCVR ALLIED SIGNAL P/N 980-6022-001
29 JUL 11
Applicable to: ALL P6634
CERTIFICATION DOCUMENTS - GENERAL - CERTIFY AIRCRAFT FOR OPERATION ON RUNWAYS LESS THAN 45M WIDTH
29 JUL 11
Applicable to: ALL P6687
INDICATING RECORDING SYSTEM-SDACINTRODUCE STANDARD SDAC P/N 350E5500202
29 JUL 11
COMMUNICATIONS-RADIO MANAGEMENTINTRODUCE NEW RMP STANDARD 2A P/NO. C12848CA01
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 20/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P6688
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P6703
COMMUNICATIONS-RADIO MANAGEMENT-INSTALL A THIRD RADIO MANAGEMENT PANEL
29 JUL 11
Applicable to: ALL P6777
AUTO-FLIGHT-FLIGHT AUGMENTATION COMPUTER-INTRODUCE FAC SOFTWARE STANDARD P/N B397BAM0515
29 JUL 11
Applicable to: ALL P6801
INFORMATION SYSTEM-ATIMS- UPGRADE ATSU HARDWARE FOR NEW ARINC 429 I/O BOARD
29 JUL 11
Applicable to: ALL P6832
INDICATING/RECORDING SYSTEMS - FWC - INSTALL FWC STANDARD H2E4
29 JUL 11
Applicable to: ALL P6863
INFORMATION SYSTEMS - ATIMS - DEFINE AND INSTALL MODIFIED SOFTWARE ATSU A/C INTERFACE UPGRADED
29 JUL 11
Applicable to: ALL P6901
NAVIGATION-STANDBY DATA-ISIS-ACT ACTIVATE "V-BAR" AIRCRAFT SYMBOL IN PLACE OF "CROSS BAR"
29 JUL 11
Applicable to: ALL P6911
FLIGHT CONTROLS - ELAC SYSTEM - INTRODUCE ELAC SOFTWARE "L90"
29 JUL 11
Applicable to: ALL P6954
INDICATING/RECORDING SYSTEM : FROM FWC-F1 PIN-PROGRAMMING FOR IMPROVING THE MONITORING ABOUT THE NORMAL BRAKING SYSTEM
29 JUL 11
Applicable to: ALL P6985
AUTO-FLIGHT - FLIGHT AUGMENTATION COMPUTER (FAC) - INTRODUCE FAC SOFTWARE "BAM0616"
29 JUL 11
Applicable to: ALL P6987
NAVIGATION - ADIRS - INSTALL HONEYWELL ADIRU 4MCU P/N HG2030AE21 (A318 COEFF CFM ADDED)
29 JUL 11
Applicable to: ALL P7005
AUTO-FLIGHT-FMGC-INSTALL FMGC P/N B546CAM0103 (CFM GPS/ACARS)
29 JUL 11
LANDING GEAR - NORMAL BRAKING - INTRODUCE STD 9 BSCU (TWIN VERSION)
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 21/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P7125
INDICATING/RECORDING SYSTEM - EIS - ACTIVATE FUEL FLOW/DELTA ISA FUNCTION BY PIN PROGRAMMING ON DMC
29 JUL 11
Applicable to: ALL P7148
INDICATING RECORDING SYSTEM-FWCINTRODUCE FWC STANDARD H2 F1
29 JUL 11
Applicable to: ALL P7175
COMMUNICATIONS-HF SYSTEM-ACTIVATE DATA LINK FUNCTION FOR HFDR1
29 JUL 11
Applicable to: ALL P7186
ELECTRICAL POWER - GENERAL - INSTALL A COMMERCIAL SHEDDING PUSH-BUTTON SWITCH IN COCKPIT
29 JUL 11
Applicable to: ALL P7187
NAVIGATION-GPWS-ACTIVATE PEAKS MODE ON EGPWS IN CONJUNCTION WITH TERRAIN DISPLAY
29 JUL 11
Applicable to: ALL P7188
NAVIGATIONS-EGPWS-ACTIVATE GEOMETRIC ALTITUDE FUNCTION IN THE EGPWS
29 JUL 11
Applicable to: ALL P7247
NAVIGATION - EGPWS - ACTIVATE OBSTACLE OPTION ON THE EGPWS
29 JUL 11
Applicable to: ALL P7268
FLIGHT CONTROLS - ELAC SYSTEM - INTRODUCE ELAC STD L81
29 JUL 11
Applicable to: ALL P7278
NAVIGATION-ADIRU-RESTORE RVSM 3 CIRCUIT CAPABILITIES (SERIAL SOLUTION)
29 JUL 11
Applicable to: ALL P7360
INDICATING/RECORDING SYSTEM-EIS2- INSTALL MODIFIED EIS2 SOFTWARE
29 JUL 11
Applicable to: ALL P7371
OXYGEN - OXYGEN DISTRIBUTION - INSTALL FOURTH OXYGEN MASK EROS WITH ASSOCIATED BOX
29 JUL 11
Applicable to: ALL P7397
AUTO FLIGHT - FMGC - INSTALL FMGC CFMI P/N C13042AA02 (FMS2 HONEYWELL)
29 JUL 11
NAVIGATION-ADIRS-INTRODUCE HONEYWELL ADIRU 4 MCU P/N HG2030AE22
P7092
Linked SB
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 22/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P7407
COMMUNICATIONS-AUDIO MANAGEMENT-INSTALL ACP WITH A NEW FRONT FACE DESIGN TO COMPLY WITH"LS"FUNCTIONS(PROD.SOLUTION)
29 JUL 11
Applicable to: ALL P7455
COMMUNICATIONS - RADIO MANAGEMENT INSTALL RMP STANDARD 3 WITH MLS AND GLS FUNCTION CAPABILITY
29 JUL 11
Applicable to: ALL P7519
ELECTRICAL POWER-GENERAL-CHANGE IFE POWER SUPPLY BUSBARS INTO SHEDDABLE BUSBARS 220XP AND 212PP
29 JUL 11
Applicable to: ALL P7613
AUTOFLIGHT-FMGC-INSTALL FMGC CFM C13042AA01 (EQUIPPED WITH FMS2) HONEYWELL
29 JUL 11
Applicable to: ALL P7635
AUTO FLIGHT - FMGC - ACTIVATE MORA DISPLAY ON ND
29 JUL 11
Applicable to: ALL P7752
FLIGHT CONTROLS - ELAC SYSTEM - INTRODUCE ELAC SOFTWARE L82
29 JUL 11
Applicable to: ALL P7754
INFORMATION SYSTEMS-ATIMS-ATSU PROVIDE ATSU A/C INTERFACE SOFTWARE CSB 3.2C CAPABLE OF VDL MODE 2
29 JUL 11
Applicable to: ALL P7790
NAVIGATION - DDRMI - REPLACE THALES DDRMI P/N 63543-150-3 BY P/N 63543-150-4.
29 JUL 11
Applicable to: ALL P7919
AUTO FLIGHT - FLIGHT MANAGEMENT AND GUIDANCE SYSTEM - ACTIVATE FMA ENHANCEMENT FUNCTION
29 JUL 11
Applicable to: ALL P7929
ENGINE FUEL AND CONTROL - FADEC SYSTEM INTRODUCE NEW FADEC SOFTWARE "5BK" ON SAC CFM56-5B ENGINES
29 JUL 11
Applicable to: ALL P8069
NAVIGATION-WEATHER RADAR SYSTEM-INSTALL COLLINS DUAL CONTROL PANEL TO ACTIVATE MULTISCAN FUNCTION
29 JUL 11
ENGINE FUEL AND CONTROL - FADEC SYSTEM INSTALL "5BL" STANDARD ECU SOFTWARE FOR CFM56-5B ENGINES (A318 CAPABLE)
P7406
Linked SB
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 23/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P8076
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P8175
LANDING GEAR - NORMAL BRAKING - INSTALL BSCU STD L4.5
29 JUL 11
Applicable to: ALL P8176
INDICATING/RECORDING SYSTEMS - SDAC ACTIVATE IAS DISCREPANCY MONITORING BY PIN PROGRAMMING
29 JUL 11
Applicable to: ALL P8194
INDICATING/RECORDING SYSTEMS - SDAC ACTIVATE DUAL PITOT MONITORING BY PIN PROGRAMMING
29 JUL 11
Applicable to: ALL P8232
NAVIGATION - ADIRS ACTIVATE ALIGNMENT IMPROVEMENT FUNCTION ON ADIRU
29 JUL 11
Applicable to: ALL P8243
INDICATING/RECORDING SYSTEMS - FWC INTRODUCE IAS DISCREPANCY AND DUAL PITOT MONITORING ON FWC H2F1
29 JUL 11
Applicable to: ALL P8256
CERTIFICATION DOCUMENTS - GENERAL - EXTEND OPERATING FLIGHT ENVELOPE TO MINUS 2000FT PRESSURE ALTITUDE
29 JUL 11
Applicable to: ALL P8274
AUTO FLIGHT - FLIGHT AUGMENTATION COMPUTER - INSTALL FAC STANDARD BAM0617 FOR A318
29 JUL 11
Applicable to: ALL P8303
INDICATING RECORDING SYSTEM - FLIGHT WARNING COMPUTER (FWC) - INSTALL FWC STANDARD H2F2
29 JUL 11
Applicable to: ALL P8564
NAVIGATION - DDRMI - REMOVE DDRMI VOR/ADF/DME INDICATORS
29 JUL 11
Applicable to: ALL P8606
INDICATING/RECORDING SYSTEM - ELECTRONIC INSTRUMENT SYSTEM (EIS)- ACTIVATE ENGINE AVAIL DISPLAY
29 JUL 11
NAVIGATION-TCAS-INSTALL A NEW HONEYWELL TCAS TPA 100 CHANGE 7.0 WITH COLLINS ATC TPR901 OR HNWL TRA67A
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 24/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P8626
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P8629
NAVIGATION - STANDBY DATA: INTEGRATED STANDBY INSTRUMENT SYSTEM (ISIS) - INSTALL ISIS STANDARD VA01
29 JUL 11
Applicable to: ALL P8671
INFORMATION SYSTEMS - ATIMS - UPGRADE ATSU A/C INTERFACE SOFTWARE FOR FANS A+ CSB4.1 IMPLEMENTATION
29 JUL 11
Applicable to: ALL P8708
INDICATING/RECORDING SYSTEMS-ELECTRONIC INSTRUMENT SYSTEM(EIS)- INSTALL DISPLAY MANAGEMENT COMPUTER SOFTWARE EIS2 S4-2
29 JUL 11
Applicable to: ALL P8710
AUTO FLIGHT - FLIGHT MANAGEMENT AND GUIDANCE COMPUTER (FMGC)-INSTALL FMS2 HONEYWELL P1C11 ON A/C WITH CFMI PPS
29 JUL 11
Applicable to: ALL P8751
NAVIGATION - WEATHER RADAR SYSTEM - INSTALL COLLINS TRANSCEIVER FULLY COMPLIANT WITH MULTI-SCAN FUNCTION
29 JUL 11
Applicable to: ALL P8799
NAVIGATION - EGPWS - INSTALL EGPWC CAPABLE OF PEAKS/OBSTACLE FUNCTIONS WITH EIS1 & USING GPS LATERAL POSITION
29 JUL 11
Applicable to: ALL P8850
NAVIGATION- GPWS - USE LATERAL GPS POSITION WITH AUTOMATIC DESELECTION
29 JUL 11
Applicable to: ALL P8863
PNEUMATIC - ENGINE BLEED AIR SUPPLY SYSTEM INSTALL BMC STD 9 CAPABLE OF A318 PW
29 JUL 11
Applicable to: ALL P8866
INDICATING/RECORDING SYSTEM FWC ACQUISITION INTERFACE CONNECT FWC TO RPWS TO PREVENT DOOR OPENING WITH RESIDUAL CABIN PRESSURE
29 JUL 11
Applicable to: ALL P9038
LANDING GEAR - NORMAL BRAKING - INSTALL BSCU STD L4.8 (EM2)
29 JUL 11
AUTOFLIGHT-MULTIPURPOSE CONTROL AND DISPLAY UNIT (MCDU) - INSTALL HONEYWELL LCD MCDU
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 25/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P9107
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P9171
INDICATING/RECORDING SYSTEMS - FLIGHT WARNING COMPUTER (FWC) - INSTALL FWC STANDARD H2F3
29 JUL 11
Applicable to: ALL P9196
NAVIGATION-AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRS) - INTRODUCE AIR DATA MONITORING FUNCTION
29 JUL 11
Applicable to: ALL P9207
NAVIGATION - STANDBY DATA: INTEGRATED STANDBY INSTRUMENT SYSTEM (ISIS) - INSTALL ISIS STD WB01
29 JUL 11
Applicable to: ALL P9225
NAVIGATION - ATC/MODE S (SELECT) - CERTIFY EHS FUNCTION
29 JUL 11
Applicable to: ALL P9522
INDICATING/RECORDING SYSTEM-ELECTRONIC INSTRUMENT SYSTEM (EIS)-INSTALL DISPLAY MANAGEMENT COMPUTER SOFTWARE EIS2 S6-1
29 JUL 11
Applicable to: ALL P9552
AUTO-FLIGHT-MULTIPURPOSE CONTROL AND DISPLAY UNIT(MCDU) - ACTIVATE BACK-UP NAV FUNCTION
29 JUL 11
Applicable to: ALL P9594
ENGINE FUEL AND CONTROL - FADEC SYSTEMINSTALL "5BM" STANDARD ECU SOFTWARE FOR CFM 56-5B ENGINES
29 JUL 11
Applicable to: ALL P9655
PNEUMATIC - LEAK DETECTION - ACTIVATE PYLON LEAK DETECTION MONITORING
29 JUL 11
Applicable to: ALL P9688
LANDING GEAR - NORMAL BRAKING - INSTALL BSCU SOFTWARE STD "L4.9"
29 JUL 11
Applicable to: ALL P9824
AUTO FLIGHT - FAC - ACTIVATE TAIL STRIKE FUNCTION ON FAC 'BAM0618' BY PIN-PROGRAMMING
29 JUL 11
INDICATING/RECORDING SYSTEMS-ELECTRONIC INSTRUMENT SYSTEM(EIS)-INSTALL DISPLAY MANAGEMENT COMPUTER SOFTWARE EIS2 S7
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 26/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
MODIFICATION P9873
Linked SB
Incorp. Date
Title
29 JUL 11
Applicable to: ALL P9894
POWER PLANT - GENERAL - INTRODUCE CFM56-5BX/3 ENGINE (SAC) "TECH INSERTION PROGRAM"
29 JUL 11
Applicable to: ALL P9895
AUTO FLIGHT - FLIGHT AUGMENTATION COMPUTER - INTRODUCE TAIL STRIKE INDICATION ON PFD FOR A320 AND A321 A/C
29 JUL 11
Applicable to: ALL P9902
AUTO FLIGHT - FLIGHT AUGMENTATION COMPUTER- INTRODUCE TAIL STRIKE "PITCHPITCH" CALL-OUT FOR A320 AND A321 A/C
29 JUL 11
Applicable to: ALL P9907
NAVIGATION - WEATHER RADAR SYSTEM INSTALL COLLINS WXR MULTISCAN WRT -2100 P/N 822-1710-213
29 JUL 11
INDICATING RECORDING SYSTEM - FLIGHT WARNING COMPUTER (FWC)- INSTALL FWC STANDARD H2-F4
Applicable to: ALL (1) Evolution code : N=New, R=Revised, E=Effectivity
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 27/28 18 SEP 12
PRELIMINARY PAGES LIST OF MODIFICATIONS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PLP-LOM P 28/28 18 SEP 12
GENERAL INFORMATION
Intentionally left blank
GENERAL INFORMATION PRELIMINARY PAGES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TABLE OF CONTENTS
GEN-PLP PRELIMINARY PAGES TABLE OF CONTENTS Main FCOM Changes..............................................................................................................................................A FCOM Purpose........................................................................................................................................................ B List of Effective Sections/Subsections (LESS) - Paper Only.................................................................................. C List of Effective Operations Engineering Bulletins (LEOEB)...................................................................................D List of Effective Documentary Units (LEDU) - Paper Only..................................................................................... E List of Effective Temporary Documentary Units (LETDU) - Paper Only................................................................. F Aircraft Allocation Table (AAT) - Paper Only..........................................................................................................G List of Modifications (LOM) - Paper Only............................................................................................................... H FCOM Use and Organization................................................................................................................................... I FCOM Format and Style Information - Paper only..................................................................................................J FCOM Revisions......................................................................................................................................................K Abbreviations............................................................................................................................................................ L
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
GEN-PLP-TOC P 1/2 18 SEP 12
GENERAL INFORMATION PRELIMINARY PAGES A318/A319/A320/A321
TABLE OF CONTENTS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
GEN-PLP-TOC P 2/2 18 SEP 12
GENERAL INFORMATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
MAIN FCOM CHANGES Ident.: GEN-A-NG01223 Applicable to: ALL Ident.: GEN-A-00012867.0001001 / 22 MAY 12
INTRODUCTION PURPOSE The purpose of the MAIN FCOM CHANGES section is to provide operators with general information about the most significant changes that are introduced in the current revision of the manual. The information provided in this section is the same for all Operators, and is not customized. In addition to this section, every revised Documentary Unit (DU) has a revision highlight (HL) that: ‐ Indicates the change(s) made to the DU ‐ Can be found in the associated “Preliminary Pages – Summary of Highlights” subchapter. In addition to this section, the Modification Operational Impact (MOI) documents available on AirbusWorld web site (Flight Operations community) provide the operation impact linked to a MOD number. Ident.: GEN-A-00014467.0001001 / 22 MAY 12
MAY 2012 IN-FLIGHT LANDING DISTANCES AIRBUS introduces a new reference for In-Flight Landing Distances assessment, both with and without in-flight failures, to replace the former Actual Landing Distances. AIRBUS modified the FCTM to reflect this new reference. AIRBUS provides detailed information, as well as training packages that explain the concepts and their implementation, on AirbusWorld in the "Safety & Operational Materials" section of the "Flight Operations Community" menu. ILLUSTRATIONS ENHANCEMENTS Many illustrations are revised without technical change. The objective is to address format standardization and enhance readability. TABLE OF CONTENTS PRO-ABN SECTION Procedures are classified in alphabetical order to ease their access from the table of contents.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
GEN P 1/34 18 SEP 12
GENERAL INFORMATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
COVERAGE OF NEW FMS SPECIFICITIES The PRO-SUP-22-20 "FMS Specificities" section of the FCOM gives the description of the following three FMS Specificities and their associated operational recommendations. 1. Undue reversion to V/S mode during climb and descent. This is applicable to all FMS Honeywell. 2. VOR/DME and VOR/TACAN not automatically tuned. This is applicable to the FMS2 Honeywell Release 1A H2 standard. 3. Erroneous lateral guidance in NAV mode during procedures that use not collocated NAVAIDs. This is applicable to all FMS Thales. REV MAX SELECTION The landing normal procedure allows the flight crews to maintain REV IDLE if the runway is dry and the aircraft performance permits. For any other case, AIRBUS recommends REV MAX selection on all thrust levers. Ident.: GEN-A-00014050.0001001 / 24 NOV 11
NOVEMBER 2011 CHANGE OF PRO-SPO-40 EXTENDED RANGE OPERATIONS FCOM section PRO-SPO-40 Extended Range Operations has been updated, in reference with FAR 121.646 and EU-OPS1 (AMC 20-6 rev.2), and for which the operators must be in compliance with. The new requirements amend essentially ETOPS weather minima, ETOPS threshold definition that corresponds now to a 60 min diversion distance and ETOPS fuel reserves. Concerning the fuel reserves, the new regulations impact mainly: ‐ the weather contingency taking into account the wind errors, ‐ the icing protection during 100% of the forecasted icing time, which is the most penalizing scenario, ‐ the go-around and second approach that are no longer considered. As a consequence the sections of PRO-SPO-40 Extended Range Operations have changed as follows: ‐ 10 General ‐ 20 Operational Limitations ‐ 30 Dispatch Consideration ‐ 40 Diversion During Extended Range Operations ‐ 50 Procedures ‐ 60 Performance
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
GEN P 2/34 18 SEP 12
GENERAL INFORMATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
For additional information, it is possible to download a slide show which was presented during session 6 of the “17th Performance and Operations conference” held in 2011 in Dubai, from the Flight Operations community at www.airbusworld.com. FUEL PENALTY FACTORS Following an in-flight failure, it is essential for the flight crew to understand and have a clear view of all the operational consequences generated by this failure. In particular, when the failure has an impact on the fuel consumption the flight crew should have the means to estimate this impact. This is the purpose of the new Fuel Penalty Factor tables introduced in the QRH-FPE In-Flight Performance. These Fuel Penalty Factors are given as a guideline in order to increase the crew awareness on the consequences of such failures and to help the decision making. On the other hand, the information is now grouped together in one part of the operational documentation (easier access), takes into account more operational cases (multiple failures, dispatch under MMEL) and the associated procedure is more formalized. It actually ensures a standardized and common treatment of all failures impacting the fuel consumption, by giving the same level of information to all flight crew. CHAPTER MOVED DSC ATA 56 (Windows) is moved to DSC ATA 25-40 (Equipment). REMOVAL OF FLIGHT CREW BULLETINS FROM THE FCOM Subsequent to suggestions received from numerous Airbus Operators, Airbus has decided to remove all Flight Crew Bulletins from the FCOM. The information in these Bulletins will either be deleted when the information becomes useless, or incorporated in one or more of the following documents, if and as applicable: ‐ In the Flight Crew Training Manual (FCTM), and/or ‐ In a relevant and already-existent section of the Flight Crew Operating Manual (FCOM), and/or ‐ In a technical “WISE” article, published on the new “World In Service Experience Knowledge Management (WISE KM)” page of the AirbusWorld website. The removal of all Flight Crew Bulletins, and the corresponding update of above-listed documents (as applicable), will be progressive. Therefore, as a first step, the following Bulletins are deleted: “Carbon Brakes Wear”, “Cabin Fans”, "Avoid Disorder in the Cockpit", "Stowage of Third Occupant Seat" and "Erroneous Airspeed/Altitude Indications". REMOVAL OF FCOM REFERENCES FROM THE QRH The Airbus aircraft are designed to be safely operated with the ECAM and QRH only. The FCOM provides only supplementary information on top of the ECAM and QRH. The FCOM
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
GEN P 3/34 18 SEP 12
GENERAL INFORMATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
references in the QRH do not contain significant information needed for the continuation of the flight, but may contain information that is useful from an operational point of view. Therefore, Airbus decided to review the QRH in order to: ‐ Introduce in the QRH the FCOM information, when useful for operations, ‐ Otherwise, remove the FCOM references. Ident.: GEN-A-00014071.0001001 / 01 SEP 11
AUGUST 2011 OEB IDENTIFICATIONS Following the entry into service of the new digital FCOM/QRH, the OEB/OEBPROC identifications were changed. The Cross Reference Table (CRT), that provides the link between former and new OEB/OEBPROC identifications, is included in the description of the List of Effective Operations Engineering Bulletins (LEOEB).Refer to GEN List of Effective Operations Engineering Bulletins (LEOEB) Ident.: GEN-A-00013970.0001001 / 07 JUL 11
JULY 2011 CHANGE OF SOP STRUCTURE LINKED TO PRECISION APPROACH The name of the Standard Operating Procedure section "18 ILS Approach" is changed into "18 Precision Approach" in order to deal with all Precision Approaches in the same section: ILS, GLS (if installed), MLS (if installed). As a consequence the following sections (if installed) are deleted : ‐ PRO Procedures / NOR Normal Procedures / SOP Standard Operating Procedures / 18A MLS Approach ‐ PRO Procedures / NOR Normal Procedures / SOP Standard Operating Procedures / 18B GLS Approach The Standard Operating Procedure section "21 Precision Approach" has been deleted. The content of this section (a link to the section SRP System Related Procedures/ 01 FMS/ 70 Approach) is part of the section "18 Precision Approach" (previous "18 ILS Approach"). As a consequence the number of the SOP sections after the removed section is changed as follows: ‐ PRO Procedures / NOR Normal Procedures / SOP Standard Operating Procedures / 21 Landing ‐ PRO Procedures / NOR Normal Procedures / SOP Standard Operating Procedures / 22 Go-Around ‐ PRO Procedures / NOR Normal Procedures / SOP Standard Operating Procedures / 23 After Landing 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
GEN P 4/34 18 SEP 12
GENERAL INFORMATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
‐ PRO Procedures / NOR Normal Procedures / SOP Standard Operating Procedures / 24 Parking ‐ PRO Procedures / NOR Normal Procedures / SOP Standard Operating Procedures / 25 Securing the Aircraft Ident.: GEN-A-00013816.0001001 / 29 MAR 11
FIRST RELEASE WEATHER RADAR The information related to the use of the weather radar is removed from the FCOM/Procedures/Supplementary Procedures/34 Navigation as: ‐ This information is already provided in the FCTM/Supplementary Information/Use of Radar ‐ This information is training related. DELETION OF THE "FPA CORRECTION CHART FOR COLD WEATHER" Last winter, Airbus published on customer request the “FPA correction chart for cold weather operations” in FCOM 3.05.05 page 7. This table provided a FPA to be set on the FCU when flying in vertical selected mode FPA, depending on: ‐ The deviation from ISA conditions and ‐ The FPA published in the approach chart. However, based on customer’s feedback, Airbus concluded that there was no satisfactory solution to provide accurate FPA correction that would apply for all different cases. This is because the altitude at which the final descent starts is not known. This altitude is indeed variable: it depends not only on Airport Temperature, but also on ATC clearance and local regulations. As a result, in all cases, the flight crew will need to fine tune the FPA during descent, based on the usual checks “Altitude (corrected in temperature) versus Distance”. Therefore, Airbus decided to describe the ADIRS behaviour with regards to FPA computation in cold weather in the FCTM but to remove the FPA correction table from the FCOM. Note:
The FCOM sections concerned are: ‐ PER Performance / OPD Operating Data / GEN General (former 3.05.05) ‐ PRO Procedures / NOR Normal Procedures / SOP Standard Operating Procedures / 19 Non Precision Approach / A.Introduction (former 3.03.19)
COCKPIT WINDSHIELD / WINDOW CRACKED FCOM PRO-ABN part The previous COCKPIT WINDSHIELD / WINDOW CRACKED procedure required to systematically descent to FL 230 for any crack. The intent was to not ask the flight crew to determine if the cracked windshield/window is still capable to sustain the difference of
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
GEN P 5/34 18 SEP 12
GENERAL INFORMATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
pressure between outside and inside. However this procedure led to descents and diversions that could have been avoided depending on the crack location. Therefore the COCKPIT WINDSHIELD / WINDOW CRACKED procedure is changed. It now requires checking the condition of the inner ply by touching the crack: ‐ If the inner ply is not damaged, the flight may be continued at the intended flight level, as the inner ply is capable to sustain the differential pressure at maximum flight level. ‐ If the inner ply is cracked, the flight must be limited to FL 230 as the flight crew cannot determine how many structural plies are affected. FCOM DSC part A descriptive of the cockpit windshield / Window is introduced to explain the cockpit windshield/window structure and fail safe concept. UNRELIABLE SPEED INDICATION Airbus conducted an internal review of the Unreliable Speed Indication (USI) procedure based on several operators’ feedback. Taking into account the training aspects and the procedure handling, Airbus decided to modify the USI procedure for aircraft equipped with Back-Up Speed Scale (BUSS). The main modification consists in providing operators with the tables for initial level-off when the aircraft is below FL 250. As a consequence the layout of the procedure has been modified: The flight crew does not any longer refer to two different procedures if above or below FL 250. However, FL 250 is kept as a reference after the affected ADR(s) identification: If the affected ADR(s) cannot be identified or if all ADRs are affected: ‐ Above FL 250, the flight crew must keep one ADR to ON and fly the pitch and thrust tables. ‐ Below FL 250, the flight crew must switch off all the ADRs in order to activate the BUSS function. With this modification, the Unreliable Speed Indication procedure for aircraft equipped with BUSS is similar to the procedure for aircraft that do not have the BUSS function. The subject modification eases the handling of the procedure for operators that have mixed-fleet (aircraft with BUSS function and aircraft without BUSS function). The modification of the Unreliable Speed Indication for aircraft equipped with the BUSS will be addressed at the 2011 Dubai Performance and Operational conference. The Flight Crew Training Manual (FCTM) provides information and recommendations associated to the use of the BUSS function.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
GEN P 6/34 18 SEP 12
GENERAL INFORMATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FCOM PURPOSE Ident.: GEN-00012627.0001001 / 23 MAR 11 Applicable to: ALL
FCOM PURPOSE The Flight Crew Operating Manual (FCOM) is the support documentation for flight crews. It provides them with the necessary information about the operational, technical, procedural, and performance characteristics of the Single Aisle aircraft family, to ensure safe and efficient operations of the aircraft during normal and abnormal/emergency situations, that may occur on ground, or in flight. The manual is not designed to provide basic jet aircraft piloting techniques, or information, that are considered as basic airmanship for trained flight crews that are familiar with that type of aircraft and with its general handling characteristics. The FCOM is intended to be used: ‐ Directly as flight crew operating manual or to provide operators with a basis for their development of a customized airline operations manual, in accordance with applicable requirements ‐ As a comprehensive reference guide during initial and refresher flight crew training. Practical and training-oriented information is addressed in the Flight Crew Training Manual (FCTM).Refer to FCTM/OP-10 Introduction . Moreover, the FCOM is not intended to be used for teaching basic piloting skills. The Flight Crew Operating Manua complements the approved Airplane Flight Manual (AFM). If the data contained in this manual differs from the data in the AFM, the AFM remains the reference. Airbus encourages all manual holders and users to submit any FCOM question and suggestion to: E.MAIL: [email protected] AIRBUS S.A.S. FLIGHT OPERATIONS SUPPORT AND SERVICES 1 ROND-POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX, FRANCE Fax: +33 5 61 93 29 68
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
GEN P 7/34 18 SEP 12
GENERAL INFORMATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FCOM CONTENTS The contents of the FCOM are organized in the following six parts: ‐ System Descriptions (DSC, organized by ATA) ‐ Procedures PRO ABN : Abnormal/Emergency PRO NOR SOP : Normal PRO NOR SRP : System Related PRO SPO : Special Operations PRO SUP : Supplementary ‐ Limitations (LIM) ‐ Performance (PER, organized by phase of flight) ‐ Operations Engineering Bulletins (OEB) ‐ Flight Crew Bulletins (FCB). DOCUMENTARY UNITS The FCOM is made of Documentary Units (DU). The DU is the smallest part of information with a technical content. The DUs are listed on a separate "List of Effective Documentary Units" (LEDU). Refer to the General section. Note:
1. DUs can be grouped into Group of DU (GDU) 2. Temporary information may be provided via Temporary DU (TDU).
IDENTIFICATION STRIP Below the title of the DU, the identification strip provides: ‐ The list of MSN the DU is applicable to ‐ For TDU, the reference to the DU impacted by the TDU. LIST OF EFFECTIVE SECTIONS/SUBSECTIONS (LESS) - PAPER ONLY Ident.: GEN-00013786.0001001 / 23 MAR 11 Applicable to: ALL
The List of Effective Sections/Subsections (LESS) summarizes all the sections and subsections contained in the FCOM. For each revision, a new LESS is issued when at least one DU of the section/subsection is changed.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
GEN P 8/34 18 SEP 12
GENERAL INFORMATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
The LESS consists of: ‐ The "M" field that may provide the following evolution code: • • • •
The "N" letter indicates a new section introduced by the revision The "R" letter indicates a section in which the content has been revised The "E" letter indicates an aircraft validity change within the section The "M” letter indicates a section that have move within the FCOM
‐ The “Localization” field that allows localizing the section within the manual with the product structure ‐ The “Subsection title” field ‐ The “Rev. Date” field that indicated the date at which the section was changed. LIST OF EFFECTIVE OPERATIONS ENGINEERING BULLETINS (LEOEB) Ident.: GEN-00013787.0001001 / 23 NOV 11 Applicable to: ALL
Refer to OEB-GEN Cross Reference Between the Former and New OEB Identifications LIST OF EFFECTIVE DOCUMENTARY UNITS (LEDU) - PAPER ONLY Ident.: GEN-00013789.0001001 / 23 MAR 11 Applicable to: ALL
For each revision, a new List of Effective Documentary Units (LEDU) is issued at the section level. The LEDU provides information about the DU localization, applicability, identification and issue date. The LEDU consists of: ‐ The "M" field that may provide the following Evolution Code: • The "N" letter indicates a new DU introduced by the revision • The "R" letter indicates a revised DU: The content of the DU is updated by the revision. A vertical line in the margin of the DU locates the modified part • The "E" letter indicates an aircraft validity change for the DU: The list of MSNs for which the DU is effective has been changed compared to the previous LEDU, by addition or deletion of one or several MSN ‐ The “Localization” field that allows localizing the DU in the manual with the product structure of the manual ‐ The "T" field (Temporary Information) that contains a cross if the associated DU is a TDU ‐ The "DU title" that provides the title of the DU ‐ The “DU identification” that identifies the DU with its own unique identification number or the GDU with its own unique code. ‐ The “DU date” that indicates when the DU has been released 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← C to E →
GEN P 9/34 18 SEP 12
GENERAL INFORMATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
‐ The DU criteria which lists the technical or operational criteria for which the DU and solution is applicable to. ‐ The “Applicable to” which provides the list of aircraft this DU and solution is applicable to ‐ The “Impacted by TDU” which is the identification of the TDU superseding the DU LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS (LETDU) - PAPER ONLY Ident.: GEN-00013803.0001001 / 29 MAR 11 Applicable to: ALL
The List of Effective Temporary Documentary Units (LETDU) provides a summary of the Temporary DU impacting the section. The LETDU consists of: ‐ The "M" field that may provide the following Evolution Code: • The "N" letter indicates a new TDU introduced by the revision • The "R" letter indicates a revised TDU: The content of the TDU is updated by the revision. A vertical line in the margin of the TDU locates the modified part • The "E" letter indicates an aircraft validity change for the TDU: The list of MSNs the TDU is applicable to has been changed compared to the previous LETDU, by addition or deletion of one or several MSN ‐ The “Localization” field that allows localizing the TDU in the manual with the product structure of the manual ‐ The “TDU Title” that provides the title of the TDU ‐ The “TDU identification” that identifies the TDU with its identification number with its own unique code ‐ The “TDU date” that indicates when the TDU has been released ‐ The TDU criteria which lists the technical or operational criteria, the it is applicable to ‐ The “Applicable to” which provides the list of aircraft this TDU is applicable to ‐ The “Impacted DU” which is the Identification of DU superseded by the TDU ‐ The “Reason for issue” of the TDU Note:
1. TDU is displayed on a yellow background 2. within the QRH the TDU replaces the impacted DU AIRCRAFT ALLOCATION TABLE (AAT) - PAPER ONLY
Ident.: GEN-00013804.0001001 / 23 MAR 11 Applicable to: ALL
The Aircraft Allocation Table (AAT) provides a view of the fleet covered in the FCOM. For each aircraft, the AAT provides its MSN, its registration number and the model.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← E to G
GEN P 10/34 18 SEP 12
GENERAL INFORMATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
LIST OF MODIFICATIONS (LOM) - PAPER ONLY Ident.: GEN-00013805.0001001 / 25 MAR 11 Applicable to: ALL
The List of Modifications (LOM) lists the criteria (Modification Proposal (MP) or Service Bulletins (SB)) which the installation on the aircraft affects the FCOM. Note:
Each MP has one or more associated MODs. The MP/MOD correlation is available in AirN@v / Engineering.
The LOM also indicates: ‐ The title of the criteria ‐ The date of incorporation of the criteria in the FCOM ‐ The list of aircraft that have the criteria ‐ The "M" field that may indicate the following evolution code ‐ The "E" letter indicates an aircraft validity change of the criteria. The list of aircraft to which the criteria applies has changed compared to the previous FCOM revision, by addition or deletion of one or several aircraft. ‐ The "N" letter indicates new criteria added by this FCOM revision ‐ The "R" letter indicates a change in the criteria title or associated SB FCOM USE AND ORGANIZATION Ident.: GEN-00012688.0001001 / 23 MAR 11 Applicable to: ALL
DEFINITIONS OF WARNINGS, CAUTIONS AND NOTES The following are the official definitions of warnings, cautions and notes taken directly from the JAR25/CS-25 and applicable to Airbus flight operation documentation: WARNING An operating procedure, technique, etc. that may result in personal injury or loss of life if not followed. CAUTION An operating procedure, technique, etc. that may result in damage to equipment if not followed. NOTE An operating procedure, technique, etc. considered essential to emphasize. Information contained in notes may also be safety related.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
H to I →
GEN P 11/34 18 SEP 12
GENERAL INFORMATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
INFORMATION TYPE AND LAYERS The FCOM has technical information that may be used for: ‐ Flight crew operations in flight, or on ground ‐ Airlines operations on ground ‐ Training. To take the above-noted objectives into account, the FCOM is organized in three layers as follows: ‐ Layer 1: "Need to know" Layer 1 presents information that is necessary in the cockpit. ‐ Layer 2: "Nice to know" Layer 2 presents information that is used as a reference, in order to fully understand the logic of the aircraft and pilot interfaces. ‐ Layer 3: Detailed information Layer 3 provides more detailed explanations, that are not necessarily needed in flight. Note:
For paper only, the following examples show the visual characteristics of each kind of layer
EXAMPLE
L2
EXAMPLE
L3
EXAMPLE
L1
EXAMPLE
‐ Text in layer 1 Layer 1 is the default layer. No symbology when not following layer 2 or layer 3 information. ‐ Text in layer 2 ‐ Text in layer 3 ‐ Text in layer 1 (as this text follows a text in layer 2 or 3, symbology "L1")
OPTIONAL EQUIPMENT The legend (if installed) indicates that a paragraph or a schematic is applicable only if the related equipment is installed. FCOM FORMAT AND STYLE INFORMATION - PAPER ONLY Ident.: GEN-00013793.0001001 / 29 MAR 11 Applicable to: ALL
TABLE OF CONTENTS Each TOC entry has an alphabetical index that identifies this TOC entry within its subsection. The manual user can easily find a TOC entry content within the manual thanks to this alphabetical 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← I to J →
GEN P 12/34 18 SEP 12
GENERAL INFORMATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
index and the subsection identification. Both are indicated in the TOC and both cross-refer to the paper page footer (see the TOC indexing part below).
HEADER AND FOOTER
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←J→
GEN P 13/34 18 SEP 12
GENERAL INFORMATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
1. Airline logo 2. Aircraft types and manual 3. Level 2 chapter (PSL level 2 : GEN, DSC, PRO, LIM, OEB, FCB, PER) 4. Level 3 chapter 5. Level 4 chapter 6. Revision mark 7. Key product (document identification and aircraft designation) 8. Key product (manual code) 9. Page index 10. Last evolution date 11. Identification strip (list of impacted aircraft) 12. PSL path REVISION MARK In the paper format, a vertical bar in the margin of the DU identifies the modified part. Each vertical bar has a numerical index that refers to the associated reason of the change in the Summary of Highlight. This Summary of Highlight lists all the changes and associated reasons of the change (if necessary) that the revision has introduced. TOC INDEXING In the paper page footer, the TOC indexing is of the following type: A : The paper page contains the whole "A" TOC entry content A to B : The paper page contains the whole "A" and "B" TOC entries contents A→ : The "A" TOC entry content starts on this paper page and continues on the following paper page ←A : The "A" TOC entry content starts on a previous paper page and finishes on this paper page ←A→ : The "A" TOC entry content starts on a previous paper page and continues on the following paper page A to C→ : The paper page contains the whole "A" and "B" TOC entries contents but the "C" TOC entry content starts on this paper page and continues on the following paper page ← A to C : The paper page contains the whole "B" and "C" TOC entries contents but the "A" TOC entry content starts on a previous paper page and finishes on this paper page ← A to C → : The paper page contains the whole "B" TOC entry content but the "A" TOC entry content starts on a previous paper page and finishes on this paper page and the "C" TOC entry content starts on this paper page and continues on the following paper page 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←J→
GEN P 14/34 18 SEP 12
GENERAL INFORMATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Note:
1. The indexes follow the alphabetical order: A, B, C, ..., Z, AA, AB, AC, ..., AZ, BA, BB, BC, ... 2. For each subsection, the index starts again from A. 3. When a TOC entry content continues on the following paper page, the text "Continued on the following page" is also indicated. FCOM REVISIONS
Ident.: GEN-00012634.0001001 / 18 MAR 11 Applicable to: ALL
FCOM REVISION FCOM revisions are issued to add, update, or revise information. The Operator determines the revision periodicity. When necessary, a revision may be issued in between the defined periodicity (e.g. need for urgent update). A vertical bar appears to the left of all revised parts of the manual. TEMPORARY INFORMATION Some FCOM sections may need a temporary update (e.g. to explain a system behavior that will be modified by a future standard). In such cases, the applicable FCOM section is updated with a Temporary Documentary Unit (TDU). Information contained in the TDU is highlighted in the manual and the initial content of the FCOM remains available for consultation and comparison and is highlighted (identification strip) as being impacted by the TDU. A List of Effective Documentary Units (LEDU) is provided in the FCOM OPERATING ENGINEERING BULLETINS Operations Engineering Bulletins (OEB) are issued, when it is necessary, to rapidly transmit technical and procedural information. The OEB chapter provides a list of all applicable OEBs. FLIGHT CREW BULLETINS Flight Crew Bulletins (FCB) are issued, when it is necessary, to transmit complementary technical or operational information. The FCB chapter provides a list of all applicable FCBs.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← J to K
GEN P 15/34 18 SEP 12
GENERAL INFORMATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ABBREVIATIONS Ident.: GEN-00012598.0001001 / 20 AUG 12 Applicable to: ALL
A Abbreviation A>B A≥B A 1 750 ft/min (resets at 1 650 ft/min).
(4)
ΔP PSI (cabin differential pressure) The analog and digital presentations appear in green when ΔP is in the normal range. They appear in amber when ΔP ≤ –0.4 PSI or ≥ 8.5 PSI. The digital presentation pulses if Δp > 1.5 PSI (resets at 1 PSI) during flight phase 7. (Refer to DSC-21-20-50 Warnings and Cautions).
(5)
CAB ALT FT (cabin altitude) The analog and digital presentations appear in green, in normal range. They appear in red if the cabin altitude goes above 9 550 ft. The digital presentation pulses if the cabin altitude is at or above 8 800 ft (resets at 8 600 ft).
(6)
Active system indication (SYS 1 or SYS 2 or MAN) SYS 1 or SYS 2 appears in green when active and in amber when faulty. When either system is inactive, its title does not appear. MAN appears in green when the MODE SEL switch is in MAN.
(7)
Safety valve position SAFETY appears in white and the diagram in green when both safety valves are fully closed. SAFETY and the diagram appear in amber when either valve is not closed. Note:
(8)
The safety valve opens when the cabin differential pressure is between 8.2 and 8.9 PSI. The range is due to the reduced accuracy of ΔP measurements (in MAN mode), combined with the decrease in cabin differential pressure that occurs immediately after the safety valves open.
Outflow valve position The diagram is green when the valve is operating normally. The diagram becomes amber when the valve opens more than 95 % during flight.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-21-20-40 P 4/6 25 NOV 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRESSURIZATION - CONTROLS AND INDICATORS
ECAM CRUISE PAGE Ident.: DSC-21-20-40-00000336.0002001 / 14 NOV 11 Applicable to: ALL
(1)
LDG ELEV AUTO/MAN Identifical to the CAB PRESS page
(2)
CAB V/S FT/MIN (cabin vertical speed) Green, in normal range. Pulses, when the V/S > 1 750 ft/min (resets at 1 650 ft/min).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C→
DSC-21-20-40 P 5/6 25 NOV 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRESSURIZATION - CONTROLS AND INDICATORS
(3)
CAB ALT FT (cabin altitude) Green, in normal range. Red, for excessive cabin altitude : ≥ 9 550 ft. Pulses for cabin altitude at, or above, 8 800 ft (resets at 8 600 ft).
(4)
ΔP indication It is normally green. Pulses green when CAB ΔP ≥ 1.5 PSI before landing. It becomes amber, when out of normal range Δp ≤ -0.4 PSI or ≥ 8.5 PSI. ECAM DOOR PAGE
Ident.: DSC-21-20-40-00000337.0003001 / 09 FEB 11 Applicable to: ALL
(1)
V/S (cabin vertical speed) This number only appears during flight phases 5, 6 and 7. (Refer to DSC-21-20-50 Warnings and Cautions for flight phase definitions). ‐ It is normally green. ‐ It pulses, when the V/S is greater than 1 750 ft/min and stops pulsing, when less than 1 650 ft/min. ‐ It becomes amber, when the V/S is greater than 2 000 ft/min, or less than -2 000 ft/min.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← C to D
DSC-21-20-40 P 6/6 25 NOV 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
PRESSURIZATION - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS
1 Ident.: DSC-21-20-50-00000338.0002001 / 14 NOV 11
Applicable to: ALL
E/WD : FAILURE TITLE conditions
EXCESS CAB ALT
AURAL WARNING
MASTER LIGHT
SD PAGE CALLED
LOCAL WARNING
FLT PHASE INHIB
CRC
MASTER WARN
CAB PRESS
NIL
2, 3, 4, 5, 7, 8, 9, 10
MODE SEL FAULT lt
4, 5, 7, 8
Cabin altitude exceeds : ‐ In CLB and DES the higher of : 9 550 ft or landing field elevation plus 1 000 ft ‐ In CRZ 9 550 ft
SYS 1 + 2 FAULT
Both pressure controllers fail.
LO DIFF PR
Time to reach ΔP = 0 < 1.5 min, and time to reach ΔP = 0 ≤ (time for cab alt to reach landing elevation) +30 s and aircraft is at least 3 000 ft above landing field. Note:
The warning is maintained, when the aircraft descends below 3 000 ft above landing field.
2, 3, 4, 5, 7, 8, 9, 10 SINGLE CHIME
MASTER CAUT
OUTFLOW VALVE NOT OPEN
NIL
Valve not fully open on ground (time delay 3 min)
SAFETY VALVE OPEN LDG ELEV FAULT
3, 4, 5, 7, 8, 9, 10
No FMGS LDG ELEV data is available. Pressure controller fault.
3, 4, 5, 6, 7, 8 4, 5, 7, 8, 9, 10
Either safety valve not fully closed on ground or not fully closed for more than 1 min in flight.
SYS 1 (or 2) FAULT
CAB PRESS
NIL
NIL
3, 4, 5, 7, 8
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-21-20-50 P 1/2 18 SEP 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRESSURIZATION - WARNINGS AND CAUTIONS
MEMO DISPLAY The “MAN LDG ELEV” message is displayed in green, if the LDG ELEV knob is not in the AUTO position.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-21-20-50 P 2/2 18 SEP 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
PRESSURIZATION - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-21-20-60-00000339.0001001 / 09 DEC 09 Applicable to: ALL
NORM AC PRESS
CAB PRESS CONT
1 2 MANUAL CTL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DC
AC ESS
EMER ELEC DC ESS X
HOT
DC2 DC BAT
A
DSC-21-20-60 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
PRESSURIZATION - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-21-20-60 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
VENTILATION - GENERAL
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-21-30-10-00000340.0002001 / 24 FEB 11 Applicable to: ALL
The ventilation system includes ventilation for: ‐ The avionics, controlled by the avionics equipment ventilation controller (AEVC), ‐ The battery, ‐ The lavatories and galleys. Note:
For more information about cargo ventilation, Refer to DSC-21-40-10 General
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-21-30-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
VENTILATION - GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-21-30-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
VENTILATION - AVIONICS VENTILATION
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-21-30-20-00000341.0001001 / 24 FEB 11 Applicable to: ALL
The avionics ventilation system is fully automatic. It cools the electrical and electronic components in the avionics compartment and on the flight deck, including the instrument and circuit breaker panels. It uses two electric fans to force the circulation of cooling air. Whatever the configuration of the avionics ventilation system is, a part of the avionics ventilation air is sucked from the cockpit through the different cockpit panels. MAIN COMPONENTS Ident.: DSC-21-30-20-00000342.0001001 / 09 DEC 09 Applicable to: ALL
FANS Two electric fans operate continuously, as long as the aircraft’s electrical system is supplied. They make the air circulate around the avionics equipment. SKIN AIR INLET AND EXTRACT VALVES These valves admit air from outside the aircraft and evacuate hot air from the avionics equipment. SKIN EXCHANGE INLET AND OUTLET BYPASS VALVES These valves enable air to circulate between the avionics bay and the space under the cargo compartment floor. AIR CONDITIONING INLET VALVE This valve opens to enable the air conditioning circuit to supply fresh air to the avionics bay. SKIN EXCHANGE ISOLATION VALVE This valve connects or isolates the skin heat exchanger. AVIONICS EQUIPMENT VENTILATION COMPUTER (AEVC) The AEVC controls the operation of all fans and valves in the avionics ventilation system. NORMAL OPERATION, OPEN-CIRCUIT CONFIGURATION Ident.: DSC-21-30-20-00000343.0001001 / 24 FEB 11 Applicable to: ALL
GROUND OPERATIONS The open-circuit configuration operates when skin temperature is above the on-ground threshold. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to C →
DSC-21-30-20 P 1/8 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
VENTILATION - AVIONICS VENTILATION
FLIGHT CREW OPERATING MANUAL
On-ground threshold =
+12 °C (53 °F), temperature increasing, or +9 °C (48 °F), temperature decreasing.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C
DSC-21-30-20 P 2/8 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
VENTILATION - AVIONICS VENTILATION
NORMAL OPERATION, CLOSE-CIRCUIT CONFIGURATION Ident.: DSC-21-30-20-00000345.0001001 / 24 FEB 11 Applicable to: ALL
FLIGHT OPERATIONS The close-circuit configuration operates when skin temperature is beneath the in-flight threshold. In flight threshold = +35 °C (95 °F), temperature increasing, or +32 °C (90 °F), temperature decreasing. GROUND OPERATIONS The close-circuit configuration operates when skin temperature is beneath the on-ground threshold. On ground threshold = +12 °C (53 °F), temperature increasing, or +9 °C (48 °F), temperature decreasing.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D→
DSC-21-30-20 P 3/8 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
VENTILATION - AVIONICS VENTILATION
NORMAL OPERATION, INTERMEDIATE CONFIGURATION Ident.: DSC-21-30-20-00000344.0001001 / 11 MAY 12 Applicable to: ALL
FLIGHT OPERATIONS The intermediate configuration operates when skin temperature is above the in-flight threshold. In flight threshold = +35 °C (95 °F), temperature increasing, or +32 °C (90 °F), temperature decreasing.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← D to E →
DSC-21-30-20 P 4/8 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Note:
VENTILATION - AVIONICS VENTILATION
The measuring range of the skin temperature sensed is between -50 °C and 80 °C. Outside of this range, the AEVC sets the avionics ventilation configuration to the intermediate configuration (partially open) until the temperature is within the operation range again.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E
DSC-21-30-20 P 5/8 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
VENTILATION - AVIONICS VENTILATION
FLIGHT CREW OPERATING MANUAL
ABNORMAL OPERATION Ident.: DSC-21-30-20-A-NG00042 Applicable to: ALL Ident.: DSC-21-30-20-A-00000346.0001001 / 24 FEB 11
BLOWER FAULT OR EXTRACT FAULT WARNING When the BLOWER or the EXTRACT pushbutton switch is set at the OVRD (override) position, the system is in closed-circuit configuration and adds air from the air conditioning system to the ventilation air.
When the BLOWER pushbutton switch is set at OVRD, the blower fan is stopped and the extract fan continues to run. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F→
DSC-21-30-20 P 6/8 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
VENTILATION - AVIONICS VENTILATION
When the EXTRACT pushbutton switch is set at OVRD, the extract fan is controlled directly from the pushbutton. Both fans continue to run. Ident.: DSC-21-30-20-A-00000347.0001001 / 24 FEB 11
SMOKE CONFIGURATION When the smoke detector detects smoke in the avionics ventilation air the BLOWER and the EXTRACT FAULT lights come on. When both the BLOWER and the EXTRACT pushbuttons are set to the OVRD position, the air conditioning system supplies cooling air, which is then exhausted overboard. The blower fan stops.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←F→
DSC-21-30-20 P 7/8 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
VENTILATION - AVIONICS VENTILATION
Ident.: DSC-21-30-20-A-00000348.0001001 / 09 DEC 09
CONTROLLER FAILURE The system goes to the same configuration as above, except that the skin exchange isolation valve stays open. The inlet valve and the skin exchange inlet bypass valve remain in the position they were in before the failure occurred. The extract fan keeps running.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←F
DSC-21-30-20 P 8/8 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
VENTILATION - BATTERY VENTILATION
FLIGHT CREW OPERATING MANUAL
BATTERY VENTILATION Ident.: DSC-21-30-40-00000350.0001001 / 09 DEC 09 Applicable to: ALL
A venturi in the skin of the aircraft draws air from the space around the batteries and vents it overboard. The resulting airflow ventilates the batteries.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-21-30-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
VENTILATION - BATTERY VENTILATION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-21-30-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
VENTILATION - LAVATORY AND GALLEY VENTILATION
LAVATORY AND GALLEY Ident.: DSC-21-30-50-00000351.0001001 / 09 DEC 09 Applicable to: ALL
An extraction fan draws ambient cabin air through the lavatories and galleys and exhausts it near the outflow valve. The extraction fan runs continually when electric power is available.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-21-30-50 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
VENTILATION - LAVATORY AND GALLEY VENTILATION
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-21-30-50 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
VENTILATION - CONTROLS AND INDICATORS
OVERHEAD PANEL Ident.: DSC-21-30-60-00000352.0001001 / 24 FEB 11 Applicable to: ALL
(1)
BLOWER pb-sw and EXTRACT pb-sw AUTO: : When both pushbutton switches are on AUTO: ‐ On the ground before the application of TO power, the ventilation system is in open circuit configuration (closed configuration when the skin temperature is below the ground threshold). ‐ On the ground after the application of TO power, and in flight, the ventilation system is in closed circuit configuration. OVRD: : When either pushbutton switch is on OVRD: ‐ The system goes to closed circuit configuration. ‐ Air from the air conditioning system is added to ventilation air. (The blower fan stops if the BLOWER pushbutton switch is in the OVRD position). When both pushbutton switches are on OVRD: ‐ Air flows from the air conditioning system and then overboard. ‐ The extract fan continues to run. FAULT : Lights up amber (and ECAM activates) lt: in the blower switch, if : ‐ blowing pressure is low (See *) ‐ duct overheats (See *) ‐ computer power supply fails ‐ smoke warning is activated in the extract switch, if : ‐ extract pressure is low (See *) ‐ computer power supply fails ‐ smoke warning is activated. * If the warning occurs on the ground when the engines are stopped, the external horn sounds.
(2)
Refer to DSC-21-10-50 Controls on Overhead Panel
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-21-30-60 P 1/4 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
VENTILATION - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
ECAM CAB PRESS PAGE Ident.: DSC-21-30-60-00000353.0003001 / 22 MAY 12 Applicable to: ALL
(1)
BLOWER, VENT and EXTRACT Indications VENT message normally appears in white. It becomes amber, if there is a BLOWER FAULT, EXTRACT FAULT, or AVNCS SYS FAULT. BLOWER message appears in amber if there is a BLOWER FAULT. EXTRACT message appears in amber if there is an EXTRACT FAULT.
(2)
INLET and OUTLET Indications Normally white. The corresponding indication becomes amber, when the inlet valve or the outlet valve is failed.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
DSC-21-30-60 P 2/4 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(3)
VENTILATION - CONTROLS AND INDICATORS
INLET and OUTLET Valve Diagrams
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-21-30-60 P 3/4 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
VENTILATION - CONTROLS AND INDICATORS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-21-30-60 P 4/4 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
VENTILATION - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-21-30-70-00000354.0001001 / 24 FEB 11 Applicable to: ALL
E/WD: FAILURE TITLE conditions
AURAL WARNING
MASTER LIGHT
SD PAGE CALLED
LOCAL WARNING
BLOWER FAULT
Blowing pressure low or duct overheat
BLOWER(1) FAULT lt
EXTRACT FAULT Extract pressure low
EXTRACT (1) FAULT lt
SKIN VALVE FAULT 1. Extract valve fully open in phase 3 or 2. Extract valve fully open in flight or 3. Inlet valve not fully closed in flight
SINGLE CHIME
MASTER CAUT
AVNCS SYS FAULT
Power up test not satisfactory or AEVC not supplied or valves position disagree (1) Associated with ground external call. (2) Only in case of AEVC power supply failure on ground.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
CAB PRESS
FLT PHASE INHIB 3, 4, 5, 7, 8
NIL
4, 5, 7, 8
BLOWER and EXTRACT FAULT lts (2)
3, 4, 5, 6, 7, 8, 9
DSC-21-30-70 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
VENTILATION - WARNINGS AND CAUTIONS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-21-30-70 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
VENTILATION - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-21-30-80-00000355.0001001 / 09 DEC 09 Applicable to: ALL
NORM AC
DC
1 2
AC1 AC2
FAN BLOWER EXTRACT
AC1 AC2 AC2 AC1
DC1 DC2 DC1 DC1
CABIN FANS AEVC VENT
AVIONIC FANS GND COOL UNIT
UNIT FAN CONTROL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
AC ESS
EMER ELEC DC ESS
HOT
SHED SHED
DSC-21-30-80 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
VENTILATION - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-21-30-80 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
CARGO - GENERAL
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-21-40-10-00000356.0003001 / 14 FEB 11 Applicable to: ALL
An extraction fan draws air from the cargo compartments and exhausts it overboard. Air from the cabin replaces the exhausted air, thus ventilating the cargo compartments. The system can add hot bleed air to the air entering from the cabin, thus giving the flight crew control of the temperature in the forward or aft cargo compartment .
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-21-40-10 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
CARGO - GENERAL
FLIGHT CREW OPERATING MANUAL
SCHEMATIC Ident.: DSC-21-40-10-00000357.0004001 / 22 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
DSC-21-40-10 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
CARGO - SYSTEM OPERATION
FLIGHT CREW OPERATING MANUAL
AFT CARGO COMPARTMENT VENTILATION Ident.: DSC-21-40-20-00005986.0001001 / 09 DEC 09 Applicable to: ALL
Air from the cabin goes via the inlet isolation valve to the aft cargo compartment, driven by an extraction fan. Air is controlled by the outlet isolation valve and then goes outboard through the outflow valve. The cargo ventilation controller controls the operation of the inlet and outlet isolation valves and the extraction fan. When the isolation valves are fully open, the extraction fan operates continuously when the aircraft is on the ground and during flight. The controller closes the isolation valves and stops the extraction fan when : ‐ the flight crew turns the AFT ISOL VALVE pushbutton switch OFF, or ‐ the aft cargo smoke detection unit detects smoke. AFT CARGO COMPARTMENT HEATING Ident.: DSC-21-40-20-00005989.0001001 / 09 DEC 09 Applicable to: ALL
The ventilation system for the aft cargo compartment uses hot engine bleed air (upstream of the packs), mixing it with the ambient cabin air that flows through the cargo compartment. The cargo regulating valve regulates the pressure of this hot air supply, and the trim air valve, which is modulated electrically by the controller, controls the flow. The cargo pressure regulating valve is pneumatically operated and electrically controlled from the HOT AIR pushbutton on the CARGO HEAT panel. The hot air is controlled by the cargo trim air valve which is modulated electrically by the controller. The hot air is then mixed with air from the cabin and supplied to the cargo compartment through the ventilation inlet isolation valve. According to the temperature selector demand, the controller regulates the amount of hot air added by the trim air valve, until the desired temperature is reached. If the inlet temperature exceeds 70 °C, the controller closes the trim air valve. If the inlet temperature exceeds 88 °C, the controller interprets this as a duct overheat and closes the pressure regulating valve. This valve then remains closed until the flight crew resets the system by pressing the HOT AIR pushbutton — which it cannot do until the temperature drops below 70 °C.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
DSC-21-40-20 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
CARGO - SYSTEM OPERATION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-21-40-20 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
CARGO - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
OVERHEAD PANEL Ident.: DSC-21-40-30-00000359.0005001 / 14 FEB 11 Applicable to: ALL
(1)
AFT ISOL VALVE pb The switch controls the isolation valves and the extraction fan. Auto : The inlet and outlet isolation valves open, blower and extraction fans run if there is no smoke detected in the aft cargo bay. OFF : The inlet and outlet isolation valves and the trim air valve close, the extraction fan stops. FAULT lt : The light, associated with the ECAM caution, comes on amber when either inlet or outlet valve is not in the selected position.
(2)
HOT AIR pb Auto : The pressure regulating valve regulates the hot air pressure. OFF : The presure regulating valves. The fault circuit is reset. FAULT lt : The amber light and ECAM caution come on, when a duct overheat is detected (88 °C – 190 °F). The light goes out, when the temperature drops below 70 °C (158 °F), and OFF is selected. Then, if the pushbutton is set to on, the system resets.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-21-40-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(3)
CARGO - CONTROLS AND INDICATORS
Temperature sel ‐ COLD : position ‐ HOT : position ‐ Middle : position Note:
Approximately 5 °C (41 °F) Approximately 26 °C (79 °F) Approximately 15 °C (59 °F)
1. The cargo compartment temperature may vary, depending on external factors (flight duration, outside temperature...). 2. The actual bulk cargo compartment temperature may be 10 °C (18 °F) lower than the selected temperature.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-21-40-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
CARGO - ECAM COND PAGE
FLIGHT CREW OPERATING MANUAL
ECAM COND PAGE Ident.: DSC-21-40-35-00006005.0003001 / 22 MAY 12 Applicable to: ALL
(1)
Cargo compartment temperature This indication is green.
(2)
Zone indication It is white.
(3)
Duct inlet temperature This is normally green, it becomes amber when T ≥ 80 °C.
(4)
Inlet isolation valve In line – Green Crossline – Amber
(5)
: :
Valve is open. Valve is closed.
Outlet isolation valve Crossline – Green : In line – Amber :
Valve is open. Valve is closed.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-21-40-35 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
CARGO - ECAM COND PAGE
FLIGHT CREW OPERATING MANUAL
(6)
(7)
Trim air valve H - Hot (Green) C - Cold (Green)
: :
Valve is open. Valve is closed.
Hot air pressure regulating valve In line and green : valve is open. In line and amber : valve failed open. Cross line and green : valve normally closed with the pushbutton in ON position. Cross line and amber : valve is closed and the pushbutton in OFF position.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-21-40-35 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
CARGO - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-21-40-40-00000361.0003001 / 14 FEB 11 Applicable to: ALL
E/WD : FAILURE TITLE conditions
AFT (FWD) CARGO DUCT temperature OVHT Duct Temperature > 88 °C (190 °F)
AURAL WARNING
MASTER LIGHT
SINGLE CHIME
MASTER CAUT
SD PAGE CALLED
COND
LOCAL FLT PHASE WARNING INHIB HOT AIR FAULT lt
AFT (FWD) CRG HEAT FAULT Cargo heating controller fault
AFT (FWD) CRG VENT FAULT Cargo fan fault
NIL NIL
Cargo isolation valve
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
NIL NIL
AFT (FWD) CRG ISOL VALVE
A
3, 4, 5, 7, 8
ISOL VALVE FAULT It
DSC-21-40-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
CARGO - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-21-40-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
CARGO - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-21-40-50-00000362.0001001 / 14 FEB 11 Applicable to: ALL
NORM AC FWD/AFT CARGO
EMER ELEC DC ESS
HOT
DC BAT DC BAT
VENT CONT HEAT CONT VENT/HEAT FANS(S)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DC
AC ESS
AC 1
A
DSC-21-40-50 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS AIR CONDITIONING / PRESSURIZATION / VENTILATION A318/A319/A320/A321
CARGO - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-21-40-50 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL
Intentionally left blank
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_10-PLP PRELIMINARY PAGES TABLE OF CONTENTS SUMMARY OF HIGHLIGHTS
DSC-22_10-10 Description Preamble.................................................................................................................................................................. A Description............................................................................................................................................................... B General Philosophy................................................................................................................................................. C Flight Management Guidance Computer (FMGC).................................................................................................. D Multipurpose Control and Display Unit (MCDU)..................................................................................................... E Flight Control Unit (FCU).........................................................................................................................................F Flight Augmentation Computer (FAC).....................................................................................................................G Other Flight Crew Interfaces................................................................................................................................... H Flight Crew Interface with FMGC............................................................................................................................. I
DSC-22_10-20 System Interface Diagram System Interface Diagram....................................................................................................................................... A
DSC-22_10-30 FMGS Modes of Operation General.....................................................................................................................................................................A Dual Mode................................................................................................................................................................B Independent Mode...................................................................................................................................................C Single Mode.............................................................................................................................................................D Back Up Navigation Mode.......................................................................................................................................E
DSC-22_10-40 Pilot Interface DSC-22_10-40-05 Management of the Displays General.....................................................................................................................................................................A
DSC-22_10-40-10 MCDU MCDU.......................................................................................................................................................................A
DSC-22_10-40-20 FCU FCU.......................................................................................................................................................................... A FCU Philosophy....................................................................................................................................................... B Speed/Mach Control Area....................................................................................................................................... C Lateral Control Area................................................................................................................................................ D AP-A/THR Control Area...........................................................................................................................................E Vertical Control Area................................................................................................................................................F
DSC-22_10-40-30 Thrust Levers Thrust Levers........................................................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_10-PLP-TOC P 1/2 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_10-40-40 Primary Flight Display PFD.......................................................................................................................................................................... A Climb Phase.............................................................................................................................................................B Approach Phase...................................................................................................................................................... C
DSC-22_10-40-50 Navigation Display ND............................................................................................................................................................................ A Arc Mode..................................................................................................................................................................B Plan Mode................................................................................................................................................................C Rose Modes.............................................................................................................................................................D Flight Plan Display Colors....................................................................................................................................... E
DSC-22_10-50 Warnings and Cautions Warnings and Cautions........................................................................................................................................... A
DSC-22_10-60 ELECTRICAL SUPPLY BUS EQUIPMENT LIST.......................................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_10-PLP-TOC P 2/2 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title
Toc Index
ID
Reason
A
1
Update of the alert « NAV FMS/GPS POS DISAGREE » since it is inhibited in the flight phases 1, 3, 4 and 10. Documentation update: Deletion of text.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_10-PLP-SOH P 1/2 18 SEP 12
DSC-22_10-50 Warnings and Cautions
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_10-PLP-SOH P 2/2 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW OPERATING MANUAL
PREAMBLE Ident.: DSC-22_10-10-00010067.0001001 / 17 AUG 10 Applicable to: ALL
This section gives a general description of the Auto Flight System and its functions: ‐ Architecture ‐ Function description ‐ Basic principle of systems: • Reversion • Protection • Managed and selected guidance modes. ‐ Mode information ‐ Display characteristics ‐ Operational principles ‐ Flight crew interface (MCDU pages) ‐ Degraded modes of operations. DESCRIPTION Ident.: DSC-22_10-10-00010068.0001001 / 17 AUG 10 Applicable to: ALL
The Flight Management Guidance System (FMGS) contains the following units: ‐ Two Flight Management Guidance Computers (FMGC) ‐ Two Multipurpose Control and Display Units (MCDU) (third MCDU optional) ‐ One Flight Control Unit (FCU) ‐ Two Flight Augmentation Computers (FAC). GENERAL PHILOSOPHY Ident.: DSC-22_10-10-00010069.0001001 / 17 AUG 10 Applicable to: ALL
The Flight Management and Guidance System (FMGS) provides predictions of flight time, mileage, speed, economy profiles and altitude. It reduces cockpit workload, improves efficiency, and eliminates many routine operations generally performed by the flight crew.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to C →
DSC-22_10-10 P 1/6 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION
The Flight Management Guidance System (FMGS) operates as follows: ‐ During cockpit preparation the flight crew uses the Multipurpose Control and Display Unit (MCDU) to insert a preplanned route from origin to destination. This route includes SID, EN ROUTE, WAYPOINTS, STAR, APPROACH, MISSED APPR, and ALTN route as available from the navigation database. ‐ Subsequently the system defines a vertical profile and a speed profile, taking into account ATC requirements and performance criteria. Either FMGC performs all operations, if one FMGC fails. The FMGS computes the aircraft position continually, using stored aircraft performance data and navigation data. Therefore it can steer the aircraft along a preplanned route and vertical and speed profiles. This type of guidance is said to be “managed”. If the flight crew wants to modify any flight parameter (SPD, V/S, HDG, etc.) temporarily, they may do so by using the various Flight Control Unit (FCU) selectors. The FMGS then guides the aircraft to the target value of this parameter that they have selected. This type of guidance is said to be “selected”. The two available types of guidance, then, are: ‐ Managed guidance guides the aircraft along the preplanned route and the vertical and speed/Mach profile. (The FMGS computes the target values of the various flight parameters). ‐ Selected guidance guides the aircraft to the target values of the various flight parameters the flight crew selects by using the FCU selectors. Selected guidance always has priority over managed guidance. FLIGHT MANAGEMENT GUIDANCE COMPUTER (FMGC) Ident.: DSC-22_10-10-00010073.0002001 / 17 AUG 10 Applicable to: ALL
Each FMGC is divided into two main parts: ‐ The Flight Management (FM) part controls the following functions: • Navigation and management of navigation radios • Management of flight planning • Prediction and optimization of performance • Display management. ‐ The Flight Guidance (FG) part performs the following functions: • Autopilot (AP) command • Flight Director (FD) command • Autothrust (A/THR) command. Each FMGC has its own set of databases. The individual databases can be independently loaded into their respective FMGC, or independently copied from one FMGC to the other.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← C to D →
DSC-22_10-10 P 2/6 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW OPERATING MANUAL
Each FMGC contains these main databases: 1. The Navigation database (2.8 Mbytes) contains standard navigation data: Navaids, waypoints, airways, enroute information, holding patterns, airports, runways, procedures (SIDs, STARs, etc.), company routes, alternates. The airline updates this part every 28 days, and is responsible for defining, acquiring, updating, loading, and using this data. The updating operation takes 20 min to complete or 5 min if cross loaded from the opposite FMGC. 2. The Airline Modifiable Information (AMI), also described as the FM Airline Configuration file, contains: ‐ Airline policy values: THR RED altitude, ACC altitude, EO ACC altitude, PERF factor, IDLE factor. ‐ Fuel policy values: Fuel for taxi, % of route reserve, maximum and minimum values of route reserve, etc. ‐ AOC functions customization. 3. The Aircraft Performance database includes the Engine model, Aerodynamical model, and Performance model. The airline cannot modify this database. 4. The Magnetic Variation database. 5. Each FMGC contains elements stored by the flight crew that enable them to create 20 waypoints, 10 runways, 20 navaids, and 5 routes. MULTIPURPOSE CONTROL AND DISPLAY UNIT (MCDU) Ident.: DSC-22_10-10-00010074.0002001 / 17 AUG 10 Applicable to: ALL
Two MCDUs are installed on the pedestal for flight crew loading and display of data. The use of the MCDU allows the flight crew to interface with the FMGC by selection of a flight plan for lateral and vertical trajectories and speed profiles. The flight crew may also modify selected navigation or performance data and specific functions of Flight Management (revised flight plan, engine-out, secondary flight plan, etc.). Additional data from peripherals (Centralized Fault Display System (CFDS), ARINC Communication Addressing and Reporting System (ACARS), Air Traffic Service Unit (ATSU)...) can also be displayed. Data that is entered into the MCDU that is illogical or beyond the aircraft capabilities will either be disregarded or will generate an advisory message. The MCDUs allow the activation of the back–up navigation in the case of a dual FM Failure. FLIGHT CONTROL UNIT (FCU) Ident.: DSC-22_10-10-00010075.0001001 / 17 AUG 10 Applicable to: ALL
The FCU located on the glareshield, is the short-term interface between the flight crew and the FMGC. It is used to select any flight parameters or modify those selected in the MCDU. The autopilots and autothrust functions may be engaged or disengaged. Different guidance modes can 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← D to F →
DSC-22_10-10 P 3/6 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW OPERATING MANUAL
be selected to change various targets (speed, heading, track, altitude, flight path angle, vertical speed). FLIGHT AUGMENTATION COMPUTER (FAC) Ident.: DSC-22_10-10-00010076.0001001 / 17 AUG 10 Applicable to: ALL
The FAC controls rudder, rudder trim and yaw damper inputs. It computes data for the flight envelope and speed functions. The FAC also provides warning for low-energy and windshear detection if these functions are installed.
OTHER FLIGHT CREW INTERFACES Ident.: DSC-22_10-10-A-NG00703 Applicable to: ALL Ident.: DSC-22_10-10-A-00010077.0001001 / 17 AUG 10
THRUST LEVERS The thrust levers are the main interface between the Flight Management Guidance Computer (FMGC), the Full Authority Digital Engine Control System (FADEC), and the flight crew. The thrust levers: ‐ Arm the autothrust at takeoff, when FLX or TOGA is selected ‐ Limit the maximum thrust by their position when autothrust is active ‐ Disconnect the autothrust system when the flight crew sets them to IDLE ‐ Command the thrust manually when autothrust is not active ‐ Engage the common modes (takeoff or go-around) when TOGA (or FLX for takeoff) is set ‐ Set the autothrust to the active mode when they are between IDLE and CL detent (MCT in engine out). Ident.: DSC-22_10-10-A-00010078.0001001 / 17 AUG 10
ELECTRONIC FLIGHT INSTRUMENTS (EFIS) Two Primary Flight Displays (PFD) and Navigation Displays (ND) provide the flight crew with full-time flight guidance, navigation and system advisory information for all flight phases. An EFIS control panel is located at each end of the glareshield and is used to control both Primary and Navigation Displays. This panel includes controls to select various modes within the PFD. A selector allows the barometric altimeter setting to be displayed on the PFD. Various distance ranges can be selected on the ND, and two switches allow either the left or right VOR/ADF bearing pointers to be displayed on the ND.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← F to H →
DSC-22_10-10 P 4/6 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW OPERATING MANUAL
Ident.: DSC-22_10-10-A-00010079.0001001 / 17 AUG 10
PRIMARY FLIGHT DISPLAYS The PFDs combine several conventional flight instrument indications on one color display panel, for centralized reference of flight data. This centralized color display includes: ‐ Flight Director attitude guidance targets ‐ Armed and engaged modes ‐ Navigation and instrument approach information ‐ Altimeter setting ‐ Barometric altitude ‐ System messages. Ident.: DSC-22_10-10-A-00010080.0002001 / 17 AUG 10
NAVIGATION DISPLAYS Five different color navigation compass displays can be selected: ‐ ARC (map mode) ‐ ROSE NAV (map mode) ‐ ROSE VOR ‐ ROSE LS ‐ PLAN. Information displayed on these modes uses the aircraft’s position as a reference point for the flight plan navigation data (lateral and vertical information).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H
DSC-22_10-10 P 5/6 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW OPERATING MANUAL
FLIGHT CREW INTERFACE WITH FMGC Ident.: DSC-22_10-10-00010082.0002001 / 14 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
I
DSC-22_10-10 P 6/6 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
SYSTEM INTERFACE DIAGRAM
FLIGHT CREW OPERATING MANUAL
SYSTEM INTERFACE DIAGRAM Ident.: DSC-22_10-20-00010084.0001001 / 17 AUG 10 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-22_10-20 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
SYSTEM INTERFACE DIAGRAM
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_10-20 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FMGS MODES OF OPERATION
GENERAL Ident.: DSC-22_10-30-00010085.0002001 / 17 AUG 10 Applicable to: ALL
The FMGS has four modes of operation: ‐ Dual mode (the normal mode) ‐ Independent mode. Each FMGC being controlled by its associated MCDU ‐ Single mode (using one FMGC only) ‐ Back–up navigation mode. DUAL MODE Ident.: DSC-22_10-30-00010086.0001001 / 17 AUG 10 Applicable to: ALL
This is the normal mode. The two FMGCs are synchronized: each performs its own computations and exchanges data with the other through a crosstalk bus. One FMGC is the master, the other the slave, so that some data in the slave FMGC comes from the master. All data inserted into any MCDU is transferred to both FMGCs and to all peripherals.
MASTER FMGC LOGIC ‐ If one autopilot (AP) is engaged, the related FMGC is master: • It uses the onside FD for guidance • It controls the A/THR • It controls the FMA 1 and 2. ‐ If two APs are engaged, FMGC1 is master. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-22_10-30 P 1/4 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
FMGS MODES OF OPERATION
FLIGHT CREW OPERATING MANUAL
‐ If no AP is engaged, and • The FD1 pb is on, then FMGC1 is master • The FD1 pb is off, and FD2 pb on then FMGC2 is master. ‐ If no AP/FD is engaged, A/THR is controlled by FMGC1. INDEPENDENT MODE Ident.: DSC-22_10-30-00010087.0001001 / 17 AUG 10 Applicable to: ALL
The system automatically selects this degraded mode under specific abnormal conditions (e.g. different database validity on both FMGCs). Both FMGCs work independently and are linked only to peripherals on their own sides of the flight deck (“onside” peripherals). When this occurs, the “INDEPENDENT OPERATION” message is displayed on both MCDU scratchpads. Each MCDU transmits data it receives from its onside FMGC. It affects only the onside EFIS (Electronic Flight Instrument System) and RMP (Radio Management Panel). On the POS MONITOR page (and GPS MONITOR page ), FMGS position (and GPS position ) from the opposite FMGC is not displayed. On the RAD NAV page (and PROG page, if the FMGS GPS is not installed), navaids tuned on the opposite MCDU are not displayed. Corresponding fields are blank. PROCEDURES ON GROUND If each FMGC is loaded with a different database, the FMGS will only operate in independent mode. CHECK the database number and validity.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
DSC-22_10-30 P 2/4 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FMGS MODES OF OPERATION
CROSSLOAD the database to restore the dual operation. Crossload function is available on ground only (in preflight or done phase), when an independent operation is detected. PROCEDURES IN FLIGHT DO NOT SWITCH the navigation databases. MAKE the same entries on both MCDUs to have both AP/FDs similar orders. Both FGs being valid, 2 APs may be engaged for CAT II or CAT III operations. In the event of a go-around and when the second AP is disconnected: ENSURE that the FMGC in command has correct flight plan orders and an updated nav database. Airbus does not recommend pulling one FMGC circuit breaker to force the system to operate in SINGLE mode. SINGLE MODE Ident.: DSC-22_10-30-00010088.0004001 / 18 AUG 10 Applicable to: ALL
The system automatically selects this degraded mode when one FMGC fails. When this occurs, the failed FMGC displays “OPP FMGC IN PROCESS” in white on the MCDU scratchpad. On the ND usually associated with the failed FM: ‐ If the NDs are not both in the same mode or range, the associated ND displays "MAP NOT AVAIL" and "SET OFFSIDE RNG/MODE". ‐ If the NDs are in the same mode and range, the associated ND displays the "OFFSIDE FM CONTROL" amber message. Both POS MONITOR pages display the same position (operative FMGC position). 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← C to D →
DSC-22_10-30 P 3/4 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
FMGS MODES OF OPERATION
FLIGHT CREW OPERATING MANUAL
Both FDs are driven by the same FMGC. Any entry on either MCDU is sent to the operative FMGC. PROCEDURES If a transient failure triggers a single mode of operation: DO NOT USE the MCDU(s) until the PLEASE WAIT message is suppressed. SET both NDs on the same range and mode to display the same information from the operative FMGC. When convenient, RESET the failed FMGC. (Refer to PRO-SUP-22-10-B Manual FMGS Reset - General). BACK UP NAVIGATION MODE Ident.: DSC-22_10-30-00010089.0001001 / 17 AUG 10 Applicable to: ALL
The flight crew selects on the MCDU MENU page this degraded mode when both FMGCs fail. They recover the navigation function through the MCDU and IRS/GPS . The MCDU continuously memorizes the active flight plan in its memory. If both FMGCs fail, the back up navigation provides the following functions: ‐ Flight Planning ‐ Aircraft position using onside IRS, IRS3, or GPIRS position (if GPS ) ‐ F-PLN display on ND ‐ No AP/FD NAV mode ‐ Limited lateral revision ‐ F-PLN automatic sequencing.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← D to E
DSC-22_10-30 P 4/4 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PILOT INTERFACE - MANAGEMENT OF THE DISPLAYS
GENERAL Ident.: DSC-22_10-40-05-00010083.0001001 / 17 AUG 10 Applicable to: ALL
The flight management system displays navigation, performance and guidance information on the: ‐ Multipurpose Control and Display Unit (MCDU) ‐ Navigation Display (ND) of the Electronic Flight Instrument System (EFIS) ‐ Primary Flight Display (PFD) of the EFIS.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-22_10-40-05 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PILOT INTERFACE - MANAGEMENT OF THE DISPLAYS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_10-40-05 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PILOT INTERFACE - MCDU
MCDU Ident.: DSC-22_10-40-10-A-NG00781 Applicable to: ALL Ident.: DSC-22_10-40-10-A-00010090.0003001 / 14 MAY 12
MCDU INTERFACE
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-22_10-40-10 P 1/10 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PILOT INTERFACE - MCDU
Ident.: DSC-22_10-40-10-A-00010091.0002001 / 17 AUG 10
GENERAL The Multipurpose Control and Display Unit (MCDU) has a Liquid Crystal Display (LCD) with 14 lines of 24 characters each, including: ‐ A title line that gives the name of the current page in large letters ‐ Six label lines, each of which nhames the data displayed just below it (on the data field line) ‐ Six data field lines that display computed data or data inserted by the flight crew ‐ The scratchpad line that displays: • Specific messages • Information the flight crew has entered by means of the number and letter keys and which can then be moved to one of the data fields. Ident.: DSC-22_10-40-10-A-00010092.0001001 / 17 AUG 10
LINE SELECT KEYS There is a column of Line Select Keys (LSKs) on each side of the screen. The flight crew uses these keys to: ‐ Move a parameter they have entered in the scratchpad to the appropriate line on the main screen ‐ Call up a specific function page indicated by a prompt displayed on the adjacent line ‐ Call up lateral or vertical revision pages from the flight plan page.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
DSC-22_10-40-10 P 2/10 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
PILOT INTERFACE - MCDU
FLIGHT CREW OPERATING MANUAL
Ident.: DSC-22_10-40-10-A-00010093.0002001 / 17 AUG 10
KEYBOARD The keyboard includes: ‐ Function and Page keys ↑ ↓ (or SLEW) keys ← → keys
Call up functions and pages the flight crew uses for flight management functions and computations. Move a page up or down to display portions that are off the screen. Moves to the next page of a multi-page element. An arrow in the top right corner indicates that another page is available. AIRPORT key Calls up the flight plan page that contains the next airport along the current flight plan. Successive pushes on the key show the alternate airport, the origin airport (before takeoff), and the next airport again. ‐ Number and letter keys allow the flight crew to insert data in the scratchpad so that they can use a line select key to enter it in the main display. ‐ Three keys have special functions: CLR (clear) key Erases material (messages or inserted data) from the scratchpad or from certain areas of displayed pages. OVFY (overfly) key Allows the aircraft to overfly a selected waypoint. SP (space) key Allows to insert a space in specific message. Ident.: DSC-22_10-40-10-A-00010094.0002001 / 17 AUG 10
ANNUNCIATORS (ON THE SIDE OF THE KEYBOARD) FAIL (amber) MCDU MENU (white) FM (white)
Indicates that the Multipurpose Control and Display Unit (MCDU) has failed. Indicates that the flight crew should call up a peripheral linked to the MCDU (such as ACARS, ATSU or CFDS). Comes on while the flight crew is using the MCDU to display peripherals. This light tells the flight crew that the FMGC has an important message to deliver. The flight crew accesses the message by pressing the MCDU MENU key and the line select key adjacent to the FMGC prompt.
Ident.: DSC-22_10-40-10-A-00010757.0002001 / 17 AUG 10
ANNUNCIATORS (ON THE TOP OF THE KEYBOARD) FM 1 and FM 2 (amber) The onside FM is failed IND (amber) The onside FM detects an independent mode of operation while both FM are healthly. RDY (green) MCDU has passed its power up test after it was turned off using its DIM key.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
DSC-22_10-40-10 P 3/10 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PILOT INTERFACE - MCDU
Ident.: DSC-22_10-40-10-A-00010750.0001001 / 17 AUG 10
BRT AND DIM KEYS Control the light intensity of the entire MCDU. MCDU power up is performed with the BRT key and MCDU shut down is performed with the DIM key. Ident.: DSC-22_10-40-10-A-00010097.0001001 / 17 AUG 10
DATA ENTRY The flight crew enters data by typing it into the scratchpad on the MCDU. Next, pressing the line select key (LSK) will load the data from the scratchpad into the desired field. An error message displays if the data is out of range or not formatted correctly. To correct data, the flight crew may clear the message with the clear (CLR) key and then retype the message into the scratchpad. Pressing the CLR key when the scratchpad is empty displays “CLR”. To clear data from a field, select CLR from the scratchpad to the data field to be cleared. Ident.: DSC-22_10-40-10-A-00010098.0001001 / 17 AUG 10
MCDU ENTRY FORMAT The flight crew enters information into the MCDU at the bottom line of the scratchpad. When data has lead zeros, they may be omitted if desired. For example a three-digit wind direction of 060 may be typed as 60. The display will still show 060. To enter an altitude below 1 000 ft, the lead zero must be added as 0400 for 400 ft. This differentiates the altitude from a flight level. To enter a double data entry such a speed/altitude, the separating slash must be used. If entering only the first part of a double entry, omit the slash. To enter only the second part of a double entry, a leading slash must be used i.e. /0400. Ident.: DSC-22_10-40-10-A-00010099.0001001 / 17 AUG 10
MESSAGES The scratchpad displays various messages for flight crew information. Theses messages are prioritized by importance to the flight crew as either amber or white. Amber messages are: ‐ Navigation messages ‐ Data entry messages ‐ EFIS repeat messages.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
DSC-22_10-40-10 P 4/10 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
PILOT INTERFACE - MCDU
FLIGHT CREW OPERATING MANUAL
Amber messages are categorized into two types: ‐ Type 1 message that is a direct result of a flight crew action. Type 1 messages are displayed immediately in the scratchpad ahead of other messages. ‐ Type 2 messages inform the flight crew of a given situation or request a specific action. Stored in “last in”, “first out” message queue that holds maximum of 5 messages. Type 2 messages are displayed in the scratchpad only if there are no Type 1 messages or other data and will remain until all the messages have been viewed and cleared with the CLR key. White messages are advisory only. Ident.: DSC-22_10-40-10-A-00010101.0001001 / 17 AUG 10
CHARACTERS Small and large fonts are displayed according to the following rules: ‐ The title line and the scratchpad are displayed in large font ‐ Datafields are usually displayed in large font ‐ Label lines are displayed in small font ‐ Flight crew entries and modifiable data are displayed in large font ‐ Defaulted/computed and non modifiable data are displayed in small font. Ident.: DSC-22_10-40-10-A-00010102.0001001 / 17 AUG 10
COLORS DATA TITLES, COMMENTS, , ↑ ↓, ← →, DASHES, MINOR MESSAGES ‐ MODIFIABLE DATA ‐ SELECTABLE DATA ‐ BRACKETS ‐ NON MODIFIABLE DATA ‐ ACTIVE DATA ‐ ‐ ‐ ‐
MANDATORY DATA (BOXES) FLIGHT CREW ACTION REQUIRED IMPORTANT MESSAGES MISSED CONSTRAINT
‐ CONSTRAINTS ‐ MAX ALTITUDE PRIMARY F-PLN TEMPORARY F-PLN
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
MCDU COLOR WHITE BLUE
GREEN AMBER
MAGENTA GREEN WAYPOINTS, WHITE LEGS YELLOW WAYPOINTS, WHITE LEGS Continued on the following page
←A→
DSC-22_10-40-10 P 5/10 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DATA SECONDARY F-PLN MISSED APPROACH (not active) ALTERNATE F-PLN (not active) OFFSET TUNED NAVAID "TO" WAYPOINT AND DESTINATION
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PILOT INTERFACE - MCDU Continued from the previous page MCDU COLOR WHITE WAYPOINTS AND LEGS BLUE WAYPOINTS, WHITE LEGS BLUE WAYPOINTS, WHITE LEGS GREEN WAYPOINTS, WHITE LEGS, OFST DISPLAYED IN THE TITLE OF THE F-PLN PAGE BLUE WHITE
←A→
DSC-22_10-40-10 P 6/10 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PILOT INTERFACE - MCDU
Ident.: DSC-22_10-40-10-A-00010103.0001001 / 14 MAY 12
SCREEN PROMPTS
Ident.: DSC-22_10-40-10-A-00010104.0002001 / 17 AUG 10
MCDU FUNCTION KEYS The function keys on the Multipurpose Control and Display Units allow the flight crew to call up MCDU pages quickly. The following is a summary of the purpose of each key: 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
DSC-22_10-40-10 P 7/10 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DIR
PROG
PERF
INIT
DATA
F-PLN
RAD NAV
PILOT INTERFACE - MCDU
Calls up the DIR TO page, and enables the flight crew to proceed directly from the present position to any waypoint, entered manually or selected in the active flight plan. Calls up the progress page corresponding to the phase of the active flight plan that is in progress. This page displays navigation information and active data such as the optimum and maximum recommended cruise flight levels. It enables the flight crew to update the FMGS position and to obtain a bearing and distance to any location. Calls up the performance pages, that display the optimum speed or Mach number for each phase. The flight crew can amend these pages. The first page to be displayed is the one corresponding to the current flight phase (except for preflight and done phases). The flight crew can then use the appropriate 6L or 6R LSK to call up pages corresponding to future flight phases. Calls up the flight plan initialization A page, which also gives the flight crew access to the B page. The flight crew uses the INIT pages to initialize Flight Management for the flight. The flight crew uses the INIT A page primarily to insert his flight plan and to align the inertial reference system. The flight crew uses the INIT B page to insert aircraft weight, fuel on board, CG and various fuel requirements. The FMGS uses this data to compute predictions and fuel planning parameters. The flight crew has access to the INIT A page only in the preflight phase. INIT B page (not accessible after engine start) is called up by pressing the "NEXT PAGE" key. Calls up the data index page. This gives the flight crew access to various reference pages that show aircraft position, aircraft status, runways, waypoints, navaids, routes, and data stored by the flight crew. Calls up the flight plan A and B pages, which contain a leg-by-leg description of the active primary flight plan. The flight crew can use the slewing keys to review the entire active flight plan. They can make all lateral and vertical revisions to the flight plan through these pages, using the left LSKs for lateral revision and the right keys for vertical revision. Calls up the radio navigation page. This page displays the Radio Navaids tuned automatically or manually through the FMGC.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
DSC-22_10-40-10 P 8/10 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FUEL PRED
SEC F-PLN
ATC COMM MCDU MENU
PILOT INTERFACE - MCDU
Calls up the fuel prediction page. Once the engines are started, this page displays the fuel predicted to be remaining at the destination and the alternate, as well as fuel management data. Calls up the index page for the secondary flight plan. The flight crew can use this page to call up the secondary flight plan and all the functions related to it (copying, deleting, reviewing, activating, and the INIT and PERF pages). Calls up the ATC applications (not activated). Calls up the MCDU MENU page, which displays the subsystems currently addressed via the MCDU. The key next to the name of a subsystem enables the flight crew to select that subsystem. When the MCDU MENU annunciator lights up, the flight crew should press the MCDU MENU key. The menu will have [REQ] displayed next to the name of the subsystem that requires attention.
Ident.: DSC-22_10-40-10-A-00010107.0005001 / 14 MAY 12
MCDU DISPLAY The MCDUs display: ‐ Position and accuracy information ‐ Tuned navaids ‐ Lateral and vertical flight plans (waypoints, pseudo waypoints, constraints) ‐ Predictions (SPD, TIME, ALT, WIND) ‐ Fuel predictions and fuel management information (estimated fuel on board, extra fuel) ‐ Performance data.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
DSC-22_10-40-10 P 9/10 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PILOT INTERFACE - MCDU
←A
DSC-22_10-40-10 P 10/10 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
PILOT INTERFACE - FCU
FLIGHT CREW OPERATING MANUAL
FCU Ident.: DSC-22_10-40-20-00010112.0003001 / 14 MAY 12 Applicable to: ALL
The Flight Control Unit (FCU) is located on the glareshield and is constituted of three control panels: One for the automatic flight controls and two for the Electronic Flight Instrument System (EFIS). The FCU has two channels, each of which can independently command the central control panel. If one channel fails, the other channel can control all the functions.
FCU PHILOSOPHY Ident.: DSC-22_10-40-20-00010113.0002001 / 14 MAY 12 Applicable to: ALL
The flight crew can use two types of guidance to control the aircraft in auto flight. One type is managed by the Flight Management Guidance System (FMGS). The other uses target quantities which are manually entered by the flight crew. When the aircraft uses target quantities from the FMGS (managed guidance), the FCU windows display dashes and the white dots next to those windows light up. When the aircraft uses target quantities, entered by the flight crew (selected guidance), the windows display the selected numbers and the white dots do not light up.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-22_10-40-20 P 1/8 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
PILOT INTERFACE - FCU
FLIGHT CREW OPERATING MANUAL
Note:
The altitude window always displays an altitude selected by the flight crew (never dashes).
The FCU has four knobs: ‐ SPD-MACH ‐ HDG-TRK ‐ ALT ‐ V/S-FPA. The knobs can be rotated, pushed in, and pulled out: ‐ In order to arm or engage managed guidance for a given mode, the flight crew pushes in the associated knob. If, for example, they push in the HDG knob, they engage or arms the NAV mode. ‐ In order to engage a selected guidance mode, the flight crew turns the knob to set the desired value, then pulls the knob out to engage the mode with a target value equal to the selected value. Note:
In managed guidance (lateral, vertical guidance or managed speed), the corresponding window is dashed. Turning a knob without pulling it, displays a value that is the sum of the current target and the turn action value. The display remains 45 s on the HDG/TRK and V/S windows and 10 s on the SPD/MACH window before the dashes reappear. This rule does not apply to the ALT knob/window.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-22_10-40-20 P 2/8 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
PILOT INTERFACE - FCU
FLIGHT CREW OPERATING MANUAL
SPEED/MACH CONTROL AREA Ident.: DSC-22_10-40-20-00010114.0002001 / 14 MAY 12 Applicable to: ALL
SPD/MACH knob Display range: between 100 and 399 kt for speed, between 0.10 and 0.99 for Mach number. One rotation of the knob corresponds to approximately 32 kt or M 0.32. SPD/MACH pb Pushing this pushbutton changes the SPD target to the corresponding MACH target and vice versa.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-22_10-40-20 P 3/8 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
PILOT INTERFACE - FCU
FLIGHT CREW OPERATING MANUAL
LATERAL CONTROL AREA Ident.: DSC-22_10-40-20-00010115.0007001 / 14 MAY 12 Applicable to: ALL
HDG/TRK knob Display range: between 0 ° and 359 °. One rotation of the knob corresponds to 32 ° (1 ° per click). LOC pb Pushing this pushbutton arms, engages, or disengages the LOC mode. HDG V/S – TRK FPA pb The flight crew uses this pushbutton to select HDG (associated with V/S) or TRK (associated with FPA). Pushing it: ‐ Displays the Flight Path Vector (FPV) on the Primary Flight Display (PFD) or deletes it. ‐ On the PFD, changes the FD crossbar display (with the aircraft attitude as its reference) to the aircraft Flight Path Director (with the flight path vector as its reference) and vice versa. ‐ Changes heading reference into track reference in the HDG/TRK window and vice versa. ‐ Changes vertical speed reference target into flight path angle reference target in the V/S-FPA window and vice versa.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D→
DSC-22_10-40-20 P 4/8 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
PILOT INTERFACE - FCU
FLIGHT CREW OPERATING MANUAL
AP-A/THR CONTROL AREA Ident.: DSC-22_10-40-20-00010116.0001001 / 14 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← D to E →
DSC-22_10-40-20 P 5/8 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
PILOT INTERFACE - FCU
FLIGHT CREW OPERATING MANUAL
AP1 pb AND AP2 pb The flight crew uses these pushbuttons to engage or disengage the autopilots. The buttons illuminate green when the autopilot is engaged. A/THR pb The flight crew uses this pushbutton to arm, activate, or disconnect the autothrust (A/THR). This button illuminates green if the A/THR is armed or active. VERTICAL CONTROL AREA Ident.: DSC-22_10-40-20-00010117.0010001 / 22 MAY 12 Applicable to: ALL
The FCU altitude window always displays a target value selected by the flight crew. It never displays dashes.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← E to F →
DSC-22_10-40-20 P 6/8 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
PILOT INTERFACE - FCU
FLIGHT CREW OPERATING MANUAL
Altitude knob (INNER AND OUTER) Display range: 100 to 49 000 ft ‐ The outer knob has two positions: 100 and 1000 ‐ The inner knob sets the altitude in the FCU window in increments of 100 or 1 000 ft, depending upon the position of the outer knob. METRIC ALT pb This pushbutton is used to display the FCU altitude target in meters on the ECAM, or the current altitude and FCU/FM altitude target in meters on the PFD . V/S or FPA knob Range (V/S) :
–6 000 to +6 000 ft/min 2 clicks = 100 ft/min If the flight crew turns the knob slowly, each click equals 100 ft/min. Range (FPA) : –9.9 ° to +9.9 ° 1 click = 0.1 ° The flight crew turns this knob to set the value of the vertical speed (V/S) or flight path angle (FPA) to be displayed in the V/S or FPA window (They choose which, V/S or FPA, is to be displayed by pushing the HDG V/S - TRK FPA pb). One rotation of the knob corresponds to 32 clicks. When the flight crew pushes in the V/S or FPA knob, the system commands an immediate level-off by engaging the V/S or FPA mode with a target of zero. The flight mode annunciator (FMA) then displays ALT in green when V/S or FPA is nulled. If the flight crew now turns the knob to put in a new setting for V/S or FPA, the aircraft changes flight path accordingly. APPR pb This pushbutton arms, disarms, engages, or disengages the approach modes: ‐ LOC and G/S modes, if an ILS approach is selected in the active F-PLN. ‐ APP NAV-FINAL modes, if a non precision approach is selected in the active F-PLN.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←F
DSC-22_10-40-20 P 7/8 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
PILOT INTERFACE - FCU
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_10-40-20 P 8/8 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
PILOT INTERFACE - THRUST LEVERS
FLIGHT CREW OPERATING MANUAL
THRUST LEVERS Ident.: DSC-22_10-40-30-00010119.0001001 / 14 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-22_10-40-30 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
PILOT INTERFACE - THRUST LEVERS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_10-40-30 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PILOT INTERFACE - PRIMARY FLIGHT DISPLAY
PFD Ident.: DSC-22_10-40-40-00010677.0001001 / 17 AUG 10 Applicable to: ALL
The Flight Management and Guidance System generates the following information to the EFIS Primary Flight Display: ‐ Armed and engaged modes on the Flight Mode Annunciator (FMA) ‐ FMGS guidance targets (SPD, ALT, HDG) ‐ Vertical deviation from descent profile ‐ Messages ‐ Navigation information. CLIMB PHASE Ident.: DSC-22_10-40-40-00010121.0001001 / 14 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
DSC-22_10-40-40 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
PILOT INTERFACE - PRIMARY FLIGHT DISPLAY
FLIGHT CREW OPERATING MANUAL
APPROACH PHASE Ident.: DSC-22_10-40-40-00010122.0013001 / 14 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-22_10-40-40 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PILOT INTERFACE - NAVIGATION DISPLAY
ND Ident.: DSC-22_10-40-50-00010123.0001001 / 17 AUG 10 Applicable to: ALL
The FMGS generates the following information, displayed on the EFIS Navigation Displays: ‐ Flight plan (active secondary, temporary, dashed) ‐ Aircraft position and lateral deviation from the flight plan ‐ Pseudo-waypoints along the flight plan ‐ Raw data from tuned Navaids and type of selected approach ‐ Various display options (waypoints, Navaids, NDBs, airports, constraints) ‐ Wind information and various messages. ARC MODE Ident.: DSC-22_10-40-50-00010124.0001001 / 14 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
DSC-22_10-40-50 P 1/4 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PILOT INTERFACE - NAVIGATION DISPLAY
PLAN MODE Ident.: DSC-22_10-40-50-00010125.0001001 / 17 AUG 10 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-22_10-40-50 P 2/4 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
PILOT INTERFACE - NAVIGATION DISPLAY
FLIGHT CREW OPERATING MANUAL
ROSE MODES Ident.: DSC-22_10-40-50-00010126.0022001 / 16 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D
DSC-22_10-40-50 P 3/4 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
PILOT INTERFACE - NAVIGATION DISPLAY
FLIGHT CREW OPERATING MANUAL
FLIGHT PLAN DISPLAY COLORS Ident.: DSC-22_10-40-50-00010127.0002001 / 17 AUG 10 Applicable to: ALL
F-PLN Primary Flight Plan
Color
Track line Alternate flight plan Missed approach Offset flight plan Temporary flight plan Engine-out SID (not inserted) Secondary flight plan Abeam/Radial
Steady green Dashed blue Steady blue Steady green (Original flight plan: Dashed green) Dashed yellow Steady yellow Steady dimmed white Dashed blue
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
‐ Managed mode: Steady green ‐ Selected mode: Dashed green
E
DSC-22_10-40-50 P 4/4 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-22_10-50-00000410.0183001 / 25 JUL 12 Applicable to: ALL 1
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-22_10-50 P 1/4 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
E/WD: FAILURE TITLE conditions
FAC 1 (2) FAULT
AURAL WARNING MASTER LIGHT SINGLE CHIME
MASTER CAUT
NIL
NIL
SD PAGE CALLED
LOCAL WARNING FAC FAULT lt
YAW DAMPER 1 (2) RUDDER TRIM 1 (2) FAULT RUD TRV LIM 1 (2) FCU 1 (2) FAULT FAC 1 + 2 FAULT YAW DAMPER SYS RUD TRIM SYS RUD TRV LIM SYS A/THR OFF
NIL
NIL
FAC FAULT lts
FLT PHASE INHIB 3, 4, 5, 7, 8 3, 4, 5, 7, 8, 10 3, 4, 5, 7, 8 4, 5, 7, 8 4, 5, 7, 8, 10
F/CTL SINGLE CHIME
4, 5, 7, 8 4, 5
MASTER CAUT
A/THR disconnection (Refer to DSC-22_30-90-B A/THR Disconnection General).
4, 8, 10
A/THR LIMITED
A/THR is active but thrust levers are set below CL detent (2 engines), or MCT detent (1 engine).
FCU 1 + 2 FAULT AP OFF
SINGLE CHIME every 5 s
MASTER CAUT every 5 s
1, 2, 3, 4, 8, 9, 10
SINGLE CHIME
MASTER CAUT
3, 4, 5, 7, 8
AP disengagement (Refer CAVALRY CHARGE MASTER WARN to DSC-22_30-30 AP Disengagement).
NIL NIL
-
(ILS) CAPABILITY DOWNGRADE
‐ Condition(s) required for CAT3/CAT2 are no longer fulfilled. (Refer to PRO-NOR-SRP-01-70 Failures and Associated Actions Above 1 000 ft for CAT II or CAT III). ‐ Mode reversions Refer to DSC-22_30-10 Mode Reversions
TRIPLE CLICK
NIL
2, 3, 4, 5, 8, 9, 10
Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
DSC-22_10-50 P 2/4 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
E/WD: FAILURE TITLE conditions
WINDSHEAR
No ECAM message.
WINDSHEAR DET FAULT or REAC W/S DET FAULT LOW ENERGY WARNING
Available between 100 and 2 000 ft in CONF ≥ 2. No ECAM message.
AURAL WARNING MASTER LIGHT SYNTHETIC VOICE "WINDSHEAR" repeated 3 times
(No ECAM message) Only available below 200 ft. When GPS primary is lost, the ″GPS PRIMARY LOST ″ message is displayed on the ND and PFD.
Continued from the previous page FLT PHASE LOCAL WARNING INHIB
"WINDSHEAR" on PFDs
SINGLE CHIME
MASTER CAUT
SYNTHETIC VOICE "SPEED" 3 times every 5 s
NIL
AUTOLAND
SD PAGE CALLED
2, 3, 4, 8, 9
3, 4, 5, 8
NIL
AUTOLAND (red) on glareshield
1, 2, 3, 4, 8, 9, 10
2, 3, 4, 5, 8, 9, 10
NIL NIL
ND/MCDU message
MASTER CAUT
NIL
NAV FMS/GPS POS DISAGREE
Is triggered, when FMS 1 or 2 position differs from GPS 1 or 2 position by more than: ‐ A longitude threshold that depends on the latitude: • 0.5 min for latitudes below 55 °, • 0.9 min for latitudes at or above 55 °, and below 70 °, ‐ A latitude threshold of 0.5 min , regardless of the latitude.
SINGLE CHIME
1, 3, 4, 10
Above 70 ° of latitude, a longitude difference does not trigger the alarm.
TCAS MODE FAULT 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
3, 4, 5, 7 Continued on the following page
←A→
DSC-22_10-50 P 3/4 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
E/WD: FAILURE TITLE conditions TCAS flight guidance mode is operative
WARNINGS AND CAUTIONS
AURAL WARNING MASTER LIGHT
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
SD PAGE CALLED
Continued from the previous page FLT PHASE LOCAL WARNING INHIB
DSC-22_10-50 P 4/4 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-22_10-60-00000411.0001001 / 09 DEC 09 Applicable to: ALL
NORM AC 1 2 1 2
FMGC MCDU 3 FCU
EMER ELEC DC ESS SHED
HOT
DC2 SHED AC2 AC1
1 2
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DC
AC ESS
X DC2
A
DSC-22_10-60 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS AUTO FLIGHT - GENERAL A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_10-60 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT
Intentionally left blank
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
1
DSC-22_20-PLP PRELIMINARY PAGES TABLE OF CONTENTS SUMMARY OF HIGHLIGHTS
DSC-22_20-10 General General.....................................................................................................................................................................A
DSC-22_20-20 Navigation DSC-22_20-20-05 General Navigation................................................................................................................................................................ A
DSC-22_20-20-10 Position Computation General.....................................................................................................................................................................A MIX IRS Position..................................................................................................................................................... B GPS Position........................................................................................................................................................... C Radio Position..........................................................................................................................................................D FM Position.............................................................................................................................................................. E Position Monitor....................................................................................................................................................... F Takeoff Update (GPS PRIMARY not Active)..........................................................................................................G Navigation Modes.................................................................................................................................................... H
DSC-22_20-20-20 Evaluation of Position Accuracy General.....................................................................................................................................................................A Estimated Position Uncertainty................................................................................................................................B FM/GPS Position Disagreement..............................................................................................................................C Predictive GPS Page...............................................................................................................................................D Navigation Accuracy Check.....................................................................................................................................E
DSC-22_20-20-30 Radio Navigation Tuning General.....................................................................................................................................................................A Architecture.............................................................................................................................................................. B VOR......................................................................................................................................................................... C DME......................................................................................................................................................................... D ADF.......................................................................................................................................................................... E ILS............................................................................................................................................................................ F Selection of Navaids on MCDU Pages...................................................................................................................G Manual Tuning......................................................................................................................................................... H Navaid Identification.................................................................................................................................................. I 2
DSC-22_20-20-40 Alignment of Inertial Reference System Alignment of Inertial Reference System..................................................................................................................A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-PLP-TOC P 1/8 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_20-20-50 Navigation Database General.....................................................................................................................................................................A Operations with an Outdated Navigation Database................................................................................................B
DSC-22_20-30 Flight Planning DSC-22_20-30-05 General Flight Planning......................................................................................................................................................... A
DSC-22_20-30-10 Lateral Functions DSC-22_20-30-10-05 General General.....................................................................................................................................................................A Manual Legs............................................................................................................................................................ B Flight Plan Construction.......................................................................................................................................... C Flight Plan Capacity................................................................................................................................................ D Lateral Revisions..................................................................................................................................................... E
DSC-22_20-30-10-15 FMS2 HONEYWELL General.....................................................................................................................................................................A Temporary F-PLN (TMPY)...................................................................................................................................... B Inserting an Airway with "Via"................................................................................................................................. C Inserting a Waypoint................................................................................................................................................D Fix Info..................................................................................................................................................................... E Inserting a New Destination.....................................................................................................................................F Holding Pattern........................................................................................................................................................G Offset........................................................................................................................................................................H Alternate Function..................................................................................................................................................... I Enable ALTN............................................................................................................................................................ J DIR Key (Direct-to-Function)................................................................................................................................... K OVFY (Overfly) Key................................................................................................................................................. L "Update at".............................................................................................................................................................. M
DSC-22_20-30-20 Vertical Functions DSC-22_20-30-20-05 General General.....................................................................................................................................................................A Vertical Flight Planning............................................................................................................................................B Flight Phases........................................................................................................................................................... C Vertical Revision...................................................................................................................................................... D Vertical Constraints (Speed, Altitude, Time)........................................................................................................... E
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-PLP-TOC P 2/8 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_20-30-20-25 FMS2 Honeywell General.....................................................................................................................................................................A Required Time of Arrival (RTA)...............................................................................................................................B Wind - Temperature - QNH.....................................................................................................................................C Constant Mach Segment.........................................................................................................................................D
DSC-22_20-40 Performance DSC-22_20-40-10 Optimization General.....................................................................................................................................................................A Optimization............................................................................................................................................................. B
DSC-22_20-40-20 Cost Index Cost Index (CI)........................................................................................................................................................ A
DSC-22_20-40-30 Predictions General.....................................................................................................................................................................A Predictions for the Primary Flight Plan................................................................................................................... B Computation of Predictions..................................................................................................................................... C Predictions Displayed on the Navigation Display................................................................................................... D Predictions Displayed on the MCDU.......................................................................................................................E Type of Predictions.................................................................................................................................................. F Examples of MCDU Predictions..............................................................................................................................G Constraint Symbols (Star)....................................................................................................................................... H Vertical Deviation...................................................................................................................................................... I Operation Rules Concerning Predictions.................................................................................................................J Other Computations.................................................................................................................................................K Return-to-Trajectory Assumptions............................................................................................................................L IDLE Factor............................................................................................................................................................. M Energy Circle........................................................................................................................................................... N PERF Factor............................................................................................................................................................O
DSC-22_20-50 Controls and Indicators DSC-22_20-50-10 MCDU - Page Description DSC-22_20-50-10-25 FMS2 Honeywell General.....................................................................................................................................................................A MCDU MENU Page.................................................................................................................................................B INIT A Page.............................................................................................................................................................C Route Selection Page..............................................................................................................................................D IRS INIT Page......................................................................................................................................................... E WIND Pages............................................................................................................................................................ F INIT B Page.............................................................................................................................................................G
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-PLP-TOC P 3/8 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Fuel Prediction Page............................................................................................................................................... H Flight Plan Pages......................................................................................................................................................I Lateral Revision Pages............................................................................................................................................ J Fix Info Page........................................................................................................................................................... K Offset Page.............................................................................................................................................................. L Airways Page.......................................................................................................................................................... M Departure Pages......................................................................................................................................................N Hold Pages.............................................................................................................................................................. O Direct TO Page........................................................................................................................................................P ARRIVAL Pages...................................................................................................................................................... Q Alternate Page......................................................................................................................................................... R Route Selection Page for Alternate.........................................................................................................................S VERTICAL REVISION Pages..................................................................................................................................T Step ALTS Page......................................................................................................................................................U RTA Page................................................................................................................................................................ V Data Index Pages................................................................................................................................................... W Waypoint/Stored Waypoint/New Waypoint Pages...................................................................................................X NAVAID/Stored NAVAID/New NAVAID Pages....................................................................................................... Y Runways/Stored Runways/New Runway Pages..................................................................................................... Z Route/Stored Route/New Route Pages................................................................................................................ AA Aircraft Status Page.............................................................................................................................................. AB P/N XLOAD Page................................................................................................................................................. AC P/N Status Pages..................................................................................................................................................AD Duplicate Names Page......................................................................................................................................... AE Position Monitor Page........................................................................................................................................... AF Position Monitor and Position Frozen Page......................................................................................................... AG Selected NAVAIDS Page......................................................................................................................................AH IRS Monitor Page................................................................................................................................................... AI GPS Monitor Page.................................................................................................................................................AJ Closest Airports Pages..........................................................................................................................................AK Equi-Time Point Page............................................................................................................................................AL Print Function Pages............................................................................................................................................ AM ACARS Function Page......................................................................................................................................... AN ACARS Function Page 1......................................................................................................................................AO Uplink TO Data REQ Pages................................................................................................................................. AP Uplink MAX TO Data Pages.................................................................................................................................AQ Uplink FLX TO Data Pages.................................................................................................................................. AR ACARS Function Page 2...................................................................................................................................... AS PERF Page............................................................................................................................................................AT PERF Takeoff Page.............................................................................................................................................. AU PERF Climb Page................................................................................................................................................. AV PERF Cruise Page...............................................................................................................................................AW
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-PLP-TOC P 4/8 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PERF Descent Page............................................................................................................................................. AX PERF APPR Page................................................................................................................................................ AY PERF Go Around Page.........................................................................................................................................AZ PROG Pages.........................................................................................................................................................BA Predictive GPS Pages...........................................................................................................................................BB Report Page.......................................................................................................................................................... BC Radio NAV Page...................................................................................................................................................BD Secondary Pages.................................................................................................................................................. BE Back Up NAV Pages.............................................................................................................................................BF
DSC-22_20-50-20 MCDU - Messages DSC-22_20-50-20-35 FMS2 Honeywell MCDU Message List................................................................................................................................................A
DSC-22_20-50-30 MCDU - Data Format List MCDU Data Format List..........................................................................................................................................A 3
DSC-22_20-60 Other Functions DSC-22_20-60-10 Effect of Baro Reference Setting GENERAL................................................................................................................................................................ A MCDU Altitude Predictions...................................................................................................................................... B Target Altitude on PFD........................................................................................................................................... C Procedures...............................................................................................................................................................D
DSC-22_20-60-20 Clear Key (Clearing Function) Clearing the Scratchpad of Data or Messages.......................................................................................................A Clearing Data Fields................................................................................................................................................ B
DSC-22_20-60-30 How to Execute a Diversion General.....................................................................................................................................................................A En Route Diversion with Several Airports Available............................................................................................... B En Route Diversion over Oceanic or Desertic Area............................................................................................... C Diversion Preparation on the Secondary Flight Plan..............................................................................................D Miscellaneous...........................................................................................................................................................E Execution of the Diversion.......................................................................................................................................F Diversion to the Alternate Airport............................................................................................................................G
DSC-22_20-60-40 Engine Out General.....................................................................................................................................................................A Flight Management Part.......................................................................................................................................... B Flight Guidance Part................................................................................................................................................C Autothrust.................................................................................................................................................................D Engine-Out Conditions.............................................................................................................................................E
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-PLP-TOC P 5/8 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Engine-Out SID........................................................................................................................................................ F Engine-Out in CLB Phase (above acceleration altitude)........................................................................................ G Engine-Out in Cruise Phase....................................................................................................................................H Engine-Out in Descent Phase.................................................................................................................................. I Engine-Out In Approach Phase............................................................................................................................... J Engine-Out in Go-Around Phase.............................................................................................................................K
DSC-22_20-60-50 Secondary Flight Plan Secondary Flight Plan............................................................................................................................................. A
DSC-22_20-60-60 Pilots/Stored Route Function Stored Route Function.............................................................................................................................................A
DSC-22_20-60-70 Report Page General.....................................................................................................................................................................A Report Page Acces..................................................................................................................................................B
DSC-22_20-60-80 Closest Airports Closest Airports........................................................................................................................................................A
DSC-22_20-60-90 Time Marker General.....................................................................................................................................................................A How to Insert a Time Marker.................................................................................................................................. B
DSC-22_20-60-100 Step ALTS Step Climb/Step Descent........................................................................................................................................ A
DSC-22_20-60-110 Required Time of Arrival (RTA) General.....................................................................................................................................................................A Estimated Takeoff Time (ETT)................................................................................................................................ B
DSC-22_20-60-120 Equitime Point Equitime Point..........................................................................................................................................................A Equitime Point Entry................................................................................................................................................ B
DSC-22_20-60-130 MCDU Back Up Navigation General.....................................................................................................................................................................A Back Up NAV Selection.......................................................................................................................................... B Back Up NAV Operation......................................................................................................................................... C
DSC-22_20-70 AOC Functions Flight Plan Initialization Through ACARS................................................................................................................A Takeoff Data............................................................................................................................................................ B Wind Data................................................................................................................................................................ C
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-PLP-TOC P 6/8 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_20-80 Print Functions Print Function...........................................................................................................................................................A Print Function Access..............................................................................................................................................B On Ground Before Engine Start..............................................................................................................................C Example (FM Preflight Report)................................................................................................................................D In Flight.................................................................................................................................................................... E Example (FM Inflight Report)...................................................................................................................................F Reaching the Gate After Landing........................................................................................................................... G Example (FM Postflight Report).............................................................................................................................. H
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-PLP-TOC P 7/8 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-PLP-TOC P 8/8 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title
Toc Index
ID
Reason
DSC-22_20-PLP-TOC Auto Flight - Flight Management
1
DSC-22_20-PLP-TOC Alignment of Inertial Reference System
2
DSC-22_20-PLP-TOC Other Functions
3
Documentation update: Deletion of the "00013372.0001001 General" documentary unit. Documentation update: Deletion of the "00013373.0001001 Description - ADIRS" documentary unit. Documentation update: Deletion of the "00013374.0001001 Description - FMGS" documentary unit. Documentation update: Deletion of the "00013375.0003001 Description - EIS PFD/ND" documentary unit. Documentation update: Deletion of the "00013377.0001001 Description - ADF and VOR Bearing Display" documentary unit. Documentation update: Deletion of the "00013378.0001001 Description - DDRMI" documentary unit. Documentation update: Deletion of the "00013429.0001001 Procedures - IRS Alignment" documentary unit. Documentation update: Deletion of the "00013430.0003001 Procedures - Flight" documentary unit. Documentation update: Deletion of the "NP02951 Polar Navigation" table of content entry. Documentation update: Deletion of the "00010145 Polar Navigation" table of content entry. Documentation update: Deletion of the "00010145.0001001 Polar Navigation" documentary unit. Documentation update: Deletion of the "NP00199 Polar Navigation" table of content entry. Documentation update: Deletion of the "00006025.0001001 GENERAL" documentary unit. Documentation update: Deletion of the "00009534.0001001 DESCRIPTION" documentary unit. Documentation update: Deletion of the "00009535.0001001 PROCEDURES" documentary unit. Update of "Back Up Nav Pages" description in order to reflect all aircraft configurations. All the information related to "Polar Navigation function" are now identified in this DU by an "if installed" symbol. Update of "Back Up Nav Pages" description in order to reflect all aircraft configurations. All the information related to "Polar Navigation function" are now identified in this DU by an "if installed" symbol.
DSC-22_20-50-10-25 Back Up NAV Pages
BF
1
DSC-22_20-50-10-25 Back Up NAV Pages
BF
2
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-PLP-SOH P 1/2 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-PLP-SOH P 2/2 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-22_20-10-00010128.0001001 / 17 AUG 10 Applicable to: ALL
The flight management and guidance system (FMGS) performs navigation functions and lateral and vertical flight planning functions. It also computes performance parameters and guides the aircraft along a preplanned route. The Flight Management (FM) part controls the following functions: ‐ Navigation ‐ Management of flight planning ‐ Prediction and optimization of performance ‐ Management of navigation radios ‐ Management of displays
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-22_20-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
NAVIGATION - GENERAL
FLIGHT CREW OPERATING MANUAL
NAVIGATION Ident.: DSC-22_20-20-05-00010129.0001001 / 17 AUG 10 Applicable to: ALL
Essential navigation functions are: ‐ Computation of position ‐ Evaluation of position accuracy ‐ Radio navigation tuning ‐ Alignment of Inertial Reference System.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-22_20-20-05 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
NAVIGATION - GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-20-05 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
NAVIGATION - POSITION COMPUTATION
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-22_20-20-10-00010130.0002001 / 16 MAR 11 Applicable to: ALL
Each FMGC computes its own aircraft position (called the "FM position") from a MIX IRS position and a computed radio position, or a GPS position. The FMGS selects the most accurate position, considering the estimated accuracy and integrity of each positioning equipment. GPS/INERTIAL is the basic navigation mode, provided GPS data is valid and successfully tested. Otherwise, navaids plus inertial or inertial only are used. (Refer to DSC-22_20-20-10 Navigation Modes). MIX IRS POSITION Ident.: DSC-22_20-20-10-00010131.0002001 / 17 AUG 10 Applicable to: ALL
Each FMGC receives a position from each of the three IRSs, and computes a mean-weighted average called the “MIX IRS” position:
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-22_20-20-10 P 1/8 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NAVIGATION - POSITION COMPUTATION
‐ If one of the IRSs drifts abnormally, the MIX IRS position uses an algorithm that decreases the influence of the drifting IRS within the MIX IRS position.
‐ If one of the IRSs fails, each FMGC uses only one IRS (onside IRS or IRS3). Each IRS position and inertial speed are continuously tested. If the test fails, the corresponding IRS is rejected. ‐ When the "CHECK IRS (1, 2 or 3)/FM POSITION" message appears on the MCDU. GPS POSITION Ident.: DSC-22_20-20-10-00010132.0002001 / 14 MAY 12 Applicable to: ALL
Each IRS computes a mixed IRS/GPS position called the GPIRS position. For this, each IRS can independently select their GPS source in order to maximize the availability of GPS data. Of the three GPIRS positions that each FMGC receives, the FMS selects one GPIRS position based on a figure of merit and priority. The FMS uses the following hierarchy to perform the selection: ‐ Onside GPIRS position ‐ GPIRS 3 ‐ Opposite GPIRS position. If the GPIRS data does not comply with an integrity criterion that is based on a Horizontal Integrity Limit (HIL) and on the automatic detection of failed satellites, the FMS rejects the GPS mode and uses the radio position update. The flight crew can deselect/select the GPS position on the SELECTED NAVAIDS page, if necessary.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
DSC-22_20-20-10 P 2/8 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
NAVIGATION - POSITION COMPUTATION
FLIGHT CREW OPERATING MANUAL
Information about the GPS position is displayed on the GPS MONITOR page.
Note:
In normal operations, all ADIRUs may select the same GPS source. As a result, the data of the GPS that is not selected may be dashed on the GPS MONITOR page, without any detected GPS failure or triggered “GPS PRIMARY LOST” message. RADIO POSITION
Ident.: DSC-22_20-20-10-00010669.0020001 / 16 MAR 11 Applicable to: ALL
Each FMGC uses onside navaids to compute its own radio position. These navaids are displayed on the SELECTED NAVAIDS page. The available navaids are: ‐ DME/DME ‐ VOR/DME ‐ LOC
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← C to D →
DSC-22_20-20-10 P 3/8 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NAVIGATION - POSITION COMPUTATION
‐ DME/DME-LOC ‐ VOR/DME-LOC. It uses LOC to update the lateral position, using LOC beam during ILS approach. LOC is also used for quick update, when in GPS/IRS mode. If one or more navaids fail, each FMGC can use offside navaids to compute the VOR/DME, or the DME/DME radio position. The radio navaid selection is displayed on the DATA “SELECTED NAVAIDS” page.
(1)
VOR/DME selection (auto or manual) for display (onside VOR).
(2)
DMEs automatic selection for DME/DME onside radio position.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-22_20-20-10 P 4/8 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
NAVIGATION - POSITION COMPUTATION
FLIGHT CREW OPERATING MANUAL
(3)
ILS selection (auto or manual) for LOC update computation. FM POSITION
Ident.: DSC-22_20-20-10-00010135.0017001 / 17 AUG 10 Applicable to: ALL
At flight initialization, each FMGC displays an FM position that is a MIX IRS/GPS position (GPIRS): ‐ At takeoff, when the FM position is updated to the runway threshold position as stored in the database, possibly corrected by the takeoff shift entered on PERF TO page. ‐ In flight, the FM position approaches the radio position or the GPS position at a rate depending upon the aircraft altitude. Note:
The FM position update at takeoff is inhibited when GPS PRIMARY is active.
BIAS Each FMGC computes a vector from its MIX IRS position to the radio position or GPIRS position. This vector is called the “bias”. Each FMGC updates its bias continuously as long as a radio position or a GPIRS position is available. If an FMGC loses its radio/GPIRS position, it memorizes the bias and uses it to compute the FM position, which equals the MIX IRS position plus the bias. Until the radio or the GPIRS position is restored, the bias does not change. The flight crew can update the FM position manually. This also updates the bias. POSITION MONITOR Ident.: DSC-22_20-20-10-00010136.0016001 / 17 AUG 10 Applicable to: ALL
The flight crew may check the position computation using the GPS MONITOR or POSITION MONITOR page.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← D to F →
DSC-22_20-20-10 P 5/8 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NAVIGATION - POSITION COMPUTATION
TAKEOFF UPDATE (GPS PRIMARY NOT ACTIVE) Ident.: DSC-22_20-20-10-00010137.0017001 / 17 AUG 10 Applicable to: ALL
A takeoff update requires that the takeoff runway be part of the flight plan. This provides the most accurate position update. If the takeoff run starts at an intersection, enter a takeoff shift on the PERF TO page to refine the takeoff update. An accurate takeoff update ensures a precise aircraft position during departure.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← F to G →
DSC-22_20-20-10 P 6/8 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
NAVIGATION - POSITION COMPUTATION
FLIGHT CREW OPERATING MANUAL
NAVIGATION MODES Ident.: DSC-22_20-20-10-00010138.0001001 / 19 JUL 11 Applicable to: ALL
The FMGS updates the FM position via the use of radio navaids or GPS, if available. It can use four different FM navigation modes to make this update. The decreasing order of priority is: ‐ IRS-GPS ‐ IRS-DME/DME ‐ IRS-VOR/DME ‐ IRS only. During ILS approaches, the system performs a temporary lateral update, via one of the following modes: ‐ IRS-GPS/LOC ‐ IRS-DME/DME-LOC ‐ IRS-VOR/DME-LOC ‐ IRS-LOC.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← G to H
DSC-22_20-20-10 P 7/8 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
NAVIGATION - POSITION COMPUTATION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-20-10 P 8/8 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NAVIGATION - EVALUATION OF POSITION ACCURACY
GENERAL Ident.: DSC-22_20-20-20-00010448.0023001 / 17 AUG 10 Applicable to: ALL
The FMGS continuously computes an Estimated Position Uncertainty (EPU). It is an estimate of how much the FM position diverged, and it is a function of the navigation mode that the system uses. CURRENT NAV MODE
EPU (RATE or THRESHOLD)
IRS/GPS IRS/DME/DME IRS/VOR/DME IRS ONLY
Note:
(in meters). Moves toward 0.28 nm. 0.1 nm + 0.05 X DME DIST. Minimum : 0.28 nm. +8 kt for the first 30 min. 0 kt for the following 60 min. +4 kt for the following 30 min. 0 kt for the following 60 min. +2 kt after.
REMARK FOM = Figure of Merit of GPS. If above 0.28 nm, the FMS rejects the GPS position. EPU decreases from initial value to 0.28 nm. Dependent on the distance between the aircraft and the VOR/DME. EPU increases continuously.
After an IRS alignment or at takeoff, the EPU is set to 0.2 nm. ESTIMATED POSITION UNCERTAINTY
Ident.: DSC-22_20-20-20-00010499.0076001 / 19 JUL 11 Applicable to: ALL
The FMS displays the EPU to the flight crew and compares it with the Required Navigation Performance (RNP): ‐ If the EPU does not exceed the RNP, accuracy is HIGH ‐ If the EPU exceeds the RNP, accuracy is LOW. The RNP is displayed in the REQUIRED field of the PROG page. The displayed RNP is (in a decreasing order of priority): ‐ The value that the flight crew entered ‐ The navigation database procedure value ‐ The system’s default value. When a flight crew enters an RNP that is higher than the published value, one of the following messages is displayed : "PROCEDURE RNP IS XX.XX", or "AREA RNP IS XX.XX". When this occurs, the flight crew should verify the RNP value that was manually entered in the REQUIRED field of the PROG page, and clear or modify it if necessary. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-22_20-20-20 P 1/6 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NAVIGATION - EVALUATION OF POSITION ACCURACY
The "AREA RNP IS XX.XX" message is also displayed at the change of flight area if the new RNP (default value) is smaller than the displayed RNP (manually entered). DEFAULT AREA RNP VALUES EN ROUTE TERMINAL APPROACH
2.0 nm 1.0 nm GPS 0.3 nm OTHER CASES 0.5 nm
When one FMGC changes the NAV accuracy from LOW to HIGH (or HIGH to LOW), the MCDU and the ND display the "NAV ACCUR UPGRAD" (or DOWNGRAD) message. These messages are inhibited when the navigation mode is IRS/GPS.
When in IRS/GPS mode, the GPS PRIMARY status combines two different criteria: ‐ The accuracy criterion previously described (HIGH/LOW accuracy) ‐ An integrity criterion: This is the capability to detect a failure and provide appropriate warning of it. This criterion indicates the confidence that the flight crew can have in the FMS position. If the GPS PRIMARY status complies with both criteria, "GPS PRIMARY" is displayed on the MCDU (PROG page, [5R] field and scratchpad) and temporarily on the ND. If the GPS PRIMARY status no longer complies with one of these criteria (Navigation downgraded or integrity lost), the GPS PRIMARY status is lost and the MCDU and the ND display the "GPS PRIMARY LOST" message. It is possible to clear the scratchpad message on the MCDU, but not on the ND. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
DSC-22_20-20-20 P 2/6 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
CAUTION
NAVIGATION - EVALUATION OF POSITION ACCURACY
"HIGH" or "LOW" on the PROG page indicates the FM position accuracy, based on estimated uncertainty. When GPS PRIMARY mode is lost, the flight crew must periodically check this position accuracy. In GPS PRIMARY mode, the position accuracy is always at HIGH.
When the GPS is manually deselected, the "GPS IS DESELECTED" message is displayed on the MCDU, 80 nm before the T/D or at approach phase transition. FM/GPS POSITION DISAGREEMENT Ident.: DSC-22_20-20-20-00010500.0011001 / 17 AUG 10 Applicable to: ALL
When the GPS PRIMARY function is active, and either of the FM positions deviate from the GPS positions 1 or 2 by more than: ‐ A longitude threshold that depends on the latitude: • 0.5' for latitudes below 55° • 0.9' for latitudes at or above 55°, and below 70°. ‐ A latitude threshold of 0.5', regardless of the latitude, then, the lower ECAM displays the NAV FM/GPS POS DISAGREE amber caution. The master caution light comes on and the single chime sounds. This amber caution is inhibited during the takeoff phase. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
DSC-22_20-20-20 P 3/6 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NAVIGATION - EVALUATION OF POSITION ACCURACY
Above 70° of latitude, a longitude difference does not trigger the alarm. PREDICTIVE GPS PAGE Ident.: DSC-22_20-20-20-00010501.0001001 / 16 MAR 11 Applicable to: ALL
The predictive GPS page is only operative with the Honeywell ADIRS equipment. All fields are blank with Litton ADIRS equipment. The predictive GPS function predicts the availability of the GPS within ± 15 min of ETA at destination, or at any waypoint entered by the flight crew.
Predictions are displayed on the predictive GPS page at time intervals of 5 min (+15 and –15 min of ETA). To access this page, press the 5L key of the PROG page. This page also enables the deselection of up to 4 satellites at a time. NAVIGATION ACCURACY CHECK Ident.: DSC-22_20-20-20-00010625.0015001 / 14 MAY 12 Applicable to: ALL
When GPS PRIMARY is available, the navigation accuracy check is not required. When GPS PRIMARY is not available, the flight crew must perform this essential check: ‐ Periodically in cruise ‐ At 10 000 ft in descent. When entering a terminal/approach area, the flight crew must monitor navigation accuracy only.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← C to E →
DSC-22_20-20-20 P 4/6 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NAVIGATION - EVALUATION OF POSITION ACCURACY
The procedure is: ‐ While en route, check the HIGH/LOW accuracy information. • If accuracy is "LOW" (and whenever "NAV ACCUR DOWNGRAD" appears), compare raw data from the tuned navaids with the corresponding FM computed data on the ND or the MCDU PROG page • If accuracy is "HIGH", periodically perform the comparison (about once per hour). ‐ In descent, and in terminal and approach areas, validate the estimated accuracy, whether it is "HIGH" or "LOW", by comparing the FM data with the raw data from the VOR/DME at the destination airfield, if available.
This check verifies and quantifies the FM accuracy. It confirms the reliability of FMGS data itself and navigation display presentation. It also validates the use of the NAV mode. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-22_20-20-20 P 5/6 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NAVIGATION - EVALUATION OF POSITION ACCURACY
By comparing the bearing, the flight crew may evaluate the validity of the overall check. In area with high magnetic variation change, the comparison of bearings may not be adequate.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E
DSC-22_20-20-20 P 6/6 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NAVIGATION - RADIO NAVIGATION TUNING
GENERAL Ident.: DSC-22_20-20-30-00010478.0001001 / 17 AUG 10 Applicable to: ALL
Radio navaids are tuned for two different purposes: Display and computation. It is possible to perform tuning for display in three different ways: ‐ Automatic tuning via FMGC software ‐ Manual tuning via the MCDU RAD NAV page ‐ Manual tuning via the Radio Management Panel (RMP) if both FMGCs or both MCDUs fail. The FMGS automatically tunes the radio navaids for computation of the radio position. Note:
The manual selection of a VOR or VOR/DME may prevent the FMGS from automatically tuning a VOR/DME to compute position. In this case, the related MCDU displays “TUNE BBB FFF.FF” (BBB = ident, FFF.FF = frequency). ARCHITECTURE
Ident.: DSC-22_20-20-30-00010479.0001001 / 17 AUG 10 Applicable to: ALL
‐ In dual mode and independent mode, each FMGC simultaneously tunes the navaids on its own side (one VOR, one DME, one ILS and one ADF). In these modes, the flight crew can also manually tune the VOR (and associated DME), ILS, and ADF. ‐ In single mode, the valid FMGC tunes navaids on both sides. The flight crew can also use the RAD NAV page to manually tune both VORs, both ADFs and the ILS. Manual tuning has priority over automatic tuning. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-22_20-20-30 P 1/6 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Note:
NAVIGATION - RADIO NAVIGATION TUNING
If one radio receiver fails, both FMGCs use the operative radio receiver to compute the position of the aircraft. VOR
Ident.: DSC-22_20-20-30-00010480.0001001 / 17 AUG 10 Applicable to: ALL
Each FMGC may tune only one VOR (manually or automatically). Automatic tuning complies with the following priorities for tuning the VOR: 1. The specified navaid for the approach 2. The navaid that the flight crew should use to compute the current radio position 3. For display purposes: ‐ A navaid specified for the active flight leg ‐ The “TO” waypoint (TO WPT), if it is a navaid ‐ The “FROM” waypoint (FROM WPT), if it is a navaid ‐ A waypoint farther along the flight path, if it is a navaid ‐ The navaid closest to the current position of the aircraft. The scratchpad displays “SPECIFIC VOR-D UNAVAIL”, if the VOR or the VOR/DME that the flight crew requires for tuning is deselected. DME Ident.: DSC-22_20-20-30-00010481.0002001 / 17 AUG 10 Applicable to: ALL
Each FMGC automatically uses its four DME frequencies as follows: ‐ One DME frequency for display. It is possible to tune it manually or automatically. This DME frequency is also used for VOR/DME position computation. ‐ Two DME frequencies in DME/DME mode for calculating the radio position of the aircraft. The FMGC automatically tunes these as a function of their best accuracy. The flight crew does not receive any indication that this process is happening. ‐ One DME frequency is connected to the ILS/DME. ADF Ident.: DSC-22_20-20-30-00010482.0001001 / 17 AUG 10 Applicable to: ALL
The FMGC automatically tunes one ADF, when the flight plan specifies a Non Directional Beacon (NDB) approach and a fix in the approach is the “TO” waypoint.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to E →
DSC-22_20-20-30 P 2/6 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NAVIGATION - RADIO NAVIGATION TUNING
The scratchpad displays “SPECIFIC NDB UNAVAIL”, if the NDB that the flight crew requires for autotuning is deselected. ILS Ident.: DSC-22_20-20-30-00010483.0001001 / 17 AUG 10 Applicable to: ALL
Each FMGC automatically tunes one ILS frequency: ‐ In the PREFLIGHT or TAKEOFF phase, when the takeoff runway has an associated ILS. ‐ In the CLIMB, CRUISE, DESCENT, APPROACH, or GO-AROUND phase, when the type of approach in the flight plan is ILS. The scratchpad displays “RWY/ILS MISMATCH” when the flight crew manually tunes the ILS and the entered frequency does not agree with the ILS or the LOC IDENT/FREQ that the flight crew requests for automatic tuning. The FMGS logic does not enable the flight crew to modify the course of an ILS when its frequency is identical to the ILS selected in the F-PLN. SELECTION OF NAVAIDS ON MCDU PAGES Ident.: DSC-22_20-20-30-00010485.0033001 / 19 JUL 11 Applicable to: ALL
The MCDU displays the navaids tuned by the FMGC on two pages: ‐ RADIO NAV Page ‐ SELECTED NAVAIDS Page. RADIO NAV PAGE This page shows which navaids have been tuned automatically or manually for display purposes.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← E to G →
DSC-22_20-20-30 P 3/6 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
NAVIGATION - RADIO NAVIGATION TUNING
FLIGHT CREW OPERATING MANUAL
SELECTED NAVAIDS PAGE This page lists the navaids tuned by the onside FMGC. No navaids can be modified on this page. The flight crew may deselect as many as four unreliable navaids for the whole flight (using 1R key, or deselect them all, using 5L key).
MANUAL TUNING Ident.: DSC-22_20-20-30-00010486.0052001 / 29 MAR 12 Applicable to: ALL
WRITE the identifier on the RADIO NAV page. Preferably use the identifier.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← G to H →
DSC-22_20-20-30 P 4/6 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
NAVIGATION - RADIO NAVIGATION TUNING
FLIGHT CREW OPERATING MANUAL
If the MCDU displays “NOT IN DATA BASE”: WRITE the frequency. DISREGARD the ident that appears in small font on the MCDU. When a frequency is entered in the VOR field, the FMGC automatically associates to the tuned frequency the closest navaid identifier with the same frequency, and displays it on the RAD NAV page. This identifier may not correspond to the tuned navaid. If the closest navaid, found in the database, is of a different type (e.g. VOR instead of VOR/DME), the flight crew will obtain a partial tuning (e.g. VOR indication instead of VOR/DME indication). ENTER the course. If the flight crew intends to manually tune an ILS that is not in the Navigation Database or to manually tune an ILS by its frequency (ident not entered), and if they do not enter the course, the flight crew will not be able to arm approach modes. NAVAID IDENTIFICATION Ident.: DSC-22_20-20-30-00010487.0001001 / 16 MAR 11 Applicable to: ALL
CHECK the ILS identifier decoding on the PFD, and the VOR or ADF identifier on the ND. When the navaid identifier is decoded in agreement with that published, no audio check is necessary. When the decoding is different from the published one, check the audio. Due to morse coding inaccuracy, wrong decoding may sometimes occur. Note:
When a DME or a TACAN only is selected using either its identifier or its frequency, the NDs do not display the decoded indication.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← H to I
DSC-22_20-20-30 P 5/6 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NAVIGATION - RADIO NAVIGATION TUNING
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-20-30 P 6/6 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NAVIGATION - ALIGNMENT OF INERTIAL REFERENCE SYSTEM
ALIGNMENT OF INERTIAL REFERENCE SYSTEM Ident.: DSC-22_20-20-40-00010143.0013001 / 16 MAR 11 Applicable to: ALL
The FMGS uses the reference point coordinates of the departure airport to align the IRS. It calls these up from the database automatically after the flight crew has entered a company route or an origin-destination city pair and pressed the ALIGN IRS key on the MCDU. The flight crew can adjust these coordinates manually to the gate position. A normal alignment takes 10 min, a fast alignment 30 s. Fast alignment is used to refine a position when time is limited.
Note:
If the “IRS IN ALIGN” memo flashes on the E/WD during the alignment process, it indicates one of the following: ‐ It has detected excessive motion. (It automatically restarts the alignment) ‐ It has detected a disagreement between the position the MCDU has sent to the IRS, and the last memorized IRS position. The flight crew must enter new coordinates in the MCDU, and realign the IRS ‐ It has detected a disagreement between the latitude the MCDU has sent to the IRS, and the latitude the IRS has computed during the alignment ‐ The IRS has not received a position from the MCDU .
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-22_20-20-40 P 1/2 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NAVIGATION - ALIGNMENT OF INERTIAL REFERENCE SYSTEM
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-20-40 P 2/2 18 SEP 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NAVIGATION - NAVIGATION DATABASE
GENERAL Ident.: DSC-22_20-20-50-00010410.0001001 / 17 AUG 10 Applicable to: ALL
Overall navigation performance is mainly based on two elements: ‐ The accuracy of the aircraft position calculation ‐ The validity of the flight path definition, as extracted from the navigation database. The level of validation depends on the type of operations. For example, JAA TGL 10 requires that, for Precision RNAV in terminal area, providers and operators implement a quality assurance program for the navigation database, which may include a navigation database validation process. The highest level of validation is required for RNAV approach, with lateral and vertical navigation. The navigation databases are revised every 28 days (ARINC cycle). Flights should be conducted with a navigation database that is within its cycle. This should be checked on the AIRCRAFT STATUS MCDU page. OPERATIONS WITH AN OUTDATED NAVIGATION DATABASE Ident.: DSC-22_20-20-50-00010411.0001001 / 17 AUG 10 Applicable to: ALL
Airbus recommends flying with an updated navigation database. However, in exceptional circumstances, and for a limited period of time, an aircraft can continue to operate beyond the end data of the database cycle, provided it is approved by the national authorities. The following precautions need to be considered: ‐ Prior to flight, identify recent changes on the intended route, with the navigation charts and manuals. Some “strategic” new waypoints, not in the navigation database, may be worth entering as DEFINED WAYPOINT on MCDU. Note:
Flying with an outdated database, in an airspace that was recently restructured with numerous new waypoints, should be avoided.
‐ Check SID, STAR, and approach procedures of departure, destination and required alternates for recent changes. Do not attempt to modify or manually construct terminal instrument procedures or approaches. ‐ Fly terminal instrument procedures and approaches with managed guidance, that are in the navigation database and that have been checked for accuracy. Otherwise, fly the procedure, or the approach, in selected guidance with conventional radio navaid raw data.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
DSC-22_20-20-50 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
NAVIGATION - NAVIGATION DATABASE
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-20-50 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
FLIGHT PLANNING - GENERAL
FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING Ident.: DSC-22_20-30-05-00010492.0002001 / 17 AUG 10 Applicable to: ALL
The flight crew uses the MCDU to insert flight plans into the FMGS: ‐ A lateral flight plan that defines the intended horizontal flight path ‐ A vertical flight plan that defines the intended speed and altitude profile for the aircraft to follow while flying the lateral flight plan. Note:
The flight planning function is available for both the primary and secondary flight plans.
The FMGS can contain two different flight plans: ‐ The ACTIVE flight plan, which is the basis for: • Lateral and vertical guidance • MCDU and ND display • Radio navigation autotuning • Performance predictions • Fuel planning. ‐ The SECONDARY flight plan which the flight crew may use: • When an alternate takeoff runway is probable • To plan a diversion • To prepare the next flight • To compare predictions or evaluations. Each flight plan is composed of the same elements: ‐ The primary flight plan, from origin to destination and missed approach ‐ The alternate flight plan, from destination to alternate destination. The flight crew enters the flight plan in either of two ways: ‐ Automatically by selecting a company route. Such a selection will call all the elements of the route out of the database. ‐ Manually by selecting an ORIGIN/DEST pair, and then selecting all successive waypoints, procedures, and vertical constraints on the MCDU. The flight crew may then modify the flight plan on the ground or in flight, by making lateral and vertical revisions.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-22_20-30-05 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
FLIGHT PLANNING - GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-30-05 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
General GENERAL Ident.: DSC-22_20-30-10-05-00011075.0002001 / 16 MAR 11 Applicable to: ALL
To insert the lateral flight plan, the flight crew can use either a company route number or an ICAO four-letter city pair. The lateral flight plan includes the following elements: ‐ Departure • Takeoff runway • SID • En route transition. ‐ En route • En route waypoints and airways. ‐ Arrival • En route transition • STARs/VIAs • Landing runway with selected approach • Missed approach. ‐ Alternate flight plan. These elements are defined by waypoints and legs between the waypoints.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-22_20-30-10-05 P 1/10 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
The FMGC automatically strings the legs in sequence. The flight plan has a discontinuity if any two waypoints do not have a leg defined between them. The computer assumes that the aircraft will fly a direct leg between the two waypoints that define the discontinuity.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
DSC-22_20-30-10-05 P 2/10 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Note:
FLIGHT PLANNING - LATERAL FUNCTIONS
1. When the aircraft overflies a flight plan discontinuity, the NAV mode automatically reverts to the HDG (TRK) mode. 2. In HDG/TRK mode, a waypoint is sequenced when it passes behind the aircraft, and the aircraft is less than 7 nm from it, and also when the difference between the track of the aircraft and the track of the leg is less than 90 °. If the aircraft is flying a discontinuity towards a waypoint, this waypoint is sequenced when the aircraft is less than 5 nm from it. The same conditions apply in NAV mode, except that no distance to the waypoint is taken into account.
The FMGS automatically strings additional types of legs, when departure or arrival procedures (SID STAR - TRANS) are defined. Those strings correspond to specific patterns that are heading or track referenced and are defined in the database, such as: ‐ DME arc leg ‐ Holding pattern to a fix, or reverse turn ‐ Course-to-fix leg ‐ Radius-to-fix leg ‐ Heading leg ‐ MANUAL leg. The flight crew cannot create these types of legs: They are part of the stored departure/arrival procedures they have selected. The flight crew can only create direct legs between manually defined geographic points (navaids, airports, waypoints).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
DSC-22_20-30-10-05 P 3/10 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW OPERATING MANUAL
Note:
The departure and arrival procedures are defined in the database to minimize the amount of memory required. They are divided, as follows: ‐ DEPARTURE = SID + EN ROUTE TRANSITION ‐ ARRIVAL = APPR VIA + STAR + EN ROUTE TRANSITION The SID is the central common part of the departure procedure, as the STAR is of the arrival procedure. Enroute transitions (TRANS) are the various possible trajectories defined between the last SID point and the first enroute waypoints, and between the last enroute waypoint and the first fix of the STAR . ”APPR VIAs” are the possible trajectories, defined between the last STAR point and the first point of the approach. MANUAL LEGS
Ident.: DSC-22_20-30-10-05-00010629.0001001 / 17 AUG 10 Applicable to: ALL
A MANUAL leg stays on a constant TRK or HDG and has no termination point. The flight crew cannot insert it into a flight plan manually: it is part of a given procedure such as a SID or a STAR. When the aircraft is flying a MANUAL leg, the NAV mode remains engaged and predictions assume that the aircraft will fly a direct leg from its present position to the next waypoint (DIR TO). When the aircraft is cleared to fly to the next waypoint of the flight plan, the flight crew performs a DIR TO. Note:
1. In NAV mode, a MANUAL leg is sequenced only by performing a DIR TO. 2. The use of the descent mode (DES) on a MANUAL leg is not recommended.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← A to B
DSC-22_20-30-10-05 P 4/10 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW OPERATING MANUAL
FLIGHT PLAN CONSTRUCTION Ident.: DSC-22_20-30-10-05-00011076.0032001 / 16 MAR 11 Applicable to: ALL
There are three ways of defining the route: 1. A company route, that is in the database, and is known by the flight crew. The flight crew enters the name of the CO RTE into the [1L] field of the INIT A page. This action enters all the elements of the flight plan. The database usually includes an alternate route associated with the destination.
2. A company route, that is in the database, but the flight crew does not know it is there. The flight crew enters a city pair in the [1R] field. The ROUTE SELECTION page automatically appears and enables the flight crew to review all stored routes between the two cities before selecting one of them.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C→
DSC-22_20-30-10-05 P 5/10 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW OPERATING MANUAL
3. There is no company route between the two cities. The flight crew enters the city pair in the [1R] field. The ROUTE SELECTION page appears and displays “NONE”. The flight crew has to manually construct the entire flight plan. For procedure, Refer to PRO-NOR-SRP-01-10-A Flight Plan Initialization - General. FLIGHT PLAN CAPACITY Ident.: DSC-22_20-30-10-05-00010631.0002001 / 17 AUG 10 Applicable to: ALL
In terms of flight plan capacity, the FMS takes into account 3 flight plans: ‐ The active flight plan ‐ The secondary flight plan ‐ The temporary flight plan. Each flight plan can contain up to 200 legs. If a flight plan contains 200 legs, and if the flight crew attempts to perform a lateral revision that increases the number of legs of this flight plan, the FMS rejects the revision and the MCDU displays the “F-PLN FULL” message. For the active and secondary flight plans, the primary parts must contain less than 135 legs, and the alternate parts must contain lesgs than 65 legs.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← C to D
DSC-22_20-30-10-05 P 6/10 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW OPERATING MANUAL
LATERAL REVISIONS Ident.: DSC-22_20-30-10-05-00010632.0002001 / 17 AUG 10 Applicable to: ALL
The flight crew can revise the lateral flight plan following two types of revisions: 1. Lateral revisions that have an immediate effect on the active flight plan: ‐ The flight crew inserts a new waypoint directly on the F-PLN page, deletes, or changes a waypoint from it:
When the flight crew enters a new waypoint, which does not exist in the flight plan, the following waypoint moves down the flight plan, with a discontinuity shown after the new waypoint. ‐ The flight crew adds a direct leg (DIR TO) from his present position to a selected waypoint: The flight crew can change the “TO” waypoint of the active leg. The DIR TO function gives access to DIR TO, DIR TO ABEAM, or DIR TO/INTERCEPT. The active leg then goes from the present position (T/P) to the waypoint selected or inserted as the new “TO” waypoint.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E→
DSC-22_20-30-10-05 P 7/10 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
2. Lateral revisions that lead to a temporary flight plan (TMPY) before they take effect: The flight crew creates a temporary flight plan, then inserts it as a revision to the active flight plan. The flight crew does this when selecting, deleting, or modifying several waypoints of an airway or procedure at once (SID, STAR, HOLD, TAKEOFF or LANDING RWY). This modification is made on specific “LAT REV” pages from the flight plan page. Possible revisions are: ‐ Insert or modify the departure procedure ‐ Insert or modify the arrival procedure ‐ Insert a waypoint ‐ Change the destination ‐ Insert an airway ‐ Insert an offset ‐ Insert a holding pattern ‐ Select or enable an alternate flight plan ‐ Fix information. The purpose of the temporary flight plan is to allow the flight crew to check a revision on the MCDU and on the ND before inserting the changes into the active flight plan. It is a copy of the active flight plan that has been changed according to the flight crew revision. While it is displayed, the aircraft will continue to follow the original active flight plan. No predictions are computed or displayed on the pages of the temporary flight plan. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-22_20-30-10-05 P 8/10 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
A temporary flight plan is displayed for a check and/or new modification. Inserting the temporary revision will modify the active flight plan.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E
DSC-22_20-30-10-05 P 9/10 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-30-10-05 P 10/10 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW OPERATING MANUAL
FMS2 HONEYWELL GENERAL Ident.: DSC-22_20-30-10-15-00005067.0001001 / 09 FEB 11 Applicable to: ALL
The lateral revision function allows the pilot to create or modify the following parts of the flight plan: ‐ Airway ‐ Waypoint ‐ New destination ‐ Holding pattern ‐ Offset ‐ Alternate ‐ Fix information Each time the pilot activates one of the above-listed revisions, he accesses a temporary flight plan that enables the modification to be checked before inserting it in the active flight plan. The crew selects these functions by pressing the left keys on F-PLN A or B. ‐ Direct to and overfly functions are accessed via the MCDU keys. No temporary flight plan is created with these functions. ‐ “Update at” capability is a specific function that manually updates the FM position. It does not .use a temporary flight plan, but the pilot must confirm its insertion before it is activated. TEMPORARY F-PLN (TMPY) Ident.: DSC-22_20-30-10-15-00000460.0001001 / 09 FEB 11 Applicable to: ALL
When a pilot makes a lateral revision to the F-PLN, the FMGS creates a temporary flight plan. This is a copy of the active F-PLN, but is corrected by the lateral revision in progress. The aircraft continues to follow the active F-PLN, until the temporary revision is inserted. The revision appears in yellow font on both MCDUs and NDs. ‐ ‐ ‐ ‐ ‐ ‐
Lateral and vertical revisions cannot be made to a temporary F-PLN. Only one temporary F-PLN may be accessed at a time. The “DIRECT TO” function, when used, erases a temporary F-PLN. When a DIR TO is in process, a temporary revision cannot be displayed on the other MCDU. A TMPY F-PLN changes the title of the flight plan pages. (TMPY appears in all titles). No predictions are computed for a temporary flight plan (dashes are displayed).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-22_20-30-10-15 P 1/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Temporary data is displayed in yellow (ND and MCDU). Once inserted, it becomes active and is displayed in green.
INSERTING AN AIRWAY WITH "VIA" Ident.: DSC-22_20-30-10-15-E-NG01127 Applicable to: ALL Ident.: DSC-22_20-30-10-15-E-00012828.0001001 / 14 MAY 12
GENERAL In the active flight plan, the pilot can insert up to 5 successive airway segments, going from a revised waypoint or ending at a given waypoint of the flight plan.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
DSC-22_20-30-10-15 P 2/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
SELECT the revised waypoint (here CDN). PRESS [ 5R ] to select the airways function. Ident.: DSC-22_20-30-10-15-E-00012829.0001001 / 14 MAY 12
THE PILOT WISHES TO INSERT SUCCESSIVE AIRWAY SEGMENTS FROM A WAYPOINT e.g. from CDN - Airways UB19 – Airways UB25 – Ending point AAA.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C→
DSC-22_20-30-10-15 P 3/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
WRITE the first airway in the scratchpad (here UB19). PRESS [ 1L ] to insert it into the VIA field. WRITE the second airway in the scratchpad (here UB25). PRESS [ 2L ] to insert it into the VIA field. The system automatically determines the first downpath intersection point between the 2 airways. ‐ If the airways have a common waypoint, the system selects it as the ending point of the first VIA. ‐ If they have no common waypoint, but have a single intersection, the system creates this intersection as an FM-computed point and displays X followed by the airway IDENT (here XUB25). ‐ If they have no common waypoint or intersection, the system displays NO INTERSECTION FOUND in the scratchpad. Once the pilot has entered the required airways (up to 5), he must enter the ending point of the last selected airways:
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C→
DSC-22_20-30-10-15 P 4/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
WRITE the ending waypoint in the scratchpad (here AAA). PRESS [ 2R ] to insert the ending waypoint into the TO field. Note:
If two waypoints with the same IDENT belong to the same airway, the DUPLICATE NAMES page will not be called up, and the system selects the first one in the database.
Ident.: DSC-22_20-30-10-15-E-00012830.0001001 / 09 FEB 11
THE PILOT WISHES TO INSERT ONE AIRWAY SEGMENT TO AN ENDING WAYPOINT
WRITE the airway IDENT in the scratchpad (here UB19). 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C→
DSC-22_20-30-10-15 P 5/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
PRESS [ 1L ] to insert it into the VIA field. WRITE the ending waypoint in the scratchpad (here PON). PRESS [ 1R ] to insert it into the TO field. Note:
‐ If the revise waypoint, or the ending waypoint, does not belong to the entered airway, the system displays AWY/WPT MISMATCH in the scratchpad. ‐ If two waypoints with the same IDENT belong to the same airway, the DUPLICATE NAMES page will not be called up and the system selects the first one in the database.
Ident.: DSC-22_20-30-10-15-E-00012831.0001001 / 09 FEB 11
FLIGHT PLAN INSERTION The flight crew either inserts the flight plan directly from the AIRWAYS page, or from the TMPY F-PLN page. In both cases: PRESS [ 6R ] to insert the temporary flight plan. Clear flight plan discontinuity, as needed.
INSERTING A WAYPOINT Ident.: DSC-22_20-30-10-15-F-NG01128 Applicable to: ALL Ident.: DSC-22_20-30-10-15-F-00012832.0001001 / 09 FEB 11
GENERAL Waypoints can be inserted in two ways: ‐ Directly into the flight plan. All modifications go directly into the active flight plan. No temporary flight plan is created. ‐ By means of a lateral revision at the “NEXT WAYPOINT”, a process that creates a temporary flight plan. The second method enables the temporary flight plan to be checked before it is inserted. Ident.: DSC-22_20-30-10-15-F-00012833.0001001 / 09 FEB 11
WAYPOINT IDENTIFICATION The pilot can identify a waypoint by: ‐ Its identifier (if it is in the navigation database). ‐ A Latitude/Longitude (LL). ‐ A Place/Bearing/Distance (PBD). The waypoint is defined by its bearing and distance from a place. ‐ A Place-Bearing/Place-Bearing (PBX). The waypoint is defined by the interception of 2 radials from 2 places. ‐ A Place/Distance (PD). The waypoint is defined by a distance from a place, along the F-PLN.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← C to D →
DSC-22_20-30-10-15 P 6/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Note:
FLIGHT PLANNING - LATERAL FUNCTIONS
If a slash or a dash is not entered properly, the MCDU displays a “FORMAT ERROR” message.
When the Flight Management Guidance System receives a waypoint that is not in the database, it identifies it as LLxx or PBD xx or PBX xx or PD xx (xx is a two-digit number between 01 and 20) and stores it in the stored waypoints file of the database. Note:
When NAV mode is engaged, the crew cannot modify the “TO” waypoint (active leg) using the waypoint insertion function. If the crew wants to modify it, the DIR TO function will be used.
Ident.: DSC-22_20-30-10-15-F-00012834.0001001 / 14 MAY 12
WAYPOINT INSERTED DIRECTLY IN THE FLIGHT PLAN
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-22_20-30-10-15 P 7/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
WRITE the waypoint identifier or LAT/LONG, Place/Bearing/Distance or Place-Bearing/Place-Bearing into the scratchpad. (Example: Place: LMG, Bearing: 330 °, Distance: 135 nm). PRESS the appropriate key to enter the waypoint into the flight plan. The rule is that the new waypoint appears next to the pressed key, and the previous waypoint moves down the flight plan path. This operation creates a discontinuity between the new waypoint and the previous one. The new flight plan will have to be cleared of the discontinuity and some waypoints erased. Ident.: DSC-22_20-30-10-15-F-00012835.0001001 / 09 FEB 11
ALONG TRACK WAYPOINT INSERTION On the F-PLN or STEP ALTS page, the pilot can enter an along track waypoint, defined as a place/distance waypoint.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-22_20-30-10-15 P 8/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
WRITE the waypoint identifier and distance from this place. According to the sign of the distance, the crew may define an along track waypoint before or after the revised place. (Example: AMB/-040). PRESS the appropriate key adjacent to the place identifier. The system automatically positions the waypoint in the flight plan. This operation does not create any discontinuity. The system does not accept an along track waypoint entered at the FROM waypoint.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-22_20-30-10-15 P 9/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Ident.: DSC-22_20-30-10-15-F-00012836.0001001 / 14 MAY 12
WAYPOINT INSERTED THROUGH THE USE OF “NEXT WAYPOINT”
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-22_20-30-10-15 P 10/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
SELECT the lateral revision (LAT REV) function at an appropriate waypoint. WRITE the waypoint identifier, or LAT/LONG, or Place/Bearing/Distance, or Place-Bearing / Place-Bearing into the scratchpad. ENTER it in the brackets under NEXT WPT (next waypoint). INSERT the temporary flight plan by pressing the [ 6R ] key. CLEAR the F-PLN discontinuity, as appropriate. Ident.: DSC-22_20-30-10-15-F-00012837.0001001 / 14 MAY 12
LATITUDE/LONGITUDE CROSSING WAYPOINT INSERTION This function allows the insertion of one or several points along the flight-plan beyond the revised waypoint, at fixed latitude or longitude intervals (INCR) from a specified latitude or longitude. These waypoints are not considered as part of the pilot-defined elements. The system deletes them when sequenced.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-22_20-30-10-15 P 11/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
WRITE the latitude (NXX, XXN, SXX or XXS), the required increment in degrees between the successive waypoints, and the number of required waypoints. (Example: The pilot wants to obtain 3 points, every degree from latitude N46: He enters N46/1/3). 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-22_20-30-10-15 P 12/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
PRESS [ 2R ] to insert it into the LL XING/INCR/NO field. PRESS [ 6R ] to insert the new waypoints in the flight plan without discontinuity. The system does not store these waypoints in the database.
FIX INFO Ident.: DSC-22_20-30-10-15-G-NG01129 Applicable to: ALL Ident.: DSC-22_20-30-10-15-G-00012838.0008001 / 09 FEB 11
GENERAL When using the FIX INFO function, the flight crew defines waypoint intersections of the flight plan with radials, circle or abeam associated to a fix. When the flight crew inserts the intersection points, the system automatically identifies these points, but does not store them in the navigation database. Ident.: DSC-22_20-30-10-15-G-00012839.0008001 / 09 FEB 11
INSERTING A RADIAL INTERCEPT WAYPOINT The flight crew accesses the radial intercept function from the lateral revision page at the origin or “from” waypoint.
WRITE the reference fix identifier into the scratchpad (here POI), and ENTER it [1L]. It may be any database or pilot-defined fix.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← D to E →
DSC-22_20-30-10-15 P 13/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
WRITE the radial into the scratchpad (here 120 °) and ENTER it [ 2L ]. The defined radial appears as a blue dashed line on the ND. If the radial line intersects the active flight plan, the system computes the time, distance to go, and the altitude at the intersection point. Up to two radials can be entered. SELECT the required radial to insert the associated waypoint into the flight plan (if needed): The system automatically assigns its IDENT as the three first characters of the reference fix IDENT, followed by the radial. (Example: ABC 140). The blue dashed line disappears from the ND.
Ident.: DSC-22_20-30-10-15-G-00012840.0001001 / 14 MAY 12
INSERTING A CIRCLE INTERCEPT WAYPOINT
WRITE the reference fix identifier into the scratchpad (here POI), and ENTER it [1L].
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-22_20-30-10-15 P 14/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
WRITE the circle radius in the scratchpad (here 20 nm), and ENTER it [ 4L ]: The defined circle appears as a blue dashed circle on the ND. If the circle intersects the active flight plan, the system computes the time, along path distance to go and altitude at the first intersection point from the current aircraft position. SELECT the required radius to insert the associated waypoint into the flight plan (if needed). The system automatically assigns its IDENT as a D, followed by the radius, and followed by the three first characters of the reference fix IDENT (example D020 POI). The blue dashed circle disappears from the ND.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-22_20-30-10-15 P 15/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Ident.: DSC-22_20-30-10-15-G-00012841.0008001 / 14 MAY 12
INSERTING AN ABEAM INTERCEPT WAYPOINT
WRITE the reference fix identifier into the scratchpad (here POI), and ENTER it [1L] SELECT the ABEAM prompt [ 5L ]: A blue dashed line from the reference fix and perpendicular to the flight plan appears on the ND. The system computes the radial, time, distance to go, altitude and predictions related to the waypoint abeam the reference fix. SELECT [ 5L ] to insert the abeam intercept waypoint into the flight plan (if needed): The system automatically assigns its identifier as AB, followed by the first five characters of the reference fix identifier (Example ABXYZ). The blue dashed line disappears from the ND.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E
DSC-22_20-30-10-15 P 16/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW OPERATING MANUAL
INSERTING A NEW DESTINATION Ident.: DSC-22_20-30-10-15-00000471.0001001 / 14 MAY 12 Applicable to: ALL
The pilot may define a new destination and insert it via the lateral revision page. The pilot may then call up the new destination from any waypoint along the flight plan, except the FROM waypoint, the destination, and the missed-approach waypoint. When the new destination has been inserted, a flight plan discontinuity appears between the revision waypoint and the new destination. All waypoints beyond the revision waypoint (including the previous destination and associated missed approach) are deleted.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F→
DSC-22_20-30-10-15 P 17/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
SELECT the lateral revision function at an appropriate waypoint. WRITE the new destination in the scratchpad. Enter it in the brackets under “NEW DEST”. INSERT the temporary flight plan ([ 6R ] key), and complete the flight plan to the new destination.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←F
DSC-22_20-30-10-15 P 18/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW OPERATING MANUAL
HOLDING PATTERN Ident.: DSC-22_20-30-10-15-A-NG00586 Applicable to: ALL Ident.: DSC-22_20-30-10-15-A-00007222.0001001 / 09 FEB 11
GENERAL This section describes holding patterns, associated guidance and flight crew procedures. The Flight Management and Guidance Computer (FMGC) has three types of holding patterns that the pilot can use in a flight plan. Ident.: DSC-22_20-30-10-15-A-00007163.0001001 / 09 FEB 11
HOLD TO FIX (HF) The holding pattern is always part of an arrival or departure procedure. The aircraft flies it once and then automatically exits the holding pattern at the fix. The predicted speed in the holding pattern is the lowest of the ICAO speed limit, max endurance speed, or any speed constraint. Guidance to the fix in the holding pattern is similar to that on any leg of a flight plan. The HF patterns are part of the navigation database and cannot be created by the crew.
Ident.: DSC-22_20-30-10-15-A-00007182.0001001 / 09 FEB 11
HOLD TO ALTITUDE (HA) The aircraft flies the hold until it reaches the specified altitude. Then, it automatically exits the hold at the fix. The predicted speed for the holding pattern is the lowest of the ICAO speed limits, the max endurance speed, or any speed constraint. The size of the holding pattern is a function of the predicted speed. Guidance in a hold to altitude (HA) is similar to that for any leg of a flight plan. The HAs are in the navigation database, as part of the arrival or departure procedures, and cannot be created by the crew.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
G→
DSC-22_20-30-10-15 P 19/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Ident.: DSC-22_20-30-10-15-A-00007206.0013001 / 14 MAY 12
HOLD WITH MANUAL TERMINATION (HM) This type of holding pattern may be part of an arrival procedure, or the pilot may enter it at the present position or at any flight plan waypoint. The pilot will use this type of holding pattern to comply with a defined procedure or a clearance limit, or to meet an operational need (such as losing altitude, holding for weather improvement, or absorbing an ATC delay). This type of holding pattern is exited according to the pilot's decision, not automatically. There are 3 types of HM. All are modifiable.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G→
DSC-22_20-30-10-15 P 20/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
DATABASE HOLD
If the holding pattern is part of the database, it is named DATABASE HOLD and all its associated data (inbound course, turn direction, time/distance) are defined in the database. The flight crew can modify this data. COMPUTED HOLD AT...
If the holding pattern is not in the database, the FMGC designs a holding pattern and proposes it to the pilot. The associated data consists of default values that the pilot can modify.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G→
DSC-22_20-30-10-15 P 21/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
HOLD AT...
If the pilot inserts into the active flight plan a holding pattern that is manually-corrected from a hold defined by the FMGS, the screen displays a “HOLD AT...” page. The 2R field displays REVERT TO DATABASE or REVERT TO COMPUTED to restore the database data, if necessary. PREDICTIONS AND GUIDANCE ASSOCIATED WITH A HM HOLDING PATTERN (HOLD WITH MANUAL TERMINATION) Before deceleration If an altitude constraint is defined at the hold entry fix, then the FMS duplicates this constraint on the hold exit. However, different constraints may be inserted at entry and exit fixes. Although the hold is inserted into the flight plan, the FMGS does not take it into account for predictions until the aircraft enters the hold. However, if the hold is not deleted by the crew, the FMGS schedules a deceleration point and displays it on the ND.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G→
DSC-22_20-30-10-15 P 22/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
The FMGS predicts the estimated time and amount of fuel remaining at which the aircraft must exit holding, so as to comply with the fuel policy specified on the fuel prediction page. When the aircraft enters the holding pattern, the FMGS revises all predictions and assumes the aircraft will fly one turn of the holding pattern. All predictions are revised for one more holding circuit at holding fix overfly. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G→
DSC-22_20-30-10-15 P 23/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Upon reaching the speed change pseudo waypoint The FMGS either causes the aircraft to decelerate to the hold speed (if managed speed is active and NAV mode engaged), or displays “SET HOLD SPD” (set hold speed) on the MCDU and primary flight display, if the flight crew had selected a speed target. The default hold speed is the lowest of the: ‐ Maximum endurance speed ‐ ICAO limit holding speed ‐ Speed constraint (if any). When no specific speed limit applies, the default hold speed is approximately equal to: ‐ Green Dot speed on the A318, A319, A320 (CFM) and A321 ‐ Green Dot + 20 kt for altitude lower than 20 000 ft, on the A320 (IAE). ‐ Green Dot + 5 kt for altitude bigger than 20 000 ft, on the A320 (IAE). The flight plan predictions for time and fuel do not yet consider that the hold will be flown, however, the navigation display shows the hold entry and holding pattern trajectory.
Deceleration receives priority, so that when the aircraft is in descent with the descent mode engaged, it will deviate above the descent path to decelerate. (VDEV becomes positive on the progress page). The flight plan page displays an immediate exit prompt.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G→
DSC-22_20-30-10-15 P 24/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
If the flight crew presses the key next to “IMM EXIT” before arriving at the holding fix, the aircraft will not enter the holding pattern, but will resume its phase-related managed-speed profile.
After reaching the hold entry fix The aircraft enters the hold. The MCDU HOLD page displays the associated holding data: ‐ The inbound course (INB CRS) ‐ The TURN direction (L or R) ‐ The TIME/DIST ‐ The LAST EXIT time and the associated fuel to reach the alternate airport with no extra fuel. The FMS assumes that the aircraft will fly one turn of the holding pattern, and revises the predictions accordingly. When the holding pattern is defined by a leg time (and not a leg distance), the system revises the size of the hold as a function of the target speed. ‐ If managed speed is active, the system uses the predicted holding speed to calculate the size of the holding pattern. ‐ If the selected speed is active, the system uses the target speed selected by the flight crew at the entry fix sequencing to calculate the size of the holding pattern. ‐ The VDEV displayed on the primary flight display and the PROG page when the aircraft is flying in the HM (hold pattern with manual termination) is the difference between the aircraft's current altitude and the altitude at which it should be when it reaches the hold exit fix in order to be correctly positioned on the descent path.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G→
DSC-22_20-30-10-15 P 25/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
With IMM EXIT pressed (aircraft in the holding pattern) The predictions and guidance assume that the aircraft is immediately returning to the hold fix. Sequencing the hold fix, the aircraft exits the holding pattern and resumes its navigation. The flight plan page displays “RESUME HOLD*” instead of “IMM EXIT*”.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G→
DSC-22_20-30-10-15 P 26/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
HOLD EXIT PROCEDURE Position (1) If “IMM EXIT” pressed, the aircraft will exit at the next fix overfly. Position (2) If “IMM EXIT” pressed, the aircraft will make an immediate turn to the fix where the hold will be exited. If managed speed is active: The computer sets the target speed to the applicable speed of the current phase (for example, speed constraint, ECON speed, or speed limit). The computer then bases its predictions on the assumption that the flight will continue on the descent path, if the aircraft is in descent.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G→
DSC-22_20-30-10-15 P 27/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
If DES mode is engaged: The following applies: ‐ The holding pattern is never included in the descent path computation. ‐ The flight crew cannot enter altitude and speed constraints at the hold exit fix. (This is only allowed at the hold entry fix). ‐ The vertical guidance in the HM, during the descent phase, calls for a constant -1 000 ft/min. But the computer considers altitude constraints that will take effect farther down the flight path as it calculates vertical guidance and predictions. The system will not allow the aircraft to descend below the next altitude constraint, neither the FCU selected altitude. If the aircraft reaches the next altitude constraint, it will level off and the altitude constraint mode will engage. With RESUME HOLD pressed If the flight crew presses the key next to “RESUME HOLD”, the aircraft remains in the holding pattern, and “IMM EXIT” is displayed again. After that, each time the aircraft flies over the holding fix, the system updates the predictions for one more holding circuit. HOLDING PATTERN ENTRIES The FMGS offers three types of entry into holding patterns: 1. Direct entry 2. Teardrop entry 3. Parallel entry
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G→
DSC-22_20-30-10-15 P 28/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
1. The direct entry
2. The teardrop entry
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G→
DSC-22_20-30-10-15 P 29/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
3. The parallel entry
Note:
If the leg the aircraft is flying toward the holding fix is on a “limit” between a teardrop entry and a parallel entry, the FMGC may compute and display either of the two entries. The pilot should keep this in mind and should not assume that the FMGC is malfunctioning. If the flight plan leg toward the hold entry fix is on a course that is the reciprocal of the inbound course of the holding pattern, the aircraft will fly a parallel entry.
Ident.: DSC-22_20-30-10-15-A-00007220.0001001 / 09 FEB 11
PROCEDURE TO INSERT A HOLD (HOLD WITH MANUAL TERMINATION) The HOLD prompt allows the flight crew to enter a hold with manual termination (HM), at the revised waypoint or at the present position. The flight crew accesses the HOLD page from a lateral revision at the present position (PPOS) or at a waypoint.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G→
DSC-22_20-30-10-15 P 30/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
SELECT lateral revision at present position (PPOS), or an applicable waypoint. PRESS the HOLD prompt [3L]. A TMPY F-PLN is created and if applicable, the database hold is proposed. If no database hold is available, the computed hold is proposed. CHECK and (if necessary) MODIFY the HOLD data. CHECK the temporary flight plan and INSERT it, if appropriate.
Ident.: DSC-22_20-30-10-15-A-00007219.0001001 / 09 FEB 11
PROCEDURE TO DELETE A HOLD (HOLD WITH MANUAL TERMINATION) CLEAR the HOLD directly in the flight plan, as can be done for a normal waypoint.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G
DSC-22_20-30-10-15 P 31/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
OFFSET Ident.: DSC-22_20-30-10-15-B-NG00587 Applicable to: ALL Ident.: DSC-22_20-30-10-15-B-00007230.0009001 / 14 MAY 12
GENERAL Offset allows the flight crew to define on offset of the active flight plan. The offset can be immediate or deferred to start on a downstream leg. The offset will end by default or at a pre-planned end waypoint. Additionally, the flight crew can specify the intercept angle used for the transitions to and from the offset path. In most cases, the pilot will use it enroute because of an ATC clearance, or to avoid bad weather expected along the flight plan route. This page is accessed from LAT REV page at the FROM waypoint or at any waypoint downpath the flight plan, except the destination airport. After inserting the offset in the flight plan, the flight plan page shows OFST in its title, left or right arrows are displayed on every label line between the start and end waypoints of the offset, and the navigation display shows the offset flight plan with a solid green line and the original flight plan with a dashed green line. The offset is cleared: ‐ Automatically (holding pattern, approach), or ‐ Manually with the clear (CLR) key, or by entering “o” in the offset value field [ 1L ] or by using the delete prompt in the OFFSET page. Note:
If the pilot enters an OFFSET when the aircraft is too close to the TO waypoint, the FMGS may refuse to accept it, in which case the MCDU displays the “ENTRY OUT OF RANGE” message.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
H→
DSC-22_20-30-10-15 P 32/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Ident.: DSC-22_20-30-10-15-B-00007207.0010001 / 18 MAR 11
INSERTING AN OFFSET SELECT LAT REV page at a waypoint. SELECT OFFSET function by pressing [ 2L ]. WRITE the required offset value and direction (for example, L5 or 5L), and enter it into [ 1L ] field. CHECK or INSERT the START WPT from the list in [ 3L ] - [ 5L ] fields or manually enter it. CHECK or ENTER the INTCP ANGLE in [ 1R ] field. CHECK OR INSERT the END WPT from the list in [ 3R ] - [ 5R ] fields or manually enter it. PRESS INSERT in [ 6R ] field to activate the OFFSET.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H→
DSC-22_20-30-10-15 P 33/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Ident.: DSC-22_20-30-10-15-B-00007218.0009001 / 14 MAY 12
MANUAL CANCELLATION OF AN OFFSET There are two standard methods for cancelling an offset: 1. SELECT DIR TO a waypoint (the next waypoint, for example). 2. SELECT a Lateral Revision (LAT REV) at FROM WPT. CLEAR the OFFSET field or enter “0” in the OFFSET value field [1L], and press INSERT* in [6R] to activate the temporary flight plan (cancelling OFFSET), or PRESS the OFFSET DELETE prompt [6R] to activate the temporary flight plan (cancelling OFFSET).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H→
DSC-22_20-30-10-15 P 34/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
ALTERNATE FUNCTION Ident.: DSC-22_20-30-10-15-C-NG00588 Applicable to: ALL Ident.: DSC-22_20-30-10-15-C-00007240.0001001 / 09 FEB 11
GENERAL The ALTERNATE FUNCTION performs two actions: ‐ It reviews and defines alternate airports and inserts them into the flight plan. ‐ It allows a diversion to be activated through the ENABLE ALTN command. Ident.: DSC-22_20-30-10-15-C-00007217.0009001 / 09 FEB 11
REVIEW AND SELECTION OF ALTERNATE AIRPORT Several alternate airfields may be stored in the database and assigned to a destination. When the pilot selects a company route (CO RTE) (or a city pair), the computer strings the preferred alternate into the active flight plan.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← H to I →
DSC-22_20-30-10-15 P 35/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
The pilot may review the alternate airports on the ALTN page and, if the one selected is not suitable because of weather or fuel considerations, another alternate may be strung into the active flight plan. The pilot may define an additional alternate airport into the list, if necessary. The ALTERNATE page shows the track and distance (airway or direct) between destination and alternate, as well as fuel management data (EXTRA fuel, assuming the associated airfield is the alternate airport). This data will help the pilot change the preferred alternate, if necessary. Access the ALTERNATE page through the ALTN prompt on the LAT REV page at destination. Alternate airfields are attached to the destination. ENTERING NEW ALTERNATE INTO THE F-PLN If the preferred alternate is unsuitable, proceed as follows: SELECT F-PLN key on MCDU. SELECT LAT REV at destination. SELECT ALTN [5L]. SELECT an AIRFIELD IDENTIFIER. INSERT the temporary flight plan. Note:
If weather and destination airfield conditions permit, you may select “NO ALTN”. Fuel predictions will be computed without alternate fuel.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←I→
DSC-22_20-30-10-15 P 36/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
SELECTION OF ANOTHER ALTERNATE Fuel management information for flight to another alternate airfield may be obtained by selecting the OTHER ALTN field. SELECT LAT REV at DESTINATION. SELECT ALTN [5L]. ENTER the airfield identifier in the brackets. ‐ If the airfield is not in the database, the NEW RUNWAY page automatically appears. ‐ If the airfield is in the database and there is a company route (CO RTE) to it, the ROUTE SELECTION page automatically appears. SELECT the route, as appropriate, or RETURN to the ALTN page. ENTER the distance in the brackets (if required). XTRA fuel and track (TRK) will appear. SELECT the other alternate (OTHER ALTN) as a primary alternate if convenient. (EXTRA fuel and DIST revert to AIRWAY distance). INSERT it, if you want to have it as a primary alternate. Note:
‐ The pilot can always overwrite the “OTHER ALTN”. The new “OTHER ALTN” then replaces the previous one, which is lost. ‐ The pilot can select OTHER ALTN as a primary alternate (active flight plan), to replace any alternate on the initial list. ‐ If the pilot selects the other alternate as a primary alternate, and overwrites the OTHER ALTN field by entering a new airport, the first one will remain a primary alternate and the system will memorize a second OTHER ALTN.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←I→
DSC-22_20-30-10-15 P 37/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
The pilot may enter a distance in the OTHER ALTN field. The system will compute the extra fuel and the track for this distance. PREDICTED DATA FOR ALTERNATE Data predictions are based on: ‐ Aircraft weight being equal to landing weight at primary destination. ‐ Flight at FL 100 if the alternate F-PLN length is less than 100 nm , at FL 220 if the alternate F-PLN length is comprised between 100 and 200 nm , or else at FL 310. ‐ Cost index 0. ‐ Constant wind (as entered in the alternate field of the DES WIND page).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←I→
DSC-22_20-30-10-15 P 38/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW OPERATING MANUAL
‐ Constant delta ISA (equal to delta ISA at primary destination). ‐ The along flight path distance from the destination to the alternate airport. If the flight crew enters an ALTN fuel value, this value is the one taken into account. ENABLE ALTN Ident.: DSC-22_20-30-10-15-00000467.0009001 / 14 MAY 12 Applicable to: ALL
This enables the pilot to initiate a diversion by entering the alternate flight plan just after the revision waypoint (with a discontinuity). The pilot may have to adjust the resulting flight plan (use “direct to”, or add or suppress waypoints), depending on the circumstances.
TO ACTIVATE THE PRIMARY ALTN: SELECT a LAT REV at the “TO” waypoint (or at another suitable waypoint). PRESS the ENABLE ALTN key. INSERT the temporary flight plan. ENTER an appropriate waypoint in DIRECT TO and adjust the flight plan. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← I to J →
DSC-22_20-30-10-15 P 39/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
ADJUST the cost index on the PERF page and the defaulted cruise flight level (CRZ FL) on the PROG page, as required.
When ENABLE ALT is pressed at ABE, a flight plan discontinuity is created from ABE down to destination and the alternate route is linked to the active flight plan.
DIR KEY (DIRECT-TO-FUNCTION) Ident.: DSC-22_20-30-10-15-D-NG00589 Applicable to: ALL Ident.: DSC-22_20-30-10-15-D-00007243.0001001 / 09 FEB 11
GENERAL The pilot uses the “Direct To” function to define a direct leg from the present position to any waypoint on the active flight plan or to any waypoint. The designated waypoint may be entered by its identifier (if it is stored in the database) or by a latitude/longitude, place/bearing/distance, or a place-bearing/place-bearing. Note:
If the autopilot or flight director is in the heading/track or localizer mode, the “DIR TO” function engages the NAV mode.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← J to K →
DSC-22_20-30-10-15 P 40/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Three functions are available through the DIR TO key: ‐ The DIR TO defines a direct leg from the present position to a specified waypoint. NAV mode engages simultaneously to the DIR TO selection. When the pilot uses DIR TO, the present position (PPOS) becomes the “FROM” waypoint and the active flight plan shows it as the T-P (turn point). ‐ The DIR TO/ABEAM function, defines the abeam waypoints along the direct leg. These waypoints are the projection on the direct leg of the initial F-PLN waypoints located between the aircraft position and the specified waypoint. NAV mode engages simultaneously to the DIR TO/ABEAM selection. ‐ The DIR TO/INTCPT function allows the definition of a specified RADIAL INBOUND or OUTBOUND at an inserted waypoint. The current aircraft track is used to compute the INTCPT point with the specified radial. NAV mode is armed simultaneously to the DIR TO/INTCPT selection. The ND displays the DIR TO leg as a temporary flight plan leg between current aircraft position and specified waypoint. In case of a DIR TO/INTCPT, the leg is not displayed when the angle between the current aircraft track and the intercept radial exceeds 160 °. Ident.: DSC-22_20-30-10-15-D-00007216.0001001 / 14 MAY 12
PROCEDURE FOR DIR TO WAYPOINT CASE 1. THE “TO” WAYPOINT IS IN THE FLIGHT PLAN Example : DIR TO FRZ PRESS the DIR key on the MCDU. PRESS the line select key next to “FRZ”.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←K→
DSC-22_20-30-10-15 P 41/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FLIGHT PLANNING - LATERAL FUNCTIONS
←K→
DSC-22_20-30-10-15 P 42/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
CASE 2. THE “TO” WAYPOINT DOES NOT BELONG TO THE FLIGHT PLAN Example : Direct to ABC (ABC being an ident, LL or PBD or PBX (Place/Bearing-Place/Bearing) PRESS the DIR key. WRITE the waypoint identifier (e.g. ABC) into the scratchpad. PRESS [1 L] to enter “ABC” in the “DIR TO” field.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←K→
DSC-22_20-30-10-15 P 43/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Clear the discontinuity and the waypoints that are not included in the new flight plan.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←K→
DSC-22_20-30-10-15 P 44/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Ident.: DSC-22_20-30-10-15-D-00007215.0001001 / 09 FEB 11
PARTICULAR CASES FOR USE OF DIR TO ‐ If the pilot is flying a manual leg (part of a SID or STAR), the flight plan page displays “F-PLN DISCONTINUITY”, preceded by “MANUAL” (see below). These legs are specific heading or track legs flown with no defined end waypoint.
‐ When the pilot encounters a flight plan discontinuity, or if a major reset occurs, the flight plan page displays “PPOS - F-PLAN DISCONTINUITY”, and the pilot looses managed guidance in both the lateral and vertical plans. The autopilot or flight director reverts to the basic HDG V/S (or TRK FPA) modes. Predictions remain available and are based on the assumption that the aircraft will fly a direct leg from its present position to the next waypoint.
‐ In both of these cases, the only way to get back to a standard flight plan is to perform a “DIR TO” to a designated waypoint. ‐ Following a DIR TO, the message “MAP PARTLY DISPLAYED” may appear on the NDs, if the new flight plan includes a very long leg (Refer to DSC-31-45 Flags and Messages Displayed on ND). When this message comes up, enter an intermediate waypoint to shorten the leg. Note:
During cruise, the DIR TO function is not available as long as uplink wind data, received through ACARS , is not inserted or cancelled on the CRUISE WIND page.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←K→
DSC-22_20-30-10-15 P 45/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Ident.: DSC-22_20-30-10-15-D-00007208.0009001 / 14 MAY 12
PROCEDURE FOR DIR TO/ABEAM Example : DIR TO/ABEAM BEROK PRESS the DIR on the MCDU. WRITE the waypoint identifier into the scratchpad (Example : BEROK). PRESS [1 L] to enter the waypoint in the DIR TO field. SELECT the ABEAM PTS function. The display reverts to F-PLN A page.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←K→
DSC-22_20-30-10-15 P 46/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Note:
FLIGHT PLANNING - LATERAL FUNCTIONS
1. If, between two waypoints projected on the direct leg, there was a discontinuity in the original flight plan, this discontinuity disappears between the corresponding abeam points on the direct leg. 2. . Abeam waypoints computed from latitude/longitude-type waypoints are renamed by the system as “AB XXXXX”, where “xxxxx” is an abbreviation in 5 characters, of the latitude and longitude of the initial waypoints.
Ident.: DSC-22_20-30-10-15-D-00007221.0001001 / 14 MAY 12
PROCEDURE FOR DIR TO/INTERCEPT PRESS the DIR key. WRITE the waypoint identifier into the scratchpad. PRESS [1L] to enter the waypoint in the DIR TO field. In the [1R] and [2R] fields, the MCDU displays the functions radial inbound and radial outbound from the waypoint. If the waypoint belongs to the flight plan, the system displays the flight plan track as the default inbound radial. The crew can modify it. WRITE the required in or out radial into the scratchpad. PRESS [1R] or [2R] to enter the radial in the required field. The ND displays the entered radial as an amber dotted line : The pilot can still modify it. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←K→
DSC-22_20-30-10-15 P 47/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
PRESS [1R] or [2R] to confirm the DIR TO/INTERCEPT selection. The display reverts to the F-PLN A page, the system arms the NAV mode, and engages the HDG mode. The FROM waypoint is the aircraft position at the time of the DIR TO/INTERCEPT selection. The MCDU indicates it as INBND or OUTBND. Note:
1. If the waypoint does not belong to the flight plan, the system strings the DIR TO/INTERCEPT leg to this waypoint, and inserts a discontinuity following the waypoint. 2. A DIR TO/INTERCEPT cancels any active offset. 3. If the current AP/FD lateral mode is HDG or TRK, NAV becomes armed. If the NAV mode was engaged, NAV becomes armed. FCU HDG or TRK must be used to guide the aircraft. The ND displays an intercept point, if the intercept angle is less than 120 °. The system constantly updates it to reflect the current aircraft track and position with respect to the intercept radial. The NAV mode engages when reaching the intercept point.
EXAMPLE: RADIAL INBND DIR TO AMB - RADIAL 200 ° INBOUND
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←K→
DSC-22_20-30-10-15 P 48/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
EXAMPLE: RADIAL OUTBND DIR TO AMB - RADIAL 200 ° OUTBOUND
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←K→
DSC-22_20-30-10-15 P 49/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FLIGHT PLANNING - LATERAL FUNCTIONS
←K→
DSC-22_20-30-10-15 P 50/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW OPERATING MANUAL
OVFY (OVERFLY) KEY Ident.: DSC-22_20-30-10-15-00000469.0001001 / 09 FEB 11 Applicable to: ALL
The overfly key programs the Flight Management Guidance Computer to fly over a specific waypoint or NAVAID. To use it: PRESS the “OVFY” key. A “Δ” appears in the scratchpad. INSERT it by pressing the key adjacent to the waypoint to be overflown. [3L] in this example.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← K to L →
DSC-22_20-30-10-15 P 51/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW OPERATING MANUAL
The pilot cannot cancel the overfly program. If you do not want to fly over the point you have entered, use DIR TO (direct to) the next waypoint or engage the heading mode, whichever is more suitable.
The overfly function allows you to fly over a specific waypoint, and return the aircraft to the great circle track. "UPDATE AT" Ident.: DSC-22_20-30-10-15-00000470.0001001 / 09 FEB 11 Applicable to: ALL
To manually change the position computed by the FMGC (FM position and bias), the pilot uses “UPDATE AT” on the progress page. Use this facility with extreme caution: It is apt to be inaccurate, because it relies on the pilot's estimation of when a designated position has been reached.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← L to M →
DSC-22_20-30-10-15 P 52/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
WRITE the ident for the NAVAID (or waypoint or airport), or the coordinates, or the PBD or PBX (Place/Bearing-Place/Bearing) at which the update is intended. PRESS [3L] to enter the ident in the “UPDATE AT” field. The coordinates of the point, along with its identifier (or “ENTRY”, if the identifier is not in the database), appear in that field. PRESS [3R] to activate the update, when you estimate that you are at the position. Note:
The system reinitializes the Estimated Position Error computation when a position update is performed. This may lead to the appearance of a “NAV ACCUR DOWNGRAD” or “NAV ACCUR UPGRAD” message.
If the “UPDATE AT” does not properly take effect, it corrupts the FM position. ‐ In an area with good radio NAVAID coverage: • If the update error is small, subsequent radio position updating will correct the FM position. • If the update error is large, the system will reject any radio updating because its internal “reasonableness test” will reject the various NAVAIDs. Thus, the FM position will only be the MIX IRS position corrected by the position bias, determined at the time of the update, and the error will be maintained. ‐ In an area without proper NAVAID coverage, radio position updating will not be available and the FM position, if incorrect, will remain incorrect until a new manual update is performed. ‐ Therefore, the pilot should only use “UPDATE AT” in case of a major position problem, such as: • On the ground, no flight plan appears on the navigation display and ARC/ROSE NAV mode is selected. • A “CHECK IRS/FM POSITION” message appears on the MCDU. • A “FM/IR POSITION DISAGREE” message appears on the ECAM. When GPS PRIMARY is operative, the FM position will always converge towards the GPS position at a rate depending on the aircraft altitude. Therefore, when GPS PRIMARY is operative, an inaccurate “update at” will have a temporary effect on the FM position.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←M
DSC-22_20-30-10-15 P 53/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-22_20-30-10-15 P 54/54 30 MAY 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - VERTICAL FUNCTIONS
General GENERAL Ident.: DSC-22_20-30-20-05-00010939.0001001 / 17 AUG 10 Applicable to: ALL
The vertical flight plan is divided into the following flight phases: Preflight - Takeoff - Climb - Cruise - Descent - Approach - Go-Around - Done. All but “Preflight” and “Done” phases are associated with speed and altitude profiles.
Each phase has an assigned profile of target speeds. For each phase the FMGS computes an optimum (ECON) speed as a function of the strategic parameters (CI, CRZ FL, ZFW, ZFWCG, block FUEL) and performance criteria. ECON speed is the basis of the managed speed profile. The ECON speed can be modified by: ‐ Presetting a speed or Mach number on the MCDU (PERF page) for the next phase ‐ Selecting on the FCU a speed or a Mach number for the active phase ‐ Inserting speed constraints or speed limits on the MCDU vertical revision (VERT REV) page. The vertical flight plan includes vertical constraints (altitude, speed, time) that may be stored in the data base or entered manually by the flight crew through vertical revision pages. The flight crew may also define step climbs or step descents for cruise purposes. If the flight crew plans to climb to a higher flight level or descend to a lower level, they can use a vertical revision at any waypoint to insert the new level. When all the vertical data has been defined, the FMGC computes the vertical profile and the managed speed/Mach profile from takeoff to landing.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-22_20-30-20-05 P 1/8 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - VERTICAL FUNCTIONS
VERTICAL FLIGHT PLANNING Ident.: DSC-22_20-30-20-05-00011065.0002001 / 17 AUG 10 Applicable to: ALL
DATA ENTRY The vertical flight plan provides the FMGS with all the data required to calculate performance and predictions. This data is either entered by the flight crew or calculated by the FMS.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
DSC-22_20-30-20-05 P 2/8 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - VERTICAL FUNCTIONS
There are three categories of data: ‐ Strategic data, that applies to the overall flight profile: • Cost Index (CI) • Cruise Flight Level (CRZ FL) and STEP ALTS if any • Zero-Fuel Weight (ZFW) • Zero-Fuel Weight Center of Gravity (ZFWCG) • Block Fuel. ‐ Weather data: • Winds (for climb, cruise, descent, approach) • Sea level atmospheric pressure (QNH) at destination • Surface temperature (TEMP) at destination • Temperature in cruise phase • The Tropopause altitude (TROPO). ‐ Tactical data for the flight phases: • Phase switching conditions: ▪ Setting of the thrust levers to TOGA or FLEX positions ▪ Reaching acceleration altitude (ACCEL ALT) ▪ Entering cruise (T/C) ▪ Initiation of descent (T/D) ▪ Passing a deceleration pseudo waypoint (DECEL PSEUDO WPT) ▪ Touchdown. • Speed profile: ▪ V2 ▪ Economy climb speed or Mach (ECON CLB SPD/MACH) ▪ Preselected speed or Mach (SPD/MACH PRESELECTION) ▪ Economy cruise Mach (ECON CRZ MACH) ▪ Constant Mach ▪ Economy descent Mach or speed (ECON DES MACH/SPD) ▪ Approach speed (VAPP). • Vertical limitations: ▪ Speed limits (SPD LIMIT) ▪ Speed and altitude constraints (SPD AND ALT CSTR) ▪ Time constraints or Required Time of Arrival (RTA). In addition to the data entered by the flight crew, the FMS uses some real flight data parameters (CRZ SAT, actual wind) to improve the accuracy of the computed predictions.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-22_20-30-20-05 P 3/8 03 APR 12
AIRCRAFT SYSTEMS AUTO FLIGHT - FLIGHT MANAGEMENT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT PLANNING - VERTICAL FUNCTIONS
FLIGHT PHASES Ident.: DSC-22_20-30-20-05-00011024.0007001 / 18 MAR 11 Applicable to: ALL
The vertical flight plan is divided into flight phases. For each phase, the FMGS computes the optimum speed or Mach Profile. These flight phases are: Preflight - Takeoff - Climb - Cruise - Descent - Approach - Go-Around - Done. FLIGHT PHASES
OPTIMUM SPEED PROFILE
PREFLIGHT
/
TAKEOFF CLIMB CRUISE
V2 (V2 + 10) ECON CLB SPD / MACH ECON CRZ MACH
DESCENT
ECON DES MACH / SPD
APPROACH
VAPP (GS Min)
GO-AROUND
VAPP or current SPD, whichever is greater. Green Dot at ACC ALT
DONE
Note:
/
SWITCHING CONDITIONS TO NEXT PHASE SRS takeoff mode engaged and N1 > 85 %(EPR ≥ 1.25) or Ground Speed >90 kt At acceleration altitude or by engagement of another vertical mode. Reaching cruise FL No step descent, and distance to destination < 200 nm, or all engines operative and selected altitude below Max [FL 200, highest DES ALT CSTR] ‐ Overflying (DECEL) pseudo waypoint with NAV (or LOC*/LOC) mode engaged and altitude 50 ° nose up or 30 ° nose down ‐ Bank angle > 125 ° 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E to F →
DSC-27-20-20 P 6/8 30 MAY 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
‐ Angle of attack > 30 ° or < -10 ° for the A320 (-15 °for the A318, A319 and A321) ‐ Speed > 440 kt or < 70 to 90 kt (depending on the aircraft pitch attitude) ‐ Mach > 0.91 The law in pitch is the alternate law with no protection, except load-factor protection, and without auto trim. In roll, it is a full-authority direct law with a yaw mechanical. When the aircraft has recovered from its abnormal attitude, the flight control laws in effect are: ‐ In pitch: Alternate law without protection, with autotrim. ‐ In roll: Full authority direct law, with yaw alternate law. There is no reversion to direct law, when the pilot extends the landing gear. MECHANICAL BACK-UP Ident.: DSC-27-20-20-00001088.0001001 / 10 DEC 09 Applicable to: ALL
PITCH Mechanical backup enables the pilot to control the aircraft during a temporary complete loss of electrical power. He does this in pitch by manually applying trim to the THS. The PFDs display “MAN PITCH TRIM ONLY” in red. LATERAL The pilot uses the rudder pedals as the mechanical backup to laterally control the aircraft .
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← F to G
DSC-27-20-20 P 7/8 30 MAY 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-27-20-20 P 8/8 30 MAY 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
PEDESTAL Ident.: DSC-27-20-30-00001090.0001001 / 16 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-27-20-30 P 1/14 30 MAY 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
DSC-27-20-30 P 2/14 30 MAY 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
RUD TRIM Rotary Switch Controls the rudder trim actuator, which moves the neutral point of the artificial feel by the equivalent of one degree of rudder travel per second. Note:
(2)
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
The rudder trim rotary selector has no effect, when the autopilot is engaged.
RESET Pushbutton By pushing the RESET pushbutton, the zero trim position is ordered at 1.5 °/s. After the reset, an indication of up to 0.3° (L or R) may be observed in the rudder trim position indication. Note:
The RESET pb is not active, when the autopilot is engaged.
(3)
Position Indicator Displays the rudder trim direction (L or R) and value (0 to 20 °).
(4)
SPEEDBRAKE Lever The lever controls: ‐ The position of the speedbrake surfaces. To set speedbrake surfaces to a required position, the lever has to be pushed down and set to the required position. A “hardpoint” is provided at “½” SPEEDBRAKE position. ‐ The manual preselection of the ground spoilers. To arm the ground spoilers, the lever must be pulled up when in the RET position. When the lever is armed (or reverse thrust is selected), all spoiler's surfaces will automatically extend at landing, or in case of a rejected takeoff.
(5)
PITCH TRIM Wheel Both pitch trim wheels provide mechanical control of the THS and have priority over electrical control. A pilot action on the pitch trim wheel disconnects the autopilot. Note:
Crew action on the pitch trim wheel does not disconnect the ELACs (micro-switches, actuated by the override mechanism, ensure that the computers remain synchronized with the manually-selected position).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
DSC-27-20-30 P 3/14 30 MAY 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
The THS is manually-controlled on ground for the THS setting, before takeoff and in flight, when in direct law. ‐ Before takeoff, the pilot sets the THS to the angular value, determined as a function of the aircraft CG, using the CG scale on the wheel. The relationship between the aircraft CG and the THS setting shown on the trim wheel is only applicable for takeoff. The limits of the THS normal setting range for takeoff are indicated by a green band on the pitch trim wheel. ‐ In flight, when in direct law, the pilot uses the THS conventionally to fly in trim. In flight, the aircraft pitch trim setting depends on aircraft CG, weight, altitude and speed. Consequently, the relation between the aircraft CG, and the THS setting displayed on the pitch trim wheel, does not apply in flight. Following nosewheel touchdown, as the pitch attitude becomes less than 2.5 ° for more than 5 s, pitch trim is automatically reset to zero. Note:
This function is inoperative, when the green or yellow hydraulic system is not pressurized. LATERAL CONSOLES
Ident.: DSC-27-20-30-00001091.0004001 / 27 JAN 12 Applicable to: ALL
SIDESTICKS Each pilot has on his lateral console a sidestick he can use to control pitch and roll manually. Each sidestick is springloaded to neutral. When the autopilot is engaged, a solenoid-operated detent locks both sidesticks in the neutral position. If the pilot applies a force above a given threshold (5 daN in pitch, 3.5 daN in roll) the stick becomes free and the autopilot disengages. The hand grip has two switches: ‐ Autopilot disconnect and sidestick takeover pushbutton. ‐ Push-to-talk button.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← A to B →
DSC-27-20-30 P 4/14 30 MAY 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
Sidestick priority logic ‐ When only one pilot operates the sidestick, it sends his control signals to the computers. ‐ When the pilots move both side stick simultaneously in the same or opposite direction and neither takes priority, the system adds the signals of both pilots algebraically. The total is limited to the signal that would result from the maximum deflection of a single sidestick. Note:
In the event of simultaneous input on both sidesticks (2 ° deflection off the neutral position in any direction) the two green SIDE STICK PRIORITY lights on the glareshield come on and “DUAL INPUT” voice message is activated.
A pilot can deactivate the other stick and take full control by pressing and keeping pressed his priority takeover pushbutton. For latching the priority condition, it is recommended to press the takeover push button for more than 40 s. This allows the pilot to release his takeover push button without losing priority. However, a pilot can at any time reactivate a deactivated stick by momentarily pressing the takeover push button on either stick. If both pilots press their takeover pushbuttons, the pilot that presses last gets priority. Note:
If an autopilot is engaged, any action on a takeover pushbutton disengages it.
In a priority situation ‐ A red light comes on in front of the pilot whose stick is deactivated. ‐ A green light comes on in front of the pilot who has taken control, if the other stick is not in the neutral position (to indicate a potential and unwanted control demand). Note:
If the aircraft is on the ground and commencing its takeoff run and one stick is deactivated, this triggers the takeoff “CONFIG” warning.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-27-20-30 P 5/14 30 MAY 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
GLARESHIELD Ident.: DSC-27-20-30-00001092.0002001 / 15 FEB 11 Applicable to: ALL
(1)
SIDE STICK PRIORITY lt Red arrow light : ‐ comes on in front of the pilot losing authority. ‐ goes out if he has recovered his authority • if the other pilot releases his TAKEOVER pushbutton prior the priority condition is latched. or • If he has used his takeover push button to cancel a latched priority situation. Sidestick priority audio : A “PRIORITY LEFT” or “PRIORITY RIGHT” audio voice message is given each time priority is taken. Green CAPT and F/O lights : ‐ Both lights flash when the pilots move both sidesticks simultaneously and neither takes priority. ‐ When a pilot has taken priority by pressing the takeover pushbutton and the other pilot's sidestick is not at neutral, the light in front of the pilot with priority lights up. It goes out when the other pilot returns his stick to the neutral position.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-27-20-30 P 6/14 30 MAY 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
OVERHEAD PANEL Ident.: DSC-27-20-30-00001093.0002001 / 15 FEB 11 Applicable to: ALL
(1)
ELAC 1(2) pushbutton Controls the Elevator and Aileron Control (ELAC) Computer 1(2).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D→
DSC-27-20-30 P 7/14 30 MAY 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ON
:
OFF
:
FAULT :
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
ELAC 1(2) performs the following functions: ‐ Normal pitch and roll ‐ Alternate pitch ‐ Direct pitch and roll ‐ Abnormal attitude ‐ Aileron droop ‐ Acquisition of autopilot orders. The corresponding computer is not active. Switching it OFF, then ON, resets the computer. Comes on amber, along with an ECAM caution: ‐ When a failure is detected ‐ During ELAC power-up test (eight seconds). Note:
The ELAC power-up test occurs when electrical power is turned on, or after the occurrence of an electrical transient lasting longer than 25 ms.
The FAULT light goes off, when the pilot selects OFF, or at the end of the ELAC power-up test, if its results are satisfactory. (2)
SEC 1(2)(3) pushbutton Controls the spoiler and elevator (SEC) computers 1(2)(3). ON : SEC 1(2)(3) performs the following functions: ‐ Normal roll (by controlling the spoilers) ‐ Speedbrakes and ground spoilers ‐ Alternate pitch (SEC 1 and SEC 2 only) ‐ Direct pitch (SEC 1 and SEC 2 only) ‐ Direct roll ‐ Abnormal attitude. OFF : The corresponding computer is not active. Switching it OFF, then on, resets the computer. FAULT : Comes on amber, along with an ECAM caution, when a failure is detected. The FAULT light goes off, when the pilot selects OFF.
(3)
FAC 1(2) pb sw Controls the flight augmentation computer (FAC) 1(2). ON : Both FACs perform the following functions: ‐ Normal roll (coordinating turns and damping dutch roll) ‐ Rudder trim ‐ Rudder travel limit ‐ Alternate yaw
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-27-20-30 P 8/14 30 MAY 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
OFF
:
FAULT :
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
The corresponding computer is not active. Switching it OFF and then ON resets the computer. Lights up in amber, along with a caution on ECAM, when a failure is detected. The FAULT light goes out when the pilot selects OFF. SIDE STICK INDICATIONS ON PFD
Ident.: DSC-27-20-30-00001094.0001001 / 10 DEC 09 Applicable to: ALL
On the ground, after the first engine start, sidestick position indications appear white on both PFDs. The indications disappear when the aircraft goes from the ground into flight.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← D to E
DSC-27-20-30 P 9/14 30 MAY 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
ECAM F/CTL PAGE Ident.: DSC-27-20-30-00001095.0004001 / 27 JAN 12 Applicable to: ALL
(1)
Spoilers/Speedbrakes’ Indication
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F→
DSC-27-20-30 P 10/14 30 MAY 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
(2)
Hydraulic System Pressure Indication It is normally green. It becomes amber, if the hydraulic system’s pressure decreases.
(3)
ELAC/SEC Indication ‐ ELAC and SEC labels are always displayed in white ‐ The computer number is normally in green, and boxed in grey. The number and box become amber, if the computer fails, or is switched OFF.
(4)
Aileron position indication It is indicated with a white scale and green index. It changes to amber, when neither (green nor blue) servojack is available.
(5)
Aileron and elevator actuator indication “G” and “B” are normally displayed in green. They become amber, in the case of a green or blue hydraulic system low pressure. The partial box also becomes amber, if the associated computer or actuator fails.
(6)
Elevator position indication It is indicated with a white scale and green index. The index becomes amber, when both associated actuators are not available.
(7)
Pitch trim position indication The pitch trim numbers are in green. They become amber, if green and yellow hydraulic system pressure decreases. The “PITCH TRIM” legend is in white. It becomes amber, if the pitch trim jams.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←F→
DSC-27-20-30 P 11/14 30 MAY 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(8)
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
Yaw control indications
(A) Rudder position indication It is normally in green. The rudder symbol becomes amber, if the blue, green, and yellow hydraulic pressures are low. (B) Rudder travel limiter It is normally in green. It becomes amber when travel limiter 1 and 2 are faulty. Two TLU messages are displayed in amber when the TLU indexes are suppressed. (C) Rudder trim position It is normally in blue. It becomes amber, if the rudder trim reset fails.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←F
DSC-27-20-30 P 12/14 30 MAY 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
ECAM WHEEL PAGE Ident.: DSC-27-20-30-00001096.0002001 / 15 FEB 11 Applicable to: ALL
(1)
Spoilers/Speedbrakes’ Indication These indications are identical to those displayed on the FLT CTL page.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
G
DSC-27-20-30 P 13/14 30 MAY 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-27-20-30 P 14/14 30 MAY 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - WARNINGS AND CAUTIONS
WARNINGS AND CAUTIONS Ident.: DSC-27-20-40-00004077.0015001 / 15 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-27-20-40 P 1/4 03 APR 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - WARNINGS AND CAUTIONS
E/WD: FAILURE TITLE conditions
AURAL WARNING
MASTER LIGHT
CONFIG SLATS/FLAPS NOT IN T.O CONFIG, or CONFIG SPD BRK NOT RETRACTED, or CONFIG PITCH TRIM NOT IN TO RANGE, or CONFIG RUD TRIM NOT IN T.O RANGE A/C not in TO configuration when thrust levers are set at TO, or Flex TO, or when pressing TO CONFIG. pb.
SD PAGE CALLED
CRC
5, 6, 7, 8
MASTER WARN
NIL
L + R ELEV FAULT
NIL
L (R) SIDESTICK FAULT
NIL
Transducers, on pitch or roll axis, are failed on one sidestick.
ELAC 1 (2) FAULT
FAULT lt on ELAC pb
Failure of ELAC
ELAC 1 (2) FAULT
F/CTL SINGLE CHIME
MASTER CAUT
FCDC 1 + 2 FAULT Failure of both FCDCs.
DIRECT LAW ALTN LAW
FAULT lt on SEC pb
3, 4, 5
NIL
4, 5, 7
4, 5, 7, 8
NIL
Alternate laws are active.
Both sidesticks are moved simultaneously.
3, 4, 5, 7, 8
NIL
PFD message
Direct laws are active.
DUAL INPUT
Red SIDESTICK PRIORITY lt
(1)
PFD message
Loss of both elevators.
Failure of one SEC.
NIL
F/CTL
L or R sidestick is inoperative (takeover pb pressed more than 30 s) when thrust levers are set at TO, or Flex TO, or when pressing TO CONFIG pb.
SEC 1 (2) (3) FAULT
FLT PHASE INHIB
NIL
CONFIG R (L) SIDESTICK FAULT (BY TAKE OVER)
One sidestick transducer fault.
LOCAL WARNING
Synthetic voice repeated every 5 s
NIL NIL
SIDESTICK Priority light
NIL
Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
DSC-27-20-40 P 2/4 03 APR 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - WARNINGS AND CAUTIONS
E/WD: FAILURE TITLE conditions
AURAL WARNING
MASTER LIGHT
GND SPLR FAULT
Continued from the previous page FLT SD PAGE LOCAL PHASE CALLED WARNING INHIB
Loss of ground spoiler function in SEC 1 + 3 or 1 + 2 or 2 + 3 or 1 + 2 + 3.
SPD BRK DISAGREE
Position disagree between surfaces and lever position.
F/CTL
3, 4, 5
NIL
1, 2, 3, 4, 5, 8, 9, 10
SPD BRK FAULT
Speedbrake lever transducers to SEC 1 and 3 failed.
SPD BRK STILL OUT
Speedbrake out with at least one engine not at idle.
STABILIZER JAM
SINGLE CHIME
MASTER CAUTION
Loss of the electrical control of the stabilizer (with or without jamming of the stabilizer)
L (R) ELEV FAULT
4, 5
Loss of both servojacks on one elevator, or activation of elevator flutter protection in ELAC.
L (R) AIL FAULT
NIL
Loss of both servojacks on one aileron.
SPLR FAULT
3, 4, 5, 7
Loss of one or more spoilers.
ELAC 1 PITCH FAULT
Failure of pitch channel in ELAC 1.
F/CTL
ELAC 2 PITCH FAULT
3, 4, 5, 7, 8
Failure of pitch channel in ELAC 2, or loss of one or both ELAC 2 rudder pedal transducers.
GND SPLR 1 + 2 (3 + 4)
Ground spoiler channel failed in SEC 3 (1).
ELEV SERVO FAULT
Loss of one servojack on one elevator.
NIL
3, 4, 5
NIL
SPD BRK 2 (3 + 4) FAULT
Speedbrake lever transducers to SEC 3 (1) failed.
AIL SERVO FAULT
3, 4, 5, 7, 8
Loss of one servojack on one aileron, or loss of one or both ELAC 1 rudder pedal transducers.
FCDC 1 (2) FAULT
NIL Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
DSC-27-20-40 P 3/4 03 APR 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - WARNINGS AND CAUTIONS
E/WD: FAILURE TITLE conditions
AURAL WARNING
SIDESTICK PRIORITY
MASTER LIGHT
Continued from the previous page FLT SD PAGE LOCAL PHASE CALLED WARNING INHIB 3, 4, 5, 6, 7, 8, 9
Failure in a sidestick priority logic circuit. The red SIDESTICK PRIORITY light comes on, as soon as the sidestick becomes inoperative.
(1)
MEMO DISPLAY ‐ The “SPEED BRK” memo display logic: • When the speedbrakes are extended in Flight Phases 2, 3, 4, and 5, the “SPEED BRK” memo flashes in amber. • When the speedbrakes are extended in Flight Phases 6 and 7, the “SPEED BRK” memo appears in green. It flashes in amber, after 50 s, if at least one engine is above idle. ‐ The “GND SPLRS ARMED” message appears in green, when the ground spoilers are armed.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-27-20-40 P 4/4 03 APR 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - ELECTRICAL SUPPLY
BUS EQUIPMENT LIST Ident.: DSC-27-20-50-00001106.0001001 / 10 DEC 09 Applicable to: ALL
NORM AC
COMPUTERS
MAIN FLT CTL
PITCH TRIM
RUDDER TRIM RUDDER TRAVEL LIMIT (1)
ELAC 1 ELAC 2 SEC 1 SEC 2 SEC 3 FAC 1 FAC 2 FCDC 1 FCDC 2 MOTOR 1 MOTOR 2 MOTOR 3 MOTOR 1 MOTOR 2 INDIC MOTOR 1 MOTOR 2
DC
AC ESS
DC2
EMER ELEC DC HOT ESS X HOT 1 (1) HOT 2 (1) X HOT 1 (1)
DC2 DC2 X AC2
SHED
DC2 SHED DC2 DC2
HOT 2 (1) X
DC2 X DC2 DC2 X DC2
standby supply
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-27-20-50 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLIGHT CONTROL SYSTEM - ELECTRICAL SUPPLY
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-27-20-50 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321
FLAPS AND SLATS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-27-30-10-00001097.0001001 / 10 DEC 09 Applicable to: ALL
Each wing has the following lift augmentation devices : ‐ Two flap surfaces. ‐ Five slat surfaces. These surfaces are electrically controlled and hydraulically operated. The pilot extends slats and flaps by moving the FLAPS lever on the center pedestal. It has five positions. MAIN COMPONENTS Ident.: DSC-27-30-10-00001098.0001001 / 10 DEC 09 Applicable to: ALL
The slat and flap systems are similar, comprising : ‐ Two slat flap control computers (SFCCs), each containing one slat channel and one flap channel. ‐ A power control unit (PCU) consisting of two independent hydraulic motors coupled by a differential gearbox. The motors use green and blue hydraulic power for the slats and yellow and green power for the flaps. Pressure-off brakes (POBs) lock the transmission when the slat or flap surfaces have reached the selected position or if hydraulic power fails. ‐ Five slat surfaces and two flap surfaces per wing. ‐ An assymetry position pick-off unit (APPU) that measures the assymetry between the left and right wings. ‐ A flap disconnect detection system, which detects attachment failure and inhibits flap operation in order to prevent further damage. A sensor detects the failure by measuring excessive differential movement between the inner and the outer flaps. ‐ Wingtip brakes (WTBs), activated in case of assymetry, mechanism overspeed, symmetrical runaway, or uncommanded movement of the surfaces. They cannot be released in flight. They use blue and green hydraulic power for the slats and for the right wing flaps, and blue and yellow hydraulic power for the left wing flaps. ‐ Feedback position pick-off units (FPPUs) that feed back position information to the SFCCs. ‐ An instrumentation position pick-off unit (IPPU) that sends position data to the ECAM.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-27-30-10 P 1/4 29 JUL 11
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Note:
FLAPS AND SLATS - DESCRIPTION
If the flap wingtip brakes are on, the pilot can still operate the slats, and if the slat wingtip brakes are on, he can still operate the flaps. If one SFCC is inoperative, slats and flaps both operate at half speed. If one hydraulic system is inoperative, the corresponding surfaces (slats or flaps) operate at half speed.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-27-30-10 P 2/4 29 JUL 11
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321
FLAPS AND SLATS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
ARCHITECTURE Ident.: DSC-27-30-10-00001099.0001001 / 10 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-27-30-10 P 3/4 29 JUL 11
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321
FLAPS AND SLATS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
CONFIGURATIONS Ident.: DSC-27-30-10-00001100.0001001 / 18 MAR 11 Applicable to: ALL
The FLAPS lever has five positions: 0, 1, 2, 3 and FULL. Two configurations correspond to position 1: Configuration 1 and Configuration 1 + F. The pilot selects these as follows:
(1)
When in Configuration 1 + F, the flaps retract to 0 ° automatically at 210 kt (before the airspeed reaches VFE).
(2)
When in configuration 1, the flaps extend to 10 ° automatically at 100 kt. ALPHA/SPEED LOCK FUNCTION (SLATS)
Ident.: DSC-27-30-10-00001101.0001001 / 10 DEC 09 Applicable to: ALL
This function inhibits slat retraction at high angles-of-attack and low speeds. The SFCCs use corrected angle-of-attack (alpha) or airspeed information from the ADIRUs to inhibit slat retraction. If alpha exceeds 8.5 ° or the airspeed goes below 148 kt, retraction from position 1 to position 0 is inhibited. The inhibition is removed when alpha goes below 7.6 ° and, when the speed exceeds 154 kt. This function is not active if : ‐ Alpha exceeds 8.5 ° or the airspeed goes below 148 kt, after the flight crew has moved the lever to 0 ‐ The aircraft is on the ground, and its speed is less than 60 kt.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D to E
DSC-27-30-10 P 4/4 29 JUL 11
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321
FLAPS AND SLATS - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
PEDESTAL Ident.: DSC-27-30-20-00001102.0001001 / 18 MAR 11 Applicable to: ALL
The five lever positions correspond to the following surface positions : Indications on ECAM
Position
SLATS
FLAPS
0
0
1 1+F 2
1
18
2 3 FULL
22
0 0 10 15
CRUISE
22
20
3
27
35
FULL
TAKEOFF
HOLD
APPR LDG
Before selecting any position, the pilot must pull the lever out of the detent. Balks at positions 1 and 3 prevent the pilot from calling for excessive flap/slat travel with a single action. Note:
The pilot cannot select an intermediate lever position.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-27-30-20 P 1/4 03 APR 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321
FLAPS AND SLATS - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
TAKEOFF IN CONFIGURATION 1 1 + F (18 °/10 °) is selected. If the pilot does not select configuration 0 after takeoff, the flaps retract automatically at 210 kt. TAKEOFF OR GO-AROUND IN CONFIGURATION 2 OR 3 If the pilot selects configuration 1, he gets 1 + F (18 °/10 °) if airspeed is under 210 kt. If the pilot does not select configuration 0 after takeoff, the flaps retract automatically at 210 kt. CONFIGURATION 0 TO CONFIGURATION 1 IN FLIGHT Configuration 1 (18 °/0 °) is selected. Note:
After flap retraction, configuration 1 + F is no longer available until the airspeed is 100 kt or less, unless configuration 2, 3, or FULL has been selected previously. ECAM UPPER DISPLAY
Ident.: DSC-27-30-20-00001103.0002001 / 14 NOV 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← A to B →
DSC-27-30-20 P 2/4 03 APR 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLAPS AND SLATS - CONTROLS AND INDICATORS
(1)
Position indexes These white points indicate that the slats and flaps are in a selectable position. They do not appear, when the aircraft is in clean configuration.
(2)
F and S “F” and “S” normally appear in white. They become amber, if: ‐ Both relevant hydraulic systems fail, unless the aircraft is on ground with both engines stopped. ‐ The wingtip brakes are on. ‐ There is a slats or flaps fault. “S (F) LOCKED” legend, appears in amber, in association with an ECAM caution, when the wingtip brakes are applied, or when the system detects a non-alignment between two flaps. The “A-LOCK” legend pulses in green, when the slat alpha/speedlock function is active.
(3)
Flaps/Slats’ actual position These green boxes indicate the actual flaps/slats position. They become amber, if: ‐ Both relevant hydraulic systems fail, unless the aircraft is on ground with both engines stopped. ‐ The wingtip brakes are on. ‐ There is a slats or flaps fault.
(4)
Selected position It is in blue, when the surfaces are in transit. It disappears, when the selected position is reached.
(5)
Flap lever position The “0”, “1 + F”, “1”, “2”, “3”, or “FULL” legend appears. ‐ It is green, when the slats and flaps are in the selected position. “0” is not displayed, when the aircraft attains clean configuration. ‐ It becomes cyan, when the slats and flaps are in transit.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-27-30-20 P 3/4 03 APR 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLAPS AND SLATS - CONTROLS AND INDICATORS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-27-30-20 P 4/4 03 APR 12
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321
FLAPS AND SLATS - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-27-30-30-00001104.0002001 / 18 MAR 11 Applicable to: ALL
E/WD: FAILURE TITLE conditions
AURAL WARNING
MASTER LIGHT
CRC
MASTER WARN
SD PAGE CALLED
LOCAL WARNING
CONFIG SLATS (FLAPS) NOT IN TO CONFIG
Slats or flaps are not in takeoff configuration, when thrust levers are set at TO or FLEX TO, or when pressing the TO CONFIG pb.
FLT PHASE INHIB
5, 6 (1), 7, 8
FLAP LVR NOT ZERO
1, 2, 3, 4, 5, 7, 8, 9, 10
Flap lever is not in the zero position, and the aircraft is above 22 000 ft.
SLATS (FLAPS) FAULT
Failure of both slat or flap channels.
SLATS (FLAPS) LOCKED
Slats or flaps' wing tip brakes applied, or non alignment detected between 2 flaps.
SINGLE CHIME
MASTER CAUT
4, 5, 8 NIL
NIL
SLATS SYS 1(2) FAULT
Failure of slat channel in one SFCC.
FLAP SYS 1 (2) FAULT
Failure of flap channel in one SFCC.
SLAT (FLAP) TIP BRK FAULT
Failure of one wing tip brake on slats or flaps, or failure of one wing tip brake solenoid on slats, or flaps.
NIL
NIL
3, 4, 5, 7, 8
FLAPS ATTACH SENSOR
Failure of flap attachment's failure detection sensor. (1) The warning is automatically recalled by pressing the TO CONFIG pb .
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-27-30-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLAPS AND SLATS - WARNINGS AND CAUTIONS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-27-30-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321
FLAPS AND SLATS - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-27-30-40-00001105.0001001 / 10 DEC 09 Applicable to: ALL
NORM AC
COMPUTERS
FLAPS SLATS
SFCC 1 slats SFCC 1 flaps SFCC 2 slats SFCC 2 flaps
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DC
AC ESS
EMER ELEC DC ESS X X
HOT
DC2 DC2
DSC-27-30-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS FLIGHT CONTROLS A318/A319/A320/A321
FLAPS AND SLATS - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-27-30-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS FUEL
Intentionally left blank
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-28-PLP PRELIMINARY PAGES TABLE OF CONTENTS SUMMARY OF HIGHLIGHTS
DSC-28-10 Description DSC-28-10-10 General GENERAL................................................................................................................................................................ A
DSC-28-10-20 Tanks Tanks........................................................................................................................................................................A
DSC-28-10-30 Engine Feed GENERAL................................................................................................................................................................ A Main Components....................................................................................................................................................B Engine Feed............................................................................................................................................................ C FUEL FEED SEQUENCE....................................................................................................................................... D
DSC-28-10-50 APU Feed APU FEED............................................................................................................................................................... A
DSC-28-10-60 Fuel Recirculation System Fuel Recirculation System.......................................................................................................................................A
DSC-28-10-70 Refueling and Defueling Refueling - Defueling............................................................................................................................................... A
DSC-28-10-80 Fuel Quantity Indication and Level Sensing FUEL QUANTITY INDICATION (FQI) SYSTEM..................................................................................................... A FUEL LEVEL SENSING CONTROL UNIT (FLSCU).............................................................................................. B Fuel System Architecture........................................................................................................................................ C
DSC-28-10-90 Fuel Tank Inerting System Fuel Tank Inerting System...................................................................................................................................... A
DSC-28-20 Controls and Indicators Overhead Panel....................................................................................................................................................... A Refueling Control Panel...........................................................................................................................................B ECAM Fuel Page.....................................................................................................................................................C ECAM Upper Display.............................................................................................................................................. D 1
DSC-28-30 Warnings and Cautions Warnings and Cautions........................................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-28-PLP-TOC P 1/2 18 SEP 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-28-40 ELECTRICAL SUPPLY BUS EQUIPMENT LIST.......................................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-28-PLP-TOC P 2/2 18 SEP 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title
Toc Index
DSC-28-PLP-TOC Warnings and Cautions
ID 1
DSC-28-10-60 Fuel Recirculation System
A
1
DSC-28-30 Warnings and Cautions
A
1
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Reason Documentation update: Deletion of the "00001131.0050001 Warnings and Cautions" documentary unit. Documentation update: Deletion of the "00001131.0058001 Warnings and Cautions" documentary unit. Update of the description of the Fuel Recirculation System, to specify that if FUEL MODE SEL is in MAN mode, wing tank overflow can occur on ground. Documentation update: Addition of "Warnings and Cautions" documentary unit
DSC-28-PLP-SOH P 1/2 18 SEP 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-28-PLP-SOH P 2/2 18 SEP 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
DESCRIPTION - GENERAL
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-28-10-10-00001107.0001001 / 10 DEC 09 Applicable to: ALL
The fuel system : ‐ Stores fuel in the tanks. ‐ Supplies fuel, in the correct quantities, to the fuel tanks during refueling. ‐ Supplies fuel to the engines and the Auxiliary Power Unit (APU). ‐ Circulates fuel to cool the Integrated Drive Generator (IDG). ‐ Keeps fuel in the outer wing for wing bending and flutter relief.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-28-10-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
DESCRIPTION - GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-28-10-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
DESCRIPTION - TANKS
FLIGHT CREW OPERATING MANUAL
TANKS Ident.: DSC-28-10-20-00001108.0014001 / 22 MAY 12 Applicable to: ALL
The fuel is stored in the wings, and the center section. The wings have inner and outer tanks. There is a vent surge tank outboard of the outer tank in each wing. When the aircraft has been refueled to maximum capacity, the fuel can expand by 2 % (20 °C temperature rise) without spilling. There is an overpressure protector in each vent, outer and inner tank and between the center tank and the left inner tank.
VOLUME WEIGHT(1) (1)
(liters) (US gallons) (KG) (LB)
USABLE FUEL OUTER TANKS INNER TANKS CENTER TANK 880 x 2 7 099 x 2 8 250
TOTAL 24 209
232 x 2
1 875 x 2
2 180
6 395
691 x 2
5 573 x 2
6 476
19 004
1 520 x 2
12 286 x 2
14 281
41 893
Fuel density : 0.785 kg/l or 6.551 lb/US Gal .
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-28-10-20 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
DESCRIPTION - TANKS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-28-10-20 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
DESCRIPTION - ENGINE FEED
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-28-10-30-00001109.0002001 / 10 DEC 09 Applicable to: ALL
The main fuel pump system supplies fuel from the center tank or the inner wing tanks to the engines. The system has six main fuel pumps.
MAIN COMPONENTS Ident.: DSC-28-10-30-A-NG00085 Applicable to: ALL Ident.: DSC-28-10-30-A-00001110.0002001 / 29 MAR 12
TANK PUMPS In normal operation each engine is supplied by one pump in the center tank or two pumps in its own side wing tank. All wing tank pumps remain on throughout the flight. They are fitted with pressure relief sequence valves which ensure that, when all pumps are running, the center tank pumps will deliver fuel preferentially. Ident.: DSC-28-10-30-A-00001111.0001001 / 10 DEC 09
TRANSFER VALVES Two electrical transfer valves are mounted in each wing to permit fuel transfer from outer to inner tank. Ident.: DSC-28-10-30-A-00001112.0001001 / 10 DEC 09
CROSS FEED VALVE A cross feed valve controlled by a double motor allows both engines to be fed from one side or one engine to be fed from both sides. Ident.: DSC-28-10-30-A-00001113.0001001 / 14 FEB 11
ENGINE LP VALVES The fuel flow to an engine can be stopped by its low pressure (LP) fuel valve, the closure of the LPLP fuel valve is by : ‐ the engine master switch, or ‐ the ENG FIRE PUSH pushbutton. Ident.: DSC-28-10-30-A-00001114.0002001 / 29 MAR 12
SUCTION VALVES Closed by pumps pressure in normal operation, they allow engines to be fed by gravity if the inner tank pumps fail. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-28-10-30 P 1/4 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
DESCRIPTION - ENGINE FEED
FLIGHT CREW OPERATING MANUAL
Note:
Center tank pumps are not fitted with suction valves. Therefore, gravity feeding is not possible from the center tank. ENGINE FEED
Ident.: DSC-28-10-30-00001115.0002001 / 22 MAY 12 Applicable to: ALL
FUEL FEED SEQUENCE Ident.: DSC-28-10-30-00001116.0003001 / 14 NOV 11 Applicable to: ALL
The tanks empty in the following sequence : 1. The center tank. 2. The inner tanks : Each inner tank empties down to 750 kg (1 650 lb). 3. The outer tanks : Fuel transfers into the inner tanks. The center tank feeds fuel to the engines, when the center tank pumps are not stopped by the control logic described below. The inner tanks feed the engines when the center tank pumps are stopped. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to D →
DSC-28-10-30 P 2/4 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - ENGINE FEED
CENTER TANK PUMPS CONTROL LOGIC
* Each center tank pump stops, until approximately 500 kg (1 100 lb ) of the fuel in its associated inner tank fuel has been used (when the fuel level reaches the underfull sensors). With the MODE SEL in the MAN position, the center tank pumps will run. In manual mode, the CTR TK PUMP pb-sw must be selected OFF, when the center tank is empty. FUEL TRANSFER FROM OUTER TO INNER TANKS The transfer valves automatically open, when the inner tank fuel reaches the low level (about 750 kg/1 650 lb), thus enabling the fuel to drain from the outer to inner tanks. When open, the valves are latched open. They will automatically close at the next refueling operation.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-28-10-30 P 3/4 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Note:
DESCRIPTION - ENGINE FEED
1. Two level sensors are installed in each inner tank. Each sensor controls two transfer valves, one in each wing, ensuring simultaneous transfer to both wings. 2. The 750 kg/1 650 lb value is based on a level aircraft attitude, with no acceleration. During steep descent or accelerations/decelerations, the transfer valves may open with more than 750 kg/1 650 lb of fuel in each inner tank, and the low level warning may be triggered.
ECAM INDICATION
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D
DSC-28-10-30 P 4/4 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
DESCRIPTION - APU FEED
FLIGHT CREW OPERATING MANUAL
APU FEED Ident.: DSC-28-10-50-00001120.0001001 / 10 DEC 09 Applicable to: ALL
A special fuel pump supplies fuel for APU startup when fuel feed pressure is low (due to loss of tank pumps or loss of normal AC electrical supply). This pump normally runs off the AC ESS SHED, but runs off the AC STAT INV BUS if the AC ESS SHED fails.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-28-10-50 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
DESCRIPTION - APU FEED
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-28-10-50 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
DESCRIPTION - FUEL RECIRCULATION SYSTEM
FLIGHT CREW OPERATING MANUAL
FUEL RECIRCULATION SYSTEM Ident.: DSC-28-10-60-00001121.0002001 / 26 JUL 12 Applicable to: ALL 1
Refer to DSC-70-40-50 IDG Cooling System. Some of the fuel supplied to each engine goes from the high-pressure fuel line in that engine, through the integrated drive generator (IDG) heat exchanger (where it absorbs heat), to the fuel return valve and to the outer fuel tank. This operation ensures the IDG cooling when the oil temperature is high or when at low engine power. The FADEC controls the fuel return valve. If the outer tank is already full, the fuel overflows to the inner tank through a spill pipe. On ground, the fuel recirculation is not inhibited if there is an overflow in the surge tanks (Refer to DSC-70-40-50 IDG Cooling System). If the FUEL MODE SEL pb-sw is in AUTO mode: If center tank is feeding, the wing tank will tend to overfill and the system automatically selects the CTR TK PUMP off when the inner tank is full. The wing tank pumps will feed until the engine have used approximately 500 kg (1 100 lb) of fuel when the fuel level reaches the underfull sensors. The logic circuits then restart the center tank pumps. If the FUEL MODE SEL pb-sw is in MAN mode: If center tank is feeding, the wing tanks will tend to overfill but the system does not automatically select the CTR TK PUMPs OFF when the inner tank is full. Therefore, an overflow of the wing tanks can occur on ground if the CTR TK PUMPs are not switched OFF.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-28-10-60 P 1/2 18 SEP 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - FUEL RECIRCULATION SYSTEM
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-28-10-60 P 2/2 18 SEP 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
DESCRIPTION - REFUELING AND DEFUELING
FLIGHT CREW OPERATING MANUAL
REFUELING - DEFUELING Ident.: DSC-28-10-70-00001122.0002001 / 22 MAY 12 Applicable to: ALL
‐ One (two) refueling point(s) is (are) installed under the wings, enabling the aircraft to be refueled from either the right or left side. ‐ A refuel panel is located on the fuselage side beneath the right wing, or under the right or left wing adjacent to the refuel coupling.
A gallery connects the refuel coupling to each tank's refuel valve. Refueling is normally automatic, the required fuel load being set on the preselector. Manual control is also available. Automatic refueling starts with the outer cells. If the selected fuel load exceeds the wing tank capacity, the center tank is simultaneously refueled. When an outer cell is full the fuel overflows into the inner cell through a spill pipe. Refuel valves close automatically, when the tanks contain the preselected load, or when sensors detect a high fuel level. The aircraft can be refueled, when only battery power is available. The wing tanks can be refueled by gravity, through refueling points on top of the wings. A transfer valve, between the engine feed system and the refueling gallery, allows : ‐ The tank pumps to transfer fuel from one tank to another. ‐ Defueling through the refuel coupling. Approximate refueling time at nominal pressure is : ‐ 17 min for wing tanks. ‐ 20 min for all tanks.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-28-10-70 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - REFUELING AND DEFUELING
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-28-10-70 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - FUEL QUANTITY INDICATION AND LEVEL SENSING
FUEL QUANTITY INDICATION (FQI) SYSTEM Ident.: DSC-28-10-80-00001123.0001001 / 10 DEC 09 Applicable to: ALL
The FQI is a computerized system that : ‐ transmits the actual total fuel mass, as well as the quantity and temperature of fuel in the tanks, to the ECAM. ‐ controls automatic refueling. Two channels perform fuel computations : channel 2 activates automatically if channel 1 fails. The FQI system has : ‐ an FQI computer. ‐ a set of capacitance probes in each tank to measure fuel level and temperature. ‐ one densitometer (cadensicon) sensor in each wing inner tank permitting the calculation of the fuel quantity. ‐ one Capacitance Index Compensator (CIC) in each inner tank giving the dielectric constant of the fuel in case of cadensicon failure. ‐ a quantity indicator for each tank installed on the refuel/defuel panel. ‐ a preselector on the refuel/defuel panel that shows the preselected and actual total fuel quantity. FUEL LEVEL SENSING CONTROL UNIT (FLSCU) Ident.: DSC-28-10-80-00001124.0001001 / 14 FEB 11 Applicable to: ALL
The fuel level system generates fuel-level and fuel-temperature signals in order to operate the appropriate switching functions for refueling and defueling and control the IDG cooling recirculation system and the center-tank-to-wing-tank fuel transfer system. The FLSCU comprises : ‐ fuel level sensors in the tanks to sense high, low, and overflow levels. ‐ a fuel temperature sensor to control the IDG cooling recirculation. When fuel quantity in one wing tank goes below 750 kg (1 650 lb), the low-level sensor triggers the LO LVL warning on ECAM.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
DSC-28-10-80 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - FUEL QUANTITY INDICATION AND LEVEL SENSING
FUEL SYSTEM ARCHITECTURE Ident.: DSC-28-10-80-00001125.0001001 / 22 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-28-10-80 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
DESCRIPTION - FUEL TANK INERTING SYSTEM
FLIGHT CREW OPERATING MANUAL
FUEL TANK INERTING SYSTEM Ident.: DSC-28-10-90-00013692.0001001 / 18 MAR 11 Applicable to: ALL
The A318, A319, A320 and A321 aircraft are equipped with a Fuel Tank Inerting System. The aim of this system is to reduce the flammability in the fuel tanks that have a high flammability exposure. The fuel center tank is the only one that has a high flammability exposure. Therefore, the Fuel Tank Inerting System only needs to be installed for the center tank. All other tanks do not need Fuel Tank Inerting System installation. To reduce the flammability in the center tank, the Fuel Tank Inerting System produces an oxygen-depleted air that goes in the center tank to replace the ambient air. The system is installed in the belly fairing of the aircraft, and is composed by: ‐ A conditioned Service Air System (CSAS) ‐ An Inert Gas Generation System (IGGS). The CSAS extracts and conditions some engine bleed air to adequate pressure and temperature. Then, the air goes through the IGGS where an Air Separation Module taps the nitrogen molecules. Therefore, an oxygen-depleted air is produced (with less than 12 % of oxygen) and replaces the ambient air of the center tank.
The Fuel Tank Inerting System does not require any flight crew action. It works independently as soon as the engines start and until they stop.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-28-10-90 P 1/2 25 NOV 11
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - FUEL TANK INERTING SYSTEM
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-28-10-90 P 2/2 25 NOV 11
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
OVERHEAD PANEL Ident.: DSC-28-20-00001126.0002001 / 17 MAR 11 Applicable to: ALL
(1)
L (R) TK PUMPS 1 (2) pushbutton sw On : Pump is on, but only fuel feeds, when the center tank pumps' delivery pressure drops below the threshold. OFF : Pump is OFF, and the OFF button comes on white. FAULT light : Amber light, and ECAM caution, comes on, when the delivery pressure drops. It does not come on when OFF is selected.
(2)
MODE SEL pushbutton sw AUTO : Control of center tank pumps is automatic. • They run at engine start for 2 min. • Before or after the engine start sequence, the pumps run if the slats are retracted. • They stop automatically 5 min after center tank low level is reached.
(3)
MAN
:
FAULT light
:
Flight crew manually controls the center tank pumps manually with the center tank pumps' pushbutton. Amber light comes on, and ECAM caution comes on when center tank has more than 250 kg (550 lb) of fuel and the left or right wing tank has less than 5 000 kg (11 000 lb).
CTR TK PUMP 1(2) pushbutton sw On : • Pump runs, if MAN mode is selected on the MODE SEL pushbutton. • Pump is automatically controlled when AUTO mode is selected.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-28-20 P 1/8 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
OFF FAULT light (4)
: :
Pump is OFF and OFF button comes on white. Amber light and associated ECAM caution come on, when the pump is in operation and the delivery pressure drops.
X FEED pushbutton sw OFF : The valve closes, and the pushbutton does not come on. ON : The valve opens, and the ON pushbutton comes on in white. OPEN light : This green light comes on, when the valve is fully open. REFUELING CONTROL PANEL
Ident.: DSC-28-20-00001128.0003001 / 22 MAY 12 Applicable to: ALL
(1)
FUEL QUANTITY indicator The number shows the quantity of fuel in each tank.
(2)
HI LVL light This blue light comes on, when the system detects a high fuel level. The corresponding refuel valve closes automatically.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← A to B →
DSC-28-20 P 2/8 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
(3)
REFUEL VALVES selector (guarded in NORM) NORM : Automatic refueling logic controls the refuel valves. OPEN : Valves open when the MODE SELECT sw is set to the REFUEL or DEFUEL XFR position. Each refuel valve closes, when the system detects a high level in the associated tank. SHUT : Valves close.
(4)
MODE SELECT sw (guarded at OFF) OFF : Refuel system is de-energized. Refuel valves are closed. REFUEL : Refuel valves operate in automatic or in manual mode depending on the position of REFUEL VALVES sw. DEFUEL XFR : Refuel/Defuel transfer valve opens. Refuel valve opens if the associated REFUEL VALVE sw is at OPEN.
(5)
OPEN light This amber light comes on when the defuel transfer valve is open.
(6)
TEST sw HI LVL Note:
:
The HI LVL lights come on if high level sensors and associated circuits are serviceable.
If tanks are full (HI LVL lights on) during this test, the HI LVL lights go out if high level sensors and associated circuits are serviceable.
LTS
:
Lights on panel and all 8's on FQI and preselector come on.
(7)
PRESELECTED display This display shows the preselected total fuel quantity in kg (lb) × 1 000 (multiply by 1 000 to get actual amount).
(8)
Preselector sw Pressing the left or right side of the switch decreases or increases the preselected quantity.
(9)
ACTUAL display This display shows the total fuel on board.
(10) END light ‐ This green light comes on steady when automatic refueling is completed ‐ It flashes green if refueling is aborted. (11) CKPT light Not used.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
DSC-28-20 P 3/8 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
CONTROLS AND INDICATORS
(12) BATT POWER toggle switch ON : When the flight crew switches this ON momentarily and releases it, HOT BUS 1 supplies the FQI. After completion of the FQI tests (about 40 s), the fuel quantity indications appear and refuel operation can be selected. The electrical supply is automatically cut off: ‐ After 10 min, if no refuel operation is selected, or ‐ At the end of refueling. NORM:
The FQI is not supplied by batteries. ECAM FUEL PAGE
Ident.: DSC-28-20-00001129.0013001 / 22 MAY 12 Applicable to: ALL
(1)
Wing pump indications Inline - Green : Pump pressure is normal (pump contactor on). “LO” - Amber : Pump pressure is low (pump contactor on). Crossline - Amber : Pump contactor is off.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
DSC-28-20 P 4/8 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
(2)
CTR tank pump indications Inline - Green : Pump pressure is normal (pump contactor on). “LO” - Amber : Pump pressure is low (pump contactor on). Crossline - Green : Pump contactor is off, and auto shut-off is required. Crossline - Amber : Pump contactor is off, and auto shut-off is not required.
(3)
LP valve (ENG) indications Inline - Green : The valve is open. Inline - Amber : The valve is open, with the ENG MASTER switch OFF. Crossline - Amber : The ENG valve is fully closed. Transit - Amber : The valve is in transit.
(4)
X feed indications Inline - Green Inline - Amber Crossline - Green Crossline - Amber Transit - Amber
(5)
: : : : :
The valve is open. The valve is open, with X Feed pushbutton off. The valve is closed. The valve is closed with X feed pushbutton ON. The valve is in transit.
Transfer valve indications Outer to Inner Transfer
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C→
DSC-28-20 P 5/8 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
CONTROLS AND INDICATORS
(6)
APU Indications
(7)
Fuel temperature indication This appears, when its associated temperature sensor is wet. It is normally in green. An advisory only appears in phases 2 and 6, when the fuel temperature is: ‐ Above 45 °C for the inner cell, or 55 °C for the outer cell. ‐ Below -40 °C. It becomes amber, and the ECAM displays a caution, if the temperature goes above the high limit or below the low limit.
(8)
Fuel quantity indication
‐ It is normally in green. ‐ An amber line appears across the last two digits, when the FQI is inaccurate (Refer to PRO-SUP-28 FQI IN DEGRADED MODE). The outer indication is boxed amber, if both transfer valves fail to open when the inner is at low level. ‐ The center tank indication is boxed amber, if both center tank pumps are failed, or are switched OFF.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C→
DSC-28-20 P 6/8 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
CONTROLS AND INDICATORS
‐ An advisory appears in flight phases 2 and 6, when the difference between the fuel quantities in the two wings is greater than 1 500 kg (3 300 lb). The wing inner and outer tank indications pulse with the highest fuel level. ‐ Units may either be in KG or LB, depending on the DMC pin program. (9)
Fuel On Board (FOB) indication It is normally in green. An amber line appears across the last two digits, when the FQI is inaccurate (Refer to PRO-SUP-28 FQI IN DEGRADED MODE). Units may either be in KG or LB, depending on the DMC pin program. The indication is half-boxed in amber, if: ‐ Center tank pumps fail, or are switched OFF. ‐ Both transfer valves fail to open, when the inner tank is at low level.
(10)
Fuel Used indication F.USED 1 3 100 ‐ The engine identification number is in amber, when the engine is below idle. It is in white, when it is at, or above, idle. ‐ The fuel used indication is green from flight phase 2, until electrical power is cut off at the end of the flight. It is automatically reset, when the engine is started on ground. ‐ Units may either be in KG or LB, depending on the DMC pin program.
( 11)
Fuel Flow indication The Total Fuel Flow is displayed in kg/mn. Units may either be in KG or LB, depending on the DMC pin program. ‐ It is normally in green. ‐ It is replaced by an amber XX if there is no valid data.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C
DSC-28-20 P 7/8 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
ECAM UPPER DISPLAY Ident.: DSC-28-20-00001130.0005001 / 18 MAR 11 Applicable to: ALL
(1)
Total fuel indication A half amber box appears around FOB, when the displayed quantity is not all usable (intercell transfer valve failure or loss of center tank pumps). In case of degraded data, the last two significant digits are dashed (Refer to PRO-SUP-28 FQI IN DEGRADED MODE). Units may either be in KG or LB, depending on the DMC pin program.
(2)
Memo indications: (green)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D
DSC-28-20 P 8/8 30 MAY 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS
1 Ident.: DSC-28-30-00001131.0002001 / 16 FEB 11
Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-28-30 P 1/4 18 SEP 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
E/WD: FAILURE TITLE conditions
AURAL WARNING
MASTER LIGHT
SD PAGE CALLED
CTR TK PUMP 1(2) LO PR CTR TK PUMPS LO PR CTR TK PUMPS OFF
CTR TK pb at OFF with no FAULT
AUTO FEED FAULT
L(R) WING TK LO LVL
FLT PHASE INHIB
L(R) TK PUMP 1+2 FAULT lt 3, 4, 5, CTR TK PUMP 1(2) 7, 8 (1) FAULT lt CTR TK PUMP FAULT lts OFF lt on 1, 3, 4, 5, CTR TK 7, 8, 9, 10 PUMP pb
L(R) TK PUMP 1 + 2 LO PR
(CTR TK > 250 kg (550 lb) and L or R WING TK < 5 000 kg (11 000 lb) ––––––––––––OR ––––––––––– (CTR TK pumps do not stop after slat extension or CTR TK low level)
LOCAL WARNING
SINGLE CHIME
MODE SEL FAULT lts ––––– NIL
MASTER CAUT
(750 kg - 1 650 lb)
FUEL
L + R WING TK LO LVL
3, 4, 5, 8
3, 4, 5, 7, 8, 9
Low level detected in both wing inner cells (remaining flight time is about 30 min)
L(R) OUTER TK HI TEMP or L(R) INNER TK HI TEMP
Fuel temp above: In outer cell, above 55 °C on ground. In outer cell, above 60 °C in flight. In inner cell, above 45 °C on ground. In inner cell, above 54 °C in flight.
NIL
3, 4, 5, 7, 8
L(R) XFR VALVE CLOSED
Both transfer valves fail to open after inner cell low level.
ENG 1(2) LP VALVE OPEN
4, 5, 7, 8
Valve disagree in open position.
APU LP VALVE FAULT Valve position disagree.
L(R) OUTER TK LO TEMP, or L(R) INNER TK LO TEMP
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
NIL
NIL
3, 4, 5, 7, 8 (2) Continued on the following page
←A→
DSC-28-30 P 2/4 18 SEP 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
E/WD: FAILURE TITLE conditions
WARNINGS AND CAUTIONS
AURAL WARNING
MASTER LIGHT
Continued from the previous page FLT SD PAGE LOCAL PHASE CALLED WARNING INHIB
Fuel temperature < approx. -43 °C L(R) TK PUMP 1(2) FAULT lt
L(R) TK PUMP 1(2) LO PR L(R) XFR VALVE OPEN
Either transfer valve opens before inner tank reaches low level.
NIL
X FEED VALVE FAULT Valve position disagree.
FQI CH 1(2) FAULT
(1) (2)
Inhibited if pump selected OFF PUMP LO PR is inhibited, if the pump is selected OFF in phases 1 and 10.
MEMO DISPLAY ‐ OUTR TK FUEL XFRD appears in green, if at least one transfer valve is open in one wing tank ‐ CTR TK FEEDG appears in green, if at least one center tank pump is energized ‐ FUEL X FEED appears in green, if the fuel X FEED valve pushbutton is ON, and the X FEED valve is not fully closed. It appears in amber in flight phases 3, 4, or 5 ‐ REFUELG appears in green, when the door of the refuel control panel on the fuselage or on the wing is open.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-28-30 P 3/4 18 SEP 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-28-30 P 4/4 18 SEP 12
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-28-40-00001132.0001001 / 10 DEC 09 Applicable to: ALL
NORM
FQI
INNER TANK PUMPS
CTR TK PUMPS CROSS FEED VALVE
ENGINE LP VALVES
XFR VALVES
APU
(1) (2) (3)
CH 1 CH 2 L1 L2 R1 R2 1 2 MOT 1 MOT 2 ENG 1 MOT 1 ENG 1 MOT 2 ENG 2 MOT 1 ENG 2 MOT 2 L1 L2 R1 R2
AC
DC
AC1 (3) AC2 AC1 (3) AC2 AC1 AC2
DC2 DC1 DC2 DC1 DC2 DC1 DC2
AC ESS
EMER ELEC DC ESS SHED
HOT (1) (1)
X (2) (3) X (2) (3)
SHED DC2 X DC2 X DC2 SHED DC2 SHED DC2 AC STAT INV or AC ESS SHED
PUMP
HOT1
LP VALVE DC BAT HOT1 (1) REFUEL VALVES DC2 HOT BUS supplies power during refueling on battery. This occurs, if DC BUS 1 is lost. In smoke configuration (GEN 1 LINE pushbutton OFF), inner tank pumps 1 are supplied directly by IDG (instead of AC 1) and pump relays by DC ESS (instead of DC 1).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-28-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS FUEL A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-28-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS HYDRAULIC
Intentionally left blank
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-29-PLP PRELIMINARY PAGES TABLE OF CONTENTS
DSC-29-10 Description DSC-29-10-10 General GENERAL................................................................................................................................................................ A
DSC-29-10-20 Generation GREEN SYSTEM PUMP.........................................................................................................................................A BLUE SYSTEM PUMPS..........................................................................................................................................B YELLOW SYSTEM PUMPS....................................................................................................................................C POWER TRANSFER UNIT (PTU).......................................................................................................................... D RAM AIR TURBINE (RAT)......................................................................................................................................E SYSTEM ACCUMULATORS................................................................................................................................... F PRIORITY VALVES.................................................................................................................................................G FIRE SHUTOFF VALVES....................................................................................................................................... H LEAK MEASUREMENT VALVES.............................................................................................................................I FILTERS................................................................................................................................................................... J GENERATION..........................................................................................................................................................K RESERVOIR PRESSURIZATION............................................................................................................................L Indications................................................................................................................................................................M
DSC-29-10-30 Distribution DISTRIBUTION........................................................................................................................................................ A
DSC-29-20 CONTROLS AND INDICATORS OVERHEAD PANEL................................................................................................................................................ A MAINTENANCE PANEL.......................................................................................................................................... B ECAM HYD Page.................................................................................................................................................... C
DSC-29-30 Warnings and Cautions Warnings and Cautions........................................................................................................................................... A
DSC-29-40 ELECTRICAL SUPPLY BUS EQUIPMENT LIST.......................................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-29-PLP-TOC P 1/2 30 MAY 12
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-29-PLP-TOC P 2/2 30 MAY 12
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321
DESCRIPTION - GENERAL
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-29-10-10-00001133.0001001 / 10 DEC 09 Applicable to: ALL
The aircraft has three continuously operating hydraulic systems : blue, green, and yellow. Each system has its own hydraulic reservoir. Normal system operating pressure is 3 000 PSI (2 500 PSI when powered by the RAT). Hydraulic fluid cannot be transferred from one system to another.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-29-10-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321
DESCRIPTION - GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-29-10-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321
DESCRIPTION - GENERATION
FLIGHT CREW OPERATING MANUAL
GREEN SYSTEM PUMP Ident.: DSC-29-10-20-00001134.0001001 / 10 DEC 09 Applicable to: ALL
A pump driven by engine 1 pressurizes the green system. BLUE SYSTEM PUMPS Ident.: DSC-29-10-20-00001135.0001001 / 10 DEC 09 Applicable to: ALL
An electric pump pressurizes the blue system. A pump driven by a ram air turbine (RAT) pressurizes this system in an emergency. YELLOW SYSTEM PUMPS Ident.: DSC-29-10-20-00001136.0001001 / 10 DEC 09 Applicable to: ALL
A pump driven by engine 2 pressurizes the yellow system. An electric pump can also pressurize the yellow system, which allows yellow hydraulics to be used on the ground when the engines are stopped. Crew members can also use a hand pump to pressurize the yellow system in order to operate the cargo doors when no electrical power is available. POWER TRANSFER UNIT (PTU) Ident.: DSC-29-10-20-00001137.0001001 / 14 NOV 11 Applicable to: ALL
A bidirectional power transfer unit enables the yellow system to pressurize the green system and vice versa. The power transfer unit comes into action automatically when the differential pressure between the green and the yellow systems is greater than 500 PSI. The PTU therefore allows the green system to be pressurized on the ground when the engines are stopped.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to D →
DSC-29-10-20 P 1/6 25 NOV 11
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321
DESCRIPTION - GENERATION
FLIGHT CREW OPERATING MANUAL
RAM AIR TURBINE (RAT) Ident.: DSC-29-10-20-00001138.0001001 / 10 DEC 09 Applicable to: ALL
A drop-out RAT coupled to a hydraulic pump allows the blue system to function if electrical power is lost or both engines fail. The RAT deploys automatically if AC BUS 1 and AC BUS 2 are both lost. It can be deployed manually from the overhead panel. It can be stowed only when the aircraft is on the ground. SYSTEM ACCUMULATORS Ident.: DSC-29-10-20-00001139.0001001 / 10 DEC 09 Applicable to: ALL
An accumulator in each system helps to maintain a constant pressure by covering transient demands during normal operation. PRIORITY VALVES Ident.: DSC-29-10-20-00001141.0001001 / 10 DEC 09 Applicable to: ALL
Priority valves cut off hydraulic power to heavy load users if hydraulic pressure in a system gets low. FIRE SHUTOFF VALVES Ident.: DSC-29-10-20-00001142.0001001 / 10 DEC 09 Applicable to: ALL
Each of the green and yellow systems has a fire shutoff valve in its line upstream of its engine-driven pump. The flight crew can close it by pushing the ENG 1(2) FIRE pushbutton.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← D to H
DSC-29-10-20 P 2/6 25 NOV 11
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321
DESCRIPTION - GENERATION
FLIGHT CREW OPERATING MANUAL
LEAK MEASUREMENT VALVES Ident.: DSC-29-10-20-00001143.0001001 / 10 DEC 09 Applicable to: ALL
Each system has a leak measurement valve upstream of the primary flight controls. These valves, which measure the leakage in each circuit, are closed by operation of the LEAK MEASUREMENT VALVES pushbutton switch on the maintenance panel. FILTERS Ident.: DSC-29-10-20-00001144.0001001 / 16 MAR 11 Applicable to: ALL L3
Filters clean the hydraulic fluid as follows : ‐ HP filters on each system and on the reservoir filling system and the normal braking system ‐ return line filters on each line ‐ case drain filters on engine pumps and the blue electric pump (which permit maintenance crew to monitor pump wear by inspecting the filters for the presence of metallic particles).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
I to J
DSC-29-10-20 P 3/6 25 NOV 11
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321
DESCRIPTION - GENERATION
FLIGHT CREW OPERATING MANUAL
GENERATION Ident.: DSC-29-10-20-00001145.0001001 / 10 DEC 09 Applicable to: ALL
RESERVOIR PRESSURIZATION Ident.: DSC-29-10-20-00001146.0001001 / 10 DEC 09 Applicable to: ALL
Normally, HP bleed air from engine 1 pressurizes the hydraulic reservoirs automatically. If the bleed air pressure is too low, the system takes bleed air pressure from the crossbleed duct. The systems maintain a high enough pressure to prevent their pumps from cavitating.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
K to L →
DSC-29-10-20 P 4/6 25 NOV 11
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DESCRIPTION - GENERATION
←L
DSC-29-10-20 P 5/6 25 NOV 11
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321
DESCRIPTION - GENERATION
FLIGHT CREW OPERATING MANUAL
INDICATIONS Ident.: DSC-29-10-20-00001147.0002001 / 16 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
M
DSC-29-10-20 P 6/6 25 NOV 11
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321
DESCRIPTION - DISTRIBUTION
FLIGHT CREW OPERATING MANUAL
DISTRIBUTION Ident.: DSC-29-10-30-00001148.0003001 / 10 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-29-10-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DESCRIPTION - DISTRIBUTION
←A
DSC-29-10-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
OVERHEAD PANEL Ident.: DSC-29-20-00001149.0001001 / 10 DEC 09 Applicable to: ALL
(1)
ENG 1 (2) PUMP pb On : The pump pressurizes the system when the engine is running. OFF : The pump is depressurized. The generation of hydraulic power stops. FAULT lt : This amber light comes on, and the ECAM caution appears, if : ‐ The reservoir level is low ‐ The reservoir overheats ‐ The reservoir air pressure is low ‐ The pump pressure is low (inhibited on the ground, when the engine is stopped). This light goes out, when the crew selects OFF, except during an overheat. (The light stays on as long as the overheat lasts).
(2)
BLUE ELEC PUMP pb AUTO : If AC power is available, the electric pump operates : ‐ In flight ‐ On the ground, if one engine is running or if the crew has pressed the BLUE PUMP OVRD pushbutton on the maintenance panel. OFF : The pump is de-energized.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-29-20 P 1/8 30 MAY 12
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
FAULT lt :
This amber light comes on, and a caution appears on the ECAM, if : ‐ The reservoir level is low ‐ The reservoir overheats ‐ The air pressure in the reservoir is low ‐ The pump is delivering low pressure (inhibited on the ground, when the engines are stopped) ‐ The pump overheats. The light goes out, when the crew selects OFF, except during an overheat. (The light stays on as long as the overheat lasts).
(3)
YELLOW ELEC PUMP pb sw (springloaded) ON : The electric pump is ON. If the electrical power supply is removed, the pump will remain off when electrical power is applied again. Off : The pump is off. It comes on automatically when a crewman sets the lever of the cargo door manual selector valve to OPEN or CLOSE. This inhibits the operation of other yellow system functions (except alternate braking and engine 2 reverse). FAULT lt : This amber light, accompanied by an ECAM caution, comes on if : ‐ the reservoir level is low ‐ air pressure in the reservoir is low ‐ the reservoir overheats ‐ pump pressure is low ‐ the pump overheats. The light goes out when the crew selects OFF, except during an overheat. (The light stays on as long as the overheat lasts).
(4)
PTU pb sw AUTO :
The bidirectional power transfer unit is armed and both the yellow and the green electrohydraulic valves are open. The power transfer unit runs automatically when the differential pressure between the green and yellow systems is more than 500 PSI. Note:
OFF
:
The PTU is inhibited during the first engine start and automatically tested during the second engine start.
Both the green and the yellow PTU electrohydraulic valves close. Power transfer stops.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
DSC-29-20 P 2/8 30 MAY 12
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FAULT lt :
(5)
CONTROLS AND INDICATORS
This amber light comes on, and a caution appears on the ECAM, if : ‐ the green or the yellow reservoir overheats ‐ the green or the yellow reservoir has low air pressure ‐ the green or the yellow reservoir has a low flluid level. The light goes out when the crew selects OFF, except during an overheat. (The light stays on as long as the overheat lasts).
RAT MAN ON pb The flight crew may extend the RAT at any time by pressing the RAT MAN ON pushbutton. Note:
The RAT extends automatically if AC BUS 1 and AC BUS 2 are lost. (Refer to DSC-24-20 Overhead Panel (Cont'd)). MAINTENANCE PANEL
Ident.: DSC-29-20-00001150.0001001 / 17 MAR 11 Applicable to: ALL
(1)
BLUE PUMP OVRD pb sw (springloaded) ON : The blue electric pump is on if the ELEC PUMP pushbutton switch on the HYD panel is at AUTO. Off : The blue electric pump is off.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← A to B →
DSC-29-20 P 3/8 30 MAY 12
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(2)
CONTROLS AND INDICATORS
LEAK MEASUREMENT VALVES pb sw OFF: The corresponding electrohydraulic valve closes and shuts off hydraulic supply to the primary flight controls. On : The corresponding electrohydraulic valve opens to go back to normal hydraulic supply. ECAM HYD PAGE
Ident.: DSC-29-20-00001151.0002001 / 22 MAY 12 Applicable to: ALL
(1)
Reservoir quantity It is in green, unless the fluid level goes below the warning level, in which case it becomes amber.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
DSC-29-20 P 4/8 30 MAY 12
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
(2)
Reservoir LO AIR PRESS This appears in amber, and a caution appears on ECAM, if the air pressure for the indicated reservoir drops below normal.
(3)
Reservoir OVHT This appears in amber, and a caution appears on ECAM, if the temperature of returning hydraulic fluid temperature at the inlet to its reservoir is above normal.
(4)
FIRE VALVE Cross line - Amber : In line - Green :
The valve is fully closed. The valve is not fully closed.
(5)
OVHT This appears in amber if the electric pump for that system (blue or yellow) overheats.
(6)
RAT RAT ▹ White RAT Green RAT ▸ Amber
: :
The RAT is stowed. The RAT is not stowed.
:
Pressure for stowing the RAT has been applied, or the RAT pump is not available.
(7)
ELEC This legend, normally white, becomes amber if the associated power supply fails.
(8)
YELLOW ELEC PUMP control ◃ White : The electric pump is off. Green : The electric pump is ON.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C→
DSC-29-20 P 5/8 30 MAY 12
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
◂ Amber (9)
:
The electric pump is ON and the yellow system has low pressure.
PTU control
(1) Green : Amber :
The power transfer unit (PTU) pushbutton switch is in AUTO and the PTU is not transferring pressure. The PTU pb-sw is OFF.
Green :
The PTU is supplying the green hydraulic system.
Green :
The PTU is supplying the yellow hydraulic system.
(2) (3) (10) ENG PUMP control and low pressure indication In line (Green) : The pushbutton switch for the designated PUMP is on and hydraulic pressure is normal. Cross line (Amber) : The pushbutton switch for the designated PUMP is OFF. “LO” (Amber) : The pushbutton switch for the designated PUMP is on and hydraulic pressure is low. (11) System label YELLOW ▵
pressure > 1 450 PSI white
pressure < 1 450 PSI amber
green
amber
(12) System pressure This legend, normally green, becomes amber when system pressure is below 1 450 PSI.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C→
DSC-29-20 P 6/8 30 MAY 12
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
CONTROLS AND INDICATORS
(13) PUMP This legend, normally white, becomes amber when N2 is below idle.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C
DSC-29-20 P 7/8 30 MAY 12
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-29-20 P 8/8 30 MAY 12
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-29-30-00001152.0005001 / 15 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-29-30 P 1/4 29 JUL 11
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
E/WD: FAILURE TITLE Conditions
B+Y B + G SYS LO PR Y+G
WARNINGS AND CAUTIONS AURAL WARNING
MASTER LIGHT
CRC
MASTER WARN
System pressure ≤ 1 450 PSI (reset if pressure ≥ 1 750 PSI)
SD PAGE CALLED
LOCAL WARNING
FLT PHASE INHIB
FAULT lt
4, 5 (1)
G (Y) RSVR LO AIR PR
3, 4, 5, 7, 8
Air pressure of the reservoir ≤ 22 PSI (reset if air pressure ≥ 25 PSI)
B RSVR LO AIR PR
1, 2, 3, 4, 5, 6, 7
Reservoir air pressure ≤ 30 PSI (detected in flight but only displayed on ground after landing)
FAULT lt on associated pump(s) pb and on PTU pb-sw if Y 3, 4, 5, 7, 8 or G SYS affected
B RSVR LO AIR PR
Reservoir air pressure ≤ 22 PSI reset if pressure ≥ 25 PSI
G (Y)(B) RSVR OVHT Fluid temperature ≥ 93 °C (reset if TEMP ≤ 88 °C)
G (Y)(B) RSVR LO LVL Fluid quantity: < 3.5 l (0.92 US Gal) (green-yellow) < 2.4 l (0.63 US Gal) (blue)
G (Y) ENG 1(2) PUMP LO PR
HYD SINGLE CHIME
4, 5 (2), 7, 8
MASTER CAUT
Pump outlet pressure ≤ 1 750 PSI (reset if pressure ≥ 2 200 PSI)
Y ELEC PUMP LO PR
Yellow system pressure ≤ 1 450 PSI (reset if pressure ≥ 1 750 PSI) with - YELLOW ELEC PUMP pb-sw at ON - Y ENG PUMP and PTU not available
4, 5, 7, 8 FAULT lt on affected pump pb
B ELEC PUMP LO PR
Pump outlet pressure ≤ 1 450 PSI (reset if pressure ≥ 1 750 PSI)
B ELEC PUMP OVHT Y ELEC PUMP OVHT G (Y) SYS LO PR
3, 4, 5, 7, 8 4, 5, 7, 8 (1)
System pressure ≤ 1 450 PSI (reset if pressure ≥ 1 750 PSI)
Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
DSC-29-30 P 2/4 29 JUL 11
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
E/WD: FAILURE TITLE Conditions
WARNINGS AND CAUTIONS
AURAL WARNING
B SYS LO PR
MASTER LIGHT
Continued from the previous page FLT SD PAGE LOCAL PHASE CALLED WARNING INHIB
NIL
1, 4, 5, 7, 8, 10
FAULT lt only in case of G or Y RSVR LO LVL or RSVR LO AIR PR or RSVR OVHT
3, 4, 5, 8, 9, 10
NIL
3, 4, 5, 6, 7, 8, 9
System pressure ≤ 1 450 PSI (reset if pressure ≥ 1 750 PSI)
PTU FAULT
PTU not running on ground in case the differential pressure is above650 PSI, between G and Y system, or in flight PTU still at AUTO position in case of G or Y reservoir low level and G or Y system low pressure.
RAT FAULT
RAT not fully stowed or pressure present in RAT stowing actuator or RAT pump not available (1) Inhibited on the ground (flight phases 1, 2, 9, 10) when corresponding engine is shut down. (2) The HYD G(Y) RSVR LO LVL alert is inhibited for the first 15 s of flight phase 5. The HYD B RSVR LO LVL alert is inhibited for the entire flight phase 5.
MEMO DISPLAY ‐ “RAT OUT” appears in green, if the ram air turbine is not fully stowed. The color changes to amber during flight phases 1 and 2. ‐ “HYD PTU” appears in green, when the power transfer unit is running.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-29-30 P 3/4 29 JUL 11
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-29-30 P 4/4 29 JUL 11
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-29-40-00001153.0001001 / 17 MAR 11 Applicable to: ALL
NORM AC
ENG 1 driven PUMP control ENG 2 driven PUMP control ENG 1 FIRE shut off valve ENG 2 FIRE shut off valve power BLUE ELEC control PUMP power Yellow control ELEC PUMP Power Transfer Unit
DC
(1)
EMER ELEC DC ESS
HOT
DC1 DC2 X X AC1 X AC2(1) DC2 DC2 DC GRND/FLT
LEAK MEASUREMENT VALVES RAT
AC ESS
Manual control
HOT 2 HOT 1
Auto control
or from external power.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-29-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS HYDRAULIC A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-29-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION
Intentionally left blank
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-30-PLP PRELIMINARY PAGES TABLE OF CONTENTS
DSC-30-10 General DSC-30-10-10 Description General.....................................................................................................................................................................A Anti-Ice..................................................................................................................................................................... B Rain Removal.......................................................................................................................................................... C
DSC-30-20 Wing Anti-Ice DSC-30-20-10 Description Description............................................................................................................................................................... A
DSC-30-20-20 Controls And Indicators OVERHEAD PANEL................................................................................................................................................ A ECAM BLEED PAGE.............................................................................................................................................. B
DSC-30-20-30 Warnings And Cautions Warnings and Cautions........................................................................................................................................... A
DSC-30-20-40 Electrical Supply BUS EQUIPMENT LIST.......................................................................................................................................... A
DSC-30-30 Engine Anti-Ice DSC-30-30-10 Description Description............................................................................................................................................................... A
DSC-30-30-20 Controls and Indicators Overhead Panel....................................................................................................................................................... A
DSC-30-30-30 Warnings and Cautions Warnings And Cautions...........................................................................................................................................A
DSC-30-30-40 Electrical Supply Bus Equipment List..................................................................................................................................................A
DSC-30-40 WINDOW HEAT DSC-30-40-10 Description Description............................................................................................................................................................... A
DSC-30-40-20 CONTROLS AND INDICATORS OVERHEAD PANEL................................................................................................................................................ A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-30-PLP-TOC P 1/2 30 MAY 12
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-30-40-30 WARNINGS AND CAUTIONS WARNINGS AND CAUTIONS.................................................................................................................................A
DSC-30-40-40 ELECTRICAL SUPPLY BUS EQUIPMENT LIST.......................................................................................................................................... A
DSC-30-50 Probes Heat DSC-30-50-10 Description Description............................................................................................................................................................... A
DSC-30-50-20 Controls and Indicators Overhead Panel....................................................................................................................................................... A
DSC-30-50-30 Warnings and Cautions Warnings and Cautions........................................................................................................................................... A
DSC-30-50-40 Electrical Supply Bus Equipment List..................................................................................................................................................A
DSC-30-60 RAIN REMOVAL DSC-30-60-10 DESCRIPTION WIPERS................................................................................................................................................................... A RAIN REPELLENT (if installed).............................................................................................................................. B
DSC-30-60-20 CONTROLS AND INDICATORS OVERHEAD PANEL................................................................................................................................................ A REAR COCKPIT...................................................................................................................................................... B
DSC-30-60-30 ELECTRICAL SUPPLY BUS EQUIPMENT LIST.......................................................................................................................................... A
DSC-30-70 ICE DETECTION SYSTEM DSC-30-70-10 DESCRIPTION VISUAL ICE INDICATOR........................................................................................................................................ A
DSC-30-70-30 ELECTRICAL SUPPLY BUS EQUIPMENT LIST.......................................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-30-PLP-TOC P 2/2 30 MAY 12
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GENERAL - DESCRIPTION
GENERAL Ident.: DSC-30-10-10-00001154.0001001 / 16 MAR 11 Applicable to: ALL
The ice and rain protection system allows unrestricted operation of the aircraft in icing conditions and heavy rain. ANTI-ICE Ident.: DSC-30-10-10-00001155.0001001 / 29 MAR 12 Applicable to: ALL
Either hot air or electrical heating protects critical areas of the aircraft as follows: HOT AIR ‐ Three outboard leading-edge slats of each wing ‐ Engine air intakes. ELECTRICAL HEATING ‐ Flight compartment windows ‐ Sensors, pitot probes and static ports ‐ Waste-water drain mast.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
DSC-30-10-10 P 1/2 03 APR 12
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
GENERAL - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
RAIN REMOVAL Ident.: DSC-30-10-10-00001156.0001001 / 29 MAR 12 Applicable to: ALL
Wipers and when necessary, fluid rain repellent, remove rain from the front windshield panels.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-30-10-10 P 2/2 03 APR 12
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
WING ANTI-ICE - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
DESCRIPTION Ident.: DSC-30-20-10-00001157.0002001 / 22 MAY 12 Applicable to: ALL
In flight, hot air from the pneumatic system heats the three outboard slats (3-4-5) of each wing. Air is supplied through one valve in each wing. The WING pushbutton on the ANTI ICE panel controls the valves. When the aircraft is on ground, the flight crew can initiate a 30 s test sequence by turning the system ON. If the system detects a leak during normal operation, the affected side’s wing anti-ice valve automatically closes (Refer to DSC-36-10-50 LEAK DETECTION). When wing anti-ice is selected, the N1 limit is automatically reduced, and the idle N1 is automatically increased. If the electrical power supply fails, the valves close.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-30-20-10 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
WING ANTI-ICE - DESCRIPTION
←A
DSC-30-20-10 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
WING ANTI-ICE - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
OVERHEAD PANEL Ident.: DSC-30-20-20-00001158.0001001 / 16 MAR 11 Applicable to: ALL
(1)
WING ANTI ICE pb sw This switch controls the wing anti ice system on the left and right sides simultaneously. ON : It lights up blue. WING A. ICE appears on the ECAM MEMO page. Wing anti ice control valves open if a pneumatic supply is available. On the ground the wing anti-icing control valves open for 30 s only (test sequence). Off : ON light goes off. Wing anti-icing control valves close. FAULT : Amber light comes on, and caution appears on ECAM, if: ‐ the position of the anti-icing control valve is not the required position, or ‐ low pressure is detected. Note:
The amber FAULT light comes on briefly as the valves transit. ECAM BLEED PAGE
Ident.: DSC-30-20-20-00001159.0001001 / 10 DEC 09 Applicable to: ALL
Refer to DSC-36-20 ECAM Bleed Page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
DSC-30-20-20 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WING ANTI-ICE - CONTROLS AND INDICATORS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-30-20-20 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
WING ANTI-ICE - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-30-20-30-00001160.0001001 / 16 FEB 11 Applicable to: ALL
E/WD: FAILURE TITLE conditions
AURAL WARNING
MASTER LIGHT
SD PAGE CALLED
WING A. ICE OPEN ON GND
On ground, valves remain open more than 35 s after wing anti-ice is selected ON.
SYS FAULT
Valve not open when wing anti-ice selected ON.
SINGLE CHIME
MASTER CAUT BLEED
L (R) VALVE OPEN
Valve not closed when wing anti-ice selected off
HI PR
High pressure detected when the wing anti-ice is selected ON.
NIL
NIL
LOCAL WARNING
FLT PHASE INHIB
NIL
3, 4, 5, 6, 7, 8
ANTI ICE WING FAULT lt
3, 4, 5, 7, 8
NIL
3, 4, 5, 7, 8
4, 5, 7, 8
MEMO DISPLAY The “WING A. ICE” message is displayed in green, if the WING ANTI ICE pb-sw is ON.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-30-20-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WING ANTI-ICE - WARNINGS AND CAUTIONS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-30-20-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
WING ANTI-ICE - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-30-20-40-00001176.0002001 / 16 FEB 11 Applicable to: ALL
NORM AC
WING ANTI ICE
L and R SHUT-OFF VALVES
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DC
AC ESS
EMER ELEC DC ESS
HOT
SHED
A
DSC-30-20-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
WING ANTI-ICE - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-30-20-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
ENGINE ANTI-ICE - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
DESCRIPTION Ident.: DSC-30-30-10-00001161.0002001 / 16 MAR 11 Applicable to: ALL
An independent air bleed from the high pressure compressor protects each engine nacelle from ice. Air is supplied through a two-position (open and closed) valve that the flight crew controls with two pushbuttons, one for each engine. The valve automatically closes, if air is unavailable (engine not running). When an engine anti-ice valve is open, the N1 limit is automatically reduced and, if necessary, the idle N1 is automatically increased for both engines in order to provide the required pressure. If electrical power fails, the valves open.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-30-30-10 P 1/2 03 APR 12
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
ENGINE ANTI-ICE - DESCRIPTION
←A
DSC-30-30-10 P 2/2 03 APR 12
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
ENGINE ANTI-ICE - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
OVERHEAD PANEL Ident.: DSC-30-30-20-00001162.0004001 / 16 MAR 11 Applicable to: ALL
(1)
ENG 1 (2) ANTI ICE pb-sw ON : Iight comes on blue. ECAM MEMO displays “ENG A. ICE”. Engine anti-icing valve opens if bleed air is available from the engine. Off : ON light goes out. Engine anti-ice valve closes. FAULT : Amber light comes on, and caution message appears on ECAM, if the position of the anti-ice valve disagrees with the ENG 1 (2) pushbutton selection. Note:
The amber FAULT light comes on briefly as valve transits.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-30-30-20 P 1/2 03 APR 12
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ENGINE ANTI-ICE - CONTROLS AND INDICATORS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-30-30-20 P 2/2 03 APR 12
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
ENGINE ANTI-ICE - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-30-30-30-00001163.0001001 / 16 MAR 11 Applicable to: ALL
E/WD : FAILURE TITLE conditions
ENG 1(2) VALVE OPEN
Valve disagree in the open position.
ENG 1(2) VALVE CLSD
AURAL WARNING
MASTER LIGHT
SD PAGE CALLED
SINGLE CHIME
MASTER CAUT
NIL
Valve disagree in the closed position.
LOCAL FLTPHASE WARNING INHIB ENG 1 (2) ANTI ICE FAULT lt
3, 4, 5, 7, 8
MEMO DISPLAY This display shows “ENG A. ICE” in green, if one or both ENG ANTI ICE pb-sw are ON.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-30-30-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ENGINE ANTI-ICE - WARNINGS AND CAUTIONS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-30-30-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
ENGINE ANTI-ICE - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-30-30-40-00001177.0001001 / 16 MAR 11 Applicable to: ALL
NORM AC
ENG ANTI ICE CLOSURE
VALVE
DC
1 2
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
AC ESS
EMER ELEC DC ESS
HOT
DC1 DC2
A
DSC-30-30-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
ENGINE ANTI-ICE - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-30-30-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
WINDOW HEAT - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
DESCRIPTION Ident.: DSC-30-40-10-00001164.0001001 / 22 MAY 12 Applicable to: ALL
The aircraft uses electrical heating for anti-icing each windshield and demisting the cockpit side windows. Two independent Window Heat Computers (WHCs), one on each side, automatically regulate the system, protect it against overheating, and indicate faults. Window heating comes on: ‐ automatically when at least one engine is running, or when the aircraft is in flight. ‐ manually, before engine start, when the flight crew switches ON the PROBE/WINDOW HEAT pushbutton switch. Windshield heating operates at low power on the ground and at normal power in flight. The changeover is automatic. Only one heating level exists for the windows.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-30-40-10 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
WINDOW HEAT - DESCRIPTION
←A
DSC-30-40-10 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
WINDOW HEAT - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
OVERHEAD PANEL Ident.: DSC-30-40-20-00001165.0001001 / 10 DEC 09 Applicable to: ALL
Refer to DSC-30-50-20 Overhead Panel
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-30-40-20 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WINDOW HEAT - CONTROLS AND INDICATORS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-30-40-20 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
WINDOW HEAT - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-30-40-30-00001166.0001001 / 10 DEC 09 Applicable to: ALL
E/WD : FAILURE TITLE conditions L(R) WINDSHIELD Failure of L or R windshield heating L+R WINDSHIELD Failure of both windshield heating L(R) WINDOW Failure of L or R window heating
AURAL WARNING
MASTER LIGHT
SINGLE CHIME
MASTER CAUT
NIL
NIL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
SD PAGE CALLED
LOCAL WARNINGS
FLT PHASE INHIB
NIL
NIL
3, 4, 5, 7, 8
DSC-30-40-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WINDOW HEAT - WARNINGS AND CAUTIONS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-30-40-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
WINDOW HEAT - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-30-40-40-00001178.0001001 / 16 MAR 11 Applicable to: ALL
NORM AC
WINDOW HEAT
WHC HEATING POWER
1 2 L R
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DC
AC ESS
EMER ELEC DC ESS
HOT
DC1 DC2 AC1 AC2
A
DSC-30-40-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
WINDOW HEAT - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-30-40-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
PROBES HEAT - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
DESCRIPTION Ident.: DSC-30-50-10-00001167.0001001 / 22 MAY 12 Applicable to: ALL
Electrical heating protects: ‐ Pitot heads ‐ Static ports ‐ Angle-Of-Attack probes (AOAs) ‐ Total Air Temperature (TAT) probes. Three independent Probe Heat Computers (PHCs) automatically control and monitor: ‐ Captain probes ‐ F/O probes ‐ STBY probes. They protect against overheating and indicate faults. The probes are heated: ‐ Automatically when at least one engine is running, or when the aircraft is in flight. ‐ Manually, when the flight crew switches ON the PROBE/WINDOW HEAT pb. On the ground, the TAT probes are not heated and pitot heating operates at a low level (the changeover to normal power in flight is automatic).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-30-50-10 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PROBES HEAT - DESCRIPTION
←A
DSC-30-50-10 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PROBES HEAT - CONTROLS AND INDICATORS
OVERHEAD PANEL Ident.: DSC-30-50-20-00001168.0001001 / 16 MAR 11 Applicable to: ALL
(1)
PROBE/WINDOW HEAT pb AUTO : Probes/Windows are heated automatically : ‐ In flight, or ‐ On the ground (except TAT probes) provided one engine is running. ON : Probes and windows are heated permanently. Blue light comes on.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-30-50-20 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PROBES HEAT - CONTROLS AND INDICATORS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-30-50-20 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
PROBES HEAT - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-30-50-30-00001169.0002001 / 15 NOV 10 Applicable to: ALL
E/WD : FAILURE TITLE conditions CAPT (F/O) PITOT CAPT (F/O) L(R) STAT CAPT (F/O) AOA CAPT (F/O) TAT Failure of corresponding probe heating STBY PITOT STBY L(R) STAT STBY AOA Failure of corresponding probe heating CAPT (F/O) (STBY) PROBES Failure of one probe heat channel/computer CAPT + F/O PITOT CAPT+ STBY PITOT F/O + STBY PITOT Failure of the corresponding probes heating ALL PITOT Failure of CAPT, F/O and STBY probes heating
AURAL WARNING
MASTER LIGHT
SD PAGE CALLED
LOCAL WARNING
FLT PHASE INHIB
3, 4, 5, 7, 8
SINGLE CHIME
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
MASTER CAUT
NIL
NIL
4, 5, 8
A
DSC-30-50-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PROBES HEAT - WARNINGS AND CAUTIONS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-30-50-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
PROBES HEAT - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-30-50-40-00001179.0001001 / 15 NOV 10 Applicable to: ALL
NORM AC
DC
AC ESS
EMER ELEC DC ESS X
HOT
CAPT F/O DC2 STBY DC1 CAPT and STBY DC1 STATICS F/O DC2 CAPT X (1) PROBE PITOT F/O AC2 HEAT STBY AC1 CAPT SHED F/O AC2 AOA STBY AC1 CAPT AC1 TAT F/O AC2 (1) When AC1 and AC2 are lost and AIR DATA is switched to “ CAPT 3”, the STBY pilot is switched to AC ESS bus and CAPT pitot heating is lost. PHC
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-30-50-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
PROBES HEAT - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-30-50-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
RAIN REMOVAL - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
WIPERS Ident.: DSC-30-60-10-00001170.0001001 / 10 DEC 09 Applicable to: ALL
Each front windshield has a dual-speed electric wiper, which are each controlled by a rotary selector. RAIN REPELLENT (IF INSTALLED) Ident.: DSC-30-60-10-00001171.0001001 / 10 DEC 09 Applicable to: ALL
In moderate to heavy rain, the flight crew can spray a rain repellent liquid on the windshield to improve visibility. After about 30 s, the windows are covered with spray. Separate pushbuttons control rain repellent application on each side of the windshield.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-30-60-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
RAIN REMOVAL - DESCRIPTION
←B
DSC-30-60-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
RAIN REMOVAL - CONTROLS AND INDICATORS
OVERHEAD PANEL Ident.: DSC-30-60-20-00001173.0001001 / 16 MAR 11 Applicable to: ALL
(1)
WIPER rotary selector Each rotary selector controls its wiper at low or high speed. When turned off, the wiper stops out of view.
(2)
RAIN RPLNT pushbuttons Each of these buttons controls the application of rain repellent fluid to the corresponding side of the front windshield. When the flight crew pushes the button, the timer applies a measured quantity of rain repellent to the windshield. To repeat the cycle, the flight crew must push the button again. This function is inhibited when the aircraft is on the ground and the engines are stopped.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-30-60-20 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
RAIN REMOVAL - CONTROLS AND INDICATORS
REAR COCKPIT Ident.: DSC-30-60-20-00001174.0001001 / 16 MAR 11 Applicable to: ALL
(1)
RAIN RPLNT pressure indicator This gauge shows the nitrogen pressure in the rain repellent bottle. When the needle is in the yellow sector the bottle should be replaced.
(2)
RAIN RPLNT quantity indicator When the REFILL float is in view the bottle should be replaced.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
DSC-30-60-20 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
RAIN REMOVAL - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-30-60-30-00001180.0001001 / 16 MAR 11 Applicable to: ALL
NORM AC
RAIN REMOVAL
WIPER RAIN REPELLENT
CAPT F/O CAPT F/O
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DC
AC ESS
EMER ELEC DC ESS
HOT
DC1 DC2 X DC2
A
DSC-30-60-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
RAIN REMOVAL - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-30-60-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
ICE DETECTION SYSTEM - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
VISUAL ICE INDICATOR Ident.: DSC-30-70-10-00001175.0002001 / 16 MAR 11 Applicable to: ALL
An external visual ice indicator is installed between the two windshields. The indicator has also a light.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-30-70-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
ICE DETECTION SYSTEM - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-30-70-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321
ICE DETECTION SYSTEM - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-30-70-30-00001181.0001001 / 16 MAR 11 Applicable to: ALL
NORM AC
ICE DETECT SYSTEM
DETECTOR 1 DETECTOR 2
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DC
AC ESS
EMER ELEC DC ESS
HOT
AC1 AC2
A
DSC-30-70-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS ICE AND RAIN PROTECTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ICE DETECTION SYSTEM - ELECTRICAL SUPPLY
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-30-70-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS
Intentionally left blank
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-31-PLP PRELIMINARY PAGES TABLE OF CONTENTS SUMMARY OF HIGHLIGHTS
DSC-31-05 EIS General DSC-31-05-10 Introduction INTRODUCTION......................................................................................................................................................A
DSC-31-05-20 Cockpit Arrangement COCKPIT ARRANGEMENT.................................................................................................................................... A
DSC-31-05-30 Architecture DISPLAY UNIT (DU)............................................................................................................................................... A Display Management Computer (DMC).................................................................................................................. B SYSTEM DATA ACQUISITION CONCENTRATOR (SDAC)..................................................................................C FLIGHT WARNING COMPUTER (FWC)................................................................................................................D ATTENTION - GETTERS........................................................................................................................................ E LOUDSPEAKER.......................................................................................................................................................F EIS Block Diagram.................................................................................................................................................. G
DSC-31-05-40 Controls and Switching ECAM CONTROL PANEL (ECP)............................................................................................................................A EIS DMC SWITCHING SELECTOR....................................................................................................................... B ECAM/ND SWITCHING...........................................................................................................................................C EFIS SWITCHING................................................................................................................................................... D
DSC-31-05-50 Reconfiguring the DMC RECONFIGURING THE DISPLAY MANAGEMENT COMPUTER (DMC)..............................................................A
DSC-31-05-60 Reconfiguring DUs FAILURE OF UPPER ECAM DU (OR CTL/BRIGHTNESS KNOB TURNED TO OFF)..........................................A FAILURE OF LOWER ECAM DU (OR CTL/BRIGHTNESS KNOB TURNED TO OFF)......................................... B FAILURE OF BOTH ECAM DUs............................................................................................................................ C PFDU/NDU RECONFIGURATION.......................................................................................................................... D DU RECONFIGURATION........................................................................................................................................E General.....................................................................................................................................................................F Failure of a DU........................................................................................................................................................G Feedback Messages................................................................................................................................................H Side1/Side2 Discrepancy Messages.........................................................................................................................I DU Reset.................................................................................................................................................................. J
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-PLP-TOC P 1/4 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-31-10 Ecam Description ECAM DU ARRANGEMENT................................................................................................................................... A COLOR CODE.........................................................................................................................................................B WARNING/CAUTION CLASSIFICATION................................................................................................................C PRIORITY RULES...................................................................................................................................................D TYPES OF FAILURES............................................................................................................................................ E Audio Indicators....................................................................................................................................................... F
DSC-31-15 Indications on E/WD General.....................................................................................................................................................................A Independent Failure................................................................................................................................................. B Primary and Secondary Failure...............................................................................................................................C FLIGHT PHASES.................................................................................................................................................... D Memos......................................................................................................................................................................E Configuration Warnings............................................................................................................................................F
DSC-31-20 Indications on SD GENERAL................................................................................................................................................................ A System Pages..........................................................................................................................................................B STATUS PAGE........................................................................................................................................................C Permanent Data.......................................................................................................................................................D Amber Crosses "XX" on the SD..............................................................................................................................E
DSC-31-25 ECAM Sequence DSC-31-25-10 General GENERAL................................................................................................................................................................ A
DSC-31-25-20 Example 1 - The ECAM Detects No Failure..........................................................................................................................A 2 - The ECAM Detects a Failure............................................................................................................................ B 3 - THE FLIGHT CREW FOLLOWS THE INSTRUCTION DISPLAYED ON THE E/WD....................................... C 4 - One of the Pilots Pushes the CLR Pushbutton on the ECP............................................................................. D 5 - One of the Pilots Pushes the CLR Pushbutton a Second Time........................................................................E 6 - One of the Pilots Pushes the CLR Pushbutton a Third Time............................................................................F
DSC-31-27 OEB Reminder GENERAL................................................................................................................................................................ A Description............................................................................................................................................................... B OEB DATABASE..................................................................................................................................................... C
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-PLP-TOC P 2/4 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-31-30 ECAM Controls ECAM Control Panel............................................................................................................................................... A Switching Panel....................................................................................................................................................... B Attention Getters......................................................................................................................................................C
DSC-31-40 Indications on PFD General.....................................................................................................................................................................A Specific Ground Indications.....................................................................................................................................B Attitude Data............................................................................................................................................................ C Airspeed................................................................................................................................................................... D Altitude..................................................................................................................................................................... E ALTITUDE (CONT'D)...............................................................................................................................................F Vertical Speed......................................................................................................................................................... G Heading....................................................................................................................................................................H FLIGHT PATH VECTOR...........................................................................................................................................I Guidance...................................................................................................................................................................J Trajectory Deviation................................................................................................................................................. K Flight Mode Annunciator.......................................................................................................................................... L Tailstrike Pitch Limit Indicator................................................................................................................................. M Altitude Alert............................................................................................................................................................ N Flags and Messages Displayed on PFD................................................................................................................ O Backup Speed/Altitude Scale.................................................................................................................................. P 1
DSC-31-45 Indications on ND GENERAL................................................................................................................................................................ A ROSE Modes........................................................................................................................................................... B ROSE LS Mode.......................................................................................................................................................C ROSE VOR Mode................................................................................................................................................... D ROSE NAV Mode/ARC Mode................................................................................................................................. E Plan Mode................................................................................................................................................................ F Weather Radar........................................................................................................................................................ G Predictive Windshear System................................................................................................................................. H EGPWS..................................................................................................................................................................... I Flags and Messages Displayed on ND................................................................................................................... J
DSC-31-50 EFIS Controls EFIS Control Panel..................................................................................................................................................A Other EFIS Controls................................................................................................................................................ B Chronometer............................................................................................................................................................ C
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-PLP-TOC P 3/4 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-31-55 CLOCK DSC-31-55-10 GENERAL GENERAL................................................................................................................................................................ A
DSC-31-55-20 CONTROLS AND INDICATORS General.....................................................................................................................................................................A INTERNAL TIME AND DATE INITIALIZATION...................................................................................................... B
DSC-31-60 FLT Recorders DSC-31-60-10 Flight Data Recording System Description............................................................................................................................................................... A
DSC-31-60-20 Controls and Indicators Overhead Panel....................................................................................................................................................... A Pedestal................................................................................................................................................................... B
DSC-31-60-30 Aircraft Integrated Data System DESCRIPTION.........................................................................................................................................................A Controls On Pedestal.............................................................................................................................................. B
DSC-31-70 Warnings and Cautions Warnings and Cautions........................................................................................................................................... A
DSC-31-75 Electrical Supply Bus Equipment List..................................................................................................................................................A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-PLP-TOC P 4/4 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title DSC-31-PLP-TOC Indications on ND DSC-31-40 Attitude Data DSC-31-40 Altitude DSC-31-45 ROSE Modes
Toc Index
ID
Reason
1 C
1
Documentation update: Deletion of the "00001250.0004001 ROSE Modes" documentary unit. Update of wording
E
2
Update of the description of the Barometric Reference.
B
1
Documentation update: Addition of "ROSE Modes" documentary unit
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-PLP-SOH P 1/2 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-PLP-SOH P 2/2 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EIS GENERAL - INTRODUCTION
FLIGHT CREW OPERATING MANUAL
INTRODUCTION Ident.: DSC-31-05-10-00001182.0001001 / 10 DEC 09 Applicable to: ALL
The Electronic Instrument System (EIS) presents data on six identical Display Units (DUs): ‐ The Electronic Flight Instrument System (EFIS) displays mostly flight parameters and navigation data on the Primary Flight Displays (PFDs) and Navigation Displays (NDs). ‐ The Electronic Centralized Aircraft Monitor (ECAM) presents data on the Engine/Warning Display (E/WD) and System Display (SD) : • Primary engine indications, fuel quantity, flap and slat position • Warning and caution alerts, or memos • Synoptic diagrams of aircraft systems, and status messages • Permanent flight data
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-31-05-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EIS GENERAL - INTRODUCTION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-05-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EIS GENERAL - COCKPIT ARRANGEMENT
FLIGHT CREW OPERATING MANUAL
COCKPIT ARRANGEMENT Ident.: DSC-31-05-20-00001183.0001001 / 10 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-31-05-20 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EIS GENERAL - COCKPIT ARRANGEMENT
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-05-20 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EIS GENERAL - ARCHITECTURE
FLIGHT CREW OPERATING MANUAL
DISPLAY UNIT (DU) Ident.: DSC-31-05-30-00001184.0002001 / 10 DEC 09 Applicable to: ALL
The instrument panels have six identical units. These DUs are full-color Liquid Crystal Displays (LCD). DISPLAY MANAGEMENT COMPUTER (DMC) Ident.: DSC-31-05-30-00001185.0002001 / 20 DEC 10 Applicable to: ALL
Three identical Display Management Computers (DMCs) obtain data from the different sensors and computers, and send it to the display units. The display units then generate and display the applicable images. Each DMC has a single DMC channel, and can simultaneously supply one PFD, one ND and both ECAM display units (E/WD and SD). SYSTEM DATA ACQUISITION CONCENTRATOR (SDAC) Ident.: DSC-31-05-30-00001186.0001001 / 10 DEC 09 Applicable to: ALL
The two identical SDACs acquire data, then generate signals. Some of these signals go to the three DMCs, which use them to generate displays of system pages and engines parameters. Others go to the flight warning computers, which use them to generate ECAM messages and aural alerts. FLIGHT WARNING COMPUTER (FWC) Ident.: DSC-31-05-30-00001187.0001001 / 10 DEC 09 Applicable to: ALL
The two identical FWCs generate alert messages, memos, aural alerts, and synthetic voice messages. For this purpose they acquire data : ‐ Directly from aircraft sensors, or systems, to generate red warnings. ‐ Through the SDACs to generate amber cautions. The ECAM display units display the alert messages generated by the FWCs. The FWCs also generate : ‐ Radio altitude callouts ‐ Decision height callouts ‐ Landing distance and landing speed increments.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to D
DSC-31-05-30 P 1/4 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EIS GENERAL - ARCHITECTURE
FLIGHT CREW OPERATING MANUAL
ATTENTION - GETTERS Ident.: DSC-31-05-30-00001188.0001001 / 10 DEC 09 Applicable to: ALL
The FWCs also drive the attention-getters. Each pilot has a set of these on the panel under the glareshield. They are : ‐ A master warning light, that flashes “MASTER WARN” in red, for red warnings. ‐ A master caution light, that illuminates “MASTER CAUT” in amber, for amber cautions. LOUDSPEAKER Ident.: DSC-31-05-30-00001189.0001001 / 10 DEC 09 Applicable to: ALL
The communications loudspeakers announce aural alerts and voice messages, and do so even when they are turned off.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E to F
DSC-31-05-30 P 2/4 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EIS GENERAL - ARCHITECTURE
FLIGHT CREW OPERATING MANUAL
EIS BLOCK DIAGRAM Ident.: DSC-31-05-30-00001190.0002001 / 16 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
G
DSC-31-05-30 P 3/4 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EIS GENERAL - ARCHITECTURE
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-05-30 P 4/4 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EIS GENERAL - CONTROLS AND SWITCHING
FLIGHT CREW OPERATING MANUAL
ECAM CONTROL PANEL (ECP) Ident.: DSC-31-05-40-00001191.0001001 / 10 DEC 09 Applicable to: ALL
The ECAM Control Panel, located on the pedestal, includes : ‐ Such E/WD controls, as CLR, STS, and the brightness control knob. ‐ Such SD controls, as ENG, BLEED, PRESS..., system page selector, and the brightness control knob. EIS DMC SWITCHING SELECTOR Ident.: DSC-31-05-40-00001192.0001001 / 10 DEC 09 Applicable to: ALL
A switch near the center of the SWITCHING panel which is located just above the ECAM control panel, enables the flight crew to replace the Captain or First Officer's Display Management Computer (DMC 1, or DMC 2) by DMC 3. ECAM/ND SWITCHING Ident.: DSC-31-05-40-00001193.0001001 / 10 DEC 09 Applicable to: ALL
A switch on the right-hand side of the SWITCHING panel enables the flight crew to transfer the ECAM System Display to either the Captain or First Officer's Navigation Display. EFIS SWITCHING Ident.: DSC-31-05-40-00001194.0001001 / 10 DEC 09 Applicable to: ALL
A PFD/ND XFR pushbutton on each side console enables the pilot to swap displays to the respective onside DUs.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to D
DSC-31-05-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EIS GENERAL - CONTROLS AND SWITCHING
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-05-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EIS GENERAL - RECONFIGURING THE DMC
RECONFIGURING THE DISPLAY MANAGEMENT COMPUTER (DMC) Ident.: DSC-31-05-50-00001195.0002001 / 20 DEC 10 Applicable to: ALL
In normal operation, each DMC drives the following Display Units : ‐ DMC 1 drives the CAPT PFD, CAPT ND the ECAM DUs. ‐ DMC 2 drives the F/O PFD and F/O ND. ‐ DMC 3 is on standby, ready to drive any DU. If DMC 1 or 2 fails (the “INVALID DATA” message is displayed on the DUs), the crew manually selects the DMC 3 source (“CAPT 3” or “F/O 3”). If DMC 1 fails (or DMC 3, if “CAPT 3” was selected), DMC 2 automatically drives the ECAM.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-31-05-50 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EIS GENERAL - RECONFIGURING THE DMC
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-05-50 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EIS GENERAL - RECONFIGURING DUS
FLIGHT CREW OPERATING MANUAL
FAILURE OF UPPER ECAM DU (OR CTL/BRIGHTNESS KNOB TURNED TO OFF) Ident.: DSC-31-05-60-00001196.0001001 / 10 DEC 09 Applicable to: ALL
If the upper ECAM display fails, or is switched off : ‐ The engine/warning page automatically replaces the system/status page on the lower ECAM DU. The flight crew can display the system/status page by : ‐ Using the “ECAM/ND XFR“ switch, on the SWITCHING panel, to move it to a Navigation Display Unit (NDU), or ‐ Pushing and holding (for a maximum of 3 min) the related system page pushbutton, on the ECAM control panel, to temporarily display it on the lower ECAM DU (instead of the engine/warning page). FAILURE OF LOWER ECAM DU (OR CTL/BRIGHTNESS KNOB TURNED TO OFF) Ident.: DSC-31-05-60-00001197.0001001 / 10 DEC 09 Applicable to: ALL
If the lower ECAM display fails, or is switched off, the flight crew can display the system/status page by : ‐ Using the "ECAM/ND XFR" switch, on the SWITCHING panel, to display it on the NDU, or ‐ Pushing and holding (for a maximum of 3 min) the related system page pushbutton, on the ECAM control panel, to temporarily display it on the upper ECAM DU (instead of the engine/warning page). FAILURE OF BOTH ECAM DUs Ident.: DSC-31-05-60-00001198.0001001 / 10 DEC 09 Applicable to: ALL
If both ECAM displays fail, the flight crew may : ‐ Use the "ECAM/ND XFR", on the SWITCHING panel, to display the engine/warning page on a navigation display and, if needed, ‐ Push and hold (for a maximum of 3 min) the related system page pushbutton, on the ECAM control panel, to temporarily display the system/status page on an ND. PFDU/NDU RECONFIGURATION Ident.: DSC-31-05-60-00001199.0001001 / 10 DEC 09 Applicable to: ALL
If a PFDU fails, the system automatically transfers the PFD image to the NDU.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to D →
DSC-31-05-60 P 1/6 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EIS GENERAL - RECONFIGURING DUS
The pilot can also make this transfer manually by : ‐ turning the PFD ON-OFF/brightness control OFF, or ‐ pressing the PFD/ND/XFR pushbutton, which cross-changes the images between the PFDU and the NDU. If an NDU fails, the pilot can use the PFD/ND/XFR pushbutton to transfer the ND image to the PFDU.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D
DSC-31-05-60 P 2/6 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EIS GENERAL - RECONFIGURING DUS
FLIGHT CREW OPERATING MANUAL
DU RECONFIGURATION Ident.: DSC-31-05-60-00001200.0001001 / 10 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E
DSC-31-05-60 P 3/6 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EIS GENERAL - RECONFIGURING DUS
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-31-05-60-00012844.0001001 / 20 DEC 10 Applicable to: ALL
These messages are displayed on either the EFIS or the ECAM Display Unit (DU) depending on the current EFIS or ECAM configuration. FAILURE OF A DU Ident.: DSC-31-05-60-00012846.0001001 / 20 DEC 10 Applicable to: ALL
If a DU fails, the flight crew may find one of the following displays: ‐ A blank screen with an “F” letter in amber, or ‐ A distorted display, or ‐ A blank screen with the “INVALID DISPLAY UNIT” message in amber. FEEDBACK MESSAGES Ident.: DSC-31-05-60-00012847.0001001 / 20 DEC 10 Applicable to: ALL
The DU displays the following messages in amber when the Display Management Computer (DMC) detects a discrepancy between the parameters obtained by the DMC and the operational parameters displayed on the DU: ‐ ”CHECK CAPT PFD” (“CHECK F/O PFD”) if the discrepancy concerns the PFD parameters ‐ ”CHECK CAPT ND” (“CHECK F/O ND”) if the discrepancy concerns the ND parameters ‐ ”CHECK EWD” if the discrepancy concerns the E/WD parameters ‐ ”CHECK SD” if the discrepancy concerns the SD parameters. In addition, if the aircraft is on ground, the “DU NOT MONITORED” message is displayed in amber when there is only one DMC, instead of two DMCs, that provides the affected DU with feedback information. This message means that there is either a DMC test in progress or that there is an EIS failure. In the case of an EIS failure, a maintenance action is necessary.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F to H
DSC-31-05-60 P 4/6 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EIS GENERAL - RECONFIGURING DUS
FLIGHT CREW OPERATING MANUAL
SIDE1/SIDE2 DISCREPANCY MESSAGES Ident.: DSC-31-05-60-00012848.0001001 / 20 DEC 10 Applicable to: ALL
The DU displays the following messages along with a caution on the ECAM E/WD when there is a discrepancy between the parameters displayed on the Captain’s EFIS and the First Officer’s EFIS: ‐ Both PFDs display the message “CHECK ATT” if there is a discrepancy of at least 5 ° between the attitude values, pitch and/or roll ‐ Both PFDs display the message “CHECK ALT” if there is a discrepancy between the altitude values greater than 250 ft when the flight crew selects a QNH different from STD, or 500 ft when the flight crew selects a QNH STD ‐ Both PFDs and NDs display the message “CHECK HDG” if there is a discrepancy of at least 5 ° between the heading values. Note:
The message “CHECK HDG” flashes for a few seconds on the NDs, and then it remains steady. If the flight crew selects the PLAN mode on the NDs the message “CHECK HDG” does not appear. DU RESET
Ident.: DSC-31-05-60-00012849.0001001 / 20 DEC 10 Applicable to: ALL
In the case of a DU reset, the message “SELF TEST IN PROGRESS” can be displayed in green and/or the message “WAITING FOR DATA” may be displayed in green during the EIS initialization.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
I to J
DSC-31-05-60 P 5/6 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EIS GENERAL - RECONFIGURING DUS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-05-60 P 6/6 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ECAM DESCRIPTION
FLIGHT CREW OPERATING MANUAL
ECAM DU ARRANGEMENT Ident.: DSC-31-10-00001201.0002001 / 10 DEC 09 Applicable to: ALL
The ECAM has two display units : ‐ one for the engine/warning display (E/WD). ‐ one for the system/status display (SD).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-31-10 P 1/6 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ECAM DESCRIPTION
FLIGHT CREW OPERATING MANUAL
COLOR CODE Ident.: DSC-31-10-00001202.0001001 / 10 DEC 09 Applicable to: ALL
The ECAM display uses a color code that indicates the importance of the failure or the indication. RED : The configuration or failure requires immediate action. AMBER : The flight crew should be aware of the configuration or failure, but need not take immediate action. GREEN : The item is operating normally. WHITE : These titles and remarks guide the flight crew, as they execute various procedures. BLUE : These are actions to be carried out, or limitations. MAGENTA : These are particular messages that apply to particular pieces of equipment or situations (inhibition messages, for example).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
DSC-31-10 P 2/6 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ECAM DESCRIPTION
FLIGHT CREW OPERATING MANUAL
WARNING/CAUTION CLASSIFICATION Ident.: DSC-31-10-00001203.0001001 / 17 FEB 11 Applicable to: ALL
FAILURE MODE
LEVEL Level 3
SIGNIFICATION
AURAL VISUAL Continuous Red warning : The configuration, or ‐ MASTER WARN Repetitive failure requires immediate action : light red flashing or Chime (CRC) or ‐ Aircraft in dangerous configuration, specific red light specific sound or or limit flight conditions (eg: stall, ‐ Warning message synthetic voice o/speed) (red) on E/WD ‐ System failure altering flight safety ‐ Automatic call of (eg : Eng fire, excess cab alt) the relevant system page on the S/D (1).
Level 2
Amber caution : The flight crew should be aware of the configuration or failure, but does not need to take any immediate action. However, time and situation permitting, these cautions should be considered without delay to prevent any further degradation of the affected system : ‐ System failure without any direct consequence on the flight safety (eg: HYD G SYS LO PR)
Level 1
INFORMATION
ADVISORY
MEMO
(1)
Amber caution : Requires crew monitoring : ‐ Failures leading to a loss of redundancy or system degradation (eg : FCDC fault) System parameters monitoring
Single Chime (SC)
NONE
NONE
Information : Recalls normal or NONE automatic selection of functions which are temporarily used
‐ MASTER CAUT light amber steady ‐ Caution message (amber) on E/WD ‐ Automatic call of the relevant system page on the S/D (1).
‐ Caution message (amber) on E/WD generally without procedure. ‐ Automatic call of the relevant system page on the S/D. The affected parameter pulses green. ‐ Green, Amber, or Magenta message on E/WD
except in some cases
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-31-10 P 3/6 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ECAM DESCRIPTION
FLIGHT CREW OPERATING MANUAL
PRIORITY RULES Ident.: DSC-31-10-00001204.0001001 / 17 FEB 11 Applicable to: ALL
There are three priority levels for warnings and cautions : - A level 3 warning has priority over a level 2 caution which has priority over a level 1 caution. The FWC observes these priorities. TYPES OF FAILURES Ident.: DSC-31-10-00001205.0001001 / 10 DEC 09 Applicable to: ALL
Independent : Primary
:
Secondary
:
a failure that affects an isolated system or item of equipment without degrading the performance of others in the aircraft. a failure of a system or an item of equipment that costs the aircraft the use of other systems or items of equipment. the loss of a system or an item of equipment resulting from a primary failure. AUDIO INDICATORS
Ident.: DSC-31-10-00001206.0347001 / 22 MAY 12 Applicable to: ALL
AUDIO INDICATOR CONTINUOUS REPETITIVE CHIME SINGLE CHIME CAVALRY CHARGE (3)
MEANING
DURATION
RED WARNINGS
PERMANENT
AMBER CAUTION A/P DISCONNECTION BY TAKE OVER pb
0.5 s 1.5 s
A/P DISCONNECTION DUE TO FAILURE
PERMANENT
TRIPLE CLICK
Landing capability downgrade or "GPS PRIMARY LOST" in approach, or mode reversion
0.5 s. (3 pulses)
CRICKET + “STALL” message (synthetic voice)
STALL
PERMANENT
AUDIO INDICATOR CANCELLATION (1) Press (1) MASTER WARN lt Second push on TAKE OVER pb Press MASTER WARN lt or TAKE OVER pb
NIL Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D to F →
DSC-31-10 P 4/6 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ECAM DESCRIPTION
FLIGHT CREW OPERATING MANUAL
Continued from the previous page AUDIO INDICATOR CANCELLATION (1) NIL
AUDIO INDICATOR
MEANING
DURATION
CABIN CALL BUZZER
EMER CABIN CALL MECH CALL (2)
3s 3 s REPEATED 3 TIMES As long as outside pb pressed
SELCAL CALL
PERMANENT
WINDSHEAR
REPEATED 3 TIMES
NIL
Windshear ahead detected during the landing phase
PERMANENT
NIL
Windshear ahead detected during the takeoff phase
PERMANENT
NIL
Windshear ahead detected caution message
PERMANENT
NIL
1.5 s or PERMANENT
new ALTITUDE selection or press MASTER WARN pb
PERMANENT
NIL
(Refer to DSC-34-70-10 Description)
PERMANENT
NIL
A/P TAKE OVER pb
1s
NIL
“RETARD" (synthetic voice)
Thrust levers not in IDLE position for landing
ONE TIME at20 ft (10 ft in autoland with A/THR ON), then PERMANENT until thrust levers are set to IDLE
NIL
TCAS (synthetic voice)
(Refer to DSC-34-80-20 Aural Messages) Current thrust is not sufficient to recover a positive flight through pitch control
PERMANENT
NIL
Every 5 s until thrust is increased
THRUST LEVER(s)
CONTINUOUS BUZZER (2) “WINDSHEAR” (synthetic voice) "GO AROUND WIND SHEAR AHEAD" (synthetic voice) "WINDSHEAR AHEAD" (twice) (synthetic voice) "MONITOR RADAR DISPLAY" (synthetic voice) C CHORD AUTO CALL OUT (synthetic voice) GROUND PROXIMITY WARNING (synthetic voice) “PRIORITY LEFT” ”PRIORITY RIGHT“ (synthetic voice)
″SPEED, SPEED, SPEED″ (Synthetic voice)
ALTITUDE ALERT (Refer to DSC-31-40 Altitude Alert) HEIGHT ANNOUNCEMENT BELOW 2 500 ft (Refer to DSC-34-40-10-A Automatic Call Out - General)
NIL NIL Press RESET key on ACP
Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←F→
DSC-31-10 P 5/6 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ECAM DESCRIPTION
FLIGHT CREW OPERATING MANUAL
AUDIO INDICATOR
MEANING
″DUAL INPUT″ (synthetic voice)
Both sidesticks are moved simultaneously The aircraft pitch attitude is becoming excessive during flare and landing.
“PITCH, PITCH” (Synthetic voice) (1)
(2) (3)
DURATION
Continued from the previous page AUDIO INDICATOR CANCELLATION (1)
Every 5 s
One sidestick deactivated
one time
NIL
The pilot can cancel any audio indicator, by pressing the: ‐ The EMER CANC pb on the ECAM control panel, or ‐ The MASTER WARN pushbutton, except for OVERSPEED or L/G NOT DOWN warnings. The pilot can cancel the continuous buzzer, by pressing the MASTER CAUT pushbutton. When the flight crew presses the MASTER WARN pushbutton (following a warning that leads to an AP disconnection), the Cavalry Charge sound is only inhibited when it has been emitted in order to avoid an unintended cancellation.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←F
DSC-31-10 P 6/6 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON E/WD
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-31-15-00001207.0003001 / 03 FEB 11 Applicable to: ALL
The Engine Warning Display (E/WD) appears on the ECAM's upper Display Unit (DU). ‐ The upper part of this DU displays: • Engine parameters (Refer to DSC-70-90-A ECAM - Primary Parameter) • Feedback messages (Refer to DSC-31-05-60 Feedback Messages) • Fuel On Board (FOB) (Refer to DSC-28-20 ECAM Upper Display) • Slats/Flaps' position (Refer to DSC-27-20-30 ECAM F/CTL Page) ‐ The lower part of this DU displays messages generated by the FWC: • Warning and caution messages, when a failure occurs • Memos when there is no failure.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-31-15 P 1/6 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON E/WD
FLIGHT CREW OPERATING MANUAL
The lower part of the DU, dedicated to ECAM messages, is divided into two sections that have several lines each. Bottom left : ‐ Primary or independent warnings and cautions, or ‐ Memo information. Bottom right : ‐ Title of the system affected by a primary or independent warning or caution, in the case of overflow on the bottom left part, or ‐ Secondary failure, or ‐ Memo, or ‐ Special lines (such as “AP OFF”, “LAND ASAP”). As soon as the FWC detects a failure, and if there is no flight phase inhibition active, the E/WD displays the title of the failure and actions that the flight crew must perform. The action line automatically clears, when the flight crew has performed the necessary action. Note:
Some action lines do not disappear from the E/WD even after the flight crew performs the necessary action. INDEPENDENT FAILURE
Ident.: DSC-31-15-00001208.0001001 / 03 FEB 11 Applicable to: ALL
If there are too many ECAM messages for the amount of space available in the lower part of the E/WD, a green arrow appears at the bottom of the display, pointing down to show that the information has overflowed off the screen. The pilot can scroll down to view additional messages by pushing the CLR pushbutton on the ECAM control panel (on the pedestal, just below the lower ECAM DU).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← A to B
DSC-31-15 P 2/6 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON E/WD
FLIGHT CREW OPERATING MANUAL
PRIMARY AND SECONDARY FAILURE Ident.: DSC-31-15-00001209.0001001 / 03 FEB 11 Applicable to: ALL
The ECAM DU displays a primary failure as a boxed title. It identifies a secondary failure by putting a star in front of the title of the affected system. Note:
The DU displays the overflow symbol, if primary or secondary failures overflow. In case of ELEC EMER CONFIG, the secondary failures are inhibited. FLIGHT PHASES
Ident.: DSC-31-15-00001210.0001001 / 03 FEB 11 Applicable to: ALL
GENERAL The FWC divides its functions according to these ten flight phases :
To improve its operational efficacy, the computer inhibits some warnings and cautions for certain flight phases. It does so to avoid alerting the pilots unnecessarily at times when they have high
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C to D →
DSC-31-15 P 3/6 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
INDICATIONS ON E/WD
workloads, such as during takeoff or landing. In these two phases, the DU displays magenta memos : “T.O. INHIBIT” (flight phases 3, 4, and 5), and “LDG INHIBIT” (flight phases 7 and 8). Note:
These flight phases are different from and independent of the ones that the FMGC uses.
FLIGHT PHASE INHIBITION Two cases are possible (for instance) :
Effect on E/WD : (a)
The failure occurs during phase 1. The E/WD displays the warning immediately and continues to display it as long as the failure is present, even in phase 2.
(b)
The failure occurs during phase 2. The E/WD displays the warning only when the aircraft has entered phase 3, where it is not inhibited. Then the warning remains displayed as long as the failure is present.
MEMOS Ident.: DSC-31-15-A-NG00087 Applicable to: ALL Ident.: DSC-31-15-A-00001211.0001001 / 10 DEC 09
DISPLAY Memos appear in the lower part of the E/WD. They are normally in green, but may be amber in abnormal situations. Memos list functions or systems that are temporarily used in normal operations. Each chapter of the “Warning and Cautions” section of this manual lists memo messages. Ident.: DSC-31-15-A-00001212.0002001 / 03 FEB 11
TO AND LDG MEMOS During the takeoff and landing phases, the right side of the memo area displays specific TO INHIBIT or LDG INHIBIT (magenta) memos. Takeoff and landing memos are displayed, as follows, during the related flight phases: 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← D to E →
DSC-31-15 P 4/6 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON E/WD
FLIGHT CREW OPERATING MANUAL
(*)
This line disappears when the test is completed. It is replaced by “TO CONFIG NORMAL”, if aircraft configuration is correct. The test is requested again, if the configuration becomes abnormal.
(*)
“CONF 3” is displayed in alternate or direct law, or if the GPWS LDG FLAP 3 pushbutton is ON. CONFIGURATION WARNINGS
Ident.: DSC-31-15-00001214.0015001 / 16 MAR 11 Applicable to: ALL
The following warnings and cautions appear in the lower part of the E/WD if the aircraft is not in takeoff configuration when the flight crew presses the TO CONFIG pushbutton on the ECAM control panel or applies takeoff power.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← E to F →
DSC-31-15 P 5/6 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON E/WD
FLIGHT CREW OPERATING MANUAL
WARNINGS/CAUTIONS
TO CONFIG TEST
CONFIG RUD TRIM NOT IN TO RANGE (R) CONFIG PITCH TRIM NOT IN TO RANGE (R) CONFIG FLAPS NOT IN TO CONFIG (R) CONFIG SPD BRK NOT RETRACTED (R) CONFIG SLATS NOT IN TO CONFIG (R) CONFIG L SIDESTICK FAULT (R) CONFIG R SIDESTICK FAULT (R) DOOR (A) FWS OEB/FWC DISCREPANCY (A) BRAKES HOT (A) FUEL R(L) TK PUMP 1+2 LO PR (A) HYD G(Y) ENG 1(2) PUMP LO PR (A) HYD G(Y)(B) SYS LO PR (A) ELEC IDG 1(2) DISCONNECTED (A) ELEC GEN 1(2) FAULT (A) ELEC GEN 1(2) OFF (A) CONFIG PARK BRK ON (R) ENG THR LEVERS NOT SET (A) (R) (A)
TO POWER
TRIGGERED TRIGGERED
NOT TRIGGERED TRIGGERED if the two GENs are inop. NOT TRIGGERED
TRIGGERED
Red warning Amber caution
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←F
DSC-31-15 P 6/6 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON SD
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-31-20-00001215.0001001 / 10 DEC 09 Applicable to: ALL
The system/status display (SD) uses the lower ECAM DU to display : ‐ pages showing synoptic diagrams of the aircraft systems, or ‐ the status page. SYSTEM PAGES Ident.: DSC-31-20-00001216.0002001 / 22 MAY 12 Applicable to: ALL
The lower ECAM DU can display 12 system pages (For description see relevant FCOM chapter): ‐ ENGINE (secondary engine parameters) ‐ BLEED (air bleed) ‐ CAB PRESS (cabin pressurization) ‐ ELEC (electric power) ‐ HYD (hydraulic) ‐ FUEL (fuel) ‐ APU (auxiliary power unit) ‐ COND (air conditioning) ‐ DOOR/OXY (doors/oxygen) ‐ WHEEL (landing gear, braking, ground spoilers, etc.) ‐ F/CTL (flight controls) ‐ CRUISE (cruise) The pilot may manually call up a system page for display on the lower ECAM DU, or the system may automatically display a page. ‐ Manual: • The pilot can, at any time, use the pushbutton on the ECAM's control panel to call up and display any system page, except the CRUISE page. • The corresponding pushbutton on the ECAM control panel lights up. • A failure-related or advisory display automatically replaces a page the pilot has manually called up. ‐ Automatic, related to a failure: • The relevant system page automatically appears, as soon as any fault or malfunction triggers a caution or warning message.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-31-20 P 1/8 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON SD
FLIGHT CREW OPERATING MANUAL
‐ Automatic, advisory: • The relevant system page automatically appears, when a parameter drifts out of its normal range. • The value (shown in green) pulses, as long as it is outside its limits. • The advisory mode is inhibited in some flight phases.
Note:
If an advisory is triggered, when the ECAM is in the single-display configuration, an advisory message appears on the upper part of the E/WD, and the associated key on the ECAM control panel flashes to identify the appropriate system page.
‐ Automatic, flight phase mode • If no other mode is engaged, the SD displays the system page related to the present flight phase, as shown in the following diagram.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
DSC-31-20 P 2/8 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON SD
FLIGHT CREW OPERATING MANUAL
• Phase 2 : The F/CTL page replaces the WHEEL page for 20 s when either pilot moves his sidestick (more than 3 ° in pitch or roll) or when the rudder pedal deflection is more than 22 °. • The APU page appears when the APU MASTER switch is ON. It disappears when APU RPM has been above 95 % for 10 s, or when the APU MASTER switch is switched OFF. • The ENGINE page appears at the beginning of start sequence or when a pilot selects “CRANK”. It disappears 10 s after the end of the start sequence, when the ENG MODE sel is set to NORM. For a description of the ENGINE and AIR indications that appear when the SD is displaying the CRUISE page, see the relevant FCOM chapter.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
DSC-31-20 P 3/8 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
INDICATIONS ON SD
STATUS PAGE Ident.: DSC-31-20-00001217.0001001 / 17 MAR 11 Applicable to: ALL
The status page displays an operational summary of the aircraft status after the SD has displayed a failure. As shown in the illustration above, the summary includes :
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
DSC-31-20 P 4/8 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON SD
FLIGHT CREW OPERATING MANUAL
(1)
Limitations (speed, flight level) : Blue
(2)
Approach procedures : White/Red or Amber
(3)
Procedures (corrections to apply for landing) : Blue
(4)
Information : Green
(5)
Cancelled caution : White
(6)
Inoperative system : Amber
(7)
Maintenance status : White
(8)
Symbol displayed if data overflows the left or right area.
The pilot scrolls the display to view overflow by pressing the CLR pushbutton. Note:
The titles of the different parts of the display are white and underlined.
The STATUS page automatically appears, once the crew has cleared all the pages corresponding to the current failure. The STATUS page also appears automatically during descent, when the slats are extended, unless the page is empty. The pilot may manually call up the status page by pressing the STS key on the ECAM control panel. If the STATUS page holds messages other than “CANCELLED CAUTION”, or the MAINTENANCE part, the E/WD screen shows “STS” (status reminder). 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C→
DSC-31-20 P 5/8 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON SD
FLIGHT CREW OPERATING MANUAL
If the STATUS page holds messages in the MAINTENANCE, part on engine shutdown, the “STS” (status reminder) flashes on the E/WD screen. The screen displays the MAINTENANCE, only when the aircraft is on ground, before engine start-up or after engine shutdown (Phases 1 and 10). PERMANENT DATA Ident.: DSC-31-20-00001218.0028001 / 17 MAR 11 Applicable to: ALL
(1)
Temperature The screen displays the Total Air Temperature (TAT) and Static Air Temperature (SAT) in green. International Standard Atmosphere temperature (ISA) is displayed in GREEN, in standard altitude mode and when the SAT is valid.
(2)
G LOAD The screen displays the load factor (G LOAD) in amber, when the value is above 1.4 g or below 0.7 g. The display of the load factor is inhibited during flight phases 1, 2 and 3.
(3)
UTC The screen displays the Universal Time Coordinated (UTC), synchronized with the cockpit clock, in green.
(4)
GW The screen displays the Gross Weight (GW) in green, as soon as the flight crew starts the first engine. The last two digits are dashed, if accuracy is degraded. On ground, blue dashes are displayed instead of the indication, if no computed data is available. Note:
When the Fuel On Board (FOB) indicated on the ECAM exceeds 23 200 kg (51 147 lb), the GW indication is inaccurate. When the FOB on the ECAM goes below 23 200 kg (51 147 lb) GW accuracy is recovered.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← C to D
DSC-31-20 P 6/8 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON SD
FLIGHT CREW OPERATING MANUAL
AMBER CROSSES "XX" ON THE SD Ident.: DSC-31-20-00013602.0001001 / 18 MAR 11 Applicable to: ALL
If a parameter value on any SD page is not available for display, amber crosses "XX" appear instead of the value.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E
DSC-31-20 P 7/8 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON SD
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-20 P 8/8 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ECAM SEQUENCE - GENERAL
GENERAL Ident.: DSC-31-25-10-00001219.0001001 / 10 DEC 09 Applicable to: ALL
If ECAM detects a failure : ‐ The E/WD displays warning or caution messages. ‐ The master warning or master caution lights light up (except in the case of a level 1 caution). ‐ The system sounds an aural signal (except in the case of a level 1 caution). ‐ The system display (SD) shows the system page for the affected system. ‐ The CLR pushbutton on the ECAM control panel lights up. In addition, a local warning light controlled directly by the affected system can light up. After completing remedial procedures, the flight crew must push the CLR pushbutton repeatedly until the displays return to their normal configurations : ‐ MEMO messages on the E/WD ‐ The system page related to the present flight phase on the SD. ‐ The CLR light on the ECAM control panel turned off.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-31-25-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ECAM SEQUENCE - GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-25-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ECAM SEQUENCE - EXAMPLE
FLIGHT CREW OPERATING MANUAL
1 - THE ECAM DETECTS NO FAILURE Ident.: DSC-31-25-20-00001220.0004001 / 10 JAN 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-31-25-20 P 1/10 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ECAM SEQUENCE - EXAMPLE
FLIGHT CREW OPERATING MANUAL
2 - THE ECAM DETECTS A FAILURE Ident.: DSC-31-25-20-00001221.0004001 / 10 JAN 11 Applicable to: ALL
For example, a hydraulic reservoir is overheat. COCKPIT INDICATIONS ‐ ‐ ‐ ‐
A single chime sounds. Both MASTER CAUTION lights come on, and stay on. A FAULT light, on the overhead HYD panel, comes on. The memo space on the E/WD displays the “HYD B RSVR OVHT” message, and the “BLUE ELEC PUMP . . . . . OFF” instruction. ‐ The lower ECAM display (SD) automatically calls up the hydraulic system's diagram, and displays “OVHT” in amber next to the blue system. ‐ The ECAM's CLR pushbutton lights up.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
DSC-31-25-20 P 2/10 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ECAM SEQUENCE - EXAMPLE
3 - THE FLIGHT CREW FOLLOWS THE INSTRUCTION DISPLAYED ON THE E/WD Ident.: DSC-31-25-20-00001222.0002001 / 10 JAN 11 Applicable to: ALL
The flight crew switches off the BLUE ELEC PUMP pushbutton, depressurizing the blue hydraulic circuit.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
DSC-31-25-20 P 3/10 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ECAM SEQUENCE - EXAMPLE
COCKPIT INDICATIONS ‐ ‐ ‐ ‐ ‐
A single chime sounds. Both MASTER CAUTION lights stay on. A FAULT/OFF light, on the overhead panel, comes on. The second part of the message on the E/WD changes to “B SYS LO PR”. The SD's system diagram shows an amber zero for the pressure in the blue system, along with the amber “OVHT”. ‐ The right side of the memo area indicates a secondary failure in the flight control system. ‐ The ECAM control panel's CLR pushbutton remains on.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C→
DSC-31-25-20 P 4/10 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ECAM SEQUENCE - EXAMPLE
4 - ONE OF THE PILOTS PUSHES THE CLR PUSHBUTTON ON THE ECP Ident.: DSC-31-25-20-00001223.0003001 / 10 JAN 11 Applicable to: ALL
COCKPIT INDICATIONS ‐ The CLR pushbutton stays on. ‐ The FAULT/OFF light stays on. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← C to D →
DSC-31-25-20 P 5/10 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ECAM SEQUENCE - EXAMPLE
‐ Hydraulic system messages disappear from the E/WD, and the right side of the memo area indicates a secondary failure in the flight control system. ‐ The SD automatically calls up the flight control system page, with surface actuator indications (associated with the blue hydraulic system) shown in amber.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D
DSC-31-25-20 P 6/10 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ECAM SEQUENCE - EXAMPLE
5 - ONE OF THE PILOTS PUSHES THE CLR PUSHBUTTON A SECOND TIME Ident.: DSC-31-25-20-00001224.0003001 / 10 JAN 11 Applicable to: ALL
COCKPIT INDICATIONS ‐ ‐ ‐ ‐
The ECP's CLR and STS pushbuttons light up. The FAULT/OFF lights stay on. The E/WD's memo area returns to normal. The STATUS page automatically appears on the SD, displaying the procedures for completing the flight with a faulty blue system.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E→
DSC-31-25-20 P 7/10 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ECAM SEQUENCE - EXAMPLE
6 - ONE OF THE PILOTS PUSHES THE CLR PUSHBUTTON A THIRD TIME Ident.: DSC-31-25-20-00001225.0003001 / 10 JAN 11 Applicable to: ALL
COCKPIT INDICATIONS ‐ The CLR pushbutton light goes off. ‐ The FAULT/OFF lights stay on. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← E to F →
DSC-31-25-20 P 8/10 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ECAM SEQUENCE - EXAMPLE
‐ A status reminder appears at the bottom of the E/WD. ‐ The SD automatically displays the system page corresponding to the flight phase.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←F
DSC-31-25-20 P 9/10 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ECAM SEQUENCE - EXAMPLE
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-25-20 P 10/10 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
OEB REMINDER
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-31-27-00001226.0001001 / 20 DEC 10 Applicable to: ALL
The OEB reminder function provides operational help to the crew by enabling them to clearly identify (on the ECAM) all procedures and status messages affected by an OEB. When a situation leading to a warning/caution occurs, a message informs the crew in real time that an OEB exists for the displayed warning and/or status and, consequently, that the procedure and/or status presented on the ECAM is not applicable. Then the crew must refer to the QRH where the correct information is provided. DESCRIPTION Ident.: DSC-31-27-00001227.0003001 / 22 MAY 12 Applicable to: ALL
The OEB reminder flag may apply to the: ‐ ECAM procedure only, ‐ ECAM procedure and corresponding status messages, ‐ Status message only. PROCEDURE ONLY AFFECTED ‐ The ECAM warning title remains unaltered, ‐ All corresponding actions are suppressed and replaced by the “REFER TO QRH/OEB PROC” message, ‐ The related status messages on the ECAM system display remains unaltered.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-31-27 P 1/4 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
OEB REMINDER
FLIGHT CREW OPERATING MANUAL
COCKPIT INDICATION
PROCEDURE AND STATUS AFFECTED ‐ The ECAM warning title remains unaltered, ‐ All corresponding actions are suppressed and replaced by the “REFER TO QRH/OEB PROC” message, ‐ The related status messages on the ECAM system display remains unchanged, except for the additional “REFER TO QRH/OEB PROC” title.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
DSC-31-27 P 2/4 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
OEB REMINDER
FLIGHT CREW OPERATING MANUAL
COCKPIT INDICATION
STATUS MESSAGE ONLY AFFECTED ‐ The ECAM warning title remains unaltered, ‐ The corresponding procedure remains unchanged, except for the additional “FOR STS REFER TO OEB" line. ‐ The related status messages on the ECAM system display remains unchanged, except for the additional " REFER TO QRH/OEB PROC" title.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
DSC-31-27 P 3/4 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
OEB REMINDER
FLIGHT CREW OPERATING MANUAL
COCKPIT INDICATION
OEB DATABASE Ident.: DSC-31-27-00001228.0001001 / 10 DEC 09 Applicable to: ALL
The OEB database lists the warnings and cautions affected by an OEB. The OEB database can be : • Loaded manually on the aircraft via the MCDU, and stored in both FWCs. • Crossloaded from one FWC to the other FWC. • Updated by entering a code via the MCDU. • Checked via the MCDU. Note:
The code provided on the OEB is designed to ensure that the OEB database is not updated before the OEB is available.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← B to C
DSC-31-27 P 4/4 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ECAM CONTROLS
FLIGHT CREW OPERATING MANUAL
ECAM CONTROL PANEL Ident.: DSC-31-30-00001229.0001001 / 16 MAR 11 Applicable to: ALL
(1)
OFF / BRT knobs Used to turn the ECAM DUs on and off, and to control their brightness (automatic adjustment of brightness for ambient light conditions is superimposed on this manual control). Note:
(2)
When the pilot turns the UPPER DISPLAY knob to OFF, the engine/warning (E/W) display appears on the lower display unit (automatic transfer).
System page pushbuttons ‐ Call up the corresponding system pages on the SD ‐ Light up, when pushed for manual selection, or when an advisory is detected ‐ Call up the aircraft system page corresponding to the present flight phase or the current warning when pushed a second time. When only one ECAM display is on, the pilot can display a system page for up to 3 min by pushing and holding the system page pushbutton. • If an advisory condition arises, the relevant system page is not automatically displayed, but the pushbutton light pulses • If an ECAM warning is triggered, the relevant system page is not automatically displayed, and the system page pushbutton does not light up.
(3)
RCL pb If the flight crew pushes the RCL pb , the E/WD displays:
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-31-30 P 1/6 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ECAM CONTROLS
FLIGHT CREW OPERATING MANUAL
‐ All warning, caution messages, and status pages that have been suppressed by the activation of the CLR pb, and ‐ All the alerts that are still active but inhibited in the whole active flight phase. If there are no suppressed warnings or cautions, the E/WD shows “NORMAL” for 5 s. If the flight crew holds this pushbutton down for more than 3 s, the E/WD displays any caution messages that were suppressed by the EMER CANC pb. (4)
STS pb The pilot pushes this pushbutton to display the STATUS page on the lower SD. The pushbutton remains lit, as long as the SD displays the STS page. If the system has no status messages, the status page displays “NORMAL” for 5 s. The pilot can clear the STATUS page by pushing the CLR pb, or by pushing the STS pb a second time. When only one ECAM display is on : ‐ It displays the STATUS page only when the pilot pushes the STATUS pushbutton and holds it. He can display the next STATUS page, if any, by releasing the pushbutton and pushing it again (before 2 s have elapsed). The new page then appears after a short delay. ‐ The pilot can keep the STS pb pressed to display the STATUS page for a maximum of 3 min, after which the ECAM automatically displays the engine/warning page.
(5)
CLR pb This pushbutton remains lit as long as the E/WD is displaying a warning or caution message, or a status message on the SD. If it is lit, pressing it changes the ECAM display.
(6)
ALL pb When this pushbutton is pressed and held down, the SD successively displays all the system pages at one-second intervals. If the ECAM control panel fails, the pilot can use this pushbutton to page through the system pages until he comes to the one he wants to look at. He then releases the pushbutton to select that page.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
DSC-31-30 P 2/6 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ECAM CONTROLS
FLIGHT CREW OPERATING MANUAL
(7)
EMER CANC pb This pushbutton affects the following : ‐ Warnings : • Cancel (stop) an aural warning for as long as the failure condition continues • Extinguishes the MASTER WARNINGS lights • Does not affect the ECAM message display. ‐ Cautions : • Cancel any present caution (single chime, MASTER CAUTION lights, ECAM message) for the rest of the flight • Automatically calls up the STATUS page, which displays “CANCELLED CAUTION” and the title of the failure that is inhibited. The inhibition is automatically suppressed when Flight Phase 1 is initiated. The pilot may restore it manually by pressing the RCL pb for more than 3 s. Note:
(8)
This pushbutton should only be used to suppress spurious MASTER CAUTIONS.
T.O CONFIG pb This pushbutton simulates the application of takeoff power. This is a test that triggers a warning, if the aircraft is not in takeoff configuration. (Refer to DSC-31-15 Configuration Warnings). If the configuration is correct, the E/WD displays the “TO CONFIG NORMAL” message in the TO MEMO section. Note:
If the ECAM control panel fails, the CLR, RCL, STS, EMER CANC, and ALL pushbuttons remain operative, because their contacts are directly wired to the flight warning and display management computers.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-31-30 P 3/6 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ECAM CONTROLS
FLIGHT CREW OPERATING MANUAL
SWITCHING PANEL Ident.: DSC-31-30-00001230.0002001 / 17 MAR 11 Applicable to: ALL
ON PEDESTAL
(1)
EIS DMC rotary selector NORM : DMC 1 supplies the CAPT's PFD, the CAPT's ND, and the ECAM's DUs. DMC 2 supplies the F/O's PFD and the F/O's ND. CAPT 3 : DMC 3 replaces DMC 1. F/O 3 : DMC 3 replaces DMC 2. Note:
(2)
If a DMC fails, each of its associated DUs displays an “INVALID DATA” message.
ECAM/ND XFR rotary selector Transfers the system/status display to either the Captain's or the First Officer's ND. The “ECAM ON ND” message is displayed on the lower ECAM display. Note:
If both ECAM DUs (E/WD and SD) fail, the flight crew may use this switch to transfer the E/WD display to either navigation display. In this case, the “ECAM ON ND” message is not displayed.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
DSC-31-30 P 4/6 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ECAM CONTROLS
FLIGHT CREW OPERATING MANUAL
ATTENTION GETTERS Ident.: DSC-31-30-00001231.0001001 / 10 JAN 11 Applicable to: ALL
(1)
MASTER WARN lights ‐ Flash red for level 3 warning ‐ Accompanied by an aural warning (continuous repetitive chime, specific sounds or synthetic voice).
(2)
MASTER CAUT lights ‐ Light up steady amber for a level 2 caution ‐ Accompanied by a single chime. These lights go out when : ‐ One pilot presses the light (except for some red warnings, such as the overspeed and stall warnings) ‐ The warning/caution situation is over ‐ The pilot presses the CLR pb on the ECAM control panel (except for some red warnings, such as the overspeed and stall warnings). ‐ The pilot presses the EMER CANC pb on the ECAM control panel. The aural warnings cease when : ‐ One pilot presses the MASTER WARN light (except for some red warnings, such as the overspeed and stall warnings) ‐ The warning situation is over ‐ The pilot presses the EMER CANC pb on the ECAM control panel.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-31-30 P 5/6 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ECAM CONTROLS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-30 P 6/6 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-31-40-00001232.0003001 / 22 MAY 12 Applicable to: ALL
The Primary Flight Display (PFD) provides the following information to the flight crew: ‐ Attitude and guidance ‐ Airspeed ‐ Altitude (BARO and radio) and vertical speed ‐ Heading and track ‐ FMGS modes (Flight Mode Annunciator) ‐ Vertical and lateral deviations ‐ Radio navigation information (ILS, DME).
The FWC monitors main parameters such as attitude, heading, and altitude. For more information, Refer to DSC-31-40 Flags and Messages Displayed on PFD.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-31-40 P 1/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
SPECIFIC GROUND INDICATIONS Ident.: DSC-31-40-00001233.0001001 / 22 MAY 12 Applicable to: ALL
(1)
Sidestick order indication This symbol is in white, and appears as soon as one engine is started. It indicates the total of the Captain’s and First Officer’s sidestick orders (shown here as left wing down, pitch up).
(2)
Max Sidestick Deflection This symbol is in white, and appears as soon as one engine is started.
(3)
Ground Roll Guidance Command Bar This symbol is in green, and appears when the aircraft is on ground, or below 30 ft radio altitude, provided that a localizer signal is available. It indicates the Flight Director yaw orders, to maintain the aircraft on the runway centerline.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
DSC-31-40 P 2/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
ATTITUDE DATA Ident.: DSC-31-40-00001234.0003001 / 15 JUN 12 Applicable to: ALL 1
(1)
Fixed Aircraft Symbol This symbol is in black, and outlined in yellow. The yellow outline is dimmed if the crew selects TRK-FPA, unless the FMA is in the TOGA or FLX mode.
(2)
Roll Scale This scale is in white, and has markers at 0, 10, 20, 30, and 45 ° of bank.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C→
DSC-31-40 P 3/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
(3)
Roll Index (yellow) This pointer indicates the bank angle. When the bank angle exceeds 45 °, all the PFD symbols, except those for attitude, speed, heading, altitude, and vertical speed, disappear. The display returns to normal when the bank angle decreases below 40 °.
(4)
Pitch Scale (white) This scale has markers every 10 ° between 80 ° nose up and 80 ° nose down (every 2.5 ° between 10 ° nose down and 30 ° nose up). When pitch angle exceeds 25 ° nose up or 13 ° nose down, all the PFD displays except attitude, speed, speed trend, heading, altitude, and vertical speed disappear. Beyond 30 °, large red arrowheads indicate that the attitude has become excessive and show the direction to move the nose in order to reduce it. The display returns to normal when pitch angle becomes less than 22 ° nose up or 10 ° nose down.
(5)
Flight Control Protection Symbols The display shows these symbols (=) in green: • On the roll scale to mark the bank angle protection availability. • On the pitch scale at 15 ° nose down or 30 ° nose up to mark the pitch limits. An amber x replaces these symbols if the corresponding protection is lost. (Refer to DSC-27-20-10-20-A Protections - General)
(6)
Sideslip Index (yellow) This trapezoidal index moves beneath the roll index. On ground, it represents the lateral acceleration of the aircraft. In flight, it shows sideslip (as computed by the FAC). One centimeter of displacement indicates 0.2 g. The sideslip index is against its stop at 0.3 g.
In case of engine failure at takeoff or go around, the sideslip index changes from yellow to blue. Note:
The sideslip target is blue, if: ‐ CONF 1, 2, or 3 is selected, and ‐ Any ENG N1 > 80 %or one Thrust Lever > MCT (≥ FLX if FLX or DERATED TO), and ‐ The difference between the ENG N1’s exceeds 35 %. In this case, the sideslip index is called β target.
When this index is centered with the roll index, the sideslip equals the sideslip target for optimum aircraft performance. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C
DSC-31-40 P 4/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
AIRSPEED Ident.: DSC-31-40-00001235.0004001 / 18 MAR 11 Applicable to: ALL
(1)
Actual Airspeed Reference Line and Scale A white scale, on a grey background, moves in front of a fixed yellow reference line (next to a yellow triangle) to indicate airspeed. The minimum airspeed indication is 30 kt.
(2)
Speed Trend (yellow) This pointer starts at the speed symbol. The tip indicates the speed the aircraft will reach in 10 s, if its acceleration remains constant. The pointer only appears, when it is greater than 2 kt, and disappears when it is less than 1 kt. It also disappears, if the FACs fail.
(3)
Target Airspeed (magenta or blue) This symbol gives the target airspeed, or the airspeed corresponding to the target Mach number. The target airspeed is the airspeed computed by FMGC in managed speed mode (magenta), or the airspeed manually entered on the FCU in selected speed mode (blue). The target speed is indicated by a magenta or blue triangle.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D→
DSC-31-40 P 5/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
When the target speed is off the speed scale, its value is displayed as numbers, either above or below the speed scale. (4)
Mach Number (green) It is displayed, when it is greater than0.5.
(5)
Speed Protection (green) This symbol indicates the speed (VMO +6 kt or MMO +0.01) at which overspeed protection becomes active (Refer to DSC-27-20-10-20-A Protections - General).
(6)
ECON Speed Range (magenta) In descent mode with the ECON/AUTO SPD mode active, these two thick lines replace the selected speed symbol. It shows the upper and lower limits, calculated by the FMGC. ‐ The upper speed is target speed +20 kt, limited to VMAX or VMO -3 kt or MMO -0.006, whichever is lowest. If a speed limit or a speed constraint applies, the upper margin is limited to ECON SPD +5 kt. ‐ The lower speed margin is the target speed -20 kt, limited to green dot, F, S, or VLS, whichever is higher.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-31-40 P 6/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
(1)
Minimum Selectable Speed (VLS) The top of the amber strip along the speed scale indicates this speed. It represents the lowest selectable speed providing an appropriate margin to the stall speed. (Refer to PRO-SUP-10 Characteristic Speeds) VLS information is inhibited from touchdown until 10 s after liftoff.
(2)
Alpha Protection Speed The top of a black and amber strip along the speed scale indicates this speed. It represents the speed corresponding to the angle of attack at which alpha protection becomes active (Refer to DSC-27-20-10-20-A Protections - General). It is displayed when in pitch normal law.
(3)
Alpha MAX Speed The top of a red strip along the speed scale indicates this speed. It represents the speed corresponding to the maximum angle of attack that the aircraft can attain in pitch normal law (Refer to DSC-27-20-10-20-A Protections - General). It is displayed when in pitch normal law.
(4)
VMAX The lower end of a red and black strip along the speed scale defines this speed. It is the lowest of the following: ‐ VMO or the speed corresponding to MMO ‐ VLE ‐ VFE (Refer to PRO-SUP-10 Characteristic Speeds)
(5)
Stall Warning Speed (VSW) The top of a red and black strip along the speed scale defines this speed. It is the speed corresponding to the stall warning. (Refer to DSC-27-20-10-20-A Protections General). VSW information is inhibited from touchdown until 5 s after liftoff. It is displayed when operating in pitch alternate or pitch direct law.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-31-40 P 7/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
(1)
Decision Speed (V1) This is a blue symbol (numeral one) that the crew manually inserts via the MCDU. When it is off the scale, the upper part of the scale shows it in numbers. It disappears after liftoff. (Refer to PRO-SUP-10 Other Speeds).
(2)
Minimum Flap Retraction Speed This is a green symbol (letter F). It appears when the flap selector is in position 3 or 2. (Refer to PRO-SUP-10 Characteristic Speeds).
(3)
Minimum Slat Retraction Speed This is a green symbol (letter S). It appears when the flap selector is in position 1. (Refer to PRO-SUP-10 Characteristic Speeds).
(4)
VFE NEXT The VFE next symbol is an amber equal sign showing the VFE corresponding to the next flap lever position. It appears when the aircraft altitude is below 15 000 ft or 20 000 ft, depending upon the FAC standard. (Refer to PRO-SUP-10 Protection Speeds).
(5)
Green Dot (Engine-out operating speed in clean configuration) This green dot appears, when the aircraft is flying in the clean configuration.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-31-40 P 8/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
INDICATIONS ON PFD
It shows the speed corresponding to the best lift-to-drag ratio. (6)
Rotation speed: (VR) VR is entered on the PERF takeoff page of the MCDU, and is indicated by a cyan circle. This cyan circle is visible during takeoff. Note:
V2 is represented by the target speed index during takeoff. V2 is manually inserted by the crew via the MCDU. ALTITUDE
Ident.: DSC-31-40-00001237.0061001 / 27 JUN 12 Applicable to: ALL 2
(1)
Altitude Indication This appears both as a white moving scale, and as a green digital readout on a grey background. Small white marks are positioned on the scale against the round values (e.g. 280, 290...). “NEG” appears in the window in white for negative values. The altitude window changes from yellow to amber, if the aircraft deviates from the FCU-selected altitude or flight level. On any approach for which an minimum is entered in the FMGS, the altitude numbers change from green to amber, when the aircraft goes below the minimum.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← D to E →
DSC-31-40 P 9/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
(2)
Linear Deviation (green filled circle) This symbol appears next to the altitude corresponding to the theoretical vertical profile computed by the FMGC. It is displayed from the top of descent down to the MAP altitude. The flight crew can read the linear deviation directly from the altitude scale. The range is ±500 ft. When the linear deviation value exceeds ±500 ft, the symbol stays at the range limit but changes to a half filled circle and the PROG page displays the exact value.
(3)
Target Altitude or Selected Flight Level Symbol (blue) This symbol shows the FCU selected altitude (if QNH or QFE BARO reference is selected) or the selected flight level (if STD BARO reference is selected.) When the FMGC operates in the vertical managed mode, this symbol is magenta if it represents a flight plan altitude constraint that the FMGC will follow. If the target altitude or flight level is on the scale, the symbol is displayed and the numerical value appears inside the symbol. If it is off the scale, the symbol is not displayed, and the numerical value appears above or underneath the scale.
(4)
Barometric Reference The display shows “STD” or it shows “QNH” or "QFE" and the numerical setting in hectoPascals or inches of mercury. It pulses when the selection made by the flight crew is not correct (STD not selected above transition altitude in climb or STD still selected in approach below transition level).
METRIC ALTITUDE INDICATION If metric reference is selected on the FCU two additional symbols are displayed on PFD.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-31-40 P 10/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
(1)
Target altitude or selected flight level (magenta or blue) The display shows the selected altitude value in meters.
(2)
Altitude indication (green) The display shows the actual aircraft altitude value in meters.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E
DSC-31-40 P 11/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
ALTITUDE (CONT'D) Ident.: DSC-31-40-00006121.0002001 / 10 DEC 09 Applicable to: ALL
(1)
Radio Height A value appears, when the aircraft is lower than 2 500 ft. ‐ If a DH has been entered, the radio height appears : • In green, when DH + 100 ft < RA < 2 500 ft • In amber, when RA < DH + 100 ft If “NO” is entered as the DH on the MCDU APPROACH page, 0 ft becomes a default value. When the aircraft reaches the decision height selected on the MCDU, DH letters flash amber for 9 s, then remain amber above the radio height indication. ‐ If no DH has been entered, or if both FMGCs fail, the radio height appears : • In green, when 400 ft < RA < 2 500 ft • In amber, when RA ≤ 400 ft The radio altitude indication changes every 10 ft down to 50 ft, then every 5 ft down to 10 ft, then every foot.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F→
DSC-31-40 P 12/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
(2)
Landing Elevation (blue) The top of the brown surface on the altitude scale represents the landing elevation at the flight-planned destination. It is displayed : ‐ during flight phases 7 and 8 and ‐ if the STD reference mode is not selected.
(3)
Ground reference A red ribbon on the right of the altitude scale represents the field elevation. This ribbon, which is driven by the radio altimeter signal, is displayed below 570 ft. It moves up, as does the lower line of the attitude sphere, with the altitude scale as the aircraft descends. When the aircraft has touched down, the top of this ribbon is at the middle of the altitude window. VERTICAL SPEED
Ident.: DSC-31-40-00001239.0002001 / 29 MAR 11 Applicable to: ALL
The displayed vertical speed information is normally based on both inertial and barometric data. If inertial data is not available, it is automatically replaced by barometric information. In this case, the window around the numerical value becomes amber.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← F to G →
DSC-31-40 P 13/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
(1)
Analog pointer This pointer, which is normally in green, points to a white vertical speed scale, displayed on a grey background and graduated at intervals of 500 ft/min. If the V/S is greater than 6 000 ft/min, the pointer stays at the end of the scale.
(2)
Digital indication This number, normally in green, is the vertical speed in hundreds of feet per minute. It disappears, if the vertical speed is less than 200 ft/min. The analog pointer and the digital indication become amber, if: • V/S is greater than 6 000 ft/min, (climb or descent) • V/S is greater than 2 000 ft/min, during descent when 1 000 ft < RA < 2 500 ft, or • V/S is greater than 1 200 ft/min, during descent and RA < 1 000 ft. Note:
For TCAS, refer to DSC / 34.Navigation / 80.TCAS / 20.Controls and Indicators.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G
DSC-31-40 P 14/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
HEADING Ident.: DSC-31-40-00001240.0002001 / 22 MAY 12 Applicable to: ALL
(1)
Heading Reference Line and Scale A white scale on a grey background moves in front of a fixed yellow reference line to indicate the actual magnetic heading. “TRUE” appears, when the display indicates the true heading, rather than the magnetic heading (latitude above 73 ° North or below 60 ° South).
(2)
Selected Heading or Track Index (blue) This pointer is in blue, and indicates the heading or track displayed on the FCU HDG-TRK window. The index is replaced by digits on the right or left side of the scale, when the selected value is off the scale. If the FD pushbutton is OFF, a second heading/track symbol appears on the horizon line, and markers are displayed every 10 °.
(3)
Actual Track Symbol This symbol is a small green diamond.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
H
DSC-31-40 P 15/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
FLIGHT PATH VECTOR Ident.: DSC-31-40-00001241.0001001 / 18 MAR 11 Applicable to: ALL
(1)
Flight Path Vector (FPV) This symbol appears, when the pilot selects TRK/FPA on the FCU. The flight path vector represents the lateral and vertical trajectory of the aircraft with respect to the ground. ‐ On the lateral scale, it indicates the aircraft’s track. ‐ On the vertical scale, it indicates the aircraft’s flight path angle. Example :
The aircraft flies a track of 009 ° (heading 360 °, wind from west) and descends with a flight path angle of minus 7.5 °.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
I
DSC-31-40 P 16/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
GUIDANCE Ident.: DSC-31-40-00001242.0001001 / 18 MAR 11 Applicable to: ALL
Two completely different flight director modes are available, each with its own characteristic symbols. The symbol displayed corresponds to the basic operating reference the pilot has selected – either HDG V/S or TRK FPA. In normal operation, PFD1 displays FD1 orders. If FD1 fails, PFD1 automatically displays FD2 orders on PFD1, the FD2 indication in the right column of the FMA flashes for a few seconds. This is also applicable to FD2 orders, that are displayed on PFD2. IF THE CREW HAS SELECTED HDG V/S TO BE THE BASIC REFERENCE : The PFD displays FD bars in green. They automatically move out of view at touchdown in ROLL OUT mode. They flash for 10 s, and then remain steady, if the following occur : ‐ A reversion to the HDG V/S basic mode (manual or automatic), or ‐ The selected flight level is changed, when ALT CAPTURE mode is engaged, or ‐ The loss of LOC or G/S in LAND mode or loss of LAND mode, or ‐ At the first AP or FD engagement. The PFD displays a yaw bar in green below 30 ft radio altitude, if a localizer signal is available: ‐ During takeoff (in RWY mode) ‐ Upon landing (in FLARE and ROLL OUT mode).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
J→
DSC-31-40 P 17/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
(1)
FD Crossed Bars (green)
(2)
Yaw Bar (green)
THE CREW HAS SELECTED TRK FPA AS THE BASIC REFERENCE : An inertial flight path vector defines the aircraft's horizontal and vertical track, taking wind effect into account. An associated flight path director symbol guides the flight crew onto the vertical and horizontal flight path targets.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←J→
DSC-31-40 P 18/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
(1)
Flight Path Vector (green)
(2)
Flight Path Director (green)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←J
DSC-31-40 P 19/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
TRAJECTORY DEVIATION Ident.: DSC-31-40-A-NG00088 Applicable to: ALL Ident.: DSC-31-40-A-00001243.0003001 / 18 MAR 11
ILS APPROACH
(1)
Localizer Deviation Scale and Index
(2)
Glideslope Deviation Scale and Index Deviation scales appear as soon as the flight crew pushes an LS pushbutton on the EFIS control panel. Deviation indexes appear, when the glideslope and localizer signals are valid, if deviation scales are displayed. When a deviation index is out of the displayed range, only half a symbol appears at the end of the scale. The LOC scale flashes and continues to flash if the deviation exceeds 1/4 dot for two seconds while the aircraft is between 15 ft and 1 000 ft and CAT2 or CAT3 capability displayed on the FMA, and either LOC, LAND, or FLARE is engaged. The glideslope scale flashes and continues to flash, if the deviation exceeds one dot for two seconds (above 100 ft RA). “LOC” and the glideslope scale half index symbols flash and continue to flash, when the deviation exceeds two dots for two seconds.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
K→
DSC-31-40 P 20/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
0ne dot represents a deviation of ± 0.8 ° on the localizer scale, and ± 0.4 ° on the glideslope scale. Ident.: DSC-31-40-A-00001244.0003001 / 22 MAY 12
ILS APPROACH (CONT'D)
(1)
ILS information (magenta) The following information appears on the PFD, when the crew has selected an ILS frequency and course, and pushed the LS pb: • ILS identification, as decoded by the ILS receiver; • ILS frequency; • DME distance, if the ILS has a DME
(2)
ILS course Pointer (magenta) This pointer appears on the PFD, when the crew has selected an ILS frequency and course, and pushed the LS pb. It is a dagger-shaped symbol on the heading scale. The ILS course pointer is replaced by digits on the right or left hand of the heading scale (in a white box) when the ILS course value is outside the displayed portion of the heading scale.
(3)
Marker Indications OM appears in blue, when the aircraft flies over the outer marker. MM appears in amber, when it flies over the middle marker.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←K→
DSC-31-40 P 21/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
IM appears in white, when it flies over an airways marker beacon or the ILS inner marker. (4)
ILS Message This flashes amber, when the APPR mode is armed and the ILS display is not selected.
Ident.: DSC-31-40-A-00001245.0022001 / 18 MAR 11
NON PRECISION APPROACH
(1)
Vertical Deviation Scale and Index These symbols appear when in the approach phase and, when either FINAL is armed/engaged or a non-LS approach has been entered. They are displayed in the approach or go-around phase, until the MDA has been reached, or the MAP or the runway has been sequenced. They give the vertical deviation from the trajectory defined by the FMGC. Each index scale graduation represents 100 ft. The range is ± 200 ft. Note:
If the LS pb is pressed, glide deviation has priority over vertical deviation information. As long as VDEV display conditions are met, and the LS pb is selected, an amber VDEV message flashes above the glide scale.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←K
DSC-31-40 P 22/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
FLIGHT MODE ANNUNCIATOR Ident.: DSC-31-40-00001246.0001001 / 23 MAR 11 Applicable to: ALL
For a detailed discussion of legends and messages that may appear during FMGS operations, see FLIGHT GUIDANCE chapter (Refer to DSC-22_30-100-A Flight Mode Annunciator (FMA) - General).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
L
DSC-31-40 P 23/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
TAILSTRIKE PITCH LIMIT INDICATOR Ident.: DSC-31-40-00013185.0003001 / 18 MAR 11 Applicable to: ALL
(1)
Tailstrike Pitch Limit The pitch limit indicates the maximum pitch attitude to avoid the tailstrike risk at landing. The indication is a fixed value corresponding to the main landing gear compressed. The indication appears at 400 ft radio height. The indication disappears, when there is no longer a risk of tailstrike. ALTITUDE ALERT
Ident.: DSC-31-40-00001247.0002001 / 22 MAY 12 Applicable to: ALL
The FWC generates an altitude warning (C chord sound and PFD’s altitude window pulses in yellow or flashes in amber), when the aircraft approaches a preselected altitude or flight level, or when it deviates from its selected altitude or flight level. This warning results from a comparison between the altitude (ADIRS) and the preselected altitude displayed on FCU.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
M to N →
DSC-31-40 P 24/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
‐ Selecting a new altitude, or pushing the ECAM’s EMER CANC pushbutton, or pressing either MASTER WARN pushbutton, cancels the continuous C chord. ‐ Selecting a new altitude stops the flashing of the altitude window. ‐ The altitude alert is inhibited: • When the slats are out, with the landing gear is selected down, or • In approach after the aircraft captures the glideslope, or • When the landing gear is locked down.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←N
DSC-31-40 P 25/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
FLAGS AND MESSAGES DISPLAYED ON PFD Ident.: DSC-31-40-00001248.0090001 / 22 MAY 12 Applicable to: ALL
(1)
ATT flag (red) If the PFD loses all attitude data, its entire sphere is cleared to display the ATT flag.
(2)
CHECK ATT, CHECK CAPT (F/O) PFD, CHECK EWD, DU NOT MONITORED (amber) For more information, Refer to DSC-31-05-10 Introduction
(3)
SI flag (red) If the sideslip information is lost or any reverse is deployed in flight, the index disappears and a red SI flag appears.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
O→
DSC-31-40 P 26/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
(4)
FPV flag (red) In the TRK FPA mode, when the drift angle or flight path angle is not valid, an FPV flag appears.
(5)
FD flag (red) If both FMGCs fail, or if both FDs are disengaged and the FD pb is on and the attitude is valid, a red FD flag appears.
(6)
SPD flag (red) If the speed information fails, a SPD flag replaces the speed scale.
(7)
SPD SEL flag (red) If the selected speed information fails, a SPD SEL flag appears.
(8)
SPD LIM flag (red) This flag appears when both FACs are inoperative, or in case of SFCC dual flap/slat channel failure. In this case, the following PFD information is lost : VLS, S, F, Green Dot, Vtrend, Vmax, VFE next, VSW.
(9)
V1 INOP flag (red) When the V1 signal is not valid, a V1 INOP flag replaces the digital value.
(10) ALT flag (red) If the altitude information fails, the ALT flag replaces the altitude scale. (11) CHECK ALT flag (amber) For more information, Refer to DSC-31-05-10 Introduction (12) ALT SEL flag (red) If the selected altitude information fails, an ALT SEL flag appears. (13) V/S flag (red) If the vertical speed information fails, the V/S flag replaces the vertical speed scale. (14) LOC and G/S flags (red) If the localizer or glideslope receiver fails, a LOC or G/S flag appears on the deviation scale. (15) VDEV flag (red) If the vertical deviation information fails, and the LS pb is not pressed, a VDEV flag replaces the VDEV scale. (16) RA flag (red) If both radio altimeters fail, this flag appears in place of the radio height indication.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←O→
DSC-31-40 P 27/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
(17) DH flag (amber) A DH flag appears, when the aircraft reaches the selected DH. (18) HDG flag (red) If the heading information fails, the HDG flag replaces the heading scale. (19) CHECK HDG flag (amber) For more information, Refer to DSC-31-05-10 Introduction (20) MACH flag (red) This flag appears, if the Mach data fails. (21) VDEV (amber) At the top of the glide scale, this message flashes when either the FINAL mode is armed/engaged and the LS pb is selected. (22) DME 1 flag (red) When the DME distance is not valid, a DME1 (on PFD1) or DME2 (on PFD2) flag replaces the DME distance indication. (23) ILS1 flag (red) If an ILS frequency fails, or if either the LOC or G/S signals fail, an ILS1 (on PFD1) or ILS2 (on PFD2) flag replaces the ILS frequency indication. (24) WINDSHEAR warning (red) This message is displayed, when windshear is detected (reactive windshear warning) by the FAC. Refer to DSC-22_40-40 Windshear Detection Function (25) W/S AHEAD This message is displayed, when the predictive windshear system has detected windshear ahead of the aircraft. The message is in amber or red, depending on the alert level. Refer to DSC-34-60-30 Windshear Alerts Inhibition (26) L/DEV flag (red) When the crosstrack error is not valid, a L/DEV flag is displayed in red instead of the lateral deviation scale. (27) CHECK SD, CHECK CAPT (F/O) ND (amber) For more information, Refer to DSC-31-05-10 Introduction (28) L/DEV (amber) At the top left of the LOC scale, this message flashes when the FINAL mode is armed/engaged, and the LS pb is selected. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←O→
DSC-31-40 P 28/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
Note:
1. All flags, except, V1 INOP which is steady, flash for 9 s, then remain steady. 2. For information on the TCAS flag, Refer to DSC-34-80-20 PFD Indications. BACKUP SPEED/ALTITUDE SCALE
Ident.: DSC-31-40-00006215.0004001 / 18 MAR 11 Applicable to: ALL
GENERAL A backup speed scale and a backup altitude scale replace simultaneously the normal speed and altitude scales when all the three ADRs are switched OFF. This enables the flight crew to fly at a safe speed and altitude in case of an unreliable speed/altitude indication. The backup speed scale information is based on the angle–of–attack, and depends on the slat/flap configuration. The backup altitude scale displays the GPS altitude. BACKUP SPEED SCALE
(1)
Red FAST area: This red area indicates excessive speed range.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← O to P →
DSC-31-40 P 29/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
(2)
Amber area: This amber area indicates excessive speed range while keeping an appropriate margin to the maximum structural speeds.
(3)
GREEN area: The green area indicates the safe speed range.
(4)
Target speed (green): This symbol indicates the optimum target speed. During approach, it indicates the target speed for the approach.
(5)
Actual Speed Reference Line (Yellow): This fixed reference line, next to a yellow triangle, indicates the aircraft’s current speed.
(6)
Amber area: The amber area indicates too low speed while keeping an appropriate margin to the stall speed.
(7)
Red SLOW area: The red SLOW area indicates the speeds that are lower than the stall speed.
BACKUP ALTITUDE SCALE
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←P→
DSC-31-40 P 30/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
(1)
GPS ALT and GPS flags (White): These flags appear to highlight the fact that the barometric altitude is replaced by the GPS altitude.
(2)
Altitude indication: Amber dashes appear over the last two digits to indicate a degraded altitude display mode.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←P
DSC-31-40 P 31/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-40 P 32/32 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-31-45-00001249.0003001 / 10 DEC 09 Applicable to: ALL
There are five different displays (five modes to display navigation information) : ‐ ROSE LS ‐ ROSE VOR ‐ ROSE NAV ‐ ARC ‐ PLAN The Navigation Display (ND) can provide a weather radar image in all modes, except PLAN. ROSE MODES
1 Ident.: DSC-31-45-00001250.0002001 / 29 MAR 12
Applicable to: ALL
(1)
Aircraft symbol (yellow) Fixed and centered in the display, this symbol points to the yellow lubber line.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-31-45 P 1/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
(2)
Aircraft heading The fixed yellow lubber line points to the aircraft magnetic heading on the moving white compass rose. Small white triangles are fixed at 45 ° intervals on the circumference of the compass rose. “TRUE” appears at the top of the compass rose, when it is displaying true heading instead of magnetic heading (latitude above 73 ° North or 60 ° South).
(3)
Selected heading or track (blue) This pointer shows the heading or track indicated on the FCU's HDG TRK counter.
(4)
Actual aircraft track (green) This symbol is a small green diamond.
(5)
Ground speed and true air speed (green) ADIRS furnishes these speeds.
(6)
Wind direction and speed ADIRS provides the wind direction and speed. The digital direction and the analog direction (green arrow) indicate the north reference that is in use. The green arrow only appears, if the wind speed is above two knots. If the display does not receive either wind speed or direction, dashes replace the numbers on the display.
(7)
NAVAIDs When the ADF-OFF-VOR selector switch on either the pilot's or copilot's EFIS control panel is set to ADF or VOR, the onside ND displays the following characteristics of the corresponding NAVAID in white for VOR or in green for ADF (left side for receiver 1 and right side for receiver 2): ‐ Type of NAVAID (ADF or VOR) ‐ Shape and color of the associated bearing pointer (if the bearing pointer is in view). ‐ NAVAID identification (or frequency by default) ‐ DME distance if a DME is collocated with the selected VOR. ADF and DME distance are never displayed at the same time. ‐ Mode of tuning • M for a NAVAID tuned manually by the pilot through the MCDU (underlined and dimmed), • R for a NAVAID tuned from an RMP (Radio Management Panel) (underlined and dimmed), • Nothing for a NAVAID tuned automatically by the FMGC. If reception fails, the ND stops displaying the associated data (except for the identification or frequency).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
DSC-31-45 P 2/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
INDICATIONS ON ND
(8)
Bearing pointer (green for ADF, white for VOR) This pointer appears when bearing data is available. If the aircraft is not receiving the beacon or if a receiver fails, the associated bearing pointer disappears.
(9)
Chronometer Indication (white) These numbers appear when the onside chronometer is started. They display the elapsed time. The indication is in minutes and seconds from 0 to 59 min 59 s, and in hours and minutes from 1 h to 99 h 59 min (Seconds are not displayed beyond 59 min 59 s).
(10) Range marks The range scale value selected on the EFIS control panel (10 to 320 nm) governs the scale of the ND. ROSE LS MODE Ident.: DSC-31-45-00009584.0065001 / 22 MAY 12 Applicable to: ALL
(1)
ILS course pointer (magenta) This dagger-shaped symbol points to the selected ILS course.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
DSC-31-45 P 3/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
The ILS is selected either by the FMGC (autotuned or manually) or through the RMP in backup mode. If no course has been entered, the value defaults to 360 °. (2)
Localizer deviation bar (magenta) This bar moves laterally with respect to the course pointer. Its scale consists of two dots on each side of zero deviation. Each dot represents a deviation of about ±0.8 °. If the deviation becomes excessive (1/4 dot, 0.2 °) above 15 ft RA, the bar and the scale pulse.
(3)
Glide deviation (magenta) This diamond moves on a vertical scale that has two white dots on each side of the yellow reference line. Each dot represents a deviation of about ±0.4 °. If the deviation becomes greater than one dot above 100 ft RA, the scale and the diamond flash.
(4)
Selected ILS information This display shows the ILS frequency (magenta), selected course (blue), and identification (magenta).
(5)
ILS message (green) This message shows the full runway name of the selected approach. It appears: ‐ When the flight crew selects an ILS approach on the MCDU, and ‐ When the FMS flight phase is DES, APP or GA, or the FMS phase is CRZ and the along track distance to destination is less then 250 nm. Note:
ILS 1 information appears on PFD 1 and ND 2. ILS 2 information appears on PFD 2 and ND 1.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C
DSC-31-45 P 4/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
ROSE VOR MODE Ident.: DSC-31-45-00001252.0029001 / 24 FEB 11 Applicable to: ALL
(1)
VOR course pointer (blue) This dagger-shaped symbol points to the selected VOR course. The VOR course is automatically selected by the FMGC or manually by the crew using the MCDU pages or the RMP backup mode.
(2)
Lateral deviation bar (blue) This bar shows the VOR deviation on a lateral scale. Each dot represents 5 °. When the lateral deviation exceeds 10 °, the bar remains displayed on the outer dot. The arrow on the bar gives the TO/FROM indication.
(3)
VOR information (white) This area displays the frequency of the selected VOR and its identification (if decoded by the receiver), the selected course.
(4)
VOR or GPS message (green) VOR 14L appears when the flight crew has selected a VOR approach on the MCDU. GPS 14L appears when the crew has selected a GPS approach.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D
DSC-31-45 P 5/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
ROSE NAV MODE/ARC MODE Ident.: DSC-31-45-00001253.0065001 / 22 MAY 12 Applicable to: ALL
ROSE NAV and ARC modes give the pilot the same information, but ARC mode limits it to the forward 90 ° sector.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E→
DSC-31-45 P 6/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
(1)
Range Marks and Values The values displayed on the ND are: In ROSE NAV mode 1/4 of the selected range for the inner circle. 1/2 of the selected range for the heading scale circle. In ARC mode 1/4 of the selected range for the first inner arc. 1/2 of the selected range for the second inner arc. 3/4 of the selected range for the third inner arc.
(2)
Fligght Plan The crew can use the MCDU to select various types of flight plan: ‐ The active flight plan (the flight plan the aircraft is actually following when the NAV mode is engaged) is represented by a continuous green line. The ND shows only the part of the flight plan that is ahead of the aircraft, as well as the waypoints that are still to be overflown and the waypoint from which the aircraft is coming. The ND does not show a SID or a STAR, except for the last waypoint of the SID and the first waypoint of the STAR, when the selected range is 160 or 320 nm. If the primary flight plan is not active, it is represented by a dotted green line. ‐ A continuous blue line portrays the missed approach procedure, and a dashed blue line portrays the flight plan to the alternate. The missed approach and the alternate flight plan are displayed when: • In ARC or ROSE NAV mode, a missed approach waypoint or an alternate flight plan waypoint is displayed on the onside MCDU. • In PLAN mode a missed approach or alternate waypoint is displayed in the 2L field of the onside MCDU. ‐ The secondary flight plan is represented by a continuous white line. The ND continues to display the active flight plan ‐ Temporary flight plan The revised portion of the flight plan is represented by a dotted yellow line ‐ Flight plan capture When the aircraft is off the primary flight plan and is flying toward it in HDG mode with the NAV mode armed, the ND shows the new active flight plan as a continuous green line if the FMGC has computed the intercept path. The part of the flight plan before the interception point shows as a dotted green line.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-31-45 P 7/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
(3)
Waypoint The ND can display various kinds of waypoints: Flight plan waypoints The ND displays these as green diamonds (white, for TO waypoints). When the flight crew selects the WPT option on his EFIS control panel, all waypoints other than flight plan waypoints are displayed in magenta. Pseudo waypoint Point of the flight path where the aircraft is predicted to reach a selected altitude or speed.
Pseudo waypoint
Definition Level symbol (top of climb or level-off position), when the aircraft reaches: ‐ The FCU-selected altitude (blue arrow), or ‐ The constrained altitude, if it is more restrictive than the FCU altitude and if appropriate modes are engaged (magenta) ‐ It does not appear when the aircraft is within 100 ft above, or below, the selected altitude. Top of descent symbol, or continue descent symbol: ‐ White, if DES is not armed ‐ Blue, if DES is armed. Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-31-45 P 8/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
Continued from the previous page
Pseudo waypoint
Definition Start of CLIMB symbol: ‐ White, if CLB is not armed ‐ Blue, if CLB is armed. Intercept point symbol: ‐ White, if only the NAV mode is engaged ‐ Blue, if DES mode is engaged ‐ Indicates the point at which the aircraft is predicted to intercept the descent path, if there is any vertical deviation while the aircraft is in DES mode.
•
Speed change symbol (magenta): Indicates the point at which the aircraft will start an automatic acceleration or deceleration from the current speed to a new computed speed for SPD LIM, SPD CSTR, or HOLDING SPD. Decelerate point symbol: ‐ Indicates the point at which the aircraft is predicted to decelerate for approach (and thus switch to the approach phase) ‐ Magenta, if in managed speed and NAV or approach mode is engaged ‐ White, if in selected speed or HDG/TRK mode ‐ Automatic decelerations only occur when displayed in magenta. ALT CSTR symbol set around the constrained waypoint: ‐ Magenta, when the ALT CSTR is predicted to be met ‐ Amber, when the ALT CSTR is predicted to be missed ‐ White, when the ALT CSTR is not taken into account by the FMGS, and NAV mode is engaged. Energy circle symbol (green arc) centered on the aircraft position and oriented to the current track line. Represents the Required Distance to Land. Only displayed if the lateral guidance mode is heading or track, and the current FMS flight phase is in cruise, descent or approach, and the aircraft is within 180 nm of the destination.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-31-45 P 9/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
(4)
TO waypoint This is the next waypoint to be overflown. This area of the screen also shows: ‐ Waypoint identification (white) ‐ Track to go (green) ‐ Distance to go (green) ‐ Estimated time of arrival (green), assuming the aircraft will fly directly from its present position to the TO waypoint at the current ground speed.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-31-45 P 10/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
(5)
NAVAIDs The display uses specific symbols for NAVAIDs: DME or TACAN + VOR VOR/DME ▵ NDB The symbol appears: ‐ In green if the NAVAID is a current waypoint of the flight plan ‐ In white if it is the TO waypoint ‐ In blue when the NAVAID is tuned for display either automatically by the FMGC or manually through the MCDU ‐ In magenta when the NAVAID is not part of the flight plan and is called for display as an option (corresponding option pushbutton pressed on the FCU EFIS control panel).
(6)
Airport Airport included in the flight plan: ‐ If the runway is not specified, the airport is represented by a star and the identification is displayed in white. Example: * LSGG ‐ If the runway is specified, it is represented by an oriented runway symbol in white.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-31-45 P 11/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
Optional airport information The airports that are not displayed as part of the flight plan may be called for display (ARPT pushbutton on the EFIS control panel). They are represented by a star and the identification in magenta. (7)
ILS Course (Magenta) When the pilot pushes the LS pb-sw on the EFIS control panel, and if an ILS station has been selected, the display shows an ILS course symbol.
(8)
ILS Marker Beacons The screen shows these as waypoints (diamonds). When the aircraft overflies a marker beacon, the corresponding symbol flashes: Blue for the outer marker. Amber for the middle marker. White for the inner marker.
(9)
Cross Track Error This is the aircraft's lateral deviation from the active leg of the flight plan (related to the great circle route). It is indicated in nautical miles (NM), with the letter R (right) or L (left), according to the position of the aircraft with respect to the flight plan.
(10) Track line This line appears in green only in the ROSE NAV or ARC mode when HDG or TRK has been selected on the FCU.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-31-45 P 12/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
(11) Procedure turns and holding patterns These only appear when they are part of the flight plan. For the 160 and 320 nm range scales, each one is represented by a white arrow that originates at the associated fix and indicates the direction of the turn.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-31-45 P 13/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
INDICATIONS ON ND
For shorter range scales, and if the procedure turn or the holding pattern is in the next or the active leg, the display shows the full circuit or pattern.
(12) Minimum Off Route Altitude (MORA) Provided CSTR is selected and range is selected equal to or above 40 nm, a digital readout (Flight Level) is displayed, which represents the Minimum Off Route Altitude allowed, within a circular area centered on present A/C position and bounded by 40 nm of radius limit. Nothing is displayed, if MORA for the chosen flight route is not available in the FMGS database. PLAN MODE Ident.: DSC-31-45-00001254.0002001 / 24 FEB 11 Applicable to: ALL
This mode statically displays the flight plan legs on a map oriented to true north. The map is centered on a map reference point, that the pilot selects by scrolling to it on his MCDU. The map reference point is the waypoint displayed on the second line of the MCDU's F-PLN page. It can either be the active waypoint (next waypoint to be overflown), or any other waypoint of the flight plan. The pilot can scroll through the overall flight plan, and display it in PLAN mode. The pilot chooses the scale of the map with the range selector (the diameter of the outer circle corresponds to the selected range).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← E to F →
DSC-31-45 P 14/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
Data on NAVAIDs and on their characteristics and associated bearing pointers are not available in this mode.
(1)
Aircraft Position and True Track The orientation of the yellow aircraft symbol always indicates the true track of the aircraft. Its position represents the aircraft position given by the FMGS.
(2)
Map Reference Point If the CSTR option is not selected, the track and distance from the map reference point to the next F-PLN waypoint is displayed in magenta.
(3)
Cross Track Error Refer to DSC-31-45 ROSE NAV Mode/ARC Mode.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←F
DSC-31-45 P 15/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
WEATHER RADAR Ident.: DSC-31-45-00001255.0007001 / 22 MAY 12 Applicable to: ALL
(1)
Weather Radar Picture ‐ When the radar is operating, and when the ND is not in PLAN mode, the ND displays the weather radar picture. ‐ The echoes appear in different colors, depending on the precipitation rates (black, green, yellow, red or magenta). ‐ The selected ND range will determine how often the image is refreshed.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
G→
DSC-31-45 P 16/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
(2)
Tilt Angle ‐ The multiscan function of the weather radar alternatively scans at low and high beam, and automatically sets the tilt of these beams to optimize the weather radar detection. The displayed weather radar picture is the result of the storing and merging of the information from each beam. ‐ The value of the tilt angle is in degrees, and quarters of a degree. It appears in the lower right corner of the screen: • In green, when the MULTISCAN sw is set to AUTO. This value represents the average of the lower and the upper beam tilts. • In blue, next to the blue “MAN” indication, when the flight crew sets the MULTISCAN sw to MAN. The tilt angle is the angle between the horizon and the radar beam axis. • When the multiscan function is lost, the tilt value is dashed and the “NO AUTO TILT” message appears in amber on the ND, until the flight crew sets the MULTISCAN sw to MAN.
(3)
Gain Mode ‐ ”MAN” appears in white, when the flight crew selects the manual gain mode.
(4)
Failure Messages The ND lists the detected failures. If the message is in “red”, the ND does not display a radar image. If the message is in “amber”, the image is not affected. WXR RT (red) : Radar transceiver failure. WXR ANT (red) : Radar antenna failure. WXR CTL (red) : Radar control unit failure. WXR RNG (red) : Range error. WXR WEAK (amber) : Calibration failure. WXR ATT (amber) : Attitude control failure. WXR STAB (amber) : Antenna stabilization failure.
(5)
PAC alert When the flight crew sets the weather radar mode to WX or WX + T, and sets the gain to CAL, and when the aircraft is within 80 nm of a thunderstorm, the Path Attenuation Compensation (PAC) alert is available. The PAC alert displays a yellow arc on the outermost scale of the ND, when an intervening rainfall creates an attenuated area behind a thunderstorm (also called a radar shadow).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G→
DSC-31-45 P 17/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
Note:
The PAC alert is available during both automatic and manual operation (MULTISCAN sw either in AUTO or MAN position). PREDICTIVE WINDSHEAR SYSTEM
Ident.: DSC-31-45-00009579.0003001 / 24 FEB 11 Applicable to: ALL
(1)
Predictive windshear area indication A PWS SCAN message is displayed when the Predictive Windshear system is active on the ND. The predicted windshear area is indicated by a red and black icon and two yellow radial lines. Windshear information is available in ARC and ROSE ND modes. When the ND range is set above 10 nm, a W/S SET RNG 10 nm (Windshear, set range 10 nm ) message appears, requesting the crew to adjust the ND range. It is displayed even if the weather radar is switched off, provided the WINDSHEAR switch on the weather radar panel is set to AUTO. Depending on the windshear alert level, ND indication may be completed with a PFD message (Refer to DSC-31-40 Flags and Messages Displayed on PFD).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← G to H
DSC-31-45 P 18/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
EGPWS Ident.: DSC-31-45-00009586.0012001 / 22 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
I→
DSC-31-45 P 19/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
(1)
EGPWS terrain picture The ND displays the EGPWS terrain picture, when the TERR ON ND switch is selected ON, and the ND is not in PLAN mode. The terrain picture replaces the weather radar image. Terrain data is displayed independently of the aircraft relative altitude. The terrain appears in different colors and densities, in accordance with its relative height:
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←I→
DSC-31-45 P 20/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
Note:
(2)
‐ Areas without available terrain data in the EGPWS database appear in magenta ‐ The reference altitude is computed based on the current aircraft altitude or, if descending more than 1 000 ft/min, the altitude expected in 30 s ‐ In case of flight above the maximum elevation number, the relief between the minimum and maximum displayed elevations is displayed by using three different green levels.
Center Part Messages ‐ The “TERR CHANGE MODE” indication is displayed in red (or amber), in the case of a Terrain Awareness Display (TAD) warning (or caution) alert, if the current selected display mode is PLAN ‐ The “TERR REDUCE RANGE” indication is displayed in red (or amber), in the case of a Terrain Awareness Display (TAD) warning (or caution) alert, if the selected range is 160 nm or 320 nm.
(3)
TERR indication To differentiate between the terrain and the weather display, the weather radar TILT is replaced by a blue TERR, and the terrain display sweeps from the center outward to both ND sides.
(4)
Warning and caution messages TERR AHEAD or OBST AHEAD : For a caution. (amber) TERR AHEAD or OBST AHEAD : For a warning. (red) When triggered, these messages flash for 9 s, then remain steady until the caution or warning alert condition disappears. TERR RNG (red) : For a RANGE error warning. TERR TST (amber) : Appears during the EGPWS test, when the terrain pattern is displayed, and there is no failure.
(5)
Terrain or obstacle caution alert Generated when a conflict exists between the terrain caution envelope, ahead of the aircraft, and database-stored terrain/obstacles. The conflict area is shown in solid yellow.
(6)
Terrain or obstacle warning alert Generated when a conflict exists between the terrain warning envelope, ahead of the aircraft, and terrain/obstacles data stored in the database. The conflict area is shown in solid red. Note:
When an alert is generated (either caution or warning) and TERR ON ND is not selected, the terrain is automatically displayed and the TERR ON ND’s pushbutton ON light comes on.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←I→
DSC-31-45 P 21/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(7)
INDICATIONS ON ND
Lowest and highest elevations Minimum and maximum elevations encountered within the selected range, are respectively displayed in this square, using the color code of paragraph 1. Note:
The elevations shown on the ND correspond to the terrain included in the selected ND range, ahead of the aircraft. In ARC mode, the elevations are linked with the terrain displayed on the ND. In ROSE mode, the elevations may not represent the lowest and highest terrain currently displayed on the ND. FLAGS AND MESSAGES DISPLAYED ON ND
Ident.: DSC-31-45-00001256.0425001 / 24 FEB 11 Applicable to: ALL
(1)
HDG Flag (red) If the heading data fails, the rose, arc and associated symbols disappear. A HDG flag flashes for 9 s, then remains steady in the upper part of the ND.
(2)
CHECK HDG Flag (amber) For more information: Refer to DSC-31-05-60 Side1/Side2 Discrepancy Messages
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← I to J →
DSC-31-45 P 22/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
(3)
Center Part Messages ‐ The screen displays a MODE CHANGE message in green if there is a discrepancy between the selected mode on the EFIS control panel and the mode sent from the onside FMGC, or while the DMC is preparing a new page for display ‐ The screen displays a RANGE CHANGE message in green if there is a discrepancy between the range selected on the EFIS control panel and the range sent from the onside FMGC. A MODE CHANGE message has priority over a RANGE CHANGE message ‐ The screen displays a MAP NOT AVAIL message in red for several reasons: • The MODE CHANGE or RANGE CHANGE message has been displayed more than 6 s, or • The FMGC has failed, or • The FMGC has delivered an invalid aircraft position. ‐ The screen displays a W/S SET RNG 10 nm message if a predictive windshear alert is triggered and the range is above 10 nm. The message is displayed in the color corresponding to the windshear alert: red for a warning, amber for a caution ‐ The screen displays a W/S CHANGE MODE message if a predictive windshear alert is triggered and the ND is not in ARC or ROSE mode. The message appears in red for a warning, or amber for a caution.
(4)
LOC Flag (red) If LOC data fails, this flag flashes for 9 s, then remains steady.
(5)
G/S Flag (red) If G/S data fails, this flag flashes for 9 s, then remains steady.
(6)
VOR Flag (red) In ROSE VOR mode, when the VOR bearing is not valid, this flag flashes for 9 s, then remains steady.
(7)
VOR 1(2) or ADF 1(2) or DME 1 Flag (red) If a navigation receiver fails, the appropriate one of these flags flashes for 9 s, then remains steady.
(8)
VOR Course Flag If the VOR course fails, a red CRSXXX flag appears. If there is non-computed data (NCD), a blue CRS - - - flag appears.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←J→
DSC-31-45 P 23/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
(9)
Other messages MAP PARTLY DISPLAYED (amber)
:
NAV ACCUR UPGRAD, : or (white) NAV ACCUR DOWNGRAD (amber) SPECIFIC VOR/D : UNAVAIL (amber) BACK-UP NAV (amber) : SET OFFSIDE RNG/MODE (amber)
:
OFFSIDE FM CONTROL : (amber) GPS PRIMARY (white, : boxed white) GPS PRIMARY LOST (amber, boxed white) ↓ (green)
: :
In case of incomplete data transmission between the FMGC (priority criteria) and the DMC, or if the DMC cannot draw the complete MAP. This message is also displayed when a very long leg exists in the flight plan. A leg is considered as “very long” when the starting point (or endpoint) is located at more than 45 ° from the aircraft location (45 ° of longitude or latitude). This DMC limitation results from a compromise between accurate drawing precision and maximum leg length that can be displayed. Signals a change in navigation accuracy.
If the NAVAID, that is tuned for the selected approach or departure, is not available. If the MCDU back-up navigation mode is activated (Refer to DSC-22_10-40-10-A MCDU - MCDU Interface) Displayed on ND 1(2), in case of an FMGC 1(2) failure when the two ND ranges or modes selected on the EFIS control panels are different. If the offside FM supplies the onside ND. This message appears when GPS PRIMARY mode is available, or has been recovered. The pilot can clear this message by pressing the CLR key on the MCDU. This message appears when GPS PRIMARY is not available, and not clearable by pilot action. Overflow arrow, displayed when more than one of the following messages are present at the same time: ‐ NAV ACCUR DOWNGRAD ‐ NAV ACCUR UPGRAD ‐ SPECIF VOR-D UNAVAIL ‐ MAP PARTLY DISPLAYED ‐ SET OFFSIDE RNG/MODE ‐ GPS PRIMARY ‐ GPS PRIMARY LOST
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←J→
DSC-31-45 P 24/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
Note:
For information about the TCAS messages: Refer to DSC-34-80-20 TCAS Messages.
(10) OFST R(L) XX message (yellow) The screen displays this message, when a temporary or an offset flight plan is entered. The offset value is given in NM. Note:
For information about the TCAS messages: Refer to DSC-34-80-20 TCAS Messages.
(11) PRED W/S flag (amber) The WINDSHEAR sw on the weather radar panel is set to AUTO, and a Predictive Windshear System fault is detected. This message appears on ground, or when flaps and slats are extended. It is associated with a single chime. The radar image remains available, provided that the fault does not affect the radar mode. (12) GPS message (green) This message shows the full runway name of the selected approach. It is displayed, when the flight crew selects a GPS approach. (13) CHECK EWD, CHECK CAPT (F/O) PFD, CHECK SD, CHECK CAPT (F/O) ND (amber) For more information: Refer to DSC-31-05-60 Feedback Messages
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←J
DSC-31-45 P 25/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-45 P 26/26 18 SEP 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EFIS CONTROLS
FLIGHT CREW OPERATING MANUAL
EFIS CONTROL PANEL Ident.: DSC-31-50-00001257.0006001 / 15 FEB 11 Applicable to: ALL
(1)
Barometer Reference Display Window Range : 745 hPa to 1 100 hPa.
(2)
Barometer Reference Selector a. Outer ring Note:
:
For selection of the units for the barometer reference-either, hectoPascals (HPA) or inches of mercury (in Hg).
The unit selected does not appear on the PFD.
b. Inner knob
:
For selection of the reference value displayed in the barometer reference display window and on the PFD below the altitude scale. At FCU initialization, the window displays 1 013 or 29.92, depending on the unit selected.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-31-50 P 1/4 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EFIS CONTROLS
FLIGHT CREW OPERATING MANUAL
‐ Pulling the knob selects the standard BARO reference setting. The PFD then displays “STD.” (Rotating the knob has no effect.) ‐ Pushing the knob from the STD position makes the last selected QFE or QNH BARO setting available. ‐ Pushing the knob again changes from QNH to QFE or vice versa. The window displays “QNH” or “QFE” according to the pilot selection. Note:
QFE option is a pin program installed on the FMGC. The FMGC operates using the selected pin program (QNH or QFE), independently of the BARO reference setting selected on the EFIS CTL panel.
(3)
FD Pushbutton Pushing this button removes the FD bars from the associated PFD (or removes the flight path director symbol if the TRK FPA reference is selected). The pushbutton light goes out. Pushing it again restores the FD bars (or the FPD symbol) and the green pushbutton light comes on.
(4)
LS Pushbutton Pushing this button displays the localizer and glide slope scales on the PFD. Deviation symbols appear if there is a valid ILS signal. The green pushbutton light comes on.
(5)
Mode Select Switch This switch selects a navigation display for the onside ND.
(6)
Range Select Switch This switch selects a range scale for the onside ND. Note:
If the mode or the range data fails, the default selection is the ROSE NAV mode and 80 nm range.
(7)
ADF-VOR Select Switches These switches select ADF or VOR bearing pointers and DME distance on the onside ND, as well as the corresponding NAVAID data characteristics in any mode except PLAN mode.
(8)
Optional Data Display Pushbutton Pushing this button displays optional data in addition to the data permanently displayed in PLAN, ARC, or ROSE NAV modes. The green pushbutton light comes on. Only one option can be activated at a time.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-31-50 P 2/4 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EFIS CONTROLS
FLIGHT CREW OPERATING MANUAL
OTHER EFIS CONTROLS Ident.: DSC-31-50-00001258.0002001 / 15 FEB 11 Applicable to: ALL
(1)
OFF/BRT knobs • These knobs turn the PFD and ND display units on and off, and control their brightness. • The display brightness adjusts automatically for changing light conditions, and is also adjusted manually. PFD Brightness Control Knob Rotating this knob all the way counterclockwise switches off the PFD. In this case, the PFD image is automatically displayed on the NDU, but the pilot may recover the ND by means of the PFD-ND XFR pushbutton . ND Brightness Control Knob The outer knob controls the brightness of both the weather radar image and EGPWS terrain display. The inner knob controls the general brightness of the ND symbols. Rotating this knob all the way counterclockwise switches off the NDU.
(2)
PFD/ND Pushbutton Pushing this button interchanges the PFD and the ND.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
DSC-31-50 P 3/4 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
EFIS CONTROLS
FLIGHT CREW OPERATING MANUAL
If the PFDU fails, the PFD automatically transfers to the NDU. CHRONOMETER Ident.: DSC-31-50-00001259.0001001 / 15 FEB 11 Applicable to: ALL
(1)
CHRONO Pushbutton Pushing this button displays chronometer time on the onside ND. Pushing it again freezes the displayed value. Pushing it a third time resets the chronometer, and the chronometer time disappears from the display.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← B to C
DSC-31-50 P 4/4 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
CLOCK - GENERAL
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-31-55-10-00001260.0002001 / 07 FEB 11 Applicable to: ALL
A fully independent clock is on the right side of the control panel. It sends time to the centralized fault data interface unit, the flight data interface unit, and the flight management and guidance computer. The clock has two electrical supplies, one of which is a direct connection to the aircraft battery hot bus. The clock performs four functions : ‐ It displays “UTC” (GMT) time in hours, minutes and seconds on the center counter. ‐ It displays elapsed time (ET) (from engine startup) in hours and minutes on the lower counter. ‐ It drives the chronometer (CHR), which measures a time interval (from the pushing of the CHRONO button) in minutes and seconds. ‐ It can replace the UTC with the date.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-31-55-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
CLOCK - GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-55-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
CLOCK - CONTROLS AND INDICATORS
GENERAL Ident.: DSC-31-55-20-00001261.0003001 / 16 MAR 11 Applicable to: ALL
(1)
UTC (GMT) counter This counter displays the present time in 24 h format from 0 to 23 h 59 min 59 s.
(2)
Elapsed Time (ET) This counter registers the elapsed time up to 99 h and 59 min.
(3)
Chrono (CHR) counter This Counter registers elapsed time from 0 to 99 min 59 s. It is controlled by the CHR pushbutton.
(4)
CHR pushbutton First push : starts the CHR counter Second push : stops the CHR counter, keeps the display at its last indication.
(5)
Reset (RST) pushbutton When pressed, the CHR counter restarts from 0 if the chrono is running.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-31-55-20 P 1/4 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
CLOCK - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
(6)
ET selector “RUN” “STP” spring loaded “RST” Note:
(7)
the ET counter starts the ET counter stops counting the ET counter is blanked. The selector returns to its STP position when the selector is released.
A cumulative elapsed time can be realized by alternatively setting this switch in “RUN” and “STP” position.
DATE/SET pushbutton First push : sets the clock to date mode. The UTC time display is replaced by the date (day month year). Second push : sets the clock to time mode. The date display disappears. Note:
(8)
: : :
in order to select the date mode, the UTC selector must be set on “GPS” or “INT” position.
UTC selector “GPS” : Time (or date, if selected) is displayed, and this data is synchronized on GPS information. Note:
“INT” : Note:
“SET” :
‐ If the signal between the GPS and the clock is not detected, dashes are displayed. Only the “INT” and “SET” positions are then available. ‐ If the signal is detected, but GPS data is invalid, the clock automatically runs on its internal time. ‐ The clock will automatically resynchronize on the GPS information, as soon as the GPS data becomes available. Internal time (or date, if selected) is displayed. ‐ The clock’s internal time is initialized with the latest valid GPS information. ‐ If there is no valid GPS information at power up, the internal time will be 00:00:00, until the clock is initialized. Allows the internal time and date to be initialized. INTERNAL TIME AND DATE INITIALIZATION
Ident.: DSC-31-55-20-00007126.0001001 / 07 FEB 11 Applicable to: ALL
Set the UTC selector on “SET”. The minute digits flash, and the seconds’ digits are blank. To increase data, turn the DATE/SET button clockwise. To decrease data, turn the DATE/SET button counterclockwise. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← A to B →
DSC-31-55-20 P 2/4 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
CLOCK - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
‐ ‐ ‐ ‐
First, push on DATE/SET Second, push on DATE/SET Third, push on DATE/SET Fourth, push on DATE/SET
: : : :
To set the hour. To set the year. To set the month. To set the day.
Switch the UTC selector to the “INT” position, and the clock starts with the seconds’ digits at 00. Note:
This process must be completed in less than one minute. Otherwise, it will be necessary to reset the CFDS in order to synchronize the lower ECAM time display with the cockpit clock display. Resetting the CFDS is a maintenance operation.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-31-55-20 P 3/4 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
CLOCK - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-55-20 P 4/4 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLT RECORDERS - FLIGHT DATA RECORDING SYSTEM
DESCRIPTION Ident.: DSC-31-60-10-00001262.0002001 / 20 DEC 10 Applicable to: ALL
The Flight Data Recording System, which records the mandatory parameters, consists of the following components: ‐ A Flight Data Interface and Management Unit (FDIMU) ‐ A Digital Flight Data Recorder (DFDR) ‐ A three-axis Linear Accelerometer (LA) The FDIMU collects and processes parameters from the SDACs, DMCs, FWCs, FCDCs, BSCU, the DFDR event pushbutton, the GND CTL pushbutton and the Clock. It stores the mandatory flight parameters in the DFDR. The DFDR can store the last 25 h data, at least. It stores this data on a fireproof and shockproof device. An underwater locator beacon is attached to the DFDR. The linear accelerometer measures the acceleration of the aircraft along each of the three axes. The QAR is an operational recorder that stores the same data as the DFDR. However the QAR is more accessible for the maintenance crew.
The recording system is automatically active : ‐ On the ground, during the first five minutes after the aircraft electric network is energized. ‐ On the ground, after the first engine start. ‐ In flight (whether the engines are running or not). On the ground, the recording system stops automatically five minutes after the second engine shuts down. On the ground, the crew can start the recording system manually by pressing the GND CTL pushbutton.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-31-60-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLT RECORDERS - FLIGHT DATA RECORDING SYSTEM
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-60-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLT RECORDERS - CONTROLS AND INDICATORS
OVERHEAD PANEL Ident.: DSC-31-60-20-00001263.0001001 / 20 DEC 10 Applicable to: ALL
(1)
GND CTL pushbutton (springloaded) ON : The Cockpit Voice Recorder (CVR) and the Flight Data Recorders are active. The ON light is on. AUTO : The Cockpit Voice Recorder (CVR) and the Flight Data Recorders are active, according to the logic. The system automatically switches from ON to AUTO at the first engine start, and also in case of an electrical transient. PEDESTAL
Ident.: DSC-31-60-20-00001264.0001001 / 22 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-31-60-20 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
FLT RECORDERS - CONTROLS AND INDICATORS
DFDR EVENT pushbutton Pressing this button (briefly) sets an event mark on the Flight Data records.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-31-60-20 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLT RECORDERS - AIRCRAFT INTEGRATED DATA SYSTEM
DESCRIPTION Ident.: DSC-31-60-30-00005369.0002001 / 20 DEC 10 Applicable to: ALL
The AIDS is used to monitor various aircraft system parameters in order to make maintenance easier and to allow formulating operational recommendations. The AIDS can generate system reports. The Airbus Standard Reports are preprogrammed reports available at aircraft delivery. The operator can create its own reports. The AIDS uses the Flight Data Interface and Management Unit (FDIMU) to acquire the relevant aircraft system parameters. The FDIMU is connected to the rest of the AIDS as shown below. The system may be programmed using the MCDUs. The crew can select any report to be displayed on the MCDUs. The Printer prints the flight phase programmed reports or any report selected on the MCDU. This printing may be automatic or in response to the AIDS PRINT pushbutton. The AIDS may send automatic reports via ACARS . An optional Digital Recorder may be installed to extend the recording capacity.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-31-60-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FLT RECORDERS - AIRCRAFT INTEGRATED DATA SYSTEM
CONTROLS ON PEDESTAL Ident.: DSC-31-60-30-00005370.0001001 / 20 DEC 10 Applicable to: ALL
(1)
AIDS PRINT pushbutton Pushing this pushbutton causes the immediate printing of a specific report, depending on the flight phase. The crew may then use the MCDU to select another report for immediate printing.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
DSC-31-60-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-31-70-00001266.0010001 / 30 MAR 12 Applicable to: ALL
E/WD: FAILURE TITLE conditions
SDAC 1 + 2 FAULT DMC 1 (2) FAULT DMC 3 FAULT SDAC 1 (2) FAULT FWC 1 (2) FAULT FWC 1 + 2 FAULT DFDR FAULT RECORDER SYS FAULT OEB/FWC DISCREPANCY
AURAL WARNING
MASTER LIGHT
SINGLE CHIME
MASTER CAUT
SD PAGE CALLED
LOCAL WARNINGS
FLT PHASE INHIB 4, 5, 7, 8 3, 4, 5(1), 7, 8 3, 4, 5, 7, 8
NIL
NIL
NIL
NIL 3, 4, 5, 7, 8
SINGLE FWC 1 and FWC 2 do not have the CHIME same OEBs listed in their OEB reminder database. (1) Inhibited only during first 15 s of Flight Phase 5.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
NIL
MASTER CAUT
A
3 to 8
DSC-31-70 P 1/2 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-70 P 2/2 03 APR 12
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-31-75-00001267.0002001 / 20 DEC 10 Applicable to: ALL
NORM
DU
DMC FWC SDAC ECP FDIU/QAR (1)
CAPT PFD CAPT ND F/O PFD F/O ND UPPER ECAM DU LOWER ECAM DU DMC 1 DMC 2 DMC 3 FWC 1 FWC 2 SDAC 1 SDAC 2 ECP
AC
AC ESS X
EMER ELEC DC ESS
HOT
SHED AC2 AC2 X AC2 X AC2 AC1
X (1) X
AC2 X AC2 X AC2
CLOCK in case of EIS DMC switching to CAPT/3, with AC BUS 1 failed.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DC
A
X
X
DSC-31-75 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS INDICATING / RECORDING SYSTEMS A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-31-75 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR
Intentionally left blank
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-32-PLP PRELIMINARY PAGES TABLE OF CONTENTS
DSC-32-10 Gears and Doors DSC-32-10-10 Description GENERAL................................................................................................................................................................ A MAIN GEAR.............................................................................................................................................................B NOSE GEAR........................................................................................................................................................... C DRAWINGS............................................................................................................................................................. D Operation of Gear and Doors..................................................................................................................................E
DSC-32-10-20 Landing Gear System/Interface LGCIUs.....................................................................................................................................................................A Proximity Detector Output Signals.......................................................................................................................... B PROXIMITY DETECTOR OUTPUT SIGNALS (CONT'D)...................................................................................... C
DSC-32-10-30 Interactions between Landing Gear and Aircraft Systems GENERAL................................................................................................................................................................ A Proximity Detectors on Shock Absorbers................................................................................................................B PROXIMITY DETECTORS ON UPLOCKS.............................................................................................................C DOORS PROX DET................................................................................................................................................D PROXIMITY DETECTORS ON DOWNLOCKS.......................................................................................................E PROXIMITY DETECTORS ON CARGO DOORS...................................................................................................F PROXIMITY DETECTORS ON FLAP ATTACHMENTS.........................................................................................G
DSC-32-10-40 Controls and Indicators LANDING GEAR INDICATOR PANEL....................................................................................................................A Landing Gear Selector Lever.................................................................................................................................. B Emergency Extension..............................................................................................................................................C ECAM Wheel Page................................................................................................................................................. D
DSC-32-10-50 Warnings and Cautions Warnings and Cautions........................................................................................................................................... A
DSC-32-10-60 Electrical Supply BUS EQUIPMENT LIST.......................................................................................................................................... A
DSC-32-20 Nose Wheel Steering DSC-32-20-10 Description Description............................................................................................................................................................... A ARCHITECTURE..................................................................................................................................................... B
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-32-PLP-TOC P 1/2 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-32-20-20 Controls and Indicators SIDE CONSOLES....................................................................................................................................................A CENTER INSTRUMENT PANEL.............................................................................................................................B ECAM WHEEL PAGE............................................................................................................................................. C
DSC-32-20-30 Warnings and Cautions Warnings and Cautions........................................................................................................................................... A
DSC-32-20-40 Electrical Supply BUS EQUIPMENT LIST.......................................................................................................................................... A
DSC-32-30 Brakes and Antiskid DSC-32-30-10 Description General.....................................................................................................................................................................A Anti-Skid System......................................................................................................................................................B ANTI-SKID PRINCIPLE........................................................................................................................................... C Auto Brake - General.............................................................................................................................................. D Operation - General.................................................................................................................................................E BRAKING SCHEMATIC...........................................................................................................................................F
DSC-32-30-20 Controls and Indicators CENTER INSTRUMENT PANEL.............................................................................................................................A Auto BRK Panel.......................................................................................................................................................B BRAKE FANS ................................................................................................................................................ C PEDESTAL.............................................................................................................................................................. D ECAM WHEEL PAGE............................................................................................................................................. E
DSC-32-30-30 Warnings and Cautions Warnings and Cautions........................................................................................................................................... A
DSC-32-30-40 Electrical Supply BUS EQUIPMENT LIST.......................................................................................................................................... A
DSC-32-40 Tire Pressure Indicating System DSC-32-40-10 Description Description............................................................................................................................................................... A
DSC-32-40-20 Controls and Indicators WHEEL SD Page.................................................................................................................................................... A
DSC-32-40-40 Electrical Supply BUS EQUIPMENT LIST.......................................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-32-PLP-TOC P 2/2 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - DESCRIPTION
GENERAL Ident.: DSC-32-10-10-00001268.0001001 / 10 DEC 09 Applicable to: ALL
The landing gear consists of : ‐ two main gear that retract inboard, ‐ a nose gear that retracts forward. Doors enclose the landing gear bays. Gear and doors are electrically controlled and hydraulically operated. The doors, which are fitted to the landing gear struts, are operated mechanically by the gear and close at the end of gear retraction. All gear doors open while the gear is retracting or extending. Two Landing Gear Control and Interface Units (LGCIUs) control the extension and retraction of the gear and the operation of the doors. They also supply information about the landing gear to ECAM for display, and send signals indicating whether the aircraft is in flight or on the ground to other aircraft systems. A hand crank on the center pedestal allows the flight crew to extend the landing gear if the aircraft loses hydraulic systems or electrical power. MAIN GEAR Ident.: DSC-32-10-10-00001269.0001001 / 10 DEC 09 Applicable to: ALL
Each main gear has twin wheels and an oleopneumatic shock absorber. Each main wheel has an antiskid brake. NOSE GEAR Ident.: DSC-32-10-10-00001270.0001001 / 10 DEC 09 Applicable to: ALL
The two-wheeled nose gear has an oleopneumatic shock strut and a nose wheel steering system.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to C
DSC-32-10-10 P 1/6 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - DESCRIPTION
DRAWINGS Ident.: DSC-32-10-10-00001271.0001001 / 17 MAR 11 Applicable to: ALL
MAIN LANDING GEAR
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D→
DSC-32-10-10 P 2/6 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
GEARS AND DOORS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
NOSE GEAR
OPERATION OF GEAR AND DOORS Ident.: DSC-32-10-10-A-NG00089 Applicable to: ALL Ident.: DSC-32-10-10-A-00001272.0001001 / 10 DEC 09
NORMAL OPERATION The flight crew normally operates the landing gear by means of the lever on the center instrument panel. The LGCIUs control the sequencing of gear and doors electrically. One LGCIU controls one complete gear cycle, then switches over automatically to the other LGCIU at the completion of the retraction cycle. It also switches over in case of failure. The green hydraulic system actuates all gear and doors. When the aircraft is flying faster than 260 kt, a safety valve automatically cuts off hydraulic supply to the landing gear system. Below 260 kt, the hydraulic supply remains cut off as long as the landing gear lever is up.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← D to E →
DSC-32-10-10 P 3/6 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - DESCRIPTION
Ident.: DSC-32-10-10-A-00001273.0001001 / 10 DEC 09
EMERGENCY EXTENSION If the normal system fails to extend the gear hydraulically, the flight crew can use a crank to extend it mechanically. When a crew member turns the crank, it : ‐ isolates the landing gear hydraulics from the green hydraulic system, ‐ unlocks the landing gear doors and the main and nose main gear, ‐ allows gravity to drop the gear into the extended position. Locking springs help the crew to crank the main gear into the locked condition, and aerodynamic forces assist in the locking of the nose gear. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-32-10-10 P 4/6 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - DESCRIPTION
The gear doors remain open. The flight crew can reset the emergency extension system in flight after using it for training (if green hydraulic pressure is available).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E
DSC-32-10-10 P 5/6 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
GEARS AND DOORS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-32-10-10 P 6/6 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - LANDING GEAR SYSTEM/INTERFACE
LGCIUS Ident.: DSC-32-10-20-A-NG00090 Applicable to: ALL Ident.: DSC-32-10-20-A-00001274.0001001 / 10 DEC 09
GENERAL The LGCIUs receive position information from the landing gear, cargo door, and landing flap systems. Ident.: DSC-32-10-20-A-00001275.0001001 / 10 DEC 09
LANDING GEAR The LGCIUs receive the following information about the landing gear from proximity detectors : ‐ gear locked down or up, ‐ shock absorbers compressed or extended, ‐ landing gear door open or closed. Failure of a proximity detector : ‐ The LGCIU detects any electrical failure in a proximity detector, and signals the associated output to the flight position (shock absorber not compressed or landing gear uplocked). The other LGCIU then automatically takes over control of the landing gear operation. ‐ In case of mechanical failure, the LGCIU does not modify the associated output. The effect that such a failure has on the system depends upon which condition is signalled incorrectly. Electrical failure of an LGCIU : ‐ The other (healthy) LGCIU takes control of the landing gear. ‐ The system does not force the outputs of the failed LGCIU to the safe (flight) condition. • Some users will see “flight” condition. • Some users will see “ground” condition. Ident.: DSC-32-10-20-A-00001276.0001001 / 10 DEC 09
CARGO DOORS Sensors send to the LGCIUs the position of the following components : ‐ manuel selector valves, ‐ locking shaft, ‐ locking handle, ‐ safety shaft, ‐ door sills.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-32-10-20 P 1/4 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - LANDING GEAR SYSTEM/INTERFACE
The LGCIUs detect electrical failures only in certain proximity switches in the cargo door system : ‐ locking shaft, ‐ locking handle, ‐ safety shaft. When an LGCIU makes such a detection, it indicates the NON LOCKED condition for that component. Ident.: DSC-32-10-20-A-00001277.0001001 / 10 DEC 09
FLAPS The LGCIUs process the signals from four flap disconnect proximity switches, then send them to the Slat/Flap Control Computers (SFCCs). The LGCIUs do not monitor failures in the SFCC system.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-32-10-20 P 2/4 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - LANDING GEAR SYSTEM/INTERFACE
PROXIMITY DETECTOR OUTPUT SIGNALS Ident.: DSC-32-10-20-00001278.0001001 / 22 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
DSC-32-10-20 P 3/4 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - LANDING GEAR SYSTEM/INTERFACE
PROXIMITY DETECTOR OUTPUT SIGNALS (CONT'D) Ident.: DSC-32-10-20-00001279.0001001 / 10 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-32-10-20 P 4/4 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
GEARS AND DOORS - INTERACTIONS BETWEEN LANDING GEAR AND AIRCRAFT SYSTEMS
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-32-10-30-00001285.0001001 / 10 DEC 09 Applicable to: ALL
The following tables present the operational effects of the proximity detectors on aircraft systems. How to read the tables : SYSTEM SERVICE INTERPHONE SFCC 1(2)
LGCIU 1 6 5
LGCIU 2 6 (5)
A/C IN FLT ........ ........
A/C ON GROUND ........ ........
The above lines mean that the service interphone receives the output n° 6 from both LGCIUs, while SFCC 1 receive the output 5 from LGCIU 1 and SFCC 2 the output 5 from LGCIU 2. The two additional columns give the system functioning when the aircraft is in flight and on the ground. PROXIMITY DETECTORS ON SHOCK ABSORBERS Ident.: DSC-32-10-30-00001286.0001001 / 17 MAR 11 Applicable to: ALL
SYSTEM STROBE lts LOGO lts AIRSTAIRS
GENERAL
LGCIU 1 LGCIU 2 A/C IN FLT OUTPUT OUTPUT 5 On when AUTO selected 5 Off when flaps retracted 3
CARGO DOOR(5) WATER FILLING
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
1 5 5
A to B →
Control inhibited(1) normal control not available Preselect water servicing inhibited
A/C ON GRND Off when AUTO selected On Control not inhibited(2) normal control available
Preselect water servicing available Continued on the following page
DSC-32-10-30 P 1/10 25 NOV 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - INTERACTIONS BETWEEN LANDING GEAR AND AIRCRAFT SYSTEMS Continued from the previous page
SYSTEM
AVNCS COOLING
AIR COND
GRND COOLING FWD CARGO VENT CAB PRESS
LGCIU 1 LGCIU 2 OUTPUT OUTPUT
5
5
1 3
1 3 5
5
PACK 1(2) TEMP CONTROL
• Skin temp. < 35 °C : The system is in closed conf.(1) • Skin temp. > 35 °C : The system is in intermediate conf.(1) Inhibited(1) Extract fan stopped when ΔP > 1 PSI Climb mode active(4)
5
3 (1)
Pack air inlet flaps opened. In case of oil low press, automatic shutdown is delayed by 15.5 s
APU AUTO SHUTDOWN
APU
A/C IN FLT
5 Speed is controlled at 101 %
APU SPEED CONTROL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
A/C ON GRND • Skin temp. < 5 °C : The system is in closed conf.(2) • Skin temp. > 5 °C : The system is in open conf.(2)
Not inhibited(2) Extract fan on ‐ Prepressurization active before TO (3) ‐ Depressurization active after LDG (3) Pack air inlet flap fully closed at TO and LDG In case of oil low press, the automatic shutdown is delayed by: • 15.5 s if the oil temp < -4 °C • 0.05 s if oil temp > -4 °C Speed is controlled at 99 % (101 % for ENG start or when ambient temp ≥ 30 °C) Continued on the following page
DSC-32-10-30 P 2/10 25 NOV 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
GEARS AND DOORS - INTERACTIONS BETWEEN LANDING GEAR AND AIRCRAFT SYSTEMS
FLIGHT CREW OPERATING MANUAL
Continued from the previous page
SYSTEM SERVICE INTERPHONE PUBLIC ADDRESS ADIRU and AVIONICS ground warning FLT INTERPHONE
COMMUNICATIONS
COCKPIT CALL LIGHT ACARS (ACARS MU or ATSU)
LGCIU 1 LGCIU 2 OUTPUT OUTPUT
A/C ON GRND
6
6
Inhibited(6)
Available(7)
1 3
1 3
P.A. increased level(6)
P.A. low level(7)
1 3
1 3
External horn and light inhibited(6)
External horn and light not inhibited(7)
9
Communication with ground mechanic inhibited
Communication with ground mechanic available
9
Inhibited
Not inhibited
7
Available
Available
Runs(6)
CVR
1 3 7
CVR
DC generation
ELEC
A/C IN FLT
1 3
Stops : (7) 5 min after second engine shutdown
5
5
GALLEY supply
5
EIS
EIS
5
FIRE
APU
5
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Runs : (7) ‐ During the first 5 min following energization ‐ With at least one engine running
←B→
• ERASE function inhibited • No low frequency signal in the loudspeakers if test performed
• ERASE function not inhibited • Low frequency signal in the loudspeakers if test performed
APU start on batteries No APU start delay only, is delayed by 45 s when on batteries only Main galley not supplied Main galley supplied when when APU GEN APU GEN only is supplying only is supplying Display test inhibited when ANN LT Display test not inhibited TEST is selected No APU fire automatic Automatic extinguishing extinguishing not inhibited Continued on the following page
DSC-32-10-30 P 3/10 25 NOV 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
GEARS AND DOORS - INTERACTIONS BETWEEN LANDING GEAR AND AIRCRAFT SYSTEMS
FLIGHT CREW OPERATING MANUAL
Continued from the previous page
SYSTEM
FLT CTL
SFCC 1(2)
LGCIU 1 LGCIU 2 OUTPUT OUTPUT
5
(5)
A/C IN FLT
• For SFCC 1(2): • For SFCC 1(2): Slats alpha/speed lock Slats alpha/speed lock function active function active if speed > • For SFCC(2): 60 kt No flaps movement • For SFCC (2): inhibition if the cargo Flaps movement door is opened inhibition if cargo door is opened Runs(6)
FLT INST
FUEL
• DFDR • QAR
1 3 7
FQI
5
A/C ON GRND
1 3
Runs: (7) • During the first 5 min following energization • With one engine running Stops: (7) 5 min after second engine shut down
FQI uses flight attitude correction due to wing bending
FQI uses ground attitude correction Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
DSC-32-10-30 P 4/10 25 NOV 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
GEARS AND DOORS - INTERACTIONS BETWEEN LANDING GEAR AND AIRCRAFT SYSTEMS
FLIGHT CREW OPERATING MANUAL
Continued from the previous page
SYSTEM
LGCIU 1 LGCIU 2 OUTPUT OUTPUT
BLUE and GREEN pumps
1 3
BLUE pump
7
BLUE and YELLOW pumps
1 3
HYD
PTU
7
A/C IN FLT
A/C ON GRND
Blue or green pump "FAULT" light not inhibited when related pump is stopped(6) Runs when electrical power is available Blue or yellow pump "FAULT" light not inhibited when related pump is stopped(6)
Blue or green pump "FAULT" light inhibited when related pump is stopped(7) Runs when at least one engine is running Blue or yellow pump "FAULT" light inhibited when related pump is stopped(8)
PTU runs if green/yellow diff. press > 500 PSI and • Both MASTER LEVERS are at OFF or • Both MASTER LEVERS are at ON or PTU runs if green/yellow • Nose wheel steering is diff. press > 500 PSI not in towing position with parking brake released. PTU is inhibited during the use of the cargo door hand pump and for 40 s after its use.
ICE RAIN PROT
• CAPT, (F/O), ((STBY)) • With engines stopped: no pitots and CAPT, heating(8) (F/O) windows : high • With at least one engine heating level applied running: • All other probes and • CAPT, (F/O), ((STBY)) windows are heated(6) pitots and CAPT, (F/O) windows are heated at low level(8)
CAPT, (F/O), ((STBY)) probes and CAPT, (F/O) windows heating
4, (2) ((8))
4, (2) ((8))
WING ANTI ICE
3
1
Wing anti ice valves open when the WING ANTI ICE pb is at ON(6)
1 3
1 3
Not inhibited(6)
9
High heating level is applied
RAIN REPELLENT DRAIN MAST(10)
Wing anti ice valves open for 30 s when the WING ANTI ICE pb is at ON(8) Inhibited if engines are stopped(7) Low heating level is applied
Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
DSC-32-10-30 P 5/10 25 NOV 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - INTERACTIONS BETWEEN LANDING GEAR AND AIRCRAFT SYSTEMS Continued from the previous page
SYSTEM
LANDING GEAR
NAVIGATION
POWER PLANT
(1) (2) (3) (4) (5) (6) (7) (8) (9) (10)
L/G SAFETY VALVE L/G control
LGCIU 1 LGCIU 2 OUTPUT OUTPUT 6 10
TIRE PRESS
5
STAND BY ALTI
5
ATC 1(2)
3
ADIRU 1(10)
7
FADEC 1(2)
10
(1)
1 3 8
(1) (3) (8)
1 3 8
(1) (3) (8)
A/C IN FLT
A/C ON GRND
Safety valve closes if Safety valve opened aircraft speed > 260 kt (9) Retraction not inhibited Retraction inhibited(9) "TYRE LO PRESS" "TYRE LO PRESS" warning threshold warning threshold set to its flight level set to its ground level VIBRATION Vibration function inhibited function active ATC 1(2) available ATC 1(2) inhibited in AUTO mode in AUTO mode No external horn when ADIRU supplied External horn not inhibited from batteries only On ENG 1(2): (6) • Reverse inhibited • No automatic start abort • FADEC always supplied • FLEX not available • If installed, BUMP not selectable
On ENG 1(2): (8) • Reverse available • Automatic start abort available • 5 min after eng-shut down FADEC 1(2) no more supplied • FLEX available • If installed, BUMP selectable
Modulated idle and approach idle are available(6)
Modulated idle only available(7)
When either LGCIU indicates flight. When both LGCIU indicate ground. When either LGCIU indicates ground. When both LGCIU indicate flight. Valid from MSN 44. When either output indicates flight. When all outputs indicate ground. When both outputs indicate ground. One valid output is sufficient. Valid from MSN 22.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-32-10-30 P 6/10 25 NOV 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
GEARS AND DOORS - INTERACTIONS BETWEEN LANDING GEAR AND AIRCRAFT SYSTEMS
FLIGHT CREW OPERATING MANUAL
PROXIMITY DETECTORS ON UPLOCKS Ident.: DSC-32-10-30-00001287.0002001 / 15 NOV 11 Applicable to: ALL
LGCIU 1 LGCIU 2 OUTPUT OUTPUT
SYSTEM L/G control
LANDING GEAR
ECAM WHEEL page L/G indicator panel
(1) (2)
19
19
16 17 18 16 17 18
16 17 18
L/G UPLOCKED
L/G NOT UPLOCKED
If UP selected :(1) L/G doors will close If UP selected :(2) L/G uplocked indications
If UP selected :(1) L/G doors will not close If UP selected :(2) L/G in transit indications
If UP selected :(2) no indication
If UP selected :(2) "UNLK" red indications
One valid output is sufficient. When all outputs indicate the same position.
DOORS PROX DET Ident.: DSC-32-10-30-00001288.0001001 / 15 NOV 11 Applicable to: ALL
LANDING GEAR
(1)
SYSTEM
LGCIU 1 OUTPUT
L/G control
24
ECAM WHEEL page
20 21 22 23
LGCIU 2 DOORS FULLY OPENED DOORS CLOSED OUTPUT L/G extension or retraction L/G extension or retraction 24 possible (1) inhibited (1) 20 Doors fully opened Doors closed indication 21 indication 22 23
One valid output is sufficient.
PROXIMITY DETECTORS ON DOWNLOCKS Ident.: DSC-32-10-30-00001289.0001001 / 17 MAR 11 Applicable to: ALL
SYSTEM
GEN
TAXI/T.O lights
COMM
SIGNS
FLT INST
WBS
LGCIU 1 OUTPUT
LGCIU 2 OUTPUT
L/G DOWNLOCKED
L/G NOT DOWNLOCKED
15
lights not inhibited
lights inhibited
12
12
15
15
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C to E →
"NO SMOKING" and "EXIT" signs on when AUTO selected (1) active (3)
"NO SMOKING" and EXIT" signs inhibited when AUTO selected (2) inhibited (4) Continued on the following page
DSC-32-10-30 P 7/10 25 NOV 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
GEARS AND DOORS - INTERACTIONS BETWEEN LANDING GEAR AND AIRCRAFT SYSTEMS
FLIGHT CREW OPERATING MANUAL
Continued from the previous page
SYSTEM
FMGS
LANDING GEAR
(1) (2) (3) (4) (5) (6)
LGCIU 2 OUTPUT
L/G DOWNLOCKED
L/G NOT DOWNLOCKED
VLE indication displayed on PFD 1(2) If DOWN selected : (5) L/G doors will close If DOWN selected : (6) L/G down indications
If DOWN selected : (5) L/G doors will not close If DOWN selected : (6) L/G in transit indications
If DOWN selected : (6) L/G down indications
If DOWN selected : (6) L/G in transit indications
FAC 1(2)
12
12
L/G control
14
14
ECAM WHEEL page
11 13 15 11 13 15
11 13 15
15
15
BSCU test operative (1)
BSCU test inhibited (1)
13
Cooling available when ON selected
Cooling inhibited when ON selected
"TOO LOW-FLAPS" or "TOO LOW TERRAIN" warning operative
"TOO LOW-GEAR" or "TOO LOW TERRAIN" warning operative
L/G INDIC panel BRAKING STEERING BRAKES COOLING
NAV
LGCIU 1 OUTPUT
GPWS
13
no VLE indication
When either output indicates DOWNLOCK. When both outputs indicate NOT DOWNLOCK. When both outputs indicate DOWNLOCK. When either output indicates NOT DOWNLOCK. One valid output is sufficient. When all outputs indicate the same position.
PROXIMITY DETECTORS ON CARGO DOORS Ident.: DSC-32-10-30-00001290.0001001 / 15 NOV 11 Applicable to: ALL
LOCKING HANDLE OR SHAFT, DOOR SILLS SYSTEM
CRG DOORS
ECAM DOOR PAGE CARGO DOOR OPERATION
LGCIU 1 LGCIU 2 OUTPUT OUTPUT
LOCKED Forward (aft) door symbol appears green
30 (31) 34 (35) 36 (37)
Forward (aft) door normal opening inhibition Forward (aft) door normal operation possible
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← E to F →
UNLOCKED Forward (aft) door symbol appears amber, associated with "CARGO" amber. Forward (aft) door normal opening possible Forward (aft) door normal operation inhibited
DSC-32-10-30 P 8/10 25 NOV 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
GEARS AND DOORS - INTERACTIONS BETWEEN LANDING GEAR AND AIRCRAFT SYSTEMS
FLIGHT CREW OPERATING MANUAL
MANUAL SELECTOR VALVE SYSTEM
CRG DOORS
LGCIU 1 LGCIU 2 OUTPUT OUTPUT
CARGO DOOR OPERATION
32 (33)
CLOSE
OPEN
Forward (aft) door normal opening inhibition
Forward (aft) door normal opening possible
PROXIMITY DETECTORS ON FLAP ATTACHMENTS Ident.: DSC-32-10-30-00001291.0001001 / 15 NOV 11 Applicable to: ALL
LGCIU 1 LGCIU 2 OUTPUT OUTPUT 28 28 SFCC FLT CTL (29) (29) When at least one SFCC detects normal operation When both SFCCs detect attachment failure SYSTEM
(1) (2)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← F to G
FLAP ATTACHMENT L(R) FLAPS normal operation (1)
FLAP ATTACHMENT FAILURE "FLAPS LOCKED” warning (2)
DSC-32-10-30 P 9/10 25 NOV 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - INTERACTIONS BETWEEN LANDING GEAR AND AIRCRAFT SYSTEMS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-32-10-30 P 10/10 25 NOV 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
GEARS AND DOORS - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
LANDING GEAR INDICATOR PANEL Ident.: DSC-32-10-40-00001292.0001001 / 14 NOV 11 Applicable to: ALL
This panel is connected to LGCIU1, which receives signals from proximity detectors. UNLK: comes on red if the gear is not locked in the selected position. ▿ : comes on green if the gear is locked down. Note:
This panel is connected to the LGCIU1 only, therefore, the lights on the LDG GEAR indicator panel come on as long as the LGCIU1 is electrically supplied. If one UNLK indication remains on, the landing gear position can be confirmed using the WHEEL SD page (information from LGCIU 1 & 2). Only one green triangle on each landing gear is sufficient to confirm that the landing gear is downlocked. LANDING GEAR SELECTOR LEVER
Ident.: DSC-32-10-40-00001293.0002001 / 14 FEB 11 Applicable to: ALL
A two-position selector lever sends electrical signals to the two LGCIUs. These control the green hydraulic supply to the landing gear system by means of selector valves. When the flight crew selects UP or DOWN (and if the airspeed is below 260 kt) : ‐ All landing gear doors open. ‐ Each landing gear moves to the selected position. ‐ All landing gear doors close.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-32-10-40 P 1/6 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - CONTROLS AND INDICATORS
(1)
L/G LEVER UP : This position selects landing gear retraction. While the landing gear doors are opening, the normal brake system brakes the wheels of the main gear automatically. DOWN : This position selects landing gear extension. An interlock mechanism prevents anyone from accidentally retracting the gear while the aircraft is on the ground. It does so by locking the lever in DOWN position when the shock absorber on either main gear is compressed (aircraft on ground) or the nose wheel steering is not centered. The landing gear hydraulic system remains pressurized as long as the landing gear is extended (if green hydraulic pressure is available).
(2)
RED ARROW This red arrow lights up if the landing gear is not locked down when the aircraft is in the landing configuration, and a red warning appears on ECAM.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-32-10-40 P 2/6 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
GEARS AND DOORS - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
EMERGENCY EXTENSION Ident.: DSC-32-10-40-00001294.0001001 / 14 FEB 11 Applicable to: ALL
To put the landing gear down by gravity, the flight crew must pull the gear crank out, then turn it clockwise for 3 turns. When the flight crew operates the crank handle, the cutout valve shuts off hydraulic pressure to the landing gear system and depressurizes it.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-32-10-40 P 3/6 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - CONTROLS AND INDICATORS
ECAM WHEEL PAGE Ident.: DSC-32-10-40-00001295.0006001 / 22 MAY 12 Applicable to: ALL
(1)
Landing gear position indication The landing gear positions are indicated by 2 triangles for each gear. ‐ ‐ ‐ ‐
A green triangle indicates that one LGCIU detects a landing gear downlocked, A red triangle indicates that one LGCIU detects a landing gear in transit, No triangle indicates that one LGCIU detects a landing gear uplocked, Amber crosses will replace the right triangle to indicate that LGCIU 1 or LGCIU 2 has failed.
Note:
Only one green triangle on each landing gear strut is sufficient to confirm that the landing gear is downlocked.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D→
DSC-32-10-40 P 4/6 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - CONTROLS AND INDICATORS
(2)
Landing gear door position indication
(3)
UP LOCK This legend appears amber along with a caution on the ECAM if the landing gear uplock is engaged when the landing gear is down locked.
(4)
L/G CTL This legend appears in amber along when the landing gear lever and the landing gear position do not agree. This legend only appears when the landing gear is moving to the selected position.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D
DSC-32-10-40 P 5/6 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - CONTROLS AND INDICATORS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-32-10-40 P 6/6 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
GEARS AND DOORS - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-32-10-50-00001296.0006001 / 17 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-32-10-50 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - WARNINGS AND CAUTIONS
E/WD: FAILURE TITLE conditions
AURAL WARNING
MASTER LIGHT
GEAR NOT DOWNLOCKED
One gear not downlocked and L/G selected down
SD PAGE CALLED
LOCAL WARNING
WHEEL
UNLK lt on
FLT PHASE INHIB
GEAR NOT DOWN
1. L/G not downlocked and radio height lower than 750 ft and both engines N1 lower than 75 % (or if engine shut down N1 of remaining engine lower than 97 %) or 2. L/G not downlocked and radio height lower than 750 ft and both engines not at T.O. power and flaps at 1, 2, 3 or FULL or 3. L/G not downlocked and flaps at 3 or FULL and both radio altimeters failed Note:
CRC
MASTER WARN NIL
DOWN ARROW lt on LDG GEAR panel
3, 4, 5
In the cases 2 and 3 above, the aural warning can only be cancelled by the emergency cancel pushbutton.
SHOCK ABSORBER FAULT
One shock absorber not extended when airborne or not compressed after landing
DOORS NOT CLOSED
One gear door is not uplocked
GEAR NOT UPLOCKED
1, 3, 4 NIL SINGLE CHIME
1, 3, 4, 5, 8, 9, 10
MASTER CAUT
One gear not uplocked and L/G not selected down
GEAR UPLOCK FAULT
WHEEL
One gear uplock engaged with corresponding gear downlocked
LGCIU 1 (2) FAULT SYS DISAGREE
Disagree between L/G positions detected by the two LGCIU's
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
UNLK lt on LDG GEAR panel
3, 4, 7, 8, 9, 10 4 4, 5, 7, 8
NIL
←A
NIL
NIL
3, 4, 5, 6,7, 8
DSC-32-10-50 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - ELECTRICAL SUPPLY
BUS EQUIPMENT LIST Ident.: DSC-32-10-60-00001329.0001001 / 10 DEC 09 Applicable to: ALL
NORM AC
DC
AC ESS
EMER ELEC DC ESS X
HOT
LGCIU 1 GRND/ FLT LGCIU 2 GRND/ FLT SAFETY VALVE X L/G INDICATOR PANEL X SHED (1) The AC STAT INV supplies the landing gear indicator panel when the main generators are lost and the emergency generator is not running.
LANDING GEAR (1)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-32-10-60 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GEARS AND DOORS - ELECTRICAL SUPPLY
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-32-10-60 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
NOSE WHEEL STEERING - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
DESCRIPTION Ident.: DSC-32-20-10-00001297.0003001 / 11 FEB 11 Applicable to: ALL
A hydraulic actuating cylinder steers the nose wheel. The yellow hydraulic system supplies pressure to the cylinder, and electric signals from the Brake and Steering Control Unit (BSCU) control it. The BSCU receives orders from: ‐ The Captain's and the First Officer’s steering hand wheels (orders added algebraically), ‐ The rudder pedals, ‐ The autopilot. The BSCU transforms these orders into nose wheel steering angle. That angle has the following limits, which depend on ground speed and the origin of the orders.
The steering system receives actuating hydraulic pressure when: ‐ The A/SKID & N/W STRG switch is on and, ‐ The towing control lever is in normal position and, ‐ At least one engine is running and, ‐ The aircraft is on ground. The handwheel can turn the nosewheel up to 75 ° in either direction. A lever, on the towing electrical box (on nose landing gear), enables ground crew to deactivate the steering system for towing. Then the wheel can be turned 95 ° in either direction. To prevent rudder pedal orders, or autopilot orders, from going to the BSCU, the pilots can use the pushbutton on either steering handwheel. An internal cam mechanism returns the nose wheel to the centered position after takeoff.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-32-20-10 P 1/4 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
NOSE WHEEL STEERING - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
ARCHITECTURE Ident.: DSC-32-20-10-00001298.0002001 / 10 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
DSC-32-20-10 P 2/4 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
NOSE WHEEL STEERING - DESCRIPTION
←B
DSC-32-20-10 P 3/4 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
NOSE WHEEL STEERING - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-32-20-10 P 4/4 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NOSE WHEEL STEERING - CONTROLS AND INDICATORS
SIDE CONSOLES Ident.: DSC-32-20-20-00001299.0001001 / 17 MAR 11 Applicable to: ALL
(1)
Steering handwheels The steering handwheels, which are interconnected, can steer the nose wheel up to 75 ° in either direction. Note:
(2)
The steering system centers the nose wheel automatically after liftoff.
Rudder PEDAL DISC pb Pressing this button on either handwheel removes control of nose wheel steering from the rudder pedals until the button is released.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-32-20-20 P 1/4 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NOSE WHEEL STEERING - CONTROLS AND INDICATORS
CENTER INSTRUMENT PANEL Ident.: DSC-32-20-20-00001300.0001001 / 11 FEB 11 Applicable to: ALL
(1)
A/SKID & N/W STRG sw This ON/OFF switch activates or deactivates the nose wheel steering and anti-skid. (Refer to DSC-32-30-10 General). ECAM WHEEL PAGE
Ident.: DSC-32-20-20-00001301.0003001 / 11 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B to C →
DSC-32-20-20 P 2/4 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NOSE WHEEL STEERING - CONTROLS AND INDICATORS
(1)
N/W STEERING label It appears in amber, when nosewheel steering is lost, due to failure of the nosewheel steering system, or of both BSCU channels, or in case of a yellow hydraulic system low pressure, or if the A/SKID & N/W STRG switch is OFF.
(2)
N/W STEERING hydraulic supply indication : Only when the N/W STEERING label is displayed : ‐ Y is displayed in green in case the yellow hydraulic system is not failed. ‐ Y is displayed in amber in case of yellow hydraulic system low pressure.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C
DSC-32-20-20 P 3/4 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NOSE WHEEL STEERING - CONTROLS AND INDICATORS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-32-20-20 P 4/4 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NOSE WHEEL STEERING - WARNINGS AND CAUTIONS
WARNINGS AND CAUTIONS Ident.: DSC-32-20-30-00001302.0002001 / 11 FEB 11 Applicable to: ALL
E/WD : FAILURE TITLE conditions NW STRG FAULT detected by BSCU
AURAL WARNING
MASTER LIGHT MASTER CAUT
SINGLE CHIME
SD PAGE CALLED
LOCAL WARNING
FLT PHASE INHIB
WHEEL
NIL
3, 4, 5, 8
MEMO DISPLAY When the nose wheel steering selector is in the towing position, this display shows “NW STRG DISC” in green. The legend is amber if one engine is running.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-32-20-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NOSE WHEEL STEERING - WARNINGS AND CAUTIONS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-32-20-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
NOSE WHEEL STEERING - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-32-20-40-00001330.0001001 / 10 DEC 09 Applicable to: ALL
NORM
BRAKES
BSCU CH 1 BSCU CH 2
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
AC
DC
AC1 AC2
DC1 DC2
A
AC ESS
EMER ELEC DC ESS
HOT
DSC-32-20-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NOSE WHEEL STEERING - ELECTRICAL SUPPLY
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-32-20-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
BRAKES AND ANTISKID - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-32-30-10-00001303.0002001 / 16 FEB 11 Applicable to: ALL
The main wheels are equipped with carbon multidisc brakes, which can be actuated by either of two independent brake systems. The normal system uses green hydraulic pressure, whereas the alternate system uses the yellow hydraulic system backed up by the hydraulic accumulator. An anti-skid and autobrake system is also provided. Braking commands come from either the brake pedals (pilot action), or the autobrake system (deceleration rate selected by the crew). In normal operation, a dual channel Brake and Steering Control Unit (BSCU) controls normal braking and antiskid. Depending on the failure, braking may revert to: ‐ Alternate braking with antiskid. This braking mode is controlled by the Alternate Braking Control Unit (ABCU). The antiskid is controlled by the BSCU. ‐ Alternate braking without antiskid. This braking mode is fully-controlled by the ABCU. ‐ Alternate braking without antiskid on accumulator. This braking mode is fully-controlled by the ABCU. All the normal and alternate braking components are fully-monitored. Any detected failure is signaled to the crew via ECAM warnings. The BSCU performs the following secondary functions: ‐ It checks the residual pressure in the brakes, ‐ It monitors the brake temperature, ‐ It provides discrete wheel speed information to other aircraft systems. A changeover between the two BSCU channels takes place at each DOWN landing gear lever selection, or in case one channel fails. The main gear wheels are fitted with fusible plugs which protect against tire burst, in the event of overheat. Main gear wheels are also equipped with brake cooling fans , which permit a high speed cooling of brakes. ANTI-SKID SYSTEM Ident.: DSC-32-30-10-00001304.0003001 / 14 MAY 12 Applicable to: ALL
The antiskid system provides maximum braking efficiency by maintaining the wheels at the limit of an impending skid.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-32-30-10 P 1/10 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
BRAKES AND ANTISKID - DESCRIPTION
At skid onset, brake release orders are sent to the normal and alternate servovalves, as well as to the ECAM system which displays the released brakes. Full braking performance is achieved only with brake pedals at full deflection. The antiskid system is deactivated below 20 kt (ground speed). An ON/OFF switch activates, or deactivates, the antiskid and nosewheel steering systems. PRINCIPLE The speed of each main gear wheel (given by a tachometer) is compared to the aircraft speed (reference speed). When the speed of a wheel decreases below approximately 0.87 times (depending on conditions) reference speed, brake release orders are given to maintain the wheel slip at that value (best braking efficiency). In normal operation, the reference speed is determined by the BSCU from the horizontal acceleration of ADIRU 1, 2 or 3. In case all ADIRUs fail, reference speed equals the maximum of either main landing gear wheel speeds.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-32-30-10 P 2/10 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
BRAKES AND ANTISKID - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
ANTI-SKID PRINCIPLE Ident.: DSC-32-30-10-00001305.0003001 / 10 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-32-30-10 P 3/10 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
BRAKES AND ANTISKID - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
AUTO BRAKE - GENERAL Ident.: DSC-32-30-10-A-NG00092 Applicable to: ALL Ident.: DSC-32-30-10-A-00001306.0001001 / 10 DEC 09
GENERAL The purposes of this system are : ‐ to reduce the braking distance in case of an aborted takeoff ‐ to establish and maintain a selected deceleration rate during landing, thereby improving passenger comfort and reducing crew workload. Ident.: DSC-32-30-10-A-00001307.0002001 / 16 FEB 11
SYSTEM ARMING The system arms when the crew presses the LO, MED, or MAX pushbutton switch if: ‐ Green pressure is available. ‐ The anti-skid system has electric power. ‐ There is no failure in the braking system. ‐ At least one ADIRS is functioning. Note:
1. Auto brake may be armed with the parking brake on. 2. MAX autobrake mode cannot be armed in flight.
Ident.: DSC-32-30-10-A-00001308.0002001 / 16 FEB 11
SYSTEM ACTIVATION Automatic braking is activated: ‐ at the command for ground spoilers extension (Refer to DSC-27-10-20-C Speed Brakes and Ground Spoilers - Speed Brake Control), for LO and MED mode. ‐ at the command for ground spoilers extension and the aircraft speed is above 40 kt, for MAX mode. Therefore, if the aircraft makes an acceleration stop and begins to decelerate when its speed is under 72 kt, the automatic braking will not activate because the ground spoilers will not extend. For autobrake to activate, at least two SEC’s must be operative. Ident.: DSC-32-30-10-A-00001309.0001001 / 10 DEC 09
SYSTEM DEACTIVATION The system deactivates : ‐ When it is disarmed (Refer to DSC-32-30-10-A Auto Brake - System Disarming). ‐ When the ground spoilers retract. In this case it remains armed. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D→
DSC-32-30-10 P 4/10 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
BRAKES AND ANTISKID - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
Ident.: DSC-32-30-10-A-00001310.0002001 / 16 FEB 11
SYSTEM DISARMING The system disarms when: ‐ Flight crew presses the pushbutton switch or, ‐ One or more arming conditions is lost or, ‐ Flight crew applies enough deflection to at least one brake pedal when autobrake is active in MAX, MED or LO mode. ‐ After take-off/touch and go.
OPERATION - GENERAL Ident.: DSC-32-30-10-B-NG00093 Applicable to: ALL Ident.: DSC-32-30-10-B-00001311.0001001 / 10 DEC 09
GENERAL There are four modes of operation : ‐ Normal braking, ‐ Alternate braking with antiskid, ‐ Alternate braking without antiskid, ‐ Parking brake. Ident.: DSC-32-30-10-B-00001312.0002001 / 16 FEB 11
NORMAL BRAKING Braking is normal when : ‐ Green hydraulic pressure is available. ‐ The A/SKID & N/W STRG switch is ON. During normal braking, antiskid operates and autobrake is available. Braking is electrically-controlled through the BSCU : ‐ From the pilot’s pedals, or ‐ Automatically : • On ground by the autobrake system, • In flight when the landing gear lever is up. The antiskid system is controlled by the BSCU via the normal servo valves. There is no brake pressure indication in the cockpit.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← D to E →
DSC-32-30-10 P 5/10 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
BRAKES AND ANTISKID - DESCRIPTION
Ident.: DSC-32-30-10-B-00001313.0002001 / 16 FEB 11
ALTERNATE BRAKING WITH ANTI-SKID Autobrake is inoperative. Braking uses this mode when green hydraulic pressure is insufficient, and : ‐ Yellow hydraulic pressure is available. ‐ The A/SKID & N/W STRG switch is ON. ‐ The parking brake is not ON. Braking inputs are made by the brake pedals and sent to the ABCU. Then, taking into account the brake pedal input, the ABCU: ‐ Energizes the alternate brake selector valve to pressurize the yellow hydraulic circuit, ‐ Electrically controls the Alternate Servo Valve to obtain the correct pressure for the related brakes. Antiskid is controlled by the BSCU. Brake pressure, as well as accumulator pressure, are indicated on a triple indicator located on the center instrument panel. Ident.: DSC-32-30-10-B-00001314.0002001 / 16 FEB 11
ALTERNATE BRAKING WITHOUT ANTI-SKID Autobrake and antiskid are inoperative. The antiskid system is either deactivated: ‐ Electrically (A/SKID & N/W STRG sw OFF, or power supply failure, or BSCU failure), or ‐ Hydraulically (Y + G system low pressure, the brakes are supplied by the brake accumulator only). Depending on the brake pedals’ demand, the ABCU controls the alternate brake selector and the alternate servovalves. Brake pressure and accumulator pressure are indicated on a triple indicator, located on the center instrument panel. To avoid wheel locking and limit the risk of tire burst, brake pressure is automatically limited to 1 000 PSI. Accumulators are designed to supply at least seven full brake applications. Ident.: DSC-32-30-10-B-00001315.0003001 / 10 DEC 09
PARKING BRAKE Brakes are supplied by the yellow hydraulic system, or by accumulator pressure via the parking brake control valve, which opens allowing full pressure application on the main gear wheel brakes. The accumulator maintains the parking pressure for at least 12 h.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-32-30-10 P 6/10 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
BRAKES AND ANTISKID - DESCRIPTION
If the parking brake is activated and no yellow hydraulic or accumulator brake pressure is available, then the normal braking system can be applied via the brake pedals. Yellow accumulators can be pressurized by pressing the yellow electrical pump switch. Brake pressure and accumulator pressure are indicated on a triple indicator, located on the center instrument panel.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E
DSC-32-30-10 P 7/10 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
BRAKES AND ANTISKID - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
BRAKING SCHEMATIC Ident.: DSC-32-30-10-00001316.0003001 / 17 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F→
DSC-32-30-10 P 8/10 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
BRAKES AND ANTISKID - DESCRIPTION
←F
DSC-32-30-10 P 9/10 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
BRAKES AND ANTISKID - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-32-30-10 P 10/10 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
BRAKES AND ANTISKID - CONTROLS AND INDICATORS
CENTER INSTRUMENT PANEL Ident.: DSC-32-30-20-00001318.0002001 / 14 NOV 11 Applicable to: ALL
(1)
A/SKID & N/W STRG sw ON : If green hydraulic pressure is available, then antiskid is available. If green hydraulic pressure is lost, then : ‐ Yellow hydraulic pressure automatically takes over to supply the brakes, ‐ Antiskid and nosewheel steering remain available. ‐ The triple indicator shows yellow system brake pressure. OFF :
The yellow hydraulic system supplies pressure to the brakes. ‐ Antiskid is deactivated. The pilot must refer to the triple indicator to limit brake pressure and avoid locking a wheel. ‐ Nosewheel steering is lost. ‐ Differential braking remains available through the pedals. ‐ The triple indicator displays yellow system brake pressure.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-32-30-20 P 1/6 03 APR 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(2)
BRAKES AND ANTISKID - CONTROLS AND INDICATORS
BRAKES and ACCU PRESS indicator Brake pressure is only indicated when the yellow hydraulic system controls the brake pressure, which means when the : ‐ Alternate braking system is activated, or ‐ Parking brake is applied. ACCU : PRESS BRAKES :
Indicates the pressure in the yellow brake accumulator. Indicates the yellow pressure delivered to the left and right brakes, as measured upstream of the alternate servovalves. AUTO BRK PANEL
Ident.: DSC-32-30-20-00001319.0002001 / 16 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← A to B →
DSC-32-30-20 P 2/6 03 APR 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(3)
BRAKES AND ANTISKID - CONTROLS AND INDICATORS
AUTO/BRK panel The springloaded MAX, MED, and LO pushbutton switches arm the appropriate deceleration rate: ‐ MAX mode is normally selected for takeoff. In the case of an aborted takeoff, maximum pressure goes to the brakes, as soon as the system generates the ground spoiler deployment order. ‐ MED or LO mode is normally selected for landing: • LO mode sends progressive pressure to the brakes 4 s after the ground spoilers deploy, in order to decelerate the aircraft at 1.7 m/s² (5.6 ft/s²). • MED mode sends progressive pressure to the brakes 2 s after the ground spoilers deploy in order to decelerate the aircraft at 3 m/s² (9.8 ft/s²). ‐ Lights: • The blue ON light comes on to indicate positive arming. • The green DECEL light comes on when the actual deceleration is 80 % of the selected rate. Note:
• Off :
On slippery runways, the predetermined deceleration may not be reached, due to antiskid operation. In this case, the DECEL light will not come on. This does not mean that autobrake is not working. The corresponding autobrake mode is not armed. BRAKE FANS
Ident.: DSC-32-30-20-00001320.0001001 / 29 MAR 12 Applicable to: ALL
(4)
BRK FAN pb sw ON : The brake fans run if the lefthand main landing gear is down and locked. OFF : The brake fans stop.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
DSC-32-30-20 P 3/6 03 APR 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
HOT lt :
BRAKES AND ANTISKID - CONTROLS AND INDICATORS
This amber light comes on when the brakes get too hot. (A caution appears on ECAM, also). PEDESTAL
Ident.: DSC-32-30-20-00001321.0002001 / 10 DEC 09 Applicable to: ALL
(1)
PARKING BRK handle Flight crew pulls this handle, then turns it clockwise, to apply the parking brake. The ECAM memo page displays “PARK BRK”. CAUTION
If the pointer is not at ON, the parking brake is not on. ECAM WHEEL PAGE
Ident.: DSC-32-30-20-00001322.0005001 / 16 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← C to E →
DSC-32-30-20 P 4/6 03 APR 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
BRAKES AND ANTISKID - CONTROLS AND INDICATORS
(1)
Release indicators It appears in amber in case of brake released fault.
(2)
ANTI SKID indication
(A) ANTISKID label It appears in amber, a long with an ECAM caution, in case of a total BSCU failure, or when the A/SKID & N/W STRG switch is OFF, or if the BSCU detects an ANTI-SKID failure, or in case of normal braking and yellow hydraulic system low pressure. It appears in green in case of autobrake, normal braking, or alternate braking failure, and antiskid is still available. (B) BSCU channel indication When ANTISKID label is displayed, the number of the failed system(s) is (are) displayed in amber, if any. (3)
AUTO BRK This legend appears: ‐ in green when auto brake is armed, ‐ flashing green for 10 s after autobrake disengagement. ‐ in amber, along with an ECAM caution, to indicate a system failure. MED, LO, or MAX appears underneath in green to show which rate has been selected.
(4)
Wheel number This white number identifies individual wheels of the main landing gear.
(5)
Brake temperature ‐ The temperature normally appears in green. ‐ The green arc appears on the hottest wheel when one brake temperature exceeds 100 °C. ‐ The green arc becomes amber, and an ECAM caution appears, when the corresponding brake temperature exceeds 300 °C.
(6)
NORM BRK indication
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-32-30-20 P 5/6 03 APR 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
BRAKES AND ANTISKID - CONTROLS AND INDICATORS
(A) NORM BRK label This indication appears in green when autobrake or alternate braking is failed, and normal braking is still available. The legend appears in amber when normal braking is failed due to total BSCU failure, or to the loss of the green hydraulic pressure, or to the loss of antiskid. (B) NORM BRK hydraulic supply indication G is displayed when the NORM BRK label is displayed. It is green when green hydraulic pressure is available and amber, in case of green hydraulic low pressure. (7)
(A) ALTN BRK label This indication appears in green, if the braking system is in alternate mode and not failed, or in case autobrake or normal braking is failed and alternate braking is still available. This indication appears in amber when alternate braking is failed. (B) ALTN BRK hydraulic supply indication Y is displayed when the ALTN BRK label is displayed. It is green when yellow hydraulic pressure is available and amber, in case of yellow hydraulic low pressure. (C) ACCU indications
(*)
Appears in green, when the ALTN BRK label is displayed, and the yellow hydraulic pressure is available. Appears in amber, with no arrow, when the yellow hydraulic system and the accumulator are in low pressure.
(**) Appears in green when the alternate braking is pressurized by the yellow accumulator.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E
DSC-32-30-20 P 6/6 03 APR 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
BRAKES AND ANTISKID - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-32-30-30-00001324.0041001 / 25 APR 12 Applicable to: ALL
E/WD: FAILURE TITLE condition
AURAL WARNING
MASTER LIGHT
parking brake is on when thrust levers are set at TO or FLX TO power position
CRC
MASTER WARN
CONFIG PARK BRK ON PARK BRK ON
SD PAGE CALLED
LOCAL WARNING
NIL
NIL
1, 2, 4 to 10 1 to 5, 8 to 10
Parking brake is ON during flight.
BRAKES HOT
HOT lt on BRK FAN pb sw
It is triggered when one brake temperature is higher than 300 °C and off when the highest brake temperature is lower than 290 °C.
AUTO BRK FAULT
failure of autobrake when armed
A/SKID NWS FAULT
‐ Loss of normal brake system associated with Y HYD SYS lo PRESS or ‐ Failure of both BSCU channels
FLT PHASE INHIB
4, 8 to 10
3 to 5 SINGLE CHIME
MASTER CAUT
WHEEL 4, 5 NIL
ANTI SKID/NWS OFF switch at OFF position
4, 5
HYD SEL FAULT
failure of brake normal selector valve or NWS selector valve in open position
SYS 1 (2) FAULT
failure of one BSCU channel
NIL NIL
3 to 5, 7, 8
NIL Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-32-30-30 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
E/WD: FAILURE TITLE condition
RELEASED
Brake of one wheel is released. It is detected when the landing gear is downlocked and, at least one engine is running, and normal braking is active.
BRAKES AND ANTISKID - WARNINGS AND CAUTIONS
AURAL WARNING
MASTER LIGHT
SINGLE CHIME
MASTER CAUT
NORM BRK FAULT
Continued from the previous page SD PAGE LOCAL FLT PHASE CALLED WARNING INHIB
4, 5 WHEEL 3 to 5
Normal braking function is lost.
ALTN BRK FAULT
NIL
Alternate braking function is lost.
NIL
3, 4, 5, 7, 8
ALTN L(R) RELEASED
Brakes of one gear is released. It is triggered when the landing gear is downlocked, and at least one engine is running, and alternate braking is active.
NORM + ALTN FAULT
Normal and alternate functions are lost. Parking brake available.
NIL
SINGLE CHIME
MASTER CAUT
BRK Y ACCU LO PR PARK BRK LO PR
Single system failure, loss of redundancy
3, 4, 5, 7, 8 3 to 8
The yellow accumulator and hydraulic system pressures are low with parking brake on
BRAKES-NWS MINOR FAULT
3, 4, 5
4, 5 WHEEL
The yellow accumulator is in low pressure.
NIL
NIL
NIL
NIL
2 to 9
MEMO DISPLAY ‐ If the parking brake is ON, the “PARK BRK” memo appears in green, during flight phases 1, 2, 9, and 10. ‐ If the autobrake is armed, AUTO BRK LO, AUTO BRK MED, or AUTO BRK MAX appears. ‐ If the autobrake is faulty, "AUTO BRK OFF" appears. ‐ "BRK FAN" appears in green, if the BRK FAN pushbutton is ON.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-32-30-30 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321
BRAKES AND ANTISKID - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-32-30-40-00001331.0002001 / 10 DEC 09 Applicable to: ALL
NORM
BRAKES
BSCU CH 1 BSCU CH 2 ABCU PARK BRK CTL PRESS INDICATOR BRK FAN CTL COOLING FANS (Wheels 1, 2, 3, 4) COOLING FANS (bogie : Wheels 5, 6, 7, 8)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
AC
DC
AC1 AC2
DC1 DC2
AC ESS
EMER ELEC DC ESS
X GRND/ FLT
HOT
X HOT1
X DC2 AC2
DC2
AC1
DC1
A
DSC-32-30-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
BRAKES AND ANTISKID - ELECTRICAL SUPPLY
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-32-30-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TIRE PRESSURE INDICATING SYSTEM - DESCRIPTION
DESCRIPTION Ident.: DSC-32-40-10-00001325.0001001 / 13 DEC 10 Applicable to: ALL
The tire pressure indicating system includes : ‐ a sensor that measures the pressure of each tire, ‐ a transmission unit that transmits the electrical pressure signal from the sensor to the computer, ‐ a tire pressure indicating unit computer that sends information to the ECAM for cautions and the system page display.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-32-40-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TIRE PRESSURE INDICATING SYSTEM - DESCRIPTION
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-32-40-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TIRE PRESSURE INDICATING SYSTEM - CONTROLS AND INDICATORS
WHEEL SD PAGE Ident.: DSC-32-40-20-00001326.0001001 / 22 MAY 12 Applicable to: ALL
(1)
Tire press indication The normal indication is green. lt becomes amber, and ECAM caution appears, if tire pressure gets too low. Note:
The prescribed tire pressure depends on the tire type and the aircraft weight.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-32-40-20 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TIRE PRESSURE INDICATING SYSTEM - CONTROLS AND INDICATORS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-32-40-20 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TIRE PRESSURE INDICATING SYSTEM - ELECTRICAL SUPPLY
BUS EQUIPMENT LIST Ident.: DSC-32-40-40-00001332.0001001 / 10 DEC 09 Applicable to: ALL
NORM AC TYRE PRESS
DC
TIRE PRESS IND UNIT
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
AC ESS
EMER ELEC DC ESS
HOT
DC1
A
DSC-32-40-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS LANDING GEAR A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TIRE PRESSURE INDICATING SYSTEM - ELECTRICAL SUPPLY
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-32-40-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS LIGHTS
Intentionally left blank
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-33-PLP PRELIMINARY PAGES TABLE OF CONTENTS SUMMARY OF HIGHLIGHTS
DSC-33-10 Cockpit Lighting DSC-33-10-10 General General.....................................................................................................................................................................A
DSC-33-10-20 Description Description............................................................................................................................................................... A Schematic.................................................................................................................................................................B
DSC-33-10-30 Controls and Indicators Overhead Panel....................................................................................................................................................... A Maintenance Panel.................................................................................................................................................. B Lateral Window........................................................................................................................................................ C Pedestal................................................................................................................................................................... D Glareshield............................................................................................................................................................... E Main Inst Panel........................................................................................................................................................ F
DSC-33-10-40 Electrical Supply BUS EQUIPMENT LIST.......................................................................................................................................... A
DSC-33-20 Exterior Lighting DSC-33-20-10 General GENERAL................................................................................................................................................................ A
DSC-33-20-20 Controls and Indicators SCHEMATIC............................................................................................................................................................ A Overhead Panel....................................................................................................................................................... B
DSC-33-20-30 Electrical Supply BUS EQUIPMENT LIST.......................................................................................................................................... A
DSC-33-30 Emergency Lighting DSC-33-30-10 Description General.....................................................................................................................................................................A PROXIMITY EMERGENCY ESCAPE PATH MARKING SYSTEM/EXIT SIGNS....................................................B Emergency Lighting Control Logic.......................................................................................................................... C
DSC-33-30-20 Controls and Indicators CONTROLS AND INDICATORS.............................................................................................................................A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-33-PLP-TOC P 1/2 18 SEP 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-33-30-30 Electrical Supply BUS EQUIPMENT LIST.......................................................................................................................................... A
DSC-33-40 Signs DSC-33-40-10 Controls and Indicators Overhead Panel....................................................................................................................................................... A Memo Display.......................................................................................................................................................... B
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-33-PLP-TOC P 2/2 18 SEP 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title DSC-33-30-10 General
Toc Index
ID
A
1
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Reason Improvement of technical wording and layout.
DSC-33-PLP-SOH P 1/2 18 SEP 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-33-PLP-SOH P 2/2 18 SEP 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
COCKPIT LIGHTING - GENERAL
GENERAL Ident.: DSC-33-10-10-00001334.0001001 / 20 DEC 10 Applicable to: ALL
The instrument panel has both integral instrument lighting and flood lighting. The brightness of all panel lighting is adjustable. Incandescent spot lights and flood lights illuminate all work surfaces and the side consoles. Two dimmable dome lights illuminate the overall cockpit. When the batteries are supplying all electrical power, only the righthand dome light is on line.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-33-10-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321
COCKPIT LIGHTING - GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-33-10-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321
COCKPIT LIGHTING - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
DESCRIPTION Ident.: DSC-33-10-20-00001335.0002001 / 20 DEC 10 Applicable to: ALL
INTEGRATED LIGHTING FOR INSTRUMENTS AND PANELS All instruments and panels in the cockpit (other than display units) have integral lighting. The brightness of all integral lighting is adjustable. ANNUNCIATOR LIGHTS The ANN LT selector on the overhead panel controls the brightness of all the annunciator lights on the flight deck. It sets the brightness of all annunciator lights at the same level. Flight crew can test the annunciator lights by selecting the TEST position on the ANN LT selector and checking to see that all the annunciator lights come on. DOME LIGHTS Two dome lights give the cockpit shadow-free illumination. MAPHOLDER LIGHTING Each pilot’s station has a lighted map and chart holder. CONSOLE AND BRIEFCASE LIGHTING Each pilot’s station has lighting for the briefcase stowage, the side console, and the floor. CENTER INSTRUMENT PANEL Lights under the glareshield illuminate the center instrument panel. STANDBY COMPASS The standby compass has integral lighting. READING LIGHTS Each pilot’s station has a reading light. PEDESTAL LIGHTING A flood light in the middle of the overhead panel illuminates the center pedestal.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-33-10-20 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
COCKPIT LIGHTING - DESCRIPTION
SCHEMATIC Ident.: DSC-33-10-20-00001336.0002001 / 22 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
DSC-33-10-20 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
COCKPIT LIGHTING - CONTROLS AND INDICATORS
OVERHEAD PANEL Ident.: DSC-33-10-30-00001337.0003001 / 22 MAY 12 Applicable to: ALL
(1)
OVHD INTEG LT knob This knob turns the overhead panel’s integral lighting on and off, and adjusts its brightness.
(2)
ICE IND & STBY COMPASS sw This switch turns the integral lighting for the standby compass and the visual indicator on and off.
(3)
DOME selector This switch controls both dome lights. BRT : Both dome lights are on and bright. DIM : Both dome lights are on and dim. OFF : Both dome lights are off.
(4)
ANN LT selector This switch sets the brightness of all the cockpit annunciator lights at either “bright” or “dim”, and also tests them. TEST : Turns on all flight deck annunciator lights. Displays 8’s in all Liquid Crystal Displays (LCDs). DIM : Reduces voltage to all annunciator lights. BRT : Allows annunciators to function normally. Note:
Data transfer between the ECAM and the ND, and switching between the Electronic Instrument System and the Display Management Computer are not allowed during the ANN LT test.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-33-10-30 P 1/6 30 MAY 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321
COCKPIT LIGHTING - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
(5)
READING LT knob The reading light on each side of the overhead panel has its own control knob that turns it on and off and adjusts its brightness. MAINTENANCE PANEL
Ident.: DSC-33-10-30-00001338.0001001 / 22 MAY 12 Applicable to: ALL
(1)
AVIONICS COMPT LT pushbutton switch AUTO : avionic compartment lighting is automatically controlled by door opening. ON : avionic compartment lighting is on. LATERAL WINDOW
Ident.: DSC-33-10-30-00001339.0002001 / 22 MAY 12 Applicable to: ALL
(1)
Reading LT knob (Captain and F/O).
(2)
Brightness adjustment
(3)
Light
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← A to C
DSC-33-10-30 P 2/6 30 MAY 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
COCKPIT LIGHTING - CONTROLS AND INDICATORS
PEDESTAL Ident.: DSC-33-10-30-00001340.0001001 / 22 MAY 12 Applicable to: ALL
(1)
FLOOD LT MAIN PANL knob This knob adjusts the brightness of the flood lighting for the center instrument panel, and turns it on and off.
(2)
INTEG LT MAIN PNL & PED knob This knob adjusts the brightness of integral lighting for the main panel and pedestal, and turns it on and off.
(3)
FLOOD LT PED knob This knob adjusts the brightness of the flood lighting for the pedestal, and turns it on and off.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D
DSC-33-10-30 P 3/6 30 MAY 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
COCKPIT LIGHTING - CONTROLS AND INDICATORS
GLARESHIELD Ident.: DSC-33-10-30-00001341.0002001 / 22 MAY 12 Applicable to: ALL
(1)
This knob adjusts the brightness of the integral lighting on the glareshield, and of the LEDs on the FCU.
(2)
This knob adjusts the brightness of the FCU displays.
(3)
This lighting illuminates the sliding table and map holder.
(4)
This knob adjusts the brightness of the sliding table and map holder lighting.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E
DSC-33-10-30 P 4/6 30 MAY 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
COCKPIT LIGHTING - CONTROLS AND INDICATORS
MAIN INST PANEL Ident.: DSC-33-10-30-00001342.0001001 / 22 MAY 12 Applicable to: ALL
(1)
CONSOLE/FLOOR switch Each of these switches controls the lights for the side console and briefcase on one side of the cockpit, and for the floor around one of the pilot's seats. The lights can either be bright, dim, or off.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F
DSC-33-10-30 P 5/6 30 MAY 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
COCKPIT LIGHTING - CONTROLS AND INDICATORS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-33-10-30 P 6/6 30 MAY 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321
COCKPIT LIGHTING - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-33-10-40-00001353.0002001 / 20 DEC 10 Applicable to: ALL
NORM AC Dome light Console light Main INST panel
Reading light Briefcase light Map holder light Floor light INST, panels-integral light Annunciator light
R L R L R
HOT
X DC1 DC2 X DC1 X DC1 DC1 DC1 DC2 DC1 DC2 DC1 DC2 DC1
L R L R L R AC1 AC1, 2 and AC STAT INV
Annunciator light test/dim
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
EMER ELEC DC ESS
DC GND/ FLT
L
STBY compass/ice ind Supplementary reading light Pedestal light COCKPIT LIGHTS
DC
AC ESS
DC2
A
DSC-33-10-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321
COCKPIT LIGHTING - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-33-10-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EXTERIOR LIGHTING - GENERAL
GENERAL Ident.: DSC-33-20-10-00001343.0001001 / 10 DEC 09 Applicable to: ALL
Exterior lighting includes : ‐ navigation lights ‐ landing lights ‐ runway turn off lights ‐ TO and TAXI lights ‐ logo lights ‐ anticollision lights ‐ wing and engine scan lights Switches on the overhead panel control the exterior lighting.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-33-20-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTING - GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-33-20-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EXTERIOR LIGHTING - CONTROLS AND INDICATORS
SCHEMATIC Ident.: DSC-33-20-20-00001344.0006001 / 14 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-33-20-20 P 1/4 29 JUL 11
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EXTERIOR LIGHTING - CONTROLS AND INDICATORS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-33-20-20 P 2/4 29 JUL 11
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EXTERIOR LIGHTING - CONTROLS AND INDICATORS
OVERHEAD PANEL Ident.: DSC-33-20-20-00001345.0014001 / 14 MAR 11 Applicable to: ALL
(1)
BEACON sw This switch turns on and off the two flashing red lights, one on top and one on the bottom of the fuselage.
(2)
WING sw This switch turns on and off two beam lights on each side of the fuselage. These lights illuminate the leading edge of the wing and the engine air intake to show if ice is accumulating there.
(3)
NAV and LOGO sw This switch turns the navigation lights on and off. There are dual navigation lights on each wing tip and in the APU tail cone. Logo lights are installed in the upper surface of each horizontal stabilizer to illuminate the company logo on the vertical stabilizer provided the main gear struts are compressed or the flaps are extended at least 15 °. 1 : Turns on the logo lights and the first set of navigation lights. 2 : Turns on the logo lights and the second set of navigation lights.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
DSC-33-20-20 P 3/4 29 JUL 11
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
OFF (4)
:
EXTERIOR LIGHTING - CONTROLS AND INDICATORS
All lights are off.
NOSE sw This switch turns the taxi and takeoff lights on and off. TO : Turns on both taxi and takeoff lights. TAXI : Turns on only taxi light. OFF : Taxi and takeoff lights off. Note:
These two lights, attached to the nose gear strut, go off automatically when landing gear is retracted.
(5)
L and R LAND sel These selectors control the landing light. ON : Extends the (left or right) landing light which comes on automatically when fully extended. OFF : Shut off the landing light but leaves it extended. RETRACT : Retracts the landing light and shuts it off.
(6)
RWY TURN OFF sw This switch turns the runway turn-off lights on and off. Note:
(7)
These lights go off automatically when landing gear is retracted.
STROBE sw This switch turns on and off the three synchronized strobe lights, one on each wing tip and one below the tail cone. ON : The strobe lights flash white. AUTO : The strobe lights come on automatically when the main gear strut is not compressed. OFF : The strobe light are off.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-33-20-20 P 4/4 29 JUL 11
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EXTERIOR LIGHTING - ELECTRICAL SUPPLY
BUS EQUIPMENT LIST Ident.: DSC-33-20-30-00001354.0001001 / 10 DEC 09 Applicable to: ALL
NORM AC
(1)
Navigation lights Landing lights L Landing lights R RWY turn off lights L RWY turn off lights R Taxi and TO lights Taxi and TO lights EXTERIOR Logo lights L LIGHTS Logo lights R Beacon lights Upper Beacon lights Lower Strobe lights Wing lights R Wing lights L Supply for the light control
DC
GRD/FLT AC1 AC2 AC1 AC2 AC1 AC2 AC1 AC2 AC1 AC2 AC2 AC1 AC2
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
AC ESS
EMER ELEC DC ESS
HOT
DC 2 (1) DC 2 (1) DC 2 (1) DC 2 (1) DC 2 (1) DC 2 (1)
A
DSC-33-20-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EXTERIOR LIGHTING - ELECTRICAL SUPPLY
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-33-20-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EMERGENCY LIGHTING - DESCRIPTION
GENERAL Ident.: DSC-33-30-10-00001347.0010001 / 19 JUL 12 Applicable to: ALL 1
The emergency lighting system has: ‐ Proximity emergency escape path marking systems (escape path and exit markers) ‐ Overhead emergency lights ‐ EXIT signs ‐ Lavatory auxiliary lights ‐ Overwing escape route lighting ‐ Escape slide lighting. EXIT signs come on, if the cabin altitude gets too high, or (depending on the CIDS/CAM programming) if the NO SMOKING signs come on. The floor proximity emergency escape path marking is a self-luminescent system. The exit marker, overhead emergency lighting, and EXIT signs come on, if the EMER EXIT LT selector is ON, or if the Purser panel’s EMER pb is pressed. ‐ With the EMER EXIT LT selector at ARM: • The exit markers of the proximity emergency escape path marking system comes on, if: ▪ Normal aircraft electrical power fails, or ▪ DC SHED ESS BUS is lost. • The overhead emergency lights come on, if: ▪ Normal aircraft electrical power system fails, or ▪ DC SHED ESS BUS fails, or ▪ AC BUS 1 fails. • Exit signs automatically come on, if: ▪ Normal aircraft electrical power system fails, or ▪ DC SHED ESS BUS fails. ‐ When lit: • The exit markers of the proximity emergency escape path marking system are powered by internal batteries for at least 12 min. • DC SHED ESS BUS supply the overhead emergency lights and the EXIT signs. If DC SHED ESS BUS fails, batteries inside the light fixtures power all the lights. • DC SHED ESS BUS charge the internal batteries, if: ▪ EMER LT selector is not at ON, and ▪ The Purser panel's EMER pb is not pressed, and ▪ DC SHED ESS BUS is supplied, and ▪ The NO SMOKING selector is OFF, or at AUTO with the landing gear retracted. Lavatory auxiliary lights are always on. They are supplied by 28 V DC ESS BUS. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-33-30-10 P 1/4 18 SEP 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EMERGENCY LIGHTING - DESCRIPTION
The escape slides have an integral lighting system. The escape slide lights and the overwing route lights come on automatically, when the slide is armed and the door or emergency exit is open. They are supplied by the internal batteries. PROXIMITY EMERGENCY ESCAPE PATH MARKING SYSTEM/EXIT SIGNS Ident.: DSC-33-30-10-00001348.0001001 / 10 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← A to B
DSC-33-30-10 P 2/4 18 SEP 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321
EMERGENCY LIGHTING - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
EMERGENCY LIGHTING CONTROL LOGIC Ident.: DSC-33-30-10-00001349.0004001 / 22 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-33-30-10 P 3/4 18 SEP 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321
EMERGENCY LIGHTING - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-33-30-10 P 4/4 18 SEP 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EMERGENCY LIGHTING - CONTROLS AND INDICATORS
CONTROLS AND INDICATORS Ident.: DSC-33-30-20-00001350.0009001 / 11 FEB 11 Applicable to: ALL
(1)
EMER EXIT LT selector The selector has three detent positions. ON : Overhead emergency lights, EXIT signs and proximity marking system come on. OFF : Above lights are off. ARM : • Exit markers comes on when the normal aircraft electrical power or DC SHED ESS BUS is lost. • The overhead emergency lights come on if: • Normal aircraft electrical power system fails or • DC SHED ESS BUS fails or • AC BUS 1 fails. • Exit signs come on if: • Normal aircraft electrical power system fails or • DC SHED ESS BUS fails or Note:
The LIGHT EMER pb on the purser's panel can turn on the emergency lighting independently of the positions of this selector switch.
(2)
EMER EXIT LT-OFF lt This light comes on amber when the EMER EXIT LT selector is selected OFF.
(3)
LIGHT EMER pb When pressed, this button performs the same function as the EMER EXIT LT switch when it is ON.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-33-30-20 P 1/2 03 APR 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EMERGENCY LIGHTING - CONTROLS AND INDICATORS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-33-30-20 P 2/2 03 APR 12
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EMERGENCY LIGHTING - ELECTRICAL SUPPLY
BUS EQUIPMENT LIST Ident.: DSC-33-30-30-00001355.0001001 / 10 DEC 09 Applicable to: ALL
NORM AC
DC
AC1 AC2 and GRND/ FLT Standby supply (Refer to DSC-33-30-10 Emergency Lighting Control Logic) CABIN LIGHTING
(1)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
AC ESS
EMER ELEC DC ESS
HOT
SHED (1)
DSC-33-30-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EMERGENCY LIGHTING - ELECTRICAL SUPPLY
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-33-30-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321
SIGNS - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
OVERHEAD PANEL Ident.: DSC-33-40-10-00001351.0001001 / 14 FEB 11 Applicable to: ALL
(1)
SEAT BELTS sw ON : FASTEN SEAT BELT and RETURN TO SEAT signs come on simultaneously, with a low tone chime. OFF : Signs are off. The low tone chime sounds when the lights turn off (depending on the CIDS/CAM programming).
(2)
NO SMOKING selector ON : NO SMOKING and EXIT signs come on simultaneously with a low tone chime. AUTO : NO SMOKING and EXIT signs come on when the landing gear is extended, and turn off when the landing gear is retracted. The low tone chime sounds (depending on the CIDS/CAM programming) when the lights go on or off. OFF : Signs are off. The low tone chime sounds when the lights turn off (depending on the CIDS/CAM programming). Note:
If the cabin altitude goes above 11 300 ft (±350 ft), the cabin illuminates (depending on the CIDS/CAM programming) and the NO SMOKING, FASTEN SEAT BELT, EXIT signs come on, regardless of the SEAT BELTS and NO SMOKING selector switches. MEMO DISPLAY
Ident.: DSC-33-40-10-00001352.0002001 / 14 FEB 11 Applicable to: ALL
‐ Displays “LDG LT” in green, if one landing light is extended. ‐ Displays “STROBE LT OFF” in green, if the STROBE switch is OFF in flight. ‐ Displays “SEAT BELTS” and “NO SMOKING” messages in green, when the corresponding sign is on. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
DSC-33-40-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS LIGHTS A318/A319/A320/A321
SIGNS - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-33-40-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION
Intentionally left blank
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-34-PLP PRELIMINARY PAGES TABLE OF CONTENTS
DSC-34-10 ADIRS DSC-34-10-10 Description General.....................................................................................................................................................................A PROBES LOCATION...............................................................................................................................................B PROBES SCHEMATIC............................................................................................................................................C ADIRS Schematic.................................................................................................................................................... D
DSC-34-10-20 Controls and Indicators Overhead Panel....................................................................................................................................................... A PEDESTAL...............................................................................................................................................................B
DSC-34-10-30 Warnings and Cautions Warnings and Cautions........................................................................................................................................... A
DSC-34-10-40 Electrical Supply BUS EQUIPMENT LIST.......................................................................................................................................... A
DSC-34-15 GPS DSC-34-15-10 Description Description............................................................................................................................................................... A
DSC-34-15-20 Normal Operation Normal Operation.....................................................................................................................................................A
DSC-34-15-30 Operation in Case of Failure Operation in Case of Failure................................................................................................................................... A
DSC-34-15-40 Warnings and Cautions Warnings and Cautions........................................................................................................................................... A
DSC-34-15-50 Electrical Supply Bus Equipment List..................................................................................................................................................A
DSC-34-20 Standby Instruments Compass.................................................................................................................................................................. A Bus Equipment List..................................................................................................................................................B
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-PLP-TOC P 1/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-34-25 ISIS Introduction...............................................................................................................................................................A Architecture.............................................................................................................................................................. B General.................................................................................................................................................................... C ATTITUDE................................................................................................................................................................D Airspeed................................................................................................................................................................... E Altitude......................................................................................................................................................................F Landing System Function........................................................................................................................................G Bugs Function..........................................................................................................................................................H Flags.......................................................................................................................................................................... I
DSC-34-30 Radio NAV DSC-34-30-10 Tuning GENERAL................................................................................................................................................................ A AUTOMATIC TUNING............................................................................................................................................. B MANUAL TUNING................................................................................................................................................... C BACK UP TUNING..................................................................................................................................................D ARCHITECTURE..................................................................................................................................................... E
DSC-34-30-20 Navaids VOR..........................................................................................................................................................................A ILS............................................................................................................................................................................ B ADF.......................................................................................................................................................................... C DME......................................................................................................................................................................... D MARKER BEACON................................................................................................................................................. E
DSC-34-30-30 Controls and Indicators Digital Distance and Radio Magnetic Indicator (DDRMI)........................................................................................ A Radio Management Panel (RMP)........................................................................................................................... B Warnings and Cautions........................................................................................................................................... C
DSC-34-30-40 Electrical Supply Bus Equipment List..................................................................................................................................................A
DSC-34-40 Radio Altimeter DSC-34-40-10 Description GENERAL................................................................................................................................................................ A INDICATIONS ON PFD...........................................................................................................................................B Automatic Call Out.................................................................................................................................................. C
DSC-34-40-20 Warnings and Cautions Warnings and Cautions........................................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-PLP-TOC P 2/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-34-40-30 Electrical Supply BUS EQUIPMENT LIST.......................................................................................................................................... A
DSC-34-50 ATC DSC-34-50-10 Description Description............................................................................................................................................................... A
DSC-34-50-20 Controls and Indicators Control Panel........................................................................................................................................................... A
DSC-34-50-50 Electrical Supply Bus Equipment List..................................................................................................................................................A
DSC-34-60 Weather Radar DSC-34-60-10 Description Description............................................................................................................................................................... A
DSC-34-60-20 Controls and Indicators Control Panel........................................................................................................................................................... A
DSC-34-60-30 Predictive Windshear System General.....................................................................................................................................................................A Windshear Alerts During Takeoff Roll, Up to 100 knots......................................................................................... B Windshear Alerts Above 50 feet............................................................................................................................. C Windshear Alerts Inhibition......................................................................................................................................D
DSC-34-60-40 Warnings and Cautions Warnings and Cautions........................................................................................................................................... A
DSC-34-60-50 ELECTRICAL SUPPLY BUS EQUIPMENT LIST.......................................................................................................................................... A
DSC-34-70 GPWS DSC-34-70-10 Description Description............................................................................................................................................................... A Schematic.................................................................................................................................................................B
DSC-34-70-20 GPWS Basics Modes Mode 1 : Excessive Rate of Descent..................................................................................................................... A Mode 2 : Excessive Terrain Closure Rate.............................................................................................................. B Mode 3 : Altitude Loss After Takeoff...................................................................................................................... C Mode 4 : Unsafe Terrain Clearance when Not in Landing Configuration............................................................... D Mode 5 : Descent Below Glideslope.......................................................................................................................E
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-PLP-TOC P 3/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-34-70-30 EGPWS Functions Terrain Awareness and Display.............................................................................................................................. A Terrain Caution and Warning Envelope.................................................................................................................. B Terrain Clearance Floor.......................................................................................................................................... C Runway Field Clearance Floor................................................................................................................................D
DSC-34-70-40 Controls and Indicators OVERHEAD PANEL................................................................................................................................................ A Instrument Panels.................................................................................................................................................... B
DSC-34-70-50 Warnings and Cautions Warnings and Cautions........................................................................................................................................... A
DSC-34-70-60 Electrical Supply BUS EQUIPMENT LIST.......................................................................................................................................... A
DSC-34-80 TCAS DSC-34-80-10 Description General.....................................................................................................................................................................A Main Components....................................................................................................................................................B Principle................................................................................................................................................................... C Intruder Classification.............................................................................................................................................. D TA/RA Thresholds....................................................................................................................................................E TCAS Modes............................................................................................................................................................F Advisory Inhibition................................................................................................................................................... G
DSC-34-80-20 Controls and Indicators ATC/TCAS Panel..................................................................................................................................................... A ND Indications..........................................................................................................................................................B TCAS Messages......................................................................................................................................................C PFD Indications....................................................................................................................................................... D Aural Messages....................................................................................................................................................... E
DSC-34-80-30 Warnings and Cautions Warnings and Cautions........................................................................................................................................... A
DSC-34-80-40 Electrical Supply BUS EQUIPMENT LIST.......................................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-PLP-TOC P 4/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ADIRS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-34-10-10-00001356.0047001 / 14 FEB 11 Applicable to: ALL
The Air Data and Inertial Reference System (ADIRS) supplies temperature, anemometric, barometric and inertial parameters to the EFIS system (PFD and ND) and to other user systems (FMGC, FADEC, ELAC, SEC, FAC, FWC, SFCC, ATC, GPWS, CFDIU, CPC). The system includes: ‐ Three identical ADIRU’s (Air Data and Inertial Reference Units). Each ADIRU is divided in two parts, either of which can work separately in case of failure in the other: • The ADR part (Air Data Reference) which supplies barometric altitude, airspeed, mach, angle of attack, temperature and overspeed warnings. • The IR part (Inertial Reference) which supplies attitude, flight path vector, track, heading, accelerations, angular rates, ground speed and aircraft position. Note:
Above 73 ° North and above 60 ° South, the ADIRU gives true heading instead of magnetic heading.
‐ One ADIRS control panel (ADIRS MSU) on the overhead panel for selection of modes (NAV, ATT, OFF). The IR is initialized with the FMGS. ‐ Two GPS receivers, which are connected to the IR part of the ADIRU’s for GP/IR hybrid position calculation. ‐ Four types of sensors: • Pitot probes (3) • Static pressure probes (STAT) (6) • Angle of attack sensors (AOA) (3) • Total air temperature probes (TAT) (2) These sensors are electrically heated to prevent from icing up. ‐ Eight ADMs (Air Data Modules) which convert pneumatic data from PITOT and STAT probes into numerical data for the ADIRUs. ‐ A switching facility for selecting ADR 3 or IR 3 for instrument displays in case of ADIRU 1 or 2 failure.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-34-10-10 P 1/4 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ADIRS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
PROBES LOCATION Ident.: DSC-34-10-10-00001358.0001001 / 09 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
DSC-34-10-10 P 2/4 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ADIRS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
PROBES SCHEMATIC Ident.: DSC-34-10-10-00001359.0001001 / 09 DEC 09 Applicable to: ALL
Note:
ADIRU (1) is supplied by CAPT probes, ADIRU (2) is supplied by F/O probes, ADIRU (3) is supplied by STBY probes and CAPT TAT.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-34-10-10 P 3/4 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ADIRS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
ADIRS SCHEMATIC Ident.: DSC-34-10-10-00001360.0016001 / 14 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D
DSC-34-10-10 P 4/4 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ADIRS - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
OVERHEAD PANEL Ident.: DSC-34-10-20-00001361.0005001 / 14 FEB 11 Applicable to: ALL
(1)
ADR 1 (2) (3) pushbutton OFF : Air data output disconnected. FAULT light : This amber light comes on with an ECAM caution if a fault is detected in the air data reference part.
(2)
IR 1 (2) (3) pushbutton OFF : Inertial data output disconnected.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-34-10-20 P 1/4 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FAULT light :
ADIRS - CONTROLS AND INDICATORS
This amber light comes on with an ECAM caution when a fault affects the respective IR. Steady : The respective IR is lost. Flashing : The attitude and heading information may be recovered in ATT mode.
(3)
IR 1 (2) (3) mode rotary selector OFF : The ADIRU is not energized. ADR and IR data are not available. NAV : Normal mode of operation. Supplies full inertial data to aircraft systems. ATT : IR mode supplying only attitude and heading information if the system loses its ability to navigate. The heading must be entered through the MCDU and has to be reset frequently (about every 10 min).
(4)
ON BAT light The ON BAT light come on in amber when the aircraft battery supplies at least one IRS. The ON BAT light also comes on for a few seconds at the beginning of a complete IRS alignment. lts does not come on in the case of a fast alignment.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-34-10-20 P 2/4 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ADIRS - CONTROLS AND INDICATORS
PEDESTAL Ident.: DSC-34-10-20-00001362.0001001 / 14 FEB 11 Applicable to: ALL
(1)
ATT HDG and AIR DATA sel NORM : ADIRU 1 supplies data to PFD 1, ND 1, RMI and VOR/DME. ADIRU 2 supplies data to PFD 2, and ND2. CAPT 3 : ADR 3 or IR 3 replaces ADR 1 or IR 1. F/O 3 : ADR 3 or IR 3 replaces ADR 2 or IR 2.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
DSC-34-10-20 P 3/4 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ADIRS - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-10-20 P 4/4 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ADIRS - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-34-10-30-00001363.0120001 / 14 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-34-10-30 P 1/4 03 APR 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ADIRS - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
E/WD: FAILURE TITLE conditions
AURAL WARNING
MASTER LIGHT
SD PAGE CALLED
LOCAL WARNING
STALL WARNING (No ECAM message)
An aural stall warning is triggered when the AOA is greater than a predetermined angle This angle depends on the: ‐ Slats/Flap position ‐ Speed/Mach ‐ F/CTL law (normal, alternate/direct)
CRICKET + STALL (SYNTHETIC VOICE)
GND
MASTER WARN
OVERSPEED ‐ VMO/MMO Aircraft speed/mach greater than VMO + 4 kt/MMO + 0.006 ‐ VLE Aircraft speed greater than VLE + 4 kt, with L/G not uplocked, or L/G doors not closed ‐ VFE Aircraft speed greater than VFE + 4 kt, with slats or/and flaps extended
2, 3, 4, 8, 9, 10
SINGLE CHIME
MASTER CAUT
CRC
MASTER WARN
SINGLE CHIME
MASTER CAUT
ADR (1+2) (1+3) (2+3) FAULT ADR 1+2+3 FAULT IR 1 (2) FAULT IR 3 FAULT IR (1+3) (2+3) FAULT IR 1+2 FAULT CAPT (F/O) (STBY) AOA FAULT
NIL
NIL
Difference between the heading on the CAPT and F/O displays is greater than 5 °. Difference between roll or pitch angle, displayed on the CAPT and F/O PFD greater than 5 °.
NIL
ADR FAULT lt
1, 4, 8, 10 1, 4, 5, 7, 8, 10 1, 4, 8, 10
NIL
1, 4, 8, 10 4, 5, 7, 8
HDG DISCREPANCY ATT DISCREPANCY
NIL
CRC
ADR 1 (2) FAULT ADR 3 FAULT
FLT PHASE INHIB
SINGLE CHIME
4, 5, 7, 8 4, 8
NIL CHECK HDG (on PFD and ND)
2 to 9 4, 8
CHECK ATT (on PFD)
3, 4, 8 CHECK ALT (on PFD) Continued on the following page
ALTI DISCREPANCY
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
MASTER CAUT
IR FAULT lt
←A→
DSC-34-10-30 P 2/4 03 APR 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
E/WD: FAILURE TITLE conditions
ADIRS - WARNINGS AND CAUTIONS
AURAL WARNING
MASTER LIGHT
Continued from the previous page FLT SD PAGE LOCAL PHASE CALLED WARNING INHIB
Difference between the altitude, displayed on the CAPT and F/O PFD, is greater than: ‐ 500 ft, if BARO ref STD is selected ‐ 250 ft, if QNH (or QFE) is selected
BARO REF DISCREPANCY
NIL
Difference between CAPT and F/O sides
IAS DISCREPANCY
Caution activated when there is a discrepancy between the speeds displayed on the PFDs.
NIL
One ADR is faulty or has been rejected by the ELAC, and there is a speed or angle-of-attack disagree between the two remaining ADRs.
FAULT lts on ELAC pbs
ADR DISAGREE
4, 5, 7, 8
3, 4, 5, 7
IR DISAGREE
PFD message
Disagree between two IR, with the third one failed.
IR NOT ALIGNED
NIL
Problem detected during IR alignment
1, 4, 5, 6, 7, 8, 10
MEMO DISPLAY ‐ ”IRS IN ALIGN X MN” memo appears during phase 1 or 2, during IRS alignment. X MN indicates the number of minutes remaining (1 < X < 10), until NAV mode is reached. • Before any engine is started, “IRS IN ALIGN X MN” memo: ▪ Appears in green when at least one active IRS is being aligned, ▪ Pulses in green if the alignment of one IRS is faulty. • When one engine is started, “IRS IN ALIGN X MN” memo appears in amber during IRS alignment. If the alignment of one IRS is faulty, “IRS IN ALIGN X MN”memo is replaced by the “IR NOT ALIGNED” ECAM caution. ‐ ”IR IN ATT ALIGN” appears in green during the IR alignment in Attitude mode.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-34-10-30 P 3/4 03 APR 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ADIRS - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-10-30 P 4/4 03 APR 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ADIRS - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-34-10-40-00001404.0001001 / 14 FEB 11 Applicable to: ALL
NORM AC
DC
ADIRU 1 AOA RESOLVER 1 ADIRU
(1) (2) (3)
AC ESS X
EMER ELEC DC ESS
HOT HOT 2 (1)
X
ADIRU 2
AC2
AOA RESOLVER 2 ADIRU 3 AOA RESOLVER 3
AC2 AC1
HOT 2 (2) during5 min HOT 1 (3)
AC1
Backup supply. Backup supply for 5 min. Backup supply, when ATT HDG is in the CAPT 3 position. Backup supply for 5 min, when the ATT HDG is in the NORM or F/03 position.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-34-10-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ADIRS - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-10-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
DESCRIPTION Ident.: DSC-34-15-10-00001364.0031001 / 07 APR 11 Applicable to: ALL
The Global Positioning System (GPS) is a satellite-based radio navigation aid. Worldwide, 24 satellites broadcast accurate navigation data that aircraft can use for precise determination of its position. The aircraft has two independent GPS receivers. Each GPS receiver is integrated in a modular avionics unit called MMR (Multi Mode Receiver) (GPS 1 receiver in MMR 1, GPS 2 receiver in MMR 2). The MMR processes the data received and transfers them to the ADIRUs, which then perform a GP-IRS hybrid position calculation. The FMGCs use the hybrid position. The GPS MONITOR page on MCDU 1 or MCDU 2 can display pure GPS position, true track, ground speed, estimated position, accuracy level, and mode of operation for the information and use of the flight crew. Note:
Flight crew can use the MCDU NAVAID page to deselect the use of GPS data for calculating position (Refer to DSC-22_20-50-10-25 Selected NAVAIDS Page).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-34-15-10 P 1/2 03 APR 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-15-10 P 2/2 03 APR 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPS - NORMAL OPERATION
FLIGHT CREW OPERATING MANUAL
NORMAL OPERATION Ident.: DSC-34-15-20-00004069.0003001 / 14 MAR 11 Applicable to: ALL
In normal operation, the GPS receiver 1 supplies ADIRU 1 and ADIRU 3, the GPS receiver 2 supplies ADIRU 2. The MMR operates in different modes which are indicated on the GPS MONITOR page:
INITIALIZATION MODE (INIT) When this mode is entered, the GPS hardware and software are initialized. ACQUISITION MODE (ACQ) The MMR enters in this mode after power-up or during long periods of lost satellite signal. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-34-15-20 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GPS - NORMAL OPERATION
It remains in this mode until it is able to track at least 4 satellites, then transfers to NAV mode. To enter navigation mode more quickly, MMR uses initial position, time and altitude from IRS. NAVIGATION MODE (NAV) When the MMR can track 4 or more satellites, it enters NAV mode and continuously supplies data to the ADIRUs. ALTITUDE AIDING (ALTAID) If the MMR can track at least 4 satellites, it uses the GPS altitude and the IR altitude to calculate an altitude bias. If the number of satellites drops to three, the altitude bias is frozen, and the MMR enters ALTAID mode, using the IR altitude (corrected with the bias). FAULT MODE (FAULT) The fault mode is entered when a failure, which may prevent the MMR from transmitting valid data, has been detected.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-34-15-20 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPS - OPERATION IN CASE OF FAILURE
FLIGHT CREW OPERATING MANUAL
OPERATION IN CASE OF FAILURE Ident.: DSC-34-15-30-00001365.0002001 / 14 MAR 11 Applicable to: ALL
If one GPS receiver fails, the three ADIRUs automatically select the only operative GPS receiver. If ADIRU 1 fails, ADIRU 3 is supplied by MMR 1, and ADIRU 2 by MMR 2. To maintain Side 1 and Side 2 segregation, in case ADIRU 2 fails, the ATT HDG selector has to be set to F/O 3, so that ADIRU 3 will be supplied with MMR 2 data. If two ADIRUs fail, the remaining ADIRU is supplied by its own side GPS receiver.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-34-15-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPS - OPERATION IN CASE OF FAILURE
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-15-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPS - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-34-15-40-00001366.0058001 / 30 MAY 11 Applicable to: ALL
E/WD: FAILURE TITLE conditions GPS 1 (2) FAULT FM/GPS POS DISAGREE
AURAL WARNING SINGLE CHIME
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
MASTER LIGHT MASTER CAUTION
SD PAGE CALLED
LOCAL WARNING
NIL
NIL
FLT PHASE INHIB 4, 5, 7, 8 1, 3, 4, 10
DSC-34-15-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPS - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-15-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPS - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-34-15-50-00004070.0013001 / 14 MAR 11 Applicable to: ALL
NORM AC
NAVAIDS
MMR 1 MMR 2
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DC
AC ESS X
EMER ELEC DC ESS
HOT
AC 2
A
DSC-34-15-50 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPS - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-15-50 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
STANDBY INSTRUMENTS
FLIGHT CREW OPERATING MANUAL
COMPASS Ident.: DSC-34-20-00001367.0001001 / 15 FEB 11 Applicable to: ALL
There is a compass located on top of the windshield center post. The deviation card is located above the compass. Note:
Because of the location of the APU power on contactor in the cockpit, the APU start sequence may disturb the compass reading.
BUS EQUIPMENT LIST Ident.: DSC-34-20-00003848.0003001 / 15 FEB 11 Applicable to: ALL
NORM AC
STD BY INST (1)
HORIZON ALTIMETER COMPASS
DC
AC ESS
EMER ELEC DC ESS X
HOT HOT 1 (1)
SHED X
Backup supply.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
DSC-34-20 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
STANDBY INSTRUMENTS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-20 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ISIS
FLIGHT CREW OPERATING MANUAL
INTRODUCTION Ident.: DSC-34-25-00001371.0001001 / 14 FEB 11 Applicable to: ALL
The Integrated Standby Instrument System (ISIS) provides a third source of information and display to the crew. It is mounted in the center of the instrument panel.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-34-25 P 1/10 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ISIS
FLIGHT CREW OPERATING MANUAL
ARCHITECTURE Ident.: DSC-34-25-00001372.0001001 / 14 FEB 11 Applicable to: ALL
GENERAL Ident.: DSC-34-25-00001373.0001001 / 14 FEB 11 Applicable to: ALL
The ISIS system displays the following information: ‐ Attitude ‐ Airspeed and mach ‐ Altitude ‐ Barometric pressure ‐ LS function ‐ Bugs Note:
When leveling the wings after performing a small turn of a small bank angle, the displayed roll attitude may temporarily be incorrect by a few degrees.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B to C →
DSC-34-25 P 2/10 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ISIS
FLIGHT CREW OPERATING MANUAL
(1)
”+”/ “-” activation pushbuttons Two pushbuttons labelled “+” and “–” are used to adjust the level of brightness. The brightness of the screen automatically adjusts after power-up tests. This is because of the photosensitive cell located on the surface of the ISIS system display. The “+” and “–” pushbuttons then allow this initial brightness to be manually adjusted and changed. ATTITUDE
Ident.: DSC-34-25-00001374.0004001 / 14 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← C to D →
DSC-34-25 P 3/10 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ISIS
FLIGHT CREW OPERATING MANUAL
(1)
Fixed aircraft symbol The fixed aircraft symbol is in black, and outlined in yellow.
(2)
Roll scale The roll scale is in white. The markers are at 0 (small yellow triangle), 10, 20, 30, 45, 60 ° of bank.
(3)
Roll index The roll index indicates the bank angle. It is in black, and outlined in white.
(4)
Lateral acceleration index Lateral acceleration index indicates the aircraft’s lateral acceleration. It is represented by a trapezoidal index that moves beneath the roll index.
(5)
Pitch scale The pitch scale indicates the aircraft attitude, and it is in white. The scale has markers every 2.5 °, between 30 ° nose up and 30 ° nose down. If the pitch exceeds 30 °, large (V-shaped) red arrowheads indicate that the attitude is excessive. They also indicate the direction to follow, to resume normal attitude. The minimum displayed pitch scale is -17.5 ° +15 ° at 0 ° pitch.
(6)
ATT RST pushbutton Attitude indication is reset, by pressing “ATT RST” for at least 2 s. The aircraft must be level, during this procedure. During the reset time (approx. 10 s), the “ATT 10 s” message is displayed on the screen. “ATT RST” is also used to realign the system, if excessive aircraft movement is detected during the alignment phase, or after 350 h of continuous electrical supply.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D
DSC-34-25 P 4/10 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ISIS
FLIGHT CREW OPERATING MANUAL
AIRSPEED Ident.: DSC-34-25-00001375.0002001 / 14 FEB 11 Applicable to: ALL
(1)
Airspeed scale A white scale moves in front of a yellow triangle indicating the airspeed. The scale ranges from 5 to 250 kt, with a mark every 5 kt, and from 250 to 520 kt, with a mark every 10 kt.
(2)
Mach Number The Mach number is displayed in green when greater than 0.5, but disappears only when it goes lower than 0.45.
(3)
Speed bug When a speed bug is entered via the BUGS function, the corresponding speed mark is indicated by a cyan dash.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E
DSC-34-25 P 5/10 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ISIS
FLIGHT CREW OPERATING MANUAL
ALTITUDE Ident.: DSC-34-25-00001376.0003001 / 14 FEB 11 Applicable to: ALL
(1)
Altitude indication The altitude indication is given as a white moving scale, and a green digital readout on a grey background. The altitude scale ranges from -2 000 to 50 000 ft every 100 ft, with altitude digital indications every 500 ft. “NEG” appears in white in the negative altitudes window. If the option is installed, the altitude is also given in meters. The altitude box changes to cyan, when it also corresponds to a bug value.
(2)
Barometric reference The barometric reference pressure is displayed in cyan, in hectoPascal (hPa). It corresponds to either the selected barometric pressure, or the standard pressure. The barometric pressure ranges from 745 to 1 100 hPa.
(3)
Barometric selection knob It enables the selection of a barometric pressure, setting a variation of 10 hPa per rotation of the knob. The standard barometric pressure can be selected by pressing the barometric knob. “STD” is then displayed in place of the pressure value. Pressing the knob again will display the selected barometric pressure.
(4)
Altitude bug When an altitude bug is entered through the bugs function, the corresponding altitude mark is indicated by a cyan dash, or a cyan box, when the dash covers the digital indication on the scale.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F
DSC-34-25 P 6/10 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ISIS
FLIGHT CREW OPERATING MANUAL
LANDING SYSTEM FUNCTION Ident.: DSC-34-25-00001377.0002001 / 14 FEB 11 Applicable to: ALL
(1)
Localizer scale and index
(2)
Glideslope scale and index The deviation scales appear when the LS pushbutton is pressed. The indexes appear when the Glideslope and Localizer signals are valid and deviation scales are displayed.
(3)
LS selection pushbutton Pressing the LS pushbutton will display the ILS scales. Pressing it again will de-select the ILS scales. CAUTION
Do not use the ISIS LS for takeoff using the localizer of the opposite runway, or for a back-course localizer approach. The LOC deviations are given in the wrong sense.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
G
DSC-34-25 P 7/10 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ISIS
FLIGHT CREW OPERATING MANUAL
BUGS FUNCTION Ident.: DSC-34-25-00001378.0001001 / 14 MAY 12 Applicable to: ALL
(1)
BUGS function selection pushbutton Pressing the BUGS pushbutton will activate the BUGS function and display the bug values to be selected.
(2)
SPD BUG and ALT BUG columns The SPD BUG column gives four speed values (in knots) that can be selected by the crew. The ALT BUG column gives two altitude values (feet) to be selected by the crew.
(3)
BUGS value selection knob It allows the bug value to be set by rotating the BARO knob. This value cannot be lower than 30 kt for a speed bug, or a negative value for an altitude bug. Pressing the BARO setting knob, once a bug value box is activated, will deselect the bug value. The “OFF” label comes on close to the activated box. The entered values are memorized by the system, when exiting the screen, by pressing the BUGS pushbutton (1), or after 15 s without any pilot action.
(4)
“+”/”-” box activation buttons Access from one box to another is obtained by pressing the “+” or “–” pushbutton. When a bug value is entered, access to the next box is obtained by pressing the “–” pushbutton. The box becomes active and flashes. The “+” pushbutton can be used to return to a previous box.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
H→
DSC-34-25 P 8/10 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ISIS
FLIGHT CREW OPERATING MANUAL
Note:
Use of the ISIS bugs function is not recommended because, in the event that both PFDs are lost in flight, when the ISIS bugs were previously set for takeoff, then for the approach, the bugs would remain at the takeoff characteristic speed settings. FLAGS
Ident.: DSC-34-25-00001379.0003001 / 14 FEB 11 Applicable to: ALL
(1)
ATT flag (red) When attitude data is lost, the red ATT flag appears.
(2)
SPD flag (red) When airspeed data is lost, the red SPD flag appears.
(3)
M flag (red) When mach number is lost, the red M flag appears.
(4)
ALT flag (red) When altitude data is lost, the red ALT flag appears.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← H to I →
DSC-34-25 P 9/10 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ISIS
FLIGHT CREW OPERATING MANUAL
(5)
G/S flag (red) When glideslope information is lost, the red G/S flag appears.
(6)
LOC flag (red) When localizer data is lost, the red LOC flag appears.
(7)
ATT: RST (yellow) The “ATT: RST” flag appears: ‐ When excessive aircraft movement is detected during the alignment phase, or ‐ After 350 h of continuous electrical supply, or ‐ When the “WAIT ATT” flag is displayed during more than 10 s . In both cases, press the ATT RST pb to reset/realign and recover the attitude indication.
(8)
MAINT flag (white) Failure not affecting ISIS operation. Service ISIS, when convenient.
(9)
OUT OF ORDER (white) When an internal failure of the ISIS indicator occurs, the “OUT OF ORDER” message appears, accompagnied by a fault code.
(10) WAIT ATT flag (yellow) If the ISIS looses attitude data, its entire sphere is cleared to display the: “WAIT ATT” flag. ‐ If the “WAIT ATT” flag is displayed during less than 10 s, a normal operation is recovered. ‐ If attitude data are lost for more than 10 s, the “WAIT ATT” flag is then replaced by the “ATT: RST” flag. (11) ATT 10 s flag (yellow) This count down flag appears, when the flight crew press the ATT RST pb, in order to indicate that the attitude reset function is in progress.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←I
DSC-34-25 P 10/10 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
RADIO NAV - TUNING
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-34-30-10-00001380.0001001 / 09 DEC 09 Applicable to: ALL
The FMGC is the basic means for tuning navaids. Three modes of tuning are available. AUTOMATIC TUNING Ident.: DSC-34-30-10-00001381.0001001 / 09 DEC 09 Applicable to: ALL
In normal operation, the FMGC tunes navaids automatically, with each FMGC controlling its own receivers. If one FMGC fails, the remaining one controls both sides receivers. MANUAL TUNING Ident.: DSC-34-30-10-00001382.0001001 / 09 DEC 09 Applicable to: ALL
The crew can use the MCDU to override the FMGC’s automatic selection and tuning of navaids and select a specific navaid for visual display. This does not affect the automatic function of the FMGC. Any entry on one MCDU is sent to both FMGC in dual mode, or the remaining FMGC in single. BACK UP TUNING Ident.: DSC-34-30-10-00001383.0001001 / 15 FEB 11 Applicable to: ALL
If both FMGCs fail, the flight crew can use the RMPs (Radio Management Panels 1 and 2) on the pedestal for back up tuning. The CAPT RMP controls VOR 1 and ADF 1 . The F/O RMP controls VOR 2 and ADF 2 . Either RMP controls both ILSs (provided NAV back up is selected on RMP 1 and RMP 2). RMP 3 is not used for navaids tuning.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to D
DSC-34-30-10 P 1/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
RADIO NAV - TUNING
FLIGHT CREW OPERATING MANUAL
ARCHITECTURE Ident.: DSC-34-30-10-00001384.0001001 / 14 MAY 12 Applicable to: ALL
NORMAL OPERATION
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E→
DSC-34-30-10 P 2/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
RADIO NAV - TUNING
FLIGHT CREW OPERATING MANUAL
FMGC 1 FAILURE
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-34-30-10 P 3/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
RADIO NAV - TUNING
FLIGHT CREW OPERATING MANUAL
BACK UP TUNING
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E
DSC-34-30-10 P 4/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
RADIO NAV - NAVAIDS
FLIGHT CREW OPERATING MANUAL
VOR Ident.: DSC-34-30-20-00001385.0003001 / 15 FEB 11 Applicable to: ALL
The aircraft has two VOR receivers. (For tuning instructions, Refer to DSC-34-30-10 General). The Navigation Displays (NDs) show VOR1 and VOR2 information, in accordance with the position of the ADF/VOR selectors on the EFIS control panel (Refer to DSC-31-45 ROSE Modes). ILS Ident.: DSC-34-30-20-00001386.0004001 / 15 FEB 11 Applicable to: ALL
The aircraft has two ILS receivers. Each ILS receiver is integrated in a modular avionics unit called MMR (Multi Mode Receiver) (ILS1 receiver in MMR1, ILS2 receiver in MMR2). (For tuning instructions, Refer to DSC-34-30-10 General). ‐ PFD1 and ND2 display ILS1 information. ‐ PFD2 and ND1 display ILS2 information. ‐ The flight crew can put the same ILS information on each PFD by pressing the LS button on the EFIS control panel (the green bars come on). ‐ The NDs display ILS information, if the flight crew selects the ROSE LS mode on the EFIS control panel (Refer to DSC-31-50 EFIS Control Panel). ADF Ident.: DSC-34-30-20-00001387.0007001 / 15 FEB 11 Applicable to: ALL
The aircraft has two ADF systems. (For tuning instructions, Refer to DSC-34-30-10 General). The NDs display ADF information, depending on the position of the ADF/VOR selectors on the EFIS control panel (Refer to DSC-31-45 ROSE Modes). DME Ident.: DSC-34-30-20-00001388.0002001 / 15 FEB 11 Applicable to: ALL
The aircraft has two DMEs. The frequency that is automatically set on the DME corresponds to the one that is set on the VOR or ILS.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to D →
DSC-34-30-20 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
RADIO NAV - NAVAIDS
FLIGHT CREW OPERATING MANUAL
The NDs can display VOR DME information, and the PFDs can display ILS/MLS DME information (Refer to DSC-31-40-A Trajectory Deviation - ILS Approach). MARKER BEACON Ident.: DSC-34-30-20-00001389.0001001 / 09 DEC 09 Applicable to: ALL
One marker beacon system is included in VOR receiver 1. The PFD displays the outer, middle, and inner marker signals (Refer to DSC-31-40-A Trajectory Deviation - ILS Approach).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← D to E
DSC-34-30-20 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
RADIO NAV - CONTROLS AND INDICATORS
DIGITAL DISTANCE AND RADIO MAGNETIC INDICATOR (DDRMI) Ident.: DSC-34-30-30-00001390.0002001 / 14 MAY 12 Applicable to: ALL
(1)
Compass card ADIRU 1 normally supplies the signal that positions the compass card. ADIRU 3 supplies it when selected by the ATT HDG SWITCHING selector.
(2)
Bearings pointers Indicate the magnetic bearing to the station received by VOR 1 or ADF 1 (dashed pointer) and VOR 2 or ADF 2 (double pointer). Note:
(3)
Depending on the quality of the VOR beacon's signal, and mainly at distances greater than 25 nm from the station, the processing of the signal, on aircraft equipped with COLLINS or BENDIX VOR may lead to bearing pointer oscillations.
VOR/ADF flags The indicators display these flags if: ‐ the VOR or ADF receiver fails (VOR/ADF selector position indicates the failed receiver) ‐ the RMI has an internal failure ‐ the heading signal from ADIRS is not valid ‐ the power supply fails. As long as the flag shows, the relevant pointer remains at the last valid position.
(4)
HDG flag Appears, along with an associated VOR/ADF flags display, when:
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-34-30-30 P 1/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
RADIO NAV - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
‐ The heading signal from the supplying ADIRS is not valid; ‐ The RMI has an internal failure; ‐ The power supply fails. (5)
DME 1(2) counters The counters indicate distances in NM and 1/10th at less than 20 nm. At less than 1 nm, 0 is shown.
(6)
VOR/ADF sel ‐ VOR 1 or ADF 1 on the dashed pointer. ‐ VOR 2 or ADF 2 (if not installed, then ADF 1) on the double pointer. RADIO MANAGEMENT PANEL (RMP)
Ident.: DSC-34-30-30-00001391.0001001 / 14 MAY 12 Applicable to: ALL
(1)
ON/OFF sw This switch controls the power supply to the panel.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← A to B →
DSC-34-30-30 P 2/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(2)
RADIO NAV - CONTROLS AND INDICATORS
NAV key (transparent switchguard) ‐ Pressing this key engages the radio navigation backup mode. It takes control of the VOR, ILS, MLS, and ADF receivers away from the FMGC and gives it to the RMP. ‐ The green monitor light comes on. ‐ Pressing the NAV key a second time returns control of the navigation radios to the FMGC. Note:
‐ The flight crew must select this backup tuning mode on both RMP1 and RMP2 if both FMGCs or both MCDUs fail. In the emergency electrical configuration, only RMP1 receives power ‐ Pressing the NAV key on RMP3 has no effect ‐ In the NAV backup mode, the flight crew can select radio communication systems as it would in the normal mode. Setting one RMP to NAV backup mode removes navaids tuning from both FMGCs. ‐ When the flight crew uses an RMP to turn an ILS/DME, the PFDs do not display the DME distance.
(3)
STBY NAV keys When the NAV key is on and the flight crew presses one of these STBY NAV keys, the ACTIVE window displays the frequency to which that receiver is tuned. The green monitor light on the selected key comes on, and the one on the previously selected STBY NAV or COM key goes out.
(4)
Frequency selector knob Two concentric knobs allow the flight crew to preselect frequencies for communication radios and stand-by navigation systems and select courses for VOR and ILS. The desired frequency or course is set in the STBY/CRS window. ‐ Setting frequency : The outer knob controls the most significant digits, the inner knob controls the least significant digits. A rate multiplier speeds up the tuning when the knob is rotated rapidly. ‐ Setting course : Selected by inner knob only.
(5)
Transfer key The flight crew presses this key to interchange ACTIVE and STBY frequencies. This action tunes the selected receiver to the new ACTIVE frequency.
(6)
STBY/CRS window The flight crew can make the frequency displayed in this window become the active frequency by pressing the transfer key, or change it by rotating the tuning knob. If this window displays a course, then the ACTIVE window displays the associated frequency.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
DSC-34-30-30 P 3/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
RADIO NAV - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
Note:
If the STBY/CRS window is displaying a course, then pressing the transfer key displays the active frequency in both windows.
(7)
ACTIVE window This window displays the frequency of the selected navaid, which is identified by a green monitor light on the selection key.
(8)
BFO key Pressing this key activates the BFO (Beat Frequency Oscillator), if the ADF receiver is selected. The green monitor light comes on. For most ADF, with BFO activated, the audio identification is heard. However there are some ADF where the BFO must be deactivated in order to hear the audio identification. WARNINGS AND CAUTIONS
Ident.: DSC-34-30-30-00013051.0002001 / 15 FEB 11 Applicable to: ALL
E/WD: FAILURE TITLE conditions
ILS 1(2)(1+2) FAULT MLS 1(2) FAULT
AURAL WARNING
MASTER LIGHT
SD PAGE CALLED
LOCAL WARNING
FLT PHASE INHIB
SINGLE CHIME
MASTER CAUT
NIL
Flag on PFD and ND
3, 4, 5
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← B to C
DSC-34-30-30 P 4/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
RADIO NAV - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-34-30-40-00001405.0005001 / 15 FEB 11 Applicable to: ALL
NORM AC
NAVAIDS
VOR 1 VOR 2 MMR 1 MMR 2 ADF 1 ADF 2 DME 1 DME 2
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DC
AC ESS X
EMER ELEC DC ESS
HOT
AC 2 X AC 2 SHED AC 2 SHED AC 2
A
DSC-34-30-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
RADIO NAV - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-30-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
RADIO ALTIMETER - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-34-40-10-00001392.0001001 / 03 FEB 11 Applicable to: ALL
The aircraft has two radio altimeters. Normally, CAPT's PFD displays the RA1 height, and the F/O’s PFD displays the RA2 height. If either radio altimeter fails, both PFDs display the height from the remaining one. INDICATIONS ON PFD Ident.: DSC-34-40-10-00001393.0001001 / 09 DEC 09 Applicable to: ALL
(Refer to DSC-31-40 General).
AUTOMATIC CALL OUT Ident.: DSC-34-40-10-A-NG00094 Applicable to: ALL Ident.: DSC-34-40-10-A-00001394.0001001 / 09 DEC 09
GENERAL The FWC generates a synthetic voice for radio height announcement below 2 500 ft. These announcements come through the cockpit loudspeakers, even if the speakers are turned off. Ident.: DSC-34-40-10-A-00001395.0002001 / 03 FEB 11
PREDETERMINED CALL OUT The altitude call out uses the following predetermined threshold: Height (ft)
Callout TWO THOUSAND FIVE HUNDRED OR TWENTY FIVE HUNDRED TWO THOUSAND ONE THOUSAND FIVE HUNDRED FOUR HUNDRED THREE HUNDRED TWO HUNDRED ONE HUNDRED FIFTY FORTY THIRTY TWENTY TEN FIVE Continued on the following page
2 500 2 000 1 000 500 400 300 200 100 50 40 30 20 10 5
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to C →
DSC-34-40-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
RADIO ALTIMETER - DESCRIPTION Continued from the previous page Callout HUNDRED ABOVE MINIMUM
Height (ft) DH (or MDA/MDH) + 100 DH (or MDA/MDH)
Note:
The reference altitude for callouts is the radio altitude for precision approaches (DH), and baro altitude (MDA/MDH) for non precision approaches.
Pin programming enables Operators to select the required callouts. If the aircraft remains at a height that is in the detection zone for a height callout, the corresponding message is repeated at regular intervals. Ident.: DSC-34-40-10-A-00001396.0001001 / 09 DEC 09
INTERMEDIATE CALL OUT If time between two consecutive predetermined call outs exceeds a certain threshold, the present height is repeated at regular intervals. The threshold is : 11 s above 50 ft 4 s below 50 ft The repeating interval is 4 s. Ident.: DSC-34-40-10-A-00001397.0001001 / 09 DEC 09
RETARD ANNOUNCEMENT The loudspeaker announces RETARD at 20 ft or at 10 ft if autothrust is active and one autopilot is in LAND mode.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C
DSC-34-40-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
RADIO ALTIMETER - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-34-40-20-00001398.0002001 / 03 FEB 11 Applicable to: ALL
E/WD: FAILURE TITLE conditions
RA 1(2) FAULT RA DEGRADED
In case a significant discrepancy occurs in flight between the two radio-altimeters.
AURAL SD PAGE MASTER LIGHT WARNING CALLED SINGLE CHIME MASTER CAUT NIL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
NIL
A
NIL
LOCAL WARNING
NIL
FLT PHASE INHIB 3, 4, 5, 8 2 to 8
DSC-34-40-20 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
RADIO ALTIMETER - WARNINGS AND CAUTIONS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-40-20 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
RADIO ALTIMETER - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-34-40-30-00001406.0001001 / 03 FEB 11 Applicable to: ALL
NORM AC
RADIO ALTIMETER
RA 1 RA 2
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DC
AC ESS
EMER ELEC DC ESS
HOT
AC1 AC2
A
DSC-34-40-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
RADIO ALTIMETER - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-40-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ATC - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
DESCRIPTION Ident.: DSC-34-50-10-00001399.0002001 / 15 FEB 11 Applicable to: ALL
The aircraft has two ATC transponders which are controlled by a dual control box on the center pedestal. Only the selected ATC transponder operates. The associated ADIRS (1 for transponder 1, etc ...) supplies the altitude for altitude reporting. The ATC transponder is capable of enhanced surveillance: It transmits the following parameters upon ground request: ‐ Indicated airspeed, Mach number, and baro vertical speed, that are all supplied by the ADRs. ‐ Magnetic heading, roll angle, ground speed, track angle, track angle rate, and inertial vertical speed, that are all supplied by the IRs. ‐ Selected altitude and barometric reference settings supplied by the FCUs. In the case of an ADR (1 or 2) failure, ADR 3 replaces the faulty ADR, when the AIR DATA SWITCHING Selector is set to CAP on 3 or F/O on 3. IR/FCU parameters are only transmitted to: ‐ ATC 1 by IR 1/FCU 1 ‐ ATC 2 by IR 2/FCU 2
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-34-50-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ATC - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-50-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ATC - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
CONTROL PANEL Ident.: DSC-34-50-20-00001400.0026001 / 14 MAY 12 Applicable to: ALL
(1)
ATC selector This switch selects transponder 1 or 2.
(2)
Mode sel STBY ON AUTO: In flight AUTO: On ground
(3)
(4)
ALT RPTG sw ON : OFF :
: : : :
BOTH ATC transponders are electrically supplied but do not operate. Selected transponder operates. Selected transponder operates. Selected transponder only operates in mode S (Selective aircraft interrogation mode).
The transponder sends barometric standard altitude data. No altitude data transmission. If the TCAS is installed, the upper ECAM displays "TCAS STBY" in green.
IDENT sw The flight crew presses this button to send the aircraft identification signal.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-34-50-20 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ATC - CONTROLS AND INDICATORS
(5)
Code display The window displays the selected code.
(6)
Keyboard The flight crew uses these pushbuttons to set the code assigned by ATC.
(7)
CLR pb The flight crew uses this pushbutton to clear the code display. Note:
(8)
As long as the four figures of the new code are not entirely written, the previous code remains.
ATC FAIL This light comes on if the selected transponder fails.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-34-50-20 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ATC - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-34-50-50-00001407.0001001 / 15 FEB 11 Applicable to: ALL
NORM AC
ATC
ATC 1 ATC 2
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DC
AC ESS SHED
EMER ELEC DC ESS
HOT
AC 2
A
DSC-34-50-50 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
ATC - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-50-50 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
WEATHER RADAR - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
DESCRIPTION Ident.: DSC-34-60-10-00001401.0002001 / 16 FEB 11 Applicable to: ALL
The aircraft has two weather radar systems. Only one receiver in working at a time. It can display the weather image on the ND, in any ND mode except PLAN. Each pilot may remove the weather image from their ND by setting the associated brightness control to the minimum (Refer to DSC-31-50 Other EFIS Controls). Note:
Some aircraft may be fitted with one weather radar only.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-34-60-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
WEATHER RADAR - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-60-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WEATHER RADAR - CONTROLS AND INDICATORS
CONTROL PANEL Ident.: DSC-34-60-20-00001402.0002001 / 14 MAY 12 Applicable to: ALL
(1)
SYS toggle switch This switch selects one radar, or turns OFF both radars.
(2)
GAIN knob It adjusts the receiver's sensitivity in weather mode (WX), or in ground mapping mode (MAP). CAL is the normal position of the knob. It adjusts the gain to a calibrated setting.
(3)
Mode selector WX : Weather mode: Weather mode: colors indicate the density of precipitation (black for the lowest intensity, green, amber and red indicating progressively for higher intensities). WX + T : The screen only displays turbulence areas (in precipitation areas) in magenta (within 40 nm). TURB : The screen only shows turbulence areas. MAP : Radar operates in ground mapping mode: black indicates water, green indicates the ground, and amber indicates cities and mountains.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-34-60-20 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WEATHER RADAR - CONTROLS AND INDICATORS
(4)
TILT knob This knob controls the antenna tilt. Radar 1 depends on ADIRS 1. Radar 2 depends on ADIRS 2. ADIRS 3 replaces either one of the ADIRS, if ATT HDG selector is set to CAPT 3 or F/O 3. Zero represents the horizon, as seen by the ADIRS.
(5)
MULTISCAN toggle switch AUTO : Automatically activates tilt to optimize weather detection and minimize ground clutter. MAN : When set to MAN, the crew can then manually adjust the tilt by using the TILT knob.
(6)
GCS toggle switch The Ground Clutter Suppression (GCS) toggle switch is spring-loaded to the AUTO position. AUTO : ‐ If MULTISCAN toggle switch is set to AUTO, the radar is in normal use. Ground clutter is not displayed on the screen ‐ If MULTISCAN toggle switch is set to MAN, the GCS switch has no utility. Ground clutter is displayed on the screen. OFF : Ground clutter is displayed on the screen.
(7)
PWS toggle switch (only operative, if the predictive windshear function is installed) AUTO : Activates the predictive windshear function: windshear areas are detected by antenna scanning below 2 300 ft RA, even if the SYS switch is set to OFF. They are displayed on the ND, if below 1 500 ft. OFF : The predictive windshear function is off.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-34-60-20 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WEATHER RADAR - PREDICTIVE WINDSHEAR SYSTEM
GENERAL Ident.: DSC-34-60-30-00006420.0001001 / 16 FEB 11 Applicable to: ALL
The weather radars have a Predictive Windshear System (PWS) that operates when: ‐ The PWS switch is in the AUTO position (Even if the weather radar is OFF), and ‐ The aircraft is below 2 300 ft AGL, and ‐ The ATC is switched to the ON, or AUTO, or XPDR, or XPNDR, position (depending on the ATC panel), and ‐ Either engine is running. Note:
When two weather radars are installed, if the selected weather radar fails, the PWS function is recovered by selecting the non-failed weather radar on the control panel.
The system scans the airspace, within a range of 5 nm ahead of the aircraft, for windshears. Below 1 500 ft, when the system detects windshear, depending on the range selected on the ND, a warning, caution, or advisory message appears on the ND. Predictive windshear warnings and cautions are associated with an aural warning. WINDSHEAR ALERTS DURING TAKEOFF ROLL, UP TO 100 KNOTS Ident.: DSC-34-60-30-00006425.0001001 / 14 MAY 12 Applicable to: ALL
During the takeoff roll, up to 100 kt, both warnings and cautions are available within a range of 3 nm.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
DSC-34-60-30 P 1/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WEATHER RADAR - PREDICTIVE WINDSHEAR SYSTEM
WINDSHEAR ALERTS ABOVE 50 FEET Ident.: DSC-34-60-30-00006422.0001001 / 14 MAY 12 Applicable to: ALL
During final approach, the visual and aural warning alerts are downgraded to caution alerts between 370 ft AGL and 50 ft AGL, and range between 1.5 nm and 0.5 nm. WINDSHEAR ALERTS INHIBITION Ident.: DSC-34-60-30-00006426.0002001 / 16 FEB 11 Applicable to: ALL
At takeoff, alerts are inhibited above 100 kt and up to 50 ft. During landing, alerts are inhibited below 50 ft. Alert Level Warning (Approach) Warning (Takeoff)
Aural Warning «GO AROUND WINDSHEAR AHEAD» «WINDSHEAR AHEAD» (twice)
PFD
ND (Refer to DSC-31-45 Predictive Windshear System)
W/S AHEAD (red)
Windshear icon
W/S AHEAD (red)
Windshear icon Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C to D →
DSC-34-60-30 P 2/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Alert Level Caution Advisory
WEATHER RADAR - PREDICTIVE WINDSHEAR SYSTEM
Aural Warning
PFD
«MONITOR RADAR DISPLAY» Nil
Continued from the previous page ND (Refer to DSC-31-45 Predictive Windshear System)
W/S AHEAD (amber)
Windshear icon
Nil
Windshear icon
The aural alerts of the Predictive Windshear System (PWS): ‐ Have priority over TCAS, GPWS, and other FWC aural warnings ‐ Are inhibited by windshear detection, via the FAC, stall warnings and aural messages.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D
DSC-34-60-30 P 3/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WEATHER RADAR - PREDICTIVE WINDSHEAR SYSTEM
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-60-30 P 4/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
WEATHER RADAR - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-34-60-40-00001403.0001001 / 17 NOV 11 Applicable to: ALL
E/WD: FAILURE TITLE Conditions
PRED. W/S DET FAULT
AURAL WARNING
MASTER LIGHT
SD PAGE CALLED
LOCAL WARNING
FLT PHASE INHIB
SINGLE CHIME
MASTER CAUTION
NIL
NIL
3, 4, 5, 8
MEMO DISPLAY The “PRED W/S OFF” message appears, when windshear is set to OFF on the weather radar panel. The “PRED W/S OFF”, message appears in green during flight phases 2 and 6. It appears in amber: ‐ In flight phases 3, 4, 5, 7, 8, and 9 ‐ When the T.O. CONFIG pb is pressed during phase 2.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-34-60-40 P 1/2 25 NOV 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WEATHER RADAR - WARNINGS AND CAUTIONS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-60-40 P 2/2 25 NOV 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
WEATHER RADAR - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-34-60-50-00001410.0001001 / 16 FEB 11 Applicable to: ALL
NORM AC WEATHER RADAR
WX 1 WX 2
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DC
AC ESS
EMER ELEC DC ESS
HOT
AC1 AC2
A
DSC-34-60-50 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
WEATHER RADAR - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-60-50 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPWS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
DESCRIPTION Ident.: DSC-34-70-10-00001409.0012001 / 17 MAR 11 Applicable to: ALL
The Ground Proximity Warning System (GPWS) generates aural and visual warnings, when one of the following conditions occurs between radio altitudes 30 ft and 2 450 ft. ‐ Mode 1: Excessive rate of descent. ‐ Mode 2: Excessive terrain closure rate. ‐ Mode 3: Altitude loss after takeoff, or go-around. ‐ Mode 4: Unsafe terrain clearance when not in landing configuration. ‐ Mode 5: Too far below glideslope. In addition to the basic GPWS functions, the GPWS has an enhanced function (EGPWS) which provides, based on a worldwide terrain database: ‐ A Terrain Awareness Display (TAD), which predicts the terrain conflict, and displays the terrain on the ND. ‐ A Terrain Clearance Floor (TCF), which improves the low terrain warning during landing. The EGPWS uses the geometric altitude. The geometric altitude is calculated by means of a specific algorithm that uses the following as inputs: The pressure altitude, GPS altitude, radio altitude, and data from the terrain database. The cockpit loudspeakers broadcast, even if turned off, the aural warning or caution messages associated with each mode. The audio volume of these messages is not controlled by the loudspeaker volume knobs. (These knobs only allow volume adjustment for radio communication). PULL UP or GPWS lights, on the Captain and First Officer instrument panels, come on to give a visual indication depending on the engaged GPWS mode. Note:
A number of airports throughout the world have approaches or departures that are not entirely compatible with standard GPWS operation. These airports are identified in the envelope modulation database, in such a way that, when the GPWS recognizes such an airport, it modifies the profile to avoid nuisance warnings.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-34-70-10 P 1/4 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPWS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
SCHEMATIC Ident.: DSC-34-70-10-00001411.0007001 / 17 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
DSC-34-70-10 P 2/4 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPWS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-34-70-10 P 3/4 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPWS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-70-10 P 4/4 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPWS - GPWS BASICS MODES
FLIGHT CREW OPERATING MANUAL
MODE 1 : EXCESSIVE RATE OF DESCENT Ident.: DSC-34-70-20-00001412.0005001 / 14 MAY 12 Applicable to: ALL
Mode 1 has two boundaries. Penetration of the first boundary generates a repeated aural alert “SINK RATE” and causes the GPWS lights to come on. Penetration of the second boundary generates a repetitive “PULL UP” and illuminates both PULL UP lights. The upper cut-off limit is 2 450 ft radio altitude. The lower cut-off limit is 10 ft radio altitude.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-34-70-20 P 1/6 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GPWS - GPWS BASICS MODES
MODE 2 : EXCESSIVE TERRAIN CLOSURE RATE Ident.: DSC-34-70-20-00001413.0055001 / 14 MAY 12 Applicable to: ALL
(*)
The upper cut-off limit varies from 1 650 to 2 450 ft radio altitude, depending on speed (between 220 to 310 kt). At certain airports, the upper boundary may be lowered down to 1 250 ft to reduce the warning sensitivity and minimize the nuisance warnings.
2A — FLAPS NOT IN LANDING CONFIGURATION, AND AIRCRAFT NOT ON THE GLIDESLOPE BEAM Penetration of the boundary causes the GPWS lights to come on, and generates the repeated aural alert: “TERRAIN”. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
DSC-34-70-20 P 2/6 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GPWS - GPWS BASICS MODES
After “TERRAIN” has sounded twice, the warning switches to “PULL UP”, and is continually repeated until the aircraft leaves the warning envelope. In addition, the PULL UP lights come on. After the aircraft leaves the boundary, the GPWS lights stay on and the “TERRAIN” aural message persists. These alerts stop when the aircraft increases either the barometric or inertial altitude by 300 ft. If it enters another alert region during this altitude-gain time, then the whole process begins again with a new reference altitude for the 300 ft altitude gain. The new enhanced operational upper limit is reduced to 1 250 ft and to 789 ft in final approach, when the enhanced functions and the Geometric Altitude are of high integrity. 2B — FLAPS ARE IN LANDING CONFIGURATION Lowering the flaps to the landing position automatically switches GPWS to Mode 2B. In this case lower boundary varies between 200 ft and 600 ft depending on radio altitude rate of change. In ILS approach (glide slope deviation < ± 2 dots) the lower boundary is fixed at 30 ft . When the aircraft enters the envelope, the alert is the same as for mode 2A. When gear and flaps are in the landing configuration, the aural message is “TERRAIN ” only and is not followed by “PULL UP” if the aircraft remains within the envelope. MODE 3 : ALTITUDE LOSS AFTER TAKEOFF Ident.: DSC-34-70-20-00001414.0004001 / 18 MAR 11 Applicable to: ALL
If the aircraft descends during the initial takeoff climb or during a go around, the PULL UP light come on and the aural alert “DON’T SINK” sounds repeatedly. The lower cut-off limit is 10 ft radio altitude. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
DSC-34-70-20 P 3/6 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GPWS - GPWS BASICS MODES
Mode 3 is desensitized in accordance with the time accumulated after departure and the radio altitude. MODE 4 : UNSAFE TERRAIN CLEARANCE WHEN NOT IN LANDING CONFIGURATION Ident.: DSC-34-70-20-00001415.0003001 / 17 MAR 11 Applicable to: ALL
4A - LANDING GEAR UP AND FLAPS NOT IN LANDING CONFIGURATION.
Two aural warnings may be triggered, depending on the area: “TOO LOW-GEAR” or “TOO LOW-TERRAIN”. In addition, the GPWS lights come on.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← C to D →
DSC-34-70-20 P 4/6 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GPWS - GPWS BASICS MODES
4B - LANDING GEAR DOWN, AND FLAPS NOT IN LANDING CONFIGURATION OR, LANDING GEAR UP, AND FLAPS IN LANDING CONFIGURATION.
Three aural warnings may be generated, depending on the area and configuration: “TOO LOW-GEAR”, “TOO LOW-FLAPS”, or “TOO LOW-TERRAIN”. In addition, the GPWS lights come on. If the enhanced GPWS functions and the geometric altitude are of high integrity, the upper operational limit is reduced to 500 ft. If not, it is only reduced to 800 ft when an overflight is detected. 4C — LANDING GEAR UP, OR FLAPS NOT IN LANDING CONFIGURATION.
If the aircraft starts an inadvertent controlled flight into the ground, during takeoff and climb, and penetrates the boundary, then the GPWS lights come on, and the “TOO LOW TERRAIN” aural alert sounds repeatedly. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D
DSC-34-70-20 P 5/6 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPWS - GPWS BASICS MODES
FLIGHT CREW OPERATING MANUAL
MODE 5 : DESCENT BELOW GLIDESLOPE Ident.: DSC-34-70-20-00001416.0002001 / 17 MAR 11 Applicable to: ALL
Note:
Normally, the glideslope alert is only triggered with the gear down. For a few airports, the gear down logic requirement is deleted and other upper limits are used to increase the warning envelope.
In both areas, the alert is a repeated “GLIDESLOPE” aural message, and the GPWS lights come on. The loudness of the aural message increases, when the aircraft enters the hard warning areas. The mode is armed, when ILS 1 receives a valid signal. Pressing the GPWS pushbutton cancels the warning. This is temporary; the mode is automatically reactivated for a new envelope. The upper cut-off limit is 1 000 ft radio altitude. The lower cut-off limit is 30 ft radio altitude.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E
DSC-34-70-20 P 6/6 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPWS - EGPWS FUNCTIONS
FLIGHT CREW OPERATING MANUAL
TERRAIN AWARENESS AND DISPLAY Ident.: DSC-34-70-30-00001417.0113001 / 17 MAR 11 Applicable to: ALL
The Terrain Awareness and Display (TAD) function computes a caution and a warning envelope in front of the aircraft, depending on the aircraft altitude, the nearest runway altitude, the distance to the nearest runway threshold, the ground speed, and the turn rate. When the boundary of these envelopes conflicts with the terrain, or with an obstacle memorized in the database, the system generates the relevant alert: Alert Level
ND (Refer to DSC-31-45 Flags and Messages Displayed on ND)
Aural Warning
TERRAIN AHEAD, PULL UP
‐ Automatic terrain display See * ‐ Solid red areas ‐ TERR AHEAD (red)
OBSTACLE AHEAD, PULL UP
‐ Automatic terrain display See * ‐ Solid red areas ‐ OBST AHEAD (red)
TERRAIN AHEAD
‐ Automatic terrain display See * ‐ Solid yellow areas ‐ TERR AHEAD (amber)
OBSTACLE AHEAD
‐ Automatic terrain display See * ‐ Solid yellow areas ‐ OBST AHEAD (amber)
Warning
Caution
Local Warning
On each pilot’s instrument panel, The pushbutton light comes on.
* When the TERR pb-sw ON ND is set to ON, and ARC or ROSE mode is selected, the ND displays the terrain and the obstacles memorized in the database, depending on the aircraft’s position. The terrain is displayed in various densities of green, yellow, red, or magenta, depending on the threat (Refer to DSC-31-45 Flags and Messages Displayed on ND). If an alert is generated (caution or warning), and TERR pb-sw ON ND is not selected, the terrain and the obstacles are automatically displayed, and the ON light of the TERR pb-sw ON ND comes on.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-34-70-30 P 1/6 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Note:
GPWS - EGPWS FUNCTIONS
1. When TERR pb-sw ON ND is selected, the weather radar image is not displayed. 2. The Geometric Altitude function can protect against certain BARO setting errors, provided the components used to compute the Geometric Altitude are valid and accurate enough. 3. The TAD and Terrain Clearance Floor (TCF) functions operate using the pure lateral GPS position and, the FMS1 position as backup.
In case of low accuracy of the aircraft position computed by the EGPWS, the enhanced modes of the EGPWS are automatically deactivated. The five GPWS modes remain active. TERRAIN CAUTION AND WARNING ENVELOPE Ident.: DSC-34-70-30-00006161.0002001 / 17 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← A to B →
DSC-34-70-30 P 2/6 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPWS - EGPWS FUNCTIONS
FLIGHT CREW OPERATING MANUAL
VERTICAL ENVELOPE
HORIZONTAL ENVELOPE
TERRAIN CLEARANCE FLOOR Ident.: DSC-34-70-30-00006162.0002001 / 17 MAR 11 Applicable to: ALL
A terrain clearance floor envelope is stored in the database for each runway for which terrain data exist. The Terrain Clearance Floor (TCF) function warns of a premature descent below this floor, regardless of aircraft configuration.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
DSC-34-70-30 P 3/6 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPWS - EGPWS FUNCTIONS
FLIGHT CREW OPERATING MANUAL
If the airplane descends below this floor, a TOO LOW TERRAIN aural warning is announciated, and the pushbutton light comes on, on the glareshield. RUNWAY FIELD CLEARANCE FLOOR Ident.: DSC-34-70-30-00006163.0002001 / 17 MAR 11 Applicable to: ALL
The Runway Field Clearance Floor (RFCF) provides an additional envelope protection, for runways that are significantly higher than the surrounding terrain. It is contained in a circle within the 5.5 nm of the runway threshold and it is based on the geometric altitude and the runway elevation.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← C to D →
DSC-34-70-30 P 4/6 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
GPWS - EGPWS FUNCTIONS
←D
DSC-34-70-30 P 5/6 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPWS - EGPWS FUNCTIONS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-70-30 P 6/6 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPWS - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
OVERHEAD PANEL Ident.: DSC-34-70-40-00001418.0002001 / 14 MAY 12 Applicable to: ALL
(1)
SYS pushbutton OFF : All basic GPWS alerts (Mode 1 to 5) are inhibited. FAULT light : This amber light comes on, along with an ECAM caution, if the basic GPWS mode 1 to 5 malfunction. Note:
If ILS 1 fails, only mode 5 is inhibited. Consequently, the FAULT light does not come on and the GPWS FAULT warning is not triggered.
(2)
G / S MODE pushbutton OFF : Glideslope mode (mode 5) is inhibited.
(3)
FLAP MODE pusbutton OFF : Flap mode (“TOO LOW FLAPS” mode 4) is inhibited. (To avoid nuisance warning in case of landing with flaps setting reduced).
(4)
LDG FLAP 3 pushbutton ON : Flap mode is inhibited when FLAPS CONF 3 is selected (to avoid nuisance warning in case of landing in CONF 3). In this case, LDG MEMO displays "FLAPS ... 3" instead of “CONF ... FULL”.
(5)
TERR pushbutton OFF : Inhibits the Terrain Awareness Display (TAD) and Terrain Clearance Floor (TCF) modes, and does not affect the basic GPWS mode 1 to 5. If OFF is selected the ECAM caution NAV GPWS TERR DET FAULT is displayed.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-34-70-40 P 1/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPWS - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
FAULT light :
This amber light comes on, along with an ECAM caution, if the TAD or TCF mode fails. The terrain is not shown on the ND. The basic GPWS mode 1 to mode 5 are still operative if the SYS pushbutton OFF or FAULT lights are not illuminated. INSTRUMENT PANELS
Ident.: DSC-34-70-40-00001419.0009001 / 17 MAR 11 Applicable to: ALL
(1)
PULL UP – GPWS pb PULL : Comes on to give a visual indication, when a PULL UP warning is triggered in UP Modes 1, 2, and TAD. The corresponding aural warning sounds. GPWS : Comes on amber, when any other mode is activated. The corresponding aural warning sounds. Note:
1. If the flight crew briefly presses this button when one of these modes is activated, the GPWS light goes out and the voice warning stops. 2. On ground, the GPWS can be tested by pressing this pushbutton. If the pushbutton is pressed briefly, some of the aural warnings sound and pushbutton captions, related to the GPWS, come on. If the pushbutton is pressed continuously, then all the aural warnings sound.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← A to B →
DSC-34-70-40 P 2/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(2)
GPWS - CONTROLS AND INDICATORS
TERR ON ND pb These pushbutton are located on either side of the ECAM. Each pushbutton controls the onside terrain display. ON : The terrain is displayed on the ND if the: ‐ TERR pb-sw is selected ON, and ‐ TERR FAULT light is not on. The ON light comes on. OFF : The terrain data is not displayed on the ND. Note:
‐ If the Terrain Awareness Display (TAD) mode generates a caution, or a warning while the TERR ON ND is not switched ON, the terrain data is automatically displayed on the NDs (see EGPWS specific caution and warning due to TAD mode) and the ON light of the, TERR ON ND pushbutton comes on. ‐ To differenciate between the terrain and the weather display, the terrain display sweeps from the center outward to both sides of the ND.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-34-70-40 P 3/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPWS - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-70-40 P 4/4 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPWS - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-34-70-50-00001420.0024001 / 17 MAR 11 Applicable to: ALL
E/WD: FAILURE TITLE conditions
AURAL WARNING
MASTER LIGHT
SD PAGE CALLED
GPWS FAULT GPWS TERR DET FAULT The enhanced terrain detection function is inoperative. The basic GPWS mode 1 to 5 are still operative.
SINGLE CHIME
MASTER CAUT
NIL
GPWS SYS FAULT lt
FLT PHASE INHIB 1, 3, 4, 5, 8, 9, 10
GPWS TERR FAULT lt
1, 3, 4, 5 8,10
LOCAL WARNING
MEMO DISPLAY GPWS FLAP 3 is displayed in green when GPWS LDG FLAP 3 pb-sw is ON. GPWS FLAP MODE OFF is displayed in green when GPWS FLAP MODE pb-sw is OFF. Airborne TERR STBY appears in green when the aircraft position accuracy (computed by the EGPWS) is not sufficient to allow the enhanced TCF and TAD modes to operate. These modes are not available until the TERR STBY memo disappears. If selected, the terrain data display on ND is automatically deselected when the TERR STBY memo is triggered.” TERR OFF is displayed when the TERR pb-sw is switched OFF: ‐ It appears in green in flight phase 2, before the Take Off Configuration test is launched, and in flight phase 6. ‐ It appears in amber in flight phase 2, after the Take Off Configuration test, and in flight phases 3, 4, 5, 7, 8 and 9.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-34-70-50 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPWS - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-70-50 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPWS - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-34-70-60-00001421.0001001 / 17 MAR 11 Applicable to: ALL
NORM AC
GPWS
DC
AC ESS
EMER ELEC DC ESS
HOT
AC1
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-34-70-60 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
GPWS - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-70-60 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
TCAS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-34-80-10-00001422.0004001 / 15 FEB 11 Applicable to: ALL
The Traffic alert and Collision Avoidance System (TCAS): ‐ Detects any aircraft, that is equipped with transponders and is flying in the vicinity ‐ Displays potential and predicted collision targets ‐ Issues vertical orders to avoid conflict. The TCAS is normally independent of the ground-based air traffic control system. The TCAS detection capability is limited to intruders flying within a maximum range of 100 nm (depending on aircraft configuration and external conditions), and within a maximum altitude range of 9 900 ft (above and below the threatened aircraft).
MAIN COMPONENTS Ident.: DSC-34-80-10-00001423.0001001 / 15 FEB 11 Applicable to: ALL
The system includes: ‐ A single channel TCAS computer ‐ Two TCAS antennas ‐ Two mode S ATC transponders, one active the other in standby. These transponders allow: • Interface between the ATC/TCAS control panel and the TCAS computer • Communication between the aircraft and intruders equipped with a TCAS system ‐ An ATC/TCAS control panel.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-34-80-10 P 1/6 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
TCAS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
DSC-34-80-10 P 2/6 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
TCAS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-34-80-10 P 3/6 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
TCAS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
PRINCIPLE Ident.: DSC-34-80-10-00001424.0001001 / 15 FEB 11 Applicable to: ALL
The TCAS interrogates transponder of intruders. From the transponder replies, the TCAS determines for each intruder: ‐ Its relative bearing ‐ Its range and closure rate ‐ Its relative altitude if available (ATC mode C or S) Then the TCAS computes the intruder trajectory, the Closest Point of Approach (CPA) and the estimated time (TAU) before reaching the CPA. Each time the relative position of the intruder presents a collision threat, aural and visual advisories are triggered. TCAS optimizes vertical orders to ensure a sufficient trajectory separation and a minimal vertical speed variation considering all intruders. INTRUDER CLASSIFICATION Ident.: DSC-34-80-10-00001425.0001001 / 15 FEB 11 Applicable to: ALL
The intruders are classified in four levels: LEVEL
Proximate
Traffic Advisory (TA)
INTRUDER POSITION
DISPLAYED INFORMATION
‐ No collision threat ‐ Intruder in the vicinity of the A/C (closer than 6 nm laterally and ±1200 ft vertically)
‐ ND: intruder position
‐ Potential collision threat ‐ TAU is about 40 s
‐ ND: intruder position ‐ Aural messages Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C to D →
DSC-34-80-10 P 4/6 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
TCAS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
LEVEL
Resolution Advisory (RA)
INTRUDER POSITION ‐ Real collision threat ‐ TAU is about 25 s
Continued from the previous page DISPLAYED INFORMATION
‐ ND: intruder position ‐ Aural messages ‐ PFD: vertical orders • Maintain actual V/S (Preventive Advisory) or • Modify V/S (Corrective Advisory)
Other intruders
‐ No collision threat ‐ Any non proximate, TA, RA within the surveillance envelope (lateral range: closer than 30 nm. vertical range: Refer to DSC-34-80-20 ATC/TCAS Panel)
‐ ND: Intruder position
TA/RA THRESHOLDS Ident.: DSC-34-80-10-00001426.0002001 / 14 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← D to E
DSC-34-80-10 P 5/6 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
TCAS - DESCRIPTION
FLIGHT CREW OPERATING MANUAL
TCAS MODES Ident.: DSC-34-80-10-00001427.0002001 / 17 MAR 11 Applicable to: ALL
The TCAS has two modes of operation: ‐ TA/RA : This mode allows the display of all intruders ‐ TA : Can be selected by: ‐ The crew, on the ATC/TCAS panel, in case of aircraft degraded performance (engine failure, landing gear extended), or when operating near closely-spaced parallel runways, or ‐ Automatically, if TA/RA is previously selected, and: • The windshear message is triggered • The stall message is triggered • GPWS messages are triggered • Aircraft is below 1 000 ft AGL. Consequently: ‐ All RAs are inhibited and converted into TAs ‐ TA threshold is set to TAU ≤20 s, irrespective of the aircraft’s altitude ‐ No vertical speed advisories are indicated on the PFDs ‐ “TA ONLY” is displayed on the NDs. If windshear, stall, or GPWS messages are triggered, or aircraft below 500 ft AGL, all the TCAS aural messages are suppressed. ADVISORY INHIBITION Ident.: DSC-34-80-10-00001428.0002001 / 17 MAR 11 Applicable to: ALL
Some advisories are inhibited depending on the aircraft altitude: ‐ All intruders flying below 380 ft AGL when the own aircraft altitude is below 1 700 ft AGL. ‐ All RA below 1 100 ft in climb and 900 ft in descent. In this case, the RAs are converted into TAs. ‐ “Descend” type advisory below 1 200 ft AGL at takeoff or 1 000 ft AGL in approach. ‐ “Increase Descent” RA below 1 450 ft. ‐ All TA aural messages below 600 ft AGL in climb and below 400 ft AGL in descent.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F to G
DSC-34-80-10 P 6/6 30 MAY 12
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
TCAS - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
ATC/TCAS PANEL Ident.: DSC-34-80-20-00001429.0004001 / 15 FEB 11 Applicable to: ALL
(1)
Mode sel TA/RA : Normal position. The RAs, TAs and proximate intruders are displayed if the ALT RPTG switch is ON and the transponder is not on STBY. TA : The TCAS does not generate any vertical orders. This mode should be used, in case of degraded aircraft performance (engine failure, landing gear extended, or approach on parallel runways). All RAs are converted into TAs. TAs, proximate and intruders are displayed if the ALT RPTG switch is ON and the transponder is not on STBY The "TA ONLY" white memo is displayed on the NDs. STBY : The TCAS is on standby.
(2)
TRAFFIC sel THRT : Proximate and other intruders are displayed only if a TA or RA is present, and they are within 2 700 ft above and 2 700 ft below the aircraft. ALL : Proximate and other intruders are displayed even if no TA or RA is present (full time function). The altitude range is –2700 ft to +2 700 ft. ABV : The same as ALL, except that the other intruders are displayed if within 9 900 ft above the aircraft and 2 700 ft below. BLW : The same as ALL, except that the other intruders are displayed if within 9 900 ft below the aircraft and 2 700 ft above.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-34-80-20 P 1/6 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
TCAS - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
ND INDICATIONS Ident.: DSC-34-80-20-00001430.0002001 / 15 FEB 11 Applicable to: ALL
The traffic is displayed in all ROSE modes and ARC mode. Only the 8 most threatening intruders are displayed.
(1)
Proximate intruder Indicated by a white filled diamond.
(2)
TA intruder Indicated by an amber circle. Associated with the TRAFFIC-TRAFFIC aural message.
(3)
RA intruder Indicated by a red square. Associated with vertical orders displayed on the PFD and aural messages.
(4)
Other intruders Indicated by a white empty diamond. Note:
(5)
If the range of an intruder is not available, the intruder is not displayed. An intruder may be partially displayed when its range is out of scale.
Relative altitude Indicated in hundred of feet above or below the symbol depending on the intruder position.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
DSC-34-80-20 P 2/6 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(6)
Vertical speed arrow Displayed only if the intruder V/S > 500 ft/min Relative altitude and vertical speed arrow are displayed in the same color as the associated intruder symbol. Note:
(7)
TCAS - CONTROLS AND INDICATORS
If the altitude of an intruder is not available, neither altitude nor vertical speed indications are displayed.
No bearing intruder If the bearing of TA or RA intruder is not available the following data is presented in digital form at the bottom of the ND: ‐ range ‐ relative altitude and vertical speed arrow if available. Displayed amber or red according to threat level.
(8)
Range ring A 2.5 nm white range ring is displayed when a 10 nm or 20 nm range is selected. TCAS MESSAGES
Ident.: DSC-34-80-20-00001431.0002001 / 15 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
DSC-34-80-20 P 3/6 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
TCAS - CONTROLS AND INDICATORS
Mode and range messages Following messages can be displayed to draw pilot’s attention: TCAS : REDUCE RANGE : Displayed when a TA or RA is detected and ND range above 40 nm TCAS : CHANGE MODE : Displayed when a TA or RA is detected and ND mode is PLAN. Displayed amber or red depending on the advisory level (TA or RA).
(2)
TCAS operation messages TCAS : Displayed in amber in case of TCAS internal failure. TA ONLY : Displayed white when the TA mode is selected automatically, or manually by the flight crew. PFD INDICATIONS
Ident.: DSC-34-80-20-00001432.0003001 / 17 MAR 11 Applicable to: ALL
In case of RA detection, the vertical speed scale becomes rectangular and the PFD presents vertical orders on the vertical speed scale. The vertical speed scale background is normally grey, but may be partially replaced by green and/or red areas.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← C to D →
DSC-34-80-20 P 4/6 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TCAS - CONTROLS AND INDICATORS
(1)
Red area Indicates the vertical speed range, when there is a high risk of conflict.
(2)
Green area Indicates the recommended vertical speed range. It is wider than the red area. Note:
(3)
‐ The aircraft can also fly in the grey vertical speed range, without the risk of conflict (preventive RA) ‐ The color of the digits corresponds to the appropriate area ‐ In case of RA detection, the vertical speed needle that is normally green, becomes white.
TCAS message Appears in amber provided that the TCAS is not in standby, when the TCAS cannot deliver RA data, or in case of an internal TCAS failure.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D
DSC-34-80-20 P 5/6 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
TCAS - CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
AURAL MESSAGES Ident.: DSC-34-80-20-00001433.0002001 / 15 FEB 11 Applicable to: ALL
TA/RA detection is associated with the following messages: "TRAFFIC TRAFFIC" : Only in case of TA detection. "CLIMB CLIMB" : Climb at the vertical speed indicated by the green area on the PFD. "CLIMB, CROSSING CLIMB" (twice) : Same as above. Indicates that you will cross through the intruder altitude. "INCREASE CLIMB" (twice) : Triggered after the CLIMB message, if vertical speed is insufficient to achieve safe vertical separation. "DESCEND DESCEND" : Descend at the vertical speed indicated by the green area on the PFD. "DESCEND, CROSSING : Same as above. Indicates that you will cross through DESCEND" (twice) the intruder altitude. "INCREASE DESCEND" (twice) : Triggered after the DESCEND message, if the vertical speed is insufficient to achieve safe vertical separation. "ADJUST VERTICAL SPEED, ADJUST": Adjust the vertical speed to that indicated on the green area of the PFD, reducing climb vertical speed or descent vertical speed, as appropriate. "CLIMB CLIMB NOW" (twice) : Triggered after the DESCEND message, if the intruder trajectory has changed. "DESCEND DESCEND NOW" (twice) : Triggered after the CLIMB message, if the intruder trajectory has changed. "MONITOR VERTICAL SPEED" : Ensure that the vertical speed remains outside the red area. Triggered only once, in case of preventive RA. "MAINTAIN VERTICAL SPEED, : Maintain the vertical speed indicated on the green MAINTAIN" area of the PFD. "MAINTAIN VERTICAL SPEED, : Maintain the vertical speed indicated on the green CROSSING MAINTAIN" area of the PFD. Indicates that you will cross through the intruder altitude. "CLEAR OF CONFLICT" : The range increases and separation is adequate. Return to assigned clearance.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E
DSC-34-80-20 P 6/6 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
TCAS - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-34-80-30-00001434.0025001 / 17 MAR 11 Applicable to: ALL
E/WD: FAILURE TITLE conditions
TCAS FAULT
in case of TCAS internal failure
TCAS STBY
in the case where the flight crew sets the TCAS on STBY in flight.
AURAL WARNING
MASTER LIGHT
SINGLE CHIME
MASTER CAUT
SINGLE CHIME
MASTER CAUT
SD PAGE CALLED
LOCAL WARNING
FLT PHASE INHIB
Flag on PFD and ND
3, 4, 5, 7
NIL
ALL, except 6
NIL
MEMO DISPLAY TCAS STBY is displayed in green, when: ‐ ATC STBY is selected by the crew, or ‐ TCAS STBY is selected by the crew during flight phases other than 6, or ‐ ALT RPTG is selected at off, or ‐ both ATC or both RA are failed. ‐ In the case of a triple ADR failure. TCAS STBY is displayed in amber, when the flight crew sets the TCAS on STBY in flight phase 6.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-34-80-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
TCAS - WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-80-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
TCAS - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-34-80-40-00001435.0001001 / 15 FEB 11 Applicable to: ALL
NORM AC
TCAS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DC
AC ESS
EMER ELEC DC ESS
HOT
AC1
A
DSC-34-80-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS NAVIGATION A318/A319/A320/A321
TCAS - ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-34-80-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS OXYGEN
Intentionally left blank
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-35-PLP PRELIMINARY PAGES TABLE OF CONTENTS SUMMARY OF HIGHLIGHTS
DSC-35-10 General Description............................................................................................................................................................... A
DSC-35-20 Fixed Oxygen System for Cockpit DSC-35-20-10 Description GENERAL................................................................................................................................................................ A OPERATION............................................................................................................................................................ B Schematic................................................................................................................................................................ C Mask Setting............................................................................................................................................................ D MASK STOWAGE................................................................................................................................................... E
DSC-35-20-20 Controls and Indicators Overhead Panel....................................................................................................................................................... A Stowage Box............................................................................................................................................................B CREW OXYGEN MASK..........................................................................................................................................C Pressure Regulator..................................................................................................................................................D Door/OXY ECAM Page........................................................................................................................................... E
DSC-35-20-30 Electrical Supply BUS EQUIPMENT LIST .........................................................................................................................................A
1
DSC-35-30 Fixed Oxygen System for Cabin DSC-35-30-10 Description GENERAL................................................................................................................................................................ A Operation..................................................................................................................................................................B Schematic................................................................................................................................................................ C
2
DSC-35-30-20 Controls and Indicators Overhead Panel....................................................................................................................................................... A Overhead Maintenance Panel................................................................................................................................. B Memo Display.......................................................................................................................................................... C
DSC-35-30-40 Electrical Supply Bus Equipment List ................................................................................................................................................ A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-35-PLP-TOC P 1/2 18 SEP 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-35-40 Portable Oxygen System DSC-35-40-10 Description Flight Crews Portable Oxygen System................................................................................................................... A Using the Hood........................................................................................................................................................B
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-35-PLP-TOC P 2/2 18 SEP 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title DSC-35-PLP-TOC Description DSC-35-PLP-TOC Controls and Indicators DSC-35-30-10 Operation DSC-35-30-20 Overhead Panel
Toc Index
ID 1
Reason
B
1
Documentation update: Deletion of the "00001460.0005001 Operation" documentary unit. Documentation update: Deletion of the "00001462.0002001 Overhead Panel" documentary unit. Effectivity update: The information now applies to all MSN.
A
1
Effectivity update: The information now applies to all MSN.
2
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-35-PLP-SOH P 1/2 18 SEP 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-35-PLP-SOH P 2/2 18 SEP 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
DESCRIPTION Ident.: DSC-35-10-00001448.0001001 / 20 DEC 10 Applicable to: ALL
The oxygen system consists of: ‐ A cockpit-fixed oxygen system, which supplies adequate breathing oxygen to the cockpit occupants in case of depressurization, or emission of smoke and noxious gases. ‐ A cabin-fixed oxygen system, which supplies oxygen for cabin occupants (passengers and cabin crew) in case of depressurization. ‐ A portable oxygen system, which is provided in both the cockpit and cabin and is to be used: • As PROTECTION for the crew during on board emergencies. • For FIRST AID purposes.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-35-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-35-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - DESCRIPTION
GENERAL Ident.: DSC-35-20-10-00001449.0002001 / 09 DEC 09 Applicable to: ALL
The cockpit’s fixed oxygen system consists of : ‐ A high-pressure cylinder, in the left-hand lower fuselage. ‐ A pressure regulator, connected directly to the cylinder that delivers oxygen, at a pressure suitable for users. ‐ Two overpressure safety systems to vent oxygen overboard, through a safety port, if the pressure gets too high. ‐ A supply solenoid valve that allows the crew to shut off the distribution system. ‐ Four full-face quick-donning masks, stowed in readily-accessible boxes adjacent to the crewmembers’ seats (one at each seat). OPERATION Ident.: DSC-35-20-10-00001450.0001001 / 09 DEC 09 Applicable to: ALL
The crewmember squeezes the red grips to pull the mask out of its box, and this action causes the mask harness to inflate. A mask-mounted regulator supplies a mixture of air and oxygen or pure oxygen, or performs emergency pressure control. With the regulator set to NORMAL, the user breathes a mixture of cabin air and oxygen up to the cabin altitude at which the regulator supplies 100 % oxygen. The user can select 100 %, in which case the regulator supplies pure oxygen at all cabin altitudes. If the situation calls for it, the user can use the emergency overpressure rotating knob and receive pure oxygen at positive pressure. The storage box contains a microphone lead, with a quick-disconnect, for connection to the appropriate mask microphone cable. Note:
Each mask may have a removable film that protects the visor against scratches. This strip is optional and may be removed from the mask at any time.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
DSC-35-20-10 P 1/4 30 MAY 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - DESCRIPTION
SCHEMATIC Ident.: DSC-35-20-10-00001451.0002001 / 14 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-35-20-10 P 2/4 30 MAY 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - DESCRIPTION
MASK SETTING Ident.: DSC-35-20-10-00001452.0001001 / 22 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D
DSC-35-20-10 P 3/4 30 MAY 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - DESCRIPTION
MASK STOWAGE Ident.: DSC-35-20-10-00001453.0001001 / 29 MAR 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E
DSC-35-20-10 P 4/4 30 MAY 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - CONTROLS AND INDICATORS
OVERHEAD PANEL Ident.: DSC-35-20-20-00001454.0001001 / 14 FEB 11 Applicable to: ALL
(1)
CREW SUPPLY pb This pushbutton controls the solenoid valve. On : The valve is open, and supplies low pressure oxygen to the masks (normal position in flight). OFF: The valve is closed, and the white light comes on.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-35-20-20 P 1/6 30 MAY 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - CONTROLS AND INDICATORS
STOWAGE BOX Ident.: DSC-35-20-20-00001455.0001001 / 22 MAY 12 Applicable to: ALL
(1)
Blinker flowmeter (yellow) This indicator flashes when oxygen is flowing.
(2)
RESET/TEST control slide The crewmember presses the slide, and pushes it in the direction of the arrow to test: the operation of the blinker; the regulator supply; system sealing downstream of the valve; and the regulator sealing and system operation. Pressing the RESET control slide, after the oxygen mask has been used, cuts off the oxygen, and the mask microphone.
(3)
OXY ON flag As soon as the left flap door opens, the mask is supplied with oxygen and, once it closes (mask still supplied with oxygen), the “OXY ON” flag appears.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
DSC-35-20-20 P 2/6 30 MAY 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - CONTROLS AND INDICATORS
CREW OXYGEN MASK Ident.: DSC-35-20-20-00001456.0001001 / 09 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-35-20-20 P 3/6 30 MAY 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - CONTROLS AND INDICATORS
PRESSURE REGULATOR Ident.: DSC-35-20-20-00001457.0001001 / 22 MAY 12 Applicable to: ALL
(1)
Red grips Squeezing the right-hand side grip unlocks the two-flap door, and permits the harness to inflate.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D→
DSC-35-20-20 P 4/6 30 MAY 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(2)
FIXED OXYGEN SYSTEM FOR COCKPIT - CONTROLS AND INDICATORS
EMERGENCY pressure selector Use of this selector creates on overpressure which eliminates condensation or fogging of the mask, and prevents smoke, smell or ashes from entering the mask. ‐ Pressing this knob generates an overpressure for a few seconds. ‐ Turning the knob, in the direction of the arrow, generates a permanent overpressure. Note:
(3)
1. Overpressure supply is automatically started, when cabin altitude exceeds 30 000 ft. 2. Overpressure supply is available only when the N/100% selector is set on the on the 100 % position.
N/100 % selector Pushing the button up from underneath releases it, and it pops up to the N (normal) position. Pressing it again returns it to 100 %. 100 % : The mask delivers 100 % oxygen. N : The mask delivers a mixture of air and oxygen, the content of which varies with cabin altitude. When cabin altitude goes above 35 000 ft, the air inlet closes and the wearer breathes 100 % oxygen. DOOR/OXY ECAM PAGE
Ident.: DSC-35-20-20-00001458.0005001 / 14 NOV 11 Applicable to: ALL
(1)
OXY high pressure indication It is in green, when the pressure is ≥ 600 PSI. It pulses in green, when the pressure is < 600 PSI (the DOOR/OXY SD page is automatically displayed). It is in amber, when the pressure is < 300 PSI. On ground, an amber half frame appears when oxygen pressure is < 1 000 PSI.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← D to E →
DSC-35-20-20 P 5/6 30 MAY 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - CONTROLS AND INDICATORS
In this case, the flight crew must check that the remaining quantity is not below the minimum (Refer to LIM-35 Cockpit Fixed Oxygen System). (2)
REGUL LO PR indication It is in amber, if oxygen pressure on the low-pressure circuit is low (50 PSI).
(3)
CKPT OXY indication It is normally in white. It becomes amber, when: ‐ Pressure goes below 300 PSI ‐ Low oxygen pressure is detected ‐ The OXYGEN CREW SUPPLY pb on the overhead panel is OFF.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E
DSC-35-20-20 P 6/6 30 MAY 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - ELECTRICAL SUPPLY
BUS EQUIPMENT LIST Ident.: DSC-35-20-30-00001466.0001001 / 09 DEC 09 Applicable to: ALL L3
NORM AC CREW OXY CTL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DC
DC BAT
AC ESS
EMER ELEC DC HOT ESS SHED
DSC-35-20-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - ELECTRICAL SUPPLY
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-35-20-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR CABIN - DESCRIPTION
GENERAL Ident.: DSC-35-30-10-00001459.0001001 / 09 DEC 09 Applicable to: ALL
The cabin’s fixed oxygen system supplies oxygen to the occupants, in case of cabin depressurization. Chemical generators produce the oxygen. Each generator feeds a group of 2, 3, or 4 masks. Generators and masks are in containers above the passenger seats, in the lavatories, in each galley , and at each cabin crew station. OPERATION Ident.: DSC-35-30-10-00001460.0004001 / 16 MAY 12 1 Applicable to: ALL
Each container has an electrical latching mechanism that opens automatically to allow the masks to drop, if the cabin pressure altitude exceeds 14 000 ft (+ 250, - 750 ft). The flight crew can override the automatic control. When the masks are released, the passenger address system automatically broadcasts prerecorded instructions for their use. The generation of oxygen begins when the passenger pulls the mask towards the passenger seat. The chemical reaction used for oxygen generation creates heat. Therefore, the smell of burning or smoke, and cabin temperature increase, may be associated with the normal operation of the oxygen generators. The mask receives pure oxygen under positive pressure for about 15 min, until the generator is exhausted. A reset is available for the rearming of the system after the masks are restowed. A manual release tool allows crew members to manually open the doors in case of electrical failure.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
DSC-35-30-10 P 1/2 18 SEP 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR CABIN - DESCRIPTION
SCHEMATIC Ident.: DSC-35-30-10-00001461.0001001 / 16 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-35-30-10 P 2/2 18 SEP 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR CABIN - CONTROLS AND INDICATORS
OVERHEAD PANEL Ident.: DSC-35-30-20-00001462.0001001 / 11 FEB 11 1 Applicable to: ALL
(1)
PASSENGER SYS ON light This light comes on in white, when the control for the oxygen mask doors is activated, and it remains on until the TMR RESET pushbutton is pressed (Refer to DSC-35-30-20 Overhead Maintenance Panel).
(2)
MASK MAN ON pushbutton The guard keeps this button in the AUTO position. AUTO : The mask doors open automatically, when the cabin altitude exceeds 14 000 ft. Pressed : The mask doors open. OVERHEAD MAINTENANCE PANEL
Ident.: DSC-35-30-20-00001463.0001001 / 11 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-35-30-20 P 1/2 18 SEP 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
FIXED OXYGEN SYSTEM FOR CABIN - CONTROLS AND INDICATORS
TMR RESET pushbutton The maintenance crew uses this pushbutton to reset the control circuit, after the system has operated. ON : The PASSENGER SYS ON light goes off. FAULT : This light comes on in white, when the door latch solenoids are energized for more than 30 s. MEMO DISPLAY
Ident.: DSC-35-30-20-00012709.0001001 / 11 FEB 11 Applicable to: ALL
HI ALT SET
:
The ECAM displays this memo in green, when the crew sets the HI ALT LANDING pb to ON. In this case, the passenger mask release altitude is 16 000 ft (+ 250 ft, - 750 ft).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← B to C
DSC-35-30-20 P 2/2 18 SEP 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR CABIN - ELECTRICAL SUPPLY
BUS EQUIPMENT LIST Ident.: DSC-35-30-40-00001467.0001001 / 11 FEB 11 Applicable to: ALL
NORM AC PAX OXYGEN
ACTUATION AUTOCONTROL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DC
DC BAT
AC ESS SHED
EMER ELEC DC HOT ESS SHED
A
DSC-35-30-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR CABIN - ELECTRICAL SUPPLY
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-35-30-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PORTABLE OXYGEN SYSTEM - DESCRIPTION
FLIGHT CREWS PORTABLE OXYGEN SYSTEM Ident.: DSC-35-40-10-00001465.0003001 / 17 MAR 11 Applicable to: ALL
The flight crew smoke hood located on the right back side of the cockpit, ensures the eyes and respiratory system protection of one flight crew member when fighting a fire and in case of smoke or noxious gas emissions or cabin depressurization. The smoke hood is based on a chemical air regeneration system, located at the back of the hood. An oronasal mask allows the inhalation of regenerated air via the inhalation valves and returns the exhaled breath to the regenerator system.
The effective time of use is between 15 and 30 min, depending on the workrate.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-35-40-10 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS OXYGEN A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PORTABLE OXYGEN SYSTEM - DESCRIPTION
USING THE HOOD Ident.: DSC-35-40-10-00006226.0003001 / 22 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
DSC-35-40-10 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS PNEUMATIC
Intentionally left blank
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-36-PLP PRELIMINARY PAGES TABLE OF CONTENTS
DSC-36-10 Description DSC-36-10-10 General GENERAL................................................................................................................................................................ A
DSC-36-10-20 Engine Bleed System GENERAL................................................................................................................................................................ A ARCHITECTURE..................................................................................................................................................... B AIR BLEED SELECTION........................................................................................................................................ C PRESSURE REGULATION AND LIMITATION...................................................................................................... D TEMPERATURE REGULATION AND LIMITATION............................................................................................... E
DSC-36-10-30 Apu Bleed Air Supply General.....................................................................................................................................................................A APU BLEED VALVE OPENING LOGIC..................................................................................................................B
DSC-36-10-40 Crossbleed GENERAL................................................................................................................................................................ A X-BLEED VALVE CONTROL LOGIC......................................................................................................................B ECAM INDICATION.................................................................................................................................................C
DSC-36-10-50 Leak Detection LEAK DETECTION.................................................................................................................................................. A
DSC-36-10-60 Operation Following Failures BMC FAILURE.........................................................................................................................................................A
DSC-36-20 Controls and Indicators OVERHEAD PANEL................................................................................................................................................ A ECAM Bleed Page...................................................................................................................................................B
DSC-36-30 Warnings and Cautions Warnings and Cautions........................................................................................................................................... A
DSC-36-40 Electrical Supply BUS EQUIPMENT LIST.......................................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-36-PLP-TOC P 1/2 03 APR 12
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-36-PLP-TOC P 2/2 03 APR 12
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
DESCRIPTION - GENERAL
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-36-10-10-00001468.0001001 / 09 DEC 09 Applicable to: ALL
The pneumatic system supplies high-pressure air for : ‐ air conditioning ‐ engine starting ‐ wing anti-icing ‐ water pressurization ‐ hydraulic reservoir pressurization High-pressure air has three sources : ‐ engine bleed systems ‐ APU load compressor ‐ HP ground connection A crossbleed duct interconnects the engine bleed systems and receives air from the APU and ground sources when appropriate. A valve mounted on the crossbleed duct allows the left side (engine 1) and right side (engine 2) to be interconnected. Two Bleed Monitoring Computers (BMC1 and BMC2), the overhead control panel, and the ECAM control and monitor the operation of the pneumatic system. A leak detection system detects any overheating in the vicinity of hot air ducts.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-36-10-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
DESCRIPTION - GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-36-10-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - ENGINE BLEED SYSTEM
GENERAL Ident.: DSC-36-10-20-00001469.0001001 / 09 DEC 09 Applicable to: ALL
The aircraft has two similar engine bleed air systems. Each system is designed to : ‐ select the compressor stage to use as a source of air ‐ regulate the bleed air temperature ‐ regulate the bleed air pressure. A Bleed Monitoring Computer (BMC) controls and monitors each system. Each BMC receives information about bleed pressure and temperature and valve position. Each is connected with : ‐ other systems using air or information from the bleed system ‐ the other BMC. Each supplies indications and warnings to the ECAM and CFDS. If one BMC fails, the other one takes over most of the monitoring functions. Each bleed valve is pneumatically operated and controlled electrically by its associated BMC.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-36-10-20 P 1/6 03 APR 12
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
DESCRIPTION - ENGINE BLEED SYSTEM
FLIGHT CREW OPERATING MANUAL
ARCHITECTURE Ident.: DSC-36-10-20-00001470.0005001 / 09 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
DSC-36-10-20 P 2/6 03 APR 12
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DESCRIPTION - ENGINE BLEED SYSTEM
←B
DSC-36-10-20 P 3/6 03 APR 12
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
DESCRIPTION - ENGINE BLEED SYSTEM
FLIGHT CREW OPERATING MANUAL
AIR BLEED SELECTION Ident.: DSC-36-10-20-00001471.0003001 / 14 NOV 11 Applicable to: ALL
Air is normally bled from the intermediate pressure stage (IP) of engine’s high-pressure (HP) compressor to minimize fuel penalty. At low engine speed, when the pressure and temperature of the IP air are too low, the system bleeds air from the HP stage and maintains it at 36 ± 4 PSI. An intermediate pressure check valve downstream of the IP port closes to prevent air from the HP stage from being circulated to the IP stage. L3
The HP valve closes automatically ‐ • In case of low upstream pressure • in case of excessive upstream pressure ‐ electrically when the bleed valve is closed electrically. ECAM INDICATION
PRESSURE REGULATION AND LIMITATION Ident.: DSC-36-10-20-00001472.0001001 / 09 FEB 11 Applicable to: ALL
The bleed valve, which is downstream of the junction of HP and IP ducting, acts as a shut-off and pressure regulating valve. It maintains delivery pressure at 45 ± 5 PSI. Note:
Bleed pressure may fluctuate between 38 and 56 PSI (with a maximum peak to peak pressure of 16 PSI) particularly at high engine power (takeoff or climb) up to FL 100.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C to D →
DSC-36-10-20 P 4/6 03 APR 12
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - ENGINE BLEED SYSTEM
The bleed valve is fully closed: ‐ Pneumatically: • If upstream pressure goes below 8 PSI • If there is return flow ‐ Electrically by means of: • The BLEED pushbutton switch (switched OFF) • The ENG FIRE pushbutton (pushed) • The Bleed air Monitoring Computer (BMC) in the following cases: ‐ ‐ ‐ ‐ ‐
Overtemperature Overpressure Leak Open starter valve APU bleed being ON.
If pressure regulation fails, the overpressure valve closes when the pressure goes over 85 PSI. Note:
If APU Bleed is ON and the crossbleed valve is SHUT, the Engine bleed valve 2, remains open. TEMPERATURE REGULATION AND LIMITATION
Ident.: DSC-36-10-20-00001473.0001001 / 09 DEC 09 Applicable to: ALL
A precooler downstream of the bleed valve regulates the temperature of the bleed air. The precooler is an air-to-air heat exchanger that uses cooling air bleed from the engine fan to regulate the temperature to approximately 200 °C. The fan air valve controls fan air flow. A spring keeps the fan air valve closed in the absence of pressure.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← D to E
DSC-36-10-20 P 5/6 03 APR 12
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
DESCRIPTION - ENGINE BLEED SYSTEM
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-36-10-20 P 6/6 03 APR 12
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
DESCRIPTION - APU BLEED AIR SUPPLY
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-36-10-30-00001474.0001001 / 09 FEB 11 Applicable to: ALL
Air from the APU load compressor is available on ground and in flight. The APU bleed valve operates as a shut-off valve to control APU bleed air. It is electrically controlled and pneumatically operated. The APU BLEED pb-sw, on the AIR COND panel, controls the APU bleed valve. When the flight crew selects ON with the pushbutton, APU bleed air supplies the pneumatic system, if the APU speed is above 95 %. This opens the crossbleed valve and closes the engine bleed automatically. A check valve near the crossbleed duct protects the APU, when bleed air comes from another source. APU BLEED VALVE OPENING LOGIC Ident.: DSC-36-10-30-00001475.0001001 / 09 FEB 11 Applicable to: ALL
Note:
1. Leak detection is disregarded during an engine start. 2. APU leak detection is lost, if BMC1 is lost.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
DSC-36-10-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
DESCRIPTION - APU BLEED AIR SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-36-10-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
DESCRIPTION - CROSSBLEED
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-36-10-40-00001476.0001001 / 09 DEC 09 Applicable to: ALL
A crossbleed valve on the crossbleed duct allows the air supply systems of the two engines to be isolated or interconnected. On the AIR COND panel, a rotary selector controls the crossbleed valve electrically. Two electric motors, one for automatic mode and one for manual mode, control the valve. In automatic mode, the crossbleed valve opens when the system uses APU bleed air. It closes, if the system detects an air leak (except during engine start). X-BLEED VALVE CONTROL LOGIC Ident.: DSC-36-10-40-00001477.0001001 / 09 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
DSC-36-10-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
DESCRIPTION - CROSSBLEED
FLIGHT CREW OPERATING MANUAL
ECAM INDICATION Ident.: DSC-36-10-40-00001478.0002001 / 09 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-36-10-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
DESCRIPTION - LEAK DETECTION
FLIGHT CREW OPERATING MANUAL
LEAK DETECTION Ident.: DSC-36-10-50-00001479.0001001 / 09 DEC 09 Applicable to: ALL
Leak detection loops detect any overheating near the hot air ducts in the fuselage, pylons, and wings. For the pylon and APU, the sensing elements are tied to form a single loop and for the wing, a double loop. When the two wing loops detect a leak, or when one loop detects the leak and the other one is inoperative, they activate a wing leak signal. BMC1 and BMC2 each contain identical control logic for the system. ‐ A wing leak signal causes : • the bleed valve on the related side to close automatically • the associated FAULT light on the AIR COND panel to come on • the x-bleed valve to close automatically (except during an engine start) • the APU bleed valve to close automatically (if it is open, and if the leak concerns the left wing) (except during engine start) ‐ A pylon leak signal causes : • the bleed valve on the related side to close automatically • the FAULT light for the related engine on the AIR COND panel to come on • the x-bleed valve to close automatically (except during an engine start). ‐ An APU leak signal causes : • the APU bleed valve to close automatically (except during engine start). • the FAULT light the APU BLEED pushbutton switch on the AIR COND panel to come on • the x-bleed valve to close automatically (except during an engine start).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-36-10-50 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DESCRIPTION - LEAK DETECTION
←A
DSC-36-10-50 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - OPERATION FOLLOWING FAILURES
BMC FAILURE Ident.: DSC-36-10-60-00001480.0001001 / 09 DEC 09 Applicable to: ALL
If one BMC fails, the adjacent BMC takes over the monitoring of the bleed system to issue the following ECAM warnings if necessary : ‐ overpressure ‐ overtemperature ‐ wing leak. Nevertheless, the associated FAULT light on the AIR COND panel is lost, and the associated bleed valve does not close automatically. ENG BLEED LEAK warning is lost for the associated engine, as is also the APU BLEED LEAK warning if BMC1 has failed.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-36-10-60 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - OPERATION FOLLOWING FAILURES
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-36-10-60 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
OVERHEAD PANEL Ident.: DSC-36-20-00001481.0001001 / 16 FEB 11 Applicable to: ALL
(1)
ENG 1 and ENG 2 BLEED pb sw On : Bleed valve opens if : ‐ Upstream pressure is above 8 PSI. ‐ APU BLEED pushbutton switch is off or APU bleed valve is closed. ‐ There is no onside wing or pylon leak, and no overpressure or overtemperature has been detected. ‐ The ENG FIRE pushbutton has not been popped out. ‐ The engine start valve is closed. FAULT lt : This amber light comes on, and an ECAM caution appears, if : ‐ There is an overpressure downstream of the bleed valve. ‐ There is a bleed air overheat. ‐ There is a wing or engine leak on the related side. ‐ The bleed valve is not closed during engine start. ‐ The bleed valve is not closed with APU bleed ON. lt goes out when the ENG BLEED pushbutton switch is OFF if the fault has disappeared. OFF : The bleed valve and HP valve close. The white OFF light comes on.
(2)
APU BLEED pb sw ON : The APU valve opens if N > 95 % and there is no leak in the APU or in the left side bleed. (If there is a leak on the right side, the x-bleed valve closes.) The blue ON light comes on.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-36-20 P 1/6 29 JUL 11
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Off FAULT light (3)
: :
CONTROLS AND INDICATORS
The APU valve closes. This amber light comes on, and an ECAM caution appears, when the system detects an APU leak.
X-BLEED selector sw AUTO : The crossbleed valve is open if the APU bleed valve is open. The crossbleed valve is closed if the APU bleed valve is closed or, in case of a wing, pylon, or APU leak (except during engine start). OPEN : The crossbleed valve is open. CLOSE : The crossbleed valve is closed.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-36-20 P 2/6 29 JUL 11
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
ECAM BLEED PAGE Ident.: DSC-36-20-00001482.0002001 / 16 MAR 11 Applicable to: ALL
(1)
(2)
HP VALVES Crossline - Green In line - Green Crossline - Amber
: : :
HP valve normally fully closed HP valve not fully closed HP valve not in commanded (closed) position
ENGINE BLEED VALVES In line - Green : BLEED valve normally open
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
DSC-36-20 P 3/6 29 JUL 11
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
Crossline - Green In line - Amber Crossline - Amber (3)
: : :
BLEED valve normally fully closed BLEED valve not in commanded (open) position BLEED valve not in commanded (closed) position
ENGINE BLEED INDICATIONS
(A) Precooler inlet pressure It is normally in green. It becomes amber, if under 4 PSI, or if overpressure is detected by the BMC (threshold between 57 and 60 PSI). (B) Precooler outlet temperature It is normally in green. It becomes amber, if the BMC detects an overheat or low temperature. Overheat: Temperature exceeds: ‐ 290 °C for more than 5 s, or ‐ 270 °C for more than 15 s, or ‐ 257 °C for more than 55 s Low temperature is detected, if the temperature is lower than 150 °C. Note: (4)
When the engines are at idle, and depending on the ambient temperature, the precooler outlet temperature may be below 150 °C (displayed amber).
APU BLEED VALVE Crossline - Green : In line - Green : Crossline - Amber :
The APU valve is not fully open, and the APU master switch is ON. The APU valve is fully open, and the APU master switch is ON. The APU valve is fully closed, the APU master switch is ON, and the APU bleed switch is ON for more than 10 s.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
DSC-36-20 P 4/6 29 JUL 11
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
(5)
CROSSBLEED VALVE Crossline - Green : In line - Green : Crossline - Amber : In line - Amber : Transit - Amber :
The crossbleed valve is normally closed. The crossbleed valve is normally open. The crossbleed valve is not in the commanded (closed) position. The crossbleed valve is not in the commanded (open) position. The crossbleed valve is in transit.
(6)
GND HP ground connection indication : Displayed in white when the aircraft is on ground.
(7)
ANTI ICE indication It is displayed in white, when the WING pushbutton on the ANTI-ICE panel is ON.
(8)
Arrow :
(9)
‐ It is normally not displayed, when the corresponding valve is closed. ‐ It is normally displayed in green, when the corresponding valve is open. ‐ It becomes amber, when the • Valve is open and air pressure is low or high, or • Valve is open on ground for more than 10 s.
Engine identification (1-2) It is normally in white. It becomes amber, when engine N2 is below idle.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-36-20 P 5/6 29 JUL 11
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-36-20 P 6/6 29 JUL 11
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-36-30-00001483.0007001 / 16 MAR 11 Applicable to: ALL
E/WD: FAILURE TITLE conditions
AURAL WARNING
MASTER LIGHT
SD PAGE CALLED
LOCAL WARNING
ENG 1 (2) BLEED FAULT
engine 1 (2) running and bleed air pressure > 57 PSI (+3/-0) or temperature: > 257 °C for more than 55 s or > 270 °C for more than 15 s or > 290 °C for more than 5 s
1, 3, 4, 5, 7, 8, 10
L (R) WING LEAK
ENG BLEED FAULT lt
temperature > 124 °C detected by the loops
ENG 1 (2) BLEED LEAK
temperature > 204 °C detected by the loop and engine 1 (2) running
ENG 1 (2) BLEED NOT CLSD
bleed valve not automatically closed during engine start or with APU bleed selected
3, 4, 5, 7, 8 SINGLE CHIME
BLEED 1 (2) OFF
MASTER CAUT
BLEED ENG BLEED 1, 3, 4, 5, OFF lt 7, 8, 9, 10
one engine bleed switched off with no fault
APU BLEED FAULT
NIL
APU available and APU bleed valve position disagrees with selected position.
3, 4, 5, 7, 8
APU BLEED LEAK
APU BLEED FAULT lt
temperature > 124 °C detected by the loop
ENG 1 (2) BLEED ABNORM PR
1, 3, 4, 5, 7, 8, 10 Continued on the following page NIL
regulated pressure is abnormal
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FLT PHASE INHIB
A→
DSC-36-30 P 1/2 03 APR 12
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
E/WD: FAILURE TITLE conditions
AURAL WARNING
MASTER LIGHT
SINGLE CHIME
MASTER CAUT
ENG 1 (2) (1+2) BLEED LO TEMP
one (both) engine bleed below 150 °C in flight with wing anti ice ON
X BLEED FAULT
Continued from the previous page FLT SD PAGE LOCAL PHASE CALLED WARNING INHIB
3, 4, 5, 8
position disagree with selected position
ENG 1 (2) HP VALVE FAULT
BLEED
HP valve is abnormally closed
BLEED MONITORING FAULT
NIL
Both BMC faulty
L(R) WING LEAK DET FAULT
Both detection loops inop in one wing
NIL
NIL
BLEED MONIT SYS 1(2) FAULT One BMC faulty
3, 4, 5, 6, 7, 8
NIL
ENG 1(2) LEAK DET FAULT
3, 4, 5, 7, 8
Detection loop inop in pylon
MEMO DISPLAY APU BLEED appears in green if the APU is available and the APU BLEED pb-sw is ON.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-36-30 P 2/2 03 APR 12
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-36-40-00001484.0002001 / 17 MAR 11 Applicable to: ALL
NORM AC 1 2 ENG 1
DC2
ENG 2
DC2
AUTO CONTROL MANUAL CONTROL
DC2
BMC BLEED VALVES, HP VALVES AND FAN AIR VALVES X-BLEED VALVE
DC
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
AC ESS
EMER ELEC DC HOT ESS SHED SHED
SHED
DSC-36-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS PNEUMATIC A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-36-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS WATER / WASTE
Intentionally left blank
AIRCRAFT SYSTEMS WATER / WASTE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-38-PLP PRELIMINARY PAGES TABLE OF CONTENTS
DSC-38-10 Description General.....................................................................................................................................................................A Potable Water.......................................................................................................................................................... B Wastewater System.................................................................................................................................................C Toilet System........................................................................................................................................................... D
DSC-38-20 ELECTRICAL SUPPLY BUS EQUIPMENT LIST.......................................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-38-PLP-TOC P 1/2 29 JUL 11
AIRCRAFT SYSTEMS WATER / WASTE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-38-PLP-TOC P 2/2 29 JUL 11
AIRCRAFT SYSTEMS WATER / WASTE A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-38-10-00001485.0001001 / 19 JAN 11 Applicable to: ALL
The water and waste system : ‐ distributes potable water to the toilets and the galleys. ‐ disposes waste water. ‐ stores toilet wastes. The system is insulated to prevent water leaks and ice build up. The water and waste control panel is on the forward cabin attendant’s panel. POTABLE WATER Ident.: DSC-38-10-00001486.0004001 / 16 MAR 11 Applicable to: ALL
Potable water is stored in a 200 l tank in front of the wing box behind the forward cargo compartment. While airborne, the aircraft uses bleed air to pressurize the water system ; on the ground, it uses air from the service panel pressure port. Potable water is piped to the galleys and lavatories. The system can be filled or drained from the service panel under the fuselage. Indicators on the forward attendant’s panel and the aft service panel show how much water is in the water tank.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-38-10 P 1/6 29 JUL 11
AIRCRAFT SYSTEMS WATER / WASTE A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW OPERATING MANUAL
WASTEWATER SYSTEM Ident.: DSC-38-10-00001487.0001001 / 19 JAN 11 Applicable to: ALL
Wastewater from the galleys and from the sinks in the lavatories, drains overboard through two anti-iced drain masts. The forward mast drains wastewater from the forward cabin; the aft mast drains it from the aft cabin. Differential pressure discharges the wastewater in flight, and gravity does so on the ground.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
DSC-38-10 P 2/6 29 JUL 11
AIRCRAFT SYSTEMS WATER / WASTE A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW OPERATING MANUAL
TOILET SYSTEM Ident.: DSC-38-10-00001488.0002001 / 16 MAR 11 Applicable to: ALL
Differential pressure forces waste from the toilet bowls into the waste storage tank. On ground, and at altitudes below 16 000 ft , a vacuum generator produces the necessary pressure differential. Clear water from the potable water system flushes the toilets. A flush control unit, within each toilet, controls the flush sequence. The Vacuum System Controller (VSC) furnishes operational information, such as the waste level in the storage tank, to the Flight Attendants’ panel, and maintenance information and a test program to the Centralized Fault Display System. The waste tank has a usable capacity of 170 l . Ground personnel services the waste tank via a single service panel under the fuselage. A manual shut-off valve isolates an inoperative toilet.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← C to D →
DSC-38-10 P 3/6 29 JUL 11
AIRCRAFT SYSTEMS WATER / WASTE A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW OPERATING MANUAL
ARCHITECTURE
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-38-10 P 4/6 29 JUL 11
AIRCRAFT SYSTEMS WATER / WASTE A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW OPERATING MANUAL
SCHEMATIC
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D
DSC-38-10 P 5/6 29 JUL 11
AIRCRAFT SYSTEMS WATER / WASTE A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-38-10 P 6/6 29 JUL 11
AIRCRAFT SYSTEMS WATER / WASTE A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-38-20-00001489.0002001 / 23 FEB 11 Applicable to: ALL
NORM AC
POTABLE WATER SYS WATER HEATER WATER DRAINING VACUUM GENERATOR PRESSURIZED WATER SYS FLUSH CONTROL UNITS VACUUM SYS CONTROLLER
DC
DC BAT
AC ESS
EMER ELEC DC ESS
HOT
GND/FLT AC2 GND/FLT AC2 AC2
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
GND/FLT GND/FLT
A
DSC-38-20 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS WATER / WASTE A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-38-20 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM
Intentionally left blank
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-45-PLP PRELIMINARY PAGES TABLE OF CONTENTS
DSC-45-10 Description GENERAL................................................................................................................................................................ A COMPONENTS........................................................................................................................................................B MODES OF OPERATION....................................................................................................................................... C Architecture.............................................................................................................................................................. D FAILURE/FAULT CLASSIFICATION.......................................................................................................................E FUNCTIONS OF THE CENTRALIZED FAULT DISPLAY SYSTEM (CFDS)..........................................................F COCKPIT/CFDS INTERFACE................................................................................................................................ G
DSC-45-20 System Operation Maintenance Menu.................................................................................................................................................. A LAST (or CURRENT) LEG REPORT......................................................................................................................B Last (or Current) Leg ECAM Report....................................................................................................................... C PREVIOUS LEGS REPORT................................................................................................................................... D AVIONICS STATUS.................................................................................................................................................E SYSTEM REPORT/TEST........................................................................................................................................ F GMT/DATE INITIALIZATION...................................................................................................................................G BACK UP MODE.....................................................................................................................................................H ACARS Print Program.............................................................................................................................................. I
DSC-45-25 Data Loading General.....................................................................................................................................................................A Data Loading Selector on the Overhead Panel...................................................................................................... B
DSC-45-30 PRINTER GENERAL................................................................................................................................................................ A SYSTEM DESCRIPTION.........................................................................................................................................B
DSC-45-40 ELECTRICAL SUPPLY BUS EQUIPMENT LIST.......................................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-45-PLP-TOC P 1/2 30 MAY 12
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-45-PLP-TOC P 2/2 30 MAY 12
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-45-10-00001490.0001001 / 09 DEC 09 Applicable to: ALL
The purpose of the Centralized Fault Display System (CFDS) is to make the maintenance task easier by displaying fault messages in the cockpit and permitting the flight crew to make some specific tests. There are two levels of maintenance : at the line stop : removal and replacement of equipment at the main base : troubleshooting COMPONENTS Ident.: DSC-45-10-00001491.0001001 / 09 DEC 09 Applicable to: ALL
The CFDS includes : ‐ the BITE (Built-In Test Equipment) for each electronic system ‐ a central computer, the Centralized Fault Display Interface Unit (CFDIU) ‐ two MCDUs (Multipurpose Control and Display Units), used also for FMGS (Flight Management and Guidance System), AIDS (Aircraft Integrated Data System), and ACARS (Aircraft Communication And Reporting System, if installed), which work with the CFDIU to display information or initiate tests ‐ one printer. If a main channel of the CFDIU fails, the backup channel takes over. MODES OF OPERATION Ident.: DSC-45-10-00001492.0001001 / 09 DEC 09 Applicable to: ALL
The CFDS operates in two main modes : ‐ the NORMAL mode or REPORTING mode (in flight) ‐ the INTERACTIVE mode or MENU mode (on ground). In NORMAL mode, the CFDS records and displays the failure messages transmitted by each system BITE. In INTERACTIVE mode, the CFDS allows any BITE to be connected with the MCDU in order to display the maintenance data stored and formatted by the BITE or to initiate a test.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to C
DSC-45-10 P 1/6 25 NOV 11
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW OPERATING MANUAL
ARCHITECTURE Ident.: DSC-45-10-00001493.0002001 / 14 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D
DSC-45-10 P 2/6 25 NOV 11
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW OPERATING MANUAL
FAILURE/FAULT CLASSIFICATION Ident.: DSC-45-10-00001494.0002001 / 14 NOV 11 Applicable to: ALL
The Centralized Fault Display System (CFDS) identifies the faulty system and puts any failures or faults into one of three classes : Class 1 : Failures indicated to the flight crew by means of the ECAM, or other flight deck effect. They must be repaired or entered in the MEL (Minimum Equipment List) before the aircraft can depart. Class 2 : Faults indicated to maintenance personnel by the CFDS and which trigger a MAINT status entry on the maintenance part of the ECAM status page. The aircraft can operate with these faults, but they must be rectified within the timescale defined in the Trouble Shooting Manual (TSM). Class 3 : Faults indicated to maintenance personnel by the CFDS, but which do not trigger a MAINT status. The operator may have these faults corrected at his convenience. Failure/fault classes
Operational consequences Indication to the flight crew
Dispatch consequences
Indication to the maintenance team
Class 1
Class 2
Class 3
YES
NO
YES
YES NO Available on ECAM status page.
Automatically displayed ‐ Warning or caution messages on Engine Warning Display ‐ Flag or indication in the flight deck.
Refer to MMEL/MI-00-08 ECAM and MAINTENANCE STATUS
Refer to MEL may be : "GO" "GO IF" "NO GO"
YES Automatically print out at the end of each flight : Fault messages on the CFDS Post Flight Report.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E
NO
MEL not applicable
YES Available on request through system report/Test
DSC-45-10 P 3/6 25 NOV 11
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW OPERATING MANUAL
FUNCTIONS OF THE CENTRALIZED FAULT DISPLAY SYSTEM (CFDS) Ident.: DSC-45-10-00001495.0002001 / 09 DEC 09 Applicable to: ALL
The main functions of the CFDS are : ‐ obtaining and storing messages transmitted by the connected system BITEs, or by the Flight Warning Computer (Warning and Caution titles) ‐ Detailing the maintenance phases.
‐ Presenting maintenance reports : • Last leg report • Last leg ECAM report • Previous leg report • Avionics status • System report test • Post-flight report.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F
DSC-45-10 P 4/6 25 NOV 11
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW OPERATING MANUAL
COCKPIT/CFDS INTERFACE Ident.: DSC-45-10-00001496.0001001 / 09 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
G
DSC-45-10 P 5/6 25 NOV 11
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-45-10 P 6/6 25 NOV 11
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW OPERATING MANUAL
MAINTENANCE MENU Ident.: DSC-45-20-00001497.0002001 / 14 MAY 12 Applicable to: ALL
The CFDS uses menus displayed on the MCDU. The operator selects functions or reports from these menus. Pressing the MCDU MENU key and then selecting CFDS brings up the MAINTENANCE MENU page (different pages for the aircraft in flight and the aircraft on the ground).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-45-20 P 1/14 30 MAY 12
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW OPERATING MANUAL
LAST (OR CURRENT) LEG REPORT Ident.: DSC-45-20-00001498.0001001 / 09 FEB 11 Applicable to: ALL
The LAST LEG REPORT (on the ground) or the CURRENT LEG REPORT (in flight), list all class 1 failures and class 2 faults and all system failure and system fault messages received by the CFDS during the last flight leg or the current flight leg. Pressing the IDENT key displays a list of the systems 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← A to B →
DSC-45-20 P 2/14 30 MAY 12
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
SYSTEM OPERATION
(called identifiers) affected by the failure or fault, which helps the pilot or maintenance person to identify the failure or fault.
LAST (OR CURRENT) LEG ECAM REPORT Ident.: DSC-45-20-A-NG00095 Applicable to: ALL Ident.: DSC-45-20-A-00001499.0001001 / 09 DEC 09
GENERAL In flight
:
On the ground :
The CURRENT LEG ECAM REPORT displays the primary and independent warning (class I) messages and MAINTENANCE STATUS (class II) messages of the current flight leg. The LAST LEG ECAM REPORT displays the primary and independent warning (class I) messages plus MAINTENANCE STATUS (class II) messages of the last flight leg.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
DSC-45-20 P 3/14 30 MAY 12
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW OPERATING MANUAL
Note:
This screen displays PRINT only if the printer is installed.
Ident.: DSC-45-20-A-00001500.0002001 / 14 MAY 12
POST FLIGHT REPORT At the end of a flight, LAST LEG and LAST LEG ECAM REPORTS are printed out automatically after landing (30 s after reaching 80 kt). The flight or ground crew can also print them out by selecting POST FLIGHT REP PRINT. It is also automatically sent to the ground, using ACARS system after the last engine shutdown, or manually by selecting the SEND key.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C→
DSC-45-20 P 4/14 30 MAY 12
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
SYSTEM OPERATION
PREVIOUS LEGS REPORT Ident.: DSC-45-20-00001501.0001001 / 09 DEC 09 Applicable to: ALL
This report gives access to the POST FLIGHT REPORTS of the previous 63 flight legs.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← C to D →
DSC-45-20 P 5/14 30 MAY 12
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW OPERATING MANUAL
On ground, the Operator can print copies of the screen. If ACARS is installed, the Operator can send the flight report (Refer to DSC-45-20-A Last (or Current) Leg ECAM Report - Post Flight Report Print). AVIONICS STATUS Ident.: DSC-45-20-00001502.0001001 / 09 DEC 09 Applicable to: ALL
This screen displays the list of systems affected by a failure or fault. If a system is affected by at least a Class 3 fault, CLASS 3 appears beside it. The display is continuously updated.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← D to E
DSC-45-20 P 6/14 30 MAY 12
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW OPERATING MANUAL
SYSTEM REPORT/TEST Ident.: DSC-45-20-00001503.0001001 / 09 DEC 09 Applicable to: ALL
This screen gives the operator access to all electronic systems. The CFDIU enters into interactive dialogue with the selected system.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F→
DSC-45-20 P 7/14 30 MAY 12
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←F→
DSC-45-20 P 8/14 30 MAY 12
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW OPERATING MANUAL
In the above example, the operator has called up menus of the selected systems : ‐ LAST or PREVIOUS LEG REPORT presents the list of Line-Replaceable Units (LRUs) affected by a failure. ‐ LRU IDENTIFICATION contains the part numbers of all LRUs in the system. ‐ GND SCANNING runs the flight monitoring on the ground and indicates the faulty LRU. ‐ CLASS 3 FAULTS lists class 3 faults detected by the system during the last flight leg. ‐ SYSTEM CONFIGURATION presents the system configuration in a digital form. Note:
These screens (except LAST or PREVIOUS LEG REPORT) are not shown above. GMT/DATE INITIALIZATION
Ident.: DSC-45-20-00001504.0001001 / 09 DEC 09 Applicable to: ALL
A CFDIU clock is synchronized with the cockpit clock in order to keep GMT (UTC) displayed on the ECAM lower display (except in flight Phases 1 and 2, if the weight and balance system is installed). If the cockpit clock fails, the CFDIU clock continues to display GMT (UTC) on the ECAM lower display. If electrical power is interrupted for more than 200 ms, the crew initializes GMT (UTC) and the DATE via the MCDU : ‐ Write GMT (UTC) in the scratchpad, then press the “INIT GMT” key. ‐ Do the same for the month and day.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← F to G →
DSC-45-20 P 9/14 30 MAY 12
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G
DSC-45-20 P 10/14 30 MAY 12
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW OPERATING MANUAL
BACK UP MODE Ident.: DSC-45-20-00001505.0001001 / 09 DEC 09 Applicable to: ALL
If the CFDIU's main channel fails, the backup channel allows the CFDS to operate in backup mode : ‐ on the ground only ‐ through MCDU1 ‐ in one mode of operation only : SYSTEM REPORT/TEST ‐ without the PRINTER or ACARS. The system changes over from main channel to backup channel : ‐ Automatically in case of an important failure (power supply, for example). In this case, when the operator selects CFDS on the MCDU MENU, it displays the BACKUP MODE page. ‐ Manually if the operator selects BACKUP MODE on the CFDS menu after a minor failure.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
H→
DSC-45-20 P 11/14 30 MAY 12
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
SYSTEM OPERATION
ACARS PRINT PROGRAM Ident.: DSC-45-20-00005361.0001001 / 14 FEB 11 Applicable to: ALL
This function gives access to reprogramming page. The programming is provided by the ACARS or manually (on the ground or in flight) :
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← H to I →
DSC-45-20 P 12/14 30 MAY 12
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW OPERATING MANUAL
Note:
The CFDIU memorizes all manual programming so that at initialisation the last configuration will be retained.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←I
DSC-45-20 P 13/14 30 MAY 12
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-45-20 P 14/14 30 MAY 12
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
DATA LOADING
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-45-25-00001506.0001001 / 10 JAN 11 Applicable to: ALL
With the data loading system, it is possible to upload databases and operational software, or to download system reports from various onboard computers. The data transfer is performed via 3.5 in disks and a portable data loader, or the aircraft fixed Multipurpose Disk Drive Unit (MDDU). DATA LOADING SELECTOR ON THE OVERHEAD PANEL Ident.: DSC-45-25-00001507.0001001 / 10 JAN 11 Applicable to: ALL
When the data loading selector is ON, the 3 keys (NEXT, PREV, SEL CTRL) enable the display and selection of various applicable aircraft systems (FMGC, TCAS etc...).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
DSC-45-25 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
DATA LOADING
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-45-25 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
PRINTER
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-45-30-00001508.0001001 / 09 DEC 09 Applicable to: ALL
The printer prints reports from the following systems (if installed) : ACARS, AIDS, FMGC, CFDIU and EVMU. It prints these on paper, and does so either on the ground or in flight. The printer is installed at the rear of the pedestal on the right side. SYSTEM DESCRIPTION Ident.: DSC-45-30-00001509.0001001 / 09 DEC 09 Applicable to: ALL
(1)
SLEW sw : The SLEW switch is used to feed paper after having loaded a new roll.
(2)
PRINTER DOOR LATCH : The printer door latch locks the door used for loading paper.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
DSC-45-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
PRINTER
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-45-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-45-40-00001510.0001001 / 09 DEC 09 Applicable to: ALL
NORM AC CFDS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DC
AC ESS
EMER ELEC DC ESS
HOT
DC1
A
DSC-45-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS MAINTENANCE SYSTEM A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-45-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS INFORMATION SYSTEMS
Intentionally left blank
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-46-PLP PRELIMINARY PAGES TABLE OF CONTENTS
DSC-46-10 General Introduction...............................................................................................................................................................A System Architecture.................................................................................................................................................B Cockpit Arrangement............................................................................................................................................... C
DSC-46-20 ATSU Communications Function Introduction...............................................................................................................................................................A Downlink and Uplink Messages.............................................................................................................................. B Datalink/Voice Transfer on VHF 3.......................................................................................................................... C Datalink/Voice Transfer on HF 1.............................................................................................................................D Scratchpad Messages on the COMM Menu........................................................................................................... E
DSC-46-30 AOC Applications Introduction...............................................................................................................................................................A Remote Applications................................................................................................................................................ B
DSC-46-40 CNS/ATM Introduction...............................................................................................................................................................A
DSC-46-60 Warnings and Cautions Warnings And Cautions...........................................................................................................................................A
DSC-46-70 Electrical Supply Bus Equipment List..................................................................................................................................................A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-46-PLP-TOC P 1/2 30 MAY 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-46-PLP-TOC P 2/2 30 MAY 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
INTRODUCTION Ident.: DSC-46-10-00001511.0002001 / 16 MAR 11 Applicable to: ALL
The information system manages the datalink communication and provides the flight crew with information coming from the airline and from the Air Traffic Control (ATC). The information system consists mainly of an Air Traffic Service Unit (ATSU), two Data-link Control and Display Units (DCDU ) located on the left and right central panels, and two illuminated pushbuttons “ATC MSG”. The ATSU manages: ‐ The Air-Ground communications through the appropriate communication media (SATCOM VHF data radio or HF data radio). ‐ The exchange of information between the aircraft and:
or
• The Operator according to the Airline Operational Control (AOC) applications defined in the ATSU, or • The Air Traffic Control. ‐ The information display via the MCDU and the DCDU ‐ The appropriate warning for flight crew information.
.
The ACARS functions are included in the ATSU. SYSTEM ARCHITECTURE Ident.: DSC-46-10-00001512.0002001 / 16 MAR 11 Applicable to: ALL
The ATSU is connected to the following systems:
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-46-10 P 1/4 30 MAY 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
The ATSU supports uplink and downlink messages. They may be either automatically or manually handled, with or without information to the crew.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-46-10 P 2/4 30 MAY 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
COCKPIT ARRANGEMENT Ident.: DSC-46-10-00001513.0002001 / 16 MAY 12 Applicable to: ALL
The pilot interface consists of: ‐ The DCDU , to display any up and downlink ATC messages. ‐ The “ATC MSG pb ”, to alert the crew of any ATC uplink arrivals , associated with a dedicated chime . ‐ The MCDU, to handle the AOC and ATC functions and data transfer with the DCDU . ‐ The PRINTER, to print any type of messages. ‐ The ECAM, for operational information. ‐ The RMP, to allow frequencies’ tuning.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-46-10 P 3/4 30 MAY 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-46-10 P 4/4 30 MAY 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
ATSU COMMUNICATIONS FUNCTION
FLIGHT CREW OPERATING MANUAL
INTRODUCTION Ident.: DSC-46-20-00001514.0002001 / 14 FEB 11 Applicable to: ALL
The Air-Ground communications are managed by the ATSU communication function either: ‐ automatically without pilot action, ‐ or manually using MCDU pages and/or RMPs. The pilot controls the communications through the COMM MENU page on MCDU.
(*)
These fields are customized according to the AOC programming.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-46-20 P 1/10 03 APR 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
ATSU COMMUNICATIONS FUNCTION
FLIGHT CREW OPERATING MANUAL
DOWNLINK AND UPLINK MESSAGES Ident.: DSC-46-20-A-NG00096 Applicable to: ALL Ident.: DSC-46-20-A-00001515.0001001 / 17 MAR 11
DOWNLINK MESSAGES Aircraft to ground messages (downlink) comprise maintenance, monitoring, operational, performance and cabin data. Reports generated by a peripheral (CFDS, AIDS, FMS, CABIN TERMINAL) system can be automatically downlinked by the ATSU depending on each airline AOC programming. Ident.: DSC-46-20-A-00001516.0016001 / 17 MAR 11
UPLINK MESSAGES Ground to aircraft messages (uplink) either contain crew information (wind for example) or data to be uploaded into the FMS (Flight plan for example). Uplinks can also contain requests for transmission of specific downlink reports. Messages are indicated to the crew by: ‐ “COMPANY MSG” memo (in green) on the ECAM memo, or ‐ “COMPANY CALL” memo (in green) on the ECAM memo, or ‐ “COMPANY ALERT” memo (pulses green for around 180 s , then remains steady, and is associated with a buzzer sound for 1 s ) on the ECAM memo, or ‐ The MCDU MENU light comes on, if the MCDU is not in the mode where the uplink message can be displayed, or ‐ A Hard copy from the cockpit printer, depending on airline's AOC programming. Note:
A steady green “COMPANY DATALINK STBY” memo is displayed, when the AOC datalink air-ground communication is temporarily unavailable, but not lost.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
DSC-46-20 P 2/10 03 APR 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ATSU COMMUNICATIONS FUNCTION
Depending on the memo displayed on the ECAM, the uplink message indications are available, as the following examples: ‐ For a "COMPANY MSG" ECAM memo:
On the AOC MENU page, pressing the [1R] key displays the received message and clears the ECAM memo. Note:
1. AOC MENU page is customized, according to AOC programming. 2. A "COMPANY ALERT" ECAM memo is processed in the same way.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
DSC-46-20 P 3/10 03 APR 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ATSU COMMUNICATIONS FUNCTION
‐ For a "COMPANY CALL" ECAM memo:
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
DSC-46-20 P 4/10 03 APR 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
ATSU COMMUNICATIONS FUNCTION
FLIGHT CREW OPERATING MANUAL
On the MCDU's COMPANY CALL page: Pressing the [1L] key clears the ACARS CALL memo and activates the VHF voice frequency on VHF 3 associated with the memo. When in VHF 3 voice mode, pressing the [1R] key reverts VHF 3 to DATALINK mode.
DATALINK/VOICE TRANSFER ON VHF 3 Ident.: DSC-46-20-B-NG00097 Applicable to: ALL Ident.: DSC-46-20-B-00001517.0016001 / 17 MAR 11
GENERAL VHF 3 can be used in voice mode in case of a: ‐ VHF 1 or VHF 2 failure, or ‐ COMPANY CALL. The green “COMPANY CALL” memo indicates that a request for voice contact was received from the ground. The green “VHF 3 VOICE” memo indicates that the VHF 3 tranceiver operates in voice mode. Therefore, datalink communication is interrupted. The voice frequency may be either tuned by the ATSU or tuned by the crew through the RMP. The DATALINK/VOICE transfer can be done either from any of the RMPs or from the ATSU through the VHF 3 VOICE DIRECTORY MCDU page.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
DSC-46-20 P 5/10 03 APR 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ATSU COMMUNICATIONS FUNCTION
Ident.: DSC-46-20-B-00001518.0023001 / 17 MAR 11
RMP DATALINK/VOICE TRANSFER FROM A RMP
Pressing again the transfer key on RMP returns to DATALINK mode.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C→
DSC-46-20 P 6/10 03 APR 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ATSU COMMUNICATIONS FUNCTION
Ident.: DSC-46-20-B-00001519.0025001 / 14 FEB 11
ATSU DATALINK/VOICE TRANSFER FROM THE ATSU THROUGH THE VHF 3 VOICE DIRECTORY PAGE
On the VHF 3 VOICE DIRECTORY MCDU page: • Below the title, it is indicated whether VHF 3 is in “VOICE”, or “DATA” mode. • Fields [1L] to [3L] and [1R] to [3R] display the voice frequencies defined in the airline database. Pressing one of the adjacent keys activates the corresponding preselected voice frequency. • Field [4L] displays the voice frequency provided in the last received COMPANY CALL message. Pressing the adjacent key deletes the adjacent COMPANY CALL memo and activates the voice frequency on VHF 3. Note:
After the activation of the voice frequency, DATA remains displayed in the active window of the RMP.
Pressing the [5R] key returns to DATALINK mode.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C
DSC-46-20 P 7/10 03 APR 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
ATSU COMMUNICATIONS FUNCTION
FLIGHT CREW OPERATING MANUAL
DATALINK/VOICE TRANSFER ON HF 1 Ident.: DSC-46-20-00001520.0004001 / 14 FEB 11 Applicable to: ALL
HF 1 can also be used in data mode. It constitutes an alternative to VHF 3 and SATCOM. The datalink HF frequency tuning is automatically managed. The green HF VOICE memo indicates that the HF transceiver operates in voice mode, therefore, datalink communications are interrupted. The datalink/voice transfer can be done from any of the RMPs as follows:
Pressing the transfer key on the RMP again returns to voice mode.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D
DSC-46-20 P 8/10 03 APR 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
ATSU COMMUNICATIONS FUNCTION
FLIGHT CREW OPERATING MANUAL
SCRATCHPAD MESSAGES ON THE COMM MENU Ident.: DSC-46-20-00001521.0002001 / 27 JAN 12 Applicable to: ALL
MESSAGE NOT ALLOWED ENTER A/C REGISTR
COLOR W A
CONDITIONS It is not permitted to press this key. The aircraft registration number is not valid. To enter this parameter, Refer to PRO-SUP-46 ATSU Initialization. PRINT FAILED W A print command is not successful. FORMAT ERROR W The message was entered in an inappropriate format. VHF 3 SWITCH IMPOSSIBLE A It is not possible to switch from VHF 3 voice mode to VHF 3 data mode. A The new SCAN MASK is not available. DEFAULT VHF SP LIST (1) The system displays the default SCAN MASK instead. SYSTEM BUSY-TRY LATER W The system is busy. The command, selected by the flight crew, cannot currently be performed. COMMAND NOT AVAIL W The command is not available. VHF 3 CAN BE SET IN VOICE A VHF 3 datalink communications are lost. However, VHF 3 can be used in voice mode. No service provider has been selected. ENTER VHF 3 SCAN SELECT (1) A To select a service provider, Refer to PRO-SUP-46 ATSU Initialization. ENTER A/L ID A The airline identification number is not valid. To enter this parameter, Refer to PRO-SUP-46 ATSU Initialization. PRT MSG PRINT FAIL W Automatic print of an AOC uplink message was not successful. (1) Depending on airline customization, access to the SCAN SELECT menu may not be possible. If it is not, the DEFAULT VHF SP LIST and ENTER VHF 3 SCAN SELECT scratchpad messages are not applicable.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E
DSC-46-20 P 9/10 03 APR 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
ATSU COMMUNICATIONS FUNCTION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-46-20 P 10/10 03 APR 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
AOC APPLICATIONS
FLIGHT CREW OPERATING MANUAL
INTRODUCTION Ident.: DSC-46-30-00001522.0001001 / 18 MAR 11 Applicable to: ALL
Two kinds of Airline Operational Control (AOC) applications are provided: ‐ Remote AOC applications embedded in systems peripheral to ATSU (AIDS, CFDS, FMGC, CABIN TERMINAL) ‐ Hosted AOC applications uploaded into the ATSU. Due to the highly customized aspect of the hosted AOC applications, only the remote AOC applications are described in this chapter. REMOTE APPLICATIONS Ident.: DSC-46-30-00001523.0001001 / 14 NOV 11 Applicable to: ALL
The remote AOC applications are accessible by pressing the related system key on the MCDU MENU page.
Message/reports are processed by the AOC peripherals (FMGC, AIDS, CFDS) ; the ATSU communication function only routes the request according to the company routing policy. FLIGHT MANAGEMENT SYSTEM (FMGC) Refer to DSC-22_45 General Through the FMGC interface it is possible to access the following data: ‐ Wind data (F-PLN page) ‐ Takeoff data (uplink only)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-46-30 P 1/4 25 NOV 11
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
AOC APPLICATIONS
FLIGHT CREW OPERATING MANUAL
‐ F-PLN initialization (uplink only) ‐ Pre-flight, post-flight report and ACARS print/program (downlink only). Refer to DSC-22_20-70 Flight Plan Initialization Through ACARS
(1)
Pressing key selects related system then
(2)
Pressing key gives access to takeoff data (Uplink only)
(3)
Pressing key gives access to wind data (F-PLN page)
(4)
Pressing key gives access to F-PLN initialisation and wind data (Uplink only)
(5)
Pressing key gives access to Pre-flight, Post-flight report and ACARS print/program (downlink only). Refer to DSC-22_20-70 Flight Plan Initialization Through ACARS.
CENTRALIZED FAULT DISPLAY SYSTEM (CFDS) (Refer to DSC-45-20 Maintenance Menu) 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
DSC-46-30 P 2/4 25 NOV 11
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
AOC APPLICATIONS
FLIGHT CREW OPERATING MANUAL
Through the CFDS interface it is possible to downlink the following data: ‐ Post flight report (on the ground) or current flight report (in flight) which includes: • All failure messages detected by the BITEs • The warnings displayed to the crew during the last or current flight leg. Report can be downlinked upon crew action or upon ground request or automatically. ‐ Previous Flight Report (on the ground) ‐ Real-time failure and warning messages (in flight) ‐ Class 3 report (on the ground) containing all class 3 failures detected during the last flight leg. The report can be downlinked upon crew action or automatically. AIRCRAFT INTEGRATED DATA SYSTEM (AIDS) The AIDS interface provides ATSU with the data for the following applications: ‐ Aircraft Performance Monitoring (APM) ‐ Engine Condition Monitoring (ECM) ‐ APU Health Monitoring (AHM). Any of the AIDS DMU reports can be downlinked (through ATSU): ‐ Manually on the ground or in flight ‐ Automatically in real-time ‐ Upon ground request or upon automatic request from the ATSU.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-46-30 P 3/4 25 NOV 11
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
AOC APPLICATIONS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-46-30 P 4/4 25 NOV 11
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
CNS/ATM
FLIGHT CREW OPERATING MANUAL
INTRODUCTION Ident.: DSC-46-40-00012715.0004001 / 29 MAR 12 Applicable to: ALL
The global Communications Navigation Surveillance/Air Traffic Management (CNS/ATM) system is made up of the C (Communications), N (Navigation) and S (Surveillance) tools, developed to provide efficient Air Traffic Management methods. Such methods include the introduction of datalink communication between pilots and controllers. This is considered to be the primary means of communication over oceans and in remote areas. The current CNS/ATM system uses ACARS networks: These networks are mainly ARINC, and SITA (Refer to DSC-23-40-40 World Map ACARS Frequencies). The related data communications are managed by the Air Traffic System Unit (ATSU), and can be supported by the SATCOM or the VHF or the HF.
The CNS/ATM system includes the following applications: ‐ The ATS Facilities Notification (AFN) ‐ The Controller Pilot Data Link Communications (CPDLC) ‐ The Automatic Dependent Surveillance-Contract (ADS-C).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-46-40 P 1/2 03 APR 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
CNS/ATM
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-46-40 P 2/2 03 APR 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-46-60-00001525.0003001 / 17 MAR 11 Applicable to: ALL
E/WD: FAILURE TITLE conditions
AURAL WARNING
MASTER LIGHT
SINGLE CHIME
MASTER CAUTION
NIL
NIL
ATSU FAULT
(Failure at ATSU initialization, if associated with ATSU INIT FAULT ECAM message).
COMPANY FAULT
AOC datalink communications failure.
SD PAGE CALLED
LOCAL WARNING
FLT PHASE INHIB
NIL
NIL
3, 4, 5, 7, 8
MEMO DISPLAY ‐ The COMPANY DATALINK STBY message is displayed in green, when AOC datalink air-ground communication is temporarily unavailable, but not lost. ‐ The COMPANY CALL message is displayed in green, when the aircraft receives a message from the ground requesting voice communication on VHF. ‐ The COMPANY MSG message is displayed in green, when the aircraft receives a message from the ground. ‐ The COMPANY ALERT message is displayed in green, when the aircraft receives an uplink alert message, or when an AOC special condition requires a pilot action on the MCDU (depends on AOC programming). This message pulses green for 180 s, then remains steady. It is associated with a buzzer for 1 s.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-46-60 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-46-60 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-46-70-00001526.0001001 / 30 MAY 12 Applicable to: ALL
NORM
ATSU
ATSU 1
AC
DC
AC1
DC1
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DC BAT
AC ESS
EMER ELEC DC ESS
HOT
DSC-46-70 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS INFORMATION SYSTEMS A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-46-70 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS APU
Intentionally left blank
AIRCRAFT SYSTEMS APU A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-49-PLP PRELIMINARY PAGES TABLE OF CONTENTS
DSC-49-10 Description DSC-49-10-10 General General.....................................................................................................................................................................A
DSC-49-10-20 Main Components APU ENGINE...........................................................................................................................................................A ELECTRONIC CONTROL BOX.............................................................................................................................. B AIR INTAKE SYSTEM.............................................................................................................................................C STARTER................................................................................................................................................................ D FUEL SYSTEM........................................................................................................................................................ E OIL SYSTEM............................................................................................................................................................F INLET GUIDE VANES (IGV)...................................................................................................................................G Air Bleed System.....................................................................................................................................................H CONTROLS...............................................................................................................................................................I GROUND OPERATION SAFETY DEVICES........................................................................................................... J
DSC-49-20 Controls and Indicators Overhead Panel....................................................................................................................................................... A EXTERNAL CONTROLS......................................................................................................................................... B ECAM APU Page.................................................................................................................................................... C
DSC-49-30 Warnings and Cautions Warnings and Cautions........................................................................................................................................... A
DSC-49-40 Electrical Supply BUS EQUIPMENT LIST.......................................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-49-PLP-TOC P 1/2 30 MAY 12
AIRCRAFT SYSTEMS APU A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-49-PLP-TOC P 2/2 30 MAY 12
AIRCRAFT SYSTEMS APU A318/A319/A320/A321
DESCRIPTION - GENERAL
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-49-10-10-00001527.0004001 / 03 FEB 11 Applicable to: ALL
GENERAL The Auxiliary Power Unit (APU) is a self-contained unit that makes the aircraft independent of external pneumatic and electrical power supplies. On the ground ‐ It supplies bleed air for starting the engines and for the air conditioning system ‐ It supplies electrical power to the electrical system. During takeoff ‐ It supplies bleed air for air conditioning, thus avoiding a reduction in engine thrust caused by the use of engine bleed air for this purpose when optimum aircraft performance is required. In flight ‐ It backs up the electrical system ‐ It backs up the air conditioning ‐ It can be used to start the engines. The APU may obtain power for starting from the aircraft's batteries or normal electrical system, or from ground service. APU starting is permitted throughout the normal flight envelope (Refer to LIM-49-20 Envelope). The ECAM displays APU parameters.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-49-10-10 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS APU A318/A319/A320/A321
DESCRIPTION - GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-49-10-10 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS APU A318/A319/A320/A321
DESCRIPTION - MAIN COMPONENTS
FLIGHT CREW OPERATING MANUAL
APU ENGINE Ident.: DSC-49-10-20-00001528.0001001 / 09 DEC 09 Applicable to: ALL
The basic element of the APU is a single-shaft gas turbine that delivers mechanical shaft power for driving the accessory gearbox (electrical generator, starter, etc.) and produces bleed air (engine starting and pneumatic supply). ELECTRONIC CONTROL BOX Ident.: DSC-49-10-20-00001529.0001001 / 09 DEC 09 Applicable to: ALL
The Electronic Control Box (ECB) is a full-authority digital electronic controller that performs the bulk of the APU system logic for all modes of engine operation, such as : ‐ Sequences the start and monitors it. ‐ Monitors speed and temperature. ‐ Monitors bleed air. ‐ Sequences the shutdown. ‐ Controls the automatic shutdown. AIR INTAKE SYSTEM Ident.: DSC-49-10-20-00001530.0001001 / 09 DEC 09 Applicable to: ALL
The air intake and an electrically operated flap allow external air to reach the compressor inlet. STARTER Ident.: DSC-49-10-20-00001531.0001001 / 09 DEC 09 Applicable to: ALL
The ECB controls the electric starter. The starter engages if the air intake is fully open and the MASTER SW and the START pushbutton are ON. FUEL SYSTEM Ident.: DSC-49-10-20-00001532.0001001 / 09 DEC 09 Applicable to: ALL
The left fuel feed line supplies the APU. The required pressure is normally available from tank pumps. If pressure is not available (batteries only or pumps off) the APU FUEL PUMP starts automatically. The ECB controls the fuel flow.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to E
DSC-49-10-20 P 1/4 29 JUL 11
AIRCRAFT SYSTEMS APU A318/A319/A320/A321
DESCRIPTION - MAIN COMPONENTS
FLIGHT CREW OPERATING MANUAL
OIL SYSTEM Ident.: DSC-49-10-20-00001533.0001001 / 09 DEC 09 Applicable to: ALL
The APU has an integral independent lubrication system (for lubrication and cooling). INLET GUIDE VANES (IGV) Ident.: DSC-49-10-20-00001534.0001001 / 09 DEC 09 Applicable to: ALL
The IGVs control bleed air flow, and a fuel-pressure-powered actuator positions the IGVs. The ECB controls the actuator in response to aircraft demand. AIR BLEED SYSTEM Ident.: DSC-49-10-20-00001535.0003001 / 03 FEB 11 Applicable to: ALL
The air bleed system is fully automatic. The ECB always sets the APU speed to 100 % except for air conditioning demand, if the ambient temperature is between -18 °C and 35 °C. In this case, the ECB sets the APU speed to 99 %. For all other ambient temperatures (less than -18 °C or more than 35 °C), the ECB sets the APU speed to 100 %. CONTROLS Ident.: DSC-49-10-20-00001536.0001001 / 09 DEC 09 Applicable to: ALL
The flight crew uses the controls on the APU panel for routine shutdown. For emergency shutdown : ‐ the flight crew can push the APU FIRE handle, or ‐ the ground crew can push the APU SHUT OFF pushbutton on the interphone panel under the nose fuselage. GROUND OPERATION SAFETY DEVICES Ident.: DSC-49-10-20-00001537.0001001 / 09 DEC 09 Applicable to: ALL
The APU may run without cockpit crew supervision when the aircraft is on the ground. In case of fire in the APU compartment : ‐ APU fire warnings operate in the cockpit. ‐ A horn in the nose gear bay sounds. ‐ The AVAIL light goes out. ‐ The FAULT light in the MASTER SW lights up. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F to J →
DSC-49-10-20 P 2/4 29 JUL 11
AIRCRAFT SYSTEMS APU A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - MAIN COMPONENTS
‐ The APU shuts down. ‐ The APU fire extinguisher discharges.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←J
DSC-49-10-20 P 3/4 29 JUL 11
AIRCRAFT SYSTEMS APU A318/A319/A320/A321
DESCRIPTION - MAIN COMPONENTS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-49-10-20 P 4/4 29 JUL 11
AIRCRAFT SYSTEMS APU A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
OVERHEAD PANEL Ident.: DSC-49-20-00001538.0016001 / 19 JAN 11 Applicable to: ALL
(1)
MASTER SW pb This switch controls the electric power supply for APU operation, and its protective features. It also controls the starting and shutdown sequences. ON : The blue ON light comes on. Electric power goes to the APU system; the ECB performs a power-up test. The APU air intake flap opens. The APU fuel isolation valve opens. If no fuel tank pump is running, the APU fuel pump operates. If the aircraft has ground power or main generator power, the APU page appears on the ECAM display. OFF : Manual shutdown sequence. ‐ The ON light on the MASTER SW pb, and the AVAIL light on the START pb, go off. ‐ If the aircraft was using APU bleed air, the APU keeps running for a cooling period of 60 s. ‐ At 7 %, the air inlet flap closes.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-49-20 P 1/6 30 MAY 12
AIRCRAFT SYSTEMS APU A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FAULT lt :
Note:
(2)
CONTROLS AND INDICATORS
This amber light comes on, and a caution appears on ECAM, when an automatic APU shutdown occurs, which happens in case of: Fire (on ground only) Air inlet flap closed Overspeed No acceleration No speed EGT overtemperature No flame Underspeed Reverse flow Low oil pressure High oil temperature DC power lost (BAT OFF when aircraft on batteries only) ECB failure Loss of overspeed protection Oil system shutdown Inlet overheat Clogged oil filter Loss of EGT thermocouples
In the case of an automatic, non–emergency shutdown, the air inlet flap closes 15 min after the APU speed is lower than 7 %. If an automatic, non-emergency shutdown happens on ground, the 15 min countdown starts after liftoff.
START pb-sw ON : Blue ON light comes on. ‐ ‐ ‐ ‐
When the flap is completely open, the starter is energized. 1.5 s after the starter is energized, the ignition turns on. When N = 60 %. The APU starter is de-energized. The ignition is turned off. 2 s after N reached 95 %, or when N is above 99.5 %: The ON light on the START pb goes out. The APU may now supply bleed air and electrical power to the aircraft systems. ‐ 10 s later, the APU page disappears from the ECAM display. AVAIL lt :
This green light comes on when N is above 99.5 % or 2 s after N reaches 95 %.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-49-20 P 2/6 30 MAY 12
AIRCRAFT SYSTEMS APU A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
EXTERNAL CONTROLS Ident.: DSC-49-20-00001539.0001001 / 16 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
DSC-49-20 P 3/6 30 MAY 12
AIRCRAFT SYSTEMS APU A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
CONTROLS AND INDICATORS
←B
DSC-49-20 P 4/6 30 MAY 12
AIRCRAFT SYSTEMS APU A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
ECAM APU PAGE Ident.: DSC-49-20-00001540.0022001 / 22 MAY 12 Applicable to: ALL
(1)
AVAIL Displayed in green when APU N is above 95 %.
(2)
APU bleed air valve position Inline-Green : The APU bleed air valve is not closed. Crossline-Green : The APU bleed air valve is closed. Crossline-Amber : The APU bleed air valve is closed and the APU bleed is ON. XX-Amber : The APU bleed air valve status information is not available, or the APU BLEED pb status is not available.
(3)
APU bleed air pressure This box displays the relative bleed air pressure in green. It shows an amber XX when the ADIRS1 is not available or selected OFF or the data from the ECB are invalid or not transmitted.
(4)
APU GEN line contactor indication Displayed in green when the APU GEN line contactor is closed.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C→
DSC-49-20 P 5/6 30 MAY 12
AIRCRAFT SYSTEMS APU A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
CONTROLS AND INDICATORS
(5)
APU GEN parameters Identical to the APU GEN parameters on the ELEC page.
(6)
FUEL LO PR Displayed in amber if APU fuel pressure gets low.
(7)
FLAP OPEN Displayed in green when APU air intake flap is fully open.
(8)
APU N ‐ Displays APU speed in green. ‐ Becomes amber when N ≥ 102 %. ‐ Becomes red when N ≥ 107 %.
(9)
APU EGT
‐ Displays APU EGT in green. ‐ Becomes amber when EGT ≥ EGT MAX See *-33 °C. ‐ Becomes red when EGT ≥ EGT MAX See * (automatic shutdown begins). *
ECB calculates EGT MAX and transmits it to the ECAM. It is a function of N during start, and a function of ambient temperature when the APU is running. Maximum EGT during start: 1 090 °C. Maximum EGT with APU running: 675 °C.
(10) LOW OIL LEVEL Advisory: Displayed if the ECB detects a low APU oil level when the aircraft is on the ground, and the APU is not running.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C
DSC-49-20 P 6/6 30 MAY 12
AIRCRAFT SYSTEMS APU A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-49-30-00001541.0001001 / 19 JAN 11 Applicable to: ALL
AURAL WARNING
MASTER LIGHT
SD PAGE CALLED
LOCAL WARNING
FLT PHASE INHIB
SINGLE CHIME
MASTER CAUT
APU
APU MASTER SW FAULT lt
3, 4, 5, 7, 8
E/WD: FAILURE TITLE conditions
AUTO SHUT DOWN
automatic shut down of APU for a reason other than a fire.
EMER SHUT DOWN
use of APU shut off pushbutton on external power panel or APU FIRE pushbutton pushed. In case of APU fire on ground, the APU FIRE warning is triggered.
MEMO DISPLAY APU AVAIL appears in green when APU N is above 95 %.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-49-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS APU A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-49-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS APU A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-49-40-00001543.0002001 / 09 DEC 09 Applicable to: ALL
NORM AC
DC
ECB SUPPLY STARTER MOTOR
Note:
DC BAT X X
AC ESS
EMER ELEC DC ESS
HOT
When the system is in electrical emergency configuration, battery contactors automatically close for a maximum of 3 min when the APU MASTER SW is ON. When the aircraft is in flight, and when the system is in electrical emergency configuration, the APU start is inhibited for 45 s.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-49-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS APU A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-49-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS DOORS
Intentionally left blank
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-52-PLP PRELIMINARY PAGES TABLE OF CONTENTS
DSC-52-10 Description DSC-52-10-10 General Description............................................................................................................................................................... A
DSC-52-10-20 Passenger Doors General.....................................................................................................................................................................A Outside..................................................................................................................................................................... B Inside........................................................................................................................................................................C
DSC-52-10-30 Emergency Exits Cockpit..................................................................................................................................................................... A CABIN...................................................................................................................................................................... B
DSC-52-10-40 Cargo Doors General.....................................................................................................................................................................A FWD and AFT Cargo Doors....................................................................................................................................B BULK CARGO DOOR (if installed)......................................................................................................................... C
DSC-52-10-50 Avionics Compartment Access Door AVIONICS COMPARTMENT ACCESS DOOR.......................................................................................................A
DSC-52-10-60 Cockpit Door COCKPIT DOOR..................................................................................................................................................... A
DSC-52-10-80 Escape Slides/Rafts DOOR SLIDES........................................................................................................................................................ A WING SLIDES......................................................................................................................................................... B ESCAPE SLIDE ARRANGEMENT..........................................................................................................................C
DSC-52-20 Controls and Indicators DOOR/OXY SD Page..............................................................................................................................................A
DSC-52-30 Warnings and Cautions Warnings and Cautions........................................................................................................................................... A
DSC-52-50 ELECTRICAL SUPPLY BUS EQUIPMENT LIST.......................................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-52-PLP-TOC P 1/2 30 MAY 12
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-52-PLP-TOC P 2/2 30 MAY 12
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321
DESCRIPTION - GENERAL
FLIGHT CREW OPERATING MANUAL
DESCRIPTION Ident.: DSC-52-10-10-00001544.0002001 / 22 MAY 12 Applicable to: ALL
The A320's fuselage has: ‐ Four passenger doors ‐ Four emergency exits in the cabin ‐ Cockpit emergency exits (two sliding windows) ‐ Three cargo compartment doors ‐ Four avionic compartment access doors.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-52-10-10 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321
DESCRIPTION - GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-52-10-10 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - PASSENGER DOORS
GENERAL Ident.: DSC-52-10-20-00001545.0001001 / 20 DEC 10 Applicable to: ALL
The aircraft has four plug-type doors that open outward and forward. There are two of these on each side of the fuselage (two forward, two aft). They can be operated from inside or outside the aircraft. Normal operation is manual, with hydraulic damping. Each door has features that tailor it to emergency situations : ‐ An escape slide stowed in a container attached to the inboard lower side of the door ‐ A damper actuator that limits door travel in normal mode, but in an emergency acts as an actuator for automatic door opening ‐ A slide arming lever. When the slide arming lever is in the ARMED position, the slide is connected to the floor brackets on both sides of the door. When the door is opened, the slide inflates and deploys automatically. If the inflation bottle fails to discharge automatically, a crew member can open its valve to make it perform its function. Opening the door from the outside disarms the door and the escape slide. Each passenger door has : ‐ A mechanical locking indicator that shows whether the door is locked or unlocked ‐ One warning light to show whether the escape slide is ARMED or DISARMED ‐ One CABIN PRESSURE warning light that warns of residual pressure in the cabin.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-52-10-20 P 1/4 30 MAY 12
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - PASSENGER DOORS
OUTSIDE Ident.: DSC-52-10-20-00001546.0001001 / 20 DEC 10 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
DSC-52-10-20 P 2/4 30 MAY 12
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - PASSENGER DOORS
INSIDE Ident.: DSC-52-10-20-00001547.0002001 / 22 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-52-10-20 P 3/4 30 MAY 12
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321
DESCRIPTION - PASSENGER DOORS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-52-10-20 P 4/4 30 MAY 12
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - EMERGENCY EXITS
COCKPIT Ident.: DSC-52-10-30-00001548.0002001 / 20 DEC 10 Applicable to: ALL
The two sliding windows in the cockpit are flight crew emergency exits. A small compartment, located above each window, contains an escape rope that is long enough to reach the ground when lowered through either sliding window. The cockpit windows can only be opened from the inside.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-52-10-30 P 1/4 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - EMERGENCY EXITS
Emergency cockpit evacuation is also possible through the cockpit door escape panel. It is designed to be pushed open in the direction of the cabin after removal of the quick-release pins.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-52-10-30 P 2/4 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - EMERGENCY EXITS
CABIN Ident.: DSC-52-10-30-00001549.0001001 / 09 DEC 09 Applicable to: ALL
In case of an emergency, two inward opening emergency exits are provided on each side of the cabin, in addition to the regular cabin doors. They are also equipped with an escape slide.
The slides of the overwing emergency exits are always in armed configuration. To open : ‐ Remove HANDLE COVER : The HANDLE LIGHT and SLIDE ARMED indicator illuminate. ‐ Pull CONTROL HANDLE : The EXIT moves inwards. ‐ Lift EXIT from frame by holding the GRIPMOULD. ‐ Throw EXIT out.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
DSC-52-10-30 P 3/4 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DESCRIPTION - EMERGENCY EXITS
←B
DSC-52-10-30 P 4/4 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321
DESCRIPTION - CARGO DOORS
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-52-10-40-00001550.0001001 / 20 DEC 10 Applicable to: ALL
The aircraft has two cargo doors (three cargo doors cabin floor.
) on the right side of the fuselage below the
FWD AND AFT CARGO DOORS Ident.: DSC-52-10-40-00001551.0001001 / 20 DEC 10 Applicable to: ALL
The yellow hydraulic system opens these doors outward and upward. They lock open or closed mechanically. If the yellow system's electric pump fails, crewmen can use a hand pump to pressurize the system. This hand pump is on the hydraulic maintenance panel. The FWD and AFT cargo doors can be opened from the outside only. Note:
When the electric pump is operating the FWD or AFT cargo doors, the only other yellow system devices that can operate are braking and engine 2 reverse. BULK CARGO DOOR (IF INSTALLED)
Ident.: DSC-52-10-40-00001552.0001001 / 09 DEC 09 Applicable to: ALL
The bulk cargo door opens inward and upward. It is a plug-type door that is mechanically locked and manually operated. This door can be opened from the outside or from the inside.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to C
DSC-52-10-40 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321
DESCRIPTION - CARGO DOORS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-52-10-40 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - AVIONICS COMPARTMENT ACCESS DOOR
AVIONICS COMPARTMENT ACCESS DOOR Ident.: DSC-52-10-50-00001553.0001001 / 09 DEC 09 Applicable to: ALL
Four inward opening, manually operated, hinged doors give external access to the avionics compartments. These doors are in the lower fuselage, around the nose landing gear bay.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-52-10-50 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
DESCRIPTION - AVIONICS COMPARTMENT ACCESS DOOR
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-52-10-50 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321
DESCRIPTION - COCKPIT DOOR
FLIGHT CREW OPERATING MANUAL
COCKPIT DOOR Ident.: DSC-52-10-60-00001554.0002001 / 09 DEC 09 Applicable to: ALL
Refer to DSC-25-11-10 Cockpit Door Description for information about the secured cockpit door.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-52-10-60 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321
DESCRIPTION - COCKPIT DOOR
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-52-10-60 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321
DESCRIPTION - ESCAPE SLIDES/RAFTS
FLIGHT CREW OPERATING MANUAL
DOOR SLIDES Ident.: DSC-52-10-80-00001555.0001001 / 09 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-52-10-80 P 1/6 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DESCRIPTION - ESCAPE SLIDES/RAFTS
←A
DSC-52-10-80 P 2/6 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321
DESCRIPTION - ESCAPE SLIDES/RAFTS
FLIGHT CREW OPERATING MANUAL
WING SLIDES Ident.: DSC-52-10-80-00001556.0001001 / 16 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
DSC-52-10-80 P 3/6 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DESCRIPTION - ESCAPE SLIDES/RAFTS
←B
DSC-52-10-80 P 4/6 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321
DESCRIPTION - ESCAPE SLIDES/RAFTS
FLIGHT CREW OPERATING MANUAL
ESCAPE SLIDE ARRANGEMENT Ident.: DSC-52-10-80-00001557.0001001 / 20 DEC 10 Applicable to: ALL
Each passenger door either has a single-lane escape slide, or a single-lane slideraft, and each emergency exit has a dual-lane escape slide.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-52-10-80 P 5/6 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321
DESCRIPTION - ESCAPE SLIDES/RAFTS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-52-10-80 P 6/6 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
DOOR/OXY SD PAGE Ident.: DSC-52-20-00001558.0016001 / 10 JAN 11 Applicable to: ALL
(1)
Door Symbol Green □ : Amber ■ :
The door is closed and locked. The door is not locked.
(2)
Door Indication This appears in amber, when the door is not locked.
(3)
Slide Indication This appears in white, when the slide is armed.
(4)
Stair Symbol This appears in amber, when the stair door is not closed.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-52-20 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-52-20 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
WARNINGS AND CAUTIONS Ident.: DSC-52-30-00001559.0001001 / 16 MAR 11 Applicable to: ALL
E/WD : FAILURE TITLE conditions
L(R) FWD (AFT) AVIONICS L(R) FWD CABIN L(R) AFT CABIN L(R) FWD EMER EXIT L(R) AFT EMER EXIT FWD CARGO AFT CARGO BULK CARGO STAIRS
AURAL WARNING
MASTER LIGHT
SD PAGE CALLED
LOCAL WARNING
FLT PHASE INHIB
SINGLE CHIME
MASTER CAUT
DOOR
NIL
1, 4, 5, 7, 8, 10
Affected door not closed (proximity detectors)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-52-30 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321
WARNINGS AND CAUTIONS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-52-30 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
BUS EQUIPMENT LIST Ident.: DSC-52-50-00001562.0002001 / 20 APR 10 Applicable to: ALL
NORM AC
AC ESS
DC
DOORS and SLIDES CTL
DC BAT DC GRND CARGO DOORS FLT AIR STAIRS DC2 (1) STBY supply (normally supplied by the EMER PWR SUPPLY UNIT) (2) STBY supply
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
(1)
A
EMER ELEC DC ESS
HOT HOT2 (1)
HOT2 (2)
DSC-52-50 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS DOORS A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-52-50 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS POWER PLANT
Intentionally left blank
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-70-PLP PRELIMINARY PAGES TABLE OF CONTENTS SUMMARY OF HIGHLIGHTS
DSC-70-10 Engine General.....................................................................................................................................................................A Description............................................................................................................................................................... B
DSC-70-20 Fadec GENERAL................................................................................................................................................................ A ARCHITECTURE..................................................................................................................................................... B FUNCTIONS ...........................................................................................................................................................C Power Supply...........................................................................................................................................................D
DSC-70-30 Thrust Control System (CFM+PW) DSC-70-30-10 General General.....................................................................................................................................................................A
DSC-70-30-20 Thrust Levers THRUST LEVERS................................................................................................................................................... A
DSC-70-30-30 Thrust Rating Limit THRUST RATING LIMIT......................................................................................................................................... A
DSC-70-30-40 Thrust Control MANUAL MODE...................................................................................................................................................... A AUTOMATIC MODE................................................................................................................................................ B THRUST CONTROL................................................................................................................................................C
DSC-70-40 Fuel System (CFM) DSC-70-40-10 General General.....................................................................................................................................................................A
DSC-70-40-20 Fuel Pump Unit FUEL PUMP UNIT...................................................................................................................................................A
DSC-70-40-30 Shut-Off Valves SHUT-OFF VALVES................................................................................................................................................A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-PLP-TOC P 1/4 18 SEP 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-70-40-40 Hydromechanical Unit GENERAL................................................................................................................................................................ A FUEL FLOW ...........................................................................................................................................................B OVERSPEED GOVERNOR SYSTEM.................................................................................................................... C IDLE CONTROL...................................................................................................................................................... D FUEL HYDRAULIC SIGNALS ................................................................................................................................E
DSC-70-40-50 IDG Cooling System IDG Cooling System ...............................................................................................................................................A
DSC-70-50 OIL SYSTEM GENERAL................................................................................................................................................................ A
DSC-70-60 Airbleed System (CFM) General.....................................................................................................................................................................A COOLING.................................................................................................................................................................B
DSC-70-70 THRUST REVERSER SYSTEM GENERAL................................................................................................................................................................ A ACTUATION LOGIC................................................................................................................................................ B PROTECTION..........................................................................................................................................................C SCHEMATIC............................................................................................................................................................ D
DSC-70-80 Ignition and Starting DSC-70-80-10 General General.....................................................................................................................................................................A
DSC-70-80-20 Architecture ARCHITECTURE..................................................................................................................................................... A
DSC-70-80-30 Ignition System GENERAL................................................................................................................................................................ A Ignition for Starting.................................................................................................................................................. B CONTINUOUS IGNITION........................................................................................................................................C
DSC-70-80-40 Engine Starting System GENERAL................................................................................................................................................................ A Automatic Starting....................................................................................................................................................B Automatic Starting Sequence..................................................................................................................................C MANUAL STARTING...............................................................................................................................................D ENGINE VENTILATION (dry cranking)................................................................................................................... E Manual Starting Sequence...................................................................................................................................... F
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-PLP-TOC P 2/4 18 SEP 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-70-90 Controls and Indicators (CFM) Pedestal................................................................................................................................................................... A OVERHEAD PANEL................................................................................................................................................ B MAINTENANCE PANEL..........................................................................................................................................C ECAM.......................................................................................................................................................................D Warnings and Cautions........................................................................................................................................... E
DSC-70-98 ELECTRICAL SUPPLY ELECTRICAL SUPPLY............................................................................................................................................A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-PLP-TOC P 3/4 18 SEP 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-PLP-TOC P 4/4 18 SEP 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title DSC-70-40-50 IDG Cooling System
Toc Index
ID
A
1
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Reason Improvement of illustration quality. Documentation update: Deletion of information. Update of the description of the Fuel Recirculation System, to specify that on ground, fuel overflow in the surge tank does not inhibit the fuel recirculation to the wing tank.
DSC-70-PLP-SOH P 1/2 18 SEP 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-PLP-SOH P 2/2 18 SEP 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
ENGINE
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-70-10-00001563.0002001 / 19 JAN 11 Applicable to: ALL
The CFM 56-5B engine is a high bypass ratio turbofan. DESCRIPTION Ident.: DSC-70-10-00001564.0002001 / 16 MAR 11 Applicable to: ALL
LOW-PRESSURE (LP) COMPRESSOR/TURBINE The low-speed rotor (N1) consists of a front fan (single-stage) and a four-stage LP compressor connected to a four-stage LP turbine. HIGH-PRESSURE (HP) COMPRESSOR/TURBINE The high-speed rotor (N2) consists of a nine-stage HP compressor connected to a single-stage HP turbine. COMBUSTION CHAMBER The annular combustion chamber is fitted with 20 fuel nozzles and 2 igniters.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-70-10 P 1/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
ENGINE
FLIGHT CREW OPERATING MANUAL
ACCESSORY GEARBOX The accessory gearbox, located at the bottom of the fan case, receives torque from horizontal HP rotor drive shaft and drives gearbox mounted accessories.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-70-10 P 2/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
FADEC
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-70-20-00001565.0001001 / 09 DEC 09 Applicable to: ALL
Each powerplant has a FADEC (Full Authority Digital Engine Control) system. FADEC, also called the Electronic Control Unit (ECU), is a digital control system that performs complete engine management. FADEC has two-channel redundancy, with one channel active and one in standby. If one channel fails, the other automatically takes control. The system has a magnetic alternator for an internal power source. FADEC is mounted on the fan case. The Engine Interface Unit (EIU) transmits to FADEC the data it uses for engine management.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-70-20 P 1/6 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
FADEC
FLIGHT CREW OPERATING MANUAL
ARCHITECTURE Ident.: DSC-70-20-00001566.0005001 / 16 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
DSC-70-20 P 2/6 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
FADEC
FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-70-20 P 3/6 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
FADEC
FLIGHT CREW OPERATING MANUAL
FUNCTIONS Ident.: DSC-70-20-00001567.0001001 / 20 DEC 10 Applicable to: ALL
The FADEC system performs the following functions : Control of gas generator • control of fuel flow • acceleration and deceleration schedules • variable bleed valve and variable stator vane schedules • control of turbine clearance • idle setting Protection against engine exceeding limits • protection against N1 and N2 overspeed • monitoring of EGT during engine start Power management • automatic control of engine thrust rating • computation of thrust parameter limits • manual management of power as a function of thrust lever position • automatic management of power (A/THR demand). Automatic engine starting sequence • control of : ‐ the start valve (ON/OFF) ‐ the HP fuel valve ‐ the fuel flow ‐ the ignition (ON/OFF) • monitoring of N1, N2, FF and EGT • initiation of abort and recycle (on the ground only) Manual engine starting sequence • passive monitoring of engine • control of : ‐ the start valve ‐ the HP fuel valve ‐ the ignition Thrust reverser control • Actuation of the blocker doors • Engine setting during reverser operation Fuel recirculation control • Recirculation of fuel to the fuel tanks, depending on the engine oil temperature, the fuel system configuration, and the flight phase.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C→
DSC-70-20 P 4/6 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
FADEC
FLIGHT CREW OPERATING MANUAL
Transmission of engine parameters and engine monitoring information to cockpit indicators • Primary engine parameters • Starting system status • Thrust reverser system status • FADEC system status Detection, isolation, and recording of failures FADEC cooling POWER SUPPLY Ident.: DSC-70-20-00001568.0004001 / 22 MAY 12 Applicable to: ALL
The FADEC system is self-powered above 12 % N2.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← C to D →
DSC-70-20 P 5/6 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
FADEC
FLIGHT CREW OPERATING MANUAL
L3
FADEC POWER SUPPLY
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D
DSC-70-20 P 6/6 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - GENERAL
GENERAL Ident.: DSC-70-30-10-00001569.0001001 / 20 DEC 10 Applicable to: ALL
A FADEC dedicated to each engine controls thrust. The pilot uses the thrust levers to set the thrust in manual mode, and the FMGS sets the thrust in automatic mode. The FADEC prevents the thrust from exceeding the limit for the thrust lever position in both manual and automatic modes.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-70-30-10 P 1/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - GENERAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-30-10 P 2/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - THRUST LEVERS
THRUST LEVERS Ident.: DSC-70-30-20-00001570.0003001 / 09 DEC 09 Applicable to: ALL
The thrust levers can only be moved manually. They move over a sector that is divided into four operating segments. The sector has five positions defined by detents or stops. Thrust lever position is transmitted to the FADEC, which computes and displays the thrust rating limit and the N1 for that Thrust Lever Angle (TLA). Note:
There is no reverse idle detent. When the pilot moves the lever out of the idle stop by pulling up the reverse lever on the front of the thrust lever, he selects reverse idle.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-70-30-20 P 1/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - THRUST LEVERS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-30-20 P 2/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - THRUST RATING LIMIT
THRUST RATING LIMIT Ident.: DSC-70-30-30-00001571.0001001 / 16 MAR 11 Applicable to: ALL
The FADEC computes the thrust rating limit for each thrust lever position, as shown below. If the thrust lever is set in a detent, the FADEC selects the rating limit corresponding to this detent. If the thrust lever is set between two detents, the FADEC selects the rating limit corresponding to the higher detent.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-70-30-30 P 1/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - THRUST RATING LIMIT
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-30-30 P 2/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - THRUST CONTROL
MANUAL MODE Ident.: DSC-70-30-40-00001572.0001001 / 16 MAR 11 Applicable to: ALL
The engines are in the manual mode provided the A/THR function is : ‐ not armed or ‐ armed and not active (thrust lever not in the A/THR operating range and no alpha floor). In these conditions, each engine is controlled by the position of its thrust lever. The pilot controls thrust by moving the thrust lever between the IDLE and TOGA positions. Each position of the thrust lever within these limits corresponds to an N1. When the thrust lever is in a detent, the corresponding N1 is equal to the N1 rating limit computed by the FADEC for that engine.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-70-30-40 P 1/6 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - THRUST CONTROL
When the thrust lever is in the FLX/MCT detent : ‐ On the ground The engine runs at the flex takeoff thrust rating if the crew has selected a flex takeoff temperature on the MCDU that is higher than the current Total Air Temperature (TAT). Otherwise the engine produces Maximum Continuous Thrust (MCT). Note:
A change in FLEX TEMP during the takeoff has no effect on the thrust.
‐ After takeoff The pilot can change from FLX to MCT by moving the thrust lever to TOGA or CL, then back to MCT. After that, he cannot use the FLX rating. Note:
Setting the thrust lever out of FLX/MCT detent without reaching TOGA or CL detent has no effect.
The pilot can always get MAX TO thrust by pushing the thrust lever all the way forward. AUTOMATIC MODE Ident.: DSC-70-30-40-00001573.0001001 / 20 DEC 10 Applicable to: ALL
In the autothrust mode (A/THR function active), the FMGC computes the thrust which is limited to the value corresponding to the thrust lever position (unless the alpha-floor mode is activated).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← A to B →
DSC-70-30-40 P 2/6 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - THRUST CONTROL
INDICATIONS ON FMA The FADECs monitor the positions of the thrust levers, and trigger appropriate indications on the FMA. ASYM : appears in amber (3rd line on the FMA) if, with A/THR active and both engines running, one thrust lever is set out of the CLB detent. CLB : flashes white (2nd line on the FMA) if the thrust levers are not in CL position while the aircraft is above the altitude of thrust reduction with both engines running. MCT : flashes white (2nd line on the FMA) if the thrust levers are not in MCT position after an engine failure (with speed above green dot).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-70-30-40 P 3/6 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - THRUST CONTROL
THRUST CONTROL Ident.: DSC-70-30-40-00001574.0002001 / 16 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C→
DSC-70-30-40 P 4/6 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - THRUST CONTROL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C
DSC-70-30-40 P 5/6 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - THRUST CONTROL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-30-40 P 6/6 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FUEL SYSTEM (CFM) - GENERAL
GENERAL Ident.: DSC-70-40-10-00001585.0001001 / 16 MAR 11 Applicable to: ALL
The fuel system supplies fuel to the combustion chamber at the required flow rate, pressure, and temperature. The fuel flows from the tank, via the fuel pump unit and the fuel/oil heat exchanger, to the Hydromechanical Unit (HMU) and to the fuel nozzles.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-70-40-10 P 1/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FUEL SYSTEM (CFM) - GENERAL
←A
DSC-70-40-10 P 2/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
FUEL SYSTEM (CFM) - FUEL PUMP UNIT
FLIGHT CREW OPERATING MANUAL
FUEL PUMP UNIT Ident.: DSC-70-40-20-00001586.0001001 / 09 DEC 09 Applicable to: ALL
The HP compressor shaft drives the HP fuel pump assembly. Fuel flows through the LP pump, then through the fuel/oil heat exchanger and the HP pump (gear pump). The fuel then divides into a filtered flow for the servo fuel heater and the servo valves of the HMU, and an unfiltered flow for the metering valve of the HMU.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-70-40-20 P 1/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
FUEL SYSTEM (CFM) - FUEL PUMP UNIT
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-40-20 P 2/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
FUEL SYSTEM (CFM) - SHUT-OFF VALVES
FLIGHT CREW OPERATING MANUAL
SHUT-OFF VALVES Ident.: DSC-70-40-30-00001587.0001001 / 09 DEC 09 Applicable to: ALL
Moving the ENG1 (ENG2) MASTER switch to OFF directly commands the closing of the LP and HP fuel shut off valves for that engine's fuel system. It also closes the fuel return valve and opens the bypass valve.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-70-40-30 P 1/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
FUEL SYSTEM (CFM) - SHUT-OFF VALVES
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-40-30 P 2/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FUEL SYSTEM (CFM) - HYDROMECHANICAL UNIT
GENERAL Ident.: DSC-70-40-40-00001588.0001001 / 09 DEC 09 Applicable to: ALL
The FADEC controls the HMU, which : ‐ controls fuel flow to the engine combustion chamber ‐ controls fuel hydraulic signals to actuators ‐ protects against overspeeding. FUEL FLOW Ident.: DSC-70-40-40-00001589.0002001 / 16 MAR 11 Applicable to: ALL L3
The Fuel Metering Valve (FMV) transforms FADEC orders through a torque motor and servo valve into fuel flow to the engine fuel nozzles. The FMV resolver generates a feedback signal proportional to the FMV position. The bypass valve maintains a constant pressure drop across the FMV to ensure that the metered fuel flow is proportional to the FMV position.
L1
The FADEC computes the fuel flow that will maintain the target N1. As the FADEC maintains this N1, it allows N2 to vary while remaining between N2 minimum and N2 maximum. The FADEC also controls the engine parameters to : ‐ Limit acceleration and deceleration ; ‐ Avoid engine stall or flameout ;
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-70-40-40 P 1/4 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
FUEL SYSTEM (CFM) - HYDROMECHANICAL UNIT
FLIGHT CREW OPERATING MANUAL
‐ Limit maximum N1 and N2 ; ‐ Maintain air bleed pressure requirement. The FADEC computes an N2 correction according to the bleed configuration.
OVERSPEED GOVERNOR SYSTEM Ident.: DSC-70-40-40-00001590.0001001 / 09 DEC 09 Applicable to: ALL
Independent of the FADEC, the overspeed governor limits the N2 by opening the fuel bypass valve, in the event of a malfunction that could lead to an overspeed condition. IDLE CONTROL Ident.: DSC-70-40-40-00001591.0002001 / 09 DEC 09 Applicable to: ALL
The FADEC has the following three idle modes : Modulated idle ‐ Is regulated according to : • bleed system demand ‐ Is selected : • In flight, when the flaps are retracted (FLAPS lever at zero position), • On ground, provided reverse is not selected. Approach idle : ‐ Is regulated according to aircraft altitude, regardless of bleed system demand. ‐ Is selected in flight, when the flaps are extended (FLAPS lever not at zero position) ‐ Allows the engine to accelerate rapidly from idle to go-around thrust Reverse idle : ‐ Is selected on ground, when the thrust lever is in REV IDLE position. ‐ Is slightly higher than forward idle thrust.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← B to D
DSC-70-40-40 P 2/4 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
FUEL SYSTEM (CFM) - HYDROMECHANICAL UNIT
FLIGHT CREW OPERATING MANUAL
FUEL HYDRAULIC SIGNALS Ident.: DSC-70-40-40-00001592.0002001 / 16 MAR 11 Applicable to: ALL L3
Fuel hydraulic signals go to : ‐ Low Pressure Turbine Clearance Control (LPTCC) valves (Refer to DSC-70-60 General) ‐ High Pressure Turbine Clearance Control (HPTCC) valves (Refer to DSC-70-60 General) ‐ Rotor Active Clearance Control (RACC) system (Refer to DSC-70-60 General)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E→
DSC-70-40-40 P 3/4 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FUEL SYSTEM (CFM) - HYDROMECHANICAL UNIT
‐ Variable Stator Vanes (VSV) The VSV system positions the compressor variable vanes. The FADEC maintains optimum compressor efficiency at a steady state and an adequate stall margin for transient engine operation. VSVs are fully closed during engine start and are fully open at high thrust.
‐ Variable Bleed Valves (VBV) The FADEC controls the VBVs, upstream of the HP compressor. Their setting depends on compressor inlet temperature and on N2. It varies between full open (start, low thrust, and during fast deceleration) and full closed (high thrust) positions.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E
DSC-70-40-40 P 4/4 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FUEL SYSTEM (CFM) - IDG COOLING SYSTEM
IDG COOLING SYSTEM
Ident.: DSC-70-40-50-00001593.0001001 / 26 JUL 12 Applicable to: ALL 1
Some of the fuel flowing out of the HMU goes to cool the oil systems of the Integrated Drive Generators (IDGs). It then returns to the fuel pump unit or to the tank. The Fuel Return Valve (FRV), controlled by the FADEC, ensures that this flow is adequate. L3 At low engine thrust, if the oil going into the IDG is too hot, the cooling fuel is sent back to the tank (300 kg/h). If oil temperature continues to rise, the ECU increases the minimum N2. If oil temperature still keeps rising, the FADEC increases the fuel flow to the tank (from 300 to 600 kg/h, depending on fuel return temperature). The fuel return valve is always mixing hot fuel with cold fuel so that the temperature of fuel returning to the tank stays below 100 °C (from 200 to 400 kg/h, depending on fuel return temperature). Fuel recirculation to the tank is inhibited (FRV closed) in the following cases : ‐ at engine shutdown ‐ during takeoff and climb ‐ if : • wing tank level is below about 300 kg (660 lb). • there is fuel overflow in the surge tank • fuel feed is by gravity only. ‐ when fuel temperature in the wing tank in flight is above 52.5 °C Note:
On the ground, high fuel temperature in the wing tank or fuel overflow in the surge tank does not inhibit the fuel recirculation to the wing tank (FRV remains open).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-70-40-50 P 1/2 18 SEP 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FUEL SYSTEM (CFM) - IDG COOLING SYSTEM
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-70-40-50 P 2/2 18 SEP 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
OIL SYSTEM
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-70-50-00001603.0001001 / 16 MAR 11 Applicable to: ALL
The oil system lubricates the engine components. It contains : ‐ the oil tank ‐ the lube and scavenge pump modules ‐ the fuel/oil heat exchanger ‐ the filters, chip detectors, pressure relief and bypass valves.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-70-50 P 1/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
OIL SYSTEM
FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
DSC-70-50 P 2/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
AIRBLEED SYSTEM (CFM)
GENERAL Ident.: DSC-70-60-00001604.0002001 / 22 MAY 12 Applicable to: ALL
The air bleed system supplies the aircraft with compressed air. It uses the air for: ‐ pneumatic system (Refer to DSC-36-10-10 General) ‐ cooling the engine compartment and the turbines.
COOLING Ident.: DSC-70-60-00001605.0002001 / 20 DEC 10 Applicable to: ALL
ROTOR ACTIVE CLEARANCE CONTROL (RACC) SYSTEM The FADEC controls the RACC system through the HMU. The RACC system controls the clearance between the rotor blades of the HP compressor and its stator case. The RACC system uses fifth-stage compressor bleed air that has been modulated according to the N2 and the flight parameters. The bleed air goes to the N°3 bearing compartment, where it is mixed with fan boost discharge. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B →
DSC-70-60 P 1/2 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
AIRBLEED SYSTEM (CFM)
Clearances are at the maximum when the RACC valve is closed. HP TURBINE CLEARANCE CONTROL (HPTCC) SYSTEM The FADEC controls the HPTCC system through the HMU. The HPTCC system controls the HP turbine clearance by modulating the HP compressor bleed air flow for cooling the HP turbine case. It optimizes HP turbine performance and reduces exhaust gas temperature. LP TURBINE CLEARANCE CONTROL (LPTCC) SYSTEM The FADEC controls the LPTCC system through the HMU. The LPTCC system controls LP turbine clearance by modulating the fan bleed air flow for cooling the LP turbine case.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
DSC-70-60 P 2/2 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
THRUST REVERSER SYSTEM
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: DSC-70-70-00001612.0005001 / 09 DEC 09 Applicable to: ALL
The aircraft reverses engine thrust by using four pivoting blocker doors on each engine to deflect the fan airstream.
A hydraulic door jack positions each door. ‐ The green circuit powers the doors on ENG 1. ‐ The yellow circuit powers the doors en ENG 2. The associated FADEC controls the thrust reverser system. Each FADEC channel performs control and monitoring functions. The systems for the two engines are independent of each other. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-70-70 P 1/6 18 SEP 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
THRUST REVERSER SYSTEM
FLIGHT CREW OPERATING MANUAL
The thrust reverser system on each engine has : ‐ 4 actuators, ‐ 4 latches, ‐ Door position switches, ‐ A Hydraulic Control Unit (HCU) that : • Pressurizes the thrust reverser hydraulic system, • Regulates the speed of the blocker doors, and • Supplies actuators with hydraulic power. ‐ A hydraulic shutoff valve which allows hydraulic pressure to the HCU. Each pivoting door moves independently (the doors are not synchronized). The total actuation time is less than two seconds. ACTUATION LOGIC Ident.: DSC-70-70-00001613.0001001 / 09 DEC 09 Applicable to: ALL
Deployment requires : ‐ One FADEC channel, operating with its associated throttle reverse signal ; ‐ Right and left main gear compressed signal from the corresponding LGCIUs ; ‐ A Thrust Lever Angle (TLA) reverse signals from at least one Spoiler Elevator Computer (SEC). Before deployment is completed, the FADEC sets reverse idle thrust on the engine that is having its thrust reversed.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← A to B
DSC-70-70 P 2/6 18 SEP 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
THRUST REVERSER SYSTEM
FLIGHT CREW OPERATING MANUAL
PROTECTION Ident.: DSC-70-70-00001614.0004001 / 09 DEC 09 Applicable to: ALL
‐ AUTO RESTOW FUNCTION The FADEC will automatically command the reverse to stow, if at least one door is unstowed and reverse thrust is not selected while the engine is running. Auto restow is totally inhibited in flight, and on ground, with N1 greater than 70 %. ‐ IDLE PROTECTION The FADEC will automatically select idle thrust if reverse thrust is not selected and : • The four doors are detected unstowed, or • At least one door is detected unstowed, and hydraulic pressure is detected in the HCU (downstream of the pressurizing valve), or • The door position is indefinite, and hydraulic pressure is detected in the HCU (downstream of the pressurizing valve).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-70-70 P 3/6 18 SEP 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
THRUST REVERSER SYSTEM
SCHEMATIC Ident.: DSC-70-70-00001615.0005001 / 17 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D→
DSC-70-70 P 4/6 18 SEP 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
THRUST REVERSER SYSTEM
←D
DSC-70-70 P 5/6 18 SEP 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
THRUST REVERSER SYSTEM
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-70 P 6/6 18 SEP 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
IGNITION AND STARTING - GENERAL
GENERAL Ident.: DSC-70-80-10-00001616.0002001 / 15 FEB 11 Applicable to: ALL
The FADEC controls the ignition and starting system according to: ‐ the position of the engine start selector ‐ the position of the ENG MASTER sw ‐ the position of the ENG MAN START pb-sw ‐ the aircraft status (flight or ground). The FADEC receives its inputs from the Engine Interface Unit (EIU).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-70-80-10 P 1/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
IGNITION AND STARTING - GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-80-10 P 2/2 03 APR 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
IGNITION AND STARTING - ARCHITECTURE
ARCHITECTURE Ident.: DSC-70-80-20-00001617.0002001 / 17 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-70-80-20 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
IGNITION AND STARTING - ARCHITECTURE
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-80-20 P 2/2 29 JUL 11
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
IGNITION AND STARTING - IGNITION SYSTEM
GENERAL Ident.: DSC-70-80-30-00001618.0001001 / 09 DEC 09 Applicable to: ALL
The ignition system is for engine starting on the ground and restarting in flight. It consists of two identical independent circuits for each engine, normally controlled by the FADEC channel A and channel B. Each FADEC channel can control both igniters.
Note:
Supply for igniter A switches to the STAT INV BUS BAR as soon as the static inverter is operative.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
DSC-70-80-30 P 1/4 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
IGNITION AND STARTING - IGNITION SYSTEM
FLIGHT CREW OPERATING MANUAL
IGNITION FOR STARTING Ident.: DSC-70-80-30-00001619.0001001 / 15 FEB 11 Applicable to: ALL
ON THE GROUND ‐ Automatic start: • Only one igniter is supplied. • The FADEC automatically alternates the use of igniters for the engine start of the successive flights following the sequence below: ▪ channel A, igniter A ▪ channel B, igniter A ▪ channel A, igniter B ▪ channel B, igniter B • The ignition comes on automatically when N2 reaches 16 % and cuts off automatically when N2 reaches 50 %. If the automatic start fails, the FADEC energizes both igniters at the same time during the second attempt at an engine start. ‐ Manual start: • Both igniters start firing when the ENG MASTER sw is set to ON. • Both igniters are cut off when N2 reaches approximately 50 %. IN FLIGHT Both igniters are supplied when the ENG MASTER sw is set to ON. CONTINUOUS IGNITION Ident.: DSC-70-80-30-00001620.0004001 / 11 MAY 12 Applicable to: ALL
Continuous ignition may be selected either manually or automatically to maintain engine combustion. MANUAL SELECTION In flight, continuous ignition is on when the ENG START selector is on IGN/START, if the corresponding engine is running. Only one igniter is selected. If failed, both igniters are automatically selected. On the ground after the engine is started, because ignition cuts off automatically, the flight crew must switch the ENG MODE selector to NORM then back to IGN/START to turn on continuous ignition.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B to C →
DSC-70-80-30 P 2/4 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
IGNITION AND STARTING - IGNITION SYSTEM
AUTOMATIC SELECTION
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C
DSC-70-80-30 P 3/4 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
IGNITION AND STARTING - IGNITION SYSTEM
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-80-30 P 4/4 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
IGNITION AND STARTING - ENGINE STARTING SYSTEM
GENERAL Ident.: DSC-70-80-40-00001621.0001001 / 09 DEC 09 Applicable to: ALL
The engine starting system consists of an air turbine starter and a start valve. The start valve admits air supplied by the pneumatic system to operate the starter. The FADEC controls the start valve electrically. If electrical control fails when the aircraft is on the ground, a handle allows the start valve to be operated manually. AUTOMATIC STARTING Ident.: DSC-70-80-40-00001622.0001001 / 15 FEB 11 Applicable to: ALL
This sequence is under the full authority of the FADEC, which controls: ‐ the start valve ‐ the igniters ‐ the fuel HP valves The FADEC: ‐ detects a hot start, a hung start, a stall, or no light up ‐ announces FAULT and identifies the fault in an ECAM message ‐ runs an abort sequence if a start aborts on the ground • closes the HP valve • closes the start valve • turns off ignition • cranks the engine crank after the start abort in order to clear out fuel vapors • controls any additional start attempts. For an inflight start, the FADEC decides whether the engine is windmilling fast enough or needs assistance from the starter in view of current engine parameters and flight environment parameters. Flight crew may interrupt this start sequence by moving the MASTER switch to OFF.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
DSC-70-80-40 P 1/6 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
IGNITION AND STARTING - ENGINE STARTING SYSTEM
AUTOMATIC STARTING SEQUENCE Ident.: DSC-70-80-40-00001623.0005001 / 22 MAY 12 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
DSC-70-80-40 P 2/6 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
IGNITION AND STARTING - ENGINE STARTING SYSTEM
MANUAL STARTING Ident.: DSC-70-80-40-00001624.0001001 / 09 DEC 09 Applicable to: ALL
The FADEC has limited authority over manual starting controlling : ‐ the opening of the start valve when the ENG MODE selector is set to IGN/START and the MAN START pushbutton switch is pressed. ‐ the position of the HP fuel valve and the operation of both igniters, when the master switch is turned ON ‐ the closing of the start valve at approximately 50 % N2, and, on the ground, the cutting off of ignition. The FADEC makes a passive survey of the engine during the starting sequence : the flight crew is made aware of an abnormal start by a proper ECAM warning and has to interrupt the start sequence. The FADEC has not the authority to abort the manual start : ‐ in flight ‐ on ground, except if the start EGT limit is exceeded before reaching 50 % N2. In this case only, the FADEC aborts the start. Flight crew may interrupt the starting sequence : ‐ before the MASTER switch is set to ON, by switching the MAN START pushbutton switch to OFF ‐ after the MASTER switch set to ON, by switching the MAN START pushbutton and the MASTER switch to OFF (flight crew must perform a dry cranking cycle). In flight, the FADEC always commands a starter-assisted air start. ENGINE VENTILATION (DRY CRANKING) Ident.: DSC-70-80-40-00001625.0001001 / 15 FEB 11 Applicable to: ALL
A dry cranking cycle ventilates the engine to remove fuel vapors after an unsuccessful start attempt on the ground. The flight crew can manually select cranking by setting the ENG MODE selector to CRANK and the MAN START pushbutton switch to ON (MASTER switch OFF). Flight crew can stop the cranking by setting the MAN START pushbutton switch to OFF.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D to E
DSC-70-80-40 P 3/6 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
IGNITION AND STARTING - ENGINE STARTING SYSTEM
MANUAL STARTING SEQUENCE Ident.: DSC-70-80-40-00001626.0005001 / 15 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F→
DSC-70-80-40 P 4/6 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
IGNITION AND STARTING - ENGINE STARTING SYSTEM
Refer to DSC-21-10-20 Pack Flow Control Valve
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←F
DSC-70-80-40 P 5/6 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
IGNITION AND STARTING - ENGINE STARTING SYSTEM
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-80-40 P 6/6 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
CONTROLS AND INDICATORS (CFM)
FLIGHT CREW OPERATING MANUAL
PEDESTAL Ident.: DSC-70-90-00001627.0002001 / 22 MAY 12 Applicable to: ALL
(1)
Thrust levers (Refer to DSC-70-30-20 Thrust Levers).
(2)
Reverser latching levers These permit the pilot to override the stop at the forward idle position to select reverse thrust. This stop resets when the pilot moves the lever back into the forward thrust area.
(3)
Autothrust instinctive disconnect pb (Refer to DSC-22_30-90-B A/THR Disconnection - General).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
DSC-70-90 P 1/16 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
CONTROLS AND INDICATORS (CFM)
ENG MODE selector CRANK : The start valve opens, if the MAN START pb-sw is ON. Ignition does not fire. NORM : This turns on continuous ignition (A and B) when the engine is running, and: ‐ A flame-out is detected, or ‐ An EIU fails. IGN : If the MASTER sw is ON and N2 ≥ idle, this position selects continuous ignition START (A and B): ‐ During an automatic start: • On ground, when N2 passes 16 %, ignition switches to A or B. However, if there is an ignition delay during the start sequence, ignition is continuous (A and B) • In flight, continuous ignition (A and B) begins when the start sequence begins. ‐ During a manual start, ignition begins when the MASTER sw is turned ON. The pack valve closes automatically during the start sequence. (Refer to DSC-21-10-10 General). Note:
On ground, ignition shuts off automatically at the end of the start sequence (N2 > 50 %).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
DSC-70-90 P 2/16 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
CONTROLS AND INDICATORS (CFM)
(2)
ENG 1 (2) MASTER sw ON : LP fuel valve opens (if the ENG FIRE pb is in): ‐ During an automatic start, the HP fuel valve opens if: • The ENG MODE selector is at IGN/START. • N2 is above the following threshold: ▪ 22 % on the ground ▪ 15 % in flight ‐ During a manual start, the HP FUEL valve opens if: • The ENG MODE selector is at IGN/START. • The MAN START pb-sw is ON. OFF: Close signals go directly to the HP fuel valve and the LP fuel valve. These signals cause both channels of the FADEC to be reset.
(3)
ENG 1 (2) FAULT light FAULT : This amber light comes on, and a caution appears on ECAM, if there is: light ‐ an automatic start abort ‐ a disagreement between the HP fuel valve position and its commanded position. OVERHEAD PANEL
Ident.: DSC-70-90-00001628.0001001 / 17 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← A to B →
DSC-70-90 P 3/16 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
CONTROLS AND INDICATORS (CFM)
ENG MAN START pb sw ON : The start valve opens if the ENG MODE selector is set to CRANK or IGN/START and N2 < 20 %. Both pack valves close during the start sequence. Note: Off :
The start valve closes automatically when N2 ≥ 50 %.
The blue ON light comes on. When the ENG MAN START pushbutton switch is set to OFF during a manual engine start, the start valve closes if the MASTER switch is OFF. MAINTENANCE PANEL
Ident.: DSC-70-90-00001629.0001001 / 17 MAR 11 Applicable to: ALL
(1)
FADEC GND PWR pb sw ON : FADEC has electrical power on the ground if the ENG FIRE pushbutton is not released.
ECAM Ident.: DSC-70-90-A-NG00098 Applicable to: ALL Ident.: DSC-70-90-A-00001630.0001001 / 17 MAR 11
GENERAL The ECAM’s upper E/WD permanently displays the engines’ primary parameters. The ECAM’s lower SD displays the secondary parameters, either when they are automatically selected by the system, or manually selected by the flight crew.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to D →
DSC-70-90 P 4/16 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
CONTROLS AND INDICATORS (CFM)
Ident.: DSC-70-90-A-00001631.0084001 / 16 MAY 12
PRIMARY PARAMETER
(1)
LP rotor speed (N1)
(A) Actual N1 The N1 needle and N1 digital indication are normally in green. They pulse in: ‐ Amber, when the actual N1 is above the N1 MAX (See (E)); ‐ Red, when the actual N1 is above the N1 RED line (104 %). When the N1 is degraded (in case both N1 sensors fail), the last digit of the digital display is dashed in amber.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-70-90 P 5/16 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
CONTROLS AND INDICATORS (CFM)
(B) N1 Command (N1 trend) The green needle corresponds to the N1 demanded by the FADEC. In addition, next to the N1 trend needle, a green triangle indicates the tendency of N1 command. These symbols are displayed when A/THR is active. (C) Transient N1 Symbolizes the difference between the N1 command and the actual N1. It is only displayed when A/THR is active. (D) N1 TLA (blue circle) N1 corresponding to the thrust lever position. (E) MAX N1 the MAX N1 amber index displays the N1 that the engine produces when the thrust levers are in full forward position or when MAX REVERSE is set. (F)
MAX permissible N1 This red arc, showing the prohibited or “redline” area of operation, begins at 104 %.
(G) N1 exceedance If N1 exceeds 104 % during a flight, this red mark appears and remains at the highest N1 attained. It disappears after a new start on the ground or after maintenance action through the MCDU. (H) REV Appears in amber when any one blocker door is unstowed or unlocked. It changes to green when all four blocker doors are fully deployed. (If a door unlocks in flight the indication first flashes for 9 s seconds, then remains steady). (I)
AVAIL indication Displayed in green to indicate a successful engine start on ground. It pulses in green to indicate a successful engine relight in flight. It is triggered when the engine is at, or above, idle.
(2)
Thrust limit mode TOGA, FLX, CL, MCT, or MREV limit mode, selected by the position of whichever thrust lever is farther forward, is displayed in blue.
(3)
N1 rating limit It is computed by the FADEC for the present thrust lever angle, and is displayed in green.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-70-90 P 6/16 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Note:
CONTROLS AND INDICATORS (CFM)
When the aircraft is on ground with the engines running, the N1 rating limit displayed here corresponds to the TOGA thrust limit, regardless of the thrust lever position. When the aircraft is on ground with the engines running and FLEX mode is selected, this number is the FLEX N1, regardless of the thrust lever position between idle and FLX/MCT.
(4)
FLEX temperature If FLX mode is selected, the flexible takeoff temperature selected through the MCDUs is displayed in blue.
(5)
EGT indicator
(A) Actual EGT ‐ It is normally green. ‐ It pulses amber above 915 °C, except for high power operation (FLEX TO or thrust lever above MCT or at MAX REV, or activation of alpha floor). ‐ It pulses amber above 725 °C during start sequence. ‐ It pulses red above 950 °C, and the numerical value becomes red. (B) MAX EGT The amber index appears at 725 °C during engine start, then at 915 °C. (C) MAX permissible EGT The EGT red line is at 950 °C. Display shows red arc from 950 °C to the end of the scale. (D) EGT exceedance If the EGT goes over 950 °C, a red mark appears at its maximum value. It disappears after a new takeoff, or after a maintenance action through the MCDU. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-70-90 P 7/16 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
CONTROLS AND INDICATORS (CFM)
(6)
HP rotor speed N2 The numbers are normally green. (During start sequence, they are green on a grey background). When N2 is above 105 %, the indication turns red and a red cross appears next to it. When the N2 value is degraded (if both N2 sensors fail), the last digit is amber and is dashed.
(7)
Fuel flow These numbers are green. Note:
(8)
If the system detects a discrepancy between the N1, N2, EGT and fuel flow values on the FADEC-DMC bus and the corresponding displayed values, an amber CHECK appears underneath the affected parameter.
IDLE indication This legend appears in green when both engines are at idle. It flashes for 10 s, then remains steady.
Ident.: DSC-70-90-A-00001632.0016001 / 22 MAY 12
SECONDARY PARAMETERS START CONFIGURATION
(1)
Fuel used The green number is the fuel used as computed by the FADEC. The green number resets, when the engine starts (MASTER switch ON) on the ground.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-70-90 P 8/16 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
CONTROLS AND INDICATORS (CFM)
The green number is frozen at the last value (until the next engine start), when the engine shuts down. (The CRUISE SD page also displays the last value). The two last digits are dashed, if the fuel-used indication is inaccurate due to the loss of fuel flow data for more than 1 min. (2)
Oil quantity The oil quantity indicators (needle and values) are green. The indication pulses, when oil quantity decreases below three quarts or increases above five quarts.
(3)
Oil pressure The oil pressure indicators (needle and values) are green. If the oil pressure: ‐ Exceeds 90 PSI, the indicators begin to pulse The indicators stop pulsing, when the oil pressure goes below 85 PSI. ‐ Goes below 16 PSI, the indicators begin to pulse The indicators stop pulsing, when the oil pressure returns above 20 PSI. ‐ Goes below 13 PSI, the indicators become red, and the ECAM displays the ENG 1(2) OIL LO PR alert.
(4)
Oil temperature The oil temperature values are green. If the oil temperature: ‐ Exceeds 140 °C, the value begins to pulse The value stops pulsing, when the oil temperature goes below 135 °C. ‐ Exceeds 140 °C for more than 15 min, the value becomes amber, and the ECAM displays the ENG 1(2) OIL HI TEMP alert ‐ Rapidly exceeds 155 °C, the value becomes amber, and the ECAM displays the ENG 1(2) OIL HI TEMP alert.
(5)
VIB The legend is green. VIB N1 pulses above 6. VIB N2 pulses above 4.3. (These numbers also appear on the CRUISE SD page).
(6)
Oil filter clog CLOG appears in amber, if there is an excessive pressure loss across the main oil scavenge filter.
(7)
Fuel filter clog CLOG appears in amber, if there is an excessive pressure loss across the fuel filter.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D→
DSC-70-90 P 9/16 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
CONTROLS AND INDICATORS (CFM)
FLIGHT CREW OPERATING MANUAL
(8)
Ignition IGN appears in white during the start sequence. The letters A, B, or AB appear in green, when the respective igniters are firing.
(9)
Start valve position In line – Green : Crossline – Green :
The valve is fully open. The valve is fully closed.
(10) Engine bleed pressure The green numbers indicate the bleed pressure upstream of the precooler. They become amber, when the pressure drops below 21 PSI with N2 ≥ 10 %, or if there is an overpressure. AFTER START CONFIGURATION
(11) Nacelle temperature The values in green indicate the nacelle temperature. These values are displayed if not during start sequence, and if one nacelle temperature is at, or above, the advisory threshold (240 °C). The nacelle temperature pulses in green at, or above, the advisory threshold. WARNINGS AND CAUTIONS Ident.: DSC-70-90-00001633.0097001 / 17 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← D to E →
DSC-70-90 P 10/16 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
E/WD: FAILURE TITLE conditions
CONTROLS AND INDICATORS (CFM) AURAL WARNING
MASTER LIGHT
SD PAGE CALLED
LOCAL WARNING
FLT PHASE INHIB NIL
ENG
Associated with GEN FAULT lts and PACK FAULT lt
ENG DUAL FAILURE CRC
ENG 1(2) OIL LO PR
Oil low pressure triggered at 13 PSI by the oil pressure switch.
ENG 1(2) THR LEVER ABV IDLE
‐ One thrust lever is above idle while the other thrust lever is in the reverse detent at landing. ‐ One thrust lever is above idle while the other thrust lever is at idle, at reverser deselection during landing roll.
1, 10
MASTER WARN
RETARD
NIL
NIL
ENG STALL ENG 1(2) HP FUEL VALVE
3, 4, 5, 7, 8
HP fuel valve failed closed.
ENG 1(2) START FAULT Start fault due to: ‐ No light up, or ‐ ENG stall or over TEMP (above 725 °C), or ‐ Starter time exceeded ‐ Thrust lever not at idle ‐ Low start air PRESS
ENG 1(2) START VALVE FAULT
1, 2, 3, 4, 5, 6, 7, 10
SINGLE CHIME
MASTER CAUT
ENG
Associated FAULT lt on ENG panel on pedestal (exception case of starter time exceeded)
3, 4, 5, 6, 7, 8
3, 4, 5, 7, 8
Position disagree.
ENG 1(2) OIL HI TEMP
Oil TEMP between 140 and 155 °C for more than 15 min, or oil TEMP above 155 °C.
4, 5, 7, 8
ENG 1(2) FADEC FAULT Both channels failed.
NIL
ENG 1(2) LOW N1
No N1 rotation during start.
ENG THRUST LOCKED
Thrust levers are not moved within 5 s, following an unvoluntary disconnection of the A/THR (or disconnection through the FCU pb).
SINGLE CHIME every 5 s
MASTER CAUT every 5 s
NIL
4, 5, 6, 7, 8, 9, 10 1, 2, 3, 4, 8, 9, 10
Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-70-90 P 11/16 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
E/WD: FAILURE TITLE conditions
ENG THR LEVERS NOT SET
The levers position does not correspond to T.O power mode.
CONTROLS AND INDICATORS (CFM)
AURAL WARNING
MASTER LIGHT
SINGLE CHIME
MASTER CAUT
Continued from the previous page FLT SD PAGE LOCAL PHASE CALLED WARNING INHIB
1, 4, 5, 6, 7, 8, 10 Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
DSC-70-90 P 12/16 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
E/WD: FAILURE TITLE conditions
CONTROLS AND INDICATORS (CFM)
AURAL WARNING
MASTER LIGHT
ENG 1(2) FADEC HI TEMP ENG TYPE DISAGREE
Rating discrepancy between the two engines.
ENG 1(2) THR LEVER DISAGREE
Continued from the previous page FLT SD PAGE LOCAL PHASE CALLED WARNING INHIB 3, 4, 5, 7, 8 NIL 3 to 10
ENG
Disagree between both resolvers of a thrust lever
4, 5 ((1))
ENG 1(2) THR LEVER FAULT
Both resolvers on one thrust lever have failed.
ENG 1(2) FAIL
ENG core speed below idle, with master sw ON and fire pb not pushed.
1, 10
ENG 1(2) SHUT DOWN
ENG master at off in phases 3 to 8, or ENG FIRE pb pushed in phases 1, 2, 9 and 10.
ENG 1(2) REVERSE UNLOCKED
4, 8 ((2))
One or more reverser doors not locked in stowed position in flight, or on ground with no deploy order.
ENG 1(2) REV PRESSURIZED
Reverser system is pressurized, while rev doors are stowed and locked with no deploy order.
ENG 1(2) COMPRESSOR VANE
SINGLE CHIME
Variable bleed valve SYS or variable stator vane SYS fault.
MASTER CAUT
NIL
NIL
4, 5, 8
4, 5, 7, 8
ENG 1(2) N1 or N2 or EGT OVER LIMIT N1 above 104 % N2 above 105.0 % EGT above 950 °C
4, 8
ENG 1(2) IGN A + B FAULT
3, 4, 5, 7, 8
Both ignition circuits are failed.
ENG 1(2) CTL VALVE FAULT
Burn stag valve failure or HPTC, or RAC system failure.
ENG 1(2) FUEL CTL FAULT
Fuel metering valve position disagree.
4, 5, 7, 8
ENG 1(2) SENSOR FAULT
PS3 or T25 or T3 or N1 or N2 data unavailable on both channels.
ENG 1(2) PROBES FAULT
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Continued on the following page
←E→
DSC-70-90 P 13/16 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
E/WD: FAILURE TITLE conditions
CONTROLS AND INDICATORS (CFM)
AURAL WARNING
MASTER LIGHT
Continued from the previous page FLT SD PAGE LOCAL PHASE CALLED WARNING INHIB
T12 or PO PT 2 data unavailable on both channels.
ENG 1(2) N1 (N2, EGT, FF) DISCREPANCY
3, 4, 5, 8
Discrepancy between real and displayed values.
ENG 1(2) BLEED STATUS FAULT
3, 4, 5, 7, 8
Bleed, X Bleed, pack, anti-ice valve position status not received by FADEC active channel.
ENG 1(2) FUEL FILTER CLOG ENG 1(2) OIL FILTER CLOG ENG VIB SYS FAULT Failure of vibration detection system.
ENG NIL
NIL
ENG 1(2) OVSPD PROT FAULT Loss of overspeed protection.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
NIL
←E→
3, 4, 5, 7, 8 3, 4, 5, 6, 7, 8, 9 3, 4, 5, 7, 8 Continued on the following page
DSC-70-90 P 14/16 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
E/WD: FAILURE TITLE conditions
CONTROLS AND INDICATORS (CFM)
AURAL WARNING
MASTER LIGHT
ENG 1(2) IGN A(B) FAULT Ignition circuit A or B failed.
Continued from the previous page FLT SD PAGE LOCAL PHASE CALLED WARNING INHIB 3, 4, 5, 6, 7, 8
ENG 1(2) FADEC ALTERNATOR
Loss of electrical auto supply of either FADEC channel.
ENG COMPRESSOR VANE
3, 4, 5, 7, 8
Engine 1 and 2 VBV or VSV fault.
ENG 1(2) FUEL RETURN VALVE
Fuel return valve is failed in the not open, or not closed position.
NIL
NIL
ENG 1(2) FADEC A(B) FAULT
4, 5, 7, 8
One FADEC channel failed.
NIL
ENG 1(2) EIU FAULT
NIL
Data bus between EIU and ECU failed.
ENG 1(2) REVERSER FAULT
3, 4, 5
Loss of thrust reverser on one engine, due to system components or input faults.
ENG 1(2) REV ISOL FAULT ENG 1(2) REV SWITCH FAULT
SC
CAUT
3 to 7 3, 4, 5, 6, 7, 8
Failure of reverser permission switch.
ENG REV SET
Reverse thrust has been selected in flight.
NIL
1 to 4 8 to 10 3, 4, 5, 6, 7, 8
NIL
ENG 1(2) ONE TLA FAULT (1) (2)
1, 3, 4, 5, 7, 8, 10
Alert not inhibited in the flight phases 4 and 5, if the FADEC automatically selects IDLE thrust. Alert not inhibited in the flight phase 4, if the engine thrust is automatically set to idle.
MEMO DISPLAY IGNITION appears in green, when continuous ignition is activated on either engine.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E
DSC-70-90 P 15/16 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
CONTROLS AND INDICATORS (CFM)
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-90 P 16/16 30 MAY 12
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
ELECTRICAL SUPPLY Ident.: DSC-70-98-00001649.0001001 / 09 DEC 09 Applicable to: ALL
NORM AC CHANNEL A FADEC
CHANNEL B EIU
ENG 1 and 2 ENG 1 ENG 2 ENG 1 ENG 2
OIL PRESS/QTY A
ENG 1 and 2
AC ESS
ENG 1 ENG 2 ENG 1 and 2
AC1 AC2 AC1
IGNITION
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
HOT
X X X X
DC2 DC1 DC2
ENG 1 ENG 2
EVMU
EMER ELEC DC ESS X
BAT DC2 BAT
HP VALVES LP VALVES
B
DC
AC ESS
AC ESS or AC STAT INV during RAT extension
DSC-70-98 P 1/2 29 JUL 11
AIRCRAFT SYSTEMS POWER PLANT A318/A319/A320/A321
ELECTRICAL SUPPLY
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
DSC-70-98 P 2/2 29 JUL 11
PROCEDURES
Intentionally left blank
PROCEDURES PRELIMINARY PAGES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TABLE OF CONTENTS
PRO-PLP PRELIMINARY PAGES TABLE OF CONTENTS LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
PRO-ABN Abnormal and Emergency Procedures PRO-NOR Normal Procedures PRO-SPO Special Operations PRO-SUP Supplementary Procedures
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-PLP-TOC P 1/2 18 SEP 12
PROCEDURES PRELIMINARY PAGES A318/A319/A320/A321
TABLE OF CONTENTS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-PLP-TOC P 2/2 18 SEP 12
PROCEDURES PRELIMINARY PAGES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
Localization
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
DU identification
DU date
PRO-ABN-31 MULTIPLE UNDUE ECAM ALERTS 00012928.0001001 Criteria: P8671, P9824 Applicable to: ALL Impacted DU: NONE Reason for issue: This Temporary Revision was re-issued to update the list of possible undue ECAM alerts.
DU Title
07 APR 11
PRO-NOR-SOP-10 Taxi NG00715 PRO-NOR-SOP-10 Taxi - AFS/Flight Instruments 00013658.0007001 07 APR 11 Criteria: P10530, P11256, P7929, P9593, P9902, SA Applicable to: ALL Impacted DU: 00011932 Taxi - AFS/Flight Instruments Reason for issue: When in the AUTO position, the MultiScan AUTO mode adjusts the tilt according to the altitude of the aircraft. In cruise, MULTISCAN function provides a large view of the weather ahead, ie display of weather cells located on and below aircraft path. At low altitudes (below FL 200), the tilt is adjusted upward to manage clutter from strong ground targets. In some cases, the weather may be low-lying and therefore may be below the radar beam and not be displayed until the aircraft descends closer to the precipitation level. Therefore, this Temporary Revision is issued to indicate that, when the Multiscan is in the AUTO position, the GAIN should be manually set to +4 when the aircraft is below FL 200.
In addition, the flight crew should temporarily set the MULTISCAN sw to MAN, if: ‐ If the weather is good, or no significant, in order to check that the radar is operating correctly: down tilt until displaying ground echoes ‐ The weather display is ambiguous or unexpected, in order to better analyze the weather situation using manual tilt according to standard technique ‐ In particular below FL 200, for situations with low-level weather, weather with low reflectivity or in front of suspected active cells, the flight crew should switch to Manual mode and adjust the tilt setting downward until the weather is detected or the ground clutter appears on the upper part of the display. In addition, the flight crew may increase the manual gain control to display lower reflectivity targets. The manual gain control can be increased in both AUTO and Manual modes to display lower levels of weather. In both cases, ground clutter may also be displayed as a result of low settings and/or increased gain.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-PLP-LETDU P 1/8 18 SEP 12
PROCEDURES PRELIMINARY PAGES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
Localization
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
DU Title
DU identification
DU date
PRO-NOR-SOP-14 Climb NG00723 PRO-NOR-SOP-14 Climb - Initial Climb 00013057.0001001 16 NOV 11 Criteria: P9207, SA Applicable to: ALL Impacted DU: 00010245 Climb - Initial Climb Reason for issue: The temporary revision is issued to advise operators that above the transition level, when the flight crew selects "STD" on the FCU, the last QNH or QFE barometric pressure setting is transmitted to the ground, instead of the standard pressure value (1 013 hPa). Only the FCU selected altitude, if used by the ATC on ground, may be misinterpreted. The real aircraft altitude transmitted to the ground is not affected, because the standard barometric altitude is transmitted, regardless of the barometric setting selected on the FCU. In addition, the "STD" value is correctly transmitted to other aircraft systems. PRO-NOR-SOP-14 Climb - Radar 00013047.0003001 16 NOV 11 Criteria: P7754, P7929, P9902, SA Applicable to: ALL Impacted DU: 00010259 Climb - Radar Reason for issue: When in the AUTO position, the MultiScan AUTO mode adjusts the tilt according to the altitude of the aircraft. In cruise, MULTISCAN function provides a large view of the weather ahead, ie display of weather cells located on and below aircraft path. At low altitudes (below FL 200), the tilt is adjusted upward to manage clutter from strong ground targets. In some cases, the weather may be low-lying and therefore may be below the radar beam and not be displayed until the aircraft descends closer to the precipitation level. Therefore, this Temporary Revision is issued to indicate that, when the Multiscan is in the AUTO position, the GAIN should be manually set to +4 when the aircraft is below FL 200.
In addition, the flight crew should temporarily set the MULTISCAN sw to MAN, if: ‐ If the weather is good, or no significant, in order to check that the radar is operating correctly: down tilt until displaying ground echoes ‐ The weather display is ambiguous or unexpected, in order to better analyze the weather situation using manual tilt according to standard technique ‐ In particular below FL 200, for situations with low-level weather, weather with low reflectivity or in front of suspected active cells, the flight crew should switch to Manual mode and adjust the tilt setting downward until the weather is detected or the ground clutter appears on the upper part of the display. In addition, the flight crew may increase the manual gain control to display lower reflectivity targets. The manual gain control can be increased in both AUTO and Manual modes to display lower levels of weather. In both cases, ground clutter may also be displayed as a result of low settings and/or increased gain.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-PLP-LETDU P 2/8 18 SEP 12
PROCEDURES PRELIMINARY PAGES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
Localization
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
DU Title
DU identification
DU date
PRO-NOR-SOP-15 Cruise NG00734 PRO-NOR-SOP-15 Cruise - Radar Tilt 00013068.0006001 16 NOV 11 Criteria: P7929, P9902, SA Applicable to: ALL Impacted DU: 00010291 Cruise - Radar Tilt Reason for issue: When in the AUTO position, the MultiScan AUTO mode adjusts the tilt according to the altitude of the aircraft. In cruise, MULTISCAN function provides a large view of the weather ahead, ie display of weather cells located on and below aircraft path. At low altitudes (below FL 200), the tilt is adjusted upward to manage clutter from strong ground targets. In some cases, the weather may be low-lying and therefore may be below the radar beam and not be displayed until the aircraft descends closer to the precipitation level. Therefore, this Temporary Revision is issued to indicate that, when the Multiscan is in the AUTO position, the GAIN should be manually set to +4 when the aircraft is below FL 200.
In addition, the flight crew should temporarily set the MULTISCAN sw to MAN, if: ‐ The weather is good, or no significant, in order to check that the radar is operating correctly: down tilt until displaying ground echoes ‐ The weather display is ambiguous or unexpected, in order to better analyze the weather situation using manual tilt according to standard technique ‐ In particular below FL 200, for situations with low-level weather, weather with low reflectivity or in front of suspected active cells, the flight crew should switch to Manual mode and adjust the tilt setting downward until the weather is detected or the ground clutter appears on the upper part of the display. In addition, the flight crew may increase the manual gain control to display lower reflectivity targets. The manual gain control can be increased in both AUTO and Manual modes to display lower levels of weather. In both cases, ground clutter may also be displayed as a result of low settings and/or increased gain.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-PLP-LETDU P 3/8 18 SEP 12
PROCEDURES PRELIMINARY PAGES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
Localization
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
DU Title
DU identification
DU date
PRO-NOR-SOP-17 Descent Adjustment NG00915 PRO-NOR-SOP-17 Descent Adjustment - Radar 00013353.0003001 07 APR 11 Criteria: P7929, P9902, SA Applicable to: ALL Impacted DU: 00011545 Descent Adjustment - Radar Reason for issue: When in the AUTO position, the MultiScan AUTO mode adjusts the tilt according to the altitude of the aircraft. In cruise, MULTISCAN function provides a large view of the weather ahead, ie display of weather cells located on and below aircraft path. At low altitudes (below FL 200), the tilt is adjusted upward to manage clutter from strong ground targets. In some cases, the weather may be low-lying and therefore may be below the radar beam and not be displayed until the aircraft descends closer to the precipitation level. Therefore, this Temporary Revision is issued to indicate that, when the Multiscan is in the AUTO position, the GAIN should be manually set to +4 when the aircraft is below FL 200.
In addition, the flight crew should temporarily set the MULTISCAN sw to MAN, if: ‐ If the weather is good, or no significant, in order to check that the radar is operating correctly: down tilt until displaying ground echoes ‐ The weather display is ambiguous or unexpected, in order to better analyze the weather situation using manual tilt according to standard technique ‐ In particular below FL 200, for situations with low-level weather, weather with low reflectivity or in front of suspected active cells, the flight crew should switch to Manual mode and adjust the tilt setting downward until the weather is detected or the ground clutter appears on the upper part of the display. In addition, the flight crew may increase the manual gain control to display lower reflectivity targets. The manual gain control can be increased in both AUTO and Manual modes to display lower levels of weather. In both cases, ground clutter may also be displayed as a result of low settings and/or increased gain.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-PLP-LETDU P 4/8 18 SEP 12
PROCEDURES PRELIMINARY PAGES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
Localization
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
DU Title
DU identification
DU date
PRO-NOR-SOP-18 Initial Approach NG00918 PRO-NOR-SOP-18 Initial Approach - Initial Approach 00013098.0001001 07 APR 11 Criteria: P4495, P7929, P8710, P9902, SA Applicable to: ALL Impacted DU: 00011573 Initial Approach - Initial Approach Reason for issue: When in the AUTO position, the MultiScan AUTO mode adjusts the tilt according to the altitude of the aircraft. In cruise, MULTISCAN function provides a large view of the weather ahead, ie display of weather cells located on and below aircraft path. At low altitudes (below FL 200), the tilt is adjusted upward to manage clutter from strong ground targets. In some cases, the weather may be low-lying and therefore may be below the radar beam and not be displayed until the aircraft descends closer to the precipitation level. Therefore, this Temporary DU is issued to indicate that, when the Multiscan is in the AUTO position, the GAIN should be manually set to +4 when the aircraft is below FL 200.
In addition, the flight crew should temporarily set the MULTISCAN sw to MAN, if: ‐ If the weather is good, or no significant, in order to check that the radar is operating correctly: down tilt until displaying ground echoes ‐ The weather display is ambiguous or unexpected, in order to better analyze the weather situation using manual tilt according to standard technique ‐ In particular below FL 200, for situations with low-level weather, weather with low reflectivity or in front of suspected active cells, the flight crew should switch to Manual mode and adjust the tilt setting downward until the weather is detected or the ground clutter appears on the upper part of the display. In addition, the flight crew may increase the manual gain control to display lower reflectivity targets. The manual gain control can be increased in both AUTO and Manual modes to display lower levels of weather. In both cases, ground clutter may also be displayed as a result of low settings and/or increased gain.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-PLP-LETDU P 5/8 18 SEP 12
PROCEDURES PRELIMINARY PAGES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
Localization
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
DU Title
DU identification
DU date
PRO-NOR-SOP-19 Initial Approach NG00982 PRO-NOR-SOP-19 Initial Approach - Initial Approach 00013522.0026001 07 APR 11 Criteria: P10530, P11256, P7929, P8710, P9593, P9902, SA Applicable to: ALL Impacted DU: 00011825 Initial Approach - Initial Approach Reason for issue: When in the AUTO position, the MultiScan AUTO mode adjusts the tilt according to the altitude of the aircraft. In cruise, MULTISCAN function provides a large view of the weather ahead, ie display of weather cells located on and below aircraft path. At low altitudes (below FL 200), the tilt is adjusted upward to manage clutter from strong ground targets. In some cases, the weather may be low-lying and therefore may be below the radar beam and not be displayed until the aircraft descends closer to the precipitation level. Therefore, this Temporary Revision is issued to indicate that, when the Multiscan is in the AUTO position, the GAIN should be manually set to +4 when the aircraft is below FL 200.
In addition, the flight crew should temporarily set the MULTISCAN sw to MAN, if: ‐ If the weather is good, or no significant, in order to check that the radar is operating correctly: down tilt until displaying ground echoes ‐ The weather display is ambiguous or unexpected, in order to better analyze the weather situation using manual tilt according to standard technique ‐ In particular below FL 200, for situations with low-level weather, weather with low reflectivity or in front of suspected active cells, the flight crew should switch to Manual mode and adjust the tilt setting downward until the weather is detected or the ground clutter appears on the upper part of the display. In addition, the flight crew may increase the manual gain control to display lower reflectivity targets. The manual gain control can be increased in both AUTO and Manual modes to display lower levels of weather. In both cases, ground clutter may also be displayed as a result of low settings and/or increased gain. PRO-SUP-24 PRO-SUP-24
Computer Reset Table NG01118 Computer Reset Table - 21 - Air 00014123.0004001 14 NOV 11 Conditioning/Ventilation/Pressurization Criteria: K10463, K6443, K9458 Applicable to: ALL Impacted DU: 00012647 Computer Reset Table - 21 - Air Conditioning/Ventilation/Pressurization Reason for issue: The TDU is issued to provide the ACSC C/B reset procedure to apply in the case of "PACK 1(2) REGUL FAULT" triggered on ground for aircraft equipped with ACSC 1803B0000-02.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-PLP-LETDU P 6/8 18 SEP 12
PROCEDURES PRELIMINARY PAGES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
(1)
M
Localization
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
DU Title
DU identification
DU date
PRO-SUP-24
Computer Reset Table - 23 00013849.0024001 01 JUL 11 Communications Criteria: K12824, K12825, K3901, K8400, SA Applicable to: ALL Impacted DU: 00012649 Computer Reset Table - 23 - Communications Reason for issue: CIDS Director Hardware 333B and On Board Replacement Module (OBRM) 33A are sensitive to short power supply interruptions. These power supply interruptions occur when the aircraft is supplied by external power. As a consequence, ECAM caution “COM CIDS 1+2 FAULT” or CIDS Maintenance status 'CIDS 1' or 'CIDS 2' could be spuriously triggered. In such event, the flight crew should verify that the CIDS is functioning normally by checking the PA, Cabin Interphone and Cabin lighting function. If the ECAM caution is spurious, it can be removed by resetting the CIDS when the aircraft is powered by the APU. PRO-SUP-24 Computer Reset Table - 27 - Flight Controls 00014180.0001001 29 MAR 12 Criteria: SA Applicable to: ALL Impacted DU: NONE Reason for issue: This Temporary Documentary Unit is created to allow flight crew to reset all SECs following a F/CTL SPLR FAULT triggered after the flight control check. This SEC reset covers the AIRBUS recommendations provided in OIT/FOT n°999.0038/11. (1) Evolution code : N=New, R=Revised, E=Effectivity
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-PLP-LETDU P 7/8 18 SEP 12
PROCEDURES PRELIMINARY PAGES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-PLP-LETDU P 8/8 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES
Intentionally left blank
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PRO-ABN-PLP PRELIMINARY PAGES TABLE OF CONTENTS SUMMARY OF HIGHLIGHTS
PRO-ABN-01 Introduction FCOM Procedure Layout.........................................................................................................................................A Operational Recommendations............................................................................................................................... B Use of Summaries...................................................................................................................................................C
PRO-ABN-10 Operating Techniques ENG Failure After V1 - Continued Takeoff............................................................................................................. A Immediate VMC LDG Following ENG Failure on TO............................................................................................. B Circling Approach with One Engine Inoperative..................................................................................................... C Landing with Slats or Flaps Jammed......................................................................................................................D Rejected Takeoff......................................................................................................................................................E Stall Recovery ........................................................................................................................................F Stall Warning At Lift-Off ........................................................................................................................ G Straight-In Approach with One Engine Inoperative.................................................................................................H
PRO-ABN-21 Air Conditioning / Pressurization / Ventilation AIR AFT CRG VENT FAULT.................................................................................................................................. A AIR COND CTL 1(2) - A(B) FAULT........................................................................................................................B AIR PACK 1(2) FAULT........................................................................................................................................... C AIR PACK 1 + 2 FAULT......................................................................................................................................... D AIR PACK 1(2) OFF................................................................................................................................................E AIR PACK 1(2) OVHT............................................................................................................................................. F AIR PACK 1(2) REGUL FAULT..............................................................................................................................G CABIN OVERPRESSURE.......................................................................................................................................H CAB PR EXCESS CAB ALT .................................................................................................................. I CAB PR EXCESS RESIDUAL PR .........................................................................................................J CAB PR LDG ELEV FAULT....................................................................................................................................K CAB PR LO DIFF PR.............................................................................................................................................. L CAB PR OFV NOT OPEN (on ground)..................................................................................................................M CAB PR SAFETY VALVE OPEN............................................................................................................................N CAB PR SYS 1(2) FAULT...................................................................................................................................... O CAB PR SYS 1+2 FAULT.......................................................................................................................................P COND AFT CARGO DUCT OVHT......................................................................................................................... Q COND AFT CRG HEAT FAULT............................................................................................................................. R COND AFT CRG ISOL VALVE...............................................................................................................................S COND FWD CAB/AFT CAB/CKPT DUCT OVHT................................................................................................... T
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-ABN-PLP-TOC P 1/12 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
PRELIMINARY PAGES - TABLE OF CONTENTS
FLIGHT CREW OPERATING MANUAL
COND HOT AIR FAULT......................................................................................................................................... U COND L + R CAB FAN FAULT.............................................................................................................................. V COND LAV + GALLEY FAN FAULT......................................................................................................................W COND TRIM AIR SYS FAULT................................................................................................................................ X VENT AVNCS SYS FAULT.....................................................................................................................................Y VENT BLOWER FAULT.......................................................................................................................................... Z VENT EXTRACT FAULT...................................................................................................................................... AA VENT SKIN VALVE FAULT..................................................................................................................................AB
PRO-ABN-22 Auto Flight AUTO FLT A/THR OFF...........................................................................................................................................A AUTO FLT AP OFF ...............................................................................................................................B AUTO FLT FAC 1(2) FAULT.................................................................................................................................. C AUTO FLT FAC 1 + 2 FAULT................................................................................................................................ D AUTO FLT FCU 1(2) FAULT.................................................................................................................................. E AUTO FLT FCU 1 + 2 FAULT................................................................................................................................ F AUTO FLT REAC W/S DET FAULT.......................................................................................................................G AUTO FLT RUD TRIM 1(2) FAULT........................................................................................................................H AUTO FLT RUD TRIM SYS..................................................................................................................................... I AUTO FLT RUD TRV LIM 1(2)............................................................................................................................... J AUTO FLT RUD TRV LIM SYS.............................................................................................................................. K AUTO FLT YAW DAMPER 1(2).............................................................................................................................. L AUTO FLT YAW DAMPER SYS............................................................................................................................ M LOSS OF FMS DATA IN DESCENT/APPROACH (SEVERE RESET).................................................................. N LOW ENERGY WARNING..................................................................................................................................... O
PRO-ABN-23 Communications COM ACARS FAULT..................................................................................................................................... A COM CIDS 1 + 2 FAULT........................................................................................................................................ B COM HF 1(2) DATA COM SATCOM DATA
FAULT..........................................................................................................................C FAULT....................................................................................................................... D
COM SATCOM FAULT.................................................................................................................................. E COM VHF 1(2)(3)/HF 1(2) EMITTING........................................................................................................... F COM VHF 3 DATA
FAULT............................................................................................................................G
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-ABN-PLP-TOC P 2/12 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PRO-ABN-24 Electrical
1
C/B TRIPPED.......................................................................................................................................................... A ELEC AC BUS 1 FAULT.........................................................................................................................................B ELEC AC BUS 2 FAULT.........................................................................................................................................C ELEC AC ESS BUS ALTN (on ground)..................................................................................................................D ELEC AC ESS BUS FAULT....................................................................................................................................E ELEC AC ESS BUS SHED..................................................................................................................................... F ELEC APU GEN FAULT.........................................................................................................................................G ELEC BAT 1(2) FAULT...........................................................................................................................................H ELEC BAT 1(2) OFF.................................................................................................................................................I ELEC BCL 1(2) FAULT............................................................................................................................................J ELEC DC BAT BUS FAULT....................................................................................................................................K ELEC DC BUS 1 FAULT.........................................................................................................................................L ELEC DC BUS 2 FAULT........................................................................................................................................M ELEC DC BUS 1+2 FAULT.................................................................................................................................... N ELEC DC EMER CONFIG......................................................................................................................................O ELEC DC ESS BUS FAULT................................................................................................................................... P ELEC DC ESS BUS SHED.................................................................................................................................... Q ELEC EMER CONFIG ...........................................................................................................................R ELEC EMER CONFIG SYS REMAINING...............................................................................................................S ELEC EMER GEN 1 LINE OFF.............................................................................................................................. T ELEC ESS BUSES ON BAT .................................................................................................................U ELEC ESS TR FAULT............................................................................................................................................ V ELEC GEN 1(2) or APU GEN OVERLOAD...........................................................................................................W ELEC GEN 1(2) FAULT.......................................................................................................................................... X ELEC GEN 1(2) OFF.............................................................................................................................................. Y ELEC IDG 1(2) DISCONNECTED (on ground)..................................................................................................... Z ELEC IDG 1(2) OIL LO PR/OVHT........................................................................................................................AA ELEC STAT INV FAULT.......................................................................................................................................AB ELEC TR 1(2) FAULT...........................................................................................................................................AC
PRO-ABN-25 Equipment COCKPIT DOOR FAULT........................................................................................................................................ A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-ABN-PLP-TOC P 3/12 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PRO-ABN-26 Fire Protection APU FIRE .............................................................................................................................................A ENG 1(2) FIRE (In Flight) .................................................................................................................... B ENG 1(2) FIRE (On Ground) ................................................................................................................ C ENG 1(2)/APU FIRE DET FAULT.......................................................................................................................... D ENG 1(2)/APU FIRE LOOP A(B) FAULT................................................................................................................E SMOKE FWD(AFT) CARGO SMOKE ................................................................................................... F SMOKE FWD(AFT) CRG BTL (1)(2 ) FAULT................................................................................................ G SMOKE FWD(AFT) CRG DET FAULT................................................................................................................... H SMOKE/FUMES/AVNCS SMOKE .......................................................................................................... I SMOKE/FUMES REMOVAL .................................................................................................................. J SMOKE DET FAULT............................................................................................................................................... K SMOKE LAVATORY DET FAULT ..........................................................................................................................L SMOKE LAVATORY SMOKE ..............................................................................................................M
PRO-ABN-27 Flight Controls CONFIG L (R) SIDESTICK FAULT BY TAKE OVER ........................................................................... A CONFIG PITCH TRIM NOT IN T.O RANGE ........................................................................................ B CONFIG RUD TRIM NOT IN T.O RANGE ........................................................................................... C CONFIG SLATS (FLAPS) NOT IN T.O CONFIG ..................................................................................D Config SPD BRK Not Retracted ............................................................................................................E F/CTL AIL SERVO FAULT...................................................................................................................................... F F/CTL ALTN LAW................................................................................................................................................... G F/CTL DIRECT LAW............................................................................................................................................... H F/CTL ELAC 1(2) FAULT (One Computer Failed)................................................................................................... I F/CTL ELAC 1 (2) FAULT (Both computers failed).................................................................................................J F/CTL ELAC 1 (2) PITCH FAULT...........................................................................................................................K F/CTL ELEV SERVO FAULT...................................................................................................................................L F/CTL FCDC 1 (2) FAULT......................................................................................................................................M F/CTL FCDC 1+2 FAULT........................................................................................................................................N F/CTL FLAP ATTACH SENSOR............................................................................................................................ O F/CTL FLAP LVR NOT ZERO .............................................................................................................. P F/CTL FLAP SYS 1(2) FAULT................................................................................................................................Q F/CTL FLAPS FAULT/LOCKED..............................................................................................................................R F/CTL FLAPS/SLATS FAULT/LOCKED..................................................................................................................S F/CTL GND SPLR / 1+2 / 3+4 / FAULT................................................................................................................. T F/CTL L (R) AIL FAULT..........................................................................................................................................U F/CTL L (R) ELEV FAULT...................................................................................................................................... V F/CTL L+R ELEV FAULT ..................................................................................................................... W F/CTL L(R) SIDESTICK FAULT.............................................................................................................................. X
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-ABN-PLP-TOC P 4/12 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
F/CTL SEC 1 (2) (3) FAULT................................................................................................................................... Y F/CTL SIDESTICK PRIORITY.................................................................................................................................Z F/CTL SLAT (FLAP) TIP BRK FAULT..................................................................................................................AA F/CTL SLAT SYS 1(2) FAULT..............................................................................................................................AB F/CTL SLATS AND FLAPS FAULT IN CONF 0.................................................................................................. AC F/CTL SLATS FAULT/LOCKED............................................................................................................................AD F/CTL SPD BRK 2(3+4) FAULT........................................................................................................................... AE F/CTL SPD BRK DISAGREE (Surfaces 3+4 Affected).........................................................................................AF F/CTL SPD BRK DISAGREE (Surfaces 2+3+4 Affected)....................................................................................AG F/CTL SPD BRK FAULT...................................................................................................................................... AH F/CTL SPD BRK STILL OUT................................................................................................................................. AI F/CTL SPLR FAULT.............................................................................................................................................. AJ F/CTL STABILIZER JAM...................................................................................................................................... AK STABILIZER JAM.................................................................................................................................................. AL ACTIVE CONTROL LAW..................................................................................................................................... AM ELEVATORS AND STABILIZER CONTROL AFTER FAILURE.......................................................................... AN F/CTL RUDDER JAM........................................................................................................................................... AO SIDESTICK/RUDDER PEDALS STIFF.................................................................................................................AP 2
PRO-ABN-28 Fuel FUEL APU LP VALVE FAULT................................................................................................................................ A FUEL AUTO FEED FAULT..................................................................................................................................... B FUEL CTR TK PUMP 1(2) LO PR......................................................................................................................... C FUEL CTR TK PUMPS LO PR...............................................................................................................................D FUEL CTR TK PUMPS OFF...................................................................................................................................E FUEL ENG 1(2) LP VALVE OPEN......................................................................................................................... F FUEL FQI CH 1(2) FAULT..................................................................................................................................... G FUEL IMBALANCE..................................................................................................................................................H FUEL LEAK............................................................................................................................................................... I FUEL L (R) OUTER (INNER) TK HI TEMP............................................................................................................ J FUEL L (R) OUTER (INNER) TK LO TEMP...........................................................................................................K FUEL L (R) TK PUMP 1(2) LO PR......................................................................................................................... L FUEL L (R) TK PUMP 1 + 2 LO PR (Center Tank Empty)....................................................................................M FUEL L (R) TK PUMP 1 + 2 LO PR (Center Tank not Empty).............................................................................. N FUEL L (R) WING TK LO LVL............................................................................................................................... O FUEL L + R WING TK LO LVL.............................................................................................................................. P FUEL L (R) XFR VALVE CLOSED.........................................................................................................................Q FUEL L (R) XFR VALVE OPEN............................................................................................................................. R FUEL X FEED VALVE FAULT................................................................................................................................S GRVTY FUEL FEEDING......................................................................................................................................... T
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-ABN-PLP-TOC P 5/12 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PRO-ABN-29 Hydraulic HYD B RSVR LO AIR PR.......................................................................................................................................A HYD B ELEC PUMP LO PR or OVHT................................................................................................................... B HYD B RSVR LO LVL............................................................................................................................................ C HYD B RSVR OVHT............................................................................................................................................... D HYD G ENG 1 PUMP LO PR (PTU Operative)......................................................................................................E HYD G ENG 1 PUMP LO PR (PTU Inoperative)....................................................................................................F HYD G RSVR LO AIR PR...................................................................................................................................... G HYD G RSVR LO LVL............................................................................................................................................ H HYD G RSVR OVHT................................................................................................................................................ I HYD Y ELEC PUMP LO PR or OVHT.................................................................................................................... J HYD Y ENG 2 PUMP LO PR (PTU Operative)...................................................................................................... K HYD Y ENG 2 PUMP LO PR (PTU Inoperative).................................................................................................... L HYD Y RSVR LO AIR PR...................................................................................................................................... M HYD Y RSVR LO LVL............................................................................................................................................ N HYD Y RSVR OVHT...............................................................................................................................................O HYD B+Y SYS LO PR .......................................................................................................................... P HYD G+B SYS LO PR ..........................................................................................................................Q HYD G+Y SYS LO PR ..........................................................................................................................R HYD PTU FAULT.................................................................................................................................................... S HYD RAT FAULT.....................................................................................................................................................T
PRO-ABN-30 Ice and Rain Protection ANTI ICE ALL PITOT.............................................................................................................................................. A ANTI ICE CAPT (F/O) TAT..................................................................................................................................... B ANTI ICE CAPT + F/O PITOT................................................................................................................................ C ANTI ICE CAPT + STBY PITOT.............................................................................................................................D ANTI ICE CAPT PITOT or L(R) STAT or AOA.......................................................................................................E ANTI ICE CAPT PROBES.......................................................................................................................................F ANTI ICE ENG 1(2) VALVE CLSD.........................................................................................................................G ANTI ICE ENG 1(2) VALVE OPEN........................................................................................................................ H ANTI ICE F/O + STBY PITOT..................................................................................................................................I ANTI ICE F/O PITOT or L(R) STAT or AOA...........................................................................................................J ANTI ICE F/O PROBES.......................................................................................................................................... K ANTI ICE L + R WINDSHIELD................................................................................................................................L ANTI ICE L(R) WINDOW........................................................................................................................................M ANTI ICE L(R) WINDSHIELD................................................................................................................................. N ANTI ICE STBY PITOT or L(R) STAT or AOA...................................................................................................... O
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-ABN-PLP-TOC P 6/12 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
ANTI ICE STBY PROBES.......................................................................................................................................P DOUBLE AOA HEAT FAILURE..............................................................................................................................Q WING ANTI ICE L(R) HI PR...................................................................................................................................R WING ANTI ICE L(R) VALVE OPEN (Failure Detected in Flight)......................................................................... S WING ANTI ICE L(R) VALVE OPEN (Failure Detected on Ground)...................................................................... T WING ANTI ICE OPEN ON GND...........................................................................................................................U WING ANTI ICE SYS FAULT (One Wing Valve Remains Closed when the Wing Anti-Ice Is Turned on)..............V WING ANTI ICE SYS FAULT (The Wing Anti-Ice Is Turned on after One Engine Shutdown or after the Loss of One Bleed)..............................................................................................................................................................W
PRO-ABN-31 Indicating / Recording Systems DISPLAY UNIT FAILURE........................................................................................................................................A EIS DMC 1(2)(3) FAULT......................................................................................................................................... B ECAM SINGLE DISPLAY........................................................................................................................................C FWS FWC 1 + 2 FAULT.........................................................................................................................................D FWS FWC 1(2) FAULT........................................................................................................................................... E FWS OEB/FWC DISCREPANCY............................................................................................................................ F FWS SDAC 1 + 2 FAULT.......................................................................................................................................G FWS SDAC 1(2) FAULT......................................................................................................................................... H MULTIPLE UNDUE ECAM ALERTS........................................................................................................................ I RECORDER DFDR FAULT..................................................................................................................................... J RECORDER SYS FAULT....................................................................................................................................... K
PRO-ABN-32 Landing Gear BRAKES - N/WS MINOR FAULT........................................................................................................................... A BRAKES A/SKID NWS FAULT or ANTI SKID/NWS OFF...................................................................................... B BRAKES ALTN BRK FAULT...................................................................................................................................C BRAKES ALTN L(R) RELEASED........................................................................................................................... D BRAKES AUTO BRK FAULT..................................................................................................................................E BRAKES BRK Y ACCU LO PR.............................................................................................................................. F BRAKES HOT......................................................................................................................................................... G BRAKES NORM + ALTN FAULT............................................................................................................................H BRAKES NORM BRK FAULT.................................................................................................................................. I BRAKES PARK BRK LO PR................................................................................................................................... J BRAKES PARK BRK ON........................................................................................................................................ K BRAKES RELEASED...............................................................................................................................................L BRAKES SYS 1(2) FAULT..................................................................................................................................... M ASYMMETRIC BRAKING........................................................................................................................................N LOSS OF BRAKING ............................................................................................................................. O RESIDUAL BRAKING PROC.................................................................................................................................. P
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-ABN-PLP-TOC P 7/12 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
CONFIG PARK BRK ON ...................................................................................................................... Q L/G DOORS NOT CLOSED....................................................................................................................................R L/G GEAR NOT DOWN ........................................................................................................................ S L/G GEAR NOT DOWNLOCKED ..........................................................................................................T L/G GEAR NOT UPLOCKED..................................................................................................................................U L/G GEAR UPLOCK FAULT................................................................................................................................... V L/G LGCIU 1 FAULT.............................................................................................................................................. W L/G LGCIU 1(2) FAULT (Two LGCIUs Faulty)...................................................................................................... X L/G LGCIU 2 FAULT............................................................................................................................................... Y L/G SHOCK ABSORBER FAULT (Shock Absorber Extended on the Ground)...................................................... Z L/G SHOCK ABSORBER FAULT (Shock Absorber not Extended after Liftoff)....................................................AA L/G SYS DISAGREE.............................................................................................................................................AB L/G GRAVITY EXTENSION..................................................................................................................................AC LDG WITH ABNORMAL L/G................................................................................................................................ AD WHEEL HYD SEL FAULT.................................................................................................................................... AE WHEEL N/W STRG FAULT.................................................................................................................................. AF WHEEL TYRE LO PR.......................................................................................................................................... AG
PRO-ABN-34 Navigation ALL ADR OFF ....................................................................................................................................... A EGPWS ALERTS .................................................................................................................................. B NAV ADR DISAGREE.............................................................................................................................................C IR ALIGNMENT IN ATT MODE.............................................................................................................................. D NAV ADR 1(2)(3) FAULT........................................................................................................................................ E NAV ADR 1+2 (1+3) (2+3) FAULT......................................................................................................................... F NAV ADR 1+2+3 FAULT ...................................................................................................................... G NAV ALTI DISCREPANCY..................................................................................................................................... H NAV ATT DISCREPANCY........................................................................................................................................I NAV BARO REF DISCREPANCY..........................................................................................................................J NAV CAPT (F/O) (STBY) AOA FAULT...................................................................................................................K NAV FM/GPS POS DISAGREE.............................................................................................................................. L NAV GPS 1(2) FAULT............................................................................................................................................M NAV GPWS FAULT.................................................................................................................................................N NAV GPWS TERR DET FAULT.............................................................................................................................O NAV HDG DISCREPANCY..................................................................................................................................... P NAV IAS DISCREPANCY....................................................................................................................................... Q NAV ILS (1+2) FAULT............................................................................................................................................ R NAV ILS 1(2) FAULT...............................................................................................................................................S NAV IR 1(2)(3) FAULT............................................................................................................................................ T NAV IR 1+2(1+3)(2+3) FAULT................................................................................................................................U
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-ABN-PLP-TOC P 8/12 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
NAV IR DISAGREE................................................................................................................................................. V NAV IR NOT ALIGNED .........................................................................................................................................W NAV PRED W/S DET FAULT................................................................................................................................. X NAV RA 1 AND 2 FAULT (Dual RA Failure).......................................................................................................... Y NAV RA 1(2) FAULT............................................................................................................................................... Z NAV RA DEGRADED........................................................................................................................................... AA NAV TCAS FAULT...................................................................................................................................... AB NAV TCAS STBY..................................................................................................................................................AC OVERSPEED ...................................................................................................................................... AD Stall Warning .......................................................................................................................................AE TCAS WARNINGS .............................................................................................................................. AF UNRELIABLE SPEED INDIC/ADR CHECK PROC..............................................................................................AG UNRELIABLE SPEED INDICATION/ADR CHECK PROC................................................................................... AH
PRO-ABN-36 Pneumatic AIR APU BLEED FAULT.........................................................................................................................................A AIR APU BLEED LEAK...........................................................................................................................................B AIR BLEED 1(2) OFF..............................................................................................................................................C AIR DUAL BLEED FAULT...................................................................................................................................... D AIR ENG 1(2) BLEED ABNORM PR...................................................................................................................... E AIR ENG 1(2) BLEED FAULT.................................................................................................................................F AIR ENG 1(2) BLEED LO TEMP (Opposite Bleed Available)................................................................................ G AIR ENG 1(2) BLEED LO TEMP (Opposite Bleed not Available).......................................................................... H AIR ENG 1 + 2 BLEED LO TEMP........................................................................................................................... I AIR ENG 1(2) BLEED NOT CLSD.......................................................................................................................... J AIR ENG 1(2) HP VALVE FAULT...........................................................................................................................K AIR ENG 1(2) LEAK DET FAULT........................................................................................................................... L AIR L(R) WING or ENG 1(2) BLEED LEAK...........................................................................................................M AIR L(R) WNG LEAK DET FAULT......................................................................................................................... N AIR X BLEED FAULT............................................................................................................................................. O BLEED MONITORING FAULT................................................................................................................................ P BLEED MONIT SYS 1(2) FAULT........................................................................................................................... Q
PRO-ABN-46 Information Systems DATALINK ATSU FAULT........................................................................................................................................ A DATALINK COMPANY FAULT................................................................................................................................B
PRO-ABN-49 APU APU AUTO (EMER) SHUT DOWN.........................................................................................................................A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-ABN-PLP-TOC P 9/12 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PRO-ABN-52 Doors DOORS (L/R/FWD/AFT) AVIONICS....................................................................................................................... A DOORS CABIN/EMER EXIT/CARGO..................................................................................................................... B
PRO-ABN-70 Power Plant ENG 1(2) BLEED STATUS FAULT (In Flight).......................................................................................................A ENG 1(2) BLEED STATUS FAULT (On Ground)................................................................................................... B ENG 1(2) COMPRESSOR VANE........................................................................................................................... C ENG 1(2) CTL VALVE FAULT................................................................................................................................D ENG 1(2) EIU FAULT ............................................................................................................................................ E ENG 1(2) FADEC A(B) FAULT............................................................................................................................... F ENG 1(2) FADEC ALTERNATOR.......................................................................................................................... G ENG 1(2) FADEC FAULT....................................................................................................................................... H ENG 1(2) FADEC HI TEMP..................................................................................................................................... I ENG 1(2) FAIL......................................................................................................................................................... J ENG 1(2) FUEL CTL FAULT.................................................................................................................................. K ENG 1(2) FUEL FILTER CLOG.............................................................................................................................. L ENG 1(2) FUEL RETURN VALVE ........................................................................................................................ M ENG 1(2) HP FUEL VALVE .................................................................................................................................. N ENG 1(2) IGN FAULT (IGN A or B Fault)..............................................................................................................O ENG 1(2) IGN FAULT (IGN A+B Fault)..................................................................................................................P ENG 1(2) LOW N1 (On Ground)...........................................................................................................................Q ENG 1(2) N1 or N2 or EGT or FF DISCREPANCY............................................................................................... R ENG 1(2) N1/N2/EGT OVERLIMIT......................................................................................................................... S ENG 1(2) OIL FILTER CLOG ................................................................................................................................ T ENG 1(2) OIL HI TEMP .........................................................................................................................................U ENG 1(2) OIL LO PR ............................................................................................................................ V ENG 1(2) ONE TLA FAULT................................................................................................................................... W ENG 1(2) OVSPD PROT FAULT............................................................................................................................X ENG 1(2) PROBES FAULT.....................................................................................................................................Y ENG 1(2) REV ISOL FAULT................................................................................................................................... Z ENG 1(2) REV PRESSURIZED .......................................................................................................................... AA ENG 1(2) REV SWITCH FAULT.......................................................................................................................... AB ENG 1(2) REVERSE UNLOCKED....................................................................................................................... AC ENG 1(2) REVERSER FAULT............................................................................................................................. AD ENG 1(2) SENSOR FAULT.................................................................................................................................. AE ENG 1(2) SHUT DOWN........................................................................................................................................AF ENG 1(2) STALL...................................................................................................................................................AG ENG 1(2) START FAULT..................................................................................................................................... AH ENG 1(2) START VALVE FAULT.......................................................................................................................... AI
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-ABN-PLP-TOC P 10/12 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
ENG 1(2) THR LEVER ABV IDLE .......................................................................................................AJ ENG 1(2) THR LEVER DISAGREE......................................................................................................................AK ENG 1(2) THR LEVER FAULT............................................................................................................................. AL ENG COMPRESSOR VANE................................................................................................................................ AM ENG DUAL FAILURE ......................................................................................................................... AN ENG DUAL FAILURE - FUEL REMAINING ......................................................................................AO ENG DUAL FAILURE - NO FUEL REMAINING ................................................................................AP ENG RELIGHT (In Flight).....................................................................................................................................AQ ENG REV SET......................................................................................................................................................AR ENG TAILPIPE FIRE............................................................................................................................................ AS ENG THR LEVERS NOT SET..............................................................................................................................AT ENG TYPE DISAGREE........................................................................................................................................ AU ENG VIB SYS FAULT ......................................................................................................................................... AV HIGH ENGINE VIBRATION................................................................................................................................. AW
PRO-ABN-80 Miscellaneous BOMB ON BOARD..................................................................................................................................................A COCKPIT WINDSHIELD/WINDOW ARCING......................................................................................................... B COCKPIT WINDSHIELD/WINDOW CRACKED......................................................................................................C CREW INCAPACITATION.......................................................................................................................................D DITCHING ..............................................................................................................................................E ECAM Advisory Conditions......................................................................................................................................F EMER DESCENT ..................................................................................................................................G EMERGENCY EVACUATION ............................................................................................................... H FORCED LANDING ................................................................................................................................ I OVERWEIGHT LANDING........................................................................................................................................ J TAILSTRIKE.............................................................................................................................................................K VOLCANIC ASH ENCOUNTER ............................................................................................................................. L WINDSHEAR .........................................................................................................................................M WINDSHEAR AHEAD ........................................................................................................................... N
PRO-ABN-90 Detailed Cabin / Cockpit Evacuation Procedure General.....................................................................................................................................................................A Cockpit-Assigned Duties for Evacuation................................................................................................................. B Cabin Crew-Assigned Areas for Evacuation...........................................................................................................C Communications...................................................................................................................................................... D On Ground Evacuation............................................................................................................................................ E Cockpit Evacuation through Window.......................................................................................................................F Evacuation on Water...............................................................................................................................................G
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-ABN-PLP-TOC P 11/12 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-ABN-PLP-TOC P 12/12 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title
Toc Index
ID
Reason
PRO-ABN-PLP-TOC ELEC ESS TR FAULT
1
PRO-ABN-PLP-TOC Fuel
2
Documentation update: Deletion of the "00012544.0001001 ELEC ESS TR FAULT - FWSPAGE" documentary unit. Documentation update: Deletion of the "00012543.0001001 ELEC ESS TR FAULT" documentary unit. Documentation update: Deletion of the "00011170.0001001 FUEL L (R) TK PUMP 1 + 2 LO PR (Center Tank not Empty)" documentary unit. Documentation update: Deletion of the "00011242.0001001 FUEL AUTO FEED FAULT" documentary unit. Documentation update: Addition of "ELEC ESS TR FAULT" documentary unit Documentation update: Addition of "ELEC ESS TR FAULT FWSPAGE" documentary unit Revision of the SMOKE/FUMES/AVNCS SMOKE procedure in order to specify the fact that the flight crew must apply the procedure also if there is a smell of smoke or fumes in the cockpit. Documentation update: Deletion of information. Update of the note in order to refer to the newly introduced QRH/Fuel Penalty Farctors tables. Documentation update: Addition of "FUEL AUTO FEED FAULT" documentary unit Documentation update: Addition of "FUEL L (R) TK PUMP 1 + 2 LO PR (Center Tank not Empty)" documentary unit
PRO-ABN-24 ELEC ESS TR FAULT PRO-ABN-24 ELEC ESS TR FAULT - FWSPAGE PRO-ABN-26 SMOKE/FUMES/AVNCS SMOKE
V
1
V
2
I
1
PRO-ABN-27 F/CTL L (R) AIL FAULT - FWSPAGE PRO-ABN-28 FUEL AUTO FEED FAULT PRO-ABN-28 FUEL L (R) TK PUMP 1 + 2 LO PR (Center Tank not Empty) PRO-ABN-34 NAV CAPT (F/O) (STBY) AOA FAULT PRO-ABN-34 NAV CAPT (F/O) (STBY) AOA FAULT - FWSPAGE PRO-ABN-34 NAV RA 1 + 2 FAULT - FWSPAGE (Dual RA Failure) PRO-ABN-70 ENG 1(2) SHUT DOWN - FWSPAGE
U
1
B
1
N
2
K
1
Administrative update: No technical change.
K
2
Administrative update: No technical change.
Y
3
'REAC W/S DET' added to the list of the 'INOP SYS'.
AF
1
A
1
Update of the status page to highlight that the landing distance procedure is to be applied only in case of severe ice accretion and ENG FIRE pb pushed. Documentation update: Information "N.00012597.0019001.014" moved from "N.00012597.0019001.006" to "N.00012597.0019001.010" Revision of the “Bomb on Board” procedure in order to replace the 4 challenge-response actions by 4 commands for layout enhancement purpose. Documentation update: Deletion of information.
PRO-ABN-80 BOMB ON BOARD
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-ABN-PLP-SOH P 1/2 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title PRO-ABN-80 WINDSHEAR PRO-ABN-80 WINDSHEAR AHEAD PRO-ABN-80 WINDSHEAR AHEAD
Toc Index
ID
M
2
N
3
N
4
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Reason Update of the technical wording. Documentation update: Deletion of information. Update of the technical wording. Documentation update: Deletion of information. Correction of the reference.
PRO-ABN-PLP-SOH P 2/2 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
INTRODUCTION
FLIGHT CREW OPERATING MANUAL
FCOM PROCEDURE LAYOUT Ident.: PRO-ABN-01-00012640.0001001 / 01 APR 11 Applicable to: ALL
INTRODUCTION The presentation of procedures is, as far as practicable, identical to the presentation on ECAM. The abbreviations are identical to those used on the cockpit panels. All actions and information displayed on ECAM are provided in large letters. Other information, not on ECAM, is provided in small letters. Expanded information is as far as practicable provided in layer 2. This information: ‐ Identifies the particular failures ‐ Explains actions for which the reason is not self-evident ‐ Furnishes additional background. PROCEDURE TITLE The title of an abnormal or emergency procedure, that appears on the ECAM, is on a white background. Abnormal procedure displayed on ECAM (amber caution) :
Emergency procedure displayed on ECAM (red warning) :
The title of an abnormal or emergency procedure, that does not appear on the ECAM is on a grey background. Abnormal procedure not displayed on ECAM :
Emergency procedure not displayed on ECAM :
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
PRO-ABN-01 P 1/8 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
INTRODUCTION
FLIGHT CREW OPERATING MANUAL
SEVERAL ALERTS UNDER THE SAME TITLE When applicable, several alerts may be grouped under the same procedure title. However, depending on the failure, the actions that the flight crew should perform may differ. Note:
Alerts that have the same procedure title may be differentiated by a subtitle (e.g. ENG FIRE (On Ground) versus ENG FIRE (In Flight)).
CONDITIONS BLACK SQUARE When several procedures appear under the same title, a black square marks the starting point of each procedure. For example:
Black squares also indicate parts of a procedure among which only one is applicable. For example:
The ECAM does not display black squares. BLACK DOT If an action depends on a precondition, a black dot identifies the precondition. If the precondition appears on ECAM, it appears in LARGE LETTERS. If not, it appears in small letters. For example: 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
PRO-ABN-01 P 2/8 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
INTRODUCTION
FLIGHT CREW OPERATING MANUAL
INDENTATION Indentation is used in order to identify when an action depends on a precondition/flight phase/procedure. For example:
‐ The APPR SPEED is equal to VREF +30 kt only if the flaps are locked, because "APPR SPEED......VREF +30" is indented below "• If flaps locked". ‐ The MAX SPEED of 250 kt does not depend on the flaps locked condition because it is aligned with "• If Flaps locked". Therefore, MAX SPEED has to be respected whether the flaps are locked or not. OPERATIONAL RECOMMENDATIONS Ident.: PRO-ABN-01-00012639.0001001 / 27 JAN 12 Applicable to: ALL
OVERVIEW Abnormal and Emergency procedures involve actions that the flight crew must perform in order to ensure adequate safety, and help to make the remainder of the flight easier.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← A to B →
PRO-ABN-01 P 3/8 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
INTRODUCTION
FLIGHT CREW OPERATING MANUAL
Abnormal and Emergency procedures are actions that the flight crew performs: ‐ After failures, that the ECAM detects, or ‐ After failures or situation, that the flight crew detects or encounters (e.g. CKPT WINDOW CRACKED, OVERWEIGHT LANDING), or ‐ After an aural alert (e.g. OBSTACLE AHEAD, PULL UP). When the flight crew performs procedures, the flight crew uses the “READ” and “DO” principle (oral reading). TASKSHARING The general tasksharing shown below applies to all procedures. The pilot's flying remains the pilot flying throughout the procedure. The Pilot Flying (PF), is responsible for the: ‐ Thrust levers ‐ Control of flight path and airspeed ‐ Aircraft configuration (request configuration change) ‐ Navigation ‐ Communications. The Pilot Not Flying (PNF), is responsible for: ‐ Monitoring and reading aloud the ECAM and checklists ‐ Performing required actions, or actions requested by the PF, if applicable ‐ Using the engine master switches, cockpit C/Bs, IR and guarded switches, with PF's confirmation. MEMORY ITEMS The following procedures are to be applied without referring to paper: ‐ CREW INCAPACITATION ‐ EGPWS , ‐ Immediate actions of EMER DESCENT ‐ Immediate actions of UNRELIABLE SPEED INDICATION/ADR CHECK PROC ‐ LOSS OF BRAKING ‐ STALL RECOVERY ‐ STALL WARNING AT LIFT-OFF ‐ TCAS ‐ WINDSHEAR ‐ WINDSHEAR AHEAD
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
PRO-ABN-01 P 4/8 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
INTRODUCTION
FLIGHT CREW OPERATING MANUAL
USE OF AUTOPILOT (AP) The AP has not been certified in all configurations, and its performance cannot be guaranteed. If the pilot chooses to use the AP in such circumstances, extra vigilance is required, and the AP must be disconnected, if the aircraft deviates from desired or safe flight path. For additional information, Refer to FCOM Limitations section (Auto Flight). INITIATION OF PROCEDURES Procedures are initiated on the Pilot Flying's command. No action is taken (apart from cancelling audio warnings, through the MASTER WARN light) until: ‐ The appropriate flight path is established, and ‐ The aircraft is at least 400 ft above the runway, if a failure occurs during takeoff, approach, or go-around. A height of 400 ft is recommended, because it is a good compromise between the necessary time for stabilization and excessive delay in procedure initiation. In some emergency cases, provided that the appropriate flight path is established, the Pilot Flying may initiate actions before this height. If an emergency causes LAND ASAP to appear in red on the ECAM, the flight crew must land as soon as possible at the nearest suitable airport at which a safe approach and landing can be made. If an abnormal procedure causes LAND ASAP to appear in amber on the ECAM, the flight crew should consider landing at the nearest suitable airport. LANDING DISTANCE Any increase in landing distance, resulting from an emergency or abnormality, must be based on the Actual Landing Distance without Autobrake - CONF FULL (Refer to FCOM Abnormal and Emergency section (Miscellaneous)). ECAM WARNING INHIBITION DURING TAKEOFF Some Warnings (non-inhibited) appear when the situation that prompts them occurs. Other warnings (inhibited) do not appear immediately, when the situation that prompts them occurs during takeoff. CREW COORDINATION When carrying out a procedure displayed on ECAM, both pilots must be aware of the present display. Before any "CLEAR" action, the pilots should crosscheck to confirm that there remains no blue message (except in case of no action feedback) that they can eliminate by a direct action. NO CLEAR ACTION BEFORE CROSS-CONFIRMATION Example of crew coordination and cross confirmation : 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
PRO-ABN-01 P 5/8 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
INTRODUCTION
FLIGHT CREW OPERATING MANUAL
For standard calls, Refer to FCOM Normal Procedures - Standard Callouts (1) Although it is the responsibility of the pilot flying to request ECAM actions, this does not preclude the captain from either taking control of the aircraft or ordering ECAM actions he (she) considers to be necessary Note:
ECAM procedures and STATUS, supplemented by a PFD/ND check suffice for handling the fault. However, before applying the ECAM procedures, the fault should be confirmed on the system display. When ECAM actions have been performed, and ECAM STATUS has been reviewed, the flight crew may refer to FCOM procedure (FCOM/PRO/ABN) for supplementary information, if time permits. USE OF SUMMARIES
Ident.: PRO-ABN-01-00013806.0001001 / 22 MAY 12 Applicable to: ALL
GENERAL The summaries consist of QRH procedures. They have been created to help the flight crew to handle the actions in the event of an ELEC EMER CONFIG or a dual HYD failure. In any case, the ECAM should be applied first. This includes both the procedure and the STATUS page review. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← B to C →
PRO-ABN-01 P 6/8 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
INTRODUCTION
FLIGHT CREW OPERATING MANUAL
SITUATION ASSESSMENT The CRUISE section highlights the remaining systems, the main limitations and the flight capability of the aircraft. This section may help the flight crew to assess the situation and to choose an appropriate landing runway. The flight crew refers, in the meantime, to the corresponding chapters of the QRH for: ‐ The evaluation of an increased fuel consumption (FPE-FPF), ‐ The VAPP computation at the selected airport (FPE-IFL), ‐ The In-Flight Landing Distance computation (FPE-IFL). APPROACH PREPARATION As always, the approach preparation begins by the review of the STATUS page. Then, the APPROACH, LANDING and GO AROUND sections of the summary should be used to prepare and conduct the approach briefing, cross-checking, as usual, the associated FMS pages. When appropriate, these sections include, among others, the LANDING WITH SLATS or FLAPS JAMMED procedure and the L/G GRAVITY EXTENSION procedure. APPROACH The APPR PROC actions given by the STATUS page should be performed by reading the APPROACH section of the summary (PNF), avoiding then to refer to other paper procedures. Once the aircraft is in final configuration, the LANDING and the GO AROUND sections may be shortly commented, as a reminder (braking, NWS, reversers and L/G retraction in case of go-around). Before the final approach, the PNF should review the STATUS page and check that all the APPR PROC actions have been completed.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C
PRO-ABN-01 P 7/8 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
INTRODUCTION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-ABN-01 P 8/8 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
OPERATING TECHNIQUES
ENG FAILURE AFTER V1 - CONTINUED TAKEOFF Ident.: PRO-ABN-10-00010679.0006001 / 22 NOV 11 Applicable to: ALL
If an engine fails after the aircraft passes V1, the takeoff must be continued. Use rudder conventionally to stay on the runway centerline. At VR, rotate the aircraft smoothly using a continuous pitch rate to a pitch attitude of 12.5 °. After lift-off, follow the Speed Reference System (SRS). When airborne with a positive rate of climb, select the landing gear up. Use rudder to prevent yaw. Shortly after lift-off, β target will appear. Adjust rudder position to zero the β target. Control heading conventionally with bank, keeping the β target at zero with rudder. Consider the use of TOGA thrust. Consider the use of autopilot. At 400 ft minimum, apply the ECAM procedure. At acceleration height, level off and allow the speed to increase. • At F speed select CONF 1. • At S speed select CONF 0. When the FLAPS lever is at zero, β target reverts to sideslip indication: Center the sideslip indication conventionally. At green dot speed (engine-out operating speed in clean configuration): Resume the climb using maximum continuous thrust and maintain green dot speed. (If already in the FLX/MCT gate, move to CL and back to MCT). MAXIMUM TAKEOFF THRUST IS ONLY ALLOWED FOR 10 min. ENGINE FAILURE DURING INITIAL CLIMB-OUT Proceed as above. However, if the failure occurs above V2 maintain the SRS commanded attitude (or the speed reached after recovery). In any case, the minimum speed must be equal to V2. ENGINE OPERATION AT MAX T.O. THRUST IS LIMITED TO 10 min
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
Continued on the following page
PRO-ABN-10 P 1/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
OPERATING TECHNIQUES
ENG FAILURE AFTER V1 - CONTINUED TAKEOFF (Cont'd)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
PRO-ABN-10 P 2/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
OPERATING TECHNIQUES
IMMEDIATE VMC LDG FOLLOWING ENG FAILURE ON TO Ident.: PRO-ABN-10-00010680.0002001 / 18 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Continued on the following page
B→
PRO-ABN-10 P 3/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
OPERATING TECHNIQUES
IMMEDIATE VMC LDG FOLLOWING ENG FAILURE ON TO (Cont'd)
Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B→
PRO-ABN-10 P 4/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
OPERATING TECHNIQUES
FLIGHT CREW OPERATING MANUAL
IMMEDIATE VMC LDG FOLLOWING ENG FAILURE ON TO (Cont'd) CIRCLING APPROACH WITH ONE ENGINE INOPERATIVE Ident.: PRO-ABN-10-00010682.0004001 / 13 AUG 10 Applicable to: ALL
LANDING WEIGHT..................................................................................................................CHECK If the aircraft weight is above the maximum weight for circling in CONF 3 (given in the table below): The aircraft cannot maintain flight level with CONF 3 and the landing gear down. FOR LDG.................................................................................................................. USE FLAP 3 CONF 3 is preferred, to minimize a configuration change in short final. GPWS LDG FLAP 3.................................................................................................................ON Delay gear extension. Note:
OAT (°C)
0 5 10 15 20 25 30 35 40 45 50 55
‐ If the approach is flown at less than 750 ft RA, the “L/G NOT DOWN” warning will be triggered. The pilot can cancel the aural warning by pressing the EMER CANC pb, located on the ECAM control panel. ‐ A ”TOO LOW GEAR” warning is to be expected, if the landing gear is not downlocked at 500 ft RA. AIRPORT ELEVATION (feet) 6 000 8 000 10 000 63 58 53
0 77
2 000 76
4 000 69
12 000 48
14 000 45
77
76
69
63
58
77
76
69
63
58
53
48
45
53
48
77
76
69
63
45
58
53
48
77
76
69
45
63
58
53
48
77
75
45
69
63
58
53
48
77
45
72
68
63
58
53
48
74
70
66
63
56
51
71
67
63
59
69
65
61
67
63
64 MAXIMUM WEIGHT FOR CIRCLING IN CONF 3 (1000 KG)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← B to C
PRO-ABN-10 P 5/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
OPERATING TECHNIQUES
FLIGHT CREW OPERATING MANUAL
LANDING WITH SLATS OR FLAPS JAMMED Ident.: PRO-ABN-10-00010683.0001001 / 06 APR 12 Applicable to: ALL
LANDING CONF..................................................................................................................... CONF 3 Repeat the following until landing configuration is reached: SPEED SEL....................................................................................................... VFE NEXT - 5 kt Decelerate towards VFE NEXT - 5 kt but not below VLS. In case of turbulence, to avoid VFE exceedance, the pilot may decide to decelerate to a lower speed, but not below VLS. Note:
‐ The autopilot may be used down to 500 ft AGL. As it is not tuned for abnormal configurations, its behavior can be less than optimum and must be monitored ‐ Approach with selected speed is recommended ‐ A/THR is recommended, except in the case of a G+B SYS LO PR warning ‐ OVERSPEED warning and VLS, displayed on the PFD, are computed according to the actual flaps/slats position ‐ VFE and VFE NEXT are displayed on the PFD according to the FLAPS lever position. If not displayed, use the placard speeds ‐ If VLS is greater than VFE NEXT (overweight landing case), the FLAPS lever can be set in the required next position, while the speed is reduced to follow VLS reduction as surfaces extend. The VFE warning threshold should not be triggered. In this case, disconnect the A/THR. A/THR can be re-engaged when the landing configuration is established.
As speed reduces through VFE NEXT: FLAPS LEVER................................................................................................ONE STEP DOWN When landing configuration is established: DECELERATE TO CALCULATED APPROACH SPEED IN FINAL APPROACH FOR GO AROUND The table (See below) provides the MAX SPEEDS for the abnormal configurations. IF SLATS FAULT: FOR CIRCUIT: MAINTAIN SLATS/FLAPS CONFIGURATION Recommended speed: MAX SPEED - 10 kt FOR DIVERSION: SELECT CLEAN CONFIGURATION
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D→
Continued on the following page
PRO-ABN-10 P 6/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
OPERATING TECHNIQUES
FLIGHT CREW OPERATING MANUAL
LANDING WITH SLATS OR FLAPS JAMMED (Cont'd) Recommended flaps retraction speed is between MAX SPEED - 10 kt and MAX SPEED. Recommended diversion speed: MAX SPEED - 10 kt. IF FLAPS FAULT: FOR CIRCUIT: MAINTAIN SLATS/FLAPS CONFIGURATION Recommended speed: MAX SPEED - 10 kt FOR DIVERSION: If FLAPS jammed at 0: SELECT CLEAN CONFIGURATION Note:
‐ Recommended speed for slats retraction is between MAX SPEED - 10 kt and MAX SPEED of actual slat/flap position.
Normal operating speeds If FLAPS jammed > 0: MAINTAIN SLAT/FLAP CONFIGURATION Recommended speed for diversion: MAX SPEED - 10 kt Note:
Slats
Flaps
S=0 0 14 000 FT: PAX OXY MASKS...........................................................................................................MAN ON This action confirms that the passenger oxygen masks are released. Note:
‐ When descent is established and if time permits, check that the OUTFLOW VALVE is closed on the CAB PRESS SD page. If it is not closed and ΔP is positive, select the other CPC. If the OUTFLOW VALVE is still not closing set the cabin pressure MODE SEL pb to MAN and the V/S CTL sw to full down. ‐ Notify the cabin crew when the aircraft reaches a safe flight level, and when cabin oxygen is no more necessary.
Ident.: PRO-ABN-21-T-00010755.0001001 / 05 AUG 10
MAX FL..................................................................... 100/MEA CAB PR EXCESS RESIDUAL PR Ident.: PRO-ABN-21-00010764.0001001 / 10 JAN 11 Applicable to: ALL
PACK 1..........................................................................................................................................OFF PACK 2..........................................................................................................................................OFF CABIN CREW........................................................................................................................... ALERT CAB PR LDG ELEV FAULT Ident.: PRO-ABN-21-00010765.0002001 / 17 MAR 11 Applicable to: ALL
L2
LDG ELEV.............................................................................................................................. ADJUST Landing field elevation from FMGC is not available. Landing elevation must be manually selected with LDG ELEV selector. Refer to the LDG ELEV indication on the CRUISE page on the CAB PRESS SD page to adjust the required landing elevation. Note:
If the landing is performed on QFE, set 0 ft on LDG ELEV selector.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← I to K
PRO-ABN-21 P 7/18 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
AIR CONDITIONING / PRESSURIZATION / VENTILATION
CAB PR LO DIFF PR Ident.: PRO-ABN-21-00010762.0002001 / 05 AUG 10 Applicable to: ALL
EXPECT HI CAB RATE A/C V/S..................................................................................................................................REDUCE L2 This line is not displayed in case of Emergency Descent due to Excessive Cabin Altitude. CAB PR OFV NOT OPEN (ON GROUND) Ident.: PRO-ABN-21-00010763.0002001 / 05 AUG 10 Applicable to: ALL
MODE SEL................................................................................................................................... MAN MAN V/S CTL........................................................................................................................FULL UP L2 It may take 10 s in manual mode before the crew notices a change of the outflow valve position. L1
IF UNSUCCESSFUL: PACK 1................................................................................................................................... OFF PACK 2................................................................................................................................... OFF
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
L to M
PRO-ABN-21 P 8/18 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
AIR CONDITIONING / PRESSURIZATION / VENTILATION
CAB PR SAFETY VALVE OPEN Ident.: PRO-ABN-21-W-NG00809 Applicable to: ALL Ident.: PRO-ABN-21-W-00010766.0002001 / 05 AUG 10 L2 L1
L2
L1
The safety valve has opened due to cabin overpressure, or negative differential pressure. IF DIFF PR ABV 8 PSI: MODE SEL.............................................................................................................................MAN MAN V/S CTL................................................................................................................AS RQRD If overpressure is confirmed, reduce cabin ΔP. It may take 10 s in manual mode before the crew notices a change of the outflow valve position. IF UNSUCCESSFUL: A/C FL...................................................................................................................... REDUCE IF DIFF PR BELOW 0 PSI: EXPECT HI CAB RATE A/C V/S........................................................................................................................... REDUCE
Ident.: PRO-ABN-21-W-00010767.0003001 / 17 MAR 11
MAN CAB PR CTL TGT V/S: CLIMB............................................ 500 FT/MIN TGT V/S: DESC............................................. 300 FT/MIN A/C FL 390 350 300 250 < 200
CAB ALT TGT 8 000 7 000 5 500 3 000 0
DURING FINAL APPR: MAN V/S CTL.............................................. FULL UP CAUTION
Check that ΔP is zero before opening the doors.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
N
PRO-ABN-21 P 9/18 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
AIR CONDITIONING / PRESSURIZATION / VENTILATION
CAB PR SYS 1(2) FAULT Ident.: PRO-ABN-21-U-NG00807 Applicable to: ALL Ident.: PRO-ABN-21-U-00010756.0001001 / 05 AUG 10 L2
Crew awareness.
Ident.: PRO-ABN-21-U-00010758.0001001 / 05 AUG 10
STATUS INOP SYS
CAB PR 1 (2)
CAB PR SYS 1+2 FAULT Ident.: PRO-ABN-21-V-NG00808 Applicable to: ALL Ident.: PRO-ABN-21-V-00010759.0001001 / 05 AUG 10 L2
Due to the slow closure of the outflow valve in manual pressurization mode and depending on the failure, the following procedure may not avoid the depressurization.
L1
MODE SEL................................................................................................................................... MAN MAN V/S CTL...................................................................................................................... AS RQRD
L2
‐ It may take 10 s in manual mode before the crew notices a change of the outflow valve position. Use the cabin V/S indication to confirm the outflow valve operation. ‐ Monitor cabin V/S and CAB ALT frequently and adjust as necessary. Maintain aircraft altitude at or above cabin altitude. ‐ The two safety valves limit ΔP to 8.6 PSI. Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
O to P →
PRO-ABN-21 P 10/18 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
AIR CONDITIONING / PRESSURIZATION / VENTILATION
CAB PR SYS 1+2 FAULT (Cont'd) Ident.: PRO-ABN-21-V-00010760.0003001 / 17 MAR 11
STATUS MAN CAB PR CTL TGT V/S: CLIMB............................................ 500 FT/MIN TGT V/S: DESC............................................. 300 FT/MIN A/C FL 390 350 300 250 < 200
CAB ALT TGT 8 000 7 000 5 500 3 000 0
INOP SYS
CAB PR 1 + 2
DURING FINAL APPR: MAN V/S CTL.............................................. FULL UP CAUTION
Check that ΔP is zero before opening the doors. COND AFT CARGO DUCT OVHT
Ident.: PRO-ABN-21-H-NG00794 Applicable to: ALL Ident.: PRO-ABN-21-H-00010724.0004001 / 05 AUG 10
L2
WHEN DUCT TEMP < 70 DEG C: HOT AIR (ON CARGO HEAT PANEL).................................................................OFF THEN ON Hot air pressure regulating valve reopens.
Ident.: PRO-ABN-21-H-00010727.0004001 / 05 AUG 10
STATUS INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← P to Q
AFT CRG HEAT
PRO-ABN-21 P 11/18 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
AIR CONDITIONING / PRESSURIZATION / VENTILATION
COND AFT CRG HEAT FAULT Ident.: PRO-ABN-21-K-NG00797 Applicable to: ALL Ident.: PRO-ABN-21-K-00010734.0001001 / 05 AUG 10 L2
Crew awareness.
Ident.: PRO-ABN-21-K-00010735.0001001 / 05 AUG 10
STATUS INOP SYS
AFT CRG HEAT
COND AFT CRG ISOL VALVE Ident.: PRO-ABN-21-J-NG00796 Applicable to: ALL Ident.: PRO-ABN-21-J-00010732.0001001 / 05 AUG 10 L2
Crew awareness
Ident.: PRO-ABN-21-J-00010733.0004001 / 05 AUG 10
STATUS INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
R to S
AFT CRG HEAT AFT CRG VENT
PRO-ABN-21 P 12/18 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
AIR CONDITIONING / PRESSURIZATION / VENTILATION
COND FWD CAB/AFT CAB/CKPT DUCT OVHT Ident.: PRO-ABN-21-F-NG00792 Applicable to: ALL Ident.: PRO-ABN-21-F-00010720.0001001 / 05 AUG 10
WHEN DUCT TEMP < 70 DEG C: HOT AIR................................................................................................................OFF THEN ON Hot air pressure regulating valve reopens.
L2
Ident.: PRO-ABN-21-F-00010721.0001001 / 05 AUG 10 L12
STATUS •
If system not recovered: CAB TEMP BY PACK ONLY Basic temperature regulation is by packs only (remains automatic).
INOP SYS
HOT AIR
COND HOT AIR FAULT Ident.: PRO-ABN-21-I-NG00795 Applicable to: ALL Ident.: PRO-ABN-21-I-00010728.0001001 / 05 AUG 10
HOT AIR (IF NOT CLOSED)........................................................................................................ OFF IF HOT AIR STILL OPEN and DUCT OVHT persists: PACK 1................................................................................................................................... OFF PACK 2................................................................................................................................... OFF DESCENT TO FL 100/MEA L2 Descend to FL 100, or MEA, whichever is higher. L1
WHEN DIFF PR < 1 PSI AND FL BELOW 100: RAM AIR...................................................................................................................................ON MAX FL........................................................................................................................... 100/MEA Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
T to U →
PRO-ABN-21 P 13/18 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
AIR CONDITIONING / PRESSURIZATION / VENTILATION
COND HOT AIR FAULT (Cont'd) Ident.: PRO-ABN-21-I-00010729.0001001 / 05 AUG 10 L12
STATUS •
if HOT AIR closed only: CAB TEMP BY PACK ONLY Basic temperature regulation by packs only (remains automatic).
INOP SYS
PACK 1 + 2 (if PACKS closed) HOT AIR
COND L + R CAB FAN FAULT Ident.: PRO-ABN-21-R-NG00804 Applicable to: ALL Ident.: PRO-ABN-21-R-00010748.0001001 / 05 AUG 10 L2
Both cabin fan motors overheat. Cabin fans stop.
L1
PACK FLOW..................................................................................................................................... HI
Ident.: PRO-ABN-21-R-00010749.0001001 / 05 AUG 10
STATUS INOP SYS
L + R CAB FAN
COND LAV + GALLEY FAN FAULT Ident.: PRO-ABN-21-S-NG00805 Applicable to: ALL Ident.: PRO-ABN-21-S-00010751.0002001 / 05 AUG 10 L2
Cabin zone temperature sensors are normally ventilated by the air extracted by the fan. Therefore, cabin zone temperature regulation is lost. Crew awareness. Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← U to W →
PRO-ABN-21 P 14/18 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
AIR CONDITIONING / PRESSURIZATION / VENTILATION
FLIGHT CREW OPERATING MANUAL
COND LAV + GALLEY FAN FAULT (Cont'd) Ident.: PRO-ABN-21-S-00010752.0011001 / 05 AUG 10 L12
STATUS •
If ACSC 2 is operative: CAB TEMP CKPT CTL ONLY
INOP SYS
‐ To adjust the cabin zone temperature, use the FWD CABIN and AFT CABIN zone temperature selectors (overhead panel). The selectors control the cabin duct temperature directly. ‐ Cockpit temperature regulation is normal. •
GALLEY FAN PACK 2
(1)
COND CTL 2
(1)
If ACSC 2 is inoperative: CAB AT FIXED TEMP
‐ FWD CABIN and AFT CABIN zone temperature selectors are inoperative. ‐ To adjust the cabin zone temperature, use the COCKPIT zone temperature selector (overhead panel). Cabin duct temperature is the same as cockpit duct temperature. ‐ Cockpit temperature regulation is normal. (1)
(If ACSC 2 is inoperative)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←W
PRO-ABN-21 P 15/18 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
AIR CONDITIONING / PRESSURIZATION / VENTILATION
COND TRIM AIR SYS FAULT Ident.: PRO-ABN-21-00010730.0001001 / 05 AUG 10 Applicable to: ALL
One trim valve failed: A message corresponding to the affected valve is displayed: AFT CAB TRIM VALVE FWD CAB TRIM VALVE CKPT TRIM VALVE High pressure detected downstream of the hot air pressure regulating valve: TRIM AIR HI PR L2
Note:
If the warning and the TRIM AIR HI PR message are triggered when all trim air valves are closed (during the first 30 s after the packs are selected on, or in flight, if all zone heating demands are fulfilled), disregard them. VENT AVNCS SYS FAULT
Ident.: PRO-ABN-21-AA-NG00813 Applicable to: ALL Ident.: PRO-ABN-21-AA-00010774.0001001 / 05 AUG 10 L2
Triggered when the AEVC is not supplied, or when the valve position disagrees with the commanded position, or when the power-up test is not satisfactory. Crew awareness.
Ident.: PRO-ABN-21-AA-00010775.0001001 / 05 AUG 10
STATUS INOP SYS AVNCS VENT VENT BLOWER
(1)
(1)
VENT EXTRACT
(1)
(If AEVC not supplied)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
X to Y
PRO-ABN-21 P 16/18 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
AIR CONDITIONING / PRESSURIZATION / VENTILATION
VENT BLOWER FAULT Ident.: PRO-ABN-21-X-NG00810 Applicable to: ALL Ident.: PRO-ABN-21-X-00010768.0005001 / 10 JAN 11
L2
L1
If NO DC ESS BUS FAULT: BLOWER..............................................................................................................................OVRD The ventilation system is in closed circuit configuration and air from air conditioning is added to the ventilation air. If DC ESS BUS FAULT:
LAND ASAP
Ident.: PRO-ABN-21-X-00010769.0005001 / 10 JAN 11
STATUS INOP SYS (1)
VENT BLOWER
(1)
(If DC ESS BUS FAULT) VENT EXTRACT FAULT
Ident.: PRO-ABN-21-Y-NG00811 Applicable to: ALL Ident.: PRO-ABN-21-Y-00010770.0001001 / 05 AUG 10
L2
EXTRACT................................................................................................................................... OVRD The ventilation system is in closed circuit configuration and air from air conditioning is added to the ventilation air.
Ident.: PRO-ABN-21-Y-00010771.0001001 / 05 AUG 10
STATUS INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Z to AA
VENT EXTRACT
PRO-ABN-21 P 17/18 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
AIR CONDITIONING / PRESSURIZATION / VENTILATION
VENT SKIN VALVE FAULT Ident.: PRO-ABN-21-Z-NG00812 Applicable to: ALL Ident.: PRO-ABN-21-Z-00010772.0001001 / 05 AUG 10
If INLET valve not fully closed in flight: L2 L1
L2
L1
L2
Crew awareness No action is required, since there is a non return valve at the air inlet. If EXTRACT valve affected: BLOWER..............................................................................................................................OVRD EXTRACT............................................................................................................................ OVRD These actions send additional closure signals to the inlet and extract valves. The weather radar image on both NDs may be lost, in case of insufficient ventilation. IF UNSUCCESSFUL: MAX FL.....................................................................................................................100/MEA CAB PR MODE SEL....................................................................................................... MAN MAN V/S CTL...........................................................................................................FULL UP The aircraft is manually depressurized. It may take 10 s in manual mode before the crew notices a change of the outflow valve position.
Ident.: PRO-ABN-21-Z-00010773.0001001 / 05 AUG 10
STATUS MAX FL: 100/MEA (or minimum obstacle clearance altitude)
INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
AB
AVNCS VALVE
PRO-ABN-21 P 18/18 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
AUTO FLIGHT
FLIGHT CREW OPERATING MANUAL
AUTO FLT A/THR OFF Ident.: PRO-ABN-22-L-NG00764 Applicable to: ALL Ident.: PRO-ABN-22-L-00010468.0001001 / 05 AUG 10 L2
This warning is displayed only for involuntary disconnection. For voluntary disconnection an amber “A/THR OFF” message is displayed in the right lower part of ECAM upper DU. If the A/THR is failed, the flight crew may recover it by engaging the other AP, and then trying to re-engage the A/THR. Note:
If the A/THR is recovered with AP 2, A/THR will be lost again at AP 2 disengagement.
Crew awareness Ident.: PRO-ABN-22-L-00010469.0001001 / 05 AUG 10
STATUS CAT 2 ONLY
INOP SYS
A/THR CAT 3
AUTO FLT AP OFF Ident.: PRO-ABN-22-K-NG00763 Applicable to: ALL Ident.: PRO-ABN-22-K-00010466.0001001 / 05 AUG 10 L2
This warning is displayed only for involuntary disconnection. For voluntary disconnection a red AP OFF message is displayed in the right lower part of ECAM upper DU. Crew awareness
Ident.: PRO-ABN-22-K-00010467.0002001 / 05 AUG 10
STATUS INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
AP (Affected) CAT 2 (If both AP lost)
PRO-ABN-22 P 1/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
AUTO FLIGHT
FLIGHT CREW OPERATING MANUAL
AUTO FLT FAC 1(2) FAULT Ident.: PRO-ABN-22-G-NG00759 Applicable to: ALL Ident.: PRO-ABN-22-G-00010457.0001001 / 05 AUG 10
FAC (AFFECTED)....................................................................................................... OFF THEN ON IF UNSUCCESSFUL: FAC (AFFECTED).................................................................................................................. OFF L2 All functions are performed by the remaining FAC. Ident.: PRO-ABN-22-G-00010458.0001001 / 05 AUG 10 L12
STATUS BOTH PFD ON SAME FAC (1) See CAT 3 SINGLE ONLY
INOP SYS
(1)
CAT 3 DUAL FAC 1(2)
Characteristic speeds, displayed on the two PFDs, are computed by the same FAC.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
PRO-ABN-22 P 2/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
AUTO FLIGHT
FLIGHT CREW OPERATING MANUAL
AUTO FLT FAC 1 + 2 FAULT Ident.: PRO-ABN-22-H-NG00760 Applicable to: ALL Ident.: PRO-ABN-22-H-00010459.0002001 / 05 AUG 10
RUD WITH CARE ABV 160 KT Depending on when the failure occurs, the rudder travel limiter system may not be in the correct position for the flight speed. Therefore, to prevent damage to the aircraft structure, use the rudder with care, when the speed is above 160 kt. At slats’ extension, full rudder travel authority is recovered. L1 FAC 1 ......................................................................................................................... OFF THEN ON FAC 2.......................................................................................................................... OFF THEN ON IF UNSUCCESSFUL: FAC 1 + 2...............................................................................................................................OFF L2 With FAC 1 + 2 inoperative, the rudder travel limit system, rudder trim control, yaw damper and PFD characteristic speeds are lost. L2
L12
ASSOCIATED PROCEDURES
L1 L2
F/CTL ALTN LAW (PROT LOST) F/CTL normal laws are lost. All protections, except maneuver protections, are lost. MAX SPEED .....................................................................................................................320 KT Speed is limited, due to the loss of high-speed protections. Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D→
PRO-ABN-22 P 3/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
AUTO FLIGHT
FLIGHT CREW OPERATING MANUAL
AUTO FLT FAC 1 + 2 FAULT (Cont'd) Ident.: PRO-ABN-22-H-00010460.0117001 / 11 MAY 12 L12
STATUS MAX SPEED................................................................ 320 KT RUD WITH CARE ABV 160 KT
APPR PROC FOR LDG......................................................USE FLAP 3 This line is replaced by "FOR LDG : USE FLAP 3" when CONF 3 is selected, as a reminder. GPWS LDG FLAP 3.................................................... ON Displayed, when flaps in CONF 3. APPR SPD.................................................VREF + 10 KT LDG DIST PROC...................................................APPLY
INOP SYS REAC W/S DET F/CTL PROT FAC 1 + 2 AP 1 + 2 A/THR CAT 2
ALTN LAW : PROT LOST WHEN L/G DN : DIRECT LAW (1) See (1)
At landing gear extension, control reverts to direct law in pitch, as well as in roll (Refer to PRO-ABN 27 F/CTL DIRECT LAW procedure). AUTO FLT FCU 1(2) FAULT
Ident.: PRO-ABN-22-J-NG00762 Applicable to: ALL Ident.: PRO-ABN-22-J-00010464.0001001 / 05 AUG 10
L2
BARO REF........................................................................................................................... X CHECK One FCU channel is lost: Therefore, crosscheck the barometric reference settings on the FCU and PFDs. Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← D to E →
PRO-ABN-22 P 4/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
AUTO FLIGHT
FLIGHT CREW OPERATING MANUAL
AUTO FLT FCU 1(2) FAULT (Cont'd) Ident.: PRO-ABN-22-J-00010465.0001001 / 05 AUG 10
STATUS INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E
FCU 1(2)
PRO-ABN-22 P 5/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
AUTO FLIGHT
FLIGHT CREW OPERATING MANUAL
AUTO FLT FCU 1 + 2 FAULT Ident.: PRO-ABN-22-I-NG00761 Applicable to: ALL Ident.: PRO-ABN-22-I-00010462.0001001 / 05 AUG 10
L2
PFD BARO REF: STD ONLY With both FCU channels failed, the barometer reference automatically goes to 1 013 hPa. Use standby altimeter, and change this to the actual barometer setting. Do not insert the MDA (MDH) value on the MCDU PERF APPR Page (because the PFD altitude is referenced to STD, and not to the correct barometric value). The PNF must then perform the standard callouts (“HUNDRED ABOVE” and “MINIMUM”), using the STBY altimeter. In addition: ‐ All FCU controls are inoperative. ‐ A/THR, AP 1 + 2, and FD 1 + 2 are not available. (Except in LAND or GO AROUND mode where only A/THR is lost). ‐ On PFD: • Altitude alert is inoperative. • ILS deviation scales are displayed. • Flight path vector is displayed. • Mach indication is inoperative. • FMA is lost except in LAND or GA mode. ‐ On ND: • ROSE NAV mode with map (80 nm range) is displayed. • VOR/ADF needles: Needle 1 is related to VOR1 only. Needle 2 is related to ADF2 only (ADF1 if ADF2 not installed). (VOR selection on DDRMI is not affected) (ADF selection on DDRMI (if available) is not affected). • The weather radar image may be lost. If the image remains displayed it must be disregarded. In all cases, red “WXR RNG” message is displayed. Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F→
PRO-ABN-22 P 6/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
AUTO FLIGHT
FLIGHT CREW OPERATING MANUAL
AUTO FLT FCU 1 + 2 FAULT (Cont'd) Ident.: PRO-ABN-22-I-00010463.0005001 / 17 MAR 11
STATUS PFD BARO REF : STD ONLY • If in LAND or GA: CAT 2 ONLY
INOP SYS FCU 1 + 2 AP 1 + 2 A/THR
(1)
(2)
CAT 3 GPWS TERR
CAT 2
(1)
(If not LAND or GA) (If in LAND or GA mode)
(1) (2)
AUTO FLT REAC W/S DET FAULT Ident.: PRO-ABN-22-N-NG00766 Applicable to: ALL Ident.: PRO-ABN-22-N-00010473.0002001 / 05 AUG 10 L2
Crew awareness.
Ident.: PRO-ABN-22-N-00010474.0002001 / 05 AUG 10 L12
STATUS INOP SYS
Note:
REAC W/S DET
On ground, this warning may appear spuriously. This warning is cancelled by resetting both FACs, one after the other. ‐ FAC 1: Pull then push AUTO FLT/FAC 1/26VAC and 28VDC circuit breakers BO3 and B04 on 49VU. ‐ FAC 2: Pull then push AUTO FLT/FAC 2/26VAC and 28VDC circuit breakers M18 and M19 on 121VU.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← F to G
PRO-ABN-22 P 7/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
AUTO FLIGHT
FLIGHT CREW OPERATING MANUAL
AUTO FLT RUD TRIM 1(2) FAULT Ident.: PRO-ABN-22-C-NG00755 Applicable to: ALL Ident.: PRO-ABN-22-C-00010449.0001001 / 05 AUG 10 L2
Crew awareness.
Ident.: PRO-ABN-22-C-00010450.0001001 / 05 AUG 10
STATUS CAT 3 SINGLE ONLY
INOP SYS
CAT 3 DUAL RUD TRIM 1(2)
AUTO FLT RUD TRIM SYS Ident.: PRO-ABN-22-D-NG00756 Applicable to: ALL Ident.: PRO-ABN-22-D-00010451.0002001 / 05 AUG 10
FAC 1.......................................................................................................................... OFF THEN ON FAC 2.......................................................................................................................... OFF THEN ON Ident.: PRO-ABN-22-D-00010452.0002001 / 05 AUG 10
STATUS INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
H to I
RUD TRIM AP 1 + 2 CAT 2
PRO-ABN-22 P 8/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
AUTO FLIGHT
FLIGHT CREW OPERATING MANUAL
AUTO FLT RUD TRV LIM 1(2) Ident.: PRO-ABN-22-E-NG00757 Applicable to: ALL Ident.: PRO-ABN-22-E-00010453.0001001 / 05 AUG 10 L2
Crew awareness.
Ident.: PRO-ABN-22-E-00010454.0001001 / 05 AUG 10
STATUS INOP SYS
RUD TRV LIM 1(2)
AUTO FLT RUD TRV LIM SYS Ident.: PRO-ABN-22-F-NG00758 Applicable to: ALL Ident.: PRO-ABN-22-F-00010455.0008001 / 05 AUG 10
RUD WITH CARE ABV 160 KT Depending on when the failure occurs, the rudder travel limiter system may not be in the correct position for the flight speed. Therefore, to prevent damage to the aircraft structure, use the rudder with care, when the speed is greater than 160 kt. At slats’ extension, full rudder travel authority can be recovered. L1 FAC 1.......................................................................................................................... OFF THEN ON FAC 2.......................................................................................................................... OFF THEN ON If TLU (rudder or pedals) remains locked at high speed after slat extension: MAX X WIND FOR LDG 15 KT AUTO BRK..............................................................................................................DO NOT USE L2 Do not use the autobrake, so as not to delay the application of differential braking at landing roll. L2
L1
AT LDG ROLL: DIFF BRAKING............................................................................................................. AS RQRD Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
J to K →
PRO-ABN-22 P 9/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
AUTO FLIGHT
FLIGHT CREW OPERATING MANUAL
AUTO FLT RUD TRV LIM SYS (Cont'd) Ident.: PRO-ABN-22-F-00010456.0018001 / 16 NOV 11 L12
STATUS RUD WITH CARE ABV 160 KT • If TLU (rudder or pedals) remains locked at high speed after slat extension: MAX X WIND FOR LDG 15 KT AUTO BRK................................................. DO NOT USE Do not use the autobrake, so as not to delay the application of differential braking at landing roll. AT LDG ROLL: DIFF BRAKING.......................................... AS RQRD
INOP SYS RUD TRV LIM CAT 3 DUAL
CAT 3 SINGLE ONLY Note:
An autoland must not be performed with a crosswind greater than 12 kt. AUTO FLT YAW DAMPER 1(2)
Ident.: PRO-ABN-22-A-NG00753 Applicable to: ALL Ident.: PRO-ABN-22-A-00010444.0001001 / 05 AUG 10 L2
Crew awareness.
Ident.: PRO-ABN-22-A-00010445.0001001 / 05 AUG 10
STATUS CAT 3 SINGLE ONLY
INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← K to L
CAT 3 DUAL YAW DAMPER 1(2)
PRO-ABN-22 P 10/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
AUTO FLIGHT
FLIGHT CREW OPERATING MANUAL
AUTO FLT YAW DAMPER SYS Ident.: PRO-ABN-22-B-NG00754 Applicable to: ALL Ident.: PRO-ABN-22-B-00010446.0002001 / 05 AUG 10 L2 L1
Loss of yaw dampers 1 + 2. FAC 1.......................................................................................................................... OFF THEN ON FAC 2.......................................................................................................................... OFF THEN ON If fault remains:
L12
ASSOCIATED PROCEDURES
L2 L1
F/CTL ALTN LAW (PROT LOST) F/CTL normal laws are lost. All protections, except maneuver protections, are lost. MAX SPEED...................................................................................................................... 320 KT Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
M→
PRO-ABN-22 P 11/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
AUTO FLIGHT
FLIGHT CREW OPERATING MANUAL
AUTO FLT YAW DAMPER SYS (Cont'd) Ident.: PRO-ABN-22-B-00010447.0015001 / 11 MAY 12 L12
STATUS MAX SPEED................................................................ 320 KT Speed is limited, due to the loss of high-speed protections.
APPR PROC FOR LDG......................................................USE FLAP 3 This line is replaced by "FOR LDG : USE FLAP 3" when CONF 3 is selected, as a reminder. GPWS LDG FLAP 3.................................................... ON Will be displayed, when flaps in CONF 3. APPR SPD.................................................VREF + 10 KT LDG DIST PROC...................................................APPLY
INOP SYS F/CTL PROT YAW DAMPER AP 1 + 2 CAT 2
ALTN LAW : PROT LOST WHEN L/G DN : DIRECT LAW (1) See (1)
At landing gear extension, control reverts to direct law in pitch,as well as in roll Refer to FCOM-PRO-ABN-27 F/CTL DIRECT LAW.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←M
PRO-ABN-22 P 12/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
AUTO FLIGHT
FLIGHT CREW OPERATING MANUAL
LOSS OF FMS DATA IN DESCENT/APPROACH (SEVERE RESET) Ident.: PRO-ABN-22-00010476.0001001 / 14 NOV 11 Applicable to: ALL
AP/FD lateral and vertical selected modes, and A/THR, are available immediately after the reset. If necessary, the pilot may perform the FCU selections for short-term navigation. When the FMS has automatically recovered: ‐ The database cycle may have changed ‐ The FMGS does not autotune the ILS and ADF ‐ The FMS position bias is lost ‐ Lateral and vertical managed modes cannot re-engage ‐ The “CAB PR LDG ELEV FAULT” message is displayed on the ECAM ‐ A “MAP NOT AVAIL” message may be displayed on one ND. Depending on the flight phase, apply the following procedure(s) as appropriate: INITIAL APPROACH OR CLOSE TO ILS INTERCEPTION: When the system has recovered: Access the RAD NAV Page, and manually tune the ILS (preferably using Ident). Enter the ILS course, if a frequency has been entered. Fly in selected speed. Note:
‐ LOC and G/S guidance modes are available ‐ VLS speed is still available and displayed on the PFD ‐ Missed approach trajectory is not available.
DESCENT (IF TIME PERMITS) : When the system has recovered: Select the initial database Perform DIR TO a downpath waypoint. Select heading, if required. Perform a LAT REV at the downpath waypoint and redefine the DESTINATION in the NEW DEST field. Redefine the arrival and/or the approach procedure. Select the FUEL PRED Page, and enter the GW. Activate the APPROACH phase. Enter destination data on the PERF APPR Page, as required. Managed speed is available.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
N
PRO-ABN-22 P 13/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
AUTO FLIGHT
FLIGHT CREW OPERATING MANUAL
LOW ENERGY WARNING Ident.: PRO-ABN-22-00010475.0001001 / 05 AUG 10 Applicable to: ALL
The “SPEED SPEED SPEED” synthetic voice sounds every 5 s whenever the aircraft energy goes below a threshold under which thrust must be increased. “SPEED SPEED SPEED” Increase the thrust until the warning stops and, depending on the circumstances, adjust the pitch accordingly.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
O
PRO-ABN-22 P 14/14 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
COMMUNICATIONS
FLIGHT CREW OPERATING MANUAL
COM ACARS
FAULT
Ident.: PRO-ABN-23-B-NG00690 Applicable to: ALL Ident.: PRO-ABN-23-B-00010443.0001001 / 05 AUG 10
No crew action required. Ident.: PRO-ABN-23-B-00010037.0001001 / 05 AUG 10
STATUS INOP SYS
ACARS
COM CIDS 1 + 2 FAULT Ident.: PRO-ABN-23-A-NG00689 Applicable to: ALL Ident.: PRO-ABN-23-A-00010033.0001001 / 05 AUG 10 L2 L1
Passenger address, cabin and service interphone, and passenger signs are inoperative. Crew awareness
Ident.: PRO-ABN-23-A-00010034.0001001 / 05 AUG 10
STATUS INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
CIDS
PRO-ABN-23 P 1/4 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
COMMUNICATIONS
FLIGHT CREW OPERATING MANUAL
COM HF 1(2) DATA
FAULT
Ident.: PRO-ABN-23-F-NG00694 Applicable to: ALL Ident.: PRO-ABN-23-F-00010044.0001001 / 17 MAR 11 L2 L1
Triggered to indicate the loss of the HFs’ DATA mode. Crew awareness.
Ident.: PRO-ABN-23-F-00010045.0001001 / 17 MAR 11
STATUS INOP SYS
COM SATCOM DATA
HF 1(2) DATA
FAULT
Ident.: PRO-ABN-23-D-NG00692 Applicable to: ALL Ident.: PRO-ABN-23-D-00010040.0001001 / 17 MAR 11
Crew awareness. Ident.: PRO-ABN-23-D-00010041.0001001 / 17 MAR 11
STATUS INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C to D
SATCOM DATA
PRO-ABN-23 P 2/4 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
COMMUNICATIONS
FLIGHT CREW OPERATING MANUAL
COM SATCOM
FAULT
Ident.: PRO-ABN-23-C-NG00691 Applicable to: ALL Ident.: PRO-ABN-23-C-00010038.0002001 / 05 AUG 10 L2 L1
ACARS
and telephone communications are inoperative.
Crew awareness.
Ident.: PRO-ABN-23-C-00010039.0003001 / 05 AUG 10
STATUS INOP SYS
COM VHF 1(2)(3)/HF 1(2)
SATCOM
EMITTING
Ident.: PRO-ABN-23-00010035.0001001 / 05 AUG 10 Applicable to: ALL L2
1. If any Push To Talk (PTT) transmission selector (sidestick radio selector , hand mike selector , or PTT switch ) is jammed in the transmit position, try to release it in order to remove the caution. 2. If unsuccessful, deselect the identified failed VHF/HF transmission keys on the associated Audio Control Panel (ACP) to remove the caution. This ACP should only be used in reception mode. The associated PTT transmission selectors must not be used. Note:
In this case, the ACP of the unaffected side may be used to recover the deselected VHF/HF channel.
3. If no transmission key on the ACP is found in the “transmit” position, pull the affected VHF/HF C/B associated to the ECAM message : COM\HF1 C/B HA 14 on 49 VU, COM NAV\HF2 C/B L13 on 121 VU, COM\VHF\1 C/B G09 on 49 VU, COM NAV\VHF\2 C/B L04 on 121 VU, COM \VHF\3 C/B L05 on 121 VU.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E to F
PRO-ABN-23 P 3/4 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
COMMUNICATIONS
FLIGHT CREW OPERATING MANUAL
COM VHF 3 DATA
FAULT
Ident.: PRO-ABN-23-E-NG00693 Applicable to: ALL Ident.: PRO-ABN-23-E-00010042.0001001 / 17 MAR 11
Crew awareness. Ident.: PRO-ABN-23-E-00010043.0001001 / 17 MAR 11
STATUS INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
G
VHF 3 DATA
PRO-ABN-23 P 4/4 30 MAY 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
C/B TRIPPED Ident.: PRO-ABN-24-00012551.0001001 / 14 NOV 11 Applicable to: ALL L2
Crew awareness.
L1
If one green circuit breaker (C/B) is tripped, one of the following messages appears after one minute, depending on the location of the affected C/B: C/B TRIPPED ON OVHD PNL C/B TRIPPED ON L(R) ELEC BAY C/B TRIPPED REAR PNL J-M OR N-R OR S-V OR W-Z
L2
Note:
In flight, do not reengage a C/B that has tripped by itself, unless the Captain judges it necessary to do so for the safe continuation of the flight. This procedure should be adopted only as a last resort, and only one reengagement should be attempted. On ground, do not reengage the C/B of the fuel pump(s) of any tank. For all other C/Bs, if the flight crew coordinates the action with maintenance, the flight crew may reengage a tripped C/B, provided that the cause of the tripped C/B is identified.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PRO-ABN-24 P 1/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC AC BUS 1 FAULT Ident.: PRO-ABN-24-I-NG01097 Applicable to: ALL Ident.: PRO-ABN-24-I-00012498.0004001 / 27 JAN 12 L2
AC BUS 1 normally supplies the AC ESS BUS, and, via the TR1, the DC ESS BUS. In the case of an AC BUS 1 FAULT, the AC ESS BUS and the DC ESS BUS will automatically recover, due to the fact that the AC BUS 2 will automatically supply the AC ESS BUS. If AC BUS 2 does not automatically supply the AC ESS BUS, the flight crew can recover the AC ESS BUS and the DC ESS BUS by setting the AC ESS FEED pb-sw to ALTN, as requested by the AC ESS BUS FAULT ECAM procedure.
L1
BLOWER.................................................................................................................................... OVRD The avionics ventilation system is in the closed circuit configuration. Air conditioning is added to the ventilation air.
L2
L1
ASSOCIATED PROCEDURES WHEEL N.W. STEER FAULT SECONDARY FAILURES * AVNCS VENT * HYD * FUEL * F/CTL Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
PRO-ABN-24 P 2/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC AC BUS 1 FAULT (Cont'd) Ident.: PRO-ABN-24-I-00014139.0009001 / 11 MAY 12 L12
STATUS LDG DIST PROC...................................................APPLY
INOP SYS
SLATS SLOW CAT 2 ONLY
See below INOP SYS
BLUE HYD RA 1 L WNDW HEAT
SPLR 3 CAPT TAT CAT 3
ADR 3 L WSHLD HEAT L+R TK PUMP 1
CTR TK PUMP 1 CRG HEAT (if both FWD and aft crg heat installed)
VENT BLOWER
GALLEY FAN
CRG vent (if both FWD and aft crg heat installed)
AFT CRG HEAT
FWD CRG HEAT
AFT CRG VENT
FWD CRG VENT
GND COOL B ELEC PUMP GPWS
N.W. STEER
MAIN GALLEY
BRK SYS 1/BSCU CH 1 LAV DET
DMC 3
Other INOP SYS Left cabin fan
ADF 1
Stby Pitot/AOA
ACARS
Radar 1
HUD EVMU eng 1 and eng 2
MCDU 3 Printer
Engine 1 ignition B
Hydraulic quantity indication
Partial galley
PVI
/ATSU
Brake fans 5, 6, 7 and 8 COND Controller Lane A
TCAS
Note:
The warning may be caused by a sub BUS failure. Consequently, only a part of the above-listed systems may be lost.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
PRO-ABN-24 P 3/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC AC BUS 2 FAULT Ident.: PRO-ABN-24-J-NG01098 Applicable to: ALL Ident.: PRO-ABN-24-J-00012500.0001001 / 17 MAR 11
L2
EXTRACT................................................................................................................................... OVRD The avionics ventilation system is in the closed circuit configuration. Air conditioning is added to the ventilation air.
L1
ASSOCIATED PROCEDURES L/G LGCIU 2 FAULT SECONDARY FAILURES * AVNCS VENT * FUEL Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C→
PRO-ABN-24 P 4/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC AC BUS 2 FAULT (Cont'd) Ident.: PRO-ABN-24-J-00014116.0013001 / 16 NOV 11 L12
STATUS INOP SYS See below INOP SYS
ADR 2 FWC 2 R WSHLD HEAT F/O PITOT R WNDW HEAT
Y ELEC PUMP DMC 2 LGCIU 2 F/O AOA L+R TK PUMP 2
SDAC 2 RECORDER SYS (OR FDIU) RA 2 F/O TAT RUD TRV LIM 2
REVERSER 2
VENT EXTRACT
PACK 2 REGUL RUD TRIM 2
MAIN GALLEY FAC 2
GND COOL YAW DAMPER 2 VHF 2
CAT 2
CTR TK PUMP 2 ILS 2 (OR LS 2 for aircraft with MLS/GLS/FLS)
RBK SYS 2 OR (BSCU CH 2)
ACT PUMP GPS 2
Other INOP SYS Right cabin fan
Brake fans 1, 2, 3 and 4
ADF 2
DME 2
MCDU 2
ENG 2 ignition B
WXR 2 VOR 2
QAR
ECAM lower DU
HF 2
F/O PFD and ND
ATC 2
Note:
The warning may be caused by a sub BUS failure. Consequently, only a part of the above-listed systems may be lost.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C
PRO-ABN-24 P 5/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC AC ESS BUS ALTN (ON GROUND) Ident.: PRO-ABN-24-00012552.0002001 / 19 AUG 10 Applicable to: ALL L2
The AC ESS BUS is supplied from the AC BUS 2 although the AC ESS FEED pb-sw switch is set to normal. Crew awareness. ELEC AC ESS BUS FAULT
Ident.: PRO-ABN-24-K-NG01099 Applicable to: ALL Ident.: PRO-ABN-24-K-00012502.0001001 / 24 JAN 11
AC ESS FEED............................................................................................................................ ALTN AC BUS 2 supplies AC ESS BUS. L1 ATC............................................................................................................................................ SYS 2 L2
ASSOCIATED PROCEDURES AUTO FLT YAW DAMPER 1 ASSOCIATED PROCEDURES AUTO FLT RUD TRIM 1 FAULT ASSOCIATED PROCEDURES AUTO FLT RUD TRV LIM 1 Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D to E →
PRO-ABN-24 P 6/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC AC ESS BUS FAULT (Cont'd) Ident.: PRO-ABN-24-K-00012503.0025001 / 17 MAR 11 L12
STATUS INOP SYS See below INOP SYS
ADR 1 RUD TRIM 1 SDAC 1 GPWS FWC 1
ILS 1 RUD TRV LIM 1 CAPT PITOT GPWS terr DMC 1
GPS 1 CAT 2 CAPT AOA YAW DAMPER 1
Other INOP SYS RMP’s lighting (RMP’s still operative) CAPT ND CAPT PFD HF 1 Passenger oxygen masks (auto + manual)
Note:
VOR 1 CVR ATC 1 DDRMI
MCDU 1 ECAM upper display DME 1 APU fuel pump
ADF 1
The warning may be caused by a sub BUS failure. As a result, only a part of the above-listed systems may be lost. ELEC AC ESS BUS SHED
Ident.: PRO-ABN-24-L-NG01100 Applicable to: ALL Ident.: PRO-ABN-24-L-00012504.0001001 / 19 AUG 10
ATC............................................................................................................................................ SYS 2 Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← E to F →
PRO-ABN-24 P 7/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC AC ESS BUS SHED (Cont'd) Ident.: PRO-ABN-24-L-00012505.0004001 / 19 AUG 10 L12
STATUS INOP SYS CAPT AOA See below
Other INOP SYS
Note:
MCDU 1 CAPT ND CAPT AOA heat ADF 1 ATC 1 DME 1 CVR APU fuel pump Passenger oxygen masks (auto + manual) HF 1
The warning may be caused by a failure in a sub BUS. Consequently only a part of the systems listed above may be lost. ELEC APU GEN FAULT
Ident.: PRO-ABN-24-E-NG01093 Applicable to: ALL Ident.: PRO-ABN-24-E-00012490.0002001 / 18 MAR 11
APU GEN.................................................................................................................... OFF THEN ON IF UNSUCCESSFUL: APU GEN................................................................................................................................OFF Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← F to G →
PRO-ABN-24 P 8/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC APU GEN FAULT (Cont'd) Ident.: PRO-ABN-24-E-00012491.0001001 / 18 MAR 11
STATUS INOP SYS
(1)
MAIN GALLEY APU GEN
(1)
(When only one GEN operating) ELEC BAT 1(2) FAULT
Ident.: PRO-ABN-24-F-NG01094 Applicable to: ALL Ident.: PRO-ABN-24-F-00012492.0001001 / 19 AUG 10 L2
Battery contactor is opened automatically by battery charge limiter. Crew awareness
Ident.: PRO-ABN-24-F-00012493.0001001 / 19 AUG 10
STATUS APU BAT START NOT AVAIL
INOP SYS
BAT 1(2)
ELEC BAT 1(2) OFF Ident.: PRO-ABN-24-G-NG01095 Applicable to: ALL Ident.: PRO-ABN-24-G-00012494.0001001 / 19 AUG 10 L2
Battery is abnormally selected off. Crew awareness Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← G to I →
PRO-ABN-24 P 9/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC BAT 1(2) OFF (Cont'd) Ident.: PRO-ABN-24-G-00012495.0001001 / 19 AUG 10
STATUS APU BAT START NOT AVAIL
ELEC BCL 1(2) FAULT Ident.: PRO-ABN-24-H-NG01096 Applicable to: ALL Ident.: PRO-ABN-24-H-00012496.0001001 / 19 AUG 10 L2
Crew awareness
Ident.: PRO-ABN-24-H-00012497.0001001 / 19 AUG 10
STATUS APU BAT START NOT AVAIL
INOP SYS
BCL 1(2)
ELEC DC BAT BUS FAULT Ident.: PRO-ABN-24-W-NG01111 Applicable to: ALL Ident.: PRO-ABN-24-W-00012545.0001001 / 19 AUG 10 L2
Crew awareness. Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← I to K →
PRO-ABN-24 P 10/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC DC BAT BUS FAULT (Cont'd) Ident.: PRO-ABN-24-W-00012546.0009001 / 19 AUG 10 L12
STATUS APU BAT START NOT AVAIL ECB is no longer supplied
INOP SYS APU FIRE DET
Other INOP SYS APU ECB Stick and rudder pedals lock (by AP) Fwd (aft) cargo fire ext Fwd cargo heat controller Fwd cargo isol valves APU fuel LP valve Manual pressure control
Note:
The warning may be caused by a sub BUS failure. Consequently, only a part of the above-listed systems may be lost.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←K
PRO-ABN-24 P 11/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC DC BUS 1 FAULT Ident.: PRO-ABN-24-M-NG01101 Applicable to: ALL Ident.: PRO-ABN-24-M-00012507.0001001 / 30 MAR 12
BLOWER.................................................................................................................................... OVRD EXTRACT................................................................................................................................... OVRD L2 The Air conditioning system provides ventilation to the avionics. This ventilation air is exhausted overboard. L1
SECONDARY FAILURES *AVNCS VENT *FUEL
Ident.: PRO-ABN-24-M-00012508.0033001 / 14 NOV 11 L12
STATUS CAT 3 SINGLE ONLY
INOP SYS See below INOP SYS
ACP 3 L. WSHLD HEAT
CAPT STAT heat L. WNDW HEAT
STBY STAT heat CTR TK PUMP 1
AVNCS VENT
GALLEY FAN
REVERSER 1 CAT 3 DUAL
BRAKES SYS 1
GND COOL LAV DET
Other INOP SYS Left cab fan
COND controller lane A
Sel cal
CFDIU Hot air
VHF 3 Capt wiper
RMP 3 Eng 1 oil press and qty ind.
TPIS
Brake temps ind.
Note:
The warning may be caused by a sub BUS failure. Consequently, only a part of the above-listed systems may be lost.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
L
PRO-ABN-24 P 12/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC DC BUS 2 FAULT Ident.: PRO-ABN-24-N-NG01102 Applicable to: ALL Ident.: PRO-ABN-24-N-00012509.0003001 / 19 AUG 10
AIR DATA SWTG......................................................................................................................... F/O3 BARO REF...............................................................................................................................CHECK L2 Since one FCU channel is lost, crosscheck the barometer reference settings on the FCU and PFD. L1
SECONDARY FAILURES * CAB PRESS * FUEL * WHEEL * F/CTL Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
M→
PRO-ABN-24 P 13/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC DC BUS 2 FAULT (Cont'd) Ident.: PRO-ABN-24-N-00012510.0048001 / 11 MAY 12 L12
STATUS LDG DIST PROC...................................................APPLY
INOP SYS
ENG 2 APPR IDLE ONLY BOTH PFD ON SAME FAC SLATS/FLAPS SLOW CAT 3 SINGLE ONLY
See below
INOP SYS SPLR 1+2+5 VHF 2 REVERSER 2 FAC 2 ENG 1 LOOP B FCU 2 BRAKES SYS 2 R WNDW HEAT
(1)
ELAC 2 CTR TK PUMP 2 FCDC 2 L TK PUMP 2 ENG 2 LOOP A MAIN GALLEY F/O STAT CAB PR 2
SEC 2+3 LGCIU 2 CAT 3 DUAL R TK PUMP 2 AP 2 Y ELEC PUMP (if selected ON) R WSLHD HEAT
Other INOP SYS SFCC 2 F/O rain rplnt CDLS RMP 2
R cabin fan Eng 1 and 2 fire ext btl 2 BMC 2 FQI channel 2
F/O wiper FMGC 2 Bleed X feed auto control Autobrake (due to loss of 2 SECs)
Brake fan rudder trim ind
Eng 2 oil low press and qty ind
R loudspeaker
Note:
(1)
CIDS 2 SMOKE DETECT
The warning may be caused by a sub BUS failure. Consequently, only a part of the above-listed systems may be lost.
Lost after 30 s, but recovered at landing gear extension.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←M
PRO-ABN-24 P 14/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC DC BUS 1+2 FAULT Ident.: PRO-ABN-24-Q-NG01105 Applicable to: ALL Ident.: PRO-ABN-24-Q-00012515.0003001 / 18 MAR 11
BLOWER.................................................................................................................................... OVRD EXTRACT................................................................................................................................... OVRD BARO REF...............................................................................................................................CHECK L2 Crosscheck the barometer reference settings on the FCU and PFDs. L1 MAX BRK PR.......................................................................................................................1 000 PSI L2 Brake pressure must be limited to approximately 1 000 PSI, since antiskid is lost. L1
ASSOCIATED PROCEDURES ELEC DC BAT BUS FAULT SECONDARY FAILURES * CAB PRESS * FUEL * AIR COND * BRAKES * F/CTL Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
N→
PRO-ABN-24 P 15/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC DC BUS 1+2 FAULT (Cont'd) Ident.: PRO-ABN-24-Q-00012516.0022001 / 11 MAY 12 L12
STATUS MAX BRK PR............................................................1000 PSI LDG DIST PROC...................................................APPLY
INOP SYS See below
ENG 1 APPR IDLE ONLY ENG 2 APPR IDLE ONLY BOTH PFD ON SAME FAC CTR TK FUEL UNUSABLE APU BAT START NOT AVAIL CAB AT FIXED TEMP SLATS/FLAPS SLOW CAT 3 SINGLE ONLY INOP SYS SPLR 1+2+5 VHF 2 F/O STAT heat WNDW HEAT FCDC 2 ANTI SKID AUTO BRK CAB PRESS 2 GALLEY FAN Y ELEC PUMP APU FIRE DET ENG 2 LOOP A L TK PUMP 2
(1)
ELAC 2 ACP 3 STBY STAT heat AP 2 CAT 3 DUAL N.W. STEER LGCIU 2 AVNCS VENT
SEC 2+3
GND COOL BRAKE SYS 1 LAV DET PACK 2 R TK PUMP 2
MAIN GALLEY
CAPT STAT heat WSHLD HEAT FCU 2 FAC 2 NORM BRK REV 1+2 L+R CAB FAN BRAKE SYS 2 ENG 1 LOOP B COND CTL 2 CTR TK PUMPS
Other INOP SYS Selcal
Brake temp indication
TPIS
Capt and F/O wipers
Autobrake
Stick and rudder pedals lock (by AP)
Brake fans Eng 1 and 2 oil pressure and quantity indication VHF 3 Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←N→
PRO-ABN-24 P 16/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC DC BUS 1+2 FAULT (Cont'd) RMP 2 Right loudspeakers APU ECB Rudder trim indication Eng 1 and 2 fire ext btl 2
Note:
(1)
RMP 3 SFCC 2 Manual pressure control BMC 2 X Bleed auto control
CFDIU CDLS FMGC 2 FQI channel 2 CIDS 2 SMOKE DETECT
The warning may be caused by a failure in a sub BUS. Consequently, only a part of the above-listed systems may be lost.
Lost after 30 s, but is recovered at landing gear extension.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←N
PRO-ABN-24 P 17/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC DC EMER CONFIG Ident.: PRO-ABN-24-X-NG01112 Applicable to: ALL Ident.: PRO-ABN-24-X-00012547.0003001 / 15 MAY 12
LAND ASAP (AMBER) Triggered, if DC BUS 1, DC BUS 2 and DC ESS BUS are lost. In addition, DC BAT BUS is lost. EMER ELEC PWR.................................................................................................................MAN ON L2 The emergency generator supplies DC ESS BUS. But, DC BUS 1, DC BUS 2, and DC BAT BUS are still not supplied. L2 L1
L1
ASSOCIATED PROCEDURES ELEC DC BUS 1 + 2 FAULT BLOWER.................................................................................................................................... OVRD EXTRACT................................................................................................................................... OVRD BARO REF...............................................................................................................................CHECK L2 Crosscheck the barometer reference settings on the FCU and PFDs. L1 MAX BRK PR.......................................................................................................................1 000 PSI L2 Brake pressure must be limited to approximately 1 000 PSI, since antiskid is lost. L1
ASSOCIATED PROCEDURES ELEC DC BAT BUS FAULT
SECONDARY FAILURES * CAB PRESS * HYD * FUEL * AIR COND * BRAKES * WHEEL * F/CTL Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
O→
PRO-ABN-24 P 18/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC DC EMER CONFIG (Cont'd) Ident.: PRO-ABN-24-X-00012548.0022001 / 11 MAY 12 L12
STATUS MIN RAT SPEED......................................................... 140 KT PROC: GRVTY FUEL FEEDING MAX BRK PR.......................................................... 1 000 PSI FUEL GRVTY FEED LDG DIST PROC...................................................APPLY
INOP SYS See below
ENG 1 APPR IDLE ONLY ENG 2 APPR IDLE ONLY BOTH PFD ON SAME FAC CTR TK FUEL UNUSABLE APU BAT START NOT AVAIL CAB AT FIXED TEMP COCKPIT AT FIXED TEMP SLATS/FLAPS SLOW CAT 2 ONLY Note:
To verify the other INOP SYS not displayed on the ECAM, Refer to PRO-ABN-24-ELEC DC BUS 1+2 FAULT-FWSPAGE, Refer to PRO-ABN-24-ELEC DC BAT BUS FAULT-FWSPAGE. INOP SYS
FCU 2 FUEL PUMPS AUTO BRK BRAKES SYS 2 ENG 1 LOOP B
CAT 3 ANTI SKID Y ELEC PUMP APU FIRE DET L+R CAB FAN
FAC 2 NORM BRK BRAKES SYS 1 LAV DET FCDC 2
GALLEY FAN
CRG HEAT ACP 3 STBY STAT PACK 1 SPLR 1+2+5 VHF 2 REVERSER 2
GND COOL CAPT STAT WSHLD HEAT PACK 2 ELAC 2 N.W. STEER CAB PRESS 2 Continued on the following page
MAIN GALLEY F/O STAT WNDW HEAT COND CTL 1 SEC 2+3 LGCIU 2
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←O→
PRO-ABN-24 P 19/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC DC EMER CONFIG (Cont'd) AVNCS VENT AP 2
VENT BLOWER COND CTL 2
ENG 2 LOOP A
ELEC DC ESS BUS FAULT Ident.: PRO-ABN-24-O-NG01103 Applicable to: ALL Ident.: PRO-ABN-24-O-00012511.0001001 / 30 MAR 12
VHF 2 OR 3.................................................................................................................................. USE AUDIO SWTG.........................................................................................................................SELECT L2 ACP 1 and 2 are lost. Therefore, set the AUDIO SWTG rotary selector to CAPT 3 or F/O 3 to recover communications. L1 BARO REF...............................................................................................................................CHECK L2 Crosscheck the barometer reference settings on the FCU and the PFD. L1 GPWS............................................................................................................................................ OFF ASSOCIATED PROCEDURES NAV GPWS FAULT GPWS............................................................................................................................................ OFF L2
Note:
To shut down the engines on ground, use the ENG FIRE pb-sw.
L1
SECONDARY FAILURES * CAB PRESS * HYD * F/CTL Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← O to P →
PRO-ABN-24 P 20/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC DC ESS BUS FAULT (Cont'd) Ident.: PRO-ABN-24-O-00012512.0003001 / 11 MAY 12 L12
STATUS LDG DIST PROC...................................................APPLY
INOP SYS
ENG 1 APPR IDLE ONLY ENG 2 APPR IDLE ONLY BOTH PFD ON SAME FAC SLATS/FLAPS SLOW CAT 2 ONLY (1)
See below
INOP SYS B HYD ACP 1+2 A/THR R TK PUMP 1 ENG 2 START B ELEC PUMP ENG 2 LOOP B
SPLR 3 WING A. ICE FCU 1 FAC 1 CAB PR 1 GPWS FCDC 1
VHF 1 AP 1 L TK PUMP 1 REV 2 VENT EXTRACT ENG 1 LOOP A CAT 3
Other INOP SYS (1)
BRK PRESS indicator
Flight interphone
EIU 2
Capt rain repellent HP fuel shutoff valves Hyd fire valves Eng 1 and 2 Left loudspeaker
Avionics air cond valve
Standby compass light
SFCC 1 Ram air inlet DC SHED ESS BUS
RMP 1 ECAM Control Panel
Note:
(1)
1. Before arming the approach mode, the ECAM STATUS displays “CAT 3 SINGLE”. However, the real landing capability is CAT 2, and is correctly displayed on the FMA when the approach mode is armed. 2. The warning may be caused by a sub BUS failure. Consequently, only a part of the above-listed systems may be lost.
Autothrust, eng start and reverser inop.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←P
PRO-ABN-24 P 21/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC DC ESS BUS SHED Ident.: PRO-ABN-24-P-NG01104 Applicable to: ALL Ident.: PRO-ABN-24-P-00012513.0001001 / 30 MAR 12
EXTRACT................................................................................................................................... OVRD Cooling air is supplied by the air conditioning system, without overboard extraction. L1 AVOID ICING CONDITIONS SECONDARY FAILURES L2
*AVNCS VENT Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Q→
PRO-ABN-24 P 22/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC DC ESS BUS SHED (Cont'd) Ident.: PRO-ABN-24-P-00012514.0026001 / 11 MAY 12 L12
STATUS AVOID ICING CONDITIONS • IF SEVERE ICE ACCRETION MIN SPD................................................VLS + 10/G DOT MANEUVER WITH CARE LDG DIST PROC...................................................APPLY
INOP SYS WING A. ICE AP 1 CAT 3 DUAL FAC 1 VENT EXTRACT AFT CRG HEAT FWD CRG HEAT AFT CRG VENT FWD CRG VENT FCDC 1 See below
BOTH PFD ON SAME FAC CAT 3 SINGLE ONLY
Other INOP SYS Passenger oxygen mask (auto drop out) X BLEED valve man ctl CIDS 1 SMOKE DETECT STBY ALTI vib FMGC 1 BMC 1 FQ1 channel 1
Note:
The warning may be caused by a failure in a sub BUS. Consequently only a part of the systems listed above may be lost.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←Q
PRO-ABN-24 P 23/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC EMER CONFIG Ident.: PRO-ABN-24-R-NG01106 Applicable to: ALL Ident.: PRO-ABN-24-R-00012517.0009001 / 16 NOV 11
LAND ASAP MIN RAT SPEED......................................................................................................................140 KT CAUTION
The RAT is capable of supplying the EMER GEN down to 125 kt, except during flare.
GEN 1 + 2................................................................................................................... OFF THEN ON IF UNSUCCESSFUL: BUS TIE.................................................................................................................................. OFF L2 Setting BUS TIE pb-sw to OFF segregates both generator channels. L1 GEN 1 + 2.............................................................................................................OFF THEN ON L2
Note:
L1
EMER ELEC PWR (IF EMER GEN NOT IN LINE)........................................................ MAN ON ENG MODE SEL..................................................................................................................... IGN Engines are fed by gravity only.
L2 L1 L2
If any generator reset is successful, reset both FAC’s.
VHF1/HF1 /ATC1/...................................................................................................................USE Only VHF 1, HF 1 and ATC 1 are supplied in the electrical emergency configuration. Note:
FMGC 1, which is lost temporarily, can be regained by flight crew passing through the MCDU MENU page.
FUEL GRVTY FEED Engines are fed by gravity only. Avoid negative Gs. L1 PROC: GRVTY FUEL FEEDING L2 Apply GRVTY FUEL FEEDING procedure (Refer to PRO-ABN-28 GRVTY FUEL FEEDING). L1 FAC 1.......................................................................................................................... OFF THEN ON L2 The rudder trim is recovered, although no indication is available. L1 BUS TIE......................................................................................................................................AUTO L2 Setting BUS TIE pb-sw to AUTO enables the APU to take an available electrical channel. L1 APU (IF AVAIL)........................................................................................................................ START L2 APU start is not available for 45 s after the loss of both engine generators. This 45 s delay prevents any interference with emergency generator coupling. L1 L2
Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
R→
PRO-ABN-24 P 24/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC EMER CONFIG (Cont'd) If the APU is available, the APU may be started when below FL 250. BLOWER + EXTRACT...............................................................................................................OVRD L2 Cooling air is supplied by the air conditioning system and exhausted overboard through the extract valve. L1
L1 L2
Note:
On IAE powered aircraft, the warning “EPR MODE FAULT N1 DEGRADED MODE” is displayed.
L1
ASSOCIATED PROCEDURES FLT CTL ALTN LAW (PROT LOST) MAX SPEED.............................................................................................................................320 KT L2 Speed limited due to loss of flight control normal laws. Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←R→
PRO-ABN-24 P 25/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC EMER CONFIG (Cont'd) Ident.: PRO-ABN-24-R-00012518.0064001 / 14 MAY 12 L2
ECAM lower display is not available. STATUS page is displayed on the upper ECAM display, as long as the STS pb is pressed.
L12
STATUS MIN RAT SPEED......................................................... 140 KT MAX SPEED................................................................ 320 KT MAX BRK PR.......................................................... 1 000 PSI FUEL GRVTY FEED AVOID NEGATIVE G FACTOR Note:
If there are discrepancies between airspeed indications on the Captain’s PFD and on the STBY indicator, disregard the STBY indication (probe not deiced).
APPR PROC FOR LDG......................................................USE FLAP 3 This line is replaced by "FOR LDG: USE FLAP 3" when CONF 3 is selected, as a reminder. APPR SPD...........................................VREF +10/140 KT Approach speed must be at least minimum RAT speed (140 kt). LDG DIST PROC...................................................APPLY
INOP SYS F/CTL PROT REVERSER 1 + 2 ADR 2+3 IR 2 RA 1+2 SPLR 1+2+5 ELAC 2 SEC 2+3 A/CALL OUT AP 1+2 A/THR FUEL PUMPS ANTI SKID N/W STRG CAT 2
ALTN LAW: PROT LOST WHEN L/G DN: DIRECT LAW SLATS/FLAPS SLOW (1) See For other systems’ status: Refer to the “ELEC EMER CONFIG SYS REMAINING” table. (1)
Note:
In ELEC EMER configuration, the center tank fuel is unusable.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←R
PRO-ABN-24 P 26/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC EMER CONFIG SYS REMAINING Ident.: PRO-ABN-24-S-NG01107 Applicable to: ALL
ELEC EMER CONFIG SYS REMAINING
EMER GEN RUNNING
Ident.: PRO-ABN-24-S-00012521.0008001 / 16 NOV 11
AIR COND PRESS
PRESS AUTO SYS 1 MAN PRESS CTL RAM AIR PACK VALVE 1 PACK VALVE 2 AVIONIC VENT AFT CRG ISOL VALVES AFT CRG HEAT
NORM INOP NORM NORM Closure Inop NORM NORM NORM
NORM INOP NORM Closure Inop Closure Inop NORM INOP INOP
NORM INOP(a) NORM Closure Inop Closure Inop(a) Partial INOP INOP
FMGC (NAV FUNCTION) MCDU FAC FCU
N°1 only N°1 only N°1 only ch 1 only
Inop Inop Inop ch 1 only
Inop Inop Inop ch 1 only
VHF 1 HF 1 RMP 1 ACP (CAPT, F/O) CIDS INTERPHONE CVR LOUDSPEAKER 1
NORM NORM NORM NORM NORM NORM NORM NORM
NORM INOP NORM NORM NORM NORM INOP NORM
NORM INOP NORM NORM NORM NORM INOP NORM
CREW OXY PAX OXY mask release (auto + man) SLIDES ARM/WARN
NORM
NORM (b)
NORM (b)
NORM
INOP
INOP
NORM
NORM
Ident.: PRO-ABN-24-S-00012522.0001001 / 19 AUG 10
FMGS
Ident.: PRO-ABN-24-S-00012523.0003001 / 24 JAN 11
COM
Ident.: PRO-ABN-24-S-00012524.0001001 / 18 MAR 11
EMER EQPT
BAT ONLY ON THE GROUND
IN FLIGHT
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
S→
NORM Continued on the following page
PRO-ABN-24 P 27/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
Continued from the previous page L1
ELEC EMER CONFIG SYS REMAINING
EMER GEN RUNNING
Ident.: PRO-ABN-24-S-00012525.0002001 / 18 MAR 11
ENG 1 LOOP ENG 2 LOOP APU LOOP CARGO SMOKE DET ENG FIRE EXT. APU FIRE EXT. CARGO FIRE EXT. APU AUTO EXT.
BAT ONLY ON THE GROUND
IN FLIGHT
A only B only INOP Channel 1 Bottle 1 only Squib A only INOP INOP
A only B only INOP INOP Bottle 1 only Squib A only INOP INOP
A only B only INOP(a) INOP Bottle 1 only Squib A only INOP(a) INOP(a)
N°1 only N°1 only N°1 only N°1 only NORM
N°1 + 2 N°1 INOP N°1 only NORM
N°1 + 2 (d) N°1 (d) INOP N°1 only NORM (c)
LP VALVE FQI channel 1 X FEED VALVE TRANSFER VALVE
NORM NORM NORM NORM
NORM INOP INOP INOP
NORM INOP INOP INOP
HYD
FIRE VALVES
NORM
NORM
NORM
ICE-RAIN
WING A.ICE ENG A.ICE VALVE CAPT PITOT CAPT AOA RAIN REPELLENT (CAPT)
NORM OPEN NORM NORM NORM
INOP OPEN NORM INOP NORM
INOP OPEN NORM(e) INOP NORM
PFD 1 ND 1 ECAM upper disp. DMC 1 or 3 SDAC 1, FWC 1 ECAM CONT. panel CLOCKS
NORM NORM NORM NORM NORM NORM NORM
NORM INOP NORM NORM NORM NORM NORM
FIRE
Ident.: PRO-ABN-24-S-00012526.0002001 / 18 MAR 11
FLT CTL
ELAC SEC FCDC SFCC Flaps pos ind
Ident.: PRO-ABN-24-S-00012527.0001001 / 19 AUG 10
FUEL
Ident.: PRO-ABN-24-S-00012528.0001001 / 19 AUG 10 Ident.: PRO-ABN-24-S-00012529.0002001 / 18 MAR 11
Ident.: PRO-ABN-24-S-00012530.0002001 / 16 NOV 11
EIS
FLT INS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←S→
NORM (c) INOP NORM (c) NORM (c) NORM (c) NORM NORM Continued on the following page
PRO-ABN-24 P 28/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
Continued from the previous page L1
ELEC EMER CONFIG SYS REMAINING
EMER GEN RUNNING
Ident.: PRO-ABN-24-S-00012531.0011001 / 24 JAN 11
L/G
NORM NORM NORM NORM
NORM NORM NORM NORM
NORM NORM NORM NORM
EMER CKPT EMER CAB
NORM NORM
NORM NORM
NORM NORM
IR ADR ADF VOR-MMR DME VOR/DDRMI ATC ISIS
N°1 only (f) N°1 only N°1 only N°1 only N°1 only NORM N°1 only NORM
N°1 only (f) N°1 only INOP N°1 only INOP NORM INOP NORM
N°1 only (f) N°1 only INOP N°1 only (e) INOP NORM (e) INOP NORM
ENG 1 BLEED ENG 2 BLEED APU BLEED X BLEED (MAN CTL)
Norm BMC 2 inop Inop Norm
BMC 1 INOP BMC 2 inop Inop Inop
BMC 1 inop BMC 2 inop Inop(g) Inop
NORM(h) NORM NORM
INOP NORM NORM
INOP(a) NORM NORM
FADEC IGNITION HP FUEL VALVE closure
A+B (i) A only NORM
A+B (i) A only NORM
A+B (i) A only NORM
MECH HORN
NORM
NORM
NORM
Ident.: PRO-ABN-24-S-00012533.0012001 / 18 MAR 11
NAV
Ident.: PRO-ABN-24-S-00012534.0004001 / 18 MAR 11
PNEU
Ident.: PRO-ABN-24-S-00012535.0001001 / 18 MAR 11
APU
ECB-STARTER FUEL LP VALVE FUEL PUMP
Ident.: PRO-ABN-24-S-00012536.0006001 / 18 MAR 11
PWR PLT
Ident.: PRO-ABN-24-S-00012537.0001001 / 19 AUG 10
MISC (a) (b) (c) (d) (e)
BAT ONLY ON THE GROUND
LGCIU SYS 1 BRK PRESS IND PARK BRK ABCU
Ident.: PRO-ABN-24-S-00012532.0001001 / 19 AUG 10
LIGHTS
IN FLIGHT
Restored, when speed is below 100 kt. Crew oxygen valve inoperative. Lost, when the speed is below 50 kt. Lost, 30 s after the last engine shutdown. lost when speed below 50 kt
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←S→
PRO-ABN-24 P 29/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
(f) (g) (h) (i)
IR 2 and IR 3 are lost 5 min after failure of main generators but if IR 3 replaces IR 1 (ATT-HDG selector at CAPT 3), IR 3 remains supplied. Restored when speed below 100 kt For APU start only. channels A and B self powered above 12 % N2. If N2 below 12 % only channel A is powered.
ELEC EMER GEN 1 LINE OFF Ident.: PRO-ABN-24-00012550.0001001 / 24 JAN 11 Applicable to: ALL L2
With the GEN 1 LINE pb-sw (on the EMER ELEC PWR panel) in the OFF position, the GEN 1 line contactor is open and GEN 2 supplies the AC BUS 1 channel. Crew awareness. Set the GEN 1 LINE pb-sw to ON. ELEC ESS BUSES ON BAT
Ident.: PRO-ABN-24-00012520.0002001 / 19 AUG 10 Applicable to: ALL L2
DC ESS BUS is supplied by the batteries. AC ESS BUS is also supplied by the batteries, via the STATIC INVERTER. LAND ASAP
L1
MIN RAT SPEED......................................................................................................................140 KT Displayed, if the RAT is extended. L1 EMER ELEC PWR.................................................................................................................MAN ON L2 ESS BUSES are supplied by the emergency generator L2
ELEC ESS TR FAULT
Ident.: PRO-ABN-24-V-NG01110 Applicable to: ALL
1 Ident.: PRO-ABN-24-V-00012543.0002001 / 25 JUL 12
L2
Crew awareness. Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← S to V →
PRO-ABN-24 P 30/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC ESS TR FAULT (Cont'd)
2 Ident.: PRO-ABN-24-V-00012544.0002001 / 25 JUL 12
STATUS INOP SYS
ESS TR
ELEC GEN 1(2) OR APU GEN OVERLOAD Ident.: PRO-ABN-24-T-NG01108 Applicable to: ALL Ident.: PRO-ABN-24-T-00012538.0002001 / 19 AUG 10
GALY/CAB..................................................................................................................................... OFF Ident.: PRO-ABN-24-T-00012540.0002001 / 19 AUG 10
STATUS INOP SYS
GALY/CAB
ELEC GEN 1(2) FAULT Ident.: PRO-ABN-24-B-NG01090 Applicable to: ALL Ident.: PRO-ABN-24-B-00012484.0001001 / 19 AUG 10
GEN (AFFECTED).......................................................................................................OFF THEN ON IF UNSUCCESSFUL: GEN (AFFECTED)..................................................................................................................OFF Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← V to X →
PRO-ABN-24 P 31/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC GEN 1(2) FAULT (Cont'd) Ident.: PRO-ABN-24-B-00012485.0001001 / 19 AUG 10 L12
STATUS Note:
INOP SYS
If available, the APU may be started, and the APU GEN used.
CAT 3 SINGLE ONLY (1)
(only if APU GEN is not online)
MAIN GALLEY GEN 1(2) CAT 3 DUAL
(1)
ELEC GEN 1(2) OFF Ident.: PRO-ABN-24-C-NG01091 Applicable to: ALL Ident.: PRO-ABN-24-C-00012486.0001001 / 19 AUG 10 L2
Turn the affected GEN ON, with the applicable pushbutton. Crew awareness
Ident.: PRO-ABN-24-C-00012487.0001001 / 19 AUG 10
STATUS CAT 3 SINGLE ONLY
INOP SYS
(1)
MAIN GALLEY GEN 1(2) CAT 3 DUAL
(1)
(only if APU GEN is not online)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← X to Y
PRO-ABN-24 P 32/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC IDG 1(2) DISCONNECTED (ON GROUND) Ident.: PRO-ABN-24-D-NG01092 Applicable to: ALL Ident.: PRO-ABN-24-D-00012488.0003001 / 19 AUG 10 L2
Crew awareness
Ident.: PRO-ABN-24-D-00012489.0006001 / 19 AUG 10 L12
STATUS Note:
INOP SYS
If available, the APU may be started, and the APU GEN used.
CAT 3 SINGLE ONLY (1)
(only if APU GEN is not online)
MAIN GALLEY GEN 1(2) CAT 3 DUAL
(1)
ELEC IDG 1(2) OIL LO PR/OVHT Ident.: PRO-ABN-24-A-NG01089 Applicable to: ALL Ident.: PRO-ABN-24-A-00012482.0001001 / 16 NOV 11
L2
IDG (AFFECTED)..........................................................................................................................OFF If the associated engine is running, the IDG (integrated drive generator) must be disconnected from the engine at, or above, idle to prevent damage to the disconnect mechanism. Press the IDG pb-sw until the GEN FAULT light comes on. However, do not press for more than 3 s, to avoid damage to the disengage solenoid The IDG FAULT light goes off, when the IDG is disconnected. Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM Z to AA →
PRO-ABN-24 P 33/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
ELECTRICAL
FLIGHT CREW OPERATING MANUAL
ELEC IDG 1(2) OIL LO PR/OVHT (Cont'd) Ident.: PRO-ABN-24-A-00012483.0001001 / 24 JAN 11 L12
STATUS Note:
INOP SYS
If available, the APU may be started and the APU GEN used.
CAT 3 SINGLE ONLY (1)
(only if APU GEN is not online)
MAIN GALLEY GEN 1(2) CAT 3 DUAL
(1)
ELEC STAT INV FAULT Ident.: PRO-ABN-24-00012549.0001001 / 19 AUG 10 Applicable to: ALL L2
Crew awareness. ELEC TR 1(2) FAULT
Ident.: PRO-ABN-24-U-NG01109 Applicable to: ALL Ident.: PRO-ABN-24-U-00012541.0001001 / 19 AUG 10 L2
Crew awareness.
Ident.: PRO-ABN-24-U-00012542.0001001 / 18 MAR 11
STATUS CAT 3 SINGLE ONLY
INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← AA to AC
TR 1(2) CAT 3 DUAL
PRO-ABN-24 P 34/34 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
EQUIPMENT
FLIGHT CREW OPERATING MANUAL
COCKPIT DOOR FAULT Ident.: PRO-ABN-25-00009968.0003001 / 17 MAR 11 Applicable to: ALL
This procedure should be applied, if the Cockpit Door Locking System (CDLS) fails. This failure is indicated when the FAULT light on the center pedestal’s COCKPIT DOOR panel comes on. In the case of a DC BUS 2 fault, no FAULT indication appears on the center pedestal’s COCKPIT DOOR panel. The CDLS is not electrically-supplied, and is inoperative. CKPT DOOR CONT panel .....................................................................................................CHECK This panel is located on the overhead panel. It is used to identify the faulty CDLS item, and to verify the status of the pressure sensors and the three electrical latches (referred to as strikes). If one or more electrical latches (strikes) are faulty: The cockpit door is not intrusion-proof if two or more electrical latches are faulty. The system may be recovered by performing the following steps: Cockpit door.........................................................................................................................OPEN COCKPIT DOOR sw.......................................................................................... SET to UNLOCK After 30 s: COCKPIT DOOR sw.............................................................................................. SET to NORM If two pressure sensors are faulty: Automatic latch release is not available, in case of cockpit decompression. If no LED on the CKPT DOOR CONT panel is on: The CDLS control unit is faulty, therefore, the cockpit door might unlock automatically. If it does not, consider using the mechanical override system to unlock the door.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PRO-ABN-25 P 1/2 03 APR 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
EQUIPMENT
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PRO-ABN-25 P 2/2 03 APR 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
APU FIRE Ident.: PRO-ABN-26-C-NG01038 Applicable to: ALL Ident.: PRO-ABN-26-C-00012209.0002001 / 16 NOV 11
LAND ASAP APU FIRE P/B............................................................................................................................ PUSH APU LP valve closes. Aural warning stops. APU FIRE pb-sw remains on, as long as a fire is detected. L1 AGENT AFTER 10 S................................................................................................................ DISCH L2 The 10 s delay allows the airflow to decrease, which increases the effect of the agent. Automatic countdown on the ECAM. L1 MASTER SW.................................................................................................................................OFF L2 Do not attempt to restart the APU. L2
Ident.: PRO-ABN-26-C-00012211.0001001 / 16 NOV 11
STATUS INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
APU
PRO-ABN-26 P 1/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
ENG 1(2) FIRE (IN FLIGHT) Ident.: PRO-ABN-26-00012208.0002001 / 18 APR 12 Applicable to: ALL
LAND ASAP THR LEVER (AFFECTED)...........................................................................................................IDLE ENG MASTER (AFFECTED)........................................................................................................ OFF L2 LP and HP valves close. L1 ENG FIRE P/B (AFFECTED)..................................................................................................... PUSH L2 Aural warning stops. ENG FIRE pushbutton remains on, as long as a fire is detected. FADEC is no longer supplied. So, the THR LEVER ... IDLE line reappears, even if the thrust lever is at idle. L1 AGENT 1 AFTER 10 S............................................................................................................. DISCH L2 The 10 s delay allows N1 to decrease, reducing nacelle ventilation, and thereby increasing the effect of the agent. Automatic countdown on the ECAM. L1 ATC..........................................................................................................................................NOTIFY L2 Notify ATC of the nature of the emergency, and state intentions L1
IF FIRE AFTER 30 S: AGENT 2.............................................................................................................................DISCH Discharge the second agent, if the fire warning remains 30 s after the discharge of the first agent.
L2
L12
ASSOCIATED PROCEDURES ENG 1(2) SHUTDOWN Do not attempt to restart the engine. For the ENG SHUTDOWN procedure, see the ENG section. (Refer to PRO-ABN-70 ENG 1(2) SHUT DOWN).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
PRO-ABN-26 P 2/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
ENG 1(2) FIRE (ON GROUND) Ident.: PRO-ABN-26-00012207.0004001 / 04 MAY 12 Applicable to: ALL
L2 L1
L2
L1
L2 L1 L2
L1
L2
THR LEVERS............................................................................................................................... IDLE Full reverse may be used to stop the aircraft. WHEN A/C IS STOPPED: PARKING BRK......................................................................................................................... ON ATC (VHF 1).....................................................................................................................NOTIFY Notify ATC of the nature of the emergency, and state intensions. Only VHF 1 is available on batteries. CABIN CREW (PA)............................................................................................................ ALERT ENG MASTER (AFFECTED)..................................................................................................OFF Associated LP and HP valves close. ENG FIRE P/B (AFFECTED)...............................................................................................PUSH Aural warning stops. ENG FIRE pushbutton remains on, as long as fire is detected. FADEC is no longer supplied. AGENT 1+2.........................................................................................................................DISCH EMER EVAC PROC...........................................................................................................APPLY Refer to PRO-ABN-80 EMERGENCY EVACUATION or Refer to QRH/ABN-80 EMERGENCY EVACUATION ENG 1(2)/APU FIRE DET FAULT
Ident.: PRO-ABN-26-B-NG01037 Applicable to: ALL Ident.: PRO-ABN-26-B-00012204.0001001 / 18 AUG 10 L2
Loss of both fire detection loops. Crew awareness. Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C to D →
PRO-ABN-26 P 3/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
ENG 1(2)/APU FIRE DET FAULT (Cont'd) Ident.: PRO-ABN-26-B-00012205.0001001 / 18 AUG 10
STATUS INOP SYS
FIRE DET 1(2) or APU FIRE DET
ENG 1(2)/APU FIRE LOOP A(B) FAULT Ident.: PRO-ABN-26-A-NG01036 Applicable to: ALL Ident.: PRO-ABN-26-A-00012202.0001001 / 12 JAN 11 L2
No crew action required in flight.
Ident.: PRO-ABN-26-A-00012203.0001001 / 18 AUG 10
STATUS INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← D to E
ENG 1(2) LOOP A(B) or APU LOOP A(B)
PRO-ABN-26 P 4/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
SMOKE FWD(AFT) CARGO SMOKE Ident.: PRO-ABN-26-E-NG01040 Applicable to: ALL Ident.: PRO-ABN-26-E-00012219.0091001 / 16 NOV 11
LAND ASAP AFT ISOL VALVE (IF NOT AUTOMATICALLY CLOSED AND AFT AFFECTED)....................... OFF CAB FANS.....................................................................................................................................OFF IF FWD (AFT) CRG CLOSED (displayed on ground only): L2
L1
Order the ground crew not to open the door of the affected cargo compartment, unless the passengers have disembarked and fire services are present. Also ensure that the FWD(AFT) cargo door is closed before discharging the extinguishing agent. AGENT................................................................................................................................ DISCH
L2
Note:
L1
ON GROUND BEFORE OPEN CRG DOORS: PAX........................................................................................................................... DISEMBARK
L2
Note:
Expect the SMOKE warning to remain after agent discharge, even if the smoke source is extinguished. Gases from the smoke source are not evacuated, and smoke detectors are also sensitive to the extinguishing agent.
If the warning has been displayed temporarily, and agent has not been discharged, normal cargo ventilation may be recovered when ventilation is required for livestock transportation: C/B of CARGO VENT controller (S20 on 122VU, or C7 on 49VU, as installed) ...... PULL then PUSH
Ident.: PRO-ABN-26-E-00012221.0011001 / 17 MAR 11
STATUS BEFORE OPEN CRG DOORS (displayed on ground only): PAX........................................................ DISEMBARK
INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F
AFT CRG VENT AFT CRG HEAT affected)
(If aft
PRO-ABN-26 P 5/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
SMOKE FWD(AFT) CRG BTL (1)(2
) FAULT
Ident.: PRO-ABN-26-00012224.0013001 / 29 MAR 12 Applicable to: ALL L2
If bottle 1 is lost, fire extinguishing capability is lost in the FWD(AFT) cargo compartment. If bottle 2 is lost, agent concentration will not be ensured after fire extinguishing. Crew awareness. SMOKE FWD(AFT) CRG DET FAULT
Ident.: PRO-ABN-26-F-NG01041 Applicable to: ALL Ident.: PRO-ABN-26-F-00012553.0005001 / 18 AUG 10
IF NO LIVE STOCK: AFT ISOL VALVE (IF AFT AFFECTED)................................................................................ OFF Ident.: PRO-ABN-26-F-00012377.0005001 / 18 AUG 10
STATUS INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
G to H
FWD(AFT) CRG DET
PRO-ABN-26 P 6/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
SMOKE/FUMES/AVNCS SMOKE Ident.: PRO-ABN-26-D-NG01039 Applicable to: ALL Ident.: PRO-ABN-26-D-00012212.0004001 / 19 JUN 12 1
This procedure includes all the steps of the AVIONICS SMOKE ECAM procedure. Apply this procedure when: ‐ The flight (cabin) crew suspect that smoke is coming from the avionics, and/or the air conditioning, and/or the cabin equipment. ‐ Requested by the AVIONICS SMOKE ECAM procedure. ‐ There is a smell of smoke/fumes in the cockpit : • If the smell is similar to that of orange peels, suspect a toxic leak of rain repellent fluid. • If the smell is similar to that of pine needles, suspect a non-toxic leak. If any other ECAM SMOKE alert triggers (CARGO, ...), the crew must first apply the ECAM procedure, then consider applying this procedure. Note that these ECAM alerts may be caused by another source, that should usually first be detected by the flight crew/cabin crew/avionics smoke detectors. The following explains the layout of this procedure: ‐ The procedure lines above the text boxes indicate the actions that the flight crew must immediately perform, if smoke is detected (with or without ECAM activation and regardless of the smoke source). These immediate actions correspond to the most common steps to be taken in smoke cases. In all cases, the flight crew must also be prepared to immediately perform a diversion. However, this diversion may be avoided if the smoke source is obvious, accessible and extinguishable or confirmed isolated (after completion of the immediate actions). ‐ The text boxes indicate the actions that the flight crew must consider, if at any time during the remainder of the procedure but always after the initial steps: • Smoke/fumes become the greatest threat and smoke/fumes removal is required, and/or • The situation becomes critical and can no longer be controlled. ‐ The procedure lines below the text boxes indicate the actions that the flight crew must perform, as soon as they suspect a source of smoke. The actions will depend on whether the smoke is coming from the avionics, and/or air conditioning, and/or cabin equipment. LAND ASAP IF PERCEPTIBLE SMOKE APPLY IMMEDIATELY: If smoke is confirmed, the following procedure must be applied. BLOWER..............................................................................................................................OVRD EXTRACT............................................................................................................................ OVRD
Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
I→
PRO-ABN-26 P 7/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
SMOKE/FUMES/AVNCS SMOKE (Cont'd) Avionics ventilation air is extracted overboard. CAB FANS.............................................................................................................................. OFF To prevent smoke from entering the cockpit and cabin. GALY & CAB.......................................................................................................................... OFF SIGNS....................................................................................................................................... ON CKPT/CABIN COM.....................................................................................................ESTABLISH Communication must be established with the cabin crew in order to follow up on the smoke origin and dissipation. If required: OXY MASK/GOGGLE...................................................................................... ON/100%/EMERG Ensure crew communication is established. Avoid continuous use of the interphone to minimize interference from the oxygen mask breathing noise. Turn the emergency knob to remove condensation or smoke from the mask. If smoke source immediately obvious, accessible, and extinguishable: FAULTY EQPT............................................................................................................... ISOLATE If smoke source not immediately isolated: DIVERSION..................................................................................................................... INITIATE DESCENT (FL 100, or MEA, or minimum obstacle clearance altitude).......................... INITIATE At ANY TIME of the remainder of the procedure, if smoke/fumes becomes the GREATEST THREAT: SMOKE FUMES REMOVAL......................................................................................CONSIDER ELEC EMER CONFIG...............................................................................................CONSIDER Refer to PRO ABN 26 SMOKE/FUMES/AVNCS SMOKE - ELEC EMER CONFIG At ANY TIME of the procedure, if situation becomes critical and can no longer be controlled: IMMEDIATE LANDING.............................................................................................. CONSIDER Guidelines to determine smoke source: ‐ If smoke initially comes out of the ventilation outlets, the crew may suspect AIR COND SMOKE. In addition, very shortly thereafter, several SMOKE warnings (cargo, lavatory, avionics) will be triggered. The displayed ECAM procedures must be applied.
Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←I→
PRO-ABN-26 P 8/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
SMOKE/FUMES/AVNCS SMOKE (Cont'd) ‐ After an ENG or APU failure, smoke may come from the faulty item via the bleed system and be perceived in the cockpit and/or cabin. In such a case, it will be recirculated throughout the aircraft, until it completely disappears from the air conditioning system. ‐ If only the AVIONICS SMOKE warning is triggered, the crew may suspect avionics smoke. ‐ If the smoke is detected while an equipment is declared faulty, the crew may suspect that smoke is coming from this equipment. ‐ Avionics or forward galley smoke may be smelt, or may enter in the cockpit before ECAM warning activation. Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←I→
PRO-ABN-26 P 9/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
SMOKE/FUMES/AVNCS SMOKE (Cont'd) Ident.: PRO-ABN-26-D-00012214.0007001 / 17 MAR 11
IF AIR COND SMOKE SUSPECTED: APU BLEED............................................................................................................................OFF BLOWER and EXTRACT.....................................................................................................AUTO Note:
When both BLOWER and EXTRACT are in the OVRD position, a single pack may not be able to maintain the cabin pressure.
CARGO AFT ISOL VALVE.....................................................................................................OFF To prevent a cargo smoke warning from being triggered due to cabin smoke. PACK 1................................................................................................................................... OFF If smoke continues: PACK 1.............................................................................................................................. ON PACK 2.............................................................................................................................OFF If smoke still continues: PACK 2........................................................................................................................ON Restore normal configuration if PACK 2 is not suspected to cause smoke BLOWER and EXTRACT....................................................................................... OVRD SMOKE/FUMES REMOVAL....................................................................................... CONSIDER IF CAB EQUIPMENT SMOKE SUSPECTED: If smoke continues: EMER EXIT LIGHT............................................................................................................ ON COMMERCIAL..................................................................................................................OFF SMOKE DISSIPATION............................................................................................... CHECK FAULTY EQPT......................................................................................... SEARCH/ISOLATE Once the cabin has been secured, try to find the smoke source and isolate it. Cabin lights, reading lights, passenger systems, galleys have dedicated control C/B in the cabin or cockpit. If smoke still continues or if faulty equipment confirmed isolated: COMMERCIAL....................................................................................................... NORM SMOKE/FUMES REMOVAL.................................................................................CONSIDER At any time of the procedure, consider applying the SMOKE/FUMES REMOVAL procedure. Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←I→
PRO-ABN-26 P 10/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
SMOKE/FUMES/AVNCS SMOKE (Cont'd) Ident.: PRO-ABN-26-D-00012215.0001001 / 18 AUG 10
IF SMOKE SOURCE CANNOT BE DETERMINED AND STILL CONTINUES OR AVNCS/ELECTRICAL SMOKE SUSPECTED: ELEC EMER CONFIG................................................................................................ CONSIDER As a last attempt, the flight crew can set the electrical emergency configuration to possibly isolate or minimize the smoke source. IF SMOKE disappears within 5 min: NORMAL VENTILATION.............................................................................................. RESTORE Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←I→
PRO-ABN-26 P 11/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
SMOKE/FUMES/AVNCS SMOKE (Cont'd) Ident.: PRO-ABN-26-D-00012565.0019001 / 14 MAY 12
TO SET EMER ELEC CONFIG EMER ELEC GEN 1 LIN.......................................................................................................... OFF GEN 1 LINE contactor opens. GEN 1 remains running and supplies one fuel pump in each wing tank. AC BUS 1 is supplied by GEN 2 through the bus tie contactor. EMER ELEC PWR.............................................................................................................MAN ON RAT is extended and the EMER GEN is connected to the aircraft network. Check emergency generator parameters on the ELEC SD page (displayed automatically). WHEN EMER GEN AVAIL: APU GEN............................................................................................................................OFF GEN 2................................................................................................................................. OFF ELEC EMER CONFIG Two different procedures can be displayed on the ECAM, depending on whether the AVIONICS SMOKE ECAM caution is triggered or not before the flight crew sets the electrical emergency configuration. If AVIONICS SMOKE is not triggered: The ECAM displays the ELEC EMER CONFIG procedure described here: Refer to PRO-ABN-24 ELEC EMER CONFIG. The flight crew must apply the ECAM without performing the GEN 1+2 reset. AT 3 MIN OR 2000 FT BEFORE LDG: Restore all generators only 3 min before landing or at 2 000 ft AAL to recover normal braking, while minimizing possible reactivation of a smoke source. GEN 2...................................................................................................................... ON EMER ELEC GEN 1 LINE...................................................................................... ON WHEN A/C IS STOPPED: ALL GEN................................................................................................................OFF If AVIONICS SMOKE is triggered: The ECAM displays a specific ELEC EMER CONFIG procedure. The flight crew must apply the following ECAM procedure. MIN RAT SPEED.....................................................................................................140 KT
Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←I→
PRO-ABN-26 P 12/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
SMOKE/FUMES/AVNCS SMOKE (Cont'd) Note:
The electrical configuration is the same as for loss of both generators (except that one fuel pump in each wing tank remains supplied).
VHF 1/HF 1/ATC 1.......................................................................................................USE Only VHF 1, HF 1 and ATC 1 are supplied in this configuration. Notify the ATC of the nature of the emergency, and state intentions. If there is no contact with the ATC, switch to code A7700, or transmit a distress message on one of the following frequencies: VHF 121.5 MHz, HF 2 182 kHz, or 8 364 kHz. FAC 1......................................................................................................... OFF THEN ON Rudder trim is recovered, despite the fact that no indication is available. 3MN/2000 FT BEFORE LDG: Restore all generators only 3 min before landing or at 2 000 ft AAL to recover normal braking, while minimizing possible reactivation of a smoke source. GEN 2...................................................................................................................... ON EMER ELEC GEN 1 LIN.........................................................................................ON F/CTL ALTN LAW (PROT LOST) Flight control normal laws and associated protections are lost. Only the load factor limitation, and the high and low speed stability remain (ALTN law with reduced protection). MAX SPEED............................................................................................................320 KT Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←I→
PRO-ABN-26 P 13/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
SMOKE/FUMES/AVNCS SMOKE (Cont'd) Ident.: PRO-ABN-26-D-00012217.0024001 / 11 MAY 12
ECAM lower display is not available. STATUS SD page is displayed on the upper ECAM display, as long as the STATUS pb is pressed. STATUS MIN RAT SPEED......................................................... 140 KT MAX SPEED................................................................ 320 KT MAX BRK PR............................................................1000 PSI FOR LDG................................................... USE FLAPS 3 GPWS LDG FLAP 3.................................................... ON APPR SPD..................................................VREF +10 KT LDG DIST PROC...................................................APPLY ENG 1+2 APPR IDLE ONLY ENG 1+2 N1 DEGRADED MODE (IAE-powered aircraft ) ALTN LAW: PROT LOST WHEN L/G DN: DIRECT LAW CTR TK FUEL UNUSABLE INCREASED FUEL CONSUMP SLATS/FLAPS SLOW After recovery of normal electrical supply, the following STATUS will be displayed: MAX SPEED................................................... 320 KT APPR SPD........................................... VREF +10 KT LDG DIST PROC............................................ APPLY
INOP SYS Refer to PRO-ABN-24-ELEC EMER CONFIG SYS REMAINING-21-AIR CONDITIONING/VENTILATION /PRESSURIZATION ELEC EMER CONFIG SYS REMAINING (except for fuel pumps).
APPR PROC 3 MN/2000 FT BEFORE LDG: GEN 2....................................................................ON EMER ELEC GEN 1 LINE.....................................ON WHEN A/C IS STOPPED: ALL GEN..............................................................OFF ALTN LAW: PROT LOST (1) See 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Continued on the following page
←I→
PRO-ABN-26 P 14/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
SMOKE/FUMES/AVNCS SMOKE (Cont'd) WHEN L/G DN: DIRECT LAW (2) See (1) (2)
Flight controls remain in alternate law, due to the loss of IR 2 and 3. At landing gear extension, control reverts to direct law in pitch, as well as in roll (Refer to PRO-ABN-F/CTL DIRECT LAW).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←I
PRO-ABN-26 P 15/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
SMOKE/FUMES REMOVAL Ident.: PRO-ABN-26-00012218.0003001 / 18 AUG 10 Applicable to: ALL
Apply the SMOKE/FUMES REMOVAL paper procedure, if smoke/fumes become the greatest threat when applying the SMOKE/FUMES/AVNICS SMOKE paper procedure. EMER EXIT LIGHT.......................................................................................................................... on If fuel vapors: CAB FANS................................................................................................................................ON The recirculating air ventilates the air mixer bay and other fuselage area. This prevents fuel vapors from accumulating and the risk of explosion. Passenger health is not affected. PACK 1+2............................................................................................................................... OFF If no fuel vapors: CAB FANS.............................................................................................................................. OFF To prevent smoke from entering the cockpit and cabin. PACK FLOW.............................................................................................................................. HI To provide maximum airflow from the packs. Do not shut down the air conditioning packs, and do not reduce ventilation in an attempt to smother the fire. Do not deploy oxygen masks, if fire is suspected in the cabin. LDG ELEV....................................................................................................................10000 FT/MEA DESCENT (FL 100, or MEA, or minimum obstacle clearance altitude)................................ INITIATE The most effective means of smoke removal is use of ram air. Therefore, descent is initiated to FL 100 or the MEA, or the minimum obstacle clearance altitude, while the cabin altitude is increased to 10 000 ft or the MEA. The increase in cabin altitude also reduces, at least temporarily, the smoke concentration. Cabin depressurization starts, when descent is initiated. Passenger oxygen, as required by regulation. ATC..........................................................................................................................................NOTIFY SMOKE/FUMES/AVNCS SMOKE PROC..........................................................................CONTINUE While descending, continue applying the appropriate steps of the SMOKE/FUMES/AVNCS SMOKE procedure depending on the suspected smoke source. At FL100, or MEA: APU MASTER SW (if in ELEC EMER CONFIG).....................................................................ON
Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
J→
PRO-ABN-26 P 16/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
SMOKE/FUMES REMOVAL (Cont'd) In electrical emergency configuration, when the APU MASTER pb-sw is ON, the battery contactors will automatically close for a maximum of 3 min . This will enable the flight crew to manually control the outflow valve that is powered by the DC BAT BUS. PACKS 1+2.............................................................................................................................OFF MODE SEL.............................................................................................................................MAN MAN V/S CTL................................................................................................................. FULL UP RAM AIR...................................................................................................................................ON At FL 100, or MEA, or minimum obstacle clearance altitude, it is possible to open the RAM AIR valve when ΔP is 1 PSI or below. Opening the RAM AIR enables flying with both packs OFF. APU MASTER SW..................................................................................................................OFF If smoke persists, open CKPT window: If there is smoke in the cockpit, open the cockpit (CKPT) window to evacuate the smoke. MAX SPEED................................................................................................................200 KT COCKPIT DOOR...........................................................................................................OPEN HEADSETS........................................................................................................................ ON PNF COCKPIT WINDOW............................................................................................. OPEN When window is open: NON-AFFECTED PACK(s)..........................................................................................ON VISUAL WARNINGS (noisy CKPT).................................................................MONITOR Due to the increased noise level, pay particular attention to visual warnings. SMOKE/FUMES/AVNCS SMOKE PROC...................................................... CONTINUE Continue applying the appropriate steps of the SMOKE/FUMES/AVNCS SMOKE paper procedure depending on the suspected smoke source. SMOKE DET FAULT Ident.: PRO-ABN-26-G-NG01042 Applicable to: ALL Ident.: PRO-ABN-26-G-00012225.0038001 / 17 MAR 11
IF NO LIVE STOCK: AFT ISOL VALVE................................................................................................................... OFF PAX SYS
............................................................................................................................... OFF Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← J to K →
PRO-ABN-26 P 17/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FIRE PROTECTION
FLIGHT CREW OPERATING MANUAL
SMOKE DET FAULT (Cont'd) Ident.: PRO-ABN-26-G-00012226.0011001 / 01 APR 11
STATUS INOP SYS
SMOKE DET
SMOKE LAVATORY DET FAULT Ident.: PRO-ABN-26-H-NG01043 Applicable to: ALL Ident.: PRO-ABN-26-H-00012229.0001001 / 18 AUG 10 L2 L1
Toilet smoke detection is lost. Crew awareness.
Ident.: PRO-ABN-26-H-00012228.0001001 / 18 AUG 10
STATUS INOP SYS
LAV DET
SMOKE LAVATORY SMOKE Ident.: PRO-ABN-26-00012227.0007001 / 18 AUG 10 Applicable to: ALL L2
Communication must be established with the cabin crew in order to follow up on the smoke origin and dissipation. Consider applying the SMOKE/FUMES/AVNCS SMOKE paper procedure.
L1
CKPT/CAB COM...............................................................................................................ESTABLISH
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← K to M
PRO-ABN-26 P 18/18 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FLIGHT CONTROLS
FLIGHT CREW OPERATING MANUAL
CONFIG L (R) SIDESTICK FAULT BY TAKE OVER Ident.: PRO-ABN-27-00011772.0001001 / 18 AUG 10 Applicable to: ALL
The warning is triggered, when on the ground, if either stick is inoperative (takeover pushbutton pressed more than 30 s). L1 L (R) TAKEOVER .............................................................................................................. DEPRESS L2 The affected stick becomes operative. L2
CONFIG PITCH TRIM NOT IN T.O RANGE Ident.: PRO-ABN-27-00011773.0001001 / 18 AUG 10 Applicable to: ALL
Crew Awareness. CONFIG RUD TRIM NOT IN T.O RANGE Ident.: PRO-ABN-27-00011776.0001001 / 18 AUG 10 Applicable to: ALL L2
Crew awareness CONFIG SLATS (FLAPS) NOT IN T.O CONFIG
Ident.: PRO-ABN-27-00011758.0001001 / 16 NOV 11 Applicable to: ALL L2
Crew awareness. Config SPD BRK NOT RETRACTED
Ident.: PRO-ABN-27-00011766.0001001 / 18 AUG 10 Applicable to: ALL L2
Crew awareness.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to E
PRO-ABN-27 P 1/36 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FLIGHT CONTROLS
FLIGHT CREW OPERATING MANUAL
F/CTL AIL SERVO FAULT Ident.: PRO-ABN-27-00011781.0002001 / 18 AUG 10 Applicable to: ALL L2
Crew awareness F/CTL ALTN LAW
Ident.: PRO-ABN-27-K-NG00967 Applicable to: ALL Ident.: PRO-ABN-27-K-00011774.0001001 / 18 AUG 10
Refer to PRO-SUP-27-10 General for flight characteristics. With autopilot engaged the FMGC (AP mode) controls the aircraft. L1 (PROT LOST) L2 All protections, except maneuver protections, are lost. Depending on the failure, static stability may be introduced. L2
L1
Note:
In case of GPWS (EGPWS ) alerts, since protections are lost, respect stall warnings when applying the GPWS (EGPWS ) procedure.
MAX SPEED.............................................................................................................................320 KT (320/.77 if dual hydraulic system low pressure). Speed is limited to 320 /.82 or 320/.77 for dual hydraulic failure, due to the loss of high-speed protection. L1 SPD BRK (IF L OR R ELEVATOR FAULT) .................................................................DO NOT USE L2
Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F to G →
PRO-ABN-27 P 2/36 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FLIGHT CONTROLS
FLIGHT CREW OPERATING MANUAL
F/CTL ALTN LAW (Cont'd) Ident.: PRO-ABN-27-K-00011775.0006001 / 11 MAY 12 L12
STATUS MAX SPEED................................................................ 320 KT (320/.77, if dual hydraulic system low pressure). SPD BRK (IF L OR R ELEVATOR FAULT)....... DO NOT USE
INOP SYS F/CTL PROT
APPR PROC FOR LDG......................................................USE FLAP 3 This line is replaced by “FOR LDG : USE FLAP 3” when CONF 3 is selected, as a reminder. GPWS LDG FLAP 3 ................................................... ON APPR SPD ........................................................VREF+10 LDG DIST PROC ..................................................APPLY •
•
If no AP engaged: WHEN L/G DN: DIRECT LAW At landing gear extension, control reverts to direct law in pitch, as well as in roll. Refer to PRO-ABN-27-F/CTL DIRECT LAW If AP engaged: WHEN L/G DN AND AP OFF: DIRECT LAW
If the autopilot is disengaged: ‐ Before landing gear extension, flight control alternate law is active. ‐ After landing gear extension, flight control direct law is active. Refer to PRO-ABN-27-F/CTL DIRECT LAW ALTN LAW: PROT LOST
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G
PRO-ABN-27 P 3/36 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FLIGHT CONTROLS
FLIGHT CREW OPERATING MANUAL
F/CTL DIRECT LAW Ident.: PRO-ABN-27-J-NG00966 Applicable to: ALL Ident.: PRO-ABN-27-J-00011770.0001001 / 14 NOV 11
L1
PFD displays « USE MAN PITCH TRIM » in amber. Refer to PRO-SUP-27-50 Aircraft Trimming (PROT LOST)
L2
Note:
L2
In case of GPWS ( EGPWS ) alerts, since protections are lost, respect stall warning when applying the GPWS (EGPWS ) procedure.
MAX SPEED.............................................................................................................................320/.77 Speed is limited, due to the loss of high-speed protection. Do not exceed M 0.77, so as not to degrade handling qualities. L1 MAN PITCH TRIM (EXCEPT IF HYD Y + G SYS LO PR).......................................................... USE L2 Automatic trim is inoperative in direct law. L1 MANEUVER WITH CARE L2 Use small control inputs at high speed, since in direct law the controls are powerful. Use of manual thrust is recommended. Avoid large thrust changes. L1 USE SPD BRK WITH CARE L2 At high Mach numbers, use speed brakes with care to avoid too strong nose up changes. L1 L2
Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
H→
PRO-ABN-27 P 4/36 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FLIGHT CONTROLS
FLIGHT CREW OPERATING MANUAL
F/CTL DIRECT LAW (Cont'd) Ident.: PRO-ABN-27-J-00011771.0006001 / 11 MAY 12 L12
STATUS MAX SPEED................................................................ 320/.77 MANEUVER WITH CARE USE SPD BRK WITH CARE
INOP SYS
F/CTL PROT
APPR PROC FOR LDG................................................... USE FLAPS 3 This line is replaced by “FOR LDG : USE FLAP 3” when CONF 3 is selected, as a reminder. GPWS LDG FLAP 3.................................................... ON MAN PITCH TRIM..................................................... USE APPR SPD.........................................................VREF+10 LDG DIST PROC...................................................APPLY DIRECT LAW
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H
PRO-ABN-27 P 5/36 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FLIGHT CONTROLS
FLIGHT CREW OPERATING MANUAL
F/CTL ELAC 1(2) FAULT (ONE COMPUTER FAILED) Ident.: PRO-ABN-27-F-NG00962 Applicable to: ALL Ident.: PRO-ABN-27-F-00011759.0002001 / 14 NOV 11
CAUTION
Do not reset ELAC, if uncommanded maneuvers occurred during the flight.
ELAC (AFFECTED)..................................................................................................... OFF THEN ON L2
L1
L2
Note:
1. In some sidestick transducer failure cases, ELAC 1(2) FAULT is triggered without the procedure, and FAULT It on associated pb does not come on. 2. If the ELAC 1 computer is reset on ground the pitch trim returns to the ground setting position (0 °).
IF UNSUCCESSFUL: ELAC (AFFECTED)................................................................................................................ OFF Functions are performed by the other ELAC. LAF is degraded (A320 with LAF only)
Ident.: PRO-ABN-27-F-00011760.0001001 / 18 AUG 10
STATUS CAT 3 SINGLE ONLY
INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
I
ELAC 1(2) CAT 3 DUAL
PRO-ABN-27 P 6/36 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FLIGHT CONTROLS
FLIGHT CREW OPERATING MANUAL
F/CTL ELAC 1 (2) FAULT (BOTH COMPUTERS FAILED) Ident.: PRO-ABN-27-G-NG00963 Applicable to: ALL Ident.: PRO-ABN-27-G-00011761.0001001 / 18 AUG 10
ELAC 1........................................................................................................................ OFF THEN ON L2
Note:
If the ELAC 1 computer is reset on ground, the pitch trim returns to the ground setting position (0 °).
L1
ELAC 2........................................................................................................................ OFF THEN ON If both ELAC FAULT remain: ELAC 1....................................................................................................................................OFF ELAC 2....................................................................................................................................OFF ASSOCIATED PROCEDURES F/CTL ALTN LAW (PROT LOST)
L2
L1
Pitch and roll normal laws are lost: Refer to PRO-ABN-27-K F/CTL ALTN LAW. THS motor 1 and both ailerons are lost. LAF is degraded and uses spoilers only (A320 only). MAX SPEED...................................................................................................................... 320 KT Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
J→
PRO-ABN-27 P 7/36 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FLIGHT CONTROLS
FLIGHT CREW OPERATING MANUAL
F/CTL ELAC 1 (2) FAULT (Cont'd) (BOTH COMPUTERS FAILED) Ident.: PRO-ABN-27-G-00011762.0003001 / 11 MAY 12 L12
STATUS MAX SPEED................................................................ 320 KT
APPR PROC FOR LDG......................................................USE FLAP 3 Do not select CONF FULL, so as not to degrade handling qualities. GPWS LDG FLAP 3.................................................... ON Will be displayed when flaps in CONF 3 APPR SPD................................................... VREF+10 KT LDG DIST PROC...................................................APPLY
INOP SYS F/CTL PROT L+R AIL ELAC 1+2 AP 1+2 CAT 2
ALTN LAW: PROT LOST WHEN L/G DOWN: DIRECT LAW (1) See (1)
At landing gear extension, control reverts to direct law in pitch, as well as in roll (Refer to PRO-ABN-27-J F/CTL DIRECT LAW). F/CTL ELAC 1 (2) PITCH FAULT
Ident.: PRO-ABN-27-H-NG00964 Applicable to: ALL Ident.: PRO-ABN-27-H-00011763.0001001 / 18 AUG 10 L2
Pitch function is achieved by the other ELAC. Crew awareness Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← J to K →
PRO-ABN-27 P 8/36 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FLIGHT CONTROLS
FLIGHT CREW OPERATING MANUAL
F/CTL ELAC 1 (2) PITCH FAULT (Cont'd) Ident.: PRO-ABN-27-H-00011765.0001001 / 18 AUG 10
STATUS CAT 3 SINGLE ONLY
INOP SYS
(1)
ELAC PITCH CAT 3 DUAL
(1)
(If ELAC 1 and 2 PITCH FAULT) F/CTL ELEV SERVO FAULT
Ident.: PRO-ABN-27-P-NG00972 Applicable to: ALL Ident.: PRO-ABN-27-P-00011786.0001001 / 18 AUG 10 L2
The remaining servojack controls the elevator.
L1 L2
Crew awareness
L1
CAUTION
Do not use speedbrakes above 350 kt/M 0.82 (VMO/MMO).
Ident.: PRO-ABN-27-P-00011787.0001001 / 18 AUG 10
STATUS CAT 3 SINGLE ONLY
INOP SYS
CAT 3 DUAL
F/CTL FCDC 1 (2) FAULT Ident.: PRO-ABN-27-L-NG00968 Applicable to: ALL Ident.: PRO-ABN-27-L-00011777.0001001 / 18 AUG 10 L2
Crew awareness Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← K to M →
PRO-ABN-27 P 9/36 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FLIGHT CONTROLS
FLIGHT CREW OPERATING MANUAL
F/CTL FCDC 1 (2) FAULT (Cont'd) Ident.: PRO-ABN-27-L-00011778.0001001 / 18 AUG 10
STATUS INOP SYS
FCDC 1(2)
F/CTL FCDC 1+2 FAULT Ident.: PRO-ABN-27-M-NG00969 Applicable to: ALL Ident.: PRO-ABN-27-M-00011779.0001001 / 18 AUG 10
L2
MONITOR F/CTL OVHD PNL F/CTL data on ECAM is lost. Control laws remains normal. Note:
When both FCDCs fails: ‐ F/CTL warning are not available on the ECAM. ‐ Stall warning may be triggered as in alternate or direct law (it may occur at speeds greater than Vα max). ‐ Bank and pitch limits are no longer displayed on the PFD. ‐ Vα prot, Vα max are lost on the PFD. ‐ Vsw, displayed on the PFD, corresponds to the stall warning of the alternate or direct law.
Ident.: PRO-ABN-27-M-00011780.0001001 / 18 AUG 10
STATUS F/CTL INDICATIONS LOST
INOP SYS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← M to N
FCDC 1 + 2
PRO-ABN-27 P 10/36 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FLIGHT CONTROLS
FLIGHT CREW OPERATING MANUAL
F/CTL FLAP ATTACH SENSOR Ident.: PRO-ABN-27-00011757.0001001 / 18 AUG 10 Applicable to: ALL L2
Failure of flap attachment failure detection sensor. Crew awareness F/CTL FLAP LVR NOT ZERO
Ident.: PRO-ABN-27-00011809.0004001 / 18 AUG 10 Applicable to: ALL L2 L1
The flap lever is not in the zero position, and the aircraft is above 22 000 ft. Crew awareness. F/CTL FLAP SYS 1(2) FAULT
Ident.: PRO-ABN-27-E-NG00961 Applicable to: ALL Ident.: PRO-ABN-27-E-00011753.0001001 / 18 AUG 10
If FLAP sys 1 fault: GPWS FLAP MODE...............................................................................................................OFF Ident.: PRO-ABN-27-E-00011754.0001001 / 18 AUG 10
STATUS ENG 1(2) APPR IDLE ONLY FLAPS SLOW
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
O to Q
PRO-ABN-27 P 11/36 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FLIGHT CONTROLS
FLIGHT CREW OPERATING MANUAL
F/CTL FLAPS FAULT/LOCKED Ident.: PRO-ABN-27-A-NG00957 Applicable to: ALL Ident.: PRO-ABN-27-A-00011744.0001001 / 14 NOV 11
L2 L1 L2
If flaps locked: WING TIP BRK ON OR ALIGNMENT FAULT MAX SPEED......................... REFER TO PRO-ABN-27 F/CTL FLAPS/SLATS FAULT/LOCKED Limit speed to the VFE corresponding to the next flap position FLAPS LEVER (IF FLAPS NOT LOCKED).................................................................. RECYCLE Return to the previous selection, then back to the desired position. If unsuccessful: Refer to PRO-ABN-10 Landing with Slats or Flaps Jammed . The autopilot may be used down to 500 ft AGL. As it is not tuned for abnormal configurations, its behavior can be less than optimum and must be monitored. Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
R→
PRO-ABN-27 P 12/36 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FLIGHT CONTROLS
FLIGHT CREW OPERATING MANUAL
F/CTL FLAPS FAULT/LOCKED (Cont'd) Ident.: PRO-ABN-27-A-00011745.0008001 / 11 MAY 12 L12
STATUS
APPR PROC
INOP SYS
FOR LDG (IF FLAPS ≤ 3)............................ USE FLAP 3 This line is replaced by “FOR LDG : USE FLAP 3” when CONF 3 is selected, as a reminder FLAPS (IF FLAPS>3)......................... KEEP CONF FULL GPWS FLAP MODE (IF FLAPS < 3)......................... OFF GPWS LDG FLAP 3 (IF FLAPS ≥ 3)........................... ON APPR SPD............................................................ REFER TO PRO-ABN-27 F/CTL FLAPS/SLATS FAULT/LOCKED LDG DIST PROC...................................................APPLY
FLAPS AP 1+2 A/THR
(1)
(1)
Moreover, both FDs are lost CAT 2
(1)
(1)
ENG 1 APPR IDLE ONLY (Only in case of FLAPS FAULT) ENG 2 APPR IDLE ONLY (Only in case of FLAPS FAULT) INCREASED FUEL CONSUMP (Refer to PRO-ABN-27 F/CTL FLAPS/SLATS FAULT/LOCKED) (1)
(If both flap channels fault.)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←R
PRO-ABN-27 P 13/36 18 SEP 12
PROCEDURES ABNORMAL AND EMERGENCY PROCEDURES A318/A319/A320/A321
FLIGHT CONTROLS
FLIGHT CREW OPERATING MANUAL
F/CTL FLAPS/SLATS FAULT/LOCKED Ident.: PRO-ABN-27-00011748.0001001 / 06 APR 12 Applicable to: ALL
(1)
MAX SPEED Flaps(1) F = 0 0 3 t (6 600 lb): Use FU parameter to determine both FOB and FU • When FOB < 3 t (6 600 lb): Use FOB parameter to determine both FOB and FU OPERATIONAL CONSIDERATIONS Some economic aspects relating to FQI accuracy are approached here and should be considered when operating an aircraft. TECHNICAL DELAYS Incorrect application of MMI check, may cause a possible delay. Knowing the FQI calibration curve helps to understand and reduce discrepancies.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB7 P 6/8 25 NOV 11
FLIGHT CREW BULLETINS FQI ACCURACY A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EXTRA FUEL LOADED ‐ Crews uplift more fuel than required for a particular flight, as a contingency factor, when they are unsure of the FQI accuracy. ‐ An under-reading FQI leads also to carrying extra fuel. ‐ 1 extra tonne will increase fuel consumption up to 1.2 %, depending on airframe and flight conditions. PAYLOAD PENALTY Extra fuel loaded due to uncertainty of FQI may lead to decreasing the payload. Payload = TOW + TAXI fuel - OEW - Fuel loaded TOW = Take-Off Weight OEW = Operating Empty Weight We have seen, that adding 130 kg (286 lb) of fuel can allow the payload to be increased by 870 kg (1 914 lb) on a 4 h flight. ‐ When the payload is limited by MTOW as TOW cannot be increased, any extra fuel will decrease and replace payload by the same amount. Also, any defueling will significantly decrease the payload. ‐ When the payload is limited by the max fuel capacity: • If the FQI under-reads, the payload could be increased • If the FQI over-reads, the payload should be decreased. For example, an inaccuracy of ± 130 kg (286 lb) on fuel can affect the payload by ± 870 kg(1 914 lb). Again, knowing your FQI calibration curve allows to adjust the payload. Note:
Although not approved by DGAC/JAA as it is a non compliance item, using the 2 % thermal expansion volume as extra-fuel could be authorized by national airworthiness authorities to increase max fuel capacity. In this case the FQI reading is limited somewhere above high level until fuel quantity falls below this value.
CONCLUSION Airbus Industrie has always improved FQI systems, because it is essential for crews to have a reliable and accurate fuel quantity indication system. Taking into account the difficulty of measuring the weight of a liquid stored in complex-shaped tanks always moving, FQI system installed on Airbus aircraft has a good accuracy, well within specifications and international standards. It is important on certain flights with certain aircraft fitted with a FQI system presenting large over-/underreadings, to know the particular FQI ground calibration curve. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB7 P 7/8 25 NOV 11
FLIGHT CREW BULLETINS FQI ACCURACY A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Crews should know this curve and FQI tolerances in order to: ‐ Understand and reduce FQI discrepancies ‐ Avoid delays ‐ Save fuel ‐ Adjust the payload. FQI calibration should be done when deemed necessary by each operator as this will be profitable for both operational and economic aspects.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
FCB-FCB7 P 8/8 25 NOV 11
FLIGHT CREW BULLETINS ELECTRONIC INTERFERENCE FROM PORTABLE EQUIPMENT CARRIED ON BY PASSENGERS
Intentionally left blank
FLIGHT CREW BULLETINS
A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ELECTRONIC INTERFERENCE FROM PORTABLE EQUIPMENT CARRIED ON BY PASSENGERS PRELIMINARY PAGES - TABLE OF CONTENTS
FCB-FCB8-PLP PRELIMINARY PAGES TABLE OF CONTENTS Electronic Interference from Portable Equipment carried on by Passengers..........................................................A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB8-PLP-TOC P 1/2 29 JUL 11
FLIGHT CREW BULLETINS
A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ELECTRONIC INTERFERENCE FROM PORTABLE EQUIPMENT CARRIED ON BY PASSENGERS PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB8-PLP-TOC P 2/2 29 JUL 11
FLIGHT CREW BULLETINS
A318/A319/A320/A321
ELECTRONIC INTERFERENCE FROM PORTABLE EQUIPMENT CARRIED ON BY PASSENGERS
FLIGHT CREW OPERATING MANUAL
ELECTRONIC INTERFERENCE FROM PORTABLE EQUIPMENT CARRIED ON BY PASSENGERS Ident.: FCB-FCB8-00013108.0001001 / 02 MAR 11 Applicable to: ALL
‐ Airlines often wonder whether they should allow passengers to operate electronic devices in the cabin without any limit. Federal Aviation Regulation (FAR) section 91.19 allows passengers to operate: • Portable voice recorders • Hearing aids • Heart pacemakers • Electric shavers • Any other portable electronic device that the operator of the aircraft has determined will not cause interference with the navigation or communication system of the aircraft on which it is to be used.
‐ ‐
‐
‐
It is obvious that the myriad portable devices that now exists or that may be available in the future cannot be tested. As far as aircraft specific electrical flight controls and engine control computers on Airbus aircraft are concerned, there is no chance of their operation being affected by passenger-operated electronic devices, due to the high level of protection applied to these systems. Nevertheless, this question arises for navigation and communication receivers and is applicable to any aircraft. A study has been conducted by an RTCA (Radio Technical Commission for Aeronautics) special commitee. The conclusion is that the probability of a passenger-operated device interfering with the ILS localizer during a typical flight is about one in a million. Airbus Industrie recommendations is that no portable device should be used during take-off and landing. Concerning radio phones Airbus Industrie recommends to prohibit the use of those devices.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
FCB-FCB8 P 1/2 29 JUL 11
FLIGHT CREW BULLETINS
A318/A319/A320/A321
ELECTRONIC INTERFERENCE FROM PORTABLE EQUIPMENT CARRIED ON BY PASSENGERS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB8 P 2/2 29 JUL 11
FLIGHT CREW BULLETINS THRUST ACCELERATION IN A/THR MODES
Intentionally left blank
FLIGHT CREW BULLETINS THRUST ACCELERATION IN A/THR MODES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
FCB-FCB9-PLP PRELIMINARY PAGES TABLE OF CONTENTS Thrust Acceleration in A/THR Modes......................................................................................................................A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB9-PLP-TOC P 1/2 29 JUL 11
FLIGHT CREW BULLETINS THRUST ACCELERATION IN A/THR MODES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB9-PLP-TOC P 2/2 29 JUL 11
FLIGHT CREW BULLETINS THRUST ACCELERATION IN A/THR MODES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
THRUST ACCELERATION IN A/THR MODES Ident.: FCB-FCB9-00013109.0001001 / 02 MAR 11 Applicable to: ALL
These are specific thrust acceleration logics when A/THR is engaged in thrust or speed mode. The crew should be aware of each. The purpose of the logic is to obtain adapted thrust variation to the whole flight envelope, depending on the current mode engaged, "G" load limitation, and vertical modes switching if any. This is based on different logics which can be summarized as following. 1. LOGIC IN THRUST MODE "CLB" (ASSOCIATED WITH OP CLB/EXP CLB/CLB) 1.1 WHEN AP IS ENGAGED During thrust increased, the maximum acceleration rate is 20 %/sec until the N1 reaches N1 target minus 5 %. At that point, the acceleration logic is speed mode. This acceleration limit is defined to achieve a smooth and rapid transition without noticeable speed excursion. However normal acceleration rate is between 1.5 %/sec and 20 %/sec. When target N1 minus 5 % is reached, N1 rate becomes 1.5 %/sec until target N1 (MAX CLB Thrust) is obtained. Note:
When decelerating (more than 10 kt between current speed and speed target), the N1 rate is maintained at 1.5 %/sec.
1.2 WHEN AP IS OFF It has been revealed, that during manual flying with AP off, the rate limit up to 20 %/sec was not as optimum as with AP engaged. The reason for this is that during transition the system was using A/THR speed mode logic to obtain N1 rate limit of 20 %/sec MAX; if the pilot did not fly the FD bars, established CLB thrust was not always obtained. Consequently, the current system maintains the fixed value of 1.5 %/sec which represents the best value when following the FD bars. Flight tests proved this logic (it means to provide maximum rate of 20 %/sec only if autopilot is engaged) to be the optimum compromise through the flight envelope. WARNING
If FD bar commands are not smoothly followed or not followed at all, a speed excursion may occur, due to the fact that the change of attitude is not adapted to the thrust acceleration rate. If required, additional manual thrust may be briefly added by the pilot during the transition.
2. LOGIC IN THRUST MODE "IDLE" (ASSOCIATED WITH OP DES/EXP DES/DES) The N1 rate limit is 2 %/sec (lS8) and 1 %/sec (full standard). Both rates were selected to preclude speed excursion and improve passenger comfort (smooth attitude variation during transition). 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
FCB-FCB9 P 1/2 29 JUL 11
FLIGHT CREW BULLETINS THRUST ACCELERATION IN A/THR MODES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
3. LOGIC IN SPEED MODE The N1 rate limit is 20 %/sec MAX, however it can be lower depending upon the difference between the current speed and the target speed. There is no difference in A/THR speed mode linked to AP ON or OFF. The speed hold is the same with AP ON or OFF. When pilot is flying manually, a temporary speed loss can occur if an increased load factor is required. This authority is not possible with AP due to system.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
FCB-FCB9 P 2/2 29 JUL 11
FLIGHT CREW BULLETINS RADIO ALTIMETER ANOMALIES DURING ADVERSE WEATHER CONDITIONS
Intentionally left blank
FLIGHT CREW BULLETINS
A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
RADIO ALTIMETER ANOMALIES DURING ADVERSE WEATHER CONDITIONS PRELIMINARY PAGES - TABLE OF CONTENTS
FCB-FCB11-PLP PRELIMINARY PAGES TABLE OF CONTENTS Radio Altimeter Anomalies during Adverse Weather Conditions............................................................................ A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB11-PLP-TOC P 1/2 29 JUL 11
FLIGHT CREW BULLETINS
A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
RADIO ALTIMETER ANOMALIES DURING ADVERSE WEATHER CONDITIONS PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB11-PLP-TOC P 2/2 29 JUL 11
FLIGHT CREW BULLETINS
A318/A319/A320/A321
RADIO ALTIMETER ANOMALIES DURING ADVERSE WEATHER CONDITIONS
FLIGHT CREW OPERATING MANUAL
RADIO ALTIMETER ANOMALIES DURING ADVERSE WEATHER CONDITIONS Ident.: FCB-FCB11-00013111.0001001 / 02 MAR 11 Applicable to: ALL
INTRODUCTION All radio altimeters are very sensitive to adverse weather conditions. Reflections from hail clouds or heavy precipitation located between the ground and the aircraft, may cause the radio altimeter to indicate a false height value momentarily. These erroneous indications are also transmitted to other systems which may induce spurious warnings or unexpected AP/FD guidance. EXAMPLE
Under heavy rain condition at 2 600 ft, at least one of the radio altimeter delivered a height indication of 480 ft during 13 s. The warning "L/G gear not down" was displayed. No other anomaly was reported until landing.
EXPLANATION ORIGIN A radio altimeter measures the shortest distance between the aircraft and the closest obstacles below it. During adverse weather conditions, returns can be generated due to reflection on hail clouds or heavy rain. The energy which is reflected depends directly upon the hail or rain density. If the energy received by the radio altimeter is powerful enough, it will be validated and a height lower than the distance to the ground will be measured and sent to system users. If the return is too weak, the measurement will be validated but the increased noise level may hide the return from the ground and thus no height indication would be provided. CHARACTERISTICS This phenomenon is rare. Typical weather conditions which trigger these effects are not frequent and generally isolated. It is less likely with increased height. Due to the physical nature of the hail and rain and the radio altimeter characteristics, the radio altimeter indication will only be influenced if the distance between the A/C and the clouds is equal or greater than 300 ft for rain and 80 ft for hail. Both radio altimeters are likely to be affected simultaneously.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
FCB-FCB11 P 1/2 29 JUL 11
FLIGHT CREW BULLETINS
RADIO ALTIMETER ANOMALIES DURING ADVERSE WEATHER CONDITIONS
A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
OPERATIONAL CONSIDERATIONS If both radio altimeters are affected simultaneously the crew may experience: ‐ If the value is greater than 150 ft: • Spurious auto call out • Spurious ECAM or GPWS warnings. ‐ If the value ranges between 150 ft and 80 ft: • During automatic approach: ▪ Degradation of the guidance, glide slope is no longer flown, excessive deviation may occur ▪ Variation of the longitudinal pitch and/or vertical speed leading to GPWS warning. • During manual approach: ▪ No adverse effect could be reproduced during simulation but GPWS or auto call out warning might be spuriously triggered. CONCLUSION AND OPERATIONAL RECOMMENDATIONS Very few cases of spurious radio altimeter indications have been reported to Airbus. Radio altimeter sensitivity issues have been tuned to the limits of improvement. There is no practical solution to cure the phenomenon without reducing system performance to an unsatisfactory level. Crews need to be aware that erroneous radio altimeter behavior is rare, but can occur during severe weather conditions. During approach and landing, crews need to consider this phenomenon. The weather radar may be used to detect heavy rain or hail. The interpretation of the color codes is as follows: Black rainfall rate Green rainfall rate Yellow rainfall rate Red rainfall rate
less than between between greater than
0.7 mm/hr 0.7 and 4 mm/hr 4 and 12 mm/hr 12 mm/hr
As an example stormy tropical shower rate can be as high as 500 mm/hr and uppest limit for hail may reach 4700 mm/hr.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
FCB-FCB11 P 2/2 29 JUL 11
FLIGHT CREW BULLETINS FMGS NAVIGATION DATABASE
Intentionally left blank
FLIGHT CREW BULLETINS FMGS NAVIGATION DATABASE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
FCB-FCB12-PLP PRELIMINARY PAGES TABLE OF CONTENTS FMGS Navigation Data Base.................................................................................................................................. A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB12-PLP-TOC P 1/2 30 MAY 12
FLIGHT CREW BULLETINS FMGS NAVIGATION DATABASE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB12-PLP-TOC P 2/2 30 MAY 12
FLIGHT CREW BULLETINS FMGS NAVIGATION DATABASE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FMGS NAVIGATION DATA BASE Ident.: FCB-FCB12-00013112.0001001 / 02 MAR 11 Applicable to: ALL
REASON FOR ISSUE AND SCOPE The aim of this FCOM Bulletin is to highlight the importance of the Navigation Data Base accuracy and therefore the importance of its update and its correctness. As any NAV data base discrepancy or false coding may induce navigation errors and lateral or vertical misguidances, this FCOM Bulletin provides flight crews with operational recommendations. INCORRECT NAV DATA BASE CASES NAVIGATION DATA BASE DISCREPANCIES Numerous in service events have been reported during the last few years, which are caused by 3 different types of Navigation Data Base discrepancies: ‐ NAV data base not updated on time ‐ Incorrect coding or impossibility of coding of published procedures ‐ Coding errors. NAV Data Base Not Updated on Time When a NAV Data Base is not updated on time, this may lead to incorrect position or misguidance: ‐ 1st example STAR MEN2 (LFBO) was modified but not incorporated in the NAV D.B. As a result the STAR displayed on the ND was not the published one. ‐ 2nd example TRANS between STAR VAREK and NDB03 was not coded at Ajaccio (LFKJ). Misguidance was the consequence.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
FCB-FCB12 P 1/6 30 MAY 12
FLIGHT CREW BULLETINS FMGS NAVIGATION DATABASE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
NAV Data Base Incorrect Coding Incorrect coding in the NAV D.B. induces misguidance in SID or STAR: ‐ 1st example STAR VAREK at Ajaccio (LFKJ). The leg STP-VAREK was coded as a TF (track to fix) and the following leg was coded as a CF (course to fix). Due to the imprecision of the magnetic variation in the area, both legs were not lined up and the A/C had to turn, after VAREK WPT, to capture the next leg.
‐ 2nd example STAR PERIK 1 and GORON 1 AT Genova (LSGG). These STARs end at WPT SINEL located in the middle of the APPR 23. This creates a F-PLN discontinuity and the procedure is not flyable. The NAV D.B. error is linked to both coding and procedure concept.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB12 P 2/6 30 MAY 12
FLIGHT CREW BULLETINS FMGS NAVIGATION DATABASE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
‐ 3rd example On several non precision approaches, the final descent angle is coded for the last leg only instead of the last 2 legs. Again this creates a level off segment which does not exist.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB12 P 3/6 30 MAY 12
FLIGHT CREW BULLETINS FMGS NAVIGATION DATABASE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Coding Errors Coding errors generally have very similar effects on the FMGS system and may induce position errors as well as misguidance: ‐ 1st example Erroneous position of runway threshold at LFMT RWY 32R inducing a lateral offset during non precision approach ‐ 2nd example ILS/DME coded as an ILS only preventing autotuning of the DME in approach (IWW and IGG at EGKK). PROBLEMS LINKED TO ARINC 424 SPECIFICATION If an item is not specified in the ARINC 424, it will not be part of the NAV D.B. For example: No specific field reserved for THR RED/ACC ALT. As a result, it is not possible to link such information to a company route (e.g noise abatement). Defaulted value is provided instead. Systematic Coding of HF Leg in Procedures When a Final Approach procedure displays a Holding Pattern, this pattern is systematically coded in the APPR VIA or STAR as an HF leg; this means that this holding is always taken 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB12 P 4/6 30 MAY 12
FLIGHT CREW BULLETINS FMGS NAVIGATION DATABASE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
into account in the F-PLN, assuming one turn; in certain cases, this is realistic but in most circumstances, it is not.
If the HF leg is of no use, it corrupts all predictions and performance computations. Furthermore if a holding pattern is ATC required, by then the crew has all means to insert it into the F-PLN, and be then provided with realistic estimates. As a consequence, realistic coding of procedure turns should be requested. Circle to Land At many airports approaches are defined only in one direction; while the landing runway may be in the other direction. If the weather is poor, a defined instrument approach is carried out down to circle to land MDA, and then a circle to land trajectory is flown. Circle to Land feature is not part of current ARINC specification; this forces the crews to improvise in order to get a realistic trajectory on the ND, and to get proper predictions on CDU
RECOMMENDATIONS In order to control and correct NAVIGATION Data Base all pilots are encouraged to report to their flight operations any misbehaviour which may have been induced by an incorrect data base. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB12 P 5/6 30 MAY 12
FLIGHT CREW BULLETINS FMGS NAVIGATION DATABASE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
This can be done during normal operations: ‐ During preflight by checking the consistency of the MCDU F-PLN versus ATC F-PLN. Refer to current FCOM ‐ In flight by performing the navigation accuracy assessment on a regular basis as described in the FCOM procedures and techniques. CONCLUSION Tomorrow, the increasing number of RNAV approaches will require faultless NAV Data Base procedures since it will not always be possible to monitor the guidance by using raw data. On a short term basis, the NAV Data Base improvement is a matter of step by step error detection which mainly requires pilot attention during preflight and in flight. On a longer term basis, the NAV Data Base improvement requires decisions and actions of concerned agencies/authorities and NAV Data Base manufacturers. It has to be reminded that the aircraft constructor has no control over the data base used by each operator.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
FCB-FCB12 P 6/6 30 MAY 12
FLIGHT CREW BULLETINS SPECIFIC FEATURES OF THE FMGS FULL STANDARD
Intentionally left blank
FLIGHT CREW BULLETINS SPECIFIC FEATURES OF THE FMGS FULL STANDARD A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
FCB-FCB13-PLP PRELIMINARY PAGES TABLE OF CONTENTS Specific Features of the FMGS Full Standard........................................................................................................ A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB13-PLP-TOC P 1/2 29 JUL 11
FLIGHT CREW BULLETINS SPECIFIC FEATURES OF THE FMGS FULL STANDARD A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB13-PLP-TOC P 2/2 29 JUL 11
FLIGHT CREW BULLETINS SPECIFIC FEATURES OF THE FMGS FULL STANDARD A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
SPECIFIC FEATURES OF THE FMGS FULL STANDARD Ident.: FCB-FCB13-00013113.0001001 / 02 MAR 11 Applicable to: ALL
Note:
This FCOM bulletin is only valid for aircraft equipped with FMGS full standard.
The FMGS full standard was introduced in 1992. During the first months of service, questions have been raised on particularities of the system. 1. ALTITUDE PREDICTIONS NOT ACCURATE ON GROUND Predicted altitudes indicated on the F-PLN A page are not accurate until take off; an error of a few hundred feet may be noticed on predicted altitudes at all waypoints until lift off. EXPLANATION The predictions are computed using simplified model for the take off run. This causes a minor error on the altitude predictions. Predictions are continuously updated during the take off roll and once airborne, they are accurate. 2. SPURIOUS "FMS 1/FMS 2 SPD TGT DIFF" MSG When changing of CRZ FL using the FCU altitude knob, the message "FMS 1/FMS 2 SPD TGT DIFF" may come up. EXPLANATION The new FCU altitude is sent by the master FMGC to the slave, therefore predictions are not computed at the same time on both FMGCs; a speed target difference may occur during a very short period, triggering the message. PROCEDURE Disregard the message. 3. "IRS ONLY NAVIGATION" MSG TRIGGERED AT DESCENT PHASE SWITCHING When the A/C is in IRS ONLY NAV mode, the message "IRS ONLY NAVIGATION" is triggered when the A/C starts the descent. EXPLANATION The system logic is triggered when the FMGS navigation mode has been in inertial only for more than 10 min in cruise or when the A/C is transitionning to descent phase without radio updating. If the FMGS is in IRS only navigation mode at descent phase switching, the message is immediately triggered, reminding the crew that the A/C is operating without radio position.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
FCB-FCB13 P 1/2 29 JUL 11
FLIGHT CREW BULLETINS SPECIFIC FEATURES OF THE FMGS FULL STANDARD A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PROCEDURE Perform a NAV ACCY CHECK. 4. VERTICAL DEVIATION DIFFERENT ON BOTH SIDES In descent or approach the vertical deviation (VDEV) indicated on the PFD and PROG page may differ on side 1 and 2. EXPLANATION The vertical deviation (VDEV) is computed independently on side 1 and 2; if FM 1/2 position ground speed or other data used for VDEV computation differ slightly from side 1 and 2, a small difference of VDEV will be observed during descent and/or approach. 5. INCREASE OF VERTICAL SPEED IN DES MODE The vertical speed may increase noticeably for a short period of time during descent with DES mode engaged. The V/S regains the normal value when intercepting the path. EXPLANATION When the A/C is above path and an increase of speed target is required manually or automatically, the V/S will increase temporarily until the vertical profile is intercepted. 6. VLS COMPUTATION 6.1
6.2
The VLS computed by the FMGS uses the same algorithm and performance table as the FAC. Nevertheless some differences may be observed due to the fact that the FAC computes the VLS from flight parameters and the precision of the computation provides an accuracy of ±3 kt (PFD VLS). In CONF 3, the performance table used to compute the VLS assumes the gear up although the table provided in the QRH and FCOM assume gear down. A VLS difference of 2 kt can be observed between performance table and FAC/FMGS in CONF 3.
7. A/C POSITION INVALID When a fast realignment is performed, the message A/C POSITION INVALID is triggered. The message disappears when the realignment is completed. EXPLANATION During an IRS alignment, the ADIRS send no data to the FMGS and the FMGS cannot process any position. The POS MONITOR page is empty and the MSG "A/C POSITION INVALID" is automatically triggered. Once the IRS are realigned, the ADIRS provide data to the FM and a mix IRS position is recomputed; the message disappears.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
FCB-FCB13 P 2/2 29 JUL 11
FLIGHT CREW BULLETINS VMO/MMO DETERMINATION
Intentionally left blank
FLIGHT CREW BULLETINS VMO/MMO DETERMINATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
FCB-FCB15-PLP PRELIMINARY PAGES TABLE OF CONTENTS VMO/MMO Determination........................................................................................................................................A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB15-PLP-TOC P 1/2 29 JUL 11
FLIGHT CREW BULLETINS VMO/MMO DETERMINATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB15-PLP-TOC P 2/2 29 JUL 11
FLIGHT CREW BULLETINS VMO/MMO DETERMINATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
VMO/MMO DETERMINATION Ident.: FCB-FCB15-00013115.0001001 / 02 MAR 11 Applicable to: ALL
GENERAL VMO (the design cruising speed) is the maximum operating speed that the crew may fly within the normal flight envelope. It is not authorized to fly intentionally above this limit. VD is the design dive speed. VMO and VD must comply with load requirements (gust loads, maneuvering loads). For example, the aircraft must be able to sustain a load factor of 2.5 up to VD. The range between VMO/VD considers normal reaction time to the crew to use standard recovery techniques for returning the aircraft to normal attitude at a speed of VMO/MMO. The A319/A320/A321 are protected by the High Speed Protection law which automatically makes the recovery if VMO is exceeded (between VMO and VMO +6) as shown in the following table. HIGH SPEED/MACH TABLE MD = 0.89
VD = 381 kt
MMO +0.04
VMO +20 kt
MMO +0.01 MMO +0.006
VMO +6 kt VMO +4 kt
MMO = 0.82
VMO = 350 kt
MMO -0.006 MMO -0.02
VMO -3 kt VMO -10 kt
VD = VMO +31 kt Structural inspection required. (Refer to relevant AMM section) Upper limit for entry into HSP Overspeed warning Max operating SPEED/MACH and lower limit for entry into HSP Max upper speed range in DES mode. Managed speed target limit (ECON mode)
Depending upon the speed trend, the autopilot will disconnect at or below VMO +6 kt/MMO +0.01 and an automatic pitching up will allow VMO to be regained. Per design, in DES mode or OP DES mode, autopilot authority is limited to 0.1 g compared to 0.15 g in EXPEDITE. This limitation was required by the launching customers for passenger's comfort. Due to the load factor limitation, some flight paths or environment conditions depending on their magnitude, may not be counteracted by the autopilot leading to VMO/MMO overshoot. A short exceedance of few knots above VMO has no consequences on the aircraft. Nevertheless, an intentional exceedance is not authorized: ‐ By regulation ‐ Because above VMO/MMO the HSP (high speed protection) may be activated automatically. Any pilot input to recover the target speed may be added to the HSP order, leading to a load factor incompatible with passenger's comfort.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
FCB-FCB15 P 1/2 29 JUL 11
FLIGHT CREW BULLETINS VMO/MMO DETERMINATION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
For this reason, it is recommended to be smooth on the stick when manually recovering from a VMO/MMO exceedance. In order to prevent this exceedance during descent, a procedure has been described in Refer to PRO-NOR-SRP-01-60 Descent Initiation.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
FCB-FCB15 P 2/2 29 JUL 11
FLIGHT CREW BULLETINS OPERATION OF FLEETS WITH/WITHOUT CPIP
Intentionally left blank
FLIGHT CREW BULLETINS OPERATION OF FLEETS WITH/WITHOUT CPIP A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
FCB-FCB16-PLP PRELIMINARY PAGES TABLE OF CONTENTS Operation of Fleets with/without CPIP.................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB16-PLP-TOC P 1/2 29 JUL 11
FLIGHT CREW BULLETINS OPERATION OF FLEETS WITH/WITHOUT CPIP A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB16-PLP-TOC P 2/2 29 JUL 11
FLIGHT CREW BULLETINS OPERATION OF FLEETS WITH/WITHOUT CPIP A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
OPERATION OF FLEETS WITH/WITHOUT CPIP Ident.: FCB-FCB16-00013116.0001001 / 02 MAR 11 Applicable to: ALL
INTRODUCTION In order to continuously improve the man/machine interface, Airbus developed continuous product improvement programmes (CPIP), the modifications of which are available for retrofit and are commonly introduced on all new A320/A321 and on A319. This FCOM bulletin details the differences which crews should be aware of. DEFINITION BASIC AIRCRAFT The A320 equipped with full standard FMGS without CPIP (continuous production improvement programme) nor ENERGY MANAGEMENT. ADVANCED STANDARD The A319/A320/A321 with CPIP 1 + 2 + 3, LOW ENERGY warning and ENERGY MANAGEMENT. This standard is basic on the A319/A321 and A320 in current production and can be retrofitted to all A320. MODIFICATION DESCRIPTION CPIP 1 (FCU MODIFICATION) ‐ Altitude selection change inhibited during push/pull action. This modification prevents any change of altitude during mode engagement. ‐ HDG and V/S preselection time increased from 10 to 45 s. ‐ V/S/FPA click differentiation for rapid selection: 1 click = 1 ° FPA 2 clicks = 100 ft/min V/S CPIP 2 (FCU MODIFICATION) ‐ V/S/FPA "push to level off" function. When pushing the V/S/FPA selector knob, V/S/FPA target is set to zero. ‐ 4 digits for V/S target. The V/S and FPA target are displayed in the window as followed: V/S = 4 digits FPA = 2 digits ‐ HDG/TRK target is synchronized when switching from HDG to TRK or vice versa. ‐ SPD/MACH, HDG/TRK, METRIC ALT switching pushbuttons are labelled.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
FCB-FCB16 P 1/8 29 JUL 11
FLIGHT CREW BULLETINS OPERATION OF FLEETS WITH/WITHOUT CPIP A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
LOW ENERGY WARNING (FAC AND FWC MODIFICATION) The low energy warning consists of an aural warning "speed speed speed" triggered every 5 s. This warning is available when CONF ≥ 2 and 100 ft < RA < 2 000 ft; it indicates that the energy level is not sufficient to recover to a positive flight path angle with only pitch command. The thrust must be increased. This warning is generated before the alpha floor is triggered.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB16 P 2/8 29 JUL 11
FLIGHT CREW BULLETINS OPERATION OF FLEETS WITH/WITHOUT CPIP A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
CPIP 3: FMA IMPROVEMENTS (DMC AND FWC MODIFICATION) ‐ Engagement status of both FDs are displayed on both PFDs:
‐ A/THR annunciations are changed as follows: • White colour and MAN label when the thrust levers are set manually in the corresponding detent. e.g. MAN TOGA, MAN FLEX, MAN MCT. MAN THR when the thrust levers are set above the applicable detent. The A/THR is armed (A/THR blue on FMA). • LVR white (or amber) label whenever the thrust levers are not in the correct detent: (e.g. LVR CLB, LVR MCT, LVR ASYM) • THR green label when the Thrust mode is active: THR CLB, THR MCT, THR IDLE. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB16 P 3/8 29 JUL 11
FLIGHT CREW BULLETINS OPERATION OF FLEETS WITH/WITHOUT CPIP A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
‐ All AP/FD modes are displayed as abbreviations (no dashes): (e.g. NAV, ALT CRZ, ALT CSTR). ‐ V/S or FPA target are displayed in the FMA: e.g. V/S: + 800 ‐ Message and MSG colours are changed as follows: "MORE DRAG" white message instead of "AIRBRAKES" "CHECK APP SEL'' white message instead of "CHECK APP GUIDANCE" "SET MANAGED SPD" white message instead of "SET AUTO SPEED" "SET GREEN DOT SPD" white message instead of "SET VFTO"
ENERGY MANAGEMENT IMPROVEMENT (FAC, FWC, DMC, FADEC modification) The ENERGY MANAGEMENT package is related to A/THR logic modification and additional ECAM announcements. The package eases the normal procedure of A/THR disconnection and improves the crew information on the current thrust setting.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB16 P 4/8 29 JUL 11
FLIGHT CREW BULLETINS OPERATION OF FLEETS WITH/WITHOUT CPIP A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
A/THR Disconnection Using the Instinctive Disconnect Pushbutton When the instinctive disconnect pushbutton is depressed: ‐ Thrust is immediately set to the thrust corresponding to the thrust lever position. (Thrust lock no longer effective) ‐ A gong sounds and the master CAUTION light illuminates for 3 s ‐ AUTO FLT A/THR OFF is displayed on the ECAM for 9 s maximum. A/THR disconnection due to a failure or an action on the A/THR FCU P/B when illuminated green:
‐ THRUST LOCK is active until the thrust levers are moved out of corresponding detent (or alpha floor activates) ‐ Annunciation is enhanced as follows: • Repetitive gong and master CAUTION light • THR LK amber displayed on both PFDs • AUTO FLT A/THR OFF displayed on ECAM • Blue "THR LEVERS.....MOVE" displayed on ECAM • With a 5 s delay, flashing "ENG THRUST LOCKED".
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB16 P 5/8 29 JUL 11
FLIGHT CREW BULLETINS OPERATION OF FLEETS WITH/WITHOUT CPIP A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Thrust levers set below CL detent: ‐ Repetitive gong and master CAUTION light ‐ "AUTO FLT A/THR LIMITED" and "THR LEVER...MOVE" displayed on ECAM ‐ LVR CLB displayed on FMA
IDLE announcement on ECAM When thrust is set automatically or manually at IDLE thrust, IDLE legend flashes green for 10 s then steady on ECAM EWD (adjacent to N1/EPR scale).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB16 P 6/8 29 JUL 11
FLIGHT CREW BULLETINS OPERATION OF FLEETS WITH/WITHOUT CPIP A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
OPERATIONAL CONSIDERATIONS FCU MODIFICATION (CPIP 1 AND CPIP 2) The introduction of FCU modifications does not significantly modify the published procedures: ‐ V/S push to level off function V/S = 0.0 selection may still apply; the "push to level off" function is a easier action. In both cases, the crew must crosscheck with FMA. ‐ Different digits for V/S and FPA The procedure which consists of crosschecking (and announcing) V/S or FPA value obtained on PFD remains mandatory. ‐ Synchronisation of HDG/TRK target This allows the switching from HDG to TRK or vice versa with bank angle. Airbus still recommends the switching with wings level. LOW ENERGY WARNING This feature provides an advanced warning to the crew before alpha floor is triggered. Standard procedures are unchanged and flight envelope remains the same. Alpha floor and alpha protection are identical. CPIP 3 The announciations of the FMA are self explanatory. The procedure remains the same: ‐ Any mode change is to be checked and announced. ‐ When a new target is selected and activated through the FCU, the resulting guidance has to be checked on the PFD. ENERGY MANAGEMENT The main feature of the ENERGY management is the suppression of the thrust lock when the A/THR instinctive disconnect pushbutton is used. The A/THR disconnection technique remains unchanged (Refer to PRO-SUP-70 Thrust Control), and may be summarized as follows: When A/THR is to be disconnected: ‐ Move the thrust levers out of the applicable detent, to the current or desired thrust level ‐ Depress the instinctive disconnected pb. The new ECAM features facilitate the crew action but do not modify the procedures.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
FCB-FCB16 P 7/8 29 JUL 11
FLIGHT CREW BULLETINS OPERATION OF FLEETS WITH/WITHOUT CPIP A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB16 P 8/8 29 JUL 11
FLIGHT CREW BULLETINS CHARACTERISTIC AND PROTECTION SPEEDS
Intentionally left blank
FLIGHT CREW BULLETINS CHARACTERISTIC AND PROTECTION SPEEDS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
FCB-FCB17-PLP PRELIMINARY PAGES TABLE OF CONTENTS Characteristic and Protection Speeds..................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB17-PLP-TOC P 1/2 29 JUL 11
FLIGHT CREW BULLETINS CHARACTERISTIC AND PROTECTION SPEEDS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB17-PLP-TOC P 2/2 29 JUL 11
FLIGHT CREW BULLETINS CHARACTERISTIC AND PROTECTION SPEEDS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
CHARACTERISTIC AND PROTECTION SPEEDS Ident.: FCB-FCB17-00013117.0001001 / 29 MAR 11 Applicable to: ALL
INTRODUCTION The different speeds displayed to the crew on the main cockpit interfaces: PFD, MCDU, ND are computed by the FACs, the FMGCs and the ADIRS. PFD FAC COMPUTATION Computed on current aircraft status and configuration. VLS F S "O" Green Dot Vαprot Vαmax Vsw (stall warning speed)
MCDU PERF PAGE FMGC COMPUTATION Computed for take off, go around and landing. VLS of the selected landing configuration. F S "O" Green Dot
Each FAC computes its own speeds which are displayed on the relevant PFD: FAC 1 on side 1 FAC 2 on side 2. Each FMGC computes its own speeds displayed on the relevant MCDU: FMGC 1 on side 1 FMGC 2 on side 2. The algorithms used to compute the characteristic speeds are the same in both FAC and FMGC but as the inputs are different, the resulting values may differ. CHARACTERISTICS SPEEDS COMPUTED BY THE FAC The FAC computes its characteristic speeds with 2 main inputs from ADIRS (Angle of Attack (α) and calibrated airspeed (Vc)). It also uses THS position, SFCC data and FADEC data. From these inputs, the FAC computes a stall speed Vs which is used to determine the aircraft weight. The following sketch gives the basic architecture for FAC speed computation.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
FCB-FCB17 P 1/6 29 JUL 11
FLIGHT CREW BULLETINS CHARACTERISTIC AND PROTECTION SPEEDS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
AOA DETERMINATION The angle of attack value used to compute the characteristic speeds is the mean value of the 3 AOAs (Vote). Accuracy of the AOAs is a paramount factor in the weight calculation. 0.3 ° of error in the AOA results in a 3 t error in weight.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB17 P 2/6 29 JUL 11
FLIGHT CREW BULLETINS CHARACTERISTIC AND PROTECTION SPEEDS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WEIGHT COMPUTATION
The weight is computed provided the following conditions are met: ‐ Aircraft altitude below 14 600 ft and speed (Vc) below 240 kt ‐ Bank angle less than 5 ° ‐ Speedbrakes retracted ‐ No dynamic maneuver (vertical load factor lower than 1.07 g) ‐ No change of aircraft configuration and not in CONF full. When one of these conditions is not met, the last calculated weight value is considered and updated for the fuel consumption based on actual engine N1. CHARACTERISTIC SPEEDS COMPUTATION A320 VLS is computed from Weight and Vc and corrected for the current CG. ‐ If the current CG is forward of 15 %, 15 % CG is used to compute the speeds ‐ If the current CG is between 15 % and 25 %, the speeds are computed using an interpolation between 15 % and 25 % CG ‐ If the current CG is aft of 25 %, 25 % CG is used for speed computation. F, S, and Green dot are independent of CG. A319-321 VLS, F, S and Green Dot are computed for a forward CG. No CG correction is applied for A319/A320 VLS as it has a negligible effect.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB17 P 3/6 29 JUL 11
FLIGHT CREW BULLETINS CHARACTERISTIC AND PROTECTION SPEEDS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PROTECTION SPEEDS CALCULATED BY THE FAC Vαprot and Vαmax are displayed in normal law. The FAC does not trigger alpha prot and alpha MAX protection. (The alpha prot and alpha max protection are activated by the ELAC). Vsw, the stall warning speed is computed by the FAC in ALTN or DIRECT law. At Vsw speed, an audio warning (crickets - STALL synthetic voice) is triggered.
TOLERANCE OF FAC COMPUTED SPEEDS Due to the data accuracy used to compute the characteristic speeds, and specifically the AOA accuracy, the precision of the computation is specified to be within 2.5 %.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB17 P 4/6 29 JUL 11
FLIGHT CREW BULLETINS CHARACTERISTIC AND PROTECTION SPEEDS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
During acceptance flight, the tolerances are as following: Clean aircraft Green Dot ±5 kt VLS ±4 kt Vαprot ±5 kt Vαmax ±5 kt Conf full VLS ±3 kt Vαprot ±5 kt Vαmax ±5 kt CHARACTERISTICS SPEEDS COMPUTED BY THE FMGC Characteristic speeds computed by the FMGC are based on a predicted GW, CG (and selected configuration for landing) at a given time at landing for example. GW and CG values are computed from entered ZFW and ZFWCG corrected for the predicted FOB and CG variation. When the Approach phase is activated, the characteristic speeds are recomputed using the actual weight and CG. The performance model used to compute the characteristic speeds, is accurate enough to provide speed errors of less than ± 2 kt from the certified speeds.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB17 P 5/6 29 JUL 11
FLIGHT CREW BULLETINS CHARACTERISTIC AND PROTECTION SPEEDS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
THE MOST FREQUENT QUESTIONS ON SPEED COMPUTATION ‐ Why are the characteristic speeds computed by the FAC subject to inaccuracy greater than FMGC computation? Answer: The precision of the AOA measurement is usually the cause of speed differences. An error of 0.3 ° in AOA measurement causes a weight inaccuracy close to 3 t. ‐ Is the FMGC computation more accurate than the FAC computation? Answer: Algorithms are the same but the initial data are different. The FAC computes current dynamic speeds. The FMGS computes characteristic speeds for given phases (and configuration for landing). Usually, the FMGC characteristic speeds for landing are more accurate due to the tolerance of FAC inputs, if the ZFW was correct initially. Note:
To determine the GW at landing, the FMGC uses the ZFW entered by the crew and adds the fuel on board. A significant difference between PFD and MCDU characteristic speeds may also indicate an error in the ZFW as entered by the crew
‐ Why are there two characteristic speed calculations? Answer: The computation done by the FAC is independent of any manually entered data and provides permanent speed values displayed on the PFD. During approach, the comparison of characteristic speeds allows the crew to detect any speed discrepancy which may affect approach and final phases. ‐ When a difference exists between computed speeds from FAC and FMGC, what are the best speeds to be relied on ? Answer: Whenever differences are observed, Airbus recommends to rely on QRH values. Refer to QRH/FPE-SPD Speeds.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
FCB-FCB17 P 6/6 29 JUL 11
FLIGHT CREW BULLETINS GROUND SPEED MINI FUNCTION
Intentionally left blank
FLIGHT CREW BULLETINS GROUND SPEED MINI FUNCTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
FCB-FCB18-PLP PRELIMINARY PAGES TABLE OF CONTENTS Ground Speed Mini Function...................................................................................................................................A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB18-PLP-TOC P 1/2 29 JUL 11
FLIGHT CREW BULLETINS GROUND SPEED MINI FUNCTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB18-PLP-TOC P 2/2 29 JUL 11
FLIGHT CREW BULLETINS GROUND SPEED MINI FUNCTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GROUND SPEED MINI FUNCTION Ident.: FCB-FCB18-00013118.0001001 / 02 MAR 11 Applicable to: ALL
GENERAL When an approach is flown in managed speed mode, the crew will notice that the target speed (magenta) displayed on the PFD, is variable during the approach. This approach target speed, also called IAS target, is computed in the FMGS using the "ground speed mini function". The purpose of the Ground speed mini function is to take advantage of the aircraft inertia, when the wind conditions vary during the approach. The aircraft flies a target speed during the approach and the energy of the aircraft is maintained above a minimum level ensuring standard aerodynamic margins over stall. If the A/THR is active in SPEED mode, it will automatically follow the IAS target, ensuring efficient thrust management during the approach. PRINCIPLE The minimum energy level is based upon the ground speed the aircraft should have at touchdown, when landing at VAPP with the expected wind. It is called "GROUND SPD MINI". During the approach, the FMGS continuously computes the IAS target to keep the ground speed at or above the "Ground Speed Mini", based upon the actual winds. This IAS target is limited to VAPP The IAS target is displayed on the PFD speed scale in magenta, when approach phase and managed speed are active. It is independent of the AP/FD and/or the A/THR engagements. The following examples provide a comparison between the ground speed mini function versus the conventional selected speed hold function, in terms of speed target, and thrust management during an approach where winds are varying.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
FCB-FCB18 P 1/8 29 JUL 11
FLIGHT CREW BULLETINS GROUND SPEED MINI FUNCTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Ground speed mini function provides all the information necessary to manage the thrust smoothly and efficiently during the approach, in the event of gusts or horizontal windshears.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB18 P 2/8 29 JUL 11
FLIGHT CREW BULLETINS GROUND SPEED MINI FUNCTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
BASIC COMPUTATION Wind is a key factor in the ground speed mini function. TOWER WIND It is the MAG WIND entered in the PERF approach page. It is the average wind as provided by the ATIS or the tower. Gusts are not inserted; they are taken into account during ground speed mini computation.
TOWER HEADWIND COMPONENT Component of the MAG WIND relative to the FMS runway axis. The FMS Runway axis is the landing runway axis entered in the F-PLN and indicated on the PERF APPR page. CURRENT WIND COMPONENT Component of the actual wind measured by ADIRS, relative to the aircraft axis. The three following formulae explain how the approach speed target (IAS target) is computed using the ground speed mini function. Note that this computation is different for the A320 and the A319, A321 or A320 with the modification which reduces VAPP (mod 25225). VAPP Computation A320 A320 with Mod 25225 A319/A321
VAPP COMPUTATION VAPP = VLS + 5 kt + 1/3 OF THE TOWER HEADWIND COMPONENT VAPP = VLS + MAX (5, 1/3 OF THE TOWER HEADWIND COMPONENT)
Wind correction limit: mini 0 kt, maxi 15 kt VAPP may be changed manually by the crew if desired. The 5 kt increment to VLS is an Airworthiness requirement when autoland is used. (CAT 2 CAT 3) Tower headwind component is counted positively. In case of a tower tailwind, the wind correction is zero and VAPP = VLS + 5. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB18 P 3/8 29 JUL 11
FLIGHT CREW BULLETINS GROUND SPEED MINI FUNCTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Ground Speed Mini Computation The ground speed mini value is not displayed to the crew, but it is of interest to understand its principle. GS mini = VAPP - TWR HEADWIND COMPONENT ‐ The TWR HEADWIND COMPONENT is counted positively ‐ The TWR HEADWIND COMPONENT is counted positively ‐ If the TWR HEADWIND COMPONENT is below 10 kt or if there is a TWR TAILWIND COMPONENT, GS mini = VAPP -10 Approach Speed Target Computation (IAS Target) Approach speed target, also called IAS target is computed as the higher of: ‐ VAPP ‐ GS mini plus current wind component IAS target = MAX (VAPP, GS mini + CURRENT WIND COMPONENT) CURRENT HEADWIND COMPONENT is counted positively. CURRENT TAILWIND COMPONENT is counted negatively. No max value limitation exists. EXAMPLES NORMAL APPROACH ‐ Approach on Runway 09 - FMS Runway 09 ‐ TWR wind on PERF APPR page: 090/30 ‐ VLS = 130 kt COMPUTATION
VAPP
GS Mini Current wind in Approach
(a) 090/50 (b) 090/10 (c) 270/10 (d) 090/30
A320 (basic configuration)
GS Mini = 145 - 30 = 115 kt
GS Mini = 140 - 30 = 110 kt
IAS target (◃) A320 (basic configuration) MAX (VAPP, 115 + 50) = 165 kt MAX (VAPP, 115 + 10) = 145 kt MAX (VAPP, 115 - 10) = 145 kt MAX (VAPP, 115 + 30) = 145 kt
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A320 (with Mod 25225) A319 - A321
←A→
IAS target (◃) A320 (with Mod 25225) A319, A321 MAX (VAPP, 110 + 50) = 160 kt MAX (VAPP, 110 + 10) = 140 kt MAX (VAPP, 110 - 10) = 140 kt MAX (VAPP, 110 + 30) = 140 kt
FCB-FCB18 P 4/8 29 JUL 11
FLIGHT CREW BULLETINS GROUND SPEED MINI FUNCTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
CIRCLING APPROACH The crew will insert (primary F-PLN) the instrument approach to be flown to MDA. The secondary flight plan should contain final approach for the landing runway with the associated wind information. During the circling maneuver, the crew must activate the secondary in order to provide valid ground speed mini information. Example: Instrument Approach on RWY 27 Circling Approach to RWY 09 Winds a. 090/50 kt b. 090/10 kt c. 270/10 kt d. 090/30 kt (TWR wind on PERF APPR) VLS = 130 kt
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB18 P 5/8 29 JUL 11
FLIGHT CREW BULLETINS GROUND SPEED MINI FUNCTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
The 3 formulae give the following results: 1. VAPP = 130 + 5 + Zero* = 135 kt for A320 basic configuration 130 + MAX (5 kt, Zero*) = 135 kt for A320 with Mod 25225, A319, A321 * wind is considered as tail wind because RWY 27 is selected in the F-PLN. 2. GS Mini = 135 - 10 = 125 kt (10 kt default wind value) 3. IAS target = MAX (135, 125 + current headwind component).
The IAS target is function of the runway which is selected in the active flight plan. Let us consider that the aircraft is actually on Final Approach onto Runway 09, the approach target speed in final will vary as follows in case Runway 27 or Runway 09 are inserted in the FMS F-PLN:
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB18 P 6/8 29 JUL 11
FLIGHT CREW BULLETINS GROUND SPEED MINI FUNCTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Runway 27 selected in the F-PLN VAPP = 135 kt GS MINI = 125 kt SELECTED RUNWAY IN F-PLN
A320 (basic configuration) Runway 09 selected in the F-PLN VAPP = 145 kt GS MINI = 115 kt
VAPP VALUE (PERF APPR PAGE)
GS MINI
(1) RUNWAY 09 A320
145 kt
115 kt
(1 ) RUNWAY 27 A320 (Mod 25225) A319, A321
140 kt
110 kt
(2) RUNWAY 27
135 kt
125 kt
A320 (Mod 25225) A319, A321 Runway 09 selected in the F-PLN VAPP = 140 kt GS MINI = 110 kt
ENCOUNTERED WINDS
IAS TARGET IN FINAL FOR RUNWAY 09
(a) 090/50 (b) 090/10 (c) 270/10 (d) 090/30 (a) 090/50 (b) 090/10 (c) 270/10 (d) 090/30 (a) 090/50 (b) 090/10 (c) 270/10 (d) 090/30
165 kt 145 kt 145 kt 145 kt 160 kt 140 kt 140 kt 140 kt 175 kt 135 kt 135 kt 155 kt
CONCLUSION If the landing runway inserted in the FMGS F-PLN is different from the actual landing runway, MANAGED APPROACH SPD shall not be used since the resulting targets may be significantly too high. (This rule applies wherever the FMS landing runway axis is different by 30 ° the actual landing runway axis). In this case, select the approach speed directly on the FCU.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
FCB-FCB18 P 7/8 29 JUL 11
FLIGHT CREW BULLETINS GROUND SPEED MINI FUNCTION A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB18 P 8/8 29 JUL 11
FLIGHT CREW BULLETINS PUBLICATION OF SOME ATTENDANT INFORMATION BULLETINS
Intentionally left blank
FLIGHT CREW BULLETINS PUBLICATION OF SOME ATTENDANT INFORMATION BULLETINS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
FCB-FCB20-PLP PRELIMINARY PAGES TABLE OF CONTENTS Publication of some Attendant Information Bulletins...............................................................................................A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB20-PLP-TOC P 1/2 29 JUL 11
FLIGHT CREW BULLETINS PUBLICATION OF SOME ATTENDANT INFORMATION BULLETINS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB20-PLP-TOC P 2/2 29 JUL 11
FLIGHT CREW BULLETINS PUBLICATION OF SOME ATTENDANT INFORMATION BULLETINS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PUBLICATION OF SOME ATTENDANT INFORMATION BULLETINS Ident.: FCB-FCB20-00013121.0001001 / 02 MAR 11 Applicable to: ALL
EMERGENCY LIGHTING SYSTEM REASON FOR ISSUE Some cases of exit signs not illuminating during takeoff, landing and on ground have been reported. In normal operation with the "EMER EXIT LT sw" 4WL (25VU) in "ARM" position and the "NO SMOKING sw" 190RH (25VU) in auto position the exit signs extinguish only when the "NO SMOKING" signs extinguish at landing gear retraction and illuminate again at landing gear extention. Investigation revealed that the emergency power supply unit could remain frozen after power transfer. PROCEDURE During taxi and before landing check exit signs for proper illumination. If one or more exit signs are not illuminated, perform a reset of the emergency power supply by: 1. From attendant panel: ‐ Press the "EMERGENCY pb" 120RH once on flight attendant panel ‐ Wait approximately 4 s ‐ Press the "EMERGENCY pb" 120RH again to recover normal configuration. or 2. From the cockpit: ‐ Select the "EMER EXIT LT sw" on panel 25VU to "ON" position ‐ Select the "EMER EXIT LT sw" to "ARM" position. If normal operation is not recovered, maintenance action is due before the next flight unless the dispatch is authorized by the MEL. DELIBERATE INHIBITION OF AMBIENT LAVATORY SMOKE DETECTORS (A/C with MOD 22561) EXPLANATION When the smoke detector grill is removed and foreing objects like tissue paper or plastic bags are packed around the detector (see graphic below), the result will have a serious impact on the detection system. The detector may not be able to "sample" the air.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
FCB-FCB20 P 1/4 29 JUL 11
FLIGHT CREW BULLETINS PUBLICATION OF SOME ATTENDANT INFORMATION BULLETINS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PROCEDURE The cabin crew is recommended to inspect the lavatory smoke detectors for tampering before every flight. If foreign bodies or sign of tampering are found, line maintenance should be informed. VACUUM TOILET RINSE VALVE LEAKAGE (A/C with MOD 26145) EXPLANATION An increase in vacuum toilet rinse value leakage has been experienced. Leakage at the vacuum toilet rinse valve in the forward lavatory may lead to water flooding in the cockpit with possible water spillage in the avionic bay. ACTION Airbus Industrie has initiated a modification consisting of the introduction of an improved rinse valve. PROCEDURE Pending the introduction of the improved rinse valve, it is recommended that the cabin crew perform a toilet flush in each lavatory before the first flight of the day. This should minimize the effect of possible overnight deposit inside the valve by draining the content. The cabin crew should advise the maintenance if abnormal water accumulation is found.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB20 P 2/4 29 JUL 11
FLIGHT CREW BULLETINS PUBLICATION OF SOME ATTENDANT INFORMATION BULLETINS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
This grill is a cover for the ambient smoke detector and the air extraction duct. The view shown is how the grill would appear when looked at from below. This grill can be removed. Foreign objects (tissues, plastic bags) have been found packed around the ambient smoke detector.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
FCB-FCB20 P 3/4 29 JUL 11
FLIGHT CREW BULLETINS PUBLICATION OF SOME ATTENDANT INFORMATION BULLETINS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB20 P 4/4 29 JUL 11
FLIGHT CREW BULLETINS EGPWS DATABASE
Intentionally left blank
FLIGHT CREW BULLETINS EGPWS DATABASE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
FCB-FCB22-PLP PRELIMINARY PAGES TABLE OF CONTENTS EGPWS Database................................................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB22-PLP-TOC P 1/2 03 APR 12
FLIGHT CREW BULLETINS EGPWS DATABASE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB22-PLP-TOC P 2/2 03 APR 12
FLIGHT CREW BULLETINS EGPWS DATABASE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EGPWS DATABASE Ident.: FCB-FCB22-00013123.0002001 / 29 MAR 12 Applicable to: ALL
PURPOSE Airbus has received some reports of EGPWS warnings that were unduly triggered due to airport data missing from the database. It is the Airlines responsibility to identify the airport(s) where the terrain data is missing from the database. During operation around such airports, the enhanced function must be switched off (TERR pb OFF on overhead panel) when the aircraft position is less than 15 nm from the runway. The purpose of this bulletin is to provide the operators and the flight crews with additional information regarding the EGPWS database and the EGPWS system reaction when the airport/terrain data is not included in the database. The FCOM-LIM-34 (Refer to LIM-34 Enhanced Ground Proximity Warning System (EGPWS)) and AFM-LIM-34 (Refer to AFM/APP-TAWS Limitations) provide limitations of the system. 1. THE ENHANCED GPWS FUNCTIONS The purpose of the Enhanced Ground Proximity Warning System (EGPWS) is to alert the crew of potential hazardous conditions with regards to Controlled Flight into Terrain (CFIT).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
FCB-FCB22 P 1/6 03 APR 12
FLIGHT CREW BULLETINS EGPWS DATABASE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Two enhanced functions have been added to the basic modes of the GPWS. These functions are the following: ‐ Terrain Awareness and Display (TAD) ‐ Terrain Clearance Floor (TCF) • The Terrain Awareness and Display (TAD) function compares the aircraft FMS position with the local terrain in the database. It also computes two envelope boundaries ahead of the aircraft. When terrain data conflicts with one of these envelopes, specific aural and visual alerts are triggered. This function also provides terrain data display on the Navigation Display (ND)
• The Terrain Clearance Floor (TCF) function computes a terrain clearance envelope around the airport runway. It is based on current aircraft location, nearest runway center point position included in the database and radio height. When the aircraft enters this envelope, an alert "TOO LOW TERRAIN" is produced even if the aircraft is in landing configuration. This alert protects against an attempt to land where there is no airfield. This can be the case for example when descending by mistake on a wrong vertical path during a non-precision approach. This function operates during any flight phase.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB22 P 2/6 03 APR 12
FLIGHT CREW BULLETINS EGPWS DATABASE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2. THE EGPWS DATABASE The terrain database divides the Earth surface into grid cells. These cells are recorded upon the WGS-84 geographic coordinate system for longitude and latitude data. Each cell records the highest terrain altitude in the respective terrain area. The resolution of the grid varies upon the geographic location, ranging from: ‐ 0.25 nm x 0.25 nm ‐ 0.5 nm x 0.5 nm ‐ 1 nm x 1 nm ‐ 2 nm x 2 nm ‐ 5 nm x 5 nm. The highest resolution (0.25 nm x 0.25 nm) is used around the airports. This is to avoid producing alerts during normal procedures (the terrain database has to reflect as closely as possible the actual terrain). The lowest resolution (5 nm x 5 nm) is used outside airports where such a coarse terrain database cannot interfere with normal en-route trajectories. The database also contains the position of the airport runway center point. This concerns all hard surface runways (whatever the surface type is) longer than or equal to 3 500 ft. Additionally, the database gives the possibility of incorporating data regarding man-made obstacles in the vicinity of the major airports. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB22 P 3/6 03 APR 12
FLIGHT CREW BULLETINS EGPWS DATABASE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
3. EGPWS REACTION WHEN AIRPORT DATA IS MISSING FROM THE DATABASE. When an airport/terrain data is not yet covered by the database, the TCF envelope cannot be defined. The system uses the lowest map resolution (5 nm x 5 nm) as no airport is detected. Therefore, early and unexpected TAD cautions and warnings are triggered. The red EGPWS legend of the GPWS/G/S pb comes on, the aural warnings "TERRAIN AHEAD" and "TERRAIN AHEAD, PULL-UP" sound and the terrain image pops up on the Navigation Display. When within 15 nm, it is recommended to switch off the enhanced functions (EGPWS TERR pb switched to OFF on overhead panel) for operations from/to runways not incorporated in the database (Refer to LIM-34 Enhanced Ground Proximity Warning System (EGPWS)). 4. THE EGPWS DATABASE UPDATE The database update is under the responsibility of the vendor. The vendor may use one or more sources of data for a particular airport: 1. Data from in-country government and/or regulatory agencies 2. Data from airlines that have surveyed an airport while establishing layout, approach/departure procedures, etc. 3. Data from commercial vendors who also produce data sets for FMS and other navigational systems 4. Data from commercial and military surveying agencies that make such information publicly available 5. Airport layout and physical properties from high-resolution maps and/or digitized data sources 6. Airport layout and physical properties from imagery. Some difficulties may be encountered in some areas to compile and validate airport data. For an official indication of the latest EGPWS database, as well as a list of covered airports, please review the manufacturer document, EGPWS Terrain Database Airport Coverage list. More information can be found on the Honeywell website: WWW51.honeywell.com/aero/ 5. CONCLUSION The enhanced functions of the EGPWS are not reliable when operating around airports which are not included in the database. In this case, these functions must be switched off (TERR pb off on the overhead panel). It is the airlines responsibility to identify with the database manufacturer the airports where terrain data is missing. Airbus strongly recommends to the airline to report to the database manufacturer and to their local airworthiness authorities any EGPWS warning occurrence due to airport data missing from the database. It is also recommended that airlines request that their national authorities publish the
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB22 P 4/6 03 APR 12
FLIGHT CREW BULLETINS EGPWS DATABASE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
necessary data in order that the database manufacturer can extend the database coverage to all operated airports.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
FCB-FCB22 P 5/6 03 APR 12
FLIGHT CREW BULLETINS EGPWS DATABASE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB22 P 6/6 03 APR 12
FLIGHT CREW BULLETINS USE OF MANAGED GUIDANCE IN APPROACH AND NAV DATABASE VALIDATION
Intentionally left blank
FLIGHT CREW BULLETINS
A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
USE OF MANAGED GUIDANCE IN APPROACH AND NAV DATABASE VALIDATION PRELIMINARY PAGES - TABLE OF CONTENTS
FCB-FCB23-PLP PRELIMINARY PAGES TABLE OF CONTENTS Use of Managed Guidance in Approach and NAV Database Validation................................................................ A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB23-PLP-TOC P 1/2 03 APR 12
FLIGHT CREW BULLETINS
A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
USE OF MANAGED GUIDANCE IN APPROACH AND NAV DATABASE VALIDATION PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB23-PLP-TOC P 2/2 03 APR 12
FLIGHT CREW BULLETINS
A318/A319/A320/A321
USE OF MANAGED GUIDANCE IN APPROACH AND NAV DATABASE VALIDATION
FLIGHT CREW OPERATING MANUAL
USE OF MANAGED GUIDANCE IN APPROACH AND NAV DATABASE VALIDATION Ident.: FCB-FCB23-00013124.0001001 / 27 JAN 12 Applicable to: ALL
1. BACKGROUND The purpose of this FCOM Bulletin is to highlight SOP recommendations on the use of managed guidance in approach. The current body of published Instrument Approach Procedures (lAP) includes "old style" procedures, based on conventional radio NAVAIDs which cannot always be coded in the navigation database, in a suitable manner for satisfactory FMGS guidance in approach. Note:
RNAV procedures are usually designed and coded for optimum FMGS guidance in FINAL APP mode.
For conventional NPA using FMS managed lateral and vertical guidance, if the navigation database has been obtained from approved suppliers compliant with the requirements of ED76/DO200A, the validation of the approach coded in the database can be deferred to the flight crew, checking the FM F-PLN (on MCDU and ND) against the published approach chart. Note:
Conventional radio NAVAIDs must be available and monitored during the approach, and must be considered as the primary means of navigation.
For RNAV approaches using FMS managed lateral guidance only, based on the provisions of AMC 20 XZ (draft), if the navigation database has been obtained from approved suppliers compliant with the requirements of ED76/DO0200A, the validation of the approach lateral flight path coded in the navigation database can be deferred to the flight crew, checking the FM F-PLN (on MCDU and ND) against the published approach chart. Note:
When flying an RNAV approach using NAV mode associated with selected vertical guidance (FPA, V/S), the distance to the runway or the MAP versus altitude is the primary means of vertical navitation, the vertical deviation on the PFD may be unreliable.
For RNAV approaches using FMS managed lateral and vertical guidance, the vertical flight path coded in the navigation database must be validated by the operator. Validation of the navigation database should ensure that the lAP is of an eligible type, and is correctly coded so that the aircraft in FINAL APP mode will fly a constant flight path angle from the FAF to the runway with the required obstacle margins. Different methods or processes can be used to validate the lAP that is coded in the navigation database. One method is to fly each approach in a simulator (or equivalent device), or with the aircraft when weather conditions are good. An lAP that is regularly and correctly flown in FINAL APP mode can be considered as validated.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
FCB-FCB23 P 1/8 03 APR 12
FLIGHT CREW BULLETINS
A318/A319/A320/A321
USE OF MANAGED GUIDANCE IN APPROACH AND NAV DATABASE VALIDATION
FLIGHT CREW OPERATING MANUAL
Another method is to use a dedicated software to read the navigation database diskette. The listing or display of the coded lAP is then assessed by comparing it with the approach chart. The airline should keep an up-to-date record of the lAPs that are approved for the use of FINAL APP mode. 2. IAP AND CODING REQUIREMENTS A number of FMGC coding guidance requirements have been identified, and must be considered, when performing navigation database validation for the use of managed guidance in approach. As an example, the following drawings show the coding of an VOR DME lAP (with the MAP before the runway), and the associated MCDU display. Refer to drawings below.
The final approach consists of a sequence of at least two waypoints. However, it more often consists of 3, or 4, waypoints. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB23 P 2/8 03 APR 12
FLIGHT CREW BULLETINS
A318/A319/A320/A321
USE OF MANAGED GUIDANCE IN APPROACH AND NAV DATABASE VALIDATION
FLIGHT CREW OPERATING MANUAL
In the above example, the 3 waypoints are the FACF, the FAF, and the MAP. Sometimes, the MAP is located at, or after, the runway threshold. We will see that it is important for the crew to identify the MAP position. Sometimes, a Step Down Fix (SDF) is added on the approach final descent, between the FAF and the MAP. The SDF is not necessarily identical to the waypoints published on the approach chart. The identification of the waypoints shown on the MCDU often differs from the identification shown on the approach chart. THE LATERAL F-PLN CODING REQUIREMENTS The FACF and the FAF must be aligned with the approach course. If the FACF and the FAF are collocated, the course change at the FAF should be small. A sharp turn would prevent the aircraft from overflying the FAF, and the final descent would start before the FAF, without the aircraft being established on the final approach course. For aircraft equipped with Honeywell FMS, approach procedures, including a Pl-CF Leg (PROC T displayed between 2 approach waypoints on the MCDU F-PLN page), are not permitted with AP or FD managed guidance. These approaches must be flown in selected guidance, using published approach chart and NAVAID raw data. THE VERTICAL F-PLN CODING REQUIREMENTS An altitude constraint must be coded at each approach waypoint. Any waypoint of the approach should not be common to a STAR or a VIA waypoint with different altitude constraints. Combining altitude constraint may lead to erroneous vertical flight path guidance. An AT or ABOVE constraint can be used for an SDF. When the MAP is located at, or before, the runway threshold, an FPA (≠ 0 °) must be coded at the MAP. or at the runway threshold (RW). This FPA will appear on the MCDU, between the MAP and the FAF, or any previous SDF in the final approach. When the MAP is located after the runway threshold, an FPA = 0 ° must be coded at the MAP. For these "old style lAP", with the MAP after the runway threshold, and depending on the position of the approach axis relative to the runway, FMGC guidance may start the final approach descent slightly before the FAF. In most cases, the crossing altitude difference at the FAF is not significant (less than 50 ft). But, sometimes, this difference may be higher. Therefore, as it is not acceptable for the use of FINAL APP mode, we recommend validating the lAP with a MAP after the runway threshold, either in a simulator (or equivalent device), or with the aircraft in good weather conditions. An FPA (≠ 0 °) must be coded for each SDF that is on the final approach descent. The MAP of an RNAV lAP must be located at the runway threshold.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB23 P 3/8 03 APR 12
FLIGHT CREW BULLETINS
A318/A319/A320/A321
USE OF MANAGED GUIDANCE IN APPROACH AND NAV DATABASE VALIDATION
FLIGHT CREW OPERATING MANUAL
Additional vertical requirements for RNAV approaches (applicable to FMS Honeywell and not applicable to FMS Honeywell R1A) The MAP of RNAV approaches must be located at the runway threshold. Whenever the FMGC identifies an lAP labelled RNAV, it constructs the vertical flight profile assuming that there is an altitude constraint at the MAP equals to the runway threshold plus 50 ft. If the MAP is located significantly before the runway threshold, the FMGC computes an incorrect vertical flight path, and will display a wrong vertical deviation indication (VDEV) on the PFD. Consequently, the MAP crossing altitude on the F-PLN page will be incorrect compared to the published value. As a result, an RNAV lAP with a MAP located before the runway threshold must not be validated to be flown with the full FMS managed mode FINAL APP. Note:
The approaches labelled "GPS" are not affected and can be flown in FINAL APP mode.
3. FLIGHT CREW PROCEDURES The SOP (Refer to PRO-NOR-SOP-19) for Non Precision and RNAV approaches are applicable. The following recommendations are provided to highlight specific vertical navigation aspects, when FINAL APP mode is used. As applicable, the crew should first check that the Airline has approved the approach for FINAL APP mode use. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB23 P 4/8 03 APR 12
FLIGHT CREW BULLETINS
A318/A319/A320/A321
USE OF MANAGED GUIDANCE IN APPROACH AND NAV DATABASE VALIDATION
FLIGHT CREW OPERATING MANUAL
3.1 APPROACH F-PLN VERIFICATION Before starting the approach, the crew must check the FMS F-PLN (on the MCDU, and on the ND in PLAN mode with the CSTR displayed), starting from the beginning of the STAR down to the runway and the missed approach procedure, and verify the profile against the published lAP chart. For the final approach procedure, the crew should check the: ‐ Approach course ‐ Waypoints and associated altitude constraints ‐ lAP must not include a Procedure Turn (PROC T indicated on the MCDU) ‐ Distance from the FAF to RW, or FAF to MAP ‐ Approach angle (shown on the MCDU line above the related waypoints): • If MAP. after the runway threshold: FPA = 0 ° at MAP • If MAP before or at runway threshold: FPA ≠ 0 ° at MAP • For each Step Down Fix, an FPA ≠ 0 ° must be defined ‐ lAP does not include a PI-CF leg (PROC displayed on the MCDU) ‐ MAP of an RNAV lAP must be located at the runway threshold. Note:
The MAP of a GPS lAP can be located before the runway threshold.
‐ Altitude at the MAP, or at the runway threshold: If the crossing altitude at MAP is not shown on the approach chart, crosscheck consistency with the distance to the runway and the approach angle. 3.2 LIMITATIONS TO APPROACH F-PLN MODIFICATIONS When performing an lAP, using NAV and FINAL APP modes, the active F-PLN, extracted from the navigation database, can be modified, provided the following limitations are observed: 1. F-PLN modifications: ‐ No lateral modification of the F-PLN from FACF (inclusive) to RW or to MAP. A modification is permitted before FACF, provided the resulting change in the flight path course is not so large that it prevents the aircraft from being laterally-stabilized on the final approach course before reaching the FAF. ‐ No altitude constraint modification from FACF to MAP. Even in case of a very low OAT, no altitude correction can be entered in this way. This may require that a minimum OAT be defined, so that the vertical flight path will clear obstacles with the required margin. This minimum OAT should be given to the crew, when appropriate. In the future, for RNAV approaches, the minimum OAT will be published on the approach chart itself.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB23 P 5/8 03 APR 12
FLIGHT CREW BULLETINS
A318/A319/A320/A321
USE OF MANAGED GUIDANCE IN APPROACH AND NAV DATABASE VALIDATION
FLIGHT CREW OPERATING MANUAL
‐ When the FAF is the TO waypoint, the FROM waypoint must not be cleared in an attempt to perform a DIR TO/INTERCEPT. ‐ To benefit from managed speed, and have a correct location of the DECEL point, it is recommended to enter VAPP as a SPD CSTR at FAF. 2. DIR TO... ‐ DIR TO FACF is permitted, provided the resulting change in flight path course at FACF is not so large that it prevents the aircraft from being laterally-stabilized on the final approach course before reaching the FAF. ‐ DIR TO FAF is permitted, provided the resulting change in flight path course at FAF is small. ‐ For aircraft with FMS 2: DIR TO/INTERCEPT TO FAF is permitted, provided the RADIAL IN corresponding to the final approach course (approach course + 180 °) is selected, and that the interception angle is not so large that it prevents the aircraft from being laterally-stabilized on the final approach course at the FAF. 3. Lateral F-PLN interception in HDG/TRK: ‐ F-PLN must be intercepted before the FACF, and the interception angle should not be so large that it prevents the aircraft from being laterally-stabilized on the final approach course before reaching the FAF, or ‐ Before FAF, at the latest, provided the interception angle is small. CAUTION
‐ Before arming NAV, check that the correct "TO" waypoint is displayed on the ND. ‐ The intercept path in HDG/TRK must not cause premature sequencing of the FAF. The FAF should be sequenced in NAV mode, when established on the final approach course.
4. Vertical F-PLN interception: ‐ The crew should manage the descent, so that the vertical F-PLN is intercepted before the FAF, at the latest. 3.3 APPROACH MONITORING Except for RNAV lAP, approach NAVAIDs should be tuned and the associated raw data should be displayed and actively-monitored. This active monitoring should include vertical navigation, using altimeter readings versus DME distances or the equivalent. For RNAV lAP, vertical navigation can be monitored by using the distance to the RW, or to the MAP displayed on the ND, and the altimeter reading. After passing the FAF, when stabilized on the final descent, the crew should check that the X-TRK and VDEV are correct, and that the FPV is consistent with the approach angle. When APPR is selected on the FCU, the crew must verify the: ‐ Correct FMA display (APP NAV green, FINAL blue) ‐ Correct TO waypoint on the ND 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB23 P 6/8 03 APR 12
FLIGHT CREW BULLETINS
A318/A319/A320/A321
USE OF MANAGED GUIDANCE IN APPROACH AND NAV DATABASE VALIDATION
FLIGHT CREW OPERATING MANUAL
‐ Blue descent arrow at FAF and the correct F-PLN ‐ Correct Vertical Flight Path deviation indication When passing the FAF, the crew must verify: ‐ Correct altitude indication ‐ Correct FMA display (FINAL APP green) ‐ Correct TO waypoint on the ND ‐ Correct blue track on the ND, armed for Missed Approach ‐ That the aircraft starts the descent and follows the correct lateral and vertical flight path. If HIGH ACCUR is lost during the approach, but active radio NAVAID monitoring confirms correct navigation, the approach can be continued in FINAL APP mode. Otherwise, the crew should revert to TRK/FPA mode to fly the aircraft with NAVAIDs raw data. The lAP must be discontinued, when one of the following warnings occurs: ‐ GPS PRIMARY LOST, if GPS accuracy is required ‐ NAV ACCUR DOWNGRAD, during an RNAV approach ‐ FM/GPS POS DISAGREE, if GPS is installed and is not deselected, and if no NAVAID raw data is available to revert to selected modes ‐ FM 1/FM 2 POS DIFF, unless NAVAID raw data is available to revert to selected modes. 3.4 CREW REPORTING The crew must report any lateral or vertical NAV guidance anomaly to their Flight Operations. The report must be fully-documented to enable further investigation and corrective actions: It should, therefore, include the following information: ‐ Approach designation and airport ‐ Aircraft type, MSN, GW, wind/temperature ‐ Navigation database cycle ‐ Pilot selections, FMA, ND, MCDU displays ‐ Description of anomaly, flight path ‐ DFDR/QAR reading.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
FCB-FCB23 P 7/8 03 APR 12
FLIGHT CREW BULLETINS
A318/A319/A320/A321
USE OF MANAGED GUIDANCE IN APPROACH AND NAV DATABASE VALIDATION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB23 P 8/8 03 APR 12
FLIGHT CREW BULLETINS AIRCRAFT HANDLING IN FINAL APPROACH
Intentionally left blank
FLIGHT CREW BULLETINS AIRCRAFT HANDLING IN FINAL APPROACH A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
FCB-FCB24-PLP PRELIMINARY PAGES TABLE OF CONTENTS Aircraft Handling in Final Approach........................................................................................................................ A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB24-PLP-TOC P 1/2 29 JUL 11
FLIGHT CREW BULLETINS AIRCRAFT HANDLING IN FINAL APPROACH A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB24-PLP-TOC P 2/2 29 JUL 11
FLIGHT CREW BULLETINS AIRCRAFT HANDLING IN FINAL APPROACH A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
AIRCRAFT HANDLING IN FINAL APPROACH Ident.: FCB-FCB24-00013125.0001001 / 31 MAR 11 Applicable to: ALL
REASON FOR ISSUE During the approach, with the A/THR active, Airbus recommended to set the thrust levers above the CL detent (but below the MCT detent), in exceptional circumstances, if the speed significantly dropped below VAPP. However this procedure is not trained and proved to have more drawbacks than advantages. Therefore, Airbus no longer recommends to use this procedure. The procedure is deleted from the operational documentation. If the A/THR performance is not satisfactory, the flight crew should take over, and control the thrust manually. GENERAL The purpose of this FCOM Bulletin is to highlight certain aspects of aircraft handling during final approach, and to illustrate that the feedback received from in-service experience merits further attention. Although approach in turbulence is part of this discussion, windshear in approach is not addressed here. For more details on the subjects of "Windshear in Approach" and "Operations in Windshear or Downburst Conditions", Refer to PRO-SUP-91-20. APPROACH STABILIZATION CRITERIA The prerequisite for a successful final approach and landing is to stabilize the aircraft on the final approach trajectory in pitch, thrust, airspeed, and bank angle. This signifies that the: ‐ Aircraft is established on the: • Final approach trajectory, and only minor heading corrections are necessary (except for indirect or curve approaches) to correct the effect of external conditions, acting on the roll axis • Final approach vertical flight path, and only minor pitch corrections are necessary to correct the effect of external conditions; ‐ The target speed is maintained on the desired descent path, with the appropriate thrust (not stabilized at idle). Airbus policy requires that stabilized conditions be reached at 1 000 ft Height Above Threshold in IMC, and 500 ft feet in VMC, and that they be kept down to the flare height. In turbulent conditions, there may be heading, pitch, and thrust corrections of such a magnitude that it could be difficult to determine when to consider the approach stabilization criteria as being lost. Thrust corrections, in particular with the A/THR ON, could lead engines to temporarily reduce thrust to idle, which may not be desirable close to the ground, if the aircraft level of energy is low.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
FCB-FCB24 P 1/4 29 JUL 11
FLIGHT CREW BULLETINS AIRCRAFT HANDLING IN FINAL APPROACH A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
The PNF callout for excessive deviation is certainly an indication for the PF to decide/determine if the approach becomes destabilized. However, the answer to this question is generally a matter of pilot judgement. The pilot must assess whether or not it is possible to return to nominal conditions early enough: That is, at the latest before flare initiation. If the pilot judges that it will not be possible to start the flare at the correct height with the correct attitude, sink rate, and thrust, or if the pilot starts to feel "out of the loop", then it is time to perform a go-around. PNF CALLOUT In approach, the PNF is expected to monitor the PFD and to make a callout, when some parameters are exceeded. The Airbus FCOM Standard Operating Procedures (Refer to PRO-SUP-91-20 and Refer to PRO-NOR-SOP-18 and Refer to PRO-NOR-SOP-19) state that a callout should be made, if: ‐ Speed becomes lower than the speed target -5 kt, or greater than the speed target +10 kt ‐ Pitch attitude becomes lower than 2.5 ° nose down, or greater than 10 ° nose up ‐ Bank angle becomes greater than 7 ° ‐ Descent rate becomes greater than 1 000 ft/min ‐ Excessive LOC or GLIDE deviation occurs (Refer to PRO-NOR-SOP-18 only). The suitable PF response would be to immediately take appropriate actions to control the exceeded parameter and evaluate whether stabilized conditions will be recovered early enough. Otherwise, a go-around must be initiated. The PF should acknowledge the PNF callout so that crew coordination remains effective. AIRCRAFT HANDLING ON THE LONGITUDINAL AXIS The pilot's objective, with respect to the longitudinal axis, is to control the airspeed and the vertical flight path. For thrust and speed control, it is recommended to use FMGS managed speed, in order to benefit from the minimum GS function. The A/THR is, in particular, best suited to tracking a moving target speed, when flying in managed speed mode. Statistically, the A/THR provides the best protection against airspeed excursions and its use is, therefore, recommended even in turbulent conditions, unless thrust variations become excessive. A/THR response to airspeed variations is the result of a design compromise between performance and comfort, and it is optimized when the AP is engaged. Therefore, in turbulent conditions and when flying manually, the pilot may sometimes find it to be too slow or lagging. If conditions are such that a large speed decrease with engines at idle is anticipated, then the PF may take over thrust manually to recover the speed target and continue the approach in manual thrust. It is not recommended to use the speedbrakes in the final approach. In final approach, the drag with the Landing Gear down is normally sufficient to cope with all kinds of situations, including a tailwind landing. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB24 P 2/4 29 JUL 11
FLIGHT CREW BULLETINS AIRCRAFT HANDLING IN FINAL APPROACH A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
The pilot's objective, with respect to vertical navigation, is to maintain a constant flight path angle down to the runway threshold, using the vertical deviation indication of an ILS, the FMGS VDEV indication, the indication of an external lighting system, or visual cues. However, when approaching flare height, the pilot's primary objective will progressively shift from vertical flight path control to safe pitch attitude and vertical speed, to start the flare in good conditions. The PF will primarily control the attitude and the vertical speed to perform a safe flare. If the vertical speed is too high, prior to starting the flare, the vertical deceleration that can be achieved during flare may be insufficient to avoid a hard landing. The aircraft may touch down with an excessive residual vertical speed and pitch rate, which may lead to bouncing and exposure to tailstrike. The pilot should also consider that the flare height might vary slightly from one aircraft type to another, depending on aircraft inertia. In the event of turbulence and wind gradient, pitch monitoring is of primary importance when close to the ground. The pilot should react promptly to any uncommanded pitch down tendency, to avoid ducking under, with a risk of premature touchdown. If vertical speed and pitch attitude become the primary objectives, the touchdown point might occur slightly further ahead on the runway, thereby reducing the available stopping distance. In the large majority of landings, and based on the pilot's judgement, this effect should be acceptable. However, in case of doubt, it is always best to perform a go-around. AIRCRAFT HANDLING ON THE LATERAL AXIS Generally speaking, lateral handling of fly-by-wire aircraft is conventional. But, in very gusty conditions, it is necessary to recall the principle of the flight control law in roll. With the sidestick, the pilot can order a roll rate up to a maximum of 15 °/s. However, the aerodynamic capacity of the roll surfaces, when fully deflected, is much higher: That is, up to about 40 °/s. This means that, if the aircraft is flying through turbulence that produces a roll rate of 25 °/s to the right, the aircraft still has the capacity to roll to the left at a rate of 15 °/s, with full sidestick command. This is more than what is necessary in the worst conditions. The sidestick's ergonomical design is such that the stop at full deflection is easily reached. This may give the pilot the impression that the aircraft is limited in roll authority, because there is a time delay before the pilot feels the result of his/her action. On conventional aircraft, due to the control wheel inertia, the pilot needs considerably more time to reach the flight control stop. The flight control system of Airbus fly-by-wire aircraft partially counteracts roll movements induced by the effect of gust, even with the sidestick in the neutral position. The PF must ensure that the overall corrective orders maintain the desired aircraft lateral axis. He/she will minimize lateral inputs and will resist applying sidestick order from one stop to the other. Every sidestick input is a roll rate demand, superimposed on the roll corrections already initiated by the fly-by-wire system. The pilot should only apply "Ionger-term" corrections as needed.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB24 P 3/4 29 JUL 11
FLIGHT CREW BULLETINS AIRCRAFT HANDLING IN FINAL APPROACH A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Before flare height, heading corrections should only be made with roll. As small bank angles are possible and acceptable close to the ground, only small heading changes can be envisaged. Otherwise, a go-around should be initiated. Use of rudder, combined with roll inputs, should be avoided, since this may significantly increase the pilot's lateral handling tasks. Rudder use should be limited to the "de-crab" maneuver in case of crosswind, while maintaining the wings level, with the sidestick in the roll axis. (Refer to the FCOM's SOP, for Crosswind Landing Techniques). SUMMARY In summary, the following are the main points addressed by this Bulletin: ‐ Strictly observe the approach stabilization criteria to decide whether to land, or to perform a go-around ‐ Promptly react to any pitch down at low height, to avoid ducking under ‐ Reach the flare height with the correct pitch attitude and sink rate ‐ In turbulent conditions, it is recommended to use the A/THR, unless the PF is not satisfied by the A/THR response ‐ Refrain from excessive sidestick roll activity. Order "Ionger-term" roll corrections ‐ Restrict rudder use to "de-crabbing" in crosswind.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
FCB-FCB24 P 4/4 29 JUL 11
FLIGHT CREW BULLETINS USE OF RUDDER ON TRANSPORT CATEGORY AIRPLANES
Intentionally left blank
FLIGHT CREW BULLETINS USE OF RUDDER ON TRANSPORT CATEGORY AIRPLANES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
FCB-FCB25-PLP PRELIMINARY PAGES TABLE OF CONTENTS Use of Rudder on Transport Category Airplanes....................................................................................................A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB25-PLP-TOC P 1/2 30 MAY 12
FLIGHT CREW BULLETINS USE OF RUDDER ON TRANSPORT CATEGORY AIRPLANES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB25-PLP-TOC P 2/2 30 MAY 12
FLIGHT CREW BULLETINS USE OF RUDDER ON TRANSPORT CATEGORY AIRPLANES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
USE OF RUDDER ON TRANSPORT CATEGORY AIRPLANES Ident.: FCB-FCB25-00013126.0001001 / 22 MAY 12 Applicable to: ALL
REASON FOR ISSUE On February 8th, 2002, the National Transportation Safety Board (NTSB), in cooperation with the French "Bureau Enquetes Accidents (BEA)", issued recommendations that aircraft manufacturers re-emphasize the structural certification requirements for the rudder and vertical stabilizer, showing how some maneuvers can result in exceeding design limits and even lead to structural failure. The purpose of this FCOM Bulletin is to re-emphasize proper operational use of the rudder, highlighting certification requirements and rudder control design characteristics. YAW CONTROL GENERAL In flight, yaw control is provided by the rudder, and directional stability is provided by the vertical stabilizer. The rudder and vertical stabilizer are sized to meet the two following objectives: ‐ Provide sufficient lateral control of the aircraft during crosswind takeoffs and landings, within the published crosswind limits (Refer to LIM-12-A Airport Operations) ‐ Provide positive aircraft control under conditions of engine failure and maximum asymmetric thrust, at any speed above VMCG (minimum control speed on ground). The vertical stabilizer and the rudder must be capable of generating sufficient yawing moments to maintain directional control of the aircraft. The rudder deflection, necessary to achieve these yawing moments, and the resulting sideslip angles can place significant aerodynamic loads on the rudder and on the vertical stabilizer. Both vertical stabilizer and rudder are designed to sustain loads as prescribed in the JAR/FAR 25 certification requirements which define several lateral loading conditions (maneuver, gust loads and asymmetrical loads due to engine failure) leading to a required level of structural strength. CERTIFICATION REQUIREMENTS For certification in accordance with JAR/FAR 25.351, loads on the stabilizer and the rudder are defined, considering yawing maneuvers as shown below, for a range of speeds from VMC (minimum control speed) to VD/MD (maximum design speed), from sea level up to maximum altitude, and over the full range of aircraft weights and Center of Gravity limits: 1. With the aircraft in unaccelerated and stabilized straight flight, the rudder pedal is suddenly displaced to the maximum available deflection at the current aircraft speed. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
FCB-FCB25 P 1/8 30 MAY 12
FLIGHT CREW BULLETINS USE OF RUDDER ON TRANSPORT CATEGORY AIRPLANES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2. With the rudder deflected as shown above, the aircraft yaws to the resulting overswing sideslip angle, and then stabilizes at a somewhat smaller steady-state slideslip angle.
3. With the airplane yawed to the steady-state (static) sideslip angle corresponding to the above rudder deflection, the certification regulations assume that the rudder pedal is released to neutral. Note:
Because the aircraft has natural yaw stability, returning the rudder to neutral will also result in returning the sideslip angle to neutral.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB25 P 2/8 30 MAY 12
FLIGHT CREW BULLETINS USE OF RUDDER ON TRANSPORT CATEGORY AIRPLANES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Certification yawing maneuver design
JAR/FAR 25 requires the above yawing maneuver to be analyzed over the full range of specified conditions. The most severe loads imposed on the vertical stabilizer and rudder are identified. The same analysis is performed for lateral gusts, rolling maneuvers and asymmetrical engine failure conditions. The most severe of all these cases and associated loads provides the design basis for the vertical stabilizer and rudder. The above loads define the limit loads according to JAR/FAR 25 requirements. These loads correspond to the maximum loads that may be expected in service. According to JAR/FAR 25 requirements, the ultimate loads are defined as the limit loads multiplied by a prescribed safety factor of 1.5 unless otherwise specified. The aircraft structure must be able to sustain limit loads without detrimental permanent deformation and ultimate loads without failure for at least 3 s. Higher loads could lead to structural failure.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB25 P 3/8 30 MAY 12
FLIGHT CREW BULLETINS USE OF RUDDER ON TRANSPORT CATEGORY AIRPLANES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
CAUTION
Sudden commanded full, or nearly full, opposite rudder movement against a sideslip can generate loads that exceed the limit loads and possibly the ultimate loads and can result in structural failure. This is true even at speeds below the maximum design maneuvering speed, VA.
Certification regulations do not consider the loads imposed on the structure when there is a sudden full, or nearly full, rudder movement that is opposite to the sideslip. RUDDER CONTROL The rudder surface is controlled by 3 actuators, commanded by a cable run from rudder pedals, to which the flight control input (yaw damping and turn coordination functions coming from the ELACs and the FACs) are added. The rudder travel limiter, controlled by the FACs, is designed to progressively reduce the available total rudder travel depending on aircraft speed. This provides sufficient yaw control within the entire flight envelope, including engine failure and maximum asymmetric thrust, limiting the lateral loads on the stabilizer and rudder so that they remain within the certification limits. Rudder travel is limited as a function of the aircraft speed, as shown below: ‐ At low speeds, the rudder deflection required to maneuver the aircraft in yaw is large, and so are the resulting pedal displacement and forces ‐ At high speeds, the rudder authority is limited but the gearing between the pedals and the rudder does not change. Therefore, less force will be required to achieve maximum available rudder deflection.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB25 P 4/8 30 MAY 12
FLIGHT CREW BULLETINS USE OF RUDDER ON TRANSPORT CATEGORY AIRPLANES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
As speed increases, the rudder deflection required by any yaw maneuver (eg, engine failure and maximum asymmetric thrust) decreases, and consequently, so do rudder pedal displacement and associated forces. Rudder pedal displacement is almost linearly proportional to rudder deflection.
Thus, to explain the two preceding graphs: The rudder pedal displacement and the resulting pedal forces required to achieve a given rudder deflection are independent from aircraft speed
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB25 P 5/8 30 MAY 12
FLIGHT CREW BULLETINS USE OF RUDDER ON TRANSPORT CATEGORY AIRPLANES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
‐ To start moving the rudder pedals from the neutral position, a minimum force of ± 9 daN must be applied ("breakout force") ‐ At low speeds, i.e. up to approximately 150 kt, maximum available rudder deflection (25 ° for the A320/A321 and 30 ° for the A318/A319) is obtained by moving the rudder pedals to their maximum travel which represents a 30 daN force applied on the pedals ‐ At higher speeds, for example at 350 kt, the maximum available rudder deflection is reduced to approximately 4 °. It is consequently obtained with less rudder pedal displacement which represents approximately a 13 daN force applied on the pedals (approximately 40 % of the maximum force to reach full pedal travel). OPERATIONAL RECOMMENDATIONS In order to avoid exceeding structural loads on the rudder and vertical stabilizer, the following recommendations must be observed. 1. The Rudder is Designed to Control the Aircraft, in the Following Circumstances 1.1 In Normal Operations, for Lateral Control: ‐ During the takeoff roll, when on ground, especially in crosswind conditions ‐ During landing flare with crosswind, for decrab purposes ‐ During the landing roll, when on ground. In these circumstances, large and even rapid rudder inputs may be necessary to maintain control of the aircraft. Rudder corrections should always be applied as necessary to obtain the appropriate aircraft response. On Airbus aircraft, the rudder control system includes a turn coordination function to achieve acceptable turn coordination. 1.2 To Counteract Thrust Asymmetry Full rudder authority can be used to compensate for the yawing moment of asymmetric thrust. Note:
At high speed (i.e. slats retracted), thrust asymmetry (eg. due to an engine failure) has relatively small effect on yaw control of the aircraft. The amount of rudder required to counter an engine failure and center the sideslip is small.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB25 P 6/8 30 MAY 12
FLIGHT CREW BULLETINS USE OF RUDDER ON TRANSPORT CATEGORY AIRPLANES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
1.3 In Some Other Abnormal Situations The rudder may also be used in such abnormal situations as: ‐ Loss of both yaw damper systems. The rudder may be used as deemed necessary, for turn coordination to prevent excessive sideslip ‐ Rudder trim runaway. The rudder may be used to return the rudder to neutral ‐ Landing with abnormal landing gear position. The rudder can be used for directional control on ground. In all of the above mentioned normal or abnormal circumstances, proper rudder maneuvers will not affect the aircraft's structural integrity. Note:
In the event of a rudder travel limit system failure, refer to the relevant RUDDER TRAVEL LIMIT FAULT procedure.
2. The Rudder Should Not be Used ‐ To induce roll, or ‐ To counter roll, induced by any type of turbulence. Whatever the airborne flight condition may be, aggressive, full or nearly full, opposite rudder pedal inputs must not be applied. Such inputs can lead to loads higher than the limit, and can result in structural damage or failure. The rudder travel limiter system is not designed to prevent structural damage or failure in the event of such rudder system inputs. Note:
Rudder pedal reversals must never be incorporated into airline policy, including so-called" aircraft defensive maneuvers" to disable or incapacitate hijackers.
As far as dutch roll is concerned, yaw damper action and natural aircraft damping are sufficient to adequately dampen dutch roll oscillations. The rudder should not be used to complement the yaw damper. Note:
Even if both yaw damper systems are lost, the rudder should not be used to dampen the dutch roll. Refer to the YAW DAMPER FAULT procedure.
3. Special Cases Recovery techniques from upset situations Proper use of the rudder, particularly during maneuvers intended to address upset recovery, are emphasized in the Airbus Training Program, supported by the industry-produced 1998 "UPSET RECOVERY TRAINING AID".
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
FCB-FCB25 P 7/8 30 MAY 12
FLIGHT CREW BULLETINS USE OF RUDDER ON TRANSPORT CATEGORY AIRPLANES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB25 P 8/8 30 MAY 12
FLIGHT CREW BULLETINS YAW DISTURBANCES DURING THE TAKEOFF ROLL
Intentionally left blank
FLIGHT CREW BULLETINS YAW DISTURBANCES DURING THE TAKEOFF ROLL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
FCB-FCB26-PLP PRELIMINARY PAGES TABLE OF CONTENTS Yaw Disturbances during the Takeoff Roll..............................................................................................................A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB26-PLP-TOC P 1/2 29 JUL 11
FLIGHT CREW BULLETINS YAW DISTURBANCES DURING THE TAKEOFF ROLL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB26-PLP-TOC P 2/2 29 JUL 11
FLIGHT CREW BULLETINS YAW DISTURBANCES DURING THE TAKEOFF ROLL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
YAW DISTURBANCES DURING THE TAKEOFF ROLL Ident.: FCB-FCB26-00013127.0001001 / 07 JUL 11 Applicable to: ALL
Various operators have reported occurrences of "unusual" yaw movement during the takeoff roll. The large majority of these events took place in extremely hot weather conditions. Flight crews have used such terms as "lateral jerk", lateral g-Ioad, or "yaw control perturbation", to describe these occurrences. Airbus has conducted extensive investigations, in order to fully understand the origin and cause of these events, and to take into account any contributing conditions, whether it be technical or external. DESCRIPTION OF THE OBSERVED EVENTS The most significant of these events, included the following characteristics: ‐ An initial sharp lateral disturbance, associated with short, but substantial, lateral acceleration and heading variation ‐ In most cases, the pilot took immediate action, with a sharp pedal deflection in the opposite direction, in order to correct the heading and the lateral deviation ‐ This induced a lateral acceleration peak, of approximately the same magnitude, in the opposite direction. The general characteristics of these events produce the typical DFDR traces, illustrated below:
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
FCB-FCB26 P 1/4 29 JUL 11
FLIGHT CREW BULLETINS YAW DISTURBANCES DURING THE TAKEOFF ROLL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
ANALYSIS OF THE EVENTS Simulation tools were specifically developed, in an attempt to reproduce the condition and assess the effects of such failure modes as: ‐ Sharp rudder deflection (mechanical) ‐ Sudden differential braking ‐ Sudden nosewheel movement ‐ Sudden thrust asymmetry None of these failure modes could reproduce and explain the typical traces that were observed on the DFDR. This led to the assumption that only external causes were at the root of these events. This assumption was confirmed, after Airbus experienced a similar event on a test aircraft, equipped with a more sophisticated flight test recording equipment (greater sampling rate than the DFDR). The data recorded onboard the aircraft during this event was used to estimate the profile of a wind variation, which could have generated the recorded lateral disturbance. This was done by two methods, which both led to the same result. It was found that wind profiles, having a magnitude of less than 15 kt, perfectly matched the simulation of the recorded flight parameters. All of these tests confirmed that the lateral perturbations were not caused by an aircraft system malfunction, but were always due to external lateral gusts. ORIGIN OF LATERAL GUSTS Different situations may create isolated lateral gusts. For example, the jet blast of another aircraft close to the active runway, or the wind between two buildings accelerated by "venturi" effect, may create such lateral gust effects. However, the most probable cause is the presence of thermals or thermal vortices that often develop in hot and dry countries. Sometimes, as these thermal streams get stronger, they create small whirlwinds referred to as "dust devils". AIRCRAFT RESPONSE AND HANDLING All aircraft can be affected by lateral disturbances and their response, in terms of lateral g, yaw acceleration, and heading variation will depend on the aircraft's aerodynamic characteristics, plus the yaw inertia combined with the dynamics of ground reactions. Generally speaking, it is easy to maintain the aircraft on the runway centerline via normal use of the rudder. The issue, in these events, is that the disturbance can be quite isolated, and sufficiently strong, to catch the pilot by surprise. During a takeoff in a gusty crosswind, the pilot may have to cope with the effect of lateral wind variations. In such cases, the pilot will readily control the aircraft on the runway centerline, throughout the takeoff roll, because the aircraft behaves as the pilot expects, and the pilot is prepared to act. In the reported events, the condition arose suddenly, during the takeoff roll, with very little, or no obvious turbulence. In such circumstances the pilot is less prepared for a such sudden lateral 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB26 P 2/4 29 JUL 11
FLIGHT CREW BULLETINS YAW DISTURBANCES DURING THE TAKEOFF ROLL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
disturbance; And analysis of these events has revealed that pilots had a tendency to overreact, by increasing rudder input, and consequently increasing the magnitude of the lateral disturbance. CONCLUSION The objective of this FCOM Bulletin is to inform flight crews that they may encounter such lateral disturbances, particularly in areas and in weather conditions where strong thermals have a tendency to develop. Pilots should, therefore, be prepared to react to these isolated disturbances by using the rudder normally, and avoiding excessive rudder input.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
FCB-FCB26 P 3/4 29 JUL 11
FLIGHT CREW BULLETINS YAW DISTURBANCES DURING THE TAKEOFF ROLL A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB26 P 4/4 29 JUL 11
FLIGHT CREW BULLETINS AUTOMATIC LANDING PERFORMANCE
Intentionally left blank
FLIGHT CREW BULLETINS AUTOMATIC LANDING PERFORMANCE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
FCB-FCB27-PLP PRELIMINARY PAGES TABLE OF CONTENTS Automatic Landing Performance............................................................................................................................. A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB27-PLP-TOC P 1/2 29 JUL 11
FLIGHT CREW BULLETINS AUTOMATIC LANDING PERFORMANCE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB27-PLP-TOC P 2/2 29 JUL 11
FLIGHT CREW BULLETINS AUTOMATIC LANDING PERFORMANCE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
AUTOMATIC LANDING PERFORMANCE Ident.: FCB-FCB27-00013128.0001001 / 02 MAR 11 Applicable to: ALL
REASON FOR ISSUE Abnormal automatic landing behaviors are periodically reported on some airports/runways with specific terrain profile before runway threshold, or specific runway profile. AUTOMATIC LANDING FLARE MODE All Airbus aircraft use similar FLARE modes for automatic landing. The FLARE mode is initiated at a given radio altitude (RA), which can be either advanced or delayed in function of the Rate Of Descent (ROD) - measured as a rate of change of RA with time. Once the FLARE mode is engaged, the flare is commenced by an open-loop elevator input (pre-command), which is adapted to the aircraft GW, CG and GS. The flare is then continued with a closed-loop signal to satisfy ROD and RA targets function of the horizontal distance (or time). The pitch demand given by the flare pre-command is modified by pitch demands in order to reduce the differences between the actual and the desired RA and ROD. The intent is to reduce both the ROD and the RA as a function of distance or time so that the aircraft touches down with a reasonable ROD in a reasonable distance (or time - typically 7 to 9 s). This is effectively what a pilot does during manual flare. As the ground approaches, pitch-up input is introduced to reduce the ROD; the importance of the input varies according to the pilot's perception of the rate at which the ground is approaching. AUTOMATIC LANDING CERTIFICATION REQUIREMENTS The automatic landing certification regulations are complex and impose many requirements on the system. Among performance requirements are limits on touch down vertical speed and touch down distance from runway threshold. These limits are expressed in term of probability to exceed ultimate values; for touch down vertical speed and distance these limits are: ‐ The probability to exceed a touch down vertical speed of 10 ft/s must be less than one per -6 million (10 ), ‐ The probability to touch down at a distance less than 60 m from the runway threshold or more -6 than 900 m must be less than one per million (10 ). There are similar requirements for the touch down lateral distance from the runway centerline, for the bank angle at touch down and lateral deviation during rollout. To demonstrate statistically compliance with these requirements, the aircraft manufacturers use a combination of flight tests and simulation tools and must cover the full range of GW, CG and winds in a range of pressure altitude up to the maximum certified altitude for automatic landing (Refer to the AFM). 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
FCB-FCB27 P 1/6 29 JUL 11
FLIGHT CREW BULLETINS AUTOMATIC LANDING PERFORMANCE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
The automatic landing system performance has been demonstrated during certification with CAT II/III ILS beams with a G/S from 2.5 ° to 3.15 °. There is no certification requirement to prove that the automatic landing system will perform as expected at all conceivable airports. Certification flight tests are performed on a limited number of airports equipped with a CAT II or CAT III ILS. However, the simulation tests must include specific unusual terrain profile before runway threshold and specific runway slope: ‐ Runway slope of ±0.8 % . ‐ 20 ft step before runway threshold ‐ Rising terrain slope of 12.5 ° followed by 60 m horizontal surface just before runway threshold. Airbus aircraft meet all these certification requirements. In addition, Airbus has assessed in simulation the effect of terrain/runway profiles of specific airports known to be somehow problematic ("special terrain/runway profile"). The appendix 8 of FAA AC 120-280 related to irregular terrain assessment as part of the CAT III operational evaluation gives the following background: "FAA type design approval of flight guidance systems provides for generic performance evaluation of autoland capability through simulation with reference terrain conditions, and flight testing at a few particular locations. This is to verify suitability of the design analysis. When an aircraft is type certificated for use of a flight guidance system, it is not the intent, nor is it practical that each model of aircraft be tested at each conceivable locations that it could potentially be used in operations ... While type design certification addresses generic system performance, specific operational review and approval of particular aircraft type/site autoland performance is necessary when minima are predicated on the use of autoland. This is especially important at airports with irregular pre-threshold terrain (e.g., cliffs, valleys, sea walls) in the area of final approach within approximately 1 500 ft of runway threshold." AUTOMATIC LANDING DISTANCE The automatic landing distance calculation uses a realistic airborne distance obtained from flight tests demonstrations - statistically determined as the mean touch down distance from runway threshold plus 3 times the standard variation of this distance -, which is then added to a ground distance calculated with maximum braking starting at the mean touchdown speed plus 3 times the standard variation of this speed. The combined airborne and ground distances are then multiplied by 1.15 to give the automatic landing distance. Refer to QRH Autoland. The required landing distance cannot be less than the manual landing distance multiplied by 1.67 (or 1.67 x 1.15 on wet runway) or the automatic landing distance, whichever is the highest. The airborne mean distance and its statistical variation is determined using data collected for the certification process. A special runway profile (for example hill top double slope) may lead to increase airborne distances.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB27 P 2/6 29 JUL 11
FLIGHT CREW BULLETINS AUTOMATIC LANDING PERFORMANCE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
EFFECT OF TERRAIN/RUNWAY PROFILE A higher ROD in the last part of the approach (due to terrain profile before runway threshold) will cause the flare mode to engage earlier than usual. A rising slope before the runway can cause the flare to engage higher, and the aircraft may temporarily float above the runway surface before the pitch is reduced to resume a gentle descent down to the runway leading to a long flare. If, in addition, the runway has a negative slope, the descent will be further prolonged. However, the system will always try to re-establish the aircraft on the flare profile. In general, runways sloping up are prone to produce firm landings whereas runways sloping down will tend to produce long flares. Double runway slope with hill top located in the touch down zone may significantly affect the statistical distribution of the touch down point, increasing sometimes the airborne distance. A flare is a dynamic maneuver, and flares are never exactly the same. To satisfy certification requirements, the RA signal is filtered to avoid irregular variations, and the aircraft reaction in pitch is limited in order to prevent over-reactions in the event of erroneous signal variations. The consequence of these requirements is a more sluggish response to variations in RA signal, which restricts the ability to cope with large variations in terrain/runway profile. OPERATIONAL DEMONSTRATION For the purpose of CAT II/III operational demonstration, the airline has to perform a number of automatic landings in good weather conditions on different runways, usually at their home base and main destinations. To determine if an airport/runway is eligible for CAT II/III operations, the Appendix 1 of JAR OPS 1.440 (h) requires that: 1. "Each aeroplane type/on-board equipment/runway combination must be verified by the completion of at least one approach and landing in Category II or better weather conditions, prior to commencing Category III operations. 2. For runways with irregular pre-threshold terrain or other foreseeable or known deficiencies, each aeroplane type/on-board equipment/runway combination must be verified by operations in Category I or better weather conditions, prior to commencing Category II or III operations". The appendix 8 of FAA AC 120-280 says: "At typical airports runways that are not considered to be "special terrain", the review and approval process usually consists of verifying the operator's report or performance for a small number of "Iine landings" using the flight guidance system in weather conditions better than those requiring use of CAT II or lower minima". Before deciding that an airport/runway is suitable for automatic landing, the operator must seek information on the local characteristics of the runway and verify that the airport is not listed as "special terrain" for CAT II/III operations (e.g., those listed for example in the CAT II/III Status on the FAA web site). 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB27 P 3/6 29 JUL 11
FLIGHT CREW BULLETINS AUTOMATIC LANDING PERFORMANCE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
For airports/runways that exhibit special characteristics (pre-threshold terrain, runway profile or a combination of both), a specific operational evaluation is generally necessary. This initial evaluation should consist in 4 to 6 automatic landings in typical wind conditions and representative LW to be performed by a CAT III qualified and experienced pilot (Airline technical pilot, senior training pilot, .... ). DFDR data need to be analyzed to verify that the automatic landing system performed adequately. Airbus may support the operator for this data analysis. This initial evaluation should be then complemented by the monitoring of typically 25 automatic landings in line operation. This evaluation program should be done with the agreement of the operational authorities using for example the guidelines from FAA AC 120-280 Appendix 8. AUTOMATIC LANDING IN CAT I OR BETTER WEATHER CONDITIONS Automatic landings need sometimes to be performed in CAT I or better weather conditions for flight crew training purpose or for operational evaluation/demonstration. Although the automatic landing system performance has been demonstrated during certification with CAT II/III ILS beams, automatic landing is possible on a CAT I ILS, or on a CAT II/III ILS when the ILS protection is not activated (Low Visibility Procedure not enforced), provided: ‐ The operator has checked that the ILS beam quality and the effect of the terrain profile before the runway have no adverse effect on autopilot guidance. For that, the operator should seek information on terrain discontinuities before runway threshold and runway slope. Information from other operators with the same aircraft type and airport authorities can also be used. ‐ The flight crew is aware that LOC or G/S beam fluctuations independent of the aircraft system may occur, and the PF is prepared to immediately disconnect the AP and to take the appropriate action, should unsatisfactory guidance occur. AUTOMATIC ROLLOUT ON CAT II RUNWAYS For CAT II operations there is no requirement on LOC beam quality for the rollout segment. Automatic rollout in CAT II operations on a runway that is not CAT III qualified remains under the crew responsibility. ‐ As LOC beam fluctuations independent of the aircraft system may occur, the PF should be prepared to take over directional control if the AP disconnects during rollout, or to immediately disconnect the AP if unsatisfactory rollout guidance occurs. AUTOMATIC LANDING ABOVE MLW For some Airbus models, the FCOM OVERWEIGHT LANDING procedure may indicate that automatic landing is certified up to the MLW but that flight tests have been performed successfully up to a higher LW. The FCOM states that in case of emergency, and under crew responsibility, an automatic landing may be performed up to this higher LW, provided the runway is approved for automatic landing. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
FCB-FCB27 P 4/6 29 JUL 11
FLIGHT CREW BULLETINS AUTOMATIC LANDING PERFORMANCE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
This means that Airbus has performed a number of automatic landings up to this higher LW for average conditions in term of CG, wind, and runway characteristics. The full range of conditions required by the certification requirements have not been assessed for LW higher than the MLW. However, the tests performed are sufficient to indicate that the possibility of an automatic landing is an option that the flight crew can consider in its decision making resulting from an emergency in particular operational situation. AUTOMATIC LANDING WITH OUT-OF-DATE ADIRS MAG VAR TABLE Some Airbus SA and LR aircraft continue to fly a number of years with ADIRS part numbers fitted with out-of-date magnetic variation tables. If the ADIRS magnetic variation differs by more than 2 ° or 3 ° (depending of aircraft type) compared to the airport current magnetic variation, the lateral performance of the automatic landing and rollout is significantly affected, which prevents from using the automatic landing system on these airports. Airbus publishes in the FCOM for each year, the list of airports where automatic landing is no more authorized with these ADIRS part numbers. AIRPORTS/RUNWAYS WITH "SPECIAL TERRAIN/RUNWAY PROFILE" The consequences of irregular terrain or runway profile on the automatic landing system performance can be quite variable. For example, the automatic landing RW 03 R in Johannesburg (JNB) had to be suspended for the Airbus SA until certification of a new standard of FMCG (refer to FCOM Limitation). Another example is RW 32 in Leeds (LBA) also with Airbus SA where the consequence of the runway profile is only a possibility of long flare. In this case an increase of the automatic landing distance of 300 m is sufficient to address the runway specificity.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
FCB-FCB27 P 5/6 29 JUL 11
FLIGHT CREW BULLETINS AUTOMATIC LANDING PERFORMANCE A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
FCB-FCB27 P 6/6 29 JUL 11
PERFORMANCE
Intentionally left blank
PERFORMANCE PRELIMINARY PAGES A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TABLE OF CONTENTS
PER-PLP PRELIMINARY PAGES TABLE OF CONTENTS
PER-LOD Loading PER-OPD Operating Data PER-THR Thrust Ratings PER-TOF Takeoff PER-FPL Flight Planning PER-CLB Climb PER-CRZ Cruise PER-HLD Holding PER-DES Descent PER-GOA Go Around PER-LDG Landing PER-OEI One Engine Inoperative
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-PLP-TOC P 1/2 18 SEP 12
PERFORMANCE PRELIMINARY PAGES A318/A319/A320/A321
TABLE OF CONTENTS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-PLP-TOC P 2/2 18 SEP 12
PERFORMANCE LOADING
Intentionally left blank
PERFORMANCE LOADING A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-LOD-PLP PRELIMINARY PAGES TABLE OF CONTENTS SUMMARY OF HIGHLIGHTS
PER-LOD-GEN GENERAL DEFINITIONS...........................................................................................................................................................A
PER-LOD-CGO CARGO LOADING GENERAL................................................................................................................................................................ A DESCRIPTION.........................................................................................................................................................B RESTRAINT SYSTEM.............................................................................................................................................C CARGO LOADING SYSTEM (If installed).............................................................................................................. D CARGO CAPACITY.................................................................................................................................................E CARGO DOOR OPERATION..................................................................................................................................F LOCATION OF SERVICE PANELS........................................................................................................................G
PER-LOD-FUL FUEL GENERAL INFORMATION......................................................................................................................................A REFUELING.............................................................................................................................................................B GROUND FUEL TRANSFER..................................................................................................................................C DEFUELING.............................................................................................................................................................D OVERWING GRAVITY REFUELING...................................................................................................................... E REFUELING WITH ONE ENGINE RUNNING........................................................................................................ F APU START/SHUTDOWN DURING REFUELING/DEFUELING............................................................................G USE OF MANUAL MAGNETIC INDICATORS (MMI)............................................................................................. H
PER-LOD-WBA WEIGHT AND BALANCE PER-LOD-WBA-LTS LOAD AND TRIM SHEET GENERAL................................................................................................................................................................ A DATA........................................................................................................................................................................B DESCRIPTION.........................................................................................................................................................C LOAD AND TRIM SHEET.......................................................................................................................................D
PER-LOD-WBA-FIT FUEL INDEX TABLES PER-LOD-WBA-FIT-10 FUEL INDEX TABLE GENERAL................................................................................................................................................................ A FUEL INDEX TABLE FOR INNER TANK...............................................................................................................B FUEL INDEX TABLE FOR OUTER TANK............................................................................................................. C FUEL INDEX TABLE FOR CENTER TANK........................................................................................................... D
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-LOD-PLP-TOC P 1/2 18 SEP 12
PERFORMANCE LOADING A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-LOD-PLP-TOC P 2/2 18 SEP 12
PERFORMANCE LOADING A318/A319/A320/A321
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title
Toc Index
ID
PER-LOD-WBA-FIT-10 FUEL INDEX TABLE FOR INNER TANK PER-LOD-WBA-FIT-10 FUEL INDEX TABLE FOR OUTER TANK PER-LOD-WBA-FIT-10 FUEL INDEX TABLE FOR CENTER TANK
B
1
Improvement of the fuel index table layout. Documentation update: Deletion of information.
C
2
Documentation update: Deletion of information. Improvement of the fuel index table layout.
D
3
Improvement of the fuel index table layout. Documentation update: Deletion of information.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Reason
PER-LOD-PLP-SOH P 1/2 18 SEP 12
PERFORMANCE LOADING A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-LOD-PLP-SOH P 2/2 18 SEP 12
PERFORMANCE LOADING A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
DEFINITIONS Ident.: PER-LOD-GEN-00001661.0001001 / 09 DEC 09 Applicable to: ALL
MANUFACTURER’S EMPTY WEIGHT (MEW) The weight of the structure, power plant, furnishings, systems and other items of equipment that are considered as integral part of the aircraft. It is essentially a “dry” weight, including only those fluids contained in closed systems (e.g. hydraulic fluid). OPERATIONAL EMPTY WEIGHT (OEW) The manufacturer’s weight empty plus the operator’s items i.e. the flight and cabin crew and their baggage, unusable fuel, engine oil, emergency equipment, toilet chemicals and fluids, galley structure, catering equipment, seats, documents etc. DRY OPERATING WEIGHT (DOW) The total weight of an aircraft ready for a specific type of operation excluding all usable fuel and traffic load. Operational Empty Weight plus items specific to the type of flight i.e. catering, newspapers, pantry equipment etc. TAKEOFF FUEL The weight of the fuel onboard at takeoff. OPERATING WEIGHT The weight obtained by addition of the operational empty weight and the takeoff fuel. TOTAL TRAFFIC LOAD The weight of the payload including cargo loads, passengers and passengers bags. ZERO FUEL WEIGHT (ZFW) The weight obtained by addition of the total traffic load and the dry operating weight. TAKEOFF WEIGHT (TOW) The weight at takeoff. It is equal to the addition of the zero fuel weight and takeoff fuel. TRIP FUEL The weight of the fuel necessary to cover the normal leg without reserves. LANDING WEIGHT The weight at landing. It is equal to takeoff weight minus trip fuel.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-LOD-GEN P 1/2 29 JUL 11
PERFORMANCE LOADING A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-LOD-GEN P 2/2 29 JUL 11
PERFORMANCE LOADING A318/A319/A320/A321
CARGO LOADING
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: PER-LOD-CGO-00001662.0002001 / 09 DEC 09 Applicable to: ALL
The aircraft has two lower deck cargo compartments : ‐ Forward cargo compartment, compartment 1. ‐ Aft cargo compartment, subdivided into compartments 3, 4 and 5. The main access doors to forward and aft compartments are hydraulically operated. A bulk cargo door gives additional access to the aft cargo compartment. It is manually operated. DESCRIPTION Ident.: PER-LOD-CGO-00001663.0001001 / 09 DEC 09 Applicable to: ALL
Each compartment is divided into sections, and is designed to be category D (for A320 and A319) or category C (A321, A319 and A320 ) as defined by FAR. A placard in each compartment indicates the maximum authorized gross weight. The compartments have separate lighting. RESTRAINT SYSTEM Ident.: PER-LOD-CGO-00001664.0001001 / 09 DEC 09 Applicable to: ALL
Divider nets subdivide the compartments to allow them to be partially loaded and to retain the bulk. Door nets which protect the doors from shifting cargo, must be used whenever the compartment contain cargo. CARGO LOADING SYSTEM (IF INSTALLED) Ident.: PER-LOD-CGO-00001665.0020001 / 09 DEC 09 Applicable to: ALL
A semi-automatic cargo loading system, which may be installed in forward and aft compartments, loads pallets and containers.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to D
PER-LOD-CGO P 1/6 29 JUL 11
PERFORMANCE LOADING A318/A319/A320/A321
CARGO LOADING
FLIGHT CREW OPERATING MANUAL
CARGO CAPACITY Ident.: PER-LOD-CGO-00001666.0003001 / 08 MAR 11 Applicable to: ALL
FULL BULK The maximum load capacity for each cargo compartment is as follows : ‐ Forward Compartment 1 : 3 402 kg (7 500 lb) ‐ Aft Compartment 3 : 2 426 kg (5 349 lb) Compartment 4 : 2 110 kg (4 652 lb) Compartment 5 : 1 497 kg (3 300 lb)
CARGO DOOR OPERATION Ident.: PER-LOD-CGO-A-NG00101 Applicable to: ALL Ident.: PER-LOD-CGO-A-00001667.0002001 / 17 MAR 11
NORMAL OPERATION OPENING On door ACCESS DOOR OPERATING HANDLE................................................................ RELEASE Push handle flap inward. DOOR........................................................................................................................ UNLOCK Move door operating handle downward (105 °) from LOCKED to UNLOCK position. On door service panel SERVICE PANEL ACCESS DOOR...............................................................................OPEN LEVER OF MANUAL SELECTOR VALVE...................................................HOLD ON OPEN The yellow hydraulic system is pressurized (YELLOW ELEC PUMP energized). Operation of the flight controls and PTU is inhibited. When the door is fully open (green light on the service panel is on) : LEVER OF MANUAL SELECTOR VALVE..............................................................RELEASE When released, the lever returns to the neutral position and shuts down the electric pump.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E to F →
PER-LOD-CGO P 2/6 29 JUL 11
PERFORMANCE LOADING A318/A319/A320/A321
CARGO LOADING
FLIGHT CREW OPERATING MANUAL
CLOSING On door service panel LEVER OF MANUAL SELECTOR VALVE.................................................HOLD ON CLOSE At first the lever locks in an intermediate position, maintaining a pre-set pressurization to prevent the door from dropping open. The operator can then move the lever to CLOSE and the door closes. When it is fully closed, the lever returns to the neutral position and shuts down the electric pump. Ensure that green indicator light goes off. On door DOOR............................................................................................................................. LOCK Immediately push the door operating handle upwards to the locked position. When the door is locked, the cargo doors view ports appear green, the CARGO door indication on ECAM extinguishes, and the handle flap mechanism locks the operating handle. On door service panel ACCESS DOOR...........................................................................................................CLOSE Ident.: PER-LOD-CGO-A-00001668.0002001 / 17 MAR 11
AUXILIARY OPERATION In case of an electrical failure or if the electric pump fails, the operator can open or close the doors by working the hand pump. HAND PUMP OPENING On door DOOR........................................................................................................................ UNLOCK Unlock the operating handle as if for normal operation. On door service panel SERVICE PANEL ACCESS DOOR...............................................................................OPEN LEVER OF MANUAL SELECTOR VALVE...................................................HOLD ON OPEN On ground service panel HAND PUMP........................................................................................................... OPERATE The door opens. When the door is fully open (green light on the service panel is on) : On door service panel LEVER OF MANUAL SELECTOR VALVE....................................................... RELEASE
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←F→
PER-LOD-CGO P 3/6 29 JUL 11
PERFORMANCE LOADING A318/A319/A320/A321
CARGO LOADING
FLIGHT CREW OPERATING MANUAL
HAND PUMP CLOSING On door service panel LEVER OF MANUAL SELECTOR VALVE.................................................HOLD ON CLOSE On ground service panel HAND PUMP........................................................................................................... OPERATE The door closes. On door service panel LEVER OF MANUAL SELECTOR VALVE..............................................................RELEASE Release when door is fully closed. On door DOOR............................................................................................................................. LOCK Lock the operating handle as for normal operation. On door service panel and ground service panel ACCESS DOORS.........................................................................................................CLOSE
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←F
PER-LOD-CGO P 4/6 29 JUL 11
PERFORMANCE LOADING A318/A319/A320/A321
CARGO LOADING
FLIGHT CREW OPERATING MANUAL
LOCATION OF SERVICE PANELS Ident.: PER-LOD-CGO-00001669.0002001 / 09 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
G→
PER-LOD-CGO P 5/6 29 JUL 11
PERFORMANCE LOADING A318/A319/A320/A321
CARGO LOADING
FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G
PER-LOD-CGO P 6/6 29 JUL 11
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
GENERAL INFORMATION Ident.: PER-LOD-FUL-A-NG00102 Applicable to: ALL Ident.: PER-LOD-FUL-A-00001670.0010001 / 17 MAR 11
USABLE FUEL VOLUME WING TANKS OUTER CELL INNER CELL 1 760 14 199
LITERS US GALLONS
464
CENTER TANK
TOTAL
8 250
24 209
2 180
6 395
3 751
Ident.: PER-LOD-FUL-A-00006117.0002001 / 17 MAR 11
USABLE FUEL VOLUME PER TANK
LITERS US GALLONS
WING TANKS OUTER CELL INNER CELL 1 760 13 849 464
3 659
LITERS US GALLONS
CENTER TANK 8 250
ACT 1
ACT 2
ACT 3
3 121
3 121
2 186
824
824
577
2 180
ACT 4 2 186
ACT 5 3 046
ACT 6 3 121
577
804
824
Ident.: PER-LOD-FUL-A-00006118.0002001 / 17 MAR 11
TOTAL USABLE FUEL VOLUME
LITERS US GALLONS
TOTAL without ACTs 23 859 6 303
TOTAL with 1 ACT
TOTAL with TOTAL with TOTAL with TOTAL with TOTAL with 2 ACTs 3 ACTs 4 ACTs 5 ACTs 6 ACTs
26 980
30 101
32 287
35 408
37 594
40 640
7 128
7 952
8 530
9 355
9 933
10 734
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
PER-LOD-FUL P 1/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
Ident.: PER-LOD-FUL-A-00001671.0009001 / 17 MAR 11
Ident.: PER-LOD-FUL-A-00001672.0005001 / 17 MAR 11
REFUELING ‐ During automatic refueling, fuel goes into the center tank and the outer cell of the wing tanks simultaneously. When the outer cell of the wing tank is full, fuel overflows into the inner cell. When the center tank is full, fuel overflows into the ACTs . During manual refueling, fill the wing tanks first, then the center tank, then the ACTs . ‐ With the tanks filled to the maximum capacity, there is enough space in each tank to allow for a 2 % thermal expansion of the fuel without its spilling through the vent system. ‐ Electrical transients (caused by switching among the APU, the external and the engine electrical supply) during automatic refueling may stop the process. If the automatic refueling process is stopped, it is necessary to re-enter the Preselected Fuel Quantity.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A→
PER-LOD-FUL P 2/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
Ident.: PER-LOD-FUL-A-00001673.0002001 / 09 DEC 09
REFUELING CONTROL PANEL
REFUELING Ident.: PER-LOD-FUL-B-NG00103 Applicable to: ALL Ident.: PER-LOD-FUL-B-00001674.0002001 / 17 MAR 11
PREPARATION ACCESS PLATFORM...................................................................................................IN POSITION SAFETY PRECAUTIONS........................................................................................................APPLY During refueling operations, ensure that: ‐ No HF transmission (including HF transmission via the HF DATA LINK pb) is performed ‐ The aircraft is properly bonded to the tanker ‐ The tanker and the aircraft are properly grounded. If suitable ground is not available, the aircraft can be bonded to the tanker only. Always connect the ground cable to the parking ground point (or to the tanker) before connecting it to the aircraft.In the cockpit, check that the PARK BRK is ON and that the ACCU PRESS has sufficient pressure. Do not refuel, if a fire or engine overheat warning is displayed. During refueling, do not operate the external lighting. 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← A to B →
PER-LOD-FUL P 3/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
Note:
For APU start/shutdown during refueling, Refer to PER-LOD-FUL APU START/SHUTDOWN DURING REFUELING/DEFUELING.
MAX REFUELING PRESSURE................................................................................50 PSI (3.5 bar) On refueling control panel: TEST...................................................................................................................................... LTS Lights on the panel come on. FUEL QTY and the PRESELECTED and ACTUAL displays show 8’s. TEST..................................................................................................................................HI.LVL HI LVL lights change state if the high level sensors and their circuits are serviceable. Ident.: PER-LOD-FUL-B-00001689.0001001 / 17 MAR 11
AUTOMATIC REFUELING REFUEL VALVES............................................................................CHECK NORM and GUARDED PRESELECTOR...........................................................................................................................SET MODE SELECT.................................................................................................................... REFUEL START REFUELING When the refueling is finished the END light comes on. ACTUAL QUANTITY.............................................................................................................. CHECK The actual quantity must be within 100 kg (220 lb) of the preselected quantity. MODE SELECT.................................................................................................OFF and GUARDED Ident.: PER-LOD-FUL-B-00001675.0001001 / 17 MAR 11
MANUAL REFUELING REFUEL VALVES..................................................................................................................... SHUT MODE SELECT.................................................................................................................... REFUEL REFUEL VALVES (tanks to be filled)...................................................................................... OPEN START REFUELING FUEL QTY..........................................................................................................................MONITOR When the contents of the tanks reach the required level : Corresponding REFUEL VALVES......................................................................................SHUT MODE SELECT.......................................................................................... OFF and GUARDED REFUEL VALVES................................................................................... NORM and GUARDED
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
PER-LOD-FUL P 4/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
GROUND FUEL TRANSFER Ident.: PER-LOD-FUL-00001690.0002001 / 17 MAR 11 Applicable to: ALL
On cockpit overhead FUEL panel PUMPS (of the tanks not to be defueled)................................................................................ OFF MODE SEL...............................................................................................................................MAN PUMPS (of the tank to be defueled).......................................................................................... ON if left wing and/or center tanks is (are) to be defueled : X FEED....................................................................................................................................... ON OPEN light comes on. On refueling control panel : REFUEL VALVES (of tanks not to be filled)..........................................................................SHUT REFUEL VALVES (of tanks to be filled)................................................................................OPEN MODE SELECT......................................................................................................... DEFUEL/XFR OPEN light comes on. FUEL QTY....................................................................................................................... MONITOR When the tank contents reach the required level : Corresponding REFUEL VALVES..........................................................................................SHUT MODE SELECT.............................................................................................. OFF and GUARDED OPEN light goes out. REFUEL VALVES.......................................................................................NORM and GUARDED Set cockpit FUEL panel to normal configuration. DEFUELING Ident.: PER-LOD-FUL-00001691.0005001 / 17 MAR 11 Applicable to: ALL
Note:
Defueling by suction is not possible
ACCESS PLATFORM.......................................................................................................IN POSITION
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C to D →
PER-LOD-FUL P 5/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
SAFETY PRECAUTIONS............................................................................................................APPLY During defueling operations, ensure that: ‐ No HF transmission (including HF transmission via the HF DATA LINK pb) is performed ‐ The aircraft is properly bonded to the tanker ‐ The tanker and the aircraft are properly grounded. If suitable ground is not available, the aircraft can be bonded to the tanker only. Always connect the ground cable to the parking ground point (or to the tanker) before connecting it to the aircraft. In the cockpit, check that the PARK BRK is ON and that the ACCU PRESS has sufficient pressure. Do not defuel, if a fire or engine overheat warning is displayed. During defueling, do not operate the external lighting. Note:
For APU start/shutdown during defueling, Refer to PER-LOD-FUL APU START/SHUTDOWN DURING REFUELING/DEFUELING.
MAX DEFUELING PRESSURE..................................................................................11 PSI (0.75 bar) On cockpit overhead FUEL panel: PUMPS...................................................................................................................................... OFF On refueling control panel: REFUEL VALVES................................................................................................................. NORM MODE SELECT (OPEN light comes on)...................................................................DEFUEL/XFR On cockpit overhead FUEL panel : MODE SEL...............................................................................................................................MAN PUMPS (of the tank(s) to be defueled)......................................................................................ON X FEED (OPEN light comes on)................................................................................................ ON FUEL QTY....................................................................................................................... MONITOR When tank contents reach required level Corresponding PUMPS............................................................................................................. OFF On refueling control panel: MODE SELECT (OPEN light goes out)..........................................................OFF and GUARDED REFUEL VALVES.......................................................................................NORM and GUARDED Set cockpit FUEL panel to normal configuration. OVERWING GRAVITY REFUELING Ident.: PER-LOD-FUL-00001676.0005001 / 17 MAR 11 Applicable to: ALL
Overwing gravity refueling is done at the refuel point in the top of each wing. Fuel is delivered directly into the outer cell from which the inner cell is filled by opening the intercell transfer valves. Fill center tank by transfer from the right wing tank (open the X FEED valve in case of transfer from the left wing tank). 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← D to E →
PER-LOD-FUL P 6/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
SAFETY PRECAUTIONS............................................................................................................APPLY Disembark all passengers. During refueling operations, ensure that: ‐ No HF transmission (including HF transmission via the HF DATA LINK pb) is performed ‐ The aircraft is properly bonded to the tanker ‐ The tanker and the aircraft are properly grounded. If suitable ground is not available, the aircraft can be bonded to the tanker only. Always connect the ground cable to the parking ground point (or to the tanker) before connecting it to the aircraft. Refer to Aircraft Maintenance Manual (AMM) 12– 11–28 PB 301 for detailed safety procedures Note:
For APU start/shutdown during refueling, Refer to PER-LOD-FUL APU START/SHUTDOWN DURING REFUELING/DEFUELING.
TRANSFER VALVES (on ECAM FUEL page)........................................................ CHECK POSITION If transfer valves closed: MODE SELECT (on the refuel control panel)............................................................... Check OFF FUEL/XFR VALVE 1/WING/L C/B (A10 on 49VU) and FUEL/XFR VALVE 2/WING/L C/B (M22 on 121VU).............................................................................. PULL for a minimum of 5 s then PUSH The refuel control panel door must be closed when the C/B’s are being pulled. FUEL/XFR VALVE 1/WING/R C/B (A11 on 49VU) and FUEL/XFR VALVE 2/WING/R C/B (M23 on 121VU).............................................................................. PULL for a minimum of 5 s then PUSH Intercell transfer valves will stay open until the next refuel selection. FUEL/XFR VALVE 1/WING/L and R C/B’s (A10 and A11 on 49VU), and FUEL/XFR VALVE 2/WING/L and R C/B’s (M22 and M23 on 121 VU).......................................................................................PULL The refuel control panel door must be closed when the C/B’s are being pulled. Then it could be opened for subsequent procedures. RH WING REFUELING PROCEDURE OVERWING REFUEL CAP.................................................................................................REMOVE REFUELING............................................................................................................................ START If the center tank is to be refueled: GROUND FUEL TRANSFER PROCEDURE................................................................... APPLY When the wing tank reaches the required level: * REFUELING....................................................................................................................STOP * OVERWING REFUEL CAP....................................................................................... INSTALL LH WING REFUELING PROCEDURE Perform the steps for RH wing refueling procedure marked * then: 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
PER-LOD-FUL P 7/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
FUEL/XFR VALVE 1/WING/L and R C/B’s (A10 and A11 on 49VU) and FUEL/XFR VALVE 2/WING/L and R C/B’s (M22 and M23 on 121VU)................................................................................... PUSH MODE SELECT................................................................................................... REFUEL then OFF Check on FUEL page that the intercell transfer valves close. Note:
The overwing refuel point is not at the highest point of the wing and therefore the wing tanks cannot be filled to full. REFUELING WITH ONE ENGINE RUNNING
Ident.: PER-LOD-FUL-00001677.0003001 / 29 MAR 12 Applicable to: ALL
‐ Refuel with one engine running only at airports where no external ground pneumatic power is available and only when APU is unserviceable. ‐ Only the RH fuel couplings can be used. ‐ Overwing gravity filling is not permitted. ‐ Disembark all passengers. ‐ Obtain airport authorization. The Airport Fire Department should standby at the aircraft during the entire refueling procedure. ‐ Point the aircraft into the wind at a location where the slope is negligible. Set the parking brake and check its pressure. Run engine n° 1 at ground idle with its generator connected. ‐ Do not start engine n° 2, do not shut down engine n° 1 or do not attempt to start the APU before all fueling operations have been completed. ‐ Position the fuel truck under the extremity of the right wing. Its pressure should not exceed 30 PSI. ‐ Follow manual refueling procedure. OPERATION MONITORING DURING THE ENTIRE REFUELING PROCEDURE : ‐ Monitor the fuel truck shut off valve. ‐ Be sure that the fueling company is keeping permanent control of the emergency fuel shut off device. ‐ Have a flight crew member in the cockpit monitoring all systems and the running engine. ‐ Have a qualified ground crew member at the fueling station to operate the refuel valve switches. ‐ Monitor the refueling closely and be prepared to close the refuel valves in order not to exceed the following fuel quantities : DENSITY (kg/l) L(R) WING (kg) CENTER (kg)
0.77 5 710 6 030
0.78 5 780 6 110
0.79 5 860 6 190
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← E to F →
0.8 5 930 6 270
0.81 6 005 6 350
0.82 6 080 6 430
0.83 6 160 6 500
PER-LOD-FUL P 8/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
FUEL
AFTER SECOND ENGINE START : Reset the 3DMCs in order to reinitialize the fuel used values : DMC 1 SPLY C/B (E11 on 49VU).................................................................................. PULL DMC 2 SPLY C/B (Q8 on 121 VU).................................................................................PULL DMC 3 SPLY C/B (Q9 on 121 VU).................................................................................PULL DMC 3 SPLY STBY (E10 on 49 VU)..............................................................................PULL After 5 s : All C/B’s....................................................................................................................PUSH Note:
The T.O MEMO does not appear automatically since one engine is kept running.
APU START/SHUTDOWN DURING REFUELING/DEFUELING Ident.: PER-LOD-FUL-00001678.0001001 / 09 DEC 09 Applicable to: ALL
APU starts or shutdowns are permitted during refuel/defuel procedures. If it is necessary to operate the APU, the limits that follow apply : a. An APU start is not permitted during a refuel/defuel procedure if the APU has failed to start or an automatic shutdown has occured b. A normal APU shutdown must be completed if a fuel spill has occured during the refuel defuel procedure.
USE OF MANUAL MAGNETIC INDICATORS (MMI) Ident.: PER-LOD-FUL-C-NG00104 Applicable to: ALL Ident.: PER-LOD-FUL-C-00001679.0007001 / 16 NOV 11
GENERAL Indicators are installed as follows: • Four in each wing tank: Three in the inner tank and one in the outer tank • One in the center tank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM ← F to H →
PER-LOD-FUL P 9/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
TO DETERMINE AIRCRAFT ATTITUDE Set ADIRS 1, 2, 3 to the NAV position. On the LH or RH MCDU, press MCDU MENU pushbutton. Select CFDS line key (LSK 4L). Select SYSTEM REPORT/TEST line key (LSK 5L). Select the line key adjacent to the FUEL indication. On the MCDU control panel, push the NEXT PAGE key to display the FUEL Main Menu second page. Select the line key adjacent to the INPUT PARAMETERS VALUES indication. Use the Table given on the next page to determine the equivalent number and letter from PITCH and ROLL data. Select RETURN line key (LSK 6L) until CFDS main menu appears. Press MCDU MENU pushbutton. PITCH
Minus 1.5 Minus 1.0 Minus 0.5 0.0 Plus 0.5 Plus 1.0 Plus 1.5
REF 1
ROLL
Minus 1.5 Minus 1.0 Minus 0.5 0.0 Plus 0.5 Plus 1.0 Plus 1.5
2 3 4 5 6 7
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H→
REF A B C D E F G
PER-LOD-FUL P 10/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
Note:
1. This procedure can only be used if: ‐ The PITCH and ROLL data is taken from the ADIRS (identified by an “A” after the PITCH and ROLL title). ‐ The PITCH data displayed for the LEFT, CTR, and RIGHT is no more or less than 0.1 of each other. ‐ The ROLL data displayed for the LEFT, CTR, and RIGHT is no more or less than 0.1 of each other. 2. The FQIS input parameters are not automatically updated. Use the NEXT PAGE control on the MCDU to cycle the pages to update the screen.
ACCESS PLATFORM...............................................................................................IN POSITION Ident.: PER-LOD-FUL-C-00001692.0001001 / 09 DEC 09
TO DETERMINE FUEL QUANTITY IN THE OUTER TANK MMI number 5......................................................................................... UNLOCK and WITHDRAW The crewmember must withdraw the MMI slowly until he feels the magnetic attraction between the rod and float magnets. Do not use force when withdrawing the MMI as this will disengage the float magnet from the rod magnet and bring the rod down onto the mechanical stop. ROD GRADUATION (which aligns with bottom wing surface).................................................READ MMI............................................................................................................. IN PLACE and LOCKED Use the table for the applicable aircraft wing side, aircraft attitude (grid square letter and number), and the MMI stick number 5, to find the volume of fuel in the outer tank (See below). Multiply the result by the specific gravity to find the fuel weight. Ident.: PER-LOD-FUL-C-00009657.0005001 / 29 MAR 12
TO DETERMINE FUEL QUANTITY IN THE WING TANK MMI (from number 4 to number 2).......................................................... UNLOCK and WITHDRAW The crewmember must slowly withdraw the MMI, until magnetic attraction is felt between the rod and float magnets. Do not use force when withdrawing the MMI, as this will disengage the float magnet from the rod magnet, and bring the rod down on to the mechanical stop. ROD GRADUATION (which aligns with bottom wing surface).................................................READ MMIs shall be withdrawn from number 4 to number 2 until one MMI measures fuel. MMI............................................................................................................. IN PLACE and LOCKED
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H→
PER-LOD-FUL P 11/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
Enter the table for the applicable aircraft wing side, aircraft attitude (grid square letter and number), and the applicable MMI stick number, to find the volume of fuel in the wing tank (See below). Multiply the result by the specific gravity to find the fuel weight. Ident.: PER-LOD-FUL-C-00001680.0003001 / 29 MAR 11
TO DETERMINE FUEL QUANTITY IN THE INNER TANK MMI (from number 4 to number 2).......................................................... UNLOCK and WITHDRAW The crewmember must withdraw the MMI slowly until he feels the magnetic attraction between the rod and float magnets. Do not use force when withdrawing the MMI as this will disengage the float magnet from the rod magnet and bring the rod down onto the mechanical stop. ROD GRADUATION (which aligns with bottom wing surface).................................................READ MMI............................................................................................................. IN PLACE and LOCKED MMIs shall be withdrawn from number 4 to number 2 until one MMI measures fuel. Use the table for the applicable aircraft wing side, aircraft attitude (grid square letter and number), and the applicable MMI stick number to find the volume of fuel in the inner tank (Refer to FCOM PER.LOD.FUL FUEL. C.USE OF MANUAL MAGNETIC INDICATORS (MMI) - WING TANKS). Multiply the result by the specific gravity to find the fuel weight. Ident.: PER-LOD-FUL-C-00009658.0001001 / 29 MAR 12
TO DETERMINE FUEL QUANTITY IN THE CENTER TANK CENTER TANK MMI............................................................................... UNLOCK and WITHDRAW The crewmember must withdraw the MMI slowly until he feels the magnetic attraction between the rod and float magnets. Do not use force when withdrawing the MMI as this will disengage the float magnet from the rod magnet and bring the rod down onto the mechanical stop. ROD GRADUATION (which aligns with bottom wing surface).................................................READ MMI............................................................................................................. IN PLACE and LOCKED Use the table for the center tank, and for the applicable aircraft attitude (grid square letter and number) to find the volume of fuel in the center tank (See below). Multiply the result by the specific gravity to find the fuel weight.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H→
PER-LOD-FUL P 12/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
Ident.: PER-LOD-FUL-C-00001681.0004001 / 17 MAR 11
WING TANKS (LITERS)
* **
GRID SQUARE LETTER GRID SQUARE NUMBER
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H→
PER-LOD-FUL P 13/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
*
GRID SQUARE LETTER
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H→
PER-LOD-FUL P 14/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
**
GRID SQUARE NUMBER
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H→
PER-LOD-FUL P 15/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
* **
GRID SQUARE LETTER GRID SQUARE NUMBER
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H→
PER-LOD-FUL P 16/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
* **
GRID SQUARE LETTER GRID SQUARE NUMBER
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H→
PER-LOD-FUL P 17/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
Ident.: PER-LOD-FUL-C-00006125.0004001 / 17 MAR 11
WING TANKS (U.S. GAL.)
(*)
GRID SQUARE LETTER
(**) GRID SQUARE NUMBER
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H→
PER-LOD-FUL P 18/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
(*)
GRID SQUARE LETTER
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H→
PER-LOD-FUL P 19/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
(**) GRID SQUARE NUMBER
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H→
PER-LOD-FUL P 20/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
(*)
GRID SQUARE LETTER
(**) GRID SQUARE NUMBER
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H→
PER-LOD-FUL P 21/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
(*)
GRID SQUARE LETTER
(**) GRID SQUARE NUMBER
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H→
PER-LOD-FUL P 22/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
Ident.: PER-LOD-FUL-C-00001682.0001001 / 16 NOV 11
CENTER TANK (LITERS)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H→
PER-LOD-FUL P 23/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321
FUEL
FLIGHT CREW OPERATING MANUAL
* **
GRID SQUARE LETTER GRID SQUARE NUMBER
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H
PER-LOD-FUL P 24/24 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WEIGHT AND BALANCE - LOAD AND TRIM SHEET
GENERAL Ident.: PER-LOD-WBA-LTS-00001685.0001001 / 09 DEC 09 Applicable to: ALL
This chart allows the determination of Aircraft CG location (MAC) function of dry operating weight, pantry adjustment, cargo loads, passengers and fuel on board. The operational limits shown on the load and trim sheet are more restrictive than the certified limits because error margins have been taken into account. The load and trim sheet needs to be updated when : ‐ a modification which changes the aircraft certified limits is included or ‐ a modification (cabin layout, cargo arrangement ...) which influences the operational limits is made. It is the airline responsibility to define a load and trim sheet and to keep it up to date. Refer to PER-LOD-WBA-LTS DESCRIPTION is a description of the Load and Trim Sheet utilization (Refer to PER-LOD-WBA-LTS LOAD AND TRIM SHEET), for a typical passenger arrangement. Refer to customized load and trim sheet for preparing a revenue flight. DATA Ident.: PER-LOD-WBA-LTS-00001686.0002001 / 12 FEB 11 Applicable to: ALL
Dry Operating Weight = 42 500 kg and CG = 27 % (H-arm = 18.93 m) Deviation or adjustment = + 100 kg in zone F Cargo = 5 500 kg with the following distribution: cargo 1 = 2 000 kg; cargo 3 = 1 500 kg; cargo 4 = 1 500 kg; cargo 5 = 500 kg Passengers = 145 PAX with the following distribution: cabin OA = 50; cabin OB = 55; cabin OC = 40 Ramp Fuel = 13 200 kg; Taxi Fuel = 200 kg; Fuel Density = 0.785 kg/l
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
PER-LOD-WBA-LTS P 1/4 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WEIGHT AND BALANCE - LOAD AND TRIM SHEET
DESCRIPTION Ident.: PER-LOD-WBA-LTS-00001687.0002001 / 12 FEB 11 Applicable to: ALL
a. b. c. d. e. f.
Enter Master data in (1). Compute Dry Operating Weight Index using the formula indicated in (2) and report in (3). Dry Operating Index = 53.4. Enter weight deviation or adjustment in (4) and read corresponding index variation in (5): +1.43. Calculate corrected index and report in (6): 54.83. Enter master data in table (7) and determine Zero Fuel Weight: 60 280 kg and Takeoff Weight: 73 280 kg. g. Enter cargo weight and passenger number per compartment in (8). h. Enter index scale (9) with corrected index and proceed through cargo and passenger scales (10). i. From the final point draw a vertical line which intersects (12) the zero fuel weight horizontal line (11). j. Check if the intersection point is within the Zero Fuel Weight operational limits, if not rearrange cargo loading. k. Read in table (13) the fuel index correction corresponding to Ramp Fuel Weight (13 200 kg) and Fuel Density (0.785 kg/l). This example will be continued assuming the FUEL INDEX = –2 was found. Carry in fuel scale (14). l. From this point draw a vertical line which intersects (16) the takeoff weight horizontal line (15). m. Check if the intersection point is within the Takeoff Weight operational limits. n. Read zero fuel weight and CG position: 32.7 % and fill in table (17). o. Read takeoff CG position: 30.5 % and fill in table (18). CAUTION
Note:
If there is no customized trim sheet for your airline in this section, do not use the information enclosed herein for day to day operation as margins and load CG vary with cabin and cargo layout.
When referring to CG lower than 27 %, an operational margin is taken into account. It is the reason why performance at forward CG (lower than 25 %) must be used for operational CG lower than 27 %.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
PER-LOD-WBA-LTS P 2/4 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WEIGHT AND BALANCE - LOAD AND TRIM SHEET
LOAD AND TRIM SHEET Ident.: PER-LOD-WBA-LTS-00001688.0002001 / 23 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D→
PER-LOD-WBA-LTS P 3/4 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WEIGHT AND BALANCE - LOAD AND TRIM SHEET
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D
PER-LOD-WBA-LTS P 4/4 03 APR 12
PERFORMANCE LOADING A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WEIGHT AND BALANCE - FUEL INDEX TABLES
FUEL INDEX TABLE GENERAL Ident.: PER-LOD-WBA-FIT-10-00012775.0002001 / 08 FEB 11 Applicable to: ALL
The fuel index table has been established assuming a fuel distribution in accordance with refuel distribution given in section Refer to PER-LOD-FUL-A GENERAL INFORMATION - REFUELING of this volume. If after refueling the actual distribution deviates from the chart values, the actual and the trim sheet CG will show a discrepancy. The following tables allow to determine the fuel index taking into account the actual fuel quantity in each tank. To determine the actual takeoff CG enter the tables with the actual fuel quantities in each tank, read the fuel index for each tank and use their sum to enter the trim sheet. Check that the actual CG is inside the operational limits. If the CG is outside the limits transfer fuel to achieve a distribution in accordance with the chart or rearrange the load. Note:
DATA:
These tables are valid only when used with the following formula for the index: I = W × (H-arm – 18.85)/1 000 + K or I = [(CG – 25) × W × 0.000042] + K (Weight in kg, H-arm in m) Fuel in left inner fuel tank = 4 500 kg Fuel in right inner fuel tank = 4 500 kg Fuel in left outer fuel tank = 200 kg Fuel in right outer fuel tank = FULL Fuel in center tank = 0 kg
Inner tank Outer tank Center tank TOTAL
Left Right Left Right
Weight 4 500
-
Index 3
4 500
-
3
200 691
0 +
0 9 891
2 0
-
4
Enter the trim sheet with a fuel index of –4
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-LOD-WBA-FIT-10 P 1/4 18 SEP 12
PERFORMANCE LOADING A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WEIGHT AND BALANCE - FUEL INDEX TABLES
FUEL INDEX TABLE FOR INNER TANK Ident.: PER-LOD-WBA-FIT-10-00012776.0001001 / 25 JUL 12 Applicable to: ALL 1
Note:
These tables are valid only when used with the following formulae for the index: I=W×(H-arm–18.85)/1 000+K or I=[(CG–25)×W×0.000042]+K (Weight in kg, H-arm in m) Weight 500 1 000 1 500 2 000 2 500 3 000 3 500 4 000 4 500 5 000 FULL
Index -1 -1 -2 -2 -2 -3 -3 -3 -3 -3 -2
FUEL INDEX TABLE FOR OUTER TANK Ident.: PER-LOD-WBA-FIT-10-00012777.0001001 / 25 JUL 12 Applicable to: ALL 2
Note:
These tables are valid only when used with the following formulae for the index: I=W×(H-arm–18.85)/1 000+K or I=[(CG–25)×W×0.000042]+K (Weight in kg, H-arm in m) Weight 250 500 FULL
Index 1 1 2
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B to C
PER-LOD-WBA-FIT-10 P 2/4 18 SEP 12
PERFORMANCE LOADING A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WEIGHT AND BALANCE - FUEL INDEX TABLES
FUEL INDEX TABLE FOR CENTER TANK Ident.: PER-LOD-WBA-FIT-10-00012778.0001001 / 25 JUL 12 Applicable to: ALL 3
Note:
These tables are valid only when used with the following formulae for the index: I=W×(H-arm–18.85)/1 000+K or I=[(CG–25)×W×0.000042]+K (Weight in kg, H-arm in m) Weight 500 1 000 1 500 2 000 2 500 3 000 3 500 4 000 4 500 5 000 5 500 6 000 FULL
Index -1 -1 -2 -3 -3 -4 -5 -6 -7 -7 -8 -9 -10
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D
PER-LOD-WBA-FIT-10 P 3/4 18 SEP 12
PERFORMANCE LOADING A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
WEIGHT AND BALANCE - FUEL INDEX TABLES
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-LOD-WBA-FIT-10 P 4/4 18 SEP 12
PERFORMANCE OPERATING DATA
Intentionally left blank
PERFORMANCE OPERATING DATA A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-OPD-PLP PRELIMINARY PAGES TABLE OF CONTENTS
PER-OPD-GEN GENERAL CONVERSIONS - IAS . MACH - TAS . MACH - SAT . TAT..................................................................................A INTERNATIONAL STANDARD ATMOSPHERE (ISA)............................................................................................B CONVERSIONS - QNH - QFE - PRESSURE ALTITUDE......................................................................................C CONVERSIONS QFE HPA - IN. HG - FT..............................................................................................................D WIND COMPONENTS (FOR TAKEOFF AND LANDING)......................................................................................E ALTITUDE TEMPERATURE CORRECTION.......................................................................................................... F
PER-OPD-CON GROUND DISTANCE/AIR DISTANCE CONVERSION PER-OPD-CON-AEO ALL ENGINES OPERATIVE GENERAL................................................................................................................................................................ A M.78......................................................................................................................................................................... B LONG RANGE SPEED UP TO FL270................................................................................................................... C LONG RANGE SPEED ABOVE FL270.................................................................................................................. D
PER-OPD-CON-OEI ONE ENGINE INOPERATIVE GENERAL................................................................................................................................................................ A LONG RANGE SPEED........................................................................................................................................... B FIXED SPEEDS.......................................................................................................................................................C
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-OPD-PLP-TOC P 1/2 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-OPD-PLP-TOC P 2/2 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
CONVERSIONS - IAS . MACH - TAS . MACH - SAT . TAT Ident.: PER-OPD-GEN-00001962.0001001 / 23 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-OPD-GEN P 1/10 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
INTERNATIONAL STANDARD ATMOSPHERE (ISA) Ident.: PER-OPD-GEN-00001963.0001001 / 09 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
PER-OPD-GEN P 2/10 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
CONVERSIONS - QNH - QFE - PRESSURE ALTITUDE Ident.: PER-OPD-GEN-00001964.0001001 / 09 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
PER-OPD-GEN P 3/10 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
CONVERSIONS QFE HPA - IN. HG - FT Ident.: PER-OPD-GEN-00001965.0001001 / 08 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D→
PER-OPD-GEN P 4/10 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D
PER-OPD-GEN P 5/10 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
WIND COMPONENTS (FOR TAKEOFF AND LANDING) Ident.: PER-OPD-GEN-00001966.0001001 / 08 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E→
PER-OPD-GEN P 6/10 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E
PER-OPD-GEN P 7/10 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
ALTITUDE TEMPERATURE CORRECTION Ident.: PER-OPD-GEN-00001967.0001001 / 12 FEB 11 Applicable to: ALL
FOR HIGH ALTITUDE USE
FOR LOW ALTITUDE USE Values to be added by the pilot to minimum promulgated heights/altitude (ft) Airport Temperature °C 0
200 20
Height above the elevation of the altimeter setting source (feet) 300 400 500 1 000 2 000 3 000 4 000 5 000 20 30 30 60 120 170 230 280 Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F→
PER-OPD-GEN P 8/10 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
Airport Temperature °C -10 -20 -30 -40 -50
200 20 30 40 50 60
Continued from the previous page Height above the elevation of the altimeter setting source (feet) 300 400 500 1 000 2 000 3 000 4 000 5 000 30 40 50 100 200 290 390 490 50 60 70 140 280 420 570 710 60 80 100 190 380 570 760 950 80 100 120 240 480 720 970 1 210 90 120 150 300 590 890 1 190 1 500
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←F
PER-OPD-GEN P 9/10 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-OPD-GEN P 10/10 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GROUND DISTANCE/AIR DISTANCE CONVERSION - ALL ENGINES OPERATIVE
GENERAL Ident.: PER-OPD-CON-AEO-00001657.0001001 / 23 FEB 11 Applicable to: ALL
The ground distance/air distance conversion tables show the air distance for a given ground distance due to the influence of the wind. The Tables are given for : ‐ M .78 ‐ Long range speed. M.78 Ident.: PER-OPD-CON-AEO-00001658.0001001 / 28 JAN 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
PER-OPD-CON-AEO P 1/4 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321
GROUND DISTANCE/AIR DISTANCE CONVERSION - ALL ENGINES OPERATIVE
FLIGHT CREW OPERATING MANUAL
LONG RANGE SPEED UP TO FL270 Ident.: PER-OPD-CON-AEO-00001659.0001001 / 28 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
PER-OPD-CON-AEO P 2/4 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321
GROUND DISTANCE/AIR DISTANCE CONVERSION - ALL ENGINES OPERATIVE
FLIGHT CREW OPERATING MANUAL
LONG RANGE SPEED ABOVE FL270 Ident.: PER-OPD-CON-AEO-00001660.0001001 / 09 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D
PER-OPD-CON-AEO P 3/4 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321
GROUND DISTANCE/AIR DISTANCE CONVERSION - ALL ENGINES OPERATIVE
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-OPD-CON-AEO P 4/4 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GROUND DISTANCE/AIR DISTANCE CONVERSION - ONE ENGINE INOPERATIVE
GENERAL Ident.: PER-OPD-CON-OEI-00004074.0001001 / 09 DEC 09 Applicable to: ALL
The ground distance/air distance conversion tables are used to calculate the air distance for a given ground distance due to the influence of the wind. Tables are given for : ‐ LONG RANGE SPEED ‐ FIXED SPEEDS
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-OPD-CON-OEI P 1/4 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321
GROUND DISTANCE/AIR DISTANCE CONVERSION - ONE ENGINE INOPERATIVE
FLIGHT CREW OPERATING MANUAL
LONG RANGE SPEED Ident.: PER-OPD-CON-OEI-00001960.0001001 / 09 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
PER-OPD-CON-OEI P 2/4 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321
GROUND DISTANCE/AIR DISTANCE CONVERSION - ONE ENGINE INOPERATIVE
FLIGHT CREW OPERATING MANUAL
FIXED SPEEDS Ident.: PER-OPD-CON-OEI-00001961.0001001 / 09 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
PER-OPD-CON-OEI P 3/4 29 JUL 11
PERFORMANCE OPERATING DATA A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
GROUND DISTANCE/AIR DISTANCE CONVERSION - ONE ENGINE INOPERATIVE
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-OPD-CON-OEI P 4/4 29 JUL 11
PERFORMANCE THRUST RATINGS
Intentionally left blank
PERFORMANCE THRUST RATINGS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-THR-PLP PRELIMINARY PAGES TABLE OF CONTENTS
PER-THR-GEN GENERAL GENERAL................................................................................................................................................................ A
PER-THR-MTO MAXIMUM TAKEOFF DEFINITION............................................................................................................................................................. A MAXIMUM TAKEOFF.............................................................................................................................................. B
PER-THR-MGA MAXIMUM GO AROUND DEFINITION............................................................................................................................................................. A MAXIMUM GO AROUND........................................................................................................................................ B
PER-THR-FLX FLEXIBLE TAKEOFF DEFINITION............................................................................................................................................................. A FLEXIBLE TAKEOFF...............................................................................................................................................B
PER-THR-MCT MAXIMUM CONTINUOUS DEFINITION............................................................................................................................................................. A MAXIMUM CONTINUOUS...................................................................................................................................... B
PER-THR-MCL MAXIMUM CLIMB DEFINITION............................................................................................................................................................. A MAXIMUM CLIMB....................................................................................................................................................B
PER-THR-MCR MAXIMUM CRUISE DEFINITION............................................................................................................................................................. A MAXIMUM CRUISE................................................................................................................................................. B
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-THR-PLP-TOC P 1/2 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-THR-PLP-TOC P 2/2 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: PER-THR-GEN-00004079.0001001 / 28 FEB 11 Applicable to: ALL
The thrust rating charts have been established for: ‐ Maximum takeoff ‐ Maximum go around ‐ Flexible takeoff ‐ Maximum continuous ‐ Maximum climb ‐ Maximum cruise
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-THR-GEN P 1/2 29 JUL 11
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-THR-GEN P 2/2 29 JUL 11
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
MAXIMUM TAKEOFF
FLIGHT CREW OPERATING MANUAL
DEFINITION Ident.: PER-THR-MTO-00001968.0001001 / 01 MAR 11 Applicable to: ALL
It is the maximum thrust certified for takeoff and is normally limited to five minutes. This time is extended to ten minutes for engine out contingency, as authorized by the approved AFM.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-THR-MTO P 1/4 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
MAXIMUM TAKEOFF
FLIGHT CREW OPERATING MANUAL
MAXIMUM TAKEOFF Ident.: PER-THR-MTO-00001969.0017001 / 28 JAN 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
PER-THR-MTO P 2/4 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
MAXIMUM TAKEOFF
FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
PER-THR-MTO P 3/4 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
MAXIMUM TAKEOFF
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-THR-MTO P 4/4 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
MAXIMUM GO AROUND
FLIGHT CREW OPERATING MANUAL
DEFINITION Ident.: PER-THR-MGA-00001971.0001001 / 23 FEB 11 Applicable to: ALL
It is the maximum permissible thrust during go-around.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-THR-MGA P 1/4 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
MAXIMUM GO AROUND
FLIGHT CREW OPERATING MANUAL
MAXIMUM GO AROUND Ident.: PER-THR-MGA-00001972.0024001 / 28 JAN 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
PER-THR-MGA P 2/4 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
MAXIMUM GO AROUND
FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
PER-THR-MGA P 3/4 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
MAXIMUM GO AROUND
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-THR-MGA P 4/4 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
FLEXIBLE TAKEOFF
FLIGHT CREW OPERATING MANUAL
DEFINITION Ident.: PER-THR-FLX-00001973.0001001 / 23 FEB 11 Applicable to: ALL
It is a reduced takeoff thrust as compared to the maximum permissible. The related N1 is calculated as a function of the flexible temperature entered in the FMGS MCDU. The flexible temperature is a function of the aircraft weight and environmental conditions. It guarantees that the regular performance requirements are met.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-THR-FLX P 1/4 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
FLEXIBLE TAKEOFF
FLIGHT CREW OPERATING MANUAL
FLEXIBLE TAKEOFF Ident.: PER-THR-FLX-00001974.0008001 / 23 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
PER-THR-FLX P 2/4 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
FLEXIBLE TAKEOFF
FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←B
PER-THR-FLX P 3/4 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
FLEXIBLE TAKEOFF
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-THR-FLX P 4/4 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
MAXIMUM CONTINUOUS
FLIGHT CREW OPERATING MANUAL
DEFINITION Ident.: PER-THR-MCT-00001975.0001001 / 28 FEB 11 Applicable to: ALL
It is the maximum thrust certified for continuous use. This rating should be used, at the pilot’s discretion, only when required to ensure safe flight (engine failure).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-THR-MCT P 1/2 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
MAXIMUM CONTINUOUS
FLIGHT CREW OPERATING MANUAL
MAXIMUM CONTINUOUS Ident.: PER-THR-MCT-00001976.0011001 / 28 JAN 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
PER-THR-MCT P 2/2 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
MAXIMUM CLIMB
FLIGHT CREW OPERATING MANUAL
DEFINITION Ident.: PER-THR-MCL-00001977.0001001 / 23 FEB 11 Applicable to: ALL
It is the maximum thrust approved for normal climb. MAXIMUM CLIMB Ident.: PER-THR-MCL-00001978.0011001 / 28 JAN 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
PER-THR-MCL P 1/2 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
MAXIMUM CLIMB
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-THR-MCL P 2/2 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
MAXIMUM CRUISE
FLIGHT CREW OPERATING MANUAL
DEFINITION Ident.: PER-THR-MCR-00001979.0004001 / 02 FEB 11 Applicable to: ALL
It is the maximum thrust approved for normal cruise. There is no thrust lever position corresponding to this thrust rating. It is not displayed to the pilot, and the N1 limit which is displayed in cruise is the maximum climb N1. The FMGS uses the maximum cruise N1 to compute the aircraft maximum speed. In manual thrust setting, in cruise, the pilot should limit N1 to the maximum cruise N1 that is equal to the displayed maximum climb N1 minus 1.9 %.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-THR-MCR P 1/2 03 APR 12
PERFORMANCE THRUST RATINGS A318/A319/A320/A321
MAXIMUM CRUISE
FLIGHT CREW OPERATING MANUAL
MAXIMUM CRUISE Ident.: PER-THR-MCR-00001980.0018001 / 28 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
PER-THR-MCR P 2/2 03 APR 12
PERFORMANCE TAKEOFF
Intentionally left blank
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-TOF-PLP PRELIMINARY PAGES TABLE OF CONTENTS SUMMARY OF HIGHLIGHTS
PER-TOF-THR THRUST OPTIONS PER-TOF-THR-FLX FLEXIBLE TAKEOFF PER-TOF-THR-FLX-10 DEFINITION OF FLEXIBLE TAKEOFF DEFINITION OF FLEXIBLE TAKEOFF...................................................................................................................A
PER-TOF-THR-FLX-20 USE OF FLEXIBLE TAKEOFF USE OF FLEXIBLE TAKEOFF................................................................................................................................A
PER-TOF-THR-FLX-30 REQUIREMENTS REQUIREMENTS.................................................................................................................................................... A
PER-TOF-THR-FLX-40 RECOMMENDATION GENERAL................................................................................................................................................................ A TAKEOFF PROCEDURE........................................................................................................................................ B
PER-TOF-TOC TAKEOFF CHARTS PER-TOF-TOC-05 INTRODUCTION TAKEOFF CHARTS.................................................................................................................................................A
PER-TOF-TOC-10 GENERAL (TEMPERATURE ENTRY) PER-TOF-TOC-10-10 TAKEOFF PERFORMANCE TAKEOFF PERFORMANCE................................................................................................................................... A 1
PER-TOF-TOC-10-20 TAKEOFF CHART DESCRIPTION GENERAL................................................................................................................................................................ A Corrections due to Different Takeoff Conditions..................................................................................................... B DESCRIPTION OF THE CORRECTIONS ON TAKEOFF CHART........................................................................ C MINIMUM SPEEDS................................................................................................................................................. D FLEX TEMPERATURE INDICATOR.......................................................................................................................E
PER-TOF-TOC-10-30 ADDITIONAL INFORMATION ONE ENGINE OUT CLIMB PROCEDURE............................................................................................................. A TAKEOFF ON A WET RUNWAY............................................................................................................................B DESCRIPTION OF TAKEOFF CHART...................................................................................................................C EXAMPLE OF TAKEOFF CHART.......................................................................................................................... D
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-PLP-TOC P 1/6 18 SEP 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-TOF-TOC-12 MTOW CALCULATION (TEMPERATURE ENTRY) PER-TOF-TOC-12-10 DETERMINATION OF MAXIMUM TAKEOFF WEIGHT AND SPEEDS DIRECT CHART READING.................................................................................................................................... A CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS.........................................................................B CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS............................................................................... C CORRECTIONS FOR WET OR CONTAMINATED RUNWAYS............................................................................ D CORRECTIONS PRODUCED ON THE RTOW CHART........................................................................................ E COMBINING CORRECTIONS FROM FCOM AND CHART................................................................................... F
PER-TOF-TOC-12-30 EXTRAPOLATION EXTRAPOLATION................................................................................................................................................... A
PER-TOF-TOC-12-40 MAXIMUM STRUCTURAL TAKEOFF WEIGHT MAXIMUM STRUCTURAL TAKEOFF WEIGHT..................................................................................................... A
PER-TOF-TOC-12-50 SUMMARY SUMMARY............................................................................................................................................................... A
PER-TOF-TOC-14 FLEXIBLE TAKEOFF (TEMPERATURE ENTRY) PER-TOF-TOC-14-10 DETERMINATION OF FLEXIBLE TAKEOFF TEMPERATURE AND SPEEDS GENERAL................................................................................................................................................................ A CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS.........................................................................B CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS............................................................................... C CORRECTIONS FOR WET RUNWAY................................................................................................................... D CORRECTIONS PRODUCED ON THE RTOW CHART........................................................................................ E COMBINING CORRECTIONS FROM FCOM AND CHART................................................................................... F
PER-TOF-TOC-14-20 FLEXIBLE TAKEOFF NOT POSSIBLE FLEXIBLE TAKEOFF NOT POSSIBLE...................................................................................................................A
PER-TOF-TOC-14-30 SUMMARY SUMMARY............................................................................................................................................................... A
PER-TOF-TOC-16 GENERAL (WEIGHT ENTRY) PER-TOF-TOC-16-10 TAKEOFF PERFORMANCE TAKEOFF PERFORMANCE................................................................................................................................... A
PER-TOF-TOC-16-20 TAKEOFF CHART DESCRIPTION GENERAL................................................................................................................................................................ A CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS.........................................................................B DESCRIPTION OF THE CORRECTIONS ON TAKEOFF CHART........................................................................ C MINIMUM SPEED................................................................................................................................................... D
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-PLP-TOC P 2/6 18 SEP 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-TOF-TOC-16-30 ADDITIONAL INFORMATION ONE ENGINE OUT CLIMB PROCEDURE............................................................................................................. A TAKEOFF ON A WET RUNWAY............................................................................................................................B RTOW CHARTS - COMPLEMENTARY INFORMATION....................................................................................... C RTOW EXAMPLE....................................................................................................................................................D
PER-TOF-TOC-18 MTOW CALCULATION (WEIGHT ENTRY) PER-TOF-TOC-18-10 DETERMINATION OF MAXIMUM TAKEOFF WEIGHT AND SPEEDS GENERAL................................................................................................................................................................ A MTOW DETERMINATION.......................................................................................................................................B CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS.........................................................................C CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS............................................................................... D CORRECTIONS FOR WET OR CONTAMINATED RUNWAYS.............................................................................E CORRECTIONS PRODUCED ON THE RTOW CHART........................................................................................ F COMBINING CORRECTIONS FROM FCOM AND CHART.................................................................................. G
PER-TOF-TOC-18-20 EXTRAPOLATION EXTRAPOLATION................................................................................................................................................... A
PER-TOF-TOC-18-30 MAXIMUM STRUCTURAL TAKEOFF WEIGHT MAXIMUM STRUCTURAL TAKEOFF WEIGHT..................................................................................................... A
PER-TOF-TOC-18-40 SUMMARY SUMMARY............................................................................................................................................................... A
PER-TOF-TOC-20 FLEXIBLE TAKEOFF (WEIGHT ENTRY) PER-TOF-TOC-20-10 DETERMINATION OF FLEXIBLE TAKEOFF TEMPERATURE AND SPEEDS GENERAL................................................................................................................................................................ A CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS.........................................................................B CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS ..............................................................................C CORRECTIONS FOR WET RUNWAY................................................................................................................... D CORRECTIONS PRODUCED ON THE RTOW CHART........................................................................................ E COMBINING CORRECTIONS FROM FCOM AND CHART................................................................................... F
PER-TOF-TOC-20-20 FLEXIBLE TAKEOFF NOT POSSIBLE FLEXIBLE TAKEOFF NOT POSSIBLE...................................................................................................................A
PER-TOF-TOC-20-30 SUMMARY SUMMARY............................................................................................................................................................... A
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-PLP-TOC P 3/6 18 SEP 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-TOF-TOD TAKEOFF DATA PER-TOF-TOD-24 QNH/BLEEDS CORRECTION EFFECT OF QNH AND BLEEDS (up to 9200 ft)................................................................................................... A EXAMPLES.............................................................................................................................................................. B EFFECT OF QNH AND BLEEDS FOR HIGH ALTITUDE OPERATIONS (above 9200 ft).....................................C EXAMPLES FOR HIGH ALTITUDE OPERATIONS............................................................................................... D
PER-TOF-TOD-25 MINIMUM SPEEDS PER-TOF-TOD-25-10 SPEEDS LIMITED BY VMC SPEEDS LIMITED BY VMC....................................................................................................................................A
PER-TOF-TOD-25-20 V2 LIMITED BY VMU/VMCA MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS).................................................................................................. A
PER-TOF-TOD-40 QUICK REFERENCE TABLES PER-TOF-TOD-40-10 INTRODUCTION INTRODUCTION......................................................................................................................................................A
PER-TOF-TOD-40-20 USE OF TABLES USE OF TABLES.................................................................................................................................................... A
PER-TOF-TOD-40-30 HOW TO PROCEED GENERAL................................................................................................................................................................ A LIMITATION CODES ..............................................................................................................................................B CORRECTIONS FOR WIND AND RUNWAY SLOPE............................................................................................C EXAMPLE................................................................................................................................................................ D
PER-TOF-TOD-40-40 QUICK REFERENCE TABLES CONFIGURATION 1+F / 0 FT................................................................................................................................ A CONFIGURATION 1+F / 1000 FT.......................................................................................................................... B CONFIGURATION 1+F / 2000 FT.......................................................................................................................... C CONFIGURATION 2 / PRESSURE ALTITUDE = 0 FT..........................................................................................D CONFIGURATION 2 / PRESSURE ALTITUDE = 1000 FT.................................................................................... E CONFIGURATION 2 / PRESSURE ALTITUDE = 2000 FT.................................................................................... F CONFIGURATION 3 / PRESSURE ALTITUDE = 0 FT......................................................................................... G CONFIGURATION 3 / PRESSURE ALTITUDE = 1000 FT....................................................................................H CONFIGURATION 3 / PRESSURE ALTITUDE = 2000 FT..................................................................................... I
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-PLP-TOC P 4/6 18 SEP 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-TOF-TOD-50 NET TAKEOFF FLIGHT PATH INTRODUCTION......................................................................................................................................................A HOW TO PROCEED............................................................................................................................................... B CLOSE OBSTACLE CLEARANCE CONF 1 + F....................................................................................................C REMOTE OBSTACLE CLEARANCE CONF 1 + F.................................................................................................D CLOSE OBSTACLE CLEARANCE CONF 2...........................................................................................................E REMOTE OBSTACLE CLEARANCE CONF 2........................................................................................................F CLOSE OBSTACLE CLEARANCE CONF 3.......................................................................................................... G REMOTE OBSTACLE CLEARANCE CONF 3....................................................................................................... H
PER-TOF-CTA RUNWAY CONTAMINATION PER-TOF-CTA-10 GENERAL GENERAL................................................................................................................................................................ A
PER-TOF-CTA-20 DEFINITIONS DEFINITIONS...........................................................................................................................................................A
PER-TOF-CTA-30 OPERATIONAL CONDITIONS OPERATIONAL CONDITIONS................................................................................................................................A
PER-TOF-CTA-40 TAKEOFF PERFORMANCE PER-TOF-CTA-40-10 TAKEOFF PERFORMANCE TAKEOFF PERFORMANCE................................................................................................................................... A
PER-TOF-CTA-40-20 TAKEOFF FROM A WET RUNWAY HOW TO PROCEED............................................................................................................................................... A NO THRUST REVERSERS OPERATIVE (NO CLEARWAY).................................................................................B ALL THRUST REVERSERS OPERATIVE (NO CLEARWAY)............................................................................... C NO THRUST REVERSERS OPERATIVE (WITH CLEARWAY).............................................................................D ALL THRUST REVERSERS OPERATIVE (WITH CLEARWAY)............................................................................E
PER-TOF-CTA-40-30 TAKEOFF FROM A CONTAMINATED RUNWAY TAKEOFF FROM A 6.3 MM (1/4 INCH) WATER COVERED RUNWAY............................................................... A TAKEOFF FROM A 12.7 MM (1/2 INCH) WATER COVERED RUNWAY............................................................. B TAKEOFF FROM A 6.3 MM (1/4 INCH) SLUSH COVERED RUNWAY................................................................ C TAKEOFF FROM A 12.7 MM (1/2 INCH) SLUSH COVERED RUNWAY.............................................................. D TAKEOFF FROM A COMPACTED SNOW COVERED RUNWAY.........................................................................E
PER-TOF-CTA-40-40 EXAMPLE TAKEOFF PERFORMANCE ON DRY RUNWAY...................................................................................................A TAKEOFF PERFORMANCE ON WET RUNWAY.................................................................................................. B TAKEOFF PERFORMANCE ON RUNWAY COVERED WITH 1/2 INCH SLUSH..................................................C
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-PLP-TOC P 5/6 18 SEP 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-PLP-TOC P 6/6 18 SEP 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title
Toc Index
PER-TOF-PLP-TOC TAKEOFF CHART DESCRIPTION
PER-TOF-TOC-10-20 Corrections due to Different Takeoff Conditions
B
ID
Reason
1
Documentation update: Deletion of the "00001707 CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS" table of content entry. Documentation update: Deletion of the "00001707.0086001 CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS" documentary unit. Documentation update: Addition of "Corrections due to Different Takeoff Conditions" documentary unit
1
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-PLP-SOH P 1/2 18 SEP 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-PLP-SOH P 2/2 18 SEP 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
THRUST OPTIONS - FLEXIBLE TAKEOFF
FLIGHT CREW OPERATING MANUAL
DEFINITION OF FLEXIBLE TAKEOFF DEFINITION OF FLEXIBLE TAKEOFF Ident.: PER-TOF-THR-FLX-10-00001718.0001001 / 28 JAN 11 Applicable to: ALL
In many cases the aircraft takes off with a weight lower than the maximum permissible takeoff weight. When this happens, it can meet the required performance (runway, second segment, obstacle,...) with a decreased thrust that is adapted to the weight : this is called FLEXIBLE TAKEOFF and the thrust is called FLEXIBLE TAKEOFF THRUST. The use of flexible takeoff thrust saves engine life.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-THR-FLX-10 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321
THRUST OPTIONS - FLEXIBLE TAKEOFF
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-THR-FLX-10 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321
THRUST OPTIONS - FLEXIBLE TAKEOFF
FLIGHT CREW OPERATING MANUAL
USE OF FLEXIBLE TAKEOFF USE OF FLEXIBLE TAKEOFF Ident.: PER-TOF-THR-FLX-20-00001719.0001001 / 09 DEC 09 Applicable to: ALL
The pilot can use flexible takeoff when the actual takeoff weight is lower than the maximum permissible takeoff weight for the actual temperature. The maximum permissible takeoff weight decreases when temperature increases, so it is possible to assume a temperature at which the actual takeoff weight would be the limiting one. This temperature is called FLEXIBLE TEMPERATURE or assumed temperature and is entered in the FADEC via the MCDU PERF TO page in order to get the adapted thrust.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-THR-FLX-20 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321
THRUST OPTIONS - FLEXIBLE TAKEOFF
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-THR-FLX-20 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321
THRUST OPTIONS - FLEXIBLE TAKEOFF
FLIGHT CREW OPERATING MANUAL
REQUIREMENTS REQUIREMENTS Ident.: PER-TOF-THR-FLX-30-00001792.0017001 / 15 MAR 11 Applicable to: ALL
‐ Thrust must not be reduced by more than 25 % of the full rated takeoff thrust. ‐ The flexible takeoff N1 cannot be lower than the Max climb N1 at the same flight conditions. The FADEC takes the above two constraints into account to determine flexible N1. The above two constraints also limit the maximum flexible temperature at ISA+ 53 (68 °C at sea level). ‐ The flexible takeoff thrust cannot be lower than the Max Continuous thrust used for the final takeoff flight path computation (at ISA +40). ‐ The flexible temperature cannot be lower than the flat rating temperature, TREF ( ISA +29 up to 2 000 ft) (See Note), or the actual temperature (OAT).
Note:
TREF being a function of pressure altitude, read it on the takeoff chart.
‐ Flexible takeoff is not permitted on contaminated runways. ‐ The operator should check the maximum thrust (TOGA) at regular intervals in order to detect any engine deterioration, or maintain an adequate engine performance monitoring program to follow up the engine parameters.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-THR-FLX-30 P 1/2 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
THRUST OPTIONS - FLEXIBLE TAKEOFF
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-THR-FLX-30 P 2/2 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
THRUST OPTIONS - FLEXIBLE TAKEOFF
FLIGHT CREW OPERATING MANUAL
RECOMMENDATION GENERAL Ident.: PER-TOF-THR-FLX-40-00001720.0002001 / 23 FEB 11 Applicable to: ALL
• In order to extend engine life and save maintenance costs, it is recommended to use flexible thrust reduction. • However, to improve the takeoff performance, the thrust can be increased by selecting a lower flexible temperature. Using the same takeoff chart, for a given weight it is possible to : ‐ Select a temperature lower than the maximum determined one and keep the speeds defined at maximum temperature or, ‐ Move towards the left side (tailwind) of the takeoff chart while remaining within the same configuration and looking for the same actual takeoff weight at lower temperature. This produces a lower flexible temperature and, in general, lower takeoff speeds (V1/VR/V2). Using one of the two above possibilities, check that the selected temperature is greater than the actual temperature (OAT) and greater than the flat rating temperature (TREF).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-THR-FLX-40 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321
THRUST OPTIONS - FLEXIBLE TAKEOFF
FLIGHT CREW OPERATING MANUAL
TAKEOFF PROCEDURE Ident.: PER-TOF-THR-FLX-40-00001721.0001001 / 28 JAN 11 Applicable to: ALL
Depending on environmental takeoff conditions, the following procedure is recommended. CONDITIONS Dry or wet well paved runway
High altitude takeoff Badly paved runway or Accelerate stop distance limited runway Windshear expected along takeoff path Contaminated runway
PROCEDURE ‐ Use the flap setting giving the highest flexible temperature. ‐ When flexible temperature difference between two flap settings is low, use the highest flap setting.
REASON Extend engine life and save maintenance costs.
Use CONF2/CONF3 Use CONF2/CONF3 or Move towards left side of the takeoff chart
Improve comfort Improve comfort Improve stopping distance
Use maximum thrust
Maintain acceleration capability
Use maximum thrust (flex forbidden)
Improve stopping distance Decrease time on runway. Required by regulations.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
PER-TOF-THR-FLX-40 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321
TAKEOFF CHARTS - INTRODUCTION
FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS Ident.: PER-TOF-TOC-05-00001704.0001001 / 21 MAR 11 Applicable to: ALL
Takeoff charts are required to provide performance at takeoff. It is possible to present the charts in two different ways, one of which is selected by the airline. The different presentations are : ‐ temperature entry (temperature provided in the left column) ‐ weight entry (weight provided in the left column). Both presentations are described here after. Sections PER-TOF-TOC-10, 12 and 14 are relative to temperature entry while PER-TOF-TOC-16, 18 and 20 are relative to weight entry.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOC-05 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321
TAKEOFF CHARTS - INTRODUCTION
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-05 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
TAKEOFF PERFORMANCE TAKEOFF PERFORMANCE Ident.: PER-TOF-TOC-10-10-00001705.0001001 / 23 FEB 11 Applicable to: ALL
Takeoff optimization is calculated for a given runway and its obstacles and for given conditions of flap setting, temperature, wind and QNH. The calculation produces a maximum permissible takeoff weight (or a maximum takeoff temperature for an actual weight). The takeoff thrust produced by the engine varies as follows :
The optimization process calculates the speeds which will produce the maximum takeoff weight. To do so, it takes into account the different takeoff limitations such as TOD, ASD, TOR, second segment..., as shown on the figure charts below.
On a typical runway, the performance of a twin engine aircraft, is generally limited by the one engine out operation at takeoff. The optimum V2/VS and optimum V1/VR are consequently unique.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOC-10-10 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-10-10 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
FLIGHT CREW OPERATING MANUAL
TAKEOFF CHART DESCRIPTION GENERAL Ident.: PER-TOF-TOC-10-20-00001706.0003001 / 03 MAR 11 Applicable to: ALL
The takeoff chart (RTOW : Regulatory Takeoff Weight) is calculated for a specific aircraft version and for a particular runway specified at the top of the chart. The top of the chart also gives some information about the runway and lists the calculation assumptions. The chart is given for 2 different configurations and 5 wind values per configuration. This allows the crew to select the configuration that gives either : ‐ the highest permissible takeoff weight, or, for a given weight, ‐ the highest flexible temperature. If different configurations give equivalent performance, the crew should select the configuration associated with the lowest takeoff speeds. For each temperature value (and for a given configuration and wind), the chart provides the following information :
The available limitation codes are : ‐ First segment ‐ Second segment ‐ Runway length ‐ Obstacles ‐ Tire speed ‐ Brake energy ‐ Maximum computation weight ‐ Final takeoff ‐ VMU
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
: : : : : : : : :
1 2 3 4 5 6 7 8 9
A
PER-TOF-TOC-10-20 P 1/4 18 SEP 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS
1 Ident.: PER-TOF-TOC-10-20-00014608.0001001 / 18 JUL 12
Applicable to: ALL
Each takeoff chart is computed for a given set of conditions (air conditioning, QNH, anti ice...) specified at the top of the chart. If the actual takeoff conditions are different, the crew must apply corrections. Two types of correction are available : ‐ Conservative corrections on Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS (to be used when not provided on the chart). ‐ Corrections (less restrictive) listed on the chart, to be applied as explained below. Note:
‐ If the RTOW chart is based on the CG being at 25 %, the crew can find the takeoff performance at a more forward CG by decreasing the takeoff weight by 1 000 kg (2 200 lb) and increasing V1, VR and V2 by 1 kt. ‐ 25 % CG is the basic certified limit, on which all takeoff computations are based. To take into account the operational margins, the above penalties must be applied when operational CG is forward 27 % CG.
DESCRIPTION OF THE CORRECTIONS ON TAKEOFF CHART Ident.: PER-TOF-TOC-10-20-00005368.0001001 / 03 MAR 11 Applicable to: ALL
The corrections are presented on 4 lines:
TVMC is a temperature value given per column. This is a fictitious value that indicates the temperature above which the speeds are close to a VMC limitation or are VMC limited. Note:
The lower two lines may be shaded on certain chart formats.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B to C
PER-TOF-TOC-10-20 P 2/4 18 SEP 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
MINIMUM SPEEDS Ident.: PER-TOF-TOC-10-20-00005372.0001001 / 02 MAR 11 Applicable to: ALL
Minimum V1/VR/V2 due to VMC are provided on the bottom right side of the takeoff chart. They are only applicable in case of speed corrections. These speeds are conservative. They may be slightly higher than V1/VR/V2 displayed on the takeoff chart. FLEX TEMPERATURE INDICATOR Ident.: PER-TOF-TOC-10-20-00005373.0001001 / 18 FEB 11 Applicable to: ALL
On the temperature entry chart, the temperature column may display asterisks or have a gray band to indicate temperature values above TMAX and which are flex temperature.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D to E
PER-TOF-TOC-10-20 P 3/4 18 SEP 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-10-20 P 4/4 18 SEP 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
ADDITIONAL INFORMATION ONE ENGINE OUT CLIMB PROCEDURE Ident.: PER-TOF-TOC-10-30-00001708.0001001 / 23 FEB 11 Applicable to: ALL
The performance given in the chart is consistent with the flight path specified for the aircraft with one engine out and takes into account significant obstacles. When the procedure to be followed is not the standard instrument departure, the chart describes a specific procedure (EOSID). When the specified procedure requires a turn, except if otherwise stated on the RTOW chart, the turn should be performed with a maximum bank of 15 ° until the aircraft reaches 1 500 ft or until green dot. The acceleration height (or altitude) ensures that the net flight path clears the highest obstacle by at least 35 ft when accelerating in level flight to green dot speed after an engine failure, in the most adverse conditions. TAKEOFF ON A WET RUNWAY Ident.: PER-TOF-TOC-10-30-00001709.0002001 / 23 FEB 11 Applicable to: ALL
Takeoff charts computed for wet runway with a 15 ft screen height and/or use of reverse thrust may produce, in some conditions, a maximum takeoff weight (or flexible temperature) higher than that obtained for a dry runway. It is thus mandatory to compare both charts (dry and wet) and retain the lower of the two weights (or flexible temperature) and the associated speeds determined for a wet runway. Note:
The crew need not compare the charts if the top of the wet runway chart specifies “DRY CHECK”. (The comparison has already been inserted in the WET runway calculation).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
PER-TOF-TOC-10-30 P 1/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
DESCRIPTION OF TAKEOFF CHART Ident.: PER-TOF-TOC-10-30-00001710.0003001 / 23 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C→
PER-TOF-TOC-10-30 P 2/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C→
PER-TOF-TOC-10-30 P 3/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C
PER-TOF-TOC-10-30 P 4/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
EXAMPLE OF TAKEOFF CHART Ident.: PER-TOF-TOC-10-30-00001711.0013001 / 01 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D→
PER-TOF-TOC-10-30 P 5/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D
PER-TOF-TOC-10-30 P 6/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
DETERMINATION OF MAXIMUM TAKEOFF WEIGHT AND SPEEDS DIRECT CHART READING Ident.: PER-TOF-TOC-12-10-00001712.0002001 / 23 FEB 11 Applicable to: ALL
The takeoff chart is computed for a given runway under a set of conditions, which are: ‐ OAT ‐ Wind ‐ Configuration ‐ QNH, air conditioning, anti ice... Two configurations are produced on the chart. This enables the crew to select that giving the highest permissible takeoff weight. In case of equivalent performance, retain the configuration giving the lower takeoff speeds. For a given configuration, enter the chart with the OAT and wind value to determine the maximum permissible weight. For an OAT or wind value not presented on the chart, interpolate between two consecutive temperature rows and/or two consecutive wind columns. Conservative OAT or wind values can also be considered. No extrapolation is allowed. CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS Ident.: PER-TOF-TOC-12-10-00001713.0002001 / 28 JAN 11 Applicable to: ALL
Retain the maximum takeoff weight, associated configuration and speeds from above. For conditions different from those of the chart, apply relevant corrections.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
PER-TOF-TOC-12-10 P 1/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS Ident.: PER-TOF-TOC-12-10-00001714.0030001 / 28 MAR 11 Applicable to: ALL
Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS Corrections are given for QNH ≠ 1 013 hPa, air conditioning ON, anti ice ON. 1. For the given wind and temperature conditions, read the maximum takeoff weight (choose the configuration giving the highest weight). 2. Apply the published weight correction(s) to the maximum takeoff weight (for each correction) to determine the maximum permissible takeoff weight. 3. Read the speeds associated with the maximum permissible takeoff weight by entering the chart with the retained configuration and wind value. EXAMPLE 1 DATA:
OAT = 25 °C Head Wind = 10 kt Air conditioning ON QNH = 1 013 hPa
Use the chart (Refer to PER-TOF-TOC-10-30 EXAMPLE OF TAKEOFF CHART) Enter the 10 kt head wind column and interpolate for 25 °C, CONF 1+F, Maximum TO weight (1 000 kg) air conditioning OFF.............................................................82.1 Enter the 10 kt head wind column and interpolate for 25 °C, CONF 2, Maximum TO weight (1 000 kg) air conditioning OFF.............................................................82.1 Retain CONF 2 as takeoff configuration. Maximum TO weight (1 000 kg) air conditioning OFF.............................................................82.1 Air conditioning correction....................................................................................................... -2.2 (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS) Maximum permissible TO weight (1 000 kg) air conditioning ON........................................ = 79.9 Determine takeoff speeds for 79.9 (1 000 kg) in the 10 kt head wind column (CONF 2) V1 = 152 kt, VR = 153 kt, V2 = 158 kt CORRECTIONS FOR WET OR CONTAMINATED RUNWAYS Ident.: PER-TOF-TOC-12-10-00001715.0001001 / 28 JAN 11 Applicable to: ALL
(Refer to PER-TOF-CTA-10 GENERAL)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C to D
PER-TOF-TOC-12-10 P 2/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
CORRECTIONS PRODUCED ON THE RTOW CHART Ident.: PER-TOF-TOC-12-10-00005953.0004001 / 23 NOV 11 Applicable to: ALL
For example: Refer to PER-TOF-TOC-10-30 EXAMPLE OF TAKEOFF CHART A description of this correction is given on Refer to PER-TOF-TOC-10-20 DESCRIPTION OF THE CORRECTIONS ON TAKEOFF CHART. The list of corrections is not exhaustive, however the most commonly used corrections are wet runway, QNH, air conditioning and/or anti ice. A maximum of three corrections can be produced on one chart. To apply the corrections, proceed as follows: 1. Enter the chart with given OAT and wind to determine the maximum takeoff weight before correction. 2. Apply the first correction: If OAT is less than or equal to TVMC (line 3), apply ΔW correction from line 1 and ΔV1/ΔVR/ΔV2 corrections from line 2. Else, (for OAT greater than TVMC), apply ΔW correction from line 3 and ΔV1/ΔVR/ΔV2 corrections from line 4. 3. To combine a second (and third, as applicable) correction: If OAT is less than or equal to TVMC (line 3), apply ΔW correction from line 1 and ΔV1/VR/ΔV2 corrections from line 2. Check that the resulting speeds are higher than the minimum speeds displayed on the RTOW chart and that V2 is higher than the VMU limited speed (Refer to PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS)). If OAT is higher than TVMC (line 3) or if the above speed check is not fulfilled, apply ΔW correction from line 3 and ΔV1/ΔVR/ΔV2 corrections from line 4. No speed check is required. Note:
‐ QNH correction is given for ±10 hPa . It is allowed to extrapolate linearly for greater QNH deviation. ‐ When using a takeoff chart with failure cases, it is not allowed to combine two failure cases. ‐ Corrections from the chart must be applied from top to bottom, i.e. in the RTOW on Refer to PER-TOF-TOC-10-30 EXAMPLE OF TAKEOFF CHART, apply the wet correction first. ‐ If asterisk or dotted lines appear in the correction boxes, refer to more conservative corrections provided in the FCOM. ‐ No speed check is required for the first correction. However, if the first influence correction follows a conversative FCOM correction, a speed check is required.
EXAMPLE 2 DATA :
OAT = Head Wind =
25 °C 10 kt
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E→
PER-TOF-TOC-12-10 P 3/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
QNH = WET runway
1 028 hPa
Use the chart : Refer to PER-TOF-TOC-10-30 EXAMPLE OF TAKEOFF CHART. • Enter the 10 kt head wind column and interpolate for 25 °C, CONF 1+F, max TO weight (1 000 kg).......................................................................................................82.1 • Enter the 10 kt head wind column and interpolate for 25 °C, CONF 2, max TO weight (1 000 kg).......................................................................................................82.1 • Retain CONF 2 for takeoff as the speeds are lower. • Read associated speeds as V1 = 156 kt, VR = 157 kt, V2 = 162 kt • Apply WET correction For OAT < TVMC (54 °C), ΔW =............................................................................................. -1.2 Intermediate weight (1 000 kg).............................................................................................= 80.9 Associated speeds, V1 = 156 kt - 10 = 146 kt VR = 157 kt - 1 = 156 kt V2 = 162 kt - 1 = 161 kt (No speed check required for first correction) • Apply QNH correction For OAT < TVMC (54 °C), ΔW = 0.2 × 15/10 =.....................................................................+ 0.3 Maximum permissible takeoff weight (1 000 kg).................................................................. = 81.2 Associated speeds, V1 = 146 kt + 1 × 15/10 = 147 kt VR = 156 kt + 1 × 15/10 = 158 kt V2 = 161 kt + 1 × 15/10 = 163 kt • Check that the speeds are higher than minimum speeds from the chart and from VMU table. TOW TOW (RTOW) FCOM correction(s) Intermediate value WET Correction Intermediate value QNH Correction Final value
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
82.1 82.1 - 1.2 80.9 + 0.3 81.2
←E
Takeoff Configuration : 2 V1 VR 156 156 -10 146 +1 147
V2 157
162
157 -1 156 +2 158
162 -1 161 +2 163
PER-TOF-TOC-12-10 P 4/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
COMBINING CORRECTIONS FROM FCOM AND CHART Ident.: PER-TOF-TOC-12-10-00005954.0026001 / 30 MAR 11 Applicable to: ALL
Proceed as follows: 1. Enter the chart with selected configuration, OAT and wind to read the maximum takeoff weight. 2. Apply corrections from FCOM to determine an intermediate weight. Interpolate associated speeds for intermediate weight in the same column (same wind and configuration). 3. Apply corrections from RTOW chart as explained above. EXAMPLE 3 DATA :
OAT = 25 °C Head wind = 10 kt Air conditioning ON QNH = 1 028 hPa WET runway
1. Use the chart (Refer to PER-TOF-TOC-10-30 EXAMPLE OF TAKEOFF CHART). Enter the 10 kt head wind column and interpolate for 25 °C, CONF 1+F, Max TO weight (1 000 kg) air conditioning OFF..................................................................... 82.1 Enter the 10 kt head wind column and interpolate for 25 °C, CONF 2, Max TO weight (1 000 kg) air conditioning OFF..................................................................... 82.1 Retain CONF 2 for takeoff configuration. 2. First, apply the correction (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS). Max TO weight (1 000 kg) air conditioning OFF..................................................................... 82.1 Air conditioning correction....................................................................................................... - 2.2 Intermediate weight.............................................................................................................. = 79.9 Interpolate takeoff speeds for 79.9 (1 000 kg) in the 10 kt head wind column, V1 = 152 kt , VR = 153 kt , V2 = 158 kt 3. Apply WET correction For OAT < TVMC (54 °C), ΔW =............................................................................................. -1.2 Intermediate weight.............................................................................................................. = 78.7 Associated speeds, V1 = 152 kt - 10 = 142 kt VR = 153 kt - 1 = 152 kt V2 = 158 kt - 1 = 157 kt Check that the speeds are higher than minimum speeds from the chart and from VMU table Apply QNH correction For OAT < TVMC (54 °C), ΔW = 0.2 × 15/10 =......................................................................+0.3 Max permissible takeoff weight............................................................................................ = 79.0 Associated speed, 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F→
PER-TOF-TOC-12-10 P 5/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
V1 = 142 kt + 1 × 15/10 = 143 kt VR = 152 kt + 1 × 15/10 = 154 kt V2 = 157 kt + 1 × 15/10 = 159 kt Check that the speeds are higher than minimum speeds from the chart and from VMU table. (It is reminded that if the speed checks are not fulfilled, the corrections must be recalculated using those provided on lines 3 and 4). Since the speed check is fulfilled: Max permissible takeoff weight = 79.0 (1 000 kg) V1 = 143 kt, VR = 154 kt, V2 = 159 kt. Takeoff Configuration : 2 V1 VR
TOW TOW (RTOW) FCOM correction(s) Intermediate value WET Correction Intermediate value QNH Correction Final value
82.1 - 2.2 79.9 - 1.2 78.7 + 0.3 79.0
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
152 -10 142 +1 143
←F
V2
153 -1 152 +2 154
158 -1 157 +2 159
PER-TOF-TOC-12-10 P 6/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
EXTRAPOLATION EXTRAPOLATION Ident.: PER-TOF-TOC-12-30-00001716.0002001 / 01 MAR 11 Applicable to: ALL
For a takeoff weight lower than those displayed on the chart, associated speeds are calculated as follows : 1. For given configuration and wind, note the speeds associated with the takeoff weight in the row displaying the highest permissible temperature. 2. Apply speed corrections provided at the bottom of the RTOW chart to V1, VR and V2 limited to the minimum speeds.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOC-12-30 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-12-30 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
MAXIMUM STRUCTURAL TAKEOFF WEIGHT MAXIMUM STRUCTURAL TAKEOFF WEIGHT Ident.: PER-TOF-TOC-12-40-00001717.0001001 / 18 MAR 11 Applicable to: ALL
The maximum structural takeoff weight is a weight limitation depending on the aircraft. This limitation is provided in the Flight Manual and in Refer to LIM-11 Weight Limitations. Compare the maximum structural takeoff weight to the maximum permissible takeoff weight computed for given conditions and retain the lower of the two values.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOC-12-40 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-12-40 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
SUMMARY SUMMARY Ident.: PER-TOF-TOC-12-50-00006313.0001001 / 11 MAR 11 Applicable to: ALL
The following flow diagram gives the different steps to follow.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOC-12-50 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-12-50 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
DETERMINATION OF FLEXIBLE TAKEOFF TEMPERATURE AND SPEEDS GENERAL Ident.: PER-TOF-TOC-14-10-00001722.0002001 / 17 MAR 11 Applicable to: ALL
Before determining the flexible temperature, calculate the maximum permissible takeoff weight (see previous section) and ensure that the actual takeoff weight is lower than the determined maximum takeoff weight. • Enter the RTOW chart with the wind condition to interpolate for the actual takeoff weight. Read the flexible temperature in the temperature column corresponding to the actual weight. • Repeat this process for the other configuration available. Select the configuration giving the highest flexible temperature. CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS Ident.: PER-TOF-TOC-14-10-00001723.0001001 / 28 JAN 11 Applicable to: ALL
When the takeoff conditions are different from those provided on the chart, apply the associated corrections. Note:
If the RTOW chart is based on the CG being at 25 %, the crew can determine the flexible temperature at a more forward CG by decreasing the flexible temperature by 2 °C. V1, VR and V2 must be increased by 1 kt.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
PER-TOF-TOC-14-10 P 1/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS Ident.: PER-TOF-TOC-14-10-00001724.0288001 / 31 MAR 11 Applicable to: ALL
CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS Corrections are given for QNH ≠ 1 013 hPa , air conditioning ON, anti ice ON. 1. For a given takeoff weight, wind condition and selected configuration, determine the flexible temperature. Retain the takeoff speeds associated with the actual weight. 2. Apply the published temperature correction. To combine two or more corrections, add the different corrections and apply to temperature value. (No speed corrections required). EXAMPLE 4 DATA :
Actual takeoff weight = 76 000 kg Head wind = 10 kt Air conditioning ON QNH = 1 013 hPa Use the chart Refer to PER-TOF-TOC-10-30 EXAMPLE OF TAKEOFF CHART. Determine the maximum permissible takeoff weight (Refer to PER-TOF-TOC-12-10 CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS). The actual weight being lower than the maximum one, flexible takeoff is possible. Enter the 10 kt head wind column and interpolate for 76 000 kg, CONF 1 + F, Flexible temperature.............................................................................................................. 52 °C Enter the 10 kt head wind column and interpolate for 76 000 kg, CONF 2, Flexible temperature.............................................................................................................. 52 °C Retain CONF 2 for takeoff configuration. Takeoff speeds are V1 = 150 kt, VR = 150 kt, V2 = 155 kt Flexible temperature with air conditioning OFF.....................................................................52 °C Air conditioning correction .....................................................................................................-7 °C Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS Maximum flexible temperature........................................................................................... = 45 °C CORRECTIONS FOR WET RUNWAY
Ident.: PER-TOF-TOC-14-10-00001725.0001001 / 28 JAN 11 Applicable to: ALL
CORRECTIONS FOR WET RUNWAY (Refer to PER-TOF-CTA-10 GENERAL) 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C to D
PER-TOF-TOC-14-10 P 2/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
CORRECTIONS PRODUCED ON THE RTOW CHART Ident.: PER-TOF-TOC-14-10-00012739.0007001 / 06 APR 11 Applicable to: ALL
A description of this correction is given on Refer to PER-TOF-TOC-10-20 DESCRIPTION OF THE CORRECTIONS ON TAKEOFF CHART. The list of corrections is not exhaustive, however the most commonly used corrections are wet runway, QNH, air conditioning and/or anti-icing. A maximum of three corrections can be produced on one chart. To apply the correction, proceed as follows: 1. Enter the chart with wind and selected configuration. Interpolate for actual takeoff weight. Read flexible temperature associated with this weight. 2. Apply the first correction: If the flexible temperature is less than or equal to TVMC (line 3), apply ΔTflex correction from line 1 and apply speed corrections (ΔV1/ΔVR/ΔV2) from line 2. Else, (flexible temperature greater than TVMC), apply ΔTflex from line 3 and ΔV1/ ΔVR/ ΔV2 corrections from line 4. Check V2 against VMU limitation (Refer to PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS)). If V2 is lower than V2 limited by VMU, flexible takeoff is not possible. Set TOGA thrust and retain the speeds associated with maximum permissible takeoff weight or the speeds read in the chart of the actual weight if they are all lower. No speed correction is required for QNH and bleeds influence (Not applicable to maximum takeoff weight determination). 3. To combine a second and/or a third correction, proceed as per point 2. 4. Check that the final flexible temperature is: ‐ higher than OAT and TREF ‐ limited to TMAXFLEX If the check is fulfilled, retain final flexible temperature as the one to be inserted in the MCDU. If the check is not fulfilled, (final flexible temperature lower than OAT or TREF), no flexible takeoff is possible. Use TOGA thrust and retain speeds that have been calculated for the maximum permissible takeoff weight. (Refer to PER-TOF-TOC-14-20 FLEXIBLE TAKEOFF NOT POSSIBLE) Note:
‐ QNH correction is given for ±10 hPa. It is allowed to extrapolate linearly for greater QNH deviation. ‐ Corrections from the chart must be applied from top to bottom, i.e. in the RTOW on Refer to PER-TOF-TOC-10-30 EXAMPLE OF TAKEOFF CHART, apply the wet influence first.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E→
PER-TOF-TOC-14-10 P 3/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Note:
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
‐ When the flexible temperature is higher than TVMC, it is allowed to limit the flexible temperature to TVMC and apply only corrections from lines 1 and 2. ‐ If asterisk or dotted lines appear in the correction boxes, refer to more conservative corrections provided in the FCOM.
EXAMPLE 5 DATA
:
Actual = 76 000 kg takeoff weight Head = 10 kt wind QNH = 1 028 hPa WET runway Air conditioning OFF Use the chart from Refer to PER-TOF-TOC-10-30 EXAMPLE OF TAKEOFF CHART. Determine the maximum permissible takeoff weight (see example 2). The actual weight being lower than the maximum one, flexible takeoff is possible. Enter the10 kt head wind column and interpolate for 76 000 kg, CONF 1 + F, Flexible temperature.................................................................................................................. 52 °C Enter the 10 kt head wind column and interpolate for 76 000 kg, CONF 2, Flexible temperature.................................................................................................................. 52 °C Equivalent performance is obtained from the two different configurations. Retain CONF 2 as the speeds are lower. Takeoff speeds are V1 = 149 kt, VR = 150 kt, V2 = 155 kt Apply WET correction For flexible temperature < TVMC (54 °C), ΔTflex =...................................................................-2 °C Intermediate flex temperature................................................................................................ = 50 °C Associated speeds, V1 = 149 kt – 10 = 139 kt VR = 150 kt – 1= 149 kt V2 = 150 kt – 1 = 154 kt Check V2 against VMU limitation Refer to PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS) Apply QNH correction For flex temperature < TVMC (54 °C), ΔTflex =......................................................................... 0 °C Maximum flexible temperature............................................................................................... = 50 °C Check that OAT/TREF < flex temperature ≤ TMAXFLEX No speed correction. Takeoff speeds are V1 = 139 kt, VR = 149 kt, V2 = 154 kt 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
PER-TOF-TOC-14-10 P 4/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
Chart temperature FCOM correction(s) Intermediate value WET Correction Intermediate value QNH Correction Final value
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Tflex 52
Takeoff Configuration: 1 + F V1 VR 149 150
V2 155
52
149
150
-2
-10
-1
155 -1
50
139
149
154
0
0
0
0
50
139
149
154
←E
PER-TOF-TOC-14-10 P 5/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
COMBINING CORRECTIONS FROM FCOM AND CHART Ident.: PER-TOF-TOC-14-10-00012741.0027001 / 31 MAR 11 Applicable to: ALL
1. Apply corrections from FCOM (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS). 2. Apply corrections from the RTOW chart. Apply speed corrections except for QNH and bleed influences. EXAMPLE 6 DATA:
Actual takeoff weight = 76 000 kg Head wind = 10 kt Air conditioning ON QNH = 1 028 hPa WET runway Use the chart (Refer to PER-TOF-TOC-10-20 DESCRIPTION OF THE CORRECTIONS ON TAKEOFF CHART). Determine the maximum permissible takeoff weight (Refer to PER-TOF-TOC-12-10 COMBINING CORRECTIONS FROM FCOM AND CHART: example 3). The actual weight being lower than the maximum one, flexible takeoff is possible. Enter the 10 kt head wind column and interpolate for 76 000 kg, CONF 1 + F, Flexible temperature.................................................................................................................. 52 °C Enter the 10 kt head wind column and interpolate for 76 000 kg, CONF 2, Flexible temperature.................................................................................................................. 52 °C Retain CONF 2 for takeoff configuration. Takeoff speeds are V1 = 150 kt, VR = 150 kt, V2 = 155 kt First, apply the correction (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS). Flexible temperature with air conditioning OFF.........................................................................52 °C Air conditioning correction.......................................................................................................... -7 °C Intermediate flexible temperature...........................................................................................= 45 °C No speed correction. Apply WET correction For flexible temperature < TVMC (54 °C), ΔTflex = ..................................................................-1 °C Intermediate flex temperature................................................................................................ = 44 °C Associated speeds, V1 = 150 kt - 5 = 145 kt VR = 150 kt - 1 = 149 kt V2 = 155 kt - 1 = 154 kt Check V2 against VMU limitation on Refer to PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS). Apply QNH correction For flexible temperature < TVMC (54 °C), ΔTflex =....................................................................0 °C 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F→
PER-TOF-TOC-14-10 P 6/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
Maximum flexible temperature............................................................................................... = 44 °C Check that OAT/TREF < flex temperature ≤ TMAXFLEX No speed correction. Takeoff speeds are V1 = 145 kt, VR = 149 kt, V2 = 154 kt
Chart temperature FCOM correction(s) Intermediate value WET Correction Intermediate value QNH Correction Final value
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
Tflex 52
Takeoff Configuration : 1 + F V1 VR 150 150
V2 155
-7
0
0
0
45
150
150
155
-1
-5
-1
-1
44
145
149
154
0
0
0
0
44
145
149
154
←F
PER-TOF-TOC-14-10 P 7/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-14-10 P 8/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
FLEXIBLE TAKEOFF NOT POSSIBLE FLEXIBLE TAKEOFF NOT POSSIBLE Ident.: PER-TOF-TOC-14-20-00001726.0001001 / 16 MAR 11 Applicable to: ALL
In some cases when the actual takeoff weight is lower than the maximum permissible one but no flexible takeoff possible (that is flexible temperature lower than TREF or OAT) : ‐ It is mandatory to use TOGA thrust ‐ You can retain the speeds that have been calculated for the maximum permissible takeoff weight; OR ‐ You can retain the speeds associated with the actual takeoff weight provided they are all lower than the speeds calculated for the maximum permissible takeoff weight.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOC-14-20 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-14-20 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
SUMMARY
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-14-30 P 1/4 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
SUMMARY Ident.: PER-TOF-TOC-14-30-00006034.0001001 / 24 MAR 11 Applicable to: ALL
The flow diagram gives the different steps to follow.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
PER-TOF-TOC-14-30 P 2/4 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
PER-TOF-TOC-14-30 P 3/4 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-14-30 P 4/4 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
TAKEOFF PERFORMANCE TAKEOFF PERFORMANCE Ident.: PER-TOF-TOC-16-10-00001727.0001001 / 01 MAR 11 Applicable to: ALL
Takeoff optimization is calculated for a given runway and its obstacles and for given conditions of flap setting, temperature, wind and QNH. The calculation produces a maximum permissible takeoff weight (or a maximum takeoff temperature for an actual weight). The takeoff thrust produced by the engine varies as follows :
The optimization process calculates the speeds which will produce the maximum takeoff weight. To do so, it takes into account the different takeoff limitations such as TOD, ASD, TOR, second segment..., as shown on the charts below.
On a typical runway, the performance of a twin engine aircraft, is generally limited by the one engine out operation at takeoff. The optimum V2/VS and optimum V1/VR are consequently unique.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOC-16-10 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-16-10 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
FLIGHT CREW OPERATING MANUAL
TAKEOFF CHART DESCRIPTION GENERAL Ident.: PER-TOF-TOC-16-20-00001728.0003001 / 28 FEB 11 Applicable to: ALL
The takeoff chart (RTOW : Regulatory Takeoff Weight) is calculated for a specific aircraft version and for a particular runway specified at the top of the chart. The top of the chart also gives some information about the runway and lists the calculation assumptions. The chart is given for 2 different configurations and 4 wind values per configuration. This allows the crew to select the configuration that gives either : ‐ the highest permissible takeoff weight, or, for a given weight, ‐ the highest flexible temperature. If different configurations give equivalent performance, the crew should select the configuration associated with the lowest takeoff speeds. The left column of the chart contains weight entry. For each weight entry (and for a given configuration and wind), the chart provides the following information :
Note:
The takeoff weight is the sum of the weight entry and the delta weight.
The available limitation codes are : ‐ First segment ‐ Second segment ‐ Runway length ‐ Obstacles ‐ Tire speed ‐ Brake energy ‐ Maximum computation weight ‐ Final takeoff ‐ VMU
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
: : : : : : : : :
1 2 3 4 5 6 7 8 9
A
PER-TOF-TOC-16-20 P 1/4 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS Ident.: PER-TOF-TOC-16-20-00001729.0105001 / 04 MAR 11 Applicable to: ALL
Each takeoff chart is computed for a given set of conditions (air conditioning, QNH, anti ice...) specified at the top of the chart. If the actual takeoff conditions are different, the crew must apply corrections. Two types of corrections are available : ‐ Conservative corrections (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS) (to be used when not provided on the chart). ‐ Corrections (less restrictive) listed on the chart, to be applied as explained below. Note:
If the RTOW chart is based on the CG being at 25 %, the crew can find the takeoff performance at a more forward CG by decreasing the takeoff weight by 1 000 kg (2 200 lb) and increasing V1, VR and V2 by 1 kt. DESCRIPTION OF THE CORRECTIONS ON TAKEOFF CHART
Ident.: PER-TOF-TOC-16-20-00006633.0001001 / 08 MAR 11 Applicable to: ALL
The corrections are presented on 4 lines :
TVMC is a temperature value given per column. This is a fictitious value that indicates the temperature above which the speeds are close to a VMC limitation or are VMC limited. Note:
The lower two lines may be shaded on certain chart formats.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B to C
PER-TOF-TOC-16-20 P 2/4 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
MINIMUM SPEED Ident.: PER-TOF-TOC-16-20-00006634.0001001 / 04 MAR 11 Applicable to: ALL
Minimum V1/VR/V2 due to VMC are provided on the bottom right side of the takeoff chart. They are only applicable in case of speed corrections. These speeds are conservative. They may be slightly higher than V1/VR/V2 displayed on the takeoff chart.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D
PER-TOF-TOC-16-20 P 3/4 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-16-20 P 4/4 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
ADDITIONAL INFORMATION ONE ENGINE OUT CLIMB PROCEDURE Ident.: PER-TOF-TOC-16-30-00001730.0001001 / 10 DEC 09 Applicable to: ALL
The performance given in the chart is consistent with the flight path specified for the aircraft with one engine out and takes into account significant obstacles. When the procedure to be followed is not the standard instrument departure, the chart describes a specific procedure (EOSID). When the specified procedure requires a turn, except if otherwise stated on the RTOW chart, the turn should be performed with a maximum bank of 15 ° until the aircraft reaches 1 500 ft or until green dot. The acceleration height (or altitude) ensures that the net flight path clears the highest obstacle by at least 35 ft when accelerating in level flight to green dot speed after an engine failure, in the most adverse conditions. TAKEOFF ON A WET RUNWAY Ident.: PER-TOF-TOC-16-30-00001731.0002001 / 10 DEC 09 Applicable to: ALL
Takeoff charts computed for wet runway with a 15 ft screen height and/or use of reverse thrust may produce, in some conditions, a maximum takeoff weight (or flexible temperature) higher than that obtained for a dry runway. It is thus mandatory to compare both charts (dry and wet) and retain the lower of the two weights (or flexible temperature) and the associated speeds determined for a wet runway. Note:
The crew need not compare the charts if the top of the wet runway chart specifies “DRY CHECK”. (The comparison has already been inserted in the WET runway calculation).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
PER-TOF-TOC-16-30 P 1/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
RTOW CHARTS - COMPLEMENTARY INFORMATION Ident.: PER-TOF-TOC-16-30-00001732.0002001 / 10 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C→
PER-TOF-TOC-16-30 P 2/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C→
PER-TOF-TOC-16-30 P 3/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←C
PER-TOF-TOC-16-30 P 4/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
RTOW EXAMPLE Ident.: PER-TOF-TOC-16-30-00001733.0013001 / 10 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D
PER-TOF-TOC-16-30 P 5/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-16-30 P 6/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
DETERMINATION OF MAXIMUM TAKEOFF WEIGHT AND SPEEDS GENERAL Ident.: PER-TOF-TOC-18-10-00001734.0002001 / 10 DEC 09 Applicable to: ALL
The takeoff chart is computed for a given runway under a set of conditions, which are : ‐ OAT ‐ Wind ‐ Configuration ‐ QNH, air conditioning, anti ice... Two configurations are produced on the chart. This enables the crew to select that giving the highest permissible takeoff weight. In case of equivalent performance, retain the configuration giving the lower takeoff speeds.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOC-18-10 P 1/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
MTOW DETERMINATION Ident.: PER-TOF-TOC-18-10-00013648.0002001 / 01 MAR 11 Applicable to: ALL
Enter the chart with the given configuration and actual wind column reading the temperature value. This temperature value stands for the OAT. Read the maximum takeoff weight corresponding to the actual OAT. Note that it is allowed to interpolate between two consecutive lines to obtain the maximum takeoff weight. It is reminded that the takeoff weight is the sum of the weight entry and the delta weight. Similarly determine the takeoff speeds associated with the maximum takeoff weight. In some cases, it may happen that the first temperature value (displayed for the highest weight entry) is higher than OAT. In this case, it is allowed to extrapolate the weight value to avoid unnecessary penalty. Use the Grad 1/Grad 2 gradients provided at the bottom of the corresponding column. CORRECTION TO WEIGHT Grad 1/Grad 2 are gradients provided for both sides of the flat rating temperature (TREF). Grad 1 applies to temperatures below TREF and Grad 2 applies above TREF. Read the lowest temperature of the column (corresponding to the highest weight entry).
If the lowest temperature and OAT are above TREF. Obtain weight increment by multiplying Grad 2 by the difference in temperature between OAT and lowest temperature. Add this weight increment to the maximum takeoff weight calculated for the lowest temperature. If the lowest temperature and OAT are below TREF. Obtain weight increment by multiplying Grad 1 by the difference in temperature between OAT and lowest temperature. Add this weight increment to the maximum takeoff weight calculated for the lowest temperature. If OAT is below TREF and lowest temperature is above TREF. The weight increment is calculated in two steps. Step one is multiplying Grad 2 by temperature difference between lowest temperature and TREF. Step two is multiplying Grad 1 by temperature difference between TREF and OAT. Add results from step one and two to maximum takeoff weight calculated for lowest temperature.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B→
PER-TOF-TOC-18-10 P 2/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Note:
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
Use the weight gradients only to extrapolate above the maximum weight shown in the RTOW chart. They are not valid for interpolation between two boxes, between filled boxes or between one filled and one blank box.
Repeat the above process for the other available configuration and retain the configuration giving the highest takeoff weight. CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS Ident.: PER-TOF-TOC-18-10-00001736.0002001 / 11 FEB 11 Applicable to: ALL
Retain the maximum takeoff weight, associated configuration and speeds from above. For conditions different from those of the chart, apply relevant corrections.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← B to C
PER-TOF-TOC-18-10 P 3/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS Ident.: PER-TOF-TOC-18-10-00013716.0028001 / 18 MAR 11 Applicable to: ALL
Corrections are given for QNH ≠ 1 013 hPa, air conditioning ON, anti ice ON. 1. For the given wind and temperature conditions, determine the maximum takeoff weight (choose the configuration giving the highest weight). 2. Apply the published weight correction(s) to the maximum takeoff weight (for each correction) to determine the maximum permissible takeoff weight. 3. Read the speeds associated with the maximum permissible takeoff weight by entering the chart with the retained configuration and weight value. EXAMPLE A DATA :
OAT = 25 °C Head Wind = 10 kt Air conditioning ON QNH = 1 013 hPa Use the chart from (Refer to PER-TOF-TOC-16-30 RTOW EXAMPLE). Enter the 10 kt head wind column CONF 1 + F, to read for 25 °C The lowest temperature of the column is 45 °C, use Grad 1/Grad 2 to extrapolate the maximum takeoff weight. MAX TO weight (1 000 kg) air conditioning OFF = 80.6 + 0.46 × 1 + 0.06 × 19 = 82.2 Enter the 10 kt head wind column CONF 2, to read for 25 °C The lowest temperature of the column is 46 °C, use Grad 1/Grad 2 to extrapolate the maximum takeoff weight. MAX TO weight (1 000 kg) air conditioning OFF = 80.3 + 0.47 × 2 + 0.05 × 19 = 82.2 Retain CONF 1 + F as takeoff configuration. Maximum TO weight (1 000 kg) air conditioning OFF................................................................ 82.2 Air conditioning correction (PER_TOF_TOD_24 QNH/BLEEDS CORRECTION)........................-2.2 Maximum permissible TO weight (1 000 kg) air conditioning ON............................................ = 80.0 Determine takeoff speeds for 80.0 (1 000 kg) in the 10 kt head wind column (CONF 1 + F) V1 = 155 kt, VR = 156 kt, V2 = 158 kt CORRECTIONS FOR WET OR CONTAMINATED RUNWAYS Ident.: PER-TOF-TOC-18-10-00004071.0001001 / 10 DEC 09 Applicable to: ALL
(Refer to PER-TOF-CTA-10 GENERAL)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D to E
PER-TOF-TOC-18-10 P 4/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
FLIGHT CREW OPERATING MANUAL
CORRECTIONS PRODUCED ON THE RTOW CHART Ident.: PER-TOF-TOC-18-10-00006112.0017001 / 14 NOV 11 Applicable to: ALL
(Refer to PER-TOF-TOC-16-30 RTOW EXAMPLE). A description of this correction is given in PER-TOF-TOC-16-20 (Refer to PER-TOF-TOC-16-20 DESCRIPTION OF THE CORRECTIONS ON TAKEOFF CHART). The list of corrections is not exhaustive, however the most commonly used corrections are wet runway, QNH, air conditioning and/or anti ice. A maximum of three corrections can be produced on one chart. To apply the corrections, proceed as follows: 1. Determine the maximum takeoff weight before correction for the given OAT and wind condition. 2. Apply the first correction: If OAT is less than or equal to TVMC (line 3), apply ΔW correction from line 1 and ΔV1/ΔVR/ΔV2 corrections from line 2. Else, (for OAT greater than TVMC), apply ΔW correction from line 3 and ΔV1/ΔVR/ΔV2 corrections from line 4. 3. To combine a second (and third, as applicable) correction: If OAT is less than or equal to TVMC (line 3), apply ΔW correction from line 1 and ΔV1/ΔVR/ΔV2 corrections from line 2. Check that the resulting speeds are higher than the minimum speeds displayed on the RTOW chart and that V2 is higher than the VMU limited speed (Refer to PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS)). If OAT is higher than TVMC (line 3) or if the above speed check is not fulfilled, apply ΔW correction from line 3 and ΔV1/ΔVR/ΔV2 corrections from line 4. No speed check is required. Note:
‐ QNH correction is given for ±10 hPa. It is allowed to extrapolate linearly for greater QNH deviation. ‐ When using a takeoff chart with failure cases, it is not allowed to combine two failure cases. ‐ Corrections from the chart must be applied from top to bottom, i.e. in the RTOW (Refer to PER-TOF-TOC-16-30 RTOW EXAMPLE), apply the wet correction first. ‐ If asterisk or dotted lines appear in the correction boxes, refer to more conservative corrections provided in the FCOM. ‐ No speed check is required for the first correction. However, if the first influence correction follows a conservative FCOM correction, a speed check is required.
EXAMPLE B DATA :
OAT Head wind QNH
= = =
45 °C 10 kt 998 hPa
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F→
PER-TOF-TOC-18-10 P 5/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
WET runway Use the chart Refer to PER-TOF-TOC-16-30 RTOW EXAMPLE. • Enter the 10 kt head wind column CONF 1+F, to read for 45 °C max TO weight (1 000 kg).......................................................................................................80.6 • Enter the 10 kt head wind column CONF 2, to read for 45 °C max TO weight (1 000 kg).......................................................................................................80.3 • Retain CONF 1+F for takeoff • Read associated speeds as V1 = 155 kt, VR = 156 kt, V2 = 158 kt • Apply WET correction For OAT < TVMC (69 °C), ΔW =........................................................................................... – 0.7 Intermediate weight (1 000 kg).............................................................................................= 79.9 Associated speeds, V1 = 155 kt – 8 = 147 kt VR = 156 kt – 2 = 154 kt V2 = 158 kt – 2 = 156 kt (No speed check required for first correction) • Apply QNH correction For OAT < TVMC (61 °C), ΔW = – 0.7 × 15/10 =.....................................................................– 1 Maximum permissible takeoff weight (1 000 kg).................................................................. = 78.9 Associated speeds, V1 = 147 kt – 1 × 15/10 = 145 kt VR = 154 kt – 1 × 15/10 = 153 kt V2 = 156 kt – 1 × 15/10 = 155 kt • Check that the speeds are higher than minimum speeds from the chart and from VMU table. TOW TOW (RTOW) FCOM correction(s) Intermediate value WET Correction Intermediate value QNH Correction Final value
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
80.6 80.6 - 0.7 79.9 -1 78.9
←F
Takeoff Configuration: 1 + F V1 VR 155 156 155 -8 147 -2 145
156 -2 154 -1 153
V2 158 158 -2 156 -1 155
PER-TOF-TOC-18-10 P 6/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
COMBINING CORRECTIONS FROM FCOM AND CHART Ident.: PER-TOF-TOC-18-10-00006113.0030001 / 31 MAR 11 Applicable to: ALL
Proceed as follows: 1. Determine the maximum takeoff weight by entering the chart with selected configuration, OAT and wind. 2. Apply corrections from FCOM to determine an intermediate weight. Interpolate associated speeds for intermediate weight in the same column (same wind and configuration). 3. Apply corrections from RTOW chart as explained above. EXAMPLE C DATA
:
OAT = 25 °C Head wind = 10 kt Air conditioning ON QNH = 998 hPa WET runway
1. Use the chart Refer to PER-TOF-TOC-16-30 RTOW EXAMPLE. Enter the 10 kt head wind column CONF 1 + F, to read for 25 °C MAX TO weight (1 000 kg) air conditioning OFF = 80.6 + 0.46 × 1 + 0.06 × 19 = 82.2 Enter the 10 kt head wind column CONF 2, to read for 25 °C MAX TO weight (1 000 kg) air conditioning OFF = 80.3 + 0.47 × 2 + 0.05 × 19 = 82.2 Retain CONF 1 + F for takeoff configuration. 2. First, apply the correction Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS. Max TO weight (1 000 kg) air conditioning OFF..................................................................... 82.2 Air conditioning correction........................................................................................................ -2.2 Intermediate weight.............................................................................................................. = 80.0 Interpolate takeoff speeds for 80.0 (1 000 kg) in the 10 kt head wind column, V1 = 155 kt, VR = 156 kt, V2 = 158 kt 3. Apply WET correction For OAT < TVMC (69 °C), ΔW =............................................................................................. -0.7 Intermediate weight.............................................................................................................. = 79.3 Associated speeds, V1 = 155 kt - 8 = 147 kt VR = 156 kt - 2 = 154 kt V2 = 158 kt - 2 = 156 kt Apply QNH correction For OAT < TVMC (61 °C), ΔW = -0.7 × 15/10 =........................................................................ -1 Maximum permissible takeoff weight....................................................................................= 78.3 Associated speed, 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
G→
PER-TOF-TOC-18-10 P 7/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
V1 = 147 kt - 1 × 15/10 = 145 kt VR = 154 kt - 1 × 15/10 = 153 kt V2 = 156 kt - 1 × 15/10 = 155 kt Check that the speeds are higher than minimum speeds from the chart and from VMU table. (It is reminded that if the speed checks are not fulfilled, the corrections must be recalculated using those provided on lines 3 and 4). Since the speed check is fulfilled: MAX permissible takeoff weight = 78.3 (1 000 kg) V1 = 145 kt, VR = 153 kt, V2 = 155 kt.
TOW (RTOW) FCOM correction(s) Intermediate value WET Correction Intermediate value QNH Correction Final value
Takeoff Configuration: 1 + F V1 VR
TOW 82.2
V2
-2.2 80.0
155
156
-0.7
-8
-2
158 -2
79.3
147
154
156
-1
-2
-1
-1
78.3
145
153
155
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←G
PER-TOF-TOC-18-10 P 8/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
EXTRAPOLATION EXTRAPOLATION Ident.: PER-TOF-TOC-18-20-00001740.0002001 / 08 MAR 11 Applicable to: ALL
For OAT lower than the lowest temperature value of a wind column, it is possible to obtain a higher maximum permissible takeoff weight by using Grad 1/Grad 2 values. Refer to PER-TOF-TOC-18-10 MTOW DETERMINATIONfor more details.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOC-18-20 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-18-20 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
MAXIMUM STRUCTURAL TAKEOFF WEIGHT MAXIMUM STRUCTURAL TAKEOFF WEIGHT Ident.: PER-TOF-TOC-18-30-00001741.0001001 / 01 MAR 11 Applicable to: ALL
The maximum structural takeoff weight is a weight limitation depending on the aircraft. This limitation is provided in the Flight Manual and in the limitation chapter (Refer to LIM-11 Weight Limitations). Compare the maximum structural takeoff weight to the maximum permissible takeoff weight computed for given conditions and retain the lower of the two values.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOC-18-30 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-18-30 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
SUMMARY
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-18-40 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
SUMMARY Ident.: PER-TOF-TOC-18-40-00006114.0001001 / 17 MAR 11 Applicable to: ALL
The following flow diagram gives the different steps to follow.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOC-18-40 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
DETERMINATION OF FLEXIBLE TAKEOFF TEMPERATURE AND SPEEDS GENERAL Ident.: PER-TOF-TOC-20-10-00013509.0002001 / 23 FEB 11 Applicable to: ALL
Before determining the flexible temperature, calculate the maximum permissible takeoff weight (see previous section) and ensure that the actual takeoff weight is lower than the determined maximum takeoff weight. ‐ For a given configuration and wind value, enter the RTOW chart with the actual takeoff weight to read the flexible temperature and associated speeds. It is reminded that the takeoff weight is the sum of the weight entry and the delta weight displayed in each box. It is allowed to interpolate between two consecutive rows and/or columns for weight and for wind values not displayed on the chart. ‐ Repeat this process for the other configuration available. Select that configuration giving the highest flexible temperature. CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS Ident.: PER-TOF-TOC-20-10-00013506.0001001 / 23 FEB 11 Applicable to: ALL
When the takeoff conditions are different from those provided on the chart, apply the associated corrections. Note:
If the RTOW chart is based on the CG being at 25 %, the crew can determine the flexible temperature at a more forward CG by decreasing the flexible temperature by 2 °C. V1, VR and V2 must be increased by 1 kt.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
PER-TOF-TOC-20-10 P 1/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS Ident.: PER-TOF-TOC-20-10-00013212.0006001 / 31 MAR 11 Applicable to: ALL
Corrections are given for QNH ≠ 1 013 hPa, air conditioning ON, anti ice ON. 1. For a given takeoff weight, wind condition and selected configuration, read the flexible temperature. Retain the takeoff speeds associated with the actual weight. 2. Apply the published temperature correction. To combine two or more corrections, add the different corrections and apply to temperature value. (No speed corrections required). EXAMPLE D DATA :
Actual takeoff weight = 68 000 kg Head wind = 10 kt Air conditioning ON QNH = 1 013 hPa Use the chart from Refer to PER-TOF-TOC-16-30 RTOW EXAMPLE. Determine the maximum permissible takeoff weight (Refer to PER-TOF-TOC-18-10 CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS). The actual weight being lower than the maximum one, flexible takeoff is possible. Enter the 10 kt head wind column and interpolate for 68 000 kg, CONF 1 + F, Flexible temperature.................................................................................................................. 67 °C Enter the 10 kt head wind column and interpolate for 68 000 kg, CONF 2, Flexible temperature.................................................................................................................. 66 °C Retain CONF 1 + F for takeoff configuration. Takeoff speeds are V1 = 153 kt, VR = 153 kt, V2 = 154 kt Flexible temperature with air conditioning OFF.........................................................................67 °C Air conditioning correction.......................................................................................................... -7 °C (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS) Maximum flexible temperature............................................................................................... = 60 °C CORRECTIONS FOR WET RUNWAY Ident.: PER-TOF-TOC-20-10-00013280.0001001 / 18 FEB 11 Applicable to: ALL
Refer to PER-TOF-CTA-10 GENERAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C to D
PER-TOF-TOC-20-10 P 2/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
CORRECTIONS PRODUCED ON THE RTOW CHART Ident.: PER-TOF-TOC-20-10-00013507.0010001 / 06 APR 11 Applicable to: ALL
A description of this correction is given on Refer to PER-TOF-TOC-16-20 CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS. The list of corrections is not exhaustive, however the most commonly used corrections are wet runway, QNH, air conditioning and/or anti-icing. A maximum of three corrections can be produced on one chart. To apply the correction, proceed as follows: 1. Enter the chart with selected configuration, wind and actual takeoff weight to read the flexible temperature associated with this weight. 2. Apply the first correction: If the flexible temperature is less than or equal to TVMC (line 3), apply ΔTflex correction from line 1 and apply speed corrections (ΔV1/ΔVR/ΔV2) from line 2. Else, (flexible temperature greater than TVMC), apply ΔTflex from line 3 and ΔV1/ ΔVR/ ΔV2 corrections from line 4. Check V2 against VMU limitation (Refer to PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS)). If V2 is lower than V2 limited by VMU, flexible takeoff is not possible. Set TOGA thrust and retain the speeds associated with maximum permissible takeoff weight or the speeds read in the chart for the actual weight if they are all lower. No speed correction is required for QNH and bleeds influence (Not applicable to maximum takeoff weight determination). 3. To combine a second and/or a third correction, proceed as per point 2. 4. Check that the final flexible temperature is: ‐ Higher than OAT and TREF ‐ Limited toTMAXFLEX If the check is fulfilled, retain final flexible temperature as the one to be inserted in the MCDU If the check is not fulfilled, (final flexible temperature lower than OAT or TREF), no flexible takeoff is possible. Use TOGA thrust and retain speeds that have been calculated for the maximum permissible takeoff weight. (Refer to PER-TOF-TOC-20-20 FLEXIBLE TAKEOFF NOT POSSIBLE) Note:
‐ QNH correction is given for ± 10 hPa . It is allowed to extrapolate linearly for greater QNH deviation. ‐ Corrections from the chart must be applied from the top to bottom, i.e in the RTOW on Refer to PER-TOF-TOC-16-30 RTOW EXAMPLE, apply the wet influence first
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E→
PER-TOF-TOC-20-10 P 3/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Note:
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
‐ When the flexible temperature is higher than TVMC, it is allowed to limit the flexible temperature to TVMC and apply only corrections from lines 1 and 2. ‐ If asterisk or dotted lines appear in the correction boxes, refer to more conservative corrections provided in the FCOM.
EXAMPLE E DATA :
Actual takeoff weight = 68 000 kg Head wind = 10 kt QNH = 998 hPa WET runway Air conditioning OFF Use the chart from Refer to PER-TOF-TOC-16-30 RTOW EXAMPLE. Determine the maximum permissible takeoff weight (Refer to PER-TOF-TOC-18-10 CORRECTIONS PRODUCED ON THE RTOW CHART) The actual weight being lower than the maximum one, flexible takeoff is possible. Enter the 10 kt head wind column and interpolate for 68 000 kg, CONF 1+F, Flexible temperature.................................................................................................................. 67 °C Enter the 10 kt head wind column and interpolate for 68 000 kg, CONF 2, Flexible temperature.................................................................................................................. 66 °C Retain CONF 1+F as the flexible temperature is higher. Takeoff speeds are V1 = 153 kt, VR = 153 kt, V2 = 154 kt Apply WET correction For flexible temperature < TVMC (69 °C), ΔTflex =...................................................................-2 °C Intermediate flex temperature................................................................................................ = 65 °C Associated speeds, V1 = 153 kt – 8 = 145 kt VR = 153 kt –2 = 151 kt V2 = 154 kt – 2 = 152 kt check V2 against VMU limitation (Refer to PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS) ). Apply QNH correction For flex temperature ≥ TVMC (61 °C), ΔTflex =....................................................................... –3 °C Maximum flexible temperature............................................................................................... = 62 °C Check that OAT/TREF > flex temperature ≤ TMAXFLEX No speed correction. Takeoff speeds are V1 = 145 kt, VR = 151 kt, V2 = 152 kt Takeoff Configuration : 1 + F Continued on the following page
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←E→
PER-TOF-TOC-20-10 P 4/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
FLIGHT CREW OPERATING MANUAL
Continued from the previous page
Tflex Tflex Chart temperature FCOM correction(s) Intermediate value WET Correction Intermediate value QNH Correction Final value
67
Takeoff Configuration : 1 + F V1 VR V1 VR 153
67 –2 65 –3 62
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
153 –8 145 0 145
←E
V2 V2 153
154
153 −2 151 0 151
154 −2 152 0 152
PER-TOF-TOC-20-10 P 5/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
COMBINING CORRECTIONS FROM FCOM AND CHART Ident.: PER-TOF-TOC-20-10-00012742.0040001 / 18 MAR 11 Applicable to: ALL
1. Apply corrections from FCOM (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS). 2. Apply corrections from the RTOW chart. Apply speed corrections except for QNH and bleed influences. EXAMPLE F DATA :
Actual takeoff weight = 68 000 kg Head wind = 10 kt Air conditioning ON QNH = 998 hPa WET runway
Use the chart fromRefer to PER-TOF-TOC-16-30 RTOW EXAMPLE. Determine the maximum permissible takeoff weight (see example C). The actual weight being lower than the maximum one, flexible takeoff is possible. ‐ Enter the 10 kt head wind column and interpolate for 68 000 kg, CONF 1+F, Flexible temperature.............................................................................................................. 67 °C ‐ Enter the 10 kt head wind column and interpolate for 68 000 kg, CONF 2, Flexible temperature.............................................................................................................. 66 °C ‐ Retain CONF 1+F for takeoff configuration. Takeoff speeds are V1 = 153 kt, VR = 153 kt, V2 = 154 kt ‐ First, apply the correction from FCOM (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS). Flexible temperature with air conditioning OFF.....................................................................67 °C Air conditioning correction...................................................................................................... -7 °C Intermediate flexible temperature.......................................................................................= 60 °C No speed correction. ‐ Apply WET correction For flexible temperature < TVMC (69 °C), ΔTflex =...............................................................-2 °C Intermediate flex temperature............................................................................................ = 58 °C Associated speeds, V1 = 153 kt - 8 = 145 kt VR = 153 kt - 2 = 151 kt V2 = 154 kt - 2 = 152 kt Check V2 against VMU limitation on FCOMRefer to PER-TOF-TOD-25-10 SPEEDS LIMITED BY VMC. ‐ Apply QNH correction For flexible temperature < TVMC (61 °C), ΔTflex =...............................................................-3 °C 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F→
PER-TOF-TOC-20-10 P 6/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
Maximum flexible temperature........................................................................................... = 55 °C Check that OAT/TREF < flex temperature ≤ TMAXFLEX No speed correction. Takeoff speeds are V1 = 145 kt, VR = 151 kt, V2 = 152 kt
Chart temperature FCOM correction(s) Intermediate value WET Correction Intermediate value QNH Correction Final value
Takeoff Configuration : 1 + F V1 VR 153 153
Tflex 67
V2 154
-7
0
0
0
60
153
153
154
-2
-8
-2
-2
58
145
151
152
-3
0
0
0
55
145
151
152
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←F
PER-TOF-TOC-20-10 P 7/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-20-10 P 8/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
FLEXIBLE TAKEOFF NOT POSSIBLE FLEXIBLE TAKEOFF NOT POSSIBLE Ident.: PER-TOF-TOC-20-20-00013281.0001001 / 18 FEB 11 Applicable to: ALL
In some cases when the actual takeoff weight is lower than the maximum permissible one but no flexible takeoff possible (that is flexible temperature lower than TREF or OAT): ‐ It is mandatory to use TOGA thrust ‐ You can retain the speeds that have been calculated for the maximum permissible takeoff weight; OR ‐ You can retain the speeds associated with the actual takeoff weight provided they are all lower than the speeds calculated for the maximum permissible takeoff weight.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOC-20-20 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-20-20 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
SUMMARY
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-20-30 P 1/4 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
SUMMARY Ident.: PER-TOF-TOC-20-30-00013282.0001001 / 24 MAR 11 Applicable to: ALL
The flow diagram gives the different steps to follow
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
PER-TOF-TOC-20-30 P 2/4 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
PER-TOF-TOC-20-30 P 3/4 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOC-20-30 P 4/4 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QNH/BLEEDS CORRECTION
EFFECT OF QNH AND BLEEDS (UP TO 9200 FT) Ident.: PER-TOF-TOD-24-00012927.0081001 / 31 MAR 11 Applicable to: ALL
Note:
‐ * Corrections valid only for OAT < 10 °C ‐ For high altitude operation, REFER TO PER-TOF-TOD-24 EFFECT OF QNH FOR HIGH ALTITUDE OPERATIONS (if applicable).
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOD-24 P 1/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QNH/BLEEDS CORRECTION
EXAMPLES Ident.: PER-TOF-TOD-24-00012924.0055001 / 28 FEB 11 Applicable to: ALL
TAKEOFF CHART DATA Airport geometric elevation = 450 ft QNH = 1 013 hPa Anti ice OFF Air conditioning OFF EXAMPLE 1 - FULL THRUST TAKEOFF Actual data :
OAT = 5 °C QNH = 1 040 hPa Engine anti ice ON Air conditioning OFF Weight read in the takeoff chart: 73 000 kg Read in the above table the corrections for high QNH and engine anti ice ON. QNH correction: none Engine anti ice correction: - 300 kg The maximum permissible takeoff weight is 73 000 + 0 - 300 = 72 700 kg EXAMPLE 2 - FLEXIBLE THRUST TAKEOFF Actual data :
OAT = 5 °C QNH = 1 040 hPa Anti ice OFF Air conditioning ON TOW = 65 000 kg Flexible temperature read on the takeoff chart: TFLEX = 55 °C. Read TREF on the takeoff chart or on the quick reference table. Read in the above table the correction for QNH and air conditioning ON: QNH correction = none Air conditioning ON correction: -7 °C New flexible temperature = 55 - 7 = 48 °C Check that the flexible temperature is above TREF and actual OAT. Check that the flexible temperature is less than the maximum flexible temperature and retain the lower of the two.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
PER-TOF-TOD-24 P 2/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QNH/BLEEDS CORRECTION
EFFECT OF QNH AND BLEEDS FOR HIGH ALTITUDE OPERATIONS (ABOVE 9200 FT) Ident.: PER-TOF-TOD-24-00012926.0055001 / 24 MAR 11 Applicable to: ALL
Note:
* Corrections valid only for OAT < 10 °C
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
PER-TOF-TOD-24 P 3/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QNH/BLEEDS CORRECTION
EXAMPLES FOR HIGH ALTITUDE OPERATIONS Ident.: PER-TOF-TOD-24-00012925.0070001 / 18 MAR 11 Applicable to: ALL
TAKEOFF CHART DATA Airport geometric elevation = 11 500 ft QNH = 1 013 hPa Anti ice OFF Air conditioning OFF OAT = 0 °C MTOW = 73 000 kg EXAMPLE 1 - FULL THRUST TAKEOFF Actual data :
QNH = 1 040 hPa Engine anti ice ON Air conditioning OFF Determine the actual airport pressure altitude (1 hPa is equivalent to 28 ft according to the ISA model). Pressure altitude = 11 500 - (1 040 - 1 013) × 28 = 10 744 ft Read in the above table the corrections for high QNH and engine anti ice ON. QNH correction = 60 kg × (11 500 - 10 744)/28 hPa = +1 620 kg Engine anti ice correction: 1 800 kg The maximum permissible takeoff weight is 73 000 + 1 620 - 1 800 = 72 820 kg EXAMPLE 2 - FLEXIBLE THRUST TAKEOFF Actual data :
QNH = 1 040 hPa Anti ice OFF Air conditioning ON TOW = 65 000 kg TFLEX = 55 °C Read TREF on the takeoff chart or on the quick reference table. Determine the actual airport pressure altitude (1 hPa is equivalent to 28 ft according to the ISA model). Pressure altitude = 11 500 - (1 040 - 1 013) × 28 = 10 744 ft Read in the above table the correction for QNH and air conditioning ON: QNH correction = 1 °C/11 hPa × (11 500 - 10 744)/28 hPa = +3 °C Air conditioning ON correction = -5 °C New flexible temperature = 55 + 3 - 5 = 53 °C Check that the flexible temperature is above TREF and actual OAT.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D→
PER-TOF-TOD-24 P 4/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QNH/BLEEDS CORRECTION
Check that the flexible temperature is less than the maximum flexible temperature and retain the lower of the two.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←D
PER-TOF-TOD-24 P 5/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QNH/BLEEDS CORRECTION
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOD-24 P 6/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
TAKEOFF DATA - MINIMUM SPEEDS
FLIGHT CREW OPERATING MANUAL
SPEEDS LIMITED BY VMC SPEEDS LIMITED BY VMC Ident.: PER-TOF-TOD-25-10-00001754.0268001 / 16 MAY 12 Applicable to: ALL
All takeoff speeds have a minimum value limited by control. These minimum speeds are usually provided on each RTOW chart. If these speeds are not available, use the following conservative values. These speeds may be slightly higher than the minimum control speeds displayed on the RTOW chart. CONF
1+F 2 3 CONF
1+F 2 3 CONF
1+F 2 3
MINIMUM V1 (KT IAS) PRESSURE ALTITUDE (FT) 2 000 3 000 4 000 5000 6 000
-2 000
0
1 000
7 000
8 000
9 200
14 100
117
115
114
113
112
112
111
110
109
108
106
100
115
113
112
111
111
110
109
108
107
106
104
100
114
112
111
110
110
110
109
108
107
105
104
100
MINIMUM VR (KT IAS) PRESSURE ALTITUDE (FT) 2 000 3 000 4 000 5000 6 000
-2 000
0
1 000
7 000
8 000
9 200
10 200
121
119
118
116
116
116
115
114
113
111
110
102
119
117
116
115
114
114
113
112
111
109
108
100
118
116
115
114
114
114
113
112
110
109
107
100
MINIMUM V2 (KT IAS) PRESSURE ALTITUDE (FT) 2 000 3 000 4 000 5000 6 000
-2 000
0
1 000
7 000
8 000
9 200
10 200
124
121
120
119
119
119
118
117
115
114
112
104
123
121
120
119
119
119
117
116
115
114
112
103
123
121
120
119
119
118
117
116
115
114
112
103
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOD-25-10 P 1/2 30 MAY 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
TAKEOFF DATA - MINIMUM SPEEDS
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOD-25-10 P 2/2 30 MAY 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
TAKEOFF DATA - MINIMUM SPEEDS
FLIGHT CREW OPERATING MANUAL
V2 LIMITED BY VMU/VMCA
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOD-25-20 P 1/4 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - MINIMUM SPEEDS
MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS) Ident.: PER-TOF-TOD-25-20-00001756.0095001 / 25 MAR 11 Applicable to: ALL
The following tables, one per configuration, provide the V2 limited by minimum unstick speed and minimum control speed in the air.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
PER-TOF-TOD-25-20 P 2/4 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
TAKEOFF DATA - MINIMUM SPEEDS
←A→
PER-TOF-TOD-25-20 P 3/4 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
TAKEOFF DATA - MINIMUM SPEEDS
←A
PER-TOF-TOD-25-20 P 4/4 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QUICK REFERENCE TABLES
INTRODUCTION INTRODUCTION Ident.: PER-TOF-TOD-40-10-00001758.0001001 / 14 DEC 09 Applicable to: ALL
These tables enable the crew to quickly determine the takeoff performance at an airport for which no takeoff chart has been established. They are conservative.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOD-40-10 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QUICK REFERENCE TABLES
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOD-40-10 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QUICK REFERENCE TABLES
USE OF TABLES USE OF TABLES Ident.: PER-TOF-TOD-40-20-00001759.0002001 / 25 MAR 11 Applicable to: ALL
A first table gives the corrections to be applied to the runway length for wind and runway slope. Nine other tables give, for three different pressure altitudes (0, 1 000 and 2 000 ft) and three configurations, the maximum takeoff weight, limitation codes and associated speeds as a function of temperature and corrected runway length. TREF and TMAX are given on the top of each table. For pressure altitudes above 2 000 ft, use a specific RTOW chart. Note:
1. Quick reference tables are established for the forward CG envelope (less than 25 %) at V1 min with air conditioning OFF and anti ice OFF 2. Do not use quick reference tables in case of tailwind.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOD-40-20 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QUICK REFERENCE TABLES
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOD-40-20 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QUICK REFERENCE TABLES
HOW TO PROCEED GENERAL Ident.: PER-TOF-TOD-40-30-00001760.0001001 / 28 JAN 11 Applicable to: ALL
HOW TO PROCEED 1. Enter the first table with runway length, slope and wind data. Determine the corrected runway length by applying the corrections due to slope and wind. 2. Select the configuration as a function of this corrected runway length. 3. Enter the table(s) corresponding to the configuration and airport pressure altitude. As far as airport pressure altitude is concerned, two methods may be applied : ‐ interpolate the takeoff performance by using the two tables enclosing the airport pressure altitude, ‐ for a more conservative figure, use the table corresponding to the pressure altitude immediately above the airport pressure altitude. 4. Enter the appropriate column of the table(s) with the corrected runway length. Once again, two methods may be applied : ‐ interpolate the takeoff performance between the two columns enclosing the corrected runway length, ‐ for a more conservative figure, use the column corresponding to the shorter corrected runway length. 5. Determination of maximum takeoff weight. Enter the table(s) and column(s) as explained above with the actual OAT and read maximum takeoff weight, limitation codes, V1, VR and V2. If necessary interpolate weight and speeds. 6. Determination of flexible temperature. The determination of flexible temperature is possible only when there is no obstacle on the flight path. Enter the table(s) and column(s) with the actual takeoff weight and read the corresponding temperature as flexible temperature. 7. In case of obstacles, use the graphs (Refer to PER-TOF-TOD-50 INTRODUCTION ) to determine the corresponding weight penalty.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOD-40-30 P 1/4 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
TAKEOFF DATA - QUICK REFERENCE TABLES
FLIGHT CREW OPERATING MANUAL
LIMITATION CODES Ident.: PER-TOF-TOD-40-30-00001761.0002001 / 25 FEB 11 Applicable to: ALL
‐ ‐ ‐ ‐ ‐ ‐ ‐ ‐
1 2 3 5 6 7 8 9
Note:
: : : : : : : :
first segment second segment runway tire speed brake energy maximum computation weight final takeoff VMU 1. Limitation code 4 (obstacles) does not appear in quick reference tables. 2. VMC limitation appears with an asterisk (*) in the chart. CORRECTIONS FOR WIND AND RUNWAY SLOPE
Ident.: PER-TOF-TOD-40-30-00001762.0013001 / 04 MAR 11 Applicable to: ALL
Runway length (m) Effect per knot of head of wind wind add (meters) per percent uphill slope Effect of subtract (meters) runway per percent slope downhill slope add (meters)
1 500
1 750
2 000
2 250
2 500
2 750
3 000
3 250
3 500
6.5
7
8
8.5
9.5
10
11
11.5
12.5
160
215
270
325
380
435
490
545
600
17
23
29
36
42
48
55
61
67
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B to C
PER-TOF-TOD-40-30 P 2/4 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QUICK REFERENCE TABLES
EXAMPLE Ident.: PER-TOF-TOD-40-30-00001763.0323001 / 25 MAR 11 Applicable to: ALL
Pressure altitude : Temperature : Runway length : Wind : Slope : Takeoff configuration:
1 400 ft 30 °C 2 750 m 10 kt head 1 % up 1+F
DETERMINATION OF CORRECTED RUNWAY LENGTH (Refer to PER-TOF-TOD-40-30 CORRECTIONS FOR WIND AND RUNWAY SLOPE ) runway length .......................................................................................................................2 750 m correction for wind................................................................................................10 × 10 = + 100 m correction for slope................................................................................................................ - 435 m corrected runway length.....................................................................................................= 2 415 m DETERMINATION OF A CONSERVATIVE MAXIMUM TAKEOFF WEIGHT : (Refer to PER-TOF-TOD-40-40 CONFIGURATION 1+F / 2000 FT) ‐ Pressure altitude : 1 400 ft - Use the table for 2 000 ft. ‐ Enter the column corresponding to 2 250 m ‐ Read the maximum takeoff weight on the line corresponding to the temperature of 30 °C : 71 300 kg V1 = 139 kt, VR = 146 kt, V2 = 148 kt DETERMINATION OF A PRECISE FLEXIBLE TEMPERATURE FOR THE ACTUAL TAKEOFF WEIGHT OF 64000 KG : (Refer to PER-TOF-TOD-40-40 CONFIGURATION 1+F / 1000 FT) (Refer to PER-TOF-TOD-40-40 CONFIGURATION 1+F / 2000 FT) ‐ Interpolate the temperature corresponding to 64 000 kg for the runway length of 2 415 m at 1 000 ft and 2 000 ft pressure altitude. Results : 1 000 ft : 61 °C, V1 = 138 kt, VR = 139 kt, V2 = 140 kt 2 000 ft : 57 °C, V1 = 137 kt, VR = 139 kt, V2 = 140 kt ‐ Interpolate between these two values to get the flexible temperature 1 400 ft : 59 °C, V1 = 137 kt, VR = 139 kt, V2 = 140 kt
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D
PER-TOF-TOD-40-30 P 3/4 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QUICK REFERENCE TABLES
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOD-40-30 P 4/4 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QUICK REFERENCE TABLES
QUICK REFERENCE TABLES CONFIGURATION 1+F / 0 FT Ident.: PER-TOF-TOD-40-40-00001764.0327001 / 02 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-TOD-40-40 P 1/10 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QUICK REFERENCE TABLES
CONFIGURATION 1+F / 1000 FT Ident.: PER-TOF-TOD-40-40-00001765.0348001 / 02 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
B
PER-TOF-TOD-40-40 P 2/10 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QUICK REFERENCE TABLES
CONFIGURATION 1+F / 2000 FT Ident.: PER-TOF-TOD-40-40-00001766.0324001 / 04 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C
PER-TOF-TOD-40-40 P 3/10 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QUICK REFERENCE TABLES
CONFIGURATION 2 / PRESSURE ALTITUDE = 0 FT Ident.: PER-TOF-TOD-40-40-00001767.0323001 / 18 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
D
PER-TOF-TOD-40-40 P 4/10 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QUICK REFERENCE TABLES
CONFIGURATION 2 / PRESSURE ALTITUDE = 1000 FT Ident.: PER-TOF-TOD-40-40-00001768.0142001 / 08 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E
PER-TOF-TOD-40-40 P 5/10 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QUICK REFERENCE TABLES
CONFIGURATION 2 / PRESSURE ALTITUDE = 2000 FT Ident.: PER-TOF-TOD-40-40-00001769.0149001 / 21 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
F
PER-TOF-TOD-40-40 P 6/10 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QUICK REFERENCE TABLES
CONFIGURATION 3 / PRESSURE ALTITUDE = 0 FT Ident.: PER-TOF-TOD-40-40-00001770.0067001 / 07 MAR 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
G
PER-TOF-TOD-40-40 P 7/10 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QUICK REFERENCE TABLES
CONFIGURATION 3 / PRESSURE ALTITUDE = 1000 FT Ident.: PER-TOF-TOD-40-40-00001771.0324001 / 09 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
H
PER-TOF-TOD-40-40 P 8/10 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QUICK REFERENCE TABLES
CONFIGURATION 3 / PRESSURE ALTITUDE = 2000 FT Ident.: PER-TOF-TOD-40-40-00001772.0078001 / 09 FEB 11 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
I
PER-TOF-TOD-40-40 P 9/10 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - QUICK REFERENCE TABLES
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-TOD-40-40 P 10/10 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
TAKEOFF DATA - NET TAKEOFF FLIGHT PATH
FLIGHT CREW OPERATING MANUAL
INTRODUCTION Ident.: PER-TOF-TOD-50-00001773.0001001 / 15 DEC 09 Applicable to: ALL
The following graphs enable the crew to quickly determine the takeoff performance out of an airport by positioning obstacles. They must be used with the corresponding quick reference table so as to determine weight decrement and required gradient. The net takeoff flight path and the associated weight decrement are conservative. HOW TO PROCEED Ident.: PER-TOF-TOD-50-00001774.0001001 / 03 MAR 11 Applicable to: ALL
1. Position the obstacle by entering its distance from end of runway and its height above the end of runway (No 35 ft margin is required as this is already included). In case of an ascending runway, increase the obstacle height by an additional value as indicated below each graph. 2. Read the associated weight correction. Interpolate if necessary. The second segment gradient is given for information only. 3. Decrease the takeoff speeds by 1 kt per 1 000 kg (0.5 kt per 1 000 lb) weight decrement. Limit the final speeds to the minimum values (Refer to PER-TOF-TOD-25-10 SPEEDS LIMITED BY VMC). Note:
In case of tailwind, do not use the obstacle clearance graphs.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A to B
PER-TOF-TOD-50 P 1/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
TAKEOFF DATA - NET TAKEOFF FLIGHT PATH
CLOSE OBSTACLE CLEARANCE CONF 1 + F Ident.: PER-TOF-TOD-50-00001775.0027001 / 11 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C→
PER-TOF-TOD-50 P 2/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Note:
TAKEOFF DATA - NET TAKEOFF FLIGHT PATH
In case of ascending runway, increase obstacle height by 50 ft per percent runway slope. REMOTE OBSTACLE CLEARANCE CONF 1 + F
Ident.: PER-TOF-TOD-50-00001776.0058001 / 08 MAR 11 Applicable to: ALL
Note:
In case of ascending runway, increase obstacle height by 50 ft per percent runway slope.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← C to D
PER-TOF-TOD-50 P 3/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
TAKEOFF DATA - NET TAKEOFF FLIGHT PATH
FLIGHT CREW OPERATING MANUAL
CLOSE OBSTACLE CLEARANCE CONF 2 Ident.: PER-TOF-TOD-50-00001777.0049001 / 11 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E→
PER-TOF-TOD-50 P 4/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
TAKEOFF DATA - NET TAKEOFF FLIGHT PATH
FLIGHT CREW OPERATING MANUAL
Note:
In case of ascending runway, increase obstacle height by 50 ft per percent runway slope. REMOTE OBSTACLE CLEARANCE CONF 2
Ident.: PER-TOF-TOD-50-00001778.0044001 / 08 MAR 11 Applicable to: ALL
Note:
In case of ascending runway, increase obstacle height by 50 ft per percent runway slope.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← E to F
PER-TOF-TOD-50 P 5/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
TAKEOFF DATA - NET TAKEOFF FLIGHT PATH
FLIGHT CREW OPERATING MANUAL
CLOSE OBSTACLE CLEARANCE CONF 3 Ident.: PER-TOF-TOD-50-00001779.0025001 / 14 DEC 09 Applicable to: ALL
Note:
In case of ascending runway, increase obstacle height by 50 ft per percent runway slope.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
G
PER-TOF-TOD-50 P 6/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
TAKEOFF DATA - NET TAKEOFF FLIGHT PATH
FLIGHT CREW OPERATING MANUAL
REMOTE OBSTACLE CLEARANCE CONF 3 Ident.: PER-TOF-TOD-50-00001780.0025001 / 11 DEC 09 Applicable to: ALL
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
H→
PER-TOF-TOD-50 P 7/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
Note:
TAKEOFF DATA - NET TAKEOFF FLIGHT PATH
In case of ascending runway, increase obstacle height by 50 ft per percent runway slope.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←H
PER-TOF-TOD-50 P 8/8 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
RUNWAY CONTAMINATION - GENERAL
GENERAL Ident.: PER-TOF-CTA-10-00001781.0001001 / 21 MAR 11 Applicable to: ALL
This section presents the recommendations of Airbus for operations from wet runways or from runways which are covered with contaminants such as standing water, slush or snow. CAUTION
Takeoff from an icy runway is not recommended.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-CTA-10 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321
RUNWAY CONTAMINATION - GENERAL
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-CTA-10 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321
RUNWAY CONTAMINATION - DEFINITIONS
FLIGHT CREW OPERATING MANUAL
DEFINITIONS Ident.: PER-TOF-CTA-20-00001782.0001001 / 28 JAN 11 Applicable to: ALL
DAMP
:
WET
:
STANDING WATER : SLUSH
:
WET SNOW
:
DRY SNOW
:
COMPACTED SNOW: ICY
:
A runway is damp when the surface is not dry, but when the water on it does not give it a shiny appearance. A runway is considered as wet when the surface has a shiny appearance due to a thin layer of water. When this layer does not exceed 3 mm depth, there is no substantial risk of hydroplaning. is caused by heavy rainfall and /or insufficient runway drainage with a depth of more than 3 mm. is water saturated with snow which spatters when stepping firmly on it. It is encountered at temperatures around 5 °C and its density is approximately 0.85 kg/l (7.1 lb/US Gal). is a condition where, if compacted by hand, snow will stick together and tend to form a snowball. Its density is approximately 0.4 kg/l (3.35 lb/US Gal). is a condition where snow can be blown if loose, or if compacted by hand, will fall apart again upon release. Its density is approximately 0.2 kg/l (1.7 lb/US Gal). is a condition where snow has been compressed (a typical friction coefficient is 0.2). is a condition where the friction coefficient is 0.05 or below.
The performance given in this chapter has been divided into two categories which are determined by the depth of the contaminant. For each of these categories an equivalent depth of contaminant has been defined for which the performance deterioration is the same. 1. WET RUNWAY and EQUIVALENT Equivalent of a wet runway is a runway covered with or less than : ‐ 3 mm (0.12 in) slush ‐ 3 mm (0.12 in) water ‐ 4 mm (0.16 in) wet snow ‐ 15 mm (0.59 in) dry snow 2. CONTAMINATED RUNWAY An equivalence between depth of slush and snow has been defined : ‐ 12.7 mm (1/2 in) wet snow is equivalent to 6.3 mm (1/4 in) slush ‐ 25.4 mm (1 in) wet snow is equivalent to 12.7 mm (1/2 in) slush ‐ 50.8 mm (2 in) dry snow is equivalent to 6.3 mm (1/4 in) slush 2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
PER-TOF-CTA-20 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
RUNWAY CONTAMINATION - DEFINITIONS
‐ 101.6 mm (4 in) dry snow is equivalent to 12.7 mm (1/2 in) slush Note:
1. On a damp runway no performance degradation should be considered. 2. It is not recommended to take off from a runway covered with more than 4 in of dry snow or 1 in of wet snow.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
←A
PER-TOF-CTA-20 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
RUNWAY CONTAMINATION - OPERATIONAL CONDITIONS
OPERATIONAL CONDITIONS Ident.: PER-TOF-CTA-30-00001783.0001001 / 14 DEC 09 Applicable to: ALL
Performance penalties for takeoff as published in this section are computed with the following assumptions : ‐ The contaminant is in a layer of uniform depth and density over the entire length of the runway. ‐ Antiskid and spoilers are operative. ‐ The friction coefficient is based on studies and checked by actual tests. ‐ The screen height at the end of takeoff segment is 15 ft, not 35 ft. In addition, for contaminated runways only : ‐ There is drag due to rolling resistance of the wheels. ‐ There is drag due to spray on the airframe and gears. ‐ Reverse thrust is used for the deceleration phase. ‐ Maximum thrust is used for takeoff. Note:
The net flight path clears obstacles by 15 ft instead of 35 ft.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-CTA-30 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
RUNWAY CONTAMINATION - OPERATIONAL CONDITIONS
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-CTA-30 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
TAKEOFF PERFORMANCE TAKEOFF PERFORMANCE Ident.: PER-TOF-CTA-40-10-00013660.0003001 / 04 MAR 11 Applicable to: ALL
CAUTION
The method is based on the use of the RTOW charts established at optimum V2/VS and optimum V1/VR. In addition, when applying corrections for a wet runway, the RTOW charts should also have been established with V1 min (minimum V1 of the V1 range). The method should not be used with takeoff charts computed for other conditions. All tables have been established for TOGA (and Flexible Takeoff for wet runways). Do not use them for Derated thrust.
Correct the determined maximum takeoff weight on dry runway to take into account QNH and bleed effects, then apply the corrections given on the following pages. Note:
1. The results obtained with this method may be different from the influence given at the bottom of the RTOW chart. 2. On contaminated runway, in some cases, no MTOW can be determined with this method (box dashed below a given weight). A specific RTOW chart must then be computed. 3. The published corrections are valid for charts calculated with forward CG and basic CG.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A
PER-TOF-CTA-40-10 P 1/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-CTA-40-10 P 2/2 29 JUL 11
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
TAKEOFF FROM A WET RUNWAY
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-CTA-40-20 P 1/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
HOW TO PROCEED Ident.: PER-TOF-CTA-40-20-00012966.0004001 / 24 MAR 11 Applicable to: ALL
1. Determine the maximum takeoff weight or flexible temperature and associated speeds on dry runway. 2. Two sets of tables are given depending on the use of thrust reversers and the presence of clearway. Select the table to use as applicable to your case. The runway length in the table corresponds to the available takeoff run (TORA). 3. Apply the corrections shown in the table to the maximum takeoff weight or flexible temperature and associated speeds determined on dry runway. 4. Check that takeoff speeds are greater than the minimum values shown on the RTOW chart. If one or more speeds are lower than these minimum values, apply the following procedure : ‐ Actual TOW = maximum TOW • If V1 is lower than the minimum V1 (V1 limited by VMCG), take this last value as V1 and further decrease weight by 3 000 kg (6 600 lb ) per knot difference between them. Check that VR and V2 are higher than or equal to the minimum values. • If VR or/and V2 falls below the minimum values, takeoff is not possible. ‐ Actual TOW lower than maximum TOW • If V1 corresponding to actual TOW is lower than the minimum V1 (V1 limited by VMCG) : ▪ If maximum TOW has a V1 equal to or above minimum V1, retain minimum V1 as V1 and decrease the flexible temperature by 4 °C per knot difference between them. ▪ In the rare case when the V1 corresponding to maximum TOW falls below the minimum V1, decrease maximum TOW by 3 000 kg (6 600 lb ) per knot difference between them. Limit the actual TOW to the value found after this decrement. Take V1 equal to minimum V1 and decrease the flexible temperature by 4 °C per knot difference between this last value and the V1 corresponding to the actual TOW. Check that VR and V2 are higher than or equal to the minimum values. • If VR or V2 corresponding to actual TOW falls below the minimum values, and if VR and V2 corresponding to maximum TOW are above the minimum values, retain the minimum speed value for VR and V2. 5. Check that V2 is above the minimum V2 value due to VMU (Refer to PER-TOF-TOD-25-10 SPEEDS LIMITED BY VMC). 6. Check that the corrected flexible temperature is higher than OAT and Tref.
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
A→
PER-TOF-CTA-40-20 P 2/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
FLIGHT CREW OPERATING MANUAL
Note:
‐ Do not extrapolate below the shortest runway length provided in the table. ‐ If no minimum speed value is available, use the conservative values provided on Refer to PER-TOF-TOD-25-10 SPEEDS LIMITED BY VMC. NO THRUST REVERSERS OPERATIVE (NO CLEARWAY)
Ident.: PER-TOF-CTA-40-20-00012743.0048001 / 04 MAR 11 Applicable to: ALL
TAKEOFF CONFIGURATION RUNWAY LENGTH (m) (ft)
FLEX TO Temperature decrement (°C) MAX TO Weight decrement (1 000 kg) (1 000 lb) V1 decrement (kt) VR and V2 decrement (kt)
1+F
2
3
2 500 8 000
3 000 10 000
3 500 11 500 and above
2 000 6 500
2 500 8 000
8
5
3
8
6
2
2.6 5.8
2.0 4.5
1.3 2.9
2.5 5.6
2.2 4.9
15
14
14
16
2
1
1
2
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
← A to B
3 000 1 750 10 000 5 750 and above
2 000 6 500
2 500 8 000 and above
6
6
2
0.7 1.6
2.1 4.7
2.1 4.7
0.7 1.6
14
14
14
15
13
1
2
1
2
0
PER-TOF-CTA-40-20 P 3/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
FLIGHT CREW OPERATING MANUAL
ALL THRUST REVERSERS OPERATIVE (NO CLEARWAY) Ident.: PER-TOF-CTA-40-20-00012744.0084001 / 04 MAR 11 Applicable to: ALL
TAKEOFF CONFIGURATION RUNWAY LENGTH (m) (ft)
FLEX TO Temperature decrement (°C) MAX TO Weight decrement (1000 kg) (1000 lb) V1 decrement (kt) VR and V2 decrement (kt)
1+F
2
3
2500 8000
3000 10000
3500 11500 and above
2000 6500
2500 8000
3000 10000 and above
1750 5750
2000 6500
2500 8000 and above
3
2
0
3
1
0
2
1
1
1.0 2.3 9
0.6 1.4 9
0.0 0.0 9
0.8 1.8 10
0.3 0.7 8
0.0 0.0 9
0.6 1.4 10
0.2 0.5 9
0.1 0.3 8
0
0
0
0
0
0
0
0
0
NO THRUST REVERSERS OPERATIVE (WITH CLEARWAY) Ident.: PER-TOF-CTA-40-20-00012745.0044001 / 08 FEB 11 Applicable to: ALL
TAKEOFF CONFIGURATION RUNWAY LENGTH (m) (ft)
FLEX TO Temperature decrement (°C) MAX TO Weight decrement (1 000 kg) (1 000 lb) V1 decrement (kt) VR and V2 decrement (kt)
1+F
2
2 500 8 000
3 000 10 000
3 500 2 000 11 500 6 500 and above
15
9
9
5.4 12.0
4.1 9.1
14 4
3
2 500 8 000
3 000 10 000 and above
1 750 5 750
2 000 6 500
2 500 8 000 and above
14
11
4
15
12
5
3.8 8.4
4.6 10.2
4.2 9.3
1.6 3.6
4.5 10.0
4.5 10.0
2.2 4.9
15
15
14
14
15
13
13
14
3
6
4
4
6
3
4
5
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
C to D
PER-TOF-CTA-40-20 P 4/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
FLIGHT CREW OPERATING MANUAL
ALL THRUST REVERSERS OPERATIVE (WITH CLEARWAY) Ident.: PER-TOF-CTA-40-20-00012941.0044001 / 28 JAN 11 Applicable to: ALL
TAKEOFF CONFIGURATION RUNWAY LENGTH (m) (ft)
FLEX TO Temperature decrement (°C) MAX TO Weight decrement (1 000 kg) (1 000 lb) V1 decrement (kt) VR and V2 decrement (kt)
1+F 2 500 3 000 8 000 10 000
2 3 500 2 000 11 500 6 500 and above
2 500 8 000
3 3 000 1 750 10 000 5 750 and above
2 000 6 500
2 500 8 000 and above
11
5
2
10
8
3
11
9
3
3.9 8.6 9
2.3 5.1 10
0.9 2.0 12
3.3 7.3 9
3.1 6.9 9
1.0 2.3 10
3.3 7.3 8
3.3 7.3 9
1.3 2.5 9
3
2
3
3
3
4
2
2
4
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
E
PER-TOF-CTA-40-20 P 5/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
Intentionally left blank
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-CTA-40-20 P 6/6 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321 FLIGHT CREW OPERATING MANUAL
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
TAKEOFF FROM A CONTAMINATED RUNWAY
2T1 A318/A319/A320/A321 For A/C: 18-CMHE FCOM
PER-TOF-CTA-40-30 P 1/12 03 APR 12
PERFORMANCE TAKEOFF A318/A319/A320/A321
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
FLIGHT CREW OPERATING MANUAL
TAKEOFF FROM A 6.3 MM (1/4 INCH) WATER COVERED RUNWAY Ident.: PER-TOF-CTA-40-30-00001786.0373001 / 25 MAR 11 Applicable to: ALL
‐ Determine maximum takeoff weight on dry runway. ‐ Apply the following weight decrement versus takeoff configuration, runway length and clearway availability to determine a corrected weight. TAKEOFF CONFIGURATION
CONF 1 + F
CONF 2
CONF 3
RUNWAY LENGTH (m) (ft)
2 500 8 000
3 00 10 000
3 500 11 500
2 000 6 500
2 500 8 000
3 000 10 000 and above
1 750 5750
2 000 6 500
Δ Weight (1 000 kg) With clearway Without clearway
4 000 13 00 and above
2 500 8 000 and above
12.8 10.5
11.7 10.1
9.8 9.0
9.8 9.0
13.9 11.1
13.2 11.1
11.4 10.4
14.9 11.4
14.5 11.8
13.1 11.8
‐ Enter the following tables with the corrected weight to determine MTOW then determine takeoff speeds associated with actual TOW. CONF 1 + F CORRECTED WEIGHT (1 000 kg)
56
58
58 to 78
46.7
50
58
EQUAL TO CORRECTED WEIGHT
ACTUAL WEIGHT