Embraer Emb-135bj Aom Vol. 1 Aom
AIRPLANE OPERATIONS MANUAL VOLUME 1 EMPRESA BRASILEIRA DE AERONÁUTICA S.A. This manual is applicable to the EMB-135BJ
Views 71 Downloads 2 File size 7MB
Recommend stories
- Author / Uploaded
- cjtrybiec
Citation preview
AIRPLANE OPERATIONS MANUAL VOLUME 1
EMPRESA BRASILEIRA DE AERONÁUTICA S.A.
This manual is applicable to the EMB-135BJ airplanes all models equipped with AE3007A1E engines, operating under FAA certification. NOTE: THE EMB-135BJ MODEL DESIGNATION OF LEGACY.
HAS
THE
THIS PUBLICATION IS INCOMPLETE WITHOUT OPERATIONS MANUAL AOM–135/1542 VOLUME 2
COMMERCIAL
AIRPLANE
AOM–135/1542-07 NOVEMBER 30, 2001 REVISION 7 – MARCH 31, 2005 Copyright 2001 by EMBRAER - Empresa Brasileira de Aeronáutica S.A.. All rights reserved. This document shall not be copied or reproduced, whether in whole or in part, in any form or by any means without the express written authorization of Embraer. The information, technical data, designs and drawings disclosed in this document are property information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer.
TRANSMITTAL LETTER
Subject: REVISION 7 of the AOM–135/1542-07 Airplane Operations Manual Dear Madam or Sir, You are receiving REVISION 7 of the AOM. To help you to better understand this revision, we are presenting the main points in the “Highlights of Change” inside the manual. This revision incorporates all preceding temporary revisions. Therefore all yellow pages should be discarded from the manual. The revised pages supersede the current ones. Therefore, the affected pages must be replaced and the new pages inserted following the numbered sequence. The Section 1-03-36 code 01 is being deleted. Current pages must be removed from manual and discarded. The information must be replaced by Section 1-03-36 code 02.
In case of any question, please contact Embraer Flight Operations Engineering Department by E-mail: [email protected] or by phone: (+55 12) 3927 1706 THIS PAGE IS NOT PART OF THE MANUAL AND MUST NOT BE INCORPORATED IN YOUR AOM. PLEASE DISCARD IT AFTER READING.
CUSTOMER COMMENT FORM Airplane Operations Manual AOM–135/1542
Please use this Customer Comment Form to notify us of any discrepancies or problems you find in the Airplane Operations Manual. We would also welcome constructive suggestions on how we can further improve our documentation or service. Your feedback will be acknowledged, and we will advise you of the action we intend to take.
Sincerely, Embraer Operations Support
Please return this form to: Embraer - DSF/GSO/SEO - PC176 Av. Brigadeiro Faria Lima, 2170 CEP 12227-901 São José dos Campos - SP - BRASIL P.O. Box 8050 Phone: +55 12 3927-1706 Fax: +55 12 3927-2477 E-mail: [email protected]
Airplane Operations Manual AOM–135/1542 Section/Page/Code: Name: Position: Company: Fax Number: E-Mail:
Date of Page:
Revision:
Phone Number:
Comment/Suggestion:
Space reserved for Embraer Comment received:
CCF nº: Date Acknowledged:
Person in Charge: Action to be taken:
Proposed date for implementation:
Implemented:
AIRPLANE OPERATIONS MANUAL
HIGHLIGHTS OF CHANGE
HIGHLIGHTS OF CHANGE REVISION 7 – MARCH 31, 2005
• 1-00-10 code 01 Update Abbreviation and Acronyms table. • 1-00-35 code 01 Update Service Bulletin Table. • 1-01-00 code 02 Update Table of Contents. • 1-01-10 code 02 Update Operational Limitations. • 1-01-30 code 01 Update EGPWS limitations. • 1-01-38 code 02 Update APU Starter Limits. • 1-01-40 code 02 Update Automatic Takeoff Thrust Control • •
System (ATTCS) limitations. 1-01-48 code 01 Update Pneumatic, Air Conditioning Pressurization limitations. 1-01-52 code 01 Update Ozone Concentration tables.
and
• 1-01-56 code 02 Update Autopilot limitations. • 1-02-09 code 01 Editorial correction. • 1-02-17 code 01 Editorial correction. • 1-02-29 code 01 Update After Start normal procedure. • 1-02-73 code 01 Editorial correction. • 1-02-77 code 01 Editorial correction. • 1-02-79 code 01 Update •
Environmental Supplementary Procedures. 1-03-06 code 01 Update APU Fire emergency procedure.
• 1-03-08 code 01 Update Ditching, Emergency Evacuation and •
Forced Landing procedures. 1-03-12 code 02 Update ATTCS No Margin and Engine ATTCS Failure emergency procedures.
REVISION 7
Page
Code
1
07
HIGHLIGHTS OF CHANGE
AIRPLANE OPERATIONS MANUAL
• 1-03-26 code 02 Update
Loss of Pressurization Indication abnormal procedure. 1-03-30 code 01 Update Baggage/Access Door Open abnormal procedure. 1-03-34 code 01 Update Abnormal Engine Start, Engine Abnormal Vibration, Engine Control Failure and Engine Dry Motoring abnormal procedures.
• •
• 1-03-36 code 02 Delete Section 1-03-36 code 01. Current pages
must be removed from manual and discarded. The information must be replaced by Section 1-03-36 code 02.
• 1-03-38 code 01 Update Flap System Failure and Rudder System
Inoperative abnormal procedures. 1-03-42 code 01 Update Partial or Gear Up Landing abnormal procedure. Update and merge Steering System Inoperative and Uncommanded Swerving abnormal procedures into On Ground on a Steering System Inoperative or Uncommanded Swerving On Ground abnormal procedure.
•
• 1-03-46 code 01 Update
Yaw Damper Failure abnormal procedure. 1-04-15 code 02 Include Climb Gradient tables for All Engines Operating. 1-05-10 code 08 Include new Autopilot Climb Schedule.
• •
• 1-05-15 code 08 Update Cruise Tables due to the new altitude ceiling of 41000 ft. 1-05-20 code 08 Update Descent Flight Planning.
•
• 1-05-25 code 08 Update Holding Tables. • 1-06-20 code 02 Update
Pitch Trim Setting table Miscellaneous Fluids table. 1-10-05 code 01 Update Emergency Equipment checklist.
•
and
• 1-11-00 code 01 Update Table of Contents. • 1-11-10 code 01 Include new section of Provisions For Extented Over Water Operations. 1-12-20 code 01 Update Cold Weather Operation information.
•
Page
Code
2
07
REVISION 7
HIGHLIGHTS OF CHANGE
AIRPLANE OPERATIONS MANUAL
• 1-12-50 code 01 Update Water/Toilet Servicing information. • 2-01-10 code 01 Update Overhead Panel information. • 2-02-35 code 01 Include new Dual Pocket Door description. • 2-04-00 code 01 Update Table of Contents. • 2-04-15 code 01 Update Aural Warnings table. • 2-04-30 code 01 Update EGPWS information and include Steep •
Approach Operation information. 2-04-40 code 01 Update TCAS information.
• 2-05-00 code 01 Update Table of Contents. • 2-05-05 code 01 Update Electrical System information. Include information regarding airplanes electrical power supply.
without
AC
• 2-05-10 code 01 Editorial correction. • 2-05-15 code 01 Include information regarding airplanes without • •
AC electrical power supply. 2-05-20 code 01 Update Circuit Breaker Distribution information. 2-07-00 code 01 Update Table of Contents.
Panel
and
Load
• 2-07-10 code 01 Update baggage compartment information. • 2-07-15 code 01 Editorial correction. • 2-07-20 code 01 Update Baggage Compartment Fire Protection •
System information. 2-08-05 code 01 Update wing tank fuel transfer description.
• 2-10-60 code 01 Update Engine Indication on EICAS information. • 2-12-10 code 01 Update Brake System information. • 2-12-15 code 01 Include SB 145LEG-32-0020 reference. • 2-14-00 code 01 Update Table of Contents.
REVISION 7
Page
Code
3
07
HIGHLIGHTS OF CHANGE
AIRPLANE OPERATIONS MANUAL
• 2-14-10 code 01 Update the Integrated Pneumatic System
Schematic illustration. 2-14-15 code 01 Update the Pressurization System description due to the inclusion of the new altitude ceiling for the EMB-135BJ.
•
• 2-16-00 code 01 Update Table of Contents. • 2-16-10 code 01 Update
Flight Crew Oxygen information, highlighting the two different types of flight crew oxygen masks.
• 2-16-15 code 01 Update Passenger Oxygen information due to
the inclusion of the EICAS version 20.6. 2-16-20 code 01 Update Protective Breathing Equipment information. 2-16-25 code 01 Update information.
• •
• 2-17-10 code 01 Update Air Data System Description. • 2-17-20 code 01 Update Integrated Standby Instrument System description. 2-18-15 code 01 Update Digital Audio Panel information.
•
• 2-18-35 code 01 Update Flight Management System Description. • 2-19-00 code 01 Update Table of Contents. • 2-19-10 code 01 Update Flight Level Change Mode due to the inclusion of the EICAS version 20.6. Update the Go Around Mode information.
Page
Code
4
07
REVISION 7
AIRPLANE OPERATIONS MANUAL
LIST OF EFFECTIVE PAGES
LIST OF EFFECTIVE PAGES (VOLUME 1) ORIGINAL ..................0.................. NOV 30, 2001 REVISION ..................1...................JUN 20, 2002 REVISION ..................2...................SEP 30, 2002 REVISION ..................3................... JAN 17, 2003 REVISION ..................4.................. OCT 24, 2003 REVISION ..................5................... JUL 20, 2004 REVISION ..................6.................. AUG 27, 2004 REVISION ..................7..................MAR 31, 2005
NOTE: The references to the deleted pages from the previous revisions (revision 6 and earlier) were removed from the LEP.
REVISION 7
1-LEP
Page
Code
1
07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
1-LEP
Page
Code
2
07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Block 1-LEP
Page Code title
07
1-LEP
1
07
1-LEP
2
07
1-LEP
3
07
1-LEP
4
07
1-LEP
5
07
1-LEP
6
07
1-LEP
7
07
1-LEP
8
07
1-LEP
9
07
1-LEP
10
07
1-LEP
11
07
1-LEP
12
07
1-LEP
13
07
1-LEP
14
07
1-LEP
15
07
1-LEP
16
07
1-LEP
17
07
1-LEP
18
07
1-LEP
19
07
1-LEP
20
07
1-LEP
21
07
1-LEP
22
07
1-LEP
23
07
1-LEP
24
07
1-LEP
25
07
1-LEP
26
07
1-LEP
27
07
1-LEP
28
07
1-LEP
29
07
1-LEP
30
07
1-LEP
31
07
1-LEP
32
07
1-LEP
33
07
Change
* * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * *
REVISION 7
LIST OF EFFECTIVE PAGES
Applicability (model, engine, certification, other) AOM 135-1542-07
REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7
* Asterisk indicates pages revised, added or deleted by the current revision.
REVISION 7
1-LEP
Page
Code
3
07
LIST OF EFFECTIVE PAGES
Page Block 1-LEP
AIRPLANE OPERATIONS MANUAL
Page Code 34
07
1-LEP
35
07
1-LEP
36
07
1-LEP
37
07
1-LEP
38
07
1-LEP
39
07
1-LEP
40
07
1-LEP
41
07
1-LEP
42
07
Change
* * * * * * * * *
REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7
1-TOC
1
01
JUN 20, 2002
1-TOC
2
01
JUN 20, 2002
1-00-00
1
01
REVISION 6
1-00-00
2
01
ORIGINAL
1-00-00
3
01
REVISION 1
1-00-00
4
01
REVISION 6
1-00-00
5
01
NOV 30, 2001
1-00-00
6
01
JUN 20, 2002
1-00-00
7
01
NOV 30, 2001
1-00-00
8
01
NOV 30, 2001
1-00-10
1
01
ORIGINAL
1-00-10
2
01
REVISION 7
1-00-10
3
01
REVISION 5
1-00-10
4
01
REVISION 5
1-00-10
5
01
REVISION 5
1-00-10
6
01
REVISION 5
1-00-10
7
01
REVISION 5
1-00-10
8
01
REVISION 5
1-00-10
9
01
REVISION 5
1-00-10
10
01
REVISION 5
1-00-10
11
01
REVISION 5
1-00-10
12
01
REVISION 5
1-00-10
13
01
REVISION 5
1-00-10
14
01
REVISION 5
1-00-10
15
01
REVISION 5
*
Applicability (model, engine, certification, other)
ALL
ALL
ALL
* Asterisk indicates pages revised, added or deleted by the current revision.
1-LEP
Page
Code
4
07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-00-10 16 01
Change
LIST OF EFFECTIVE PAGES
Applicability (model, engine, certification, other)
ORIGINAL
1-00-10
17
01
NOV 30, 2001
1-00-10
18
01
NOV 30, 2001
1-00-20
1
01
JAN 17, 2003
1-00-20
2
01
NOV 30, 2001
1-00-35
1
01
1-00-35
2
01
1-01-00
1
02
1-01-00
2
02
REVISION 4
1-01-01
1
01
SEP 30, 2002
1-01-01
2
01
NOV 30, 2001
1-01-05
1
02
REVISION 4
1-01-05
2
02
REVISION 4
1-01-05
3
02
REVISION 4
1-01-05
4
02
REVISION 3
1-01-10
1
02
1-01-10
2
02
1-01-10
2A
02
1-01-10
2B
02
1-01-10
3
02
1-01-10
4
02
REVISION 5
1-01-10
5
02
REVISION 4
1-01-10
6
02
REVISION 4
1-01-30
1
01
1-01-30
2
01
REVISION 5
1-01-32
1
01
NOV 30, 2001
1-01-32
2
01
NOV 30, 2001
1-01-36
1
02
REVISION 6
1-01-36
2
02
REVISION 4
1-01-36
3
02
REVISION 6
1-01-36
4
02
REVISION 4
1-01-38
1
02
1-01-38
2
02
*
REVISION 7
ALL
ALL
REVISION 6
*
* * * * *
*
*
REVISION 7
REVISION 7
FAA
ALL
lb
FAA
REVISION 7 REVISION 7 REVISION 7 REVISION 7
REVISION 7
REVISION 7
ALL
ALL
FAA
FAA
REVISION 5
* Asterisk indicates pages revised, added or deleted by the current revision.
REVISION 7
1-LEP
Page
Code
5
07
LIST OF EFFECTIVE PAGES
Page Page Code Block 1-01-40 1 02 1-01-40
2
02
1-01-40
3
02
1-01-40
4
02
AIRPLANE OPERATIONS MANUAL Change REVISION 7
* * *
Applicability (model, engine, certification, other) A1E
REVISION 7 REVISION 7 REVISION 3
1-01-48
1
01
1-01-48
2
01
REVISION 7 ORIGINAL
*
1-01-50
1
02
REVISION 6
1-01-50
2
02
REVISION 6
1-01-52
1
01
1-01-52
2
01
1-01-52
3
01
1-01-52
4
01
1-01-52
5
01
1-01-52
6
01
1-01-52
7
01
1-01-52
8
01
1-01-52
9
01
1-01-52
10
01
1-01-56
1
02
REVISION 5 REVISION 5
* * * * * * * * * *
REVISION 7
ALL
FAA/JAA
CTA/FAA
REVISION 7 REVISION 7 REVISION 7 new REVISION 7 new REVISION 7 new REVISION 7 new REVISION 7 new REVISION 7 new REVISION 7
1-01-56
2
02
1-01-56
3
02
1-01-56
4
02
REVISION 3
1-01-60
1
02
REVISION 6
1-01-60
2
02
REVISION 5
1-01-65
1
01
REVISION 3
1-01-65
2
01
REVISION 5
1-02-00
1
02
REVISION 6
1-02-00
2
02
REVISION 5
1-02-00
3
02
REVISION 4
1-02-00
4
02
REVISION 4
1-02-00
5
02
REVISION 4
1-02-00
6
02
REVISION 4
1-02-01
1
01
JUN 20, 2002
*
FAA
REVISION 7
FAA
CTA/FAA
FAA/JAA
ALL
* Asterisk indicates pages revised, added or deleted by the current revision.
1-LEP
Page
Code
6
07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-02-01 2 01
Change JAN 17, 2003
1-02-01
3
01
JAN 17, 2003
1-02-01
4
01
JAN 17, 2003
1-02-05
1
01
REVISION 3
1-02-05
2
01
REVISION 5
1-02-05
3
01
REVISION 5
1-02-05
4
01
REVISION 5
1-02-09
1
01
JAN 17, 2003
1-02-09
2
01
JUN 20, 2002
1-02-09
3
01
1-02-09
4
01
REVISION 4
*
Applicability (model, engine, certification, other)
ALL
ALL
REVISION 7
1-02-13
1
01
REVISION 5
1-02-13
2
01
REVISION 5
1-02-13
3
01
JUN 20, 2002
1-02-13
4
01
JAN 17, 2003
1-02-13
5
01
REVISION 3
1-02-13
6
01
REVISION 4
1-02-13
7
01
JAN 17, 2003
1-02-13
8
01
JAN 17, 2003
1-02-17
1
01
REVISION 3
1-02-17
2
01
REVISION 7
1-02-17
3
01
1-02-17
4
01
1-02-17
5
01
JUN 20, 2002
1-02-17
6
01
JAN 17, 2003
1-02-17
7
01
JAN 17, 2003
1-02-17
8
01
JAN 17, 2003
1-02-17
9
01
REVISION 5
1-02-17
10
01
REVISION 3
1-02-21
1
01
JAN 17, 2003
* * *
LIST OF EFFECTIVE PAGES
ALL
ALL
REVISION 7 REVISION 7
1-02-21
2
01
JAN 17, 2003
1-02-21
3
01
REVISION 3
1-02-21
4
01
REVISION 6
1-02-25
1
01
REVISION 5
ALL
ALL
* Asterisk indicates pages revised, added or deleted by the current revision.
REVISION 7
1-LEP
Page
Code
7
07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
Page Page Code Block 1-02-25 2 01
Change REVISION 6
1-02-25
3
01
REVISION 6
1-02-25
4
01
REVISION 6
1-02-27
1
01
JAN 17, 2003
1-02-27
2
01
JAN 17, 2003
1-02-29
1
01
*
REVISION 7
1-02-29
2
01
REVISION 2
1-02-33
1
01
JAN 17, 2003
1-02-33
2
01
JAN 17, 2003
1-02-33
3
01
JAN 17, 2003
1-02-33
4
01
NOV 30, 2001
1-02-37
1
01
JAN 17, 2003
1-02-37
2
01
NOV 30, 2001
1-02-41
1
01
NOV 30, 2001
1-02-41
2
01
JAN 17, 2003
1-02-45
1
01
JAN 17, 2003
1-02-45
2
01
JAN 17, 2003
1-02-47
1
01
NOV 30, 2001
1-02-47
2
01
NOV 30, 2001
1-02-48
1
01
REVISION 6
1-02-48
2
01
REVISION 6
1-02-49
1
01
REVISION 5
1-02-49
2
01
REVISION 5
1-02-49
3
01
REVISION 4
1-02-49
4
01
ORIGINAL
1-02-53
1
01
JAN 17, 2003
1-02-53
2
01
NOV 30, 2001
1-02-57
1
01
REVISION 3
1-02-57
2
01
REVISION 4
1-02-61
1
01
JAN 17, 2003
1-02-61
2
01
NOV 30, 2001
1-02-65
1
01
NOV 30, 2001
1-02-65
2
01
NOV 30, 2001
Applicability (model, engine, certification, other)
ALL
ALL
ALL
ALL
ALL
ALL
ALL
ALL
ALL
ALL
ALL
ALL
ALL
* Asterisk indicates pages revised, added or deleted by the current revision.
1-LEP
Page
Code
8
07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-02-69 1 01
Change JUN 20, 2002
1-02-69
2
01
JAN 17, 2003
1-02-73
1
01
REVISION 3
1-02-73
2
01
REVISION 7
1-02-77
1
01
1-02-77
2
01
* * *
REVISION 7
Applicability (model, engine, certification, other) ALL
ALL
ALL
REVISION 7
1-02-79
1
01
NOV 30, 2001
1-02-79
2
01
NOV 30, 2001
1-02-79
3
01
1-02-79
4
01
1-02-79
5
01
1-02-79
6
01
1-02-79
7
01
1-02-79
8
01
REVISION 6
1-02-79
9
01
REVISION 6
1-02-79
10
01
1-02-79
11
01
1-02-79
12
01
1-02-79
13
01
1-02-79
14
01
1-02-79
15
01
1-02-79
16
01
1-02-79
16A
01
1-02-79
16B
01
1-02-79
17
1-02-79
* *
LIST OF EFFECTIVE PAGES
ALL
REVISION 7 REVISION 7 REVISION 4
* *
* * *
REVISION 7 REVISION 7
REVISION 7 REVISION 7 REVISION 7 ORIGINAL
*
REVISION 7 REVISION 6 REVISION 7
* * *
new REVISION 7
01
ORIGINAL
18
01
*
REVISION 7
1-02-79
19
01
ORIGINAL
1-02-79
20
01
*
REVISION 7
1-02-79
21
01
ORIGINAL
1-02-79
22
01
1-02-79
23
01
1-02-79
24
01
* * *
REVISION 7
1-02-79
25
01
JUN 20, 2002
1-02-79
26
01
JUN 20, 2002
new REVISION 7
REVISION 7 REVISION 7
* Asterisk indicates pages revised, added or deleted by the current revision.
REVISION 7
1-LEP
Page
Code
9
07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
Page Page Code Block 1-02-79 27 01
Change JUN 20, 2002
1-02-79
28
01
JUN 20, 2002
1-02-80
1
01
NOV 30, 2001
1-02-80
2
01
JUN 20, 2002
1-02-80
3
01
REVISION 6
1-02-80
4
01
ORIGINAL
1-02-80
5
01
NOV 30, 2001
1-02-80
6
01
NOV 30, 2001
1-02-81
1
01
ORIGINAL
1-02-81
2
01
REVISION 4
1-02-81
3
01
NOV 30, 2001
1-02-81
4
01
NOV 30, 2001
1-02-81
5
01
NOV 30, 2001
1-02-81
6
01
NOV 30, 2001
1-02-83
1
01
SEP 30, 2002
1-02-83
2
01
SEP 30, 2002
1-02-86
1
01
REVISION 5
1-02-86
2
01
REVISION 5
1-02-86
3
01
REVISION 5
1-02-86
4
01
REVISION 5
1-02-95
1
01
NOV 30, 2001
1-02-95
2
01
NOV 30, 2001
1-02-95
3
01
NOV 30, 2001
1-02-95
4
01
NOV 30, 2001
1-02-95
5
01
NOV 30, 2001
1-02-95
6
01
SEP 30, 2002
1-03-00
1
01
REVISION 6
1-03-00
2
01
REVISION 3
1-03-00
3
01
REVISION 4
1-03-00
4
01
REVISION 3
1-03-02
1
01
JAN 17, 2003
1-03-02
2
01
NOV 30, 2001
1-03-02
3
01
ORIGINAL
1-03-02
4
01
REVISION 6
Applicability (model, engine, certification, other)
ALL
ALL
CTA/FAA
ALL
CTA/FAA
CTA/FAA
CTA/FAA
* Asterisk indicates pages revised, added or deleted by the current revision. Page
1-LEP
Code
10 07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-03-04 1 02
Change JAN 17, 2003
1-03-04
2
02
JAN 17, 2003
1-03-06
1
01
1-03-06
2
01
*
REVISION 7
LIST OF EFFECTIVE PAGES
Applicability (model, engine, certification, other) FAA
CTA/FAA
ORIGINAL
1-03-08
1
01
1-03-08
2
01
1-03-08
3
01
ORIGINAL
1-03-08
4
01
REVISION 7
1-03-08
5
01
JAN 17, 2003
1-03-08
6
01
NOV 30, 2001
* * *
REVISION 7
1-03-10
1
02
JAN 17, 2003
1-03-10
2
02
JAN 17, 2003
1-03-12
1
02
1-03-12
2
02
* *
CTA/FAA
REVISION 7
REVISION 7
FAA
FAA
REVISION 7
1-03-12
3
02
JAN 17, 2003
1-03-12
4
02
JAN 17, 2003
1-03-12
5
02
JAN 17, 2003
1-03-12
6
02
JAN 17, 2003
1-03-14
1
01
REVISION 6
1-03-14
2
01
REVISION 6
1-03-14
3
01
JUN 20, 2002
1-03-14
4
01
JUN 20, 2002
1-03-14
5
01
REVISION 1
1-03-14
6
01
REVISION 4
1-03-14
7
01
JUN 20, 2002
1-03-14
8
01
JAN 17, 2003
1-03-16
1
01
JAN 17, 2003
1-03-16
2
01
NOV 30, 2001
1-03-18
1
01
JAN 17, 2003
1-03-18
2
01
NOV 30, 2001
1-03-20
1
01
REVISION 5
1-03-20
2
01
ORIGINAL
1-03-22
1
01
JAN 17, 2003
CTA/FAA
CTA/FAA
CTA/FAA
CTA/FAA
CTA/FAA
* Asterisk indicates pages revised, added or deleted by the current revision. Page
REVISION 7
1-LEP
Code
11 07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
Page Page Code Block 1-03-22 2 01
Change NOV 30, 2001
1-03-24
1
01
JUN 20, 2002
1-03-24
2
01
JAN 17, 2003
1-03-26
1
02
REVISION 3
1-03-26
2
02
REVISION 5
1-03-26
3
02
REVISION 5
1-03-26
4
02
REVISION 3
1-03-26
5
02
JAN 17, 2003
1-03-26
6
02
JAN 17, 2003
1-03-26
7
02
REVISION 3
1-03-26
8
02
1-03-26
9
02
1-03-26
10
02
* * *
Applicability (model, engine, certification, other) CTA/FAA
FAA
REVISION 7 new REVISION 7 new REVISION 7
1-03-28
1
01
REVISION 5
1-03-28
2
01
ORIGINAL
1-03-30
1
01
1-03-30
2
01
1-03-30
3
01
JAN 17, 2003
1-03-30
4
01
NOV 30, 2001
1-03-30
5
01
JUN 20, 2002
1-03-30
6
01
NOV 30, 2001
1-03-32
1
02
JAN 17, 2003
1-03-32
2
02
JAN 17, 2003
1-03-32
3
02
JAN 17, 2003
1-03-32
4
02
JAN 17, 2003
*
REVISION 7
CTA/FAA
CTA/FAA
REVISION 3
1-03-34
1
01
1-03-34
2
01
1-03-34
2A
01
1-03-34
2B
01
REVISION 6
1-03-34
3
01
REVISION 6
1-03-34
4
01
ORIGINAL
1-03-34
5
01
REVISION 7
1-03-34
6
01
1-03-34
6A
01
*
REVISION 7
FAA
CTA/FAA
REVISION 5
*
* * *
REVISION 7
REVISION 7 REVISION 7
* Asterisk indicates pages revised, added or deleted by the current revision. Page
1-LEP
Code
12 07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-03-34 6B 01
Change REVISION 5
1-03-34
7
01
REVISION 5
1-03-34
8
01
REVISION 3
1-03-34
9
01
REVISION 4
1-03-34
10
01
REVISION 6
1-03-34
11
01
JAN 17, 2003
1-03-34
12
01
NOV 30, 2001
1-03-36
1
01
1-03-36
2
01
* * * *
del
REVISION 7
del
REVISION 7
1-03-36
1
02
1-03-36
2
02
1-03-38
1
01
REVISION 1
1-03-38
2
01
REVISION 7
1-03-38
3
01
1-03-38
4
01
1-03-38
5
01
1-03-38
6
01
*
new REVISION 7
LIST OF EFFECTIVE PAGES
Applicability (model, engine, certification, other)
CTA/FAA
FAA
new REVISION 7 CTA/FAA
REVISION 5
* *
REVISION 7 REVISION 7 REVISION 5
1-03-40
1
01
JAN 17, 2003
1-03-40
2
01
JAN 17, 2003
1-03-40
3
01
JAN 17, 2003
1-03-40
4
01
JUN 20, 2002
1-03-40
5
01
JAN 17, 2003
1-03-40
6
01
JAN 17, 2003
1-03-40
7
01
JAN 17, 2003
1-03-40
8
01
JAN 17, 2003
1-03-42
1
01
ORIGINAL
1-03-42
2
01
REVISION 6
1-03-42
3
01
REVISION 4
1-03-42
4
01
REVISION 1
1-03-42
5
01
JAN 17, 2003
1-03-42
6
01
JUN 20, 2002
1-03-42
7
01
REVISION 6
1-03-42
8
01
REVISION 6
1-03-42
9
01
REVISION 6
CTA/FAA
CTA/FAA
* Asterisk indicates pages revised, added or deleted by the current revision. Page
REVISION 7
1-LEP
Code
13 07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
Page Page Code Block 1-03-42 10 01
Change REVISION 6
1-03-42
11
01
REVISION 1
1-03-42
12
01
1-03-42
13
01
1-03-42
14
01
ORIGINAL
1-03-44
1
01
REVISION 4
1-03-44
2
01
REVISION 4
1-03-44
3
01
REVISION 4
1-03-44
4
01
REVISION 3
1-03-44
5
01
NOV 30, 2001
1-03-44
6
01
JUN 20, 2002
1-03-44
7
01
JUN 20, 2002
1-03-44
8
01
JUN 20, 2002
1-03-44
9
01
JUN 20, 2002
1-03-44
10
01
NOV 30, 2001
1-03-46
1
01
JAN 17, 2003
1-03-46
2
01
JAN 17, 2003
1-03-46
3
01
JAN 17, 2003
1-03-46
4
01
JUN 20, 2002
1-03-46
5
01
REVISION 6
1-03-46
6
01
REVISION 1
1-03-46
7
01
JUN 20, 2002
1-03-46
8
01
NOV 30, 2001
1-03-46
9
01
NOV 30, 2001
* *
REVISION 7 REVISION 7
1-03-46
10
01
NOV 30, 2001
1-03-46
11
01
NOV 30, 2001
1-03-46
12
01
NOV 30, 2001
1-03-46
13
01
1-03-46
14
01
ORIGINAL
1-03-48
1
02
JAN 17, 2003
1-03-48
2
02
JAN 17, 2003
1-03-48
3
02
JAN 17, 2003
1-03-48
4
02
JAN 17, 2003
1-03-49
1
01
SEP 30, 2002
*
Applicability (model, engine, certification, other)
CTA/FAA
CTA/FAA
REVISION 7
FAA
CTA/FAA
* Asterisk indicates pages revised, added or deleted by the current revision. Page
1-LEP
Code
14 07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-03-49 2 01
Change SEP 30, 2002
1-03-49
3
01
SEP 30, 2002
1-03-49
4
01
SEP 30, 2002
1-03-60
1
01
REVISION 4
1-03-60
2
01
REVISION 4
1-03-62
1
01
REVISION 4
1-03-62
2
01
REVISION 4
1-03-62
3
01
REVISION 4
1-03-62
4
01
REVISION 4
1-04-00
1
04
REVISION 6
1-04-00
2
04
REVISION 6
1-04-00
3
04
JAN 17, 2003
1-04-00
4
04
JAN 17, 2003
1-04-05
1
01
NOV 30, 2001
1-04-05
2
01
NOV 30, 2001
1-04-05
3
01
NOV 30, 2001
1-04-05
4
01
NOV 30, 2001
1-04-05
5
01
REVISION 4
1-04-05
6
01
ORIGINAL
1-04-10
1
02
REVISION 4
1-04-10
2
02
REVISION 3
1-04-10
3
02
JAN 17, 2003
1-04-10
4
02
JAN 17, 2003
1-04-10
5
02
JAN 17, 2003
1-04-10
6
02
JAN 17, 2003
1-04-10
7
02
JAN 17, 2003
1-04-10
8
02
JAN 17, 2003
1-04-10
9
02
JAN 17, 2003
1-04-10
10
02
JAN 17, 2003
1-04-10
11
02
JAN 17, 2003
1-04-10
12
02
JAN 17, 2003
1-04-10
13
02
JAN 17, 2003
1-04-10
14
02
JAN 17, 2003
1-04-10
15
02
JAN 17, 2003
LIST OF EFFECTIVE PAGES
Applicability (model, engine, certification, other)
CTA/FAA
CTA/FAA
A1E
ALL
A1E
* Asterisk indicates pages revised, added or deleted by the current revision. Page
REVISION 7
1-LEP
Code
15 07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
Page Page Code Block 1-04-10 16 02
Change JAN 17, 2003
1-04-10
17
02
JAN 17, 2003
1-04-10
18
02
JAN 17, 2003
1-04-10
19
02
JAN 17, 2003
1-04-10
20
02
JAN 17, 2003
1-04-10
21
02
JAN 17, 2003
1-04-10
22
02
JAN 17, 2003
1-04-15
1
02
JAN 17, 2003
1-04-15
2
02
JAN 17, 2003
1-04-15
3
02
JAN 17, 2003
1-04-15
4
02
JAN 17, 2003
1-04-15
5
02
JAN 17, 2003
1-04-15
6
02
JAN 17, 2003
1-04-15
7
02
JAN 17, 2003
1-04-15
8
02
JAN 17, 2003
1-04-15
9
02
JAN 17, 2003
1-04-15
10
02
JAN 17, 2003
1-04-15
11
02
JAN 17, 2003
1-04-15
12
02
JAN 17, 2003
1-04-15
13
02
JAN 17, 2003
1-04-15
14
02
JAN 17, 2003
1-04-15
15
02
JAN 17, 2003
1-04-15
16
02
JAN 17, 2003
1-04-15
17
02
JAN 17, 2003
1-04-15
18
02
JAN 17, 2003
1-04-15
19
02
JAN 17, 2003
1-04-15
20
02
JAN 17, 2003
1-04-15
21
02
JAN 17, 2003
1-04-15
22
02
JAN 17, 2003
1-04-15
23
02
JAN 17, 2003
1-04-15
24
02
JAN 17, 2003
1-04-15
25
02
JAN 17, 2003
1-04-15
26
02
JAN 17, 2003
1-04-15
27
02
JAN 17, 2003
Applicability (model, engine, certification, other)
A1E FAA
* Asterisk indicates pages revised, added or deleted by the current revision. Page
1-LEP
Code
16 07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-04-15 28 02
Change JAN 17, 2003
1-04-15
29
02
JAN 17, 2003
1-04-15
30
02
JAN 17, 2003
1-04-15
31
02
JAN 17, 2003
1-04-15
32
02
JAN 17, 2003
1-04-15
33
02
JAN 17, 2003
1-04-15
34
02
JAN 17, 2003
1-04-15
35
02
JAN 17, 2003
1-04-15
36
02
JAN 17, 2003
1-04-15
37
02
JAN 17, 2003
1-04-15
38
02
JAN 17, 2003
1-04-15
39
02
JAN 17, 2003
1-04-15
40
02
JAN 17, 2003
1-04-15
41
02
JAN 17, 2003
1-04-15
42
02
JAN 17, 2003
1-04-15
43
02
JAN 17, 2003
1-04-15
44
02
JAN 17, 2003
1-04-15
45
02
JAN 17, 2003
1-04-15
46
02
JAN 17, 2003
1-04-15
47
02
JAN 17, 2003
1-04-15
48
02
JAN 17, 2003
1-04-15
49
02
JAN 17, 2003
1-04-15
50
02
JAN 17, 2003
1-04-15
51
02
JAN 17, 2003
1-04-15
52
02
JAN 17, 2003
1-04-15
53
02
JAN 17, 2003
1-04-15
54
02
JAN 17, 2003
1-04-15
55
02
JAN 17, 2003
1-04-15
56
02
JAN 17, 2003
1-04-15
57
02
JAN 17, 2003
1-04-15
58
02
JAN 17, 2003
1-04-15
59
02
JAN 17, 2003
1-04-15
60
02
JAN 17, 2003
1-04-15
61
02
JAN 17, 2003
LIST OF EFFECTIVE PAGES
Applicability (model, engine, certification, other)
* Asterisk indicates pages revised, added or deleted by the current revision. Page
REVISION 7
1-LEP
Code
17 07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
Page Page Code Block 1-04-15 62 02
Change JAN 17, 2003
1-04-15
63
02
JAN 17, 2003
1-04-15
64
02
JAN 17, 2003
1-04-15
65
02
JAN 17, 2003
1-04-15
66
02
JAN 17, 2003
1-04-15
67
02
JAN 17, 2003
1-04-15
68
02
JAN 17, 2003
1-04-15
69
02
JAN 17, 2003
1-04-15
70
02
JAN 17, 2003
1-04-15
71
02
JAN 17, 2003
1-04-15
72
02
JAN 17, 2003
1-04-15
73
02
JAN 17, 2003
1-04-15
74
02
JAN 17, 2003
1-04-15
75
02
JAN 17, 2003
1-04-15
76
02
JAN 17, 2003
1-04-15
77
02
JAN 17, 2003
1-04-15
78
02
JAN 17, 2003
1-04-15
79
02
JAN 17, 2003
1-04-15
80
02
JAN 17, 2003
1-04-15
81
02
JAN 17, 2003
1-04-15
82
02
JAN 17, 2003
1-04-15
83
02
JAN 17, 2003
1-04-15
84
02
JAN 17, 2003
1-04-15
85
02
JAN 17, 2003
1-04-15
86
02
JAN 17, 2003
1-04-15
87
02
JAN 17, 2003
1-04-15
88
02
JAN 17, 2003
1-04-15
89
02
JAN 17, 2003
1-04-15
90
02
JAN 17, 2003
1-04-15
91
02
JAN 17, 2003
1-04-15
92
02
JAN 17, 2003
1-04-15
93
02
JAN 17, 2003
1-04-15
94
02
JAN 17, 2003
1-04-15
95
02
JAN 17, 2003
Applicability (model, engine, certification, other)
* Asterisk indicates pages revised, added or deleted by the current revision. Page
1-LEP
Code
18 07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-04-15 96 02
JAN 17, 2003
1-04-15
97
02
JAN 17, 2003
1-04-15
98
02
JAN 17, 2003
1-04-15
99
02
JAN 17, 2003
1-04-15
100
02
JAN 17, 2003
1-04-15
101
02
JAN 17, 2003
1-04-15
102
02
JAN 17, 2003
1-04-15
103
02
JAN 17, 2003
1-04-15
104
02
JAN 17, 2003
1-04-15
105
02
REVISION 3
1-04-15
106
02
REVISION 4
1-04-15
107
02
JAN 17, 2003
1-04-15
108
02
JAN 17, 2003
1-04-15
109
02
JAN 17, 2003
1-04-15
110
02
JAN 17, 2003
1-04-15
111
02
new REVISION 7
1-04-15
112
02
1-04-15
113
02
1-04-15
114
02
1-04-15
115
02
1-04-15
116
02
1-04-15
117
02
1-04-15
118
02
Change
* * * * * * * * * *
LIST OF EFFECTIVE PAGES
Applicability (model, engine, certification, other)
new REVISION 7 new REVISION 7 new REVISION 7 new REVISION 7 new REVISION 7 new REVISION 7 new REVISION 7
1-04-15
119
02
1-04-15
120
02
new REVISION 7
1-04-20
1
02
JAN 17, 2003
1-04-20
2
02
JAN 17, 2003
1-04-20
3
02
JAN 17, 2003
1-04-20
4
02
JAN 17, 2003
1-04-20
5
02
JAN 17, 2003
1-04-20
6
02
JAN 17, 2003
1-04-20
7
02
JAN 17, 2003
1-04-20
8
02
JAN 17, 2003
1-04-20
9
02
JAN 17, 2003
new REVISION 7 lb
* Asterisk indicates pages revised, added or deleted by the current revision. Page
REVISION 7
1-LEP
Code
19 07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
Page Page Code Block 1-04-20 10 02
Change JAN 17, 2003
1-04-20
11
02
JAN 17, 2003
1-04-20
12
02
JAN 17, 2003
1-04-20
13
02
JAN 17, 2003
1-04-20
14
02
JAN 17, 2003
1-04-20
15
02
JAN 17, 2003
1-04-20
16
02
JAN 17, 2003
1-04-25
1
02
JAN 17, 2003
1-04-25
2
02
JAN 17, 2003
1-04-25
3
02
REVISION 5
1-04-25
4
02
REVISION 3
1-04-25
5
02
JAN 17, 2003
1-04-25
6
02
JAN 17, 2003
1-04-30
1
02
JAN 17, 2003
1-04-30
2
02
JAN 17, 2003
1-04-30
3
02
JAN 17, 2003
1-04-30
4
02
JAN 17, 2003
1-04-30
5
02
JAN 17, 2003
1-04-30
6
02
JAN 17, 2003
1-04-30
7
02
JAN 17, 2003
1-04-30
8
02
JAN 17, 2003
1-04-30
9
02
JAN 17, 2003
1-04-30
10
02
JAN 17, 2003
1-04-30
11
02
JAN 17, 2003
1-04-30
12
02
JAN 17, 2003
1-04-30
13
02
JAN 17, 2003
1-04-30
14
02
JAN 17, 2003
1-04-30
15
02
JAN 17, 2003
1-04-30
16
02
JAN 17, 2003
1-04-30
17
02
JAN 17, 2003
1-04-30
18
02
JAN 17, 2003
1-04-30
19
02
JAN 17, 2003
1-04-30
20
02
JAN 17, 2003
1-04-30
21
02
JAN 17, 2003
Applicability (model, engine, certification, other)
A1E FAA
A1E FAA
* Asterisk indicates pages revised, added or deleted by the current revision. Page
1-LEP
Code
20 07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-04-30 22 02
Change JAN 17, 2003
1-04-30
23
02
JAN 17, 2003
1-04-30
24
02
JAN 17, 2003
1-04-30
25
02
JAN 17, 2003
1-04-30
26
02
JAN 17, 2003
1-04-30
27
02
JAN 17, 2003
1-04-30
28
02
JAN 17, 2003
1-04-30
29
02
JAN 17, 2003
1-04-30
30
02
JAN 17, 2003
1-04-30
31
02
JAN 17, 2003
1-04-30
32
02
JAN 17, 2003
1-05-00
1
01
REVISION 6
1-05-00
2
01
REVISION 6
1-05-05
1
08
REVISION 4
1-05-05
2
08
REVISION 4
1-05-05
3
08
REVISION 4
1-05-05
4
08
REVISION 4
1-05-05
5
08
REVISION 4
1-05-05
6
08
REVISION 4
1-05-05
7
08
REVISION 4
1-05-05
8
08
REVISION 4
1-05-05
9
08
REVISION 4
1-05-05
10
08
REVISION 4
1-05-05
11
08
REVISION 4
1-05-05
12
08
REVISION 4
1-05-05
13
08
REVISION 4
1-05-05
14
08
REVISION 4
1-05-05
15
08
REVISION 4
1-05-05
16
08
REVISION 4
1-05-05
17
08
REVISION 4
1-05-05
18
08
REVISION 4
1-05-05
19
08
REVISION 4
1-05-05
20
08
REVISION 4
1-05-07
1
02
REVISION 4
LIST OF EFFECTIVE PAGES
Applicability (model, engine, certification, other)
ALL
CONFIG D lb
A1P / A1E lb
* Asterisk indicates pages revised, added or deleted by the current revision. Page
REVISION 7
1-LEP
Code
21 07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
Page Page Code Block 1-05-07 2 02 1-05-10
1
08
Change
Applicability (model, engine, certification, other)
REVISION 4
*
REVISION 7
1-05-10
2
08
1-05-10
3
08
1-05-10
4
08
REVISION 4
1-05-10
5
08
REVISION 4
1-05-10
6
08
REVISION 4
1-05-10
7
08
REVISION 4
1-05-10
8
08
REVISION 4
1-05-10
9
08
REVISION 4
1-05-10
10
08
REVISION 4
1-05-10
11
08
REVISION 4
1-05-10
12
08
REVISION 4
1-05-10
13
08
REVISION 4
1-05-10
14
08
REVISION 4
1-05-10
15
08
REVISION 4
1-05-10
16
08
REVISION 4
1-05-10
17
08
REVISION 4
1-05-10
18
08
REVISION 4
1-05-10
19
08
REVISION 4
1-05-10
20
08
REVISION 4
1-05-10
21
08
REVISION 4
1-05-10
22
08
REVISION 4
1-05-10
23
08
1-05-10
24
08
1-05-10
25
08
1-05-10
26
08
1-05-10
27
08
1-05-10
28
08
1-05-10
29
08
1-05-10
30
08
1-05-10
31
08
1-05-10
32
08
1-05-10
33
08
CONFIG D lb
REVISION 4
*
*
REVISION 7
REVISION 7 REVISION 4
* * * * * * * * *
REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7
* Asterisk indicates pages revised, added or deleted by the current revision. Page
1-LEP
Code
22 07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-05-10 34 08
Change
* * * * * * * * * * * *
35
08
1-05-10
36
08
1-05-10
37
08
1-05-10
38
08
1-05-10
39
08
1-05-10
40
08
1-05-10
41
08
1-05-10
42
08
1-05-10
43
08
1-05-10
44
08
1-05-15
1
08
1-05-15
2
08
REVISION 4
1-05-15
3
08
REVISION 4
1-05-15
4
08
REVISION 4
1-05-15
5
08
REVISION 4
1-05-15
6
08
REVISION 4
1-05-15
7
08
REVISION 4
1-05-15
8
08
REVISION 4
1-05-15
9
08
REVISION 4
1-05-15
10
08
1-05-15
11
08
1-05-15
12
08
REVISION 4
1-05-15
13
08
REVISION 4
1-05-15
14
08
REVISION 4
1-05-15
15
08
REVISION 4
1-05-15
16
08
REVISION 4
1-05-15
17
08
REVISION 4
1-05-15
18
08
1-05-15
19
08
1-05-15
20
08
REVISION 4
1-05-15
21
08
REVISION 4
1-05-15
22
08
1-05-15
23
08
* *
* *
Applicability (model, engine, certification, other)
REVISION 7
1-05-10
* *
LIST OF EFFECTIVE PAGES
REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 new REVISION 7 new REVISION 7 REVISION 7
CONFIG D lb
REVISION 7 REVISION 7
REVISION 7 REVISION 7
REVISION 7 REVISION 7
* Asterisk indicates pages revised, added or deleted by the current revision. Page
REVISION 7
1-LEP
Code
23 07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
Page Page Code Block 1-05-15 24 08
Change REVISION 4
1-05-15
25
08
REVISION 4
1-05-15
26
08
1-05-15
27
08
1-05-15
28
08
REVISION 4
1-05-15
29
08
REVISION 4
1-05-15
30
08
1-05-15
31
08
1-05-15
32
08
REVISION 4
1-05-15
33
08
REVISION 4
1-05-15
34
08
1-05-15
35
08
1-05-15
36
08
REVISION 4
1-05-15
37
08
REVISION 4
1-05-15
38
08
1-05-15
39
08
1-05-15
40
08
1-05-20
1
08
1-05-20
2
08
1-05-20
3
08
1-05-20
4
08
1-05-20
5
08
1-05-20
6
08
1-05-25
1
08
1-05-25
2
08
1-05-25
3
08
1-05-25
4
08
1-05-25
5
08
1-05-25
6
08
1-05-25
7
08
1-05-25
8
08
1-05-25
9
08
1-05-25
10
08
1-05-30
1
11
Applicability (model, engine, certification, other)
REVISION 7
* *
REVISION 7
REVISION 7
* *
REVISION 7
REVISION 7
* *
REVISION 7
REVISION 7
* *
REVISION 7 REVISION 4
* * * * * * * * * * * * * * * *
REVISION 7
CONFIG D lb
REVISION 7 new REVISION 7 new REVISION 7 new REVISION 7 new REVISION 7 REVISION 7
CONFIG D lb
REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 new REVISION 7 new REVISION 7 new REVISION 7 new REVISION 7 REVISION 4
CONFIG D FAA
* Asterisk indicates pages revised, added or deleted by the current revision. Page
1-LEP
Code
24 07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-05-30 2 11
Change REVISION 4
1-05-30
3
11
REVISION 4
1-05-30
4
11
REVISION 4
1-05-30
5
11
REVISION 4
1-05-30
6
11
REVISION 4
1-05-30
7
11
REVISION 4
1-05-30
8
11
REVISION 4
1-05-30
9
11
REVISION 4
1-05-30
10
11
REVISION 4
1-05-30
11
11
REVISION 4
1-05-30
12
11
REVISION 4
1-05-30
13
11
REVISION 4
1-05-30
14
11
REVISION 4
1-06-00
1
01
NOV 30, 2001
1-06-00
2
01
NOV 30, 2001
1-06-10
1
01
NOV 30, 2001
1-06-10
2
01
NOV 30, 2001
1-06-10
3
01
NOV 30, 2001
1-06-10
4
01
NOV 30, 2001
1-06-20
1
02
JAN 17, 2003
1-06-20
2
02
JAN 17, 2003
1-06-20
3
02
REVISION 5
1-06-20
4
02
REVISION 5
1-06-20
5
02
1-06-20
6
02
REVISION 3
1-06-20
7
02
REVISION 5
1-06-20
8
02
REVISION 3
1-06-30
1
02
JAN 17, 2003
*
LIST OF EFFECTIVE PAGES
Applicability (model, engine, certification, other)
ALL
ALL
lb
REVISION 7
1-06-30
2
02
JAN 17, 2003
1-06-30
3
02
JAN 17, 2003
1-06-30
4
02
JAN 17, 2003
1-06-30
5
02
REVISION 5
1-06-30
6
02
REVISION 5
1-06-30
7
02
REVISION 5
lb
* Asterisk indicates pages revised, added or deleted by the current revision. Page
REVISION 7
1-LEP
Code
25 07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
Page Page Code Block 1-06-30 8 02
Change
Applicability (model, engine, certification, other)
REVISION 5
1-07-00
1
01
NOV 30, 2001
1-07-00
2
01
NOV 30, 2001
1-07-10
1
01
NOV 30, 2001
1-07-10
2
01
NOV 30, 2001
1-07-10
3
01
NOV 30, 2001
1-07-10
4
01
NOV 30, 2001
1-07-20
1
01
NOV 30, 2001
1-07-20
2
01
NOV 30, 2001
1-07-30
1
01
NOV 30, 2001
1-07-30
2
01
JUN 20, 2002
1-07-30
3
01
JUN 20, 2002
1-07-30
4
01
JUN 20, 2002
1-07-30
5
01
JUN 20, 2002
1-07-30
6
01
JUN 20, 2002
1-07-30
7
01
REVISION 4
1-07-30
8
01
REVISION 4
1-07-30
9
01
REVISION 4
1-07-30
10
01
REVISION 6
1-07-30
11
01
REVISION 4
1-07-30
12
01
REVISION 6
1-07-40
1
01
NOV 30, 2001
1-07-40
2
01
NOV 30, 2001
1-07-50
1
01
NOV 30, 2001
1-07-50
2
01
NOV 30, 2001
1-07-60
1
01
JUN 20, 2002
1-07-60
2
01
NOV 30, 2001
1-07-60
3
01
NOV 30, 2001
1-07-60
4
01
NOV 30, 2001
1-07-70
1
01
NOV 30, 2001
1-07-70
2
01
NOV 30, 2001
1-07-70
3
01
NOV 30, 2001
1-07-70
4
01
NOV 30, 2001
ALL
ALL
ALL
ALL
ALL
ALL
ALL
ALL
* Asterisk indicates pages revised, added or deleted by the current revision. Page
1-LEP
Code
26 07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-07-80 1 01
NOV 30, 2001
1-07-80
01
NOV 30, 2001
2
Change
1-08-00
1
02
REVISION 6
1-08-00
2
02
REVISION 3
1-08-00
3
02
JAN 17, 2003
1-08-00
4
02
JAN 17, 2003
1-08-06
1
02
JAN 17, 2003
1-08-06
2
02
JAN 17, 2003
1-08-06
3
02
JAN 17, 2003
1-08-06
4
02
JAN 17, 2003
1-08-06
5
02
JAN 17, 2003
1-08-06
6
02
JAN 17, 2003
1-08-06
7
02
JAN 17, 2003
1-08-06
8
02
JAN 17, 2003
1-08-23
1
02
JAN 17, 2003
1-08-23
2
02
JAN 17, 2003
1-08-28
1
02
JAN 17, 2003
1-08-28
2
02
JAN 17, 2003
1-08-28
3
02
JAN 17, 2003
1-08-28
4
02
JAN 17, 2003
1-08-32
1
02
JAN 17, 2003
1-08-32
2
02
JAN 17, 2003
1-08-33
1
02
JAN 17, 2003
1-08-33
2
02
JAN 17, 2003
1-08-49
1
02
JAN 17, 2003
1-08-49
2
02
JAN 17, 2003
1-08-52
1
02
JAN 17, 2003
1-08-52
2
02
JAN 17, 2003
1-08-54
1
02
REVISION 6
1-08-54
2
02
REVISION 3
1-08-54
3
02
JAN 17, 2003
1-08-54
4
02
JAN 17, 2003
1-08-55
1
02
JAN 17, 2003
LIST OF EFFECTIVE PAGES
Applicability (model, engine, certification, other) ALL
FAA
FAA
FAA
FAA
FAA
FAA
FAA
FAA
FAA
FAA
* Asterisk indicates pages revised, added or deleted by the current revision. Page
REVISION 7
1-LEP
Code
27 07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
Page Page Code Block 1-08-55 2 02
Change JAN 17, 2003
1-08-55
3
02
JAN 17, 2003
1-08-55
4
02
JAN 17, 2003
1-08-55
5
02
JAN 17, 2003
1-08-55
6
02
JAN 17, 2003
1-08-55
7
02
JAN 17, 2003
1-08-55
8
02
JAN 17, 2003
1-08-57
1
02
JAN 17, 2003
1-08-57
2
02
JAN 17, 2003
1-08-78
1
02
REVISION 6
1-08-78
2
02
REVISION 6
1-09-00
1
06
REVISION 6
1-09-00
2
06
REVISION 6
1-09-00
3
06
REVISION 6
1-09-00
4
06
REVISION 6
1-09-00
5
06
REVISION 6
1-09-00
6
06
REVISION 6
1-09-00
7
06
REVISION 6
1-09-00
8
06
REVISION 6
1-09-00
9
06
REVISION 6
1-09-00
10
06
REVISION 6
1-09-00
11
06
REVISION 6
1-09-00
12
06
REVISION 6
1-09-02
1
06
REVISION 6
1-09-02
2
06
REVISION 6
1-09-02
3
06
REVISION 6
1-09-02
4
06
REVISION 6
1-09-02
5
06
REVISION 6
1-09-02
6
06
REVISION 6
1-09-02
7
06
REVISION 6
1-09-02
8
06
REVISION 6
1-09-02
9
06
REVISION 6
1-09-02
10
06
REVISION 6
1-09-21
1
06
REVISION 6
Applicability (model, engine, certification, other)
FAA
FAA
FAA
FAA
FAA
* Asterisk indicates pages revised, added or deleted by the current revision. Page
1-LEP
Code
28 07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-09-21 2 06
Change REVISION 6
1-09-21
3
06
REVISION 6
1-09-21
4
06
REVISION 6
1-09-21
5
06
REVISION 6
1-09-21
6
06
REVISION 6
1-09-21
7
06
REVISION 6
1-09-21
8
06
REVISION 6
1-09-21
9
06
REVISION 6
1-09-21
10
06
REVISION 6
1-09-21
11
06
REVISION 6
1-09-21
12
06
REVISION 6
1-09-21
13
06
REVISION 6
1-09-21
14
06
REVISION 6
1-09-21
15
06
REVISION 6
1-09-21
16
06
REVISION 6
1-09-21
17
06
REVISION 6
1-09-21
18
06
REVISION 6
1-09-21
19
06
REVISION 6
1-09-21
20
06
REVISION 6
1-09-21
21
06
REVISION 6
1-09-21
22
06
REVISION 6
1-09-21
23
06
REVISION 6
1-09-21
24
06
REVISION 6
1-09-21
25
06
REVISION 6
1-09-21
26
06
REVISION 6
1-09-22
1
06
REVISION 6
1-09-22
2
06
REVISION 6
1-09-22
3
06
REVISION 6
1-09-22
4
06
REVISION 6
1-09-23
1
06
REVISION 6
1-09-23
2
06
REVISION 6
1-09-23
3
06
REVISION 6
1-09-23
4
06
REVISION 6
1-09-23
5
06
REVISION 6
LIST OF EFFECTIVE PAGES
Applicability (model, engine, certification, other)
FAA
FAA
* Asterisk indicates pages revised, added or deleted by the current revision. Page
REVISION 7
1-LEP
Code
29 07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
Page Page Code Block 1-09-23 6 06
Change REVISION 6
1-09-23
7
06
REVISION 6
1-09-23
8
06
REVISION 6
1-09-23
9
06
REVISION 6
1-09-23
10
06
REVISION 6
1-09-23
11
06
REVISION 6
1-09-23
12
06
REVISION 6
1-09-23
13
06
REVISION 6
1-09-23
14
06
REVISION 6
1-09-24
1
06
REVISION 6
1-09-24
2
06
REVISION 6
1-09-24
3
06
REVISION 6
1-09-24
4
06
REVISION 6
1-09-24
5
06
REVISION 6
1-09-24
6
06
REVISION 6
1-09-25
1
06
REVISION 6
1-09-25
2
06
REVISION 6
1-09-25
3
06
REVISION 6
1-09-25
4
06
REVISION 6
1-09-25
5
06
REVISION 6
1-09-25
6
06
REVISION 6
1-09-25
7
06
REVISION 6
1-09-25
8
06
REVISION 6
1-09-25
9
06
REVISION 6
1-09-25
10
06
REVISION 6
1-09-25
11
06
REVISION 6
1-09-25
12
06
REVISION 6
1-09-25
13
06
REVISION 6
1-09-25
14
06
REVISION 6
1-09-25
15
06
REVISION 6
1-09-25
16
06
REVISION 6
1-09-25
17
06
REVISION 6
1-09-25
18
06
REVISION 6
1-09-26
1
06
REVISION 6
Applicability (model, engine, certification, other)
FAA
FAA
FAA
* Asterisk indicates pages revised, added or deleted by the current revision. Page
1-LEP
Code
30 07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-09-26 2 06
Change REVISION 6
1-09-26
3
06
REVISION 6
1-09-26
4
06
REVISION 6
1-09-26
5
06
REVISION 6
1-09-26
6
06
REVISION 6
1-09-26
7
06
REVISION 6
1-09-26
8
06
REVISION 6
1-09-26
9
06
REVISION 6
1-09-26
10
06
REVISION 6
1-09-27
1
06
REVISION 6
1-09-27
2
06
REVISION 6
1-09-27
3
06
REVISION 6
1-09-27
4
06
REVISION 6
1-09-27
5
06
REVISION 6
1-09-27
6
06
REVISION 6
1-09-27
7
06
REVISION 6
1-09-27
8
06
REVISION 6
1-09-27
9
06
REVISION 6
1-09-27
10
06
REVISION 6
1-09-27
11
06
REVISION 6
1-09-27
12
06
REVISION 6
1-09-27
13
06
REVISION 6
1-09-27
14
06
REVISION 6
1-09-27
15
06
REVISION 6
1-09-27
16
06
REVISION 6
1-09-28
1
06
REVISION 6
1-09-28
2
06
REVISION 6
1-09-28
3
06
REVISION 6
1-09-28
4
06
REVISION 6
1-09-28
5
06
REVISION 6
1-09-28
6
06
REVISION 6
1-09-28
7
06
REVISION 6
1-09-28
8
06
REVISION 6
1-09-28
9
06
REVISION 6
LIST OF EFFECTIVE PAGES
Applicability (model, engine, certification, other)
FAA
FAA
* Asterisk indicates pages revised, added or deleted by the current revision. Page
REVISION 7
1-LEP
Code
31 07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
Page Page Code Block 1-09-28 10 06
Change REVISION 6
1-09-28
11
06
REVISION 6
1-09-28
12
06
REVISION 6
1-09-28
13
06
REVISION 6
1-09-28
14
06
REVISION 6
1-09-28
15
06
REVISION 6
1-09-28
16
06
REVISION 6
1-09-28
17
06
REVISION 6
1-09-28
18
06
REVISION 6
1-09-28
19
06
REVISION 6
1-09-28
20
06
REVISION 6
1-09-28
21
06
REVISION 6
1-09-28
22
06
REVISION 6
1-09-28
23
06
REVISION 6
1-09-28
24
06
REVISION 6
1-09-28
25
06
REVISION 6
1-09-28
26
06
REVISION 6
1-09-28
27
06
REVISION 6
1-09-28
28
06
REVISION 6
1-09-28
29
06
REVISION 6
1-09-28
30
06
REVISION 6
1-09-28
31
06
REVISION 6
1-09-28
32
06
REVISION 6
1-09-28
33
06
REVISION 6
1-09-28
34
06
REVISION 6
1-09-28
35
06
REVISION 6
1-09-28
36
06
REVISION 6
1-09-28
37
06
REVISION 6
1-09-28
38
06
REVISION 6
1-09-28
39
06
REVISION 6
1-09-28
40
06
REVISION 6
1-09-28
41
06
REVISION 6
1-09-28
42
06
REVISION 6
1-09-28
43
06
REVISION 6
Applicability (model, engine, certification, other)
* Asterisk indicates pages revised, added or deleted by the current revision. Page
1-LEP
Code
32 07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-09-28 44 06
Change REVISION 6
1-09-28
45
06
REVISION 6
1-09-28
46
06
REVISION 6
1-09-28
47
06
REVISION 6
1-09-28
48
06
REVISION 6
1-09-28
49
06
REVISION 6
1-09-28
50
06
REVISION 6
1-09-28
51
06
REVISION 6
1-09-28
52
06
REVISION 6
1-09-29
1
06
REVISION 6
1-09-29
2
06
REVISION 6
1-09-29
3
06
REVISION 6
1-09-29
4
06
REVISION 6
1-09-29
5
06
REVISION 6
1-09-29
6
06
REVISION 6
1-09-29
7
06
REVISION 6
1-09-29
8
06
REVISION 6
1-09-29
9
06
REVISION 6
1-09-29
10
06
REVISION 6
1-09-29
11
06
REVISION 6
1-09-29
12
06
REVISION 6
1-09-29
13
06
REVISION 6
1-09-29
14
06
REVISION 6
1-09-30
1
06
REVISION 6
1-09-30
2
06
REVISION 6
1-09-30
3
06
REVISION 6
1-09-30
4
06
REVISION 6
1-09-30
5
06
REVISION 6
1-09-30
6
06
REVISION 6
1-09-30
7
06
REVISION 6
1-09-30
8
06
REVISION 6
1-09-30
9
06
REVISION 6
1-09-30
10
06
REVISION 6
1-09-30
11
06
REVISION 6
LIST OF EFFECTIVE PAGES
Applicability (model, engine, certification, other)
FAA
FAA
* Asterisk indicates pages revised, added or deleted by the current revision. Page
REVISION 7
1-LEP
Code
33 07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
Page Page Code Block 1-09-30 12 06
Change REVISION 6
1-09-30
13
06
REVISION 6
1-09-30
14
06
REVISION 6
1-09-30
15
06
REVISION 6
1-09-30
16
06
REVISION 6
1-09-30
17
06
REVISION 6
1-09-30
18
06
REVISION 6
1-09-31
1
06
REVISION 6
1-09-31
2
06
REVISION 6
1-09-31
3
06
REVISION 6
1-09-31
4
06
REVISION 6
1-09-31
5
06
REVISION 6
1-09-31
6
06
REVISION 6
1-09-32
1
06
REVISION 6
1-09-32
2
06
REVISION 6
1-09-32
3
06
REVISION 6
1-09-32
4
06
REVISION 6
1-09-32
5
06
REVISION 6
1-09-32
6
06
REVISION 6
1-09-32
7
06
REVISION 6
1-09-32
8
06
REVISION 6
1-09-32
9
06
REVISION 6
1-09-32
10
06
REVISION 6
1-09-33
1
06
REVISION 6
1-09-33
2
06
REVISION 6
1-09-33
3
06
REVISION 6
1-09-33
4
06
REVISION 6
1-09-33
5
06
REVISION 6
1-09-33
6
06
REVISION 6
1-09-33
7
06
REVISION 6
1-09-33
8
06
REVISION 6
1-09-33
9
06
REVISION 6
1-09-33
10
06
REVISION 6
1-09-33
11
06
REVISION 6
Applicability (model, engine, certification, other)
FAA
FAA
FAA
* Asterisk indicates pages revised, added or deleted by the current revision. Page
1-LEP
Code
34 07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-09-33 12 06
Change REVISION 6
1-09-33
13
06
REVISION 6
1-09-33
14
06
REVISION 6
1-09-34
1
06
REVISION 6
1-09-34
2
06
REVISION 6
1-09-34
3
06
REVISION 6
1-09-34
4
06
REVISION 6
1-09-34
5
06
REVISION 6
1-09-34
6
06
REVISION 6
1-09-34
7
06
REVISION 6
1-09-34
8
06
REVISION 6
1-09-34
9
06
REVISION 6
1-09-34
10
06
REVISION 6
1-09-34
11
06
REVISION 6
1-09-34
12
06
REVISION 6
1-09-34
13
06
REVISION 6
1-09-34
14
06
REVISION 6
1-09-34
15
06
REVISION 6
1-09-34
16
06
REVISION 6
1-09-34
17
06
REVISION 6
1-09-34
18
06
REVISION 6
1-09-34
19
06
REVISION 6
1-09-34
20
06
REVISION 6
1-09-34
21
06
REVISION 6
1-09-34
22
06
REVISION 6
1-09-34
23
06
REVISION 6
1-09-34
24
06
REVISION 6
1-09-35
1
06
REVISION 6
1-09-35
2
06
REVISION 6
1-09-35
3
06
REVISION 6
1-09-35
4
06
REVISION 6
1-09-35
5
06
REVISION 6
1-09-35
6
06
REVISION 6
1-09-36
1
06
REVISION 6
LIST OF EFFECTIVE PAGES
Applicability (model, engine, certification, other)
FAA
FAA
FAA
* Asterisk indicates pages revised, added or deleted by the current revision. Page
REVISION 7
1-LEP
Code
35 07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
Page Page Code Block 1-09-36 2 06
Change REVISION 6
1-09-36
3
06
REVISION 6
1-09-36
4
06
REVISION 6
1-09-36
5
06
REVISION 6
1-09-36
6
06
REVISION 6
1-09-36
7
06
REVISION 6
1-09-36
8
06
REVISION 6
1-09-36
9
06
REVISION 6
1-09-36
10
06
REVISION 6
1-09-38
1
06
REVISION 6
1-09-38
2
06
REVISION 6
1-09-38
3
06
REVISION 6
1-09-38
4
06
REVISION 6
1-09-45
1
06
REVISION 6
1-09-45
2
06
REVISION 6
1-09-49
1
06
REVISION 6
1-09-49
2
06
REVISION 6
1-09-49
3
06
REVISION 6
1-09-49
4
06
REVISION 6
1-09-52
1
06
REVISION 6
1-09-52
2
06
REVISION 6
1-09-52
3
06
REVISION 6
1-09-52
4
06
REVISION 6
1-09-52
5
06
REVISION 6
1-09-52
6
06
REVISION 6
1-09-56
1
06
REVISION 6
1-09-56
2
06
REVISION 6
1-09-73
1
06
REVISION 6
1-09-73
2
06
REVISION 6
1-09-73
3
06
REVISION 6
1-09-73
4
06
REVISION 6
1-09-73
5
06
REVISION 6
1-09-73
6
06
REVISION 6
1-09-73
7
06
REVISION 6
Applicability (model, engine, certification, other)
FAA
FAA
FAA
FAA
FAA
FAA
* Asterisk indicates pages revised, added or deleted by the current revision. Page
1-LEP
Code
36 07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-09-73 8 06
Change REVISION 6
1-09-73
9
06
REVISION 6
1-09-73
10
06
REVISION 6
1-09-74
1
06
REVISION 6
1-09-74
2
06
REVISION 6
1-09-77
1
06
REVISION 6
1-09-77
2
06
REVISION 6
1-09-78
1
06
REVISION 6
1-09-78
2
06
REVISION 6
1-09-79
1
06
REVISION 6
1-09-79
2
06
REVISION 6
1-09-79
3
06
REVISION 6
1-09-79
4
06
REVISION 6
1-09-80
1
06
REVISION 6
1-09-80
2
06
REVISION 6
1-10-00
1
01
NOV 30, 2001
1-10-00
2
01
NOV 30, 2001
1-10-05
1
01
NOV 30, 2001
1-10-05
2
01
NOV 30, 2001
1-10-05
3
01
NOV 30, 2001
1-10-05
4
01
NOV 30, 2001
1-10-05
5
01
NOV 30, 2001
1-10-05
6
01
NOV 30, 2001
1-10-05
7
01
NOV 30, 2001
1-10-05
8
01
NOV 30, 2001
1-10-05
9
01
1-10-05
10
01
ORIGINAL
*
LIST OF EFFECTIVE PAGES
Applicability (model, engine, certification, other)
FAA
FAA
FAA
FAA
FAA
ALL
ALL
REVISION 7
1-10-08
1
01
NOV 30, 2001
1-10-08
2
01
NOV 30, 2001
1-10-10
1
01
NOV 30, 2001
1-10-10
2
01
NOV 30, 2001
1-10-15
1
01
NOV 30, 2001
1-10-15
2
01
NOV 30, 2001
ALL
ALL
ALL
* Asterisk indicates pages revised, added or deleted by the current revision. Page
REVISION 7
1-LEP
Code
37 07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
Page Page Code Block 1-10-20 1 01
Change NOV 30, 2001
1-10-20
2
01
NOV 30, 2001
1-10-20
3
01
NOV 30, 2001
1-10-20
4
01
NOV 30, 2001
1-10-20
5
01
JUN 20, 2002
1-10-20
6
01
JUN 20, 2002
1-10-20
7
01
JUN 20, 2002
1-10-20
8
01
JUN 20, 2002
1-10-25
1
01
NOV 30, 2001 NOV 30, 2001
1-10-25
2
01
1-11-00
1
01
1-11-00
2
01
ORIGINAL
REVISION 7
*
1-11-05
1
01
REVISION 4
1-11-05
2
01
ORIGINAL
1-11-10
1
01
1-11-10
2
01
1-11-10
3
01
1-11-10
4
01
* * * *
new REVISION 7
Applicability (model, engine, certification, other) ALL
ALL
ALL
ALL
ALL
new REVISION 7 new REVISION 7 new REVISION 7
1-11-40
1
01
NOV 30, 2001
1-11-40
2
01
NOV 30, 2001
1-11-40
3
01
NOV 30, 2001
1-11-40
4
01
NOV 30, 2001
1-11-40
5
01
NOV 30, 2001
1-11-40
6
01
NOV 30, 2001
1-11-40
7
01
NOV 30, 2001
1-11-40
8
01
NOV 30, 2001
1-11-45
1
01
NOV 30, 2001
1-11-45
2
01
NOV 30, 2001
1-11-45
3
01
NOV 30, 2001
1-11-45
4
01
NOV 30, 2001
1-12-00
1
01
REVISION 5
1-12-00
2
01
ORIGINAL
1-12-00
3
01
NOV 30, 2001
1-12-00
4
01
NOV 30, 2001
ALL
ALL
ALL
* Asterisk indicates pages revised, added or deleted by the current revision. Page
1-LEP
Code
38 07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-12-05 1 01
Change NOV 30, 2001
1-12-05
2
01
NOV 30, 2001
1-12-05
3
01
NOV 30, 2001
1-12-05
4
01
NOV 30, 2001
1-12-05
5
01
NOV 30, 2001
1-12-05
6
01
NOV 30, 2001
1-12-05
7
01
NOV 30, 2001
1-12-05
8
01
NOV 30, 2001
1-12-10
1
01
NOV 30, 2001
1-12-10
2
01
NOV 30, 2001
1-12-10
3
01
NOV 30, 2001
1-12-10
4
01
NOV 30, 2001
1-12-15
1
01
NOV 30, 2001
1-12-15
2
01
NOV 30, 2001
1-12-15
3
01
NOV 30, 2001
1-12-15
4
01
NOV 30, 2001
1-12-20
1
01
ORIGINAL
1-12-20
2
01
1-12-20
3
01
1-12-20
4
01
1-12-20
5
01
1-12-20
6
01
1-12-20
7
01
1-12-20
8
01
1-12-25
1
01
REVISION 6
1-12-25
2
01
REVISION 6
1-12-25
3
01
REVISION 6
1-12-25
4
01
REVISION 4
1-12-25
5
01
REVISION 4
1-12-25
6
01
REVISION 4
1-12-25
7
01
REVISION 3
1-12-25
8
01
REVISION 4
1-12-25
8A
01
REVISION 4
1-12-25
8B
01
REVISION 4
* * * * * * *
LIST OF EFFECTIVE PAGES
Applicability (model, engine, certification, other) ALL
ALL
ALL
ALL
REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 REVISION 7 ALL
* Asterisk indicates pages revised, added or deleted by the current revision. Page
REVISION 7
1-LEP
Code
39 07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
Page Page Code Block 1-12-25 9 01
Change
Applicability (model, engine, certification, other)
REVISION 3
1-12-25
10
01
REVISION 6
1-12-25
11
01
JUN 20, 2002
1-12-25
12
01
JUN 20, 2002
1-12-25
13
01
REVISION 1
1-12-25
14
01
REVISION 4
1-12-25
15
01
REVISION 1
1-12-25
16
01
REVISION 4
1-12-25
17
01
JUN 20, 2002
1-12-25
18
01
JUN 20, 2002
1-12-25
19
01
REVISION 4
1-12-25
20
01
REVISION 4
1-12-25
21
01
REVISION 4
1-12-25
22
01
REVISION 4
1-12-25
23
01
REVISION 6
1-12-25
24
01
REVISION 4
1-12-30
1
01
NOV 30, 2001
1-12-30
2
01
NOV 30, 2001
1-12-30
3
01
NOV 30, 2001
1-12-30
4
01
NOV 30, 2001
1-12-35
1
01
NOV 30, 2001
1-12-35
2
01
NOV 30, 2001
1-12-40
1
01
NOV 30, 2001
1-12-40
2
01
NOV 30, 2001
1-12-40
3
01
NOV 30, 2001
1-12-40
4
01
NOV 30, 2001
1-12-40
5
01
NOV 30, 2001
1-12-40
6
01
NOV 30, 2001
1-12-45
1
01
NOV 30, 2001
1-12-45
2
01
NOV 30, 2001
1-12-50
1
01
1-12-50
2
01
1-12-50
3
01
1-12-50
4
01
*
REVISION 7
ALL
ALL
ALL
ALL
ALL
REVISION 5
*
REVISION 7 REVISION 5
* Asterisk indicates pages revised, added or deleted by the current revision. Page
1-LEP
Code
40 07
REVISION 7
AIRPLANE OPERATIONS MANUAL Page Page Code Block 1-12-50 5 01
Change
LIST OF EFFECTIVE PAGES
Applicability (model, engine, certification, other)
REVISION 5
1-12-50
6
01
1-12-50
7
01
REVISION 5
1-12-50
8
01
REVISION 5
1-12-50
9
01
REVISION 4
1-12-50
10
01
REVISION 4
1-12-50
11
01
REVISION 4
1-12-50
12
01
REVISION 5
1-12-50
13
01
REVISION 4
1-12-50
14
01
REVISION 4
*
REVISION 7
* Asterisk indicates pages revised, added or deleted by the current revision. Page
REVISION 7
1-LEP
Code
41 07
LIST OF EFFECTIVE PAGES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-LEP
Code
42 07
REVISION 7
TABLE OF CONTENTS
AIRPLANE OPERATIONS MANUAL
TABLE OF CONTENTS AOM - VOLUME 1 1-00 -
GENERAL INFORMATION AND DEFINITION OF TERMS
1-01 -
LIMITATIONS
1-02 -
NORMAL PROCEDURES
1-03 -
EMERGENCY PROCEDURES
1-04 -
PERFORMANCE
1-05 -
FLIGHT PLANNING
1-06 -
WEIGHT AND BALANCE
1-07 -
LOADING
1-08 -
CONFIGURATION DEVIATION LIST
1-09 -
MINIMUM EQUIPMENT LIST
1-10 -
EMERGENCY INFORMATION
1-11 -
EMERGENCY EVACUATION
1-12 -
GROUND SERVICING
AND
ABNORMAL
Page
JUNE 20, 2002
1-TOC
Code
1 01
TABLE OF CONTENTS
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-TOC
Code
2 01
JUNE 20, 2002
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
SECTION 1-08 CONFIGURATION DEVIATION LIST TABLE OF CONTENTS Page Block Introduction ................................................................................ 1-08-00 ATA Chapter 06 Dimensions and Areas .................................... 1-08-06 ATA Chapter 23 Communications ............................................. 1-08-23 ATA Chapter 28 Fuel ................................................................. 1-08-28 ATA Chapter 32 Landing Gear................................................... 1-08-32 ATA Chapter 33 Lights............................................................... 1-08-33 ATA Chapter 49 Airborne Auxiliary Power ................................. 1-08-49 ATA Chapter 52 Doors............................................................... 1-08-52 ATA Chapter 54 Nacelle/Pylons................................................. 1-08-54 ATA Chapter 55 Stabilizers........................................................ 1-08-55 ATA Chapter 57 Wings .............................................................. 1-08-57 ATA Chapter 78 Engine Exhaust ............................................... 1-08-78
Page
REVISION 6
1-08-00
Code
1 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
INTRODUCTION This Configuration Deviation List contains additional certificate limitations for operation of the EMB-135 BJ airplanes without certain secondary airframe and engine parts as listed herein. When the airplane is operated using the CDL, it must be operated in accordance with the limitations specified in the AFM, as amended in the CDL. All the items which are related to the airworthiness of the airplane and not included on the list are automatically required. The associated limitations must be listed on a placard affixed in the cockpit in clear view of the pilots and other appropriate crewmember(s). The pilot in command should be notified of each operation with a missing part(s) by listing the missing part(s) in the flight or dispatch release. The operator should list in the airplane logbook an appropriate notation covering the missing part(s) on each flight. If an additional part is lost, the airplane may not depart the airport at which it landed following this event, until it complies with the limitation of the CDL. This, of course, does not preclude the issuance of a ferry permit to allow the airplane to be flown to a point where the necessary repairs or replacement can be made. No more than one part for any one system may be missing, unless specific combinations of parts are included in the CDL. Unless otherwise specified, parts from different systems may be missing. The performance penalties are cumulative, unless specifically designated penalties are indicated for the combination of missing parts. No more than three parts that have each been determined to cause negligible performance degradation may be missing for takeoff without applying a performance penalty. When more than three of such parts are missing, a performance penalty of either 0.5 percent of the maximum takeoff weight or 45 kilograms (100 pounds), whichever is less, must be applied for takeoff, en route, and landing for each missing part. No more than ten parts that have each been determined to cause no performance penalty may be missing.
Page
1-08-00
Code
2 02
REVISION 3
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
Takeoff performance penalties should be applied to the takeoff weights that are limited by performance considerations (i.e., takeoff field length, first, second, or final segment climb, or takeoff flight path). If the performance-limited takeoff weight is greater than the maximum certified takeoff weight, the takeoff performance penalties should be applied to the maximum certified takeoff weight to ensure compliance with the noise requirements. Landing performance penalties should be applied to the landing weights that are limited by performance considerations (i.e., landing field length, landing climb, or approach climb). If the performancelimited landing weight is greater than the maximum certified landing weight, the landing performance penalties should be applied to the maximum certified landing weight to ensure compliance with the noise requirements. En route performance penalties apply only to operations that are limited by the one-engine inoperative en route climb performance.
Page
JANUARY 17, 2003
1-08-00
Code
3 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
COMPONENT LOCATION The numbering and designation of systems in this section are based on ATA Spec. 100. The parts within each system are identified by their functional description and, when necessary, by door or panel identification, followed by the appropriate figure. The access doors and panels in a zone are identified by an alphanumeric system which has three digits. They identify the zone where the access door or panel is located, followed by a two-letter or three-letter suffix. − The first digit indicates a major zone of the airplane, which gives the necessary reference for the identification of the service areas or components: MAJOR ZONE AREA 100 Lower fuselage (below the floor line) 200 Upper fuselage (above the floor line) 300 Tail cone and empennage group 400 Powerplant and nacellles 500 Left half-wing 600 Right half-wing 700 Landing gear wheel well doors 800 Doors (main, service, cargo, emergency) − The following two digits indicates sub-zones. For example: 111 - Radome; 510 - Wing Leading Edge. − The first letter identifies a sequence which starts with the letter A. − The second letter shows the location of each access door or panel in relation to the aircraft as follows: B: Bottom T: Top L: Left R: Right − Each panel gets a fastener identification code, boxed, which identifies the type and quantity of the fasteners for each panel. L: Latch S: Screw C: Camloc For further details on this system, please see Airplane Maintenance Manual, Chapter 6, for the part identification. Page
1-08-00
Code
4 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
ATA CHAPTER 06 DIMENSIONS AND AREAS System & Sequence Number
ITEM
1. 2. Number installed 3. Number required for dispatch 4. Remarks and/or exceptions
6 DIMENSIONS AND AREAS 41-1 Main Door Closing Control Panel Access Door (123AL – Figure 1)
1
0
May be missing with no penalty.
41-2 External Power Connection Access Door (113EL – Figure 1)
1
0
May be missing with no penalty.
41-3 Ground Air Conditioning Connection Access Door (196CR – Figure 3)
1
0
May be missing provided maximum airspeed is limited to 250 KIAS/0.65 M, whichever is lower.
41-5 Air Conditioning Heat Exchanger Grills (191ML – Figure 2) (191NR – Figure 3)
2
0
May be missing provided maximum airspeed is limited to 250 KIAS/0.65 M, whichever is lower.
41-6 Pack Valve/Wing Anti-ice Valve Access Door (191KL – Figure 2) (191LR – Figure 3)
2
0
May be missing provided maximum airspeed is limited to 250 KIAS/0.65 M, whichever is lower.
41-7 Bleed Flexible Joint Access Door (195AL/CL – Figure 2) (194AR/CR – Figure 3)
4
0
May be missing provided maximum airspeed is limited to 250 KIAS/0.65 M, whichever is lower.
41-8 Red Beacon Fairing (192EL – Figure 2)
1
0
May be missing provided maximum airspeed is limited to 250 KIAS/0.65 M, whichever is lower.
Page
JANUARY 17, 2003
1-08-06
Code
1 02
CONFIGURATION DEVIATION LIST
System & Sequence Number
AIRPLANE OPERATIONS MANUAL
ITEM
1. 2. Number installed 3. Number required for dispatch 4. Remarks and/or exceptions
6 DIMENSIONS AND AREAS 41-9 Hydraulic System Servicing Access Door (193DL/EL/FL – Figure 2) (193GR/HR/JR – Figure 3)
6
0
May be missing provided maximum airspeed is limited to 250 KIAS/0.65 M, whichever is lower.
41-10 Wing Center Region Access Door (192AL – Figure 2) (192BR – Figure 3)
2
0
May be missing provided maximum airspeed is limited to 250 KIAS/0.65 M, whichever is lower.
42-1 Pressure Fueling Panel Access Door (191SR – Figure 3)
1
0
May be missing provided: a) Door microswitch is locked in the actuated position (simulating door closed); b) Refueling, defueling and power switches are checked in the CLOSED/NORMAL position; c) Refueling cap is locked and latched; and d) Maximum airspeed is limited to 250 KIAS/0.65 M, whichever is lower.
42-2 Potable Water Service Access Door (193NR – Figure 3)
1
0
May be missing provided maximum airspeed is limited to 250 KIAS/0.65 M, whichever is lower.
42-3 Waste Service Panel Access Door (193MR – Figure 3)
1
0
May be missing with no penalty.
Page
1-08-06
Code
2 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
FIGURE 1 Page
JANUARY 17, 2003
1-08-06
Code
3 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
FIGURE 2 Page
1-08-06
Code
4 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
FIGURE 3 Page
JANUARY 17, 2003
1-08-06
Code
5 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
System & Sequence
1. 2. Number installed ITEM
3. Number required for dispatch
Number
4. Remarks and/or exceptions
6 DIMENSIONS AND AREAS 42-4 Ground Pneumatic Engine Starting Connection Access Door (272CR – Figure 4)
1
0
May be missing with no penalty.
42-5 Ramp Interphone Connection Access Door (272BR – Figure 4)
1
0
May be missing with no penalty.
42-6 APU Cowling Attaching Bolts Access Door (313GR/DR/AL/BL – Figure 5)
4
0
May be missing with no penalty.
42-7 APU Servicing Access Door (313CL – Figure 5)
1
0
May be missing provided APU operates on the ground only.
Page
1-08-06
Code
6 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
FIGURE 4 Page
JANUARY 17, 2003
1-08-06
Code
7 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
FIGURE 5 Page
1-08-06
Code
8 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL System & Sequence
CONFIGURATION DEVIATION LIST
1. 2. Number installed ITEM
Number
3. Number required for dispatch 4. Remarks and/or exceptions
23 COMMUNICATIONS 60-1 Static Dischargers (Figure 6)
24 16 A maximum of 8 (eight) static discharges may be missing in any combination provided: a) 1 (one) is installed on the nose landing gear; b) 4 (four) are installed on each wing; c) 1 (one) is installed on the rudder; d) 3 (three) are installed on each elevator.
Page
JANUARY 17, 2003
1-08-23
Code
1 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
Page
1-08-23
Code
2 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
ATA CHAPTER 28 FUEL System & Sequence Number
ITEM
1. 2. Number installed 3. Number required for dispatch 4. Remarks and/or exceptions
28 FUEL 11-1 Fuel Tank Drain Access Door (192CL/HL – Figure 2) (192DR/JR – Figure 3)
4
0
May be missing provided maximum airspeed is limited to 250 KIAS/0.65 M, whichever is lower.
12-1 Vent Valves Screen Assembly (2 on the Forward Fuel Tanks and 2 on the Wing Fuel Tanks)
4
0
May be missing with no penalty.
42-1 Direct Quantity Measuring Sticks (192FL – Figure 2) (192GR – Figure 3) (531CB and 541BB – Figure 7) (631CB and 641BB – Figure 8)
6
0
May be missing with no penalty.
Page
JANUARY 17, 2003
1-08-28
Code
1 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
FIGURE 7 Page
1-08-28
Code
2 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
FIGURE 8 Page
JANUARY 17, 2003
1-08-28
Code
3 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-08-28
Code
4 02
JANUARY 17, 2003
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
ATA CHAPTER 32 LANDING GEAR System & Sequence Number
ITEM
1. 2. Number installed 3. Number required for dispatch 4. Remarks and/or exceptions
32 LANDING GEAR 10-1 Main Landing Gear Doors
2
0
May be missing provided maximum airspeed is limited to 250 KIAS/0.65 M, whichever is lower.
10-2 Main Landing Gear Wheels Fairing
2
0
May be missing provided maximum airspeed is limited to 250 KIAS/0.65 M, whichever is lower.
Page
JANUARY 17, 2003
1-08-32
Code
1 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-08-32
Code
2 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
ATA CHAPTER 33 LIGHTS System & Sequence Number
ITEM
1. 2. Number installed 3. Number required for dispatch 4. Remarks and/or exceptions
33 LIGHTS 41-1 Nose Landing Light
1
0
May be missing with no penalty.
42-1 Taxi Light
2
0
May be missing with no penalty.
43-1 Navigation Light Protective Lens
3
0
May be missing with no penalty.
44-1 Inspection Light Protective Lens
2
0
May be missing with no penalty.
46-1 Logotype Light Protective Lens
2
0
May be missing with no penalty.
47-1 Red Beacon Light Protective Lens
2
0
May be missing with no penalty.
50-1 Exterior Emergency Light Protective Lens
2
0
May be missing with no penalty.
Page
JANUARY 17, 2003
1-08-33
Code
1 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-08-33
Code
2 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
ATA CHAPTER 49 AIRBORNE AUXILIARY POWER System & Sequence Number
ITEM
1. 2. Number installed 3. Number required for dispatch 4. Remarks and/or exceptions
49 AUXILIARY POWER UNIT 42-1 APU Starter/Generator Air Intake Scoop
1
0
May be missing provided APU operates on the ground only.
52-1 APU Compartment Cooling Air Intake Scoop
1
0
May be missing provided APU operates on the ground only.
Page
JANUARY 17, 2003
1-08-49
Code
1 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-08-49
Code
2 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
ATA CHAPTER 52 DOORS System & Sequence Number
ITEM
1. 2. Number installed 3. Number required for dispatch 4. Remarks and/or exceptions
52 DOORS 10-1 Main Door Handgrip
1
0
May be missing with no penalty.
43-2 Tail Cone Access Door (312AR – Figure 5)
1
0
May be missing with no penalty.
Page
JANUARY 17, 2003
1-08-52
Code
1 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-08-52
Code
2 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
ATA CHAPTER 54 NACELLE/PYLONS System & Sequence Number
ITEM
1. 2. Number installed 3. Number required for dispatch 4. Remarks and/or exceptions
54 NACELLE/PYLONS 50-1 Systems Access Door (414AB/BB/EB – Figure 9) (424AB/BB/EB – Figure 10)
6
4
A maximum of 1 per pylon for a total of 2 may be missing provided maximum airspeed is limited to 250 KIAS/0.65 M, whichever is lower.
50-2 Bleed Valve Access Door (414DB – Figure 9) (424DB – Figure 10)
2
0
May be missing with no penalty.
50-3 Pre-cooler and Fan Air Valve Access Door (414CB – Figure 9) (424CB – Figure 10)
2
0
May be missing with no penalty.
50-4 Engine Pylon Fairing (414HL, 424HR)
2
0
May be missing with no penalty.
Page
REVISION 6
1-08-54
Code
1 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
FIGURE 9 Page
1-08-54
Code
2 02
REVISION 3
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
FIGURE 10 Page
JANUARY 17, 2003
1-08-54
Code
3 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-08-54
Code
4 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
ATA CHAPTER 55 STABILIZERS System & Sequence Number
ITEM
1. 2. Number installed 3. Number required for dispatch 4. Remarks and/or exceptions
55 STABILIZERS 10-2 Horizontal Stabilizer Access Door (333AB/BB/CB – Figure 11) (334AB/BB/CB – Figure 12)
6
4
A maximum of 1 per side for a total of 2 may be missing with no penalty.
20-2 Spring Tab Control Rod Fairing and Associated Bracket (1 – Figure 15 2 – Figure 15)
4
0
May be missing with no penalty.
20-3 Servo Tab Control Rod Fairing and Associated Bracket (3 – Figure 15)
2
0
May be missing with no penalty.
20-4 Elevator Access Door (335AB/BB/CB/DB/ EB/FB/GB/HB – Figure 11) (336AB/BB/CB/DB/ EB/FB/GB/HB Figure 12)
16 15 One may be missing with no penalty. 335AB/BB/CB/DB/EB and 336AB/BB/CB/DB/EB cannot be missing.
30-1 Vertical Stabilizer Access Door (322AL, 324AL/BL/CL/DL/EL, 325AL/BL/CL/DL/EL, FL – Figure 13) (322BR, 324FR, 325FR/GR/HR/JR/ KR/LR – Figure 14)
20 17 A maximum of 3 in any combination may be missing with no penalty. 324EL/FR and 325EL/LR cannot be missing.
Page
JANUARY 17, 2003
1-08-55
Code
1 02
CONFIGURATION DEVIATION LIST
System & Sequence Number
AIRPLANE OPERATIONS MANUAL
ITEM
1. 2. Number installed 3. Number required for dispatch 4. Remarks and/or exceptions
55 STABILIZERS 40-1 Rudder Access Door (326AL/BL/CL/DL/EL/ FL/GL/HL, 327AL/BL/CL/DL – Figure 13) (327ER/FR/GR/HR – Figure 14)
Page
1-08-55
16 14 A maximum of 2 in any combination may be missing with no penalty.
Code
2 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
FIGURE 11 Page
JANUARY 17, 2003
1-08-55
Code
3 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
FIGURE 12 Page
1-08-55
Code
4 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
FIGURE 13 Page
JANUARY 17, 2003
1-08-55
Code
5 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
FIGURE 14 Page
1-08-55
Code
6 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
FIGURE 15 Page
JANUARY 17, 2003
1-08-55
Code
7 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-08-55
Code
8 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
ATA CHAPTER 57 WINGS System & Sequence Number
ITEM
1. 2. Number installed 3. Number required for dispatch 4. Remarks and/or exceptions
57 WINGS 20-1 Vortex Generator
24 22 A maximum of 1 per wing for a total of 2 may be missing with no penalty.
30-2 Wing Tip Len
2
0
May be missing with no penalty.
52-1 Flap Track Fairing
10
9
One may be missing with no penalty.
52-2 Wing-to-Flap Seal
4
3
One may be missing provided maximum airspeed is limited to 250 KIAS / 0.65M, whichever is lower.
Page
JANUARY 17, 2003
1-08-57
Code
1 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-08-57
Code
2 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
CONFIGURATION DEVIATION LIST
ATA CHAPTER 78 ENGINE EXHAUST System & Sequence ITEM Number
1.
2. Number installed 3. Number required for dispatch 4. Remarks and/or exceptions
78 ENGINE EXHAUST 31-1 Plug Inhibition of the Thrust Reverses
4
0
May be missing with no penalty.
Page
REVISION 6
1-08-78
Code
1 02
CONFIGURATION DEVIATION LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-08-78
Code
2 02
REVISION 6
EMERGENCY AND ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
SECTION 1-03 EMERGENCY AND ABNORMAL PROCEDURES TABLE OF CONTENTS Page Block INTRODUCTION ....................................................................... 1-03-00
EMERGENCY PROCEDURES SMOKE AIR CONDITIONING SMOKE ................................................... 1-03-02 BAGGAGE COMPARTMENT SMOKE...................................... 1-03-02 CABIN FIRE OR SMOKE........................................................... 1-03-02 ELECTRICAL SYSTEM FIRE OR SMOKE................................ 1-03-02 LAVATORY SMOKE (IF APPLICABLE) .................................... 1-03-02 SMOKE EVACUATION.............................................................. 1-03-02 AIR CONDITIONING, PNEUMATICS, PRESSURIZATION BLEED LEAK ............................................................................. 1-03-04 BLEED OVERTEMPERATURE ................................................. 1-03-04 EMERGENCY DESCENT.......................................................... 1-03-04 RAPID CABIN DEPRESSURIZATION....................................... 1-03-04 APU APU FIRE................................................................................... 1-03-06 APU OVERTEMPERATURE ..................................................... 1-03-06 DOORS, DITCHING, EVACUATION
FORCED
LANDING
,
EMERGENCY
DITCHING.................................................................................. 1-03-08 EMERGENCY EVACUATION.................................................... 1-03-08 FORCED LANDING ................................................................... 1-03-08 MAIN DOOR OPEN ................................................................... 1-03-08
Page
REVISION 6
1-03-00
Code
1 01
EMERGENCY AND ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
ELECTRICAL POWER, LIGHTING BATTERY OVERTEMPERATURE ............................................1-03-10 ELECTRIC ESSENTIAL TRANSFER FAILURE ........................1-03-10 LOSS OF ALL GENERATORS ..................................................1-03-10 ENGINE ATTCS NO MARGIN..................................................................1-03-12 DUAL ENGINE FAILURE...........................................................1-03-12 ENGINE ATTCS FAILURE.........................................................1-03-12 ENGINE FIRE, SEVERE DAMAGE OR SEPARATION.............1-03-12 ENGINE LOW N1.......................................................................1-03-12 ENGINE OIL LOW PRESSURE.................................................1-03-12 REJECTED TAKEOFF (AT OR BELOW V1) .............................1-03-12 TAKEOFF WITH ENGINE FAILURE ABOVE V1 .......................1-03-12 FLIGHT CONTROLS AILERON/ROLL TRIM RUNAWAY............................................1-03-14 INADVERTENT SPOILER OPENING IN FLIGHT .....................1-03-14 JAMMED AILERON ...................................................................1-03-14 JAMMED ELEVATOR ................................................................1-03-14 JAMMED RUDDER....................................................................1-03-14 PITCH TRIM INOPERATIVE......................................................1-03-14 PITCH TRIM RUNAWAY ...........................................................1-03-14 FUEL AIRPLANE FUEL LOAD.............................................................1-03-16 FUEL LOW LEVEL.....................................................................1-03-16 HYDRAULICS, LANDING GEAR AND BRAKES LANDING GEAR/LEVER DISAGREE........................................1-03-18 ICE AND RAIN PROTECTION, OXYGEN ANTI-ICING INOPERATIVE IN ICING CONDITIONS ...............1-03-20
Page
1-03-00
Code
2 01
REVISION 3
EMERGENCY AND ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL NAVIGATION, FLIGHT INSTRUMENTS, AUTOPILOT
AUTOPILOT FAILURE .............................................................. 1-03-22 WARNING SYSTEMS STALL PROTECTION INOPERATIVE ...................................... 1-03-24 STICK PUSHER FAILURE ........................................................ 1-03-24 TAKEOFF CONFIGURATION WARNING ................................ 1-03-24
ABNORMAL PROCEDURES AIR CONDITIONING, PNEUMATICS AND PRESSURIZATION .............................................................. 1-03-26 APU ......................................................................................... 1-03-28 DOORS AND MISCELLANEOUS.............................................. 1-03-30 ELECTRICAL POWER, LIGHTING ........................................... 1-03-32 ENGINE ..................................................................................... 1-03-34 FIRE PROTECTION .................................................................. 1-03-36 FLIGHT CONTROLS ................................................................. 1-03-38 FUEL ......................................................................................... 1-03-40 HYDRAULICS, LANDING GEAR & BRAKES............................ 1-03-42 ICE & RAIN PROTECTION, OXYGEN ...................................... 1-03-44 NAVIGATION, FLIGHT INSTRUMENTS, AUTOPILOT ............ 1-03-46 WARNING SYSTEMS ............................................................... 1-03-48 CAT II OPERATION................................................................... 1-03-49 STEEP APPROACH OPERATION............................................ 1-03-51
PROFILES EMERGENCY PROFILES ......................................................... 1-03-60 ABNORMAL PROFILES ............................................................ 1-03-62
Page
REVISION 4
1-03-00
Code
3 01
EMERGENCY AND ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
INTRODUCTION The emergency and abnormal procedures contained in this manual have been developed by the airplane manufacturer and approved by the certification authority for use in the operation of this airplane. This Section provides the emergency and abnormal procedures to be performed in case of a system malfunction or failure, in order to protect passengers and/or crew from serious harm and to maintain the airworthiness of the airplane. Some procedures require a landing at the nearest suitable airport. Such information is provided with the intent of establishing that the flight should be terminated at the pilot's discretion. It is the pilot’s responsibility to use good judgement concerning the time and place to land, as well as to evaluate factors such as airplane condition, weather, etc... However, it is emphasized that for fire or smoke that cannot be positively located and extinguished, an immediate descent, landing and passenger evacuation should be performed. The procedures are presented as follows: − The actions contained in a box are immediate actions. They must be performed expeditiously and from memory to minimize hazards. The other actions should be performed as soon as the condition permits. − All the actions must be performed in the given order. Procedures contained herein assume: − Airplane systems are operating normally prior to the failure. − Normal procedures have been properly accomplished. − System controls are in normal condition prior to initiation of the associated procedure. − Aural warnings are silenced as applicable. Master Warning/Caution lights are reset as soon as the failure is recognized. − Oxygen masks and smoke goggles are donned when cabin altitude is excessive or ambient air is contaminated. − Crew communication is established when required. − Circuit breakers are checked.
Page
1-03-00
Code
4 01
REVISION 3
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
EMERGENCY PROCEDURES SMOKE AIR CONDITIONING SMOKE Suspect Bleed ............................................................... CLOSE Crossbleed .................................................................... OPEN If procedure does not eliminate smoke, change bleed source supplying the air conditioning (including APU bleed). SMOKE EVACUATION and CABIN FIRE OR SMOKE Procedures................ AS REQUIRED WARNING: IF IN ICING CONDITIONS, REFER TO SINGLE ENGINE OR SINGLE BLEED OPERATION IN ICING CONDITIONS PROCEDURE.
BAGGAGE COMPARTMENT SMOKE EICAS WARNING: BAGG SMOKE LIGHT: Master Warning EICAS CAUTION BAGG ACCESS OPN ...................... NOT DISPLAYED Baggage Fire Extinguishing Button............................... PRESS Diversion ....................................................................... CONSIDER Altitude .......................................................................... MAINTAIN Maintain the current flight level as long as possible. Alternate Airport ............................................................ IDENTIFY Commence the diversion to land at the nearest suitable airport. NOTE: - The extinguishing agent duration is approximately 75 minutes. - Advise ground crew of possible presence of Halon vapors and smoke trapped in the compartment.
Page
JANUARY 17, 2003
1-03-02
Code
1 01
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
CABIN FIRE OR SMOKE Crew Oxygen Masks .....................................................DON, SELECT 100% Smoke Goggles or PBE ................................................DON Recirculation Fan ..........................................................OFF Crew Communication ....................................................ESTABLISH Diversion........................................................................CONSIDER Fire or Smoke Source ...................................................IDENTIFY AIR CONDITIONING SMOKE Procedure.................................................................AS REQUIRED ELECTRICAL SYSTEM FIRE OR SMOKE Procedure...................................................AS REQUIRED SMOKE EVACUATION Procedure (if necessary) ..........................................ACCOMPLISH Determine and extinguish any source of fire or smoke within the cabin. After conducting the fire or smoke procedures, even though smoke has dissipated, land at the nearest suitable airport, unless it can be visually verified that the fire has been extinguished.
Page
1-03-02
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
EMERGENCY PROCEDURES
ELECTRICAL SYSTEM FIRE OR SMOKE If smoke source can be determined: Electrical Power to Associated Equipment .............. OFF If smoke source cannot be determined: Shed Buses.............................................................. OFF If smoke does not stop or decrease after a reasonable time, cut power to Central DC Bus as follows: Bus Ties .............................................................. OFF APU Generator ................................................... OFF Battery 2.............................................................. OFF If smoke does not stop or decrease after a reasonable time, cut power to DC Bus 1 and Essential DC Bus 1 as follows: Fuel Pumps......................................................... 1B AND 2A OR 2C Battery 2.............................................................. AUTO Battery 1.............................................................. OFF Generators 1 and 3............................................. OFF If smoke does not stop or decrease after a reasonable time, restore power to the previously deenergized buses and cut power to DC Bus 2 and Essential DC Bus 2 as follows: Generators 1 and 3............................................. ON Battery 1.............................................................. AUTO Fuel Pumps......................................................... 1A OR 1C AND 2B Battery 2.............................................................. OFF Generators 2 and 4............................................. OFF If smoke does not stop or decrease after a reasonable time, restore power to the previously deenergized buses and cut power to Backup Buses as follows: Generators 2 and 4............................................. ON Battery 2.............................................................. AUTO APU Generator ................................................... AS REQUIRED Bus Ties .............................................................. AUTO Shed Buses......................................................... AUTO Backup Battery.................................................... OFF Land at the nearest suitable airport. SMOKE EVACUATION Procedure (if necessary) .......................................... ACCOMPLISH
Page
ORIGINAL
1-03-02
Code
3 01
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
LAVATORY SMOKE (IF APPLICABLE) EICAS WARNING: LAV SMOKE LIGHT: Master Warning Lavatory Flush and Light CBs (Located in Line E) ........PULL CABIN FIRE OR SMOKE Procedure ............................AS REQUIRED
SMOKE EVACUATION Cockpit Door..................................................................CLOSE Recirculation Fan ..........................................................OFF Gasper Fan ...................................................................OFF Pressurization Manual Controller ..................................1 O'CLOCK Wait 15 seconds. Pressurization Mode Selector........................................MAN Pressurization Manual Controller ..................................AS REQUIRED Passenger Oxygen ........................................................AS REQUIRED To evacuate the smoke faster: Pressurization Manual Controller .............................UP Packs 1 and 2 ..........................................................OFF Bleeds (engine or APU)............................................OPEN Emergency Descent .................................................AS REQUIRED Altitude .....................................................................MEA OR 10000 ft, WHICHEVER IS HIGHER Recover cabin pressure as soon as smoke has been cleared.
Page
1-03-02
Code
4 01
REVISION 6
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
AIR CONDITIONING, PRESSURIZATION
PNEUMATICS,
BLEED LEAK EICAS WARNING: BLD 1 (2) LEAK or BLD APU LEAK LIGHT: Master Warning Crossbleed .................................................................... CLOSE Associated Bleed and APU Bleed................................. CLOSE Altitude .......................................................................... MAX 25000 ft MINIMUM MEA Icing Conditions............................................................. EXIT/AVOID Wait 3 minutes. If the message remains on, but the associated advisory message on EICAS (BLD 1 or 2 VLV CLSD) indicates the valve is closed: Opposite Bleed ........................................................ CLOSE Associated Bleed ..................................................... OPEN Wait 3 minutes. If the message still remains: Associated Bleed ................................................ CLOSE Altitude ................................................................ MEA OR 10000 ft WHICHEVER IS HIGHER If the message remains on and is associated with a failed engine bleed valve (BLD 1 or 2 VLV FAIL caution message): Associated Thrust Lever .......................................... IDLE Wait 3 minutes. If the message still remains: Associated Engine (or APU) ............................... SHUTDOWN
BLEED OVERTEMPERATURE EICAS WARNING: BLD 1 (2) OVTEMP LIGHT: Master Warning Crossbleed .................................................................... OPEN Cross-side Bleed........................................................... OPEN Associated Bleed .......................................................... CLOSE Altitude .......................................................................... MAX 25000 ft MINIMUM MEA WARNING: IF IN ICING CONDITIONS, REFER TO SINGLE ENGINE OR SINGLE BLEED OPERATION IN ICING CONDITIONS PROCEDURE. Page
JANUARY 17, 2003
1-03-04
Code
1 02
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
EMERGENCY DESCENT Cabin Crew....................................................................NOTIFY Fasten Belts ..................................................................ON Thrust Levers ................................................................IDLE Speed Brakes................................................................OPEN Airspeed ........................................................................250 KIAS Landing Gear.................................................................DOWN Minimum Enroute Altitude .............................................CHECK CAUTION: THIS PROCEDURE ASSUMES THAT THE INTEGRITY OF THE STRUCTURE IS NOT AFFECTED. IF STRUCTURAL DAMAGE IS SUSPECTED, USE THE FLIGHT CONTROLS WITH CAUTION AVOIDING HIGH MANEUVERING LOADS AND REDUCING AIRSPEED AS APPROPRIATE. NOTE: It is recommended that descent be initiated by a turn with a bank angle of 30°.
RAPID CABIN DEPRESSURIZATION AURAL WARNING: CABIN Crew Oxygen Masks .....................................................DON Crew Communication ....................................................ESTABLISH Emergency Descent ......................................................AS REQUIRED Passenger Announcement ............................................PERFORM Passengers inside the baggage compartment must be told to return immediately to their seats. Passenger Oxygen ........................................................AS REQUIRED Altitude...........................................................................MEA OR 10000 ft, WHICHEVER IS HIGHER
Page
1-03-04
Code
2 02
JANUARY 17, 2003
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
APU APU FIRE EICAS WARNING: APU FIRE AURAL WARNING: BELL LIGHT: Master Warning APU Fuel Shutoff Valve ................................................ CLOSE APU Master Knob ......................................................... OFF APU FUEL SOV CLSD message on EICAS ................................................................. CONFIRM If the valve is not confirmed closed and the fire message remains: Right Electric Fuel Pumps........................................ OFF Crossfeed................................................................. OFF Initiate a descent to 25000 ft or MEA, whichever is higher. After 30 seconds, if the APU FIRE message remains displayed on EICAS or an APU failure is associated to an APU FIREDET FAIL message: APU Fire Extinguishing Button................................. PRESS Land at the nearest suitable airport. WARNING: DO NOT ATTEMPT TO RESTART APU.
APU OVERTEMPERATURE APU Bleed .................................................................... CLOSE Wait 10 seconds. If EGT still in red or yellow range: APU Fuel Shutoff Valve ........................................... CLOSE APU Master Knob .................................................... OFF
Page
REVISION 7
1-03-06
Code
1 01
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-06
Code
2 01
ORIGINAL
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
DOORS, DITCHING, FORCED EMERGENCY EVACUATION DITCHING
LANDING,
WARNING: THE EMB 135 BJ WAS NOT TESTED FOR DITCHING. BELOW ARE THE RECOMMENDED PROCEDURES, WHICH HAVE BEEN DEVELOPED BASED ON PREVIOUS EXPERIENCE. ATC/Cabin Crew ........................................................... NOTIFY Transponder.................................................................. 7700 ELT ............................................................................... ON Emergency Lights ......................................................... ON Passengers .................................................................. PREPARE FOR DITCHING Cabin (below 10000 ft) .................................................. DEPRESSURIZE If necessary, inhibit EGPWS (D2 or J8) and Aural Warning System (B4 and E30) by pulling their circuit breakers. When reaching 1000 ft: Air Conditioning 1 and 2........................................... OFF Engine Bleeds .......................................................... CLOSE Approach configuration: If in icing conditions: Landing Gear ........................................................... UP Flaps ........................................................................ 22° If it is not possible to achieve the selected flap position, maintain airspeed according to the following: FLAPS POSITION 0 to 8° 9° to 21° 22°
MINIMUM AIRSPEED VREF 45 + 30 KIAS VREF 45 + 10 KIAS VREF 45 + 5 KIAS
If not in icing conditions: Landing Gear ........................................................... UP Flaps ........................................................................ 45° If it is not possible to achieve the selected flap position, maintain airspeed according to the following: FLAPS POSITION 0 to 8° 9° to 21° 22° to 44° 45°
MINIMUM AIRSPEED VREF 45 + 30 KIAS VREF 45 + 10 KIAS VREF 45 + 5 KIAS VREF 45 Page
REVISION 7
1-03-08
Code
1 01
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
The final path should be made with airplane straight and level. Yaw angles should be limited to one ball of sideslip. If possible, ditching should be made parallel to the line of the wave crests. Before touchdown: Rate of Descent .......................................................LESS THAN 180 ft/MIN Attitude .....................................................................4° NOSE UP Upon water contact: Start/Stop Selectors .................................................STOP EMERGENCY EVACUATION Procedure ................ACCOMPLISH WARNING: AIRPLANE EVACUATION MUST BE DONE THROUGH THE OVERWING EMERGENCY EXITS ONLY. DO NOT OPEN REMAINING DOORS. Before leaving the airplane: Batteries ...................................................................OFF
EMERGENCY EVACUATION Parking Brake (if necessary) .........................................APPLY Cabin .............................................................................DEPRESSURIZE Fire Extinguishing Handles............................................PULL APU Fuel Shutoff Valve.................................................CLOSE APU and Engine Fire Extinguishing Bottles (if necessary)................................................DISCHARGE Electric Fuel Pumps ......................................................OFF Electric Hydraulic Pumps ..............................................OFF Cabin Crew....................................................................NOTIFY Emergency Lighting.......................................................ON Evacuation.....................................................................INITIATE NOTE: - Cockpit door blow-out panels may be broken to be used as an alternative way to leave cockpit. - In case of the cabin dual pocket door becomes jammed, push or kick at the center until door breaks free and then restow it. - The fwd lavatory bi-fold door must be securely locked to ensure a free pathway. ATC ...............................................................................NOTIFY Before leaving the airplane: Batteries ...................................................................OFF Page
1-03-08
Code
2 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
EMERGENCY PROCEDURES
FORCED LANDING This procedure is recommended for landings with all engines inoperative or for landings in unprepared surfaces. Landing on unprepared surfaces is not recommended. However, if specific circumstances render such landing inevitable, accomplish the procedures below. ATC and Cabin Crew .................................................... NOTIFY Transponder.................................................................. 7700 ELT................................................................................ ON Emergency Lights ......................................................... ON Passenger ..................................................................... PREPARE FOR FORCED LANDING Cabin (below 10000 ft) .................................................. DEPRESSURIZE When committed to land: If in icing conditions: Landing Gear ........................................................... AS REQUIRED Flaps ........................................................................ 22° If it is not possible to achieve the selected flap position, maintain airspeed according to the following: FLAPS POSITION 0 to 8° 9° to 21° 22°
MINIMUM AIRSPEED VREF 45 + 30 KIAS VREF 45 + 10 KIAS VREF 45 + 5 KIAS
If not in icing conditions: Landing Gear ........................................................... AS REQUIRED Flaps ........................................................................ 45° If it is not possible to achieve the selected flap position, maintain airspeed according to the following: FLAPS POSITION 0 to 8° 9° to 21° 22° to 44° 45°
MINIMUM AIRSPEED VREF 45 + 30 KIAS VREF 45 + 10 KIAS VREF 45 + 5 KIAS VREF 45
Page
ORIGINAL
1-03-08
Code
3 01
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
If necessary, inhibit EGPWS (D2 or J8) and Aural Warning System (B4 and E30) by pulling their circuit breakers. If crash is unavoidable, just before touchdown: Fire Extinguishing Handles.......................................PULL APU Fuel Shutoff Valve............................................CLOSE Batteries ...................................................................OFF When the airplane comes to a complete stop: EMERGENCY EVACUATION Procedure............................................................ACCOMPLISH In case of fire: Fire Extinguishing Handles.......................................PULL AND ROTATE AS REQUIRED
Page
1-03-08
Code
4 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
EMERGENCY PROCEDURES
MAIN DOOR OPEN EICAS WARNING: MAIN DOOR OPN LIGHT: Master Warning Fasten Seat Belts.......................................................... ON Check doors pictorial indication on MFD Takeoff Page. If message is confirmed or if MFD is not available: Door Internal Lock Indicator (red marks) ................. CHECK If the door is confirmed locked: Continue flight normally. If the door internal lock indicators are not aligned or it is not possible to maintain the pressurization, proceed: Altitude ..................................................................... MEA OR 10000 ft, WHICHEVER IS HIGHER Cabin........................................................................ DEPRESSURIZE Land at the nearest suitable airport.
Page
JANUARY 17, 2003
1-03-08
Code
5 01
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-08
Code
6 01
NOVEMBER 30, 2001
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
ELECTRICAL POWER, LIGHTING BATTERY OVERTEMPERATURE EICAS WARNING: BATT 1 (2) OVTEMP LIGHT: Master Warning Associated Battery......................................................OFF If the associated BATT OFF BUS message is not on, land at the nearest suitable airport.
ELECTRIC ESSENTIAL TRANSFER FAILURE EICAS WARNING: ELEC ESS XFR FAIL LIGHT: Master Warning If no generator is available: LOSS OF ALL GENERATORS Procedure ........................................................... ACCOMPLISH If the message remains: Bus Ties ................................................................... OFF If the message still remains: Shed Buses.............................................................. OFF Turn off equipment not essential for the flight. Begin with the equipment connected to DC Buses 1 and 2 (Circuit Breaker Panel rows D, E, F, G, H). Land at the nearest suitable airport.
Page
JANUARY 17, 2003
1-03-10
Code
1 02
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
LOSS OF ALL GENERATORS EICAS CAUTION: GEN 1, 2, 3, 4 OFF BUS and APU GEN OFF BUS LIGHT: Master Caution INDICATION: Generators voltage indication on MFD may be amber. Airspeed ........................................................................MAXIMUM 250 KIAS Altitude...........................................................................MEA OR 10000 ft, WHICHEVER IS HIGHER Essential Power.............................................................ON Crew Oxygen.................................................................AS REQUIRED Passenger Oxygen ........................................................AS REQUIRED Emergency Lights..........................................................OFF If required, turn on Emergency Lights before landing. Land at the nearest suitable airport. CAUTION: • MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45O BY 1.58. • BATTERY DURATION IS 40 MINUTES. NOTE: - The nose landing doors will open if DC Bus 2 is off, therefore the pilot should expect noise increase. - The following warning messages will be presented: SPS 1-2 INOP and ICE COND-A/I INOP. - The following caution messages will be presented: STICK PUSHER FAIL, SPS ADVANCED, GPWS INOP, WINDSHEAR INOP, CHECK PFD 1, IC BUS FAIL, APU GEN OFF BUS, GEN 1-2-3-4 OFF BUS, DC BUS 1-2 OFF, SHED BUS 1-2 OFF, 115 VAC BUS OFF, EMERG LT NOT ARMD, E1-2 CTL A-B FAIL, ENG 1-2 REV FAIL, LG AIR/GND FAIL, FLAP FAIL, SPOILER FAIL, PITOT 1-2 INOP, W/S 1-2 HEAT FAIL, TAT 1-2 HEAT INOP, STAB A/ICE FAIL, A/ICE SW OFF, WG 1-2 A/ICE FAIL, E1-2 A/ICE FAIL, AOA 1-2 HEAT INOP, ICE DET 1-2 FAIL and ICE DETECTORS FAIL.
Page
1-03-10
Code
2 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
EMERGENCY PROCEDURES
ENGINE ATTCS NO MARGIN EICAS WARNING: E1 (2) ATTCS NO MRGN LIGHT: Master Warning During takeoff, below V1: REJECTED TAKEOFF Procedure........................... ACCOMPLISH Report to the maintenance personnel. Another takeoff is not permitted. CAUTION: BRAKES TEMPERATURE MUST BE CHECKED AFTER REJECTED TAKEOFFS.
DUAL ENGINE FAILURE EICAS WARNING: ENG 1-2 OUT LIGHT: Master Warning Airspeed ........................................................................ MINIMUM 260 KIAS Altitude .......................................................................... MAX 25000 ft Oxygen Mask (if required)............................................. DON ENGINE AIRSTART Procedure.................................... ACCOMPLISH CAUTION: IF APU HAS BEEN USED TO START THE ENGINES, DO NOT ALTERNATE THE FADECS AFTER START. NOTE: If APU is not available, only equipment supplied by the Essential DC Bus 1 and 2 will be available. Engine windmilling should drive engine driven pumps and supply hydraulic pressure. If neither engine can be restarted: FORCED LANDING Procedure ............................... ACCOMPLISH
Page
REVISION 7
1-03-12
Code
1 02
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
ENGINE ATTCS FAILURE EICAS WARNING: ATTCS FAIL LIGHT: Master Warning Thrust Levers ................................................................MAX Maintenance is required and another takeoff is not permitted.
Page
1-03-12
Code
2 02
REVISION 7
AIRPLANE OPERATIONS MANUAL
ENGINE FIRE, SEPARATION
SEVERE
EMERGENCY PROCEDURES
DAMAGE
OR
EICAS WARNING: ENG 1 (2) FIRE LIGHT: Engine Fire Handle AURAL WARNING: BELL (in case of fire) Identify the affected engine. Thrust Lever .................................................................. IDLE Start/Stop Selector ........................................................ STOP Fire Extinguishing Handle ............................................. PULL (DO NOT ROTATE) If the fire indications remains displayed after 30 seconds: st Fire Extinguishing Handle (1 shot) ......................... ROTATE If the fire indications remains displayed after 30 seconds: nd Fire Extinguishing Handle (2 shot)......................... ROTATE Crossfeed...................................................................... OFF Associated Fuel Pumps ................................................ OFF Associated Bleed .......................................................... CLOSE Associated Generators ................................................. OFF APU (if available) .......................................................... START APU Generator.............................................................. ON Confirm that the fuel shutoff valve has closed (E1 or E2 FUELSOV CLSD advisory message on EICAS). If ITT remains high: ENGINE DRY MOTORING Procedure .................... AS REQUIRED In flight: Land at the nearest suitable airport. On ground: EMERGENCY EVACUATION Procedure................ AS REQUIRED WARNING: • DO NOT ATTEMPT TO RESTART ENGINE. • IF IN ICING CONDITIONS, REFER TO SINGLE ENGINE OR SINGLE BLEED OPERATION IN ICING CONDITIONS PROCEDURE.
Page
JANUARY 17, 2003
1-03-12
Code
3 02
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
NOTE: - If in flight below 9700 ft, the air conditioning pack valves will close automatically. The APU may be used as pneumatic source by closing the remaining engine bleed valve. - Engine will not shutdown with the Start/Stop Selector unless associated Thrust Lever is first moved to IDLE. If STOP is selected before Thrust Lever is retarded to IDLE, momentarily cycle START/STOP Selector to RUN and back to STOP.
ENGINE LOW N1 EICAS WARNING: E1 (2) LOW N1 LIGHT: Master Warning If during takeoff, below V1: REJECTED TAKEOFF Procedure ...........................ACCOMPLISH If during takeoff, above V1 and associated with an engine flameout: TAKEOFF WITH ENGINE FAILURE Procedure......ACCOMPLISH If during takeoff, above V1 not associated with an engine flameout or during flight: Associated FADEC...................................................RESET If low thrust remains: Associated FADEC .............................................ALTN If engine flames out: Thrust Lever ........................................................IDLE Start/Stop Selector ..............................................STOP ENGINE AIRSTART Procedure..........................ACCOMPLISH
ENGINE OIL LOW PRESSURE EICAS WARNING: E1 (2) OIL LOW PRESS LIGHT: Master Warning Oil Pressure Indication ..................................................CHECK If flight conditions permit, reduce N2 below 88%, and monitor oil temperature and oil quantity indication. Monitor oil pressure for the remainder of the flight. If oil pressure is in the red range: Associated Thrust Lever ..........................................IDLE If oil pressure is still in the red range: PRECAUTIONARY ENGINE SHUTDOWN Procedure ................................ACCOMPLISH
Page
1-03-12
Code
4 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
EMERGENCY PROCEDURES
ENGINE REVERSER FAILURE EICAS CAUTION: ENG1 (2) REV FAIL If during takeoff, below V1: REJECTED TAKEOFF Procedure........................... ACCOMPLISH Associated Thrust Lever ............................................... IDLE Airspeed ........................................................................ MAXIMUM 200 KIAS PRECAUTIONARY ENGINE SHUTDOWN Procedure (if required) ...................... ACCOMPLISH Land at the nearest suitable airport. WARNING: DO NOT SET THRUST LEVER OUT OF IDLE.
REJECTED TAKEOFF (AT OR BELOW V1) Thrust Levers ................................................................ IDLE OR MAX REVERSE Brakes ........................................................................... APPLY MAXIMUM Directional Control......................................................... MAINTAIN Immediately after stopping: PRECAUTIONARY ENGINE SHUTDOWN or ENGINE FIRE, SEVERE DAMAGE OR SEPARATION Procedure ................................... AS REQUIRED
Page
JANUARY 17, 2003
1-03-12
Code
5 02
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
TAKEOFF WITH ENGINE FAILURE ABOVE V1 Maximum Takeoff Thrust ..............................................CHECK At VR rotate the airplane to 14° (for flaps 9°). With positive rate of climb: Landing Gear............................................................UP Airspeed ...................................................................V2 Maintain V2 up to the level off altitude. If maneuvering is required, maintain a maximum bank of 15°. When reaching the level off height: At V2 + 15 KIAS ........................................................FLAPS UP Airspeed ...................................................................ACCELERATE TO FINAL SEGMENT SPEED After flaps are retracted: PRECAUTIONARY ENGINE SHUTDOWN or ENGINE FIRE, SEVERE DAMAGE OR SEPARATION Procedure ...................................AS REQUIRED After a maximum of 5 minutes at T/O-1 or T/O RSV: Thrust Rating............................................................AS REQUIRED
Page
1-03-12
Code
6 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
EMERGENCY PROCEDURES
FLIGHT CONTROLS AILERON/ROLL TRIM RUNAWAY Control roll attitude manually with control wheels and rudder. Quick Disconnect Button............................................... PRESS AND HOLD Aileron Systems 1 and 2 ............................................... OFF Roll Trim Circuit Breaker (F22) ..................................... PULL Quick Disconnect Button............................................... RELEASE Airspeed ........................................................................ MAXIMUM 250 KIAS If necessary, turn on one aileron hydraulic system at a time to identify the failed system. Prepare to overcome the roll generated by the failed aileron system. Continue the flight with the failed aileron system off. If the failure is confirmed in one aileron system, the roll trim system may be used as required. Perform a long final approach.
Page
REVISION 6
1-03-14
Code
1 01
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
INADVERTENT SPOILER OPENING IN FLIGHT EICAS CAUTION: SPOILER FAIL (may be presented) LIGHT: Master Caution CONDITION: Sudden airspeed or altitude decrease. Speed Brake..................................................................CLOSE Speed Brake Circuit Breaker (F13) ...............................PULL Ground Spoiler Outboard Circuit Breaker (F14)................................................PULL Ground Spoiler Inboard Circuit Breaker (F20)................................................PULL If any panel is jammed closed, open or is floating: Approach and landing configuration: Landing Gear ......................................................DOWN Flaps ...................................................................22° Airspeed ..............................................................VREF 45 + 10 KIAS Do not reduce engine thrust during flare to avoid abrupt lateral and directional corrections before touchdown. CAUTION: • IN CASE OF PANEL JAMMED CLOSED OR FLOATING, TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.50. • IN CASE OF PANEL JAMMED OPEN, TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.45.
Page
1-03-14
Code
2 01
REVISION 6
AIRPLANE OPERATIONS MANUAL
EMERGENCY PROCEDURES
JAMMED AILERON CONDITION: Both control columns can not be moved to either side. Aileron Disconnect ........................................................ PULL Autopilot ........................................................................ OFF Airspeed ........................................................................ MAXIMUM 200 KIAS NOTE: Roll rate with aileron disconnected is lower than with full system. After control is regained: If the copilot's aileron is operative, roll trim and artificial feel are available. If the pilot's aileron is operative, roll trim and artificial feel are not available. Do not make sudden and large aileron inputs. Do not increase bank angle above 20°. In either case, autopilot must not be reengaged. If both ailerons are jammed, use rudder to control the airplane. Avoid landing at airports with anticipated turbulence or crosswind. Approach and landing configuration: If in icing conditions: Landing Gear ........................................................... DOWN Flaps ........................................................................ 22° Airspeed................................................................... VREF 45 + 15 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45º BY 1.55. If not in icing conditions: Landing Gear ........................................................... DOWN Flaps ........................................................................ 45° Airspeed................................................................... VREF 45 + 5 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45º BY 1.13.
Page
JUNE 20, 2002
1-03-14
Code
3 01
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
JAMMED ELEVATOR EICAS WARNING: SPS 1-2 INOP (may be presented) EICAS CAUTION: STICK PUSHER FAIL LIGHT: Master Warning and Master Caution lights illuminate if STICK PUSHER FAIL and SPS 1-2 INOP messages are presented. CONDITION: Both control columns can not be moved either forward or backward. Elevator Disconnect ......................................................PULL Autopilot.........................................................................OFF Airspeed ........................................................................MAXIMUM 200 KIAS Pitch Trim ......................................................................AS REQUIRED Avoid landing at airports with anticipated turbulence or crosswind. Approach and landing configuration: Landing Gear............................................................DOWN Flaps.........................................................................22° Airspeed ...................................................................VREF 45 + 10 KIAS If both elevators are jammed, pitch trim may be used to land the airplane. If left elevator is jammed, Stick Pusher will not be available. Depending on the jammed elevator position, the remaining elevator power to flare the airplane will be reduced. Do not reengage autopilot. CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.45.
JAMMED RUDDER CONDITION: Pedals can not be moved. Command rudder through yaw trim. If not possible: Rudder System 2......................................................OFF If still jammed: Rudder System 2......................................................ON Rudder System 1......................................................OFF If rudder control through pedals is not restored: Airspeed ...................................................................MAXIMUM 200 KIAS Page
1-03-14
Code
4 01
JUNE 20, 2002
AIRPLANE OPERATIONS MANUAL
EMERGENCY PROCEDURES
Avoid landing at airports with anticipated turbulence or crosswind. Approach and landing configuration: If in icing conditions: Landing Gear ...................................................... DOWN Flaps ................................................................... 22° Airspeed.............................................................. VREF 45 + 15 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.55. If not in icing conditions: Landing Gear ...................................................... DOWN Flaps ................................................................... 45° Airspeed.............................................................. VREF 45 + 5 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.13. If required, use asymmetric thrust to trim the airplane and do not reduce engine thrust during flare in order to avoid abrupt lateral and directional corrections before touchdown. During approach, the pilot not flying must keep the Steering Disengage Button pressed to avoid inadvertent nose wheel deflection once on ground. When the airplane is firmly on ground, use the Steering Handle to control the airplane still keeping the Steering Disengage Button pressed and then reduce the engine thrust to IDLE. If necessary, use differential braking to steer the airplane. NOTE: The Steering handle is effective Steering Disengage Button pressed.
even
with
Page
REVISION 1
1-03-14
the
Code
5 01
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
PITCH TRIM INOPERATIVE EICAS WARNING: PTRIM MAIN INOP, PTRIM BACKUP INOP LIGHT: Master Warning EICAS CAUTION: AUTO TRIM FAIL LIGHT: Master Caution If at least one message is presented without pressing any Pitch Trim Switch: Affected Pitch Trim System......................................OFF Continue the flight with the remaining Pitch Trim System. If both Pitch Trim Systems become inoperative: Pitch Trim Main System ......................................OFF Pitch Trim Back Up System ................................OFF Consider landing at the nearest suitable airport. If message is presented when pressing any Pitch Trim Switch: Airspeed ...................................................................REDUCE Airspeed reduction alleviates control column forces and may permit Pitch Trim command to be recovered. If Pitch Trim command is reestablished continue the flight with the remaining Pitch Trim System. NOTE: - Do not engage the Autopilot if the Main Pitch Trim System is inoperative. - If only one segment of the Pitch Trim Switch is pressed, the TRIM aural warning message will be generated. WARNING: IF PITCH TRIM COMMAND IS NOT REESTABLISHED, DO NOT OPEN SPEEDBRAKE. If pitch trim command is not reestablished and the airplane presents a NOSE UP tendency: Airspeed ...................................................................REDUCE If it is necessary to reduce airspeed below 180 KIAS (or 200 KIAS in icing conditions), extend flaps to 9° (at 20000 ft maximum). If it is necessary to reduce airspeed below 160 KIAS, extend flaps to 22°. NOTE: Turning the airplane and extending the landing gear helps to maintain minimum airspeed with unwanted pitch up tendency. Pitch Trim Command ...............................................CHECK ALL SWITCHES If pitch trim is recovered, retrim the airplane and proceed with flight normally. Page
1-03-14
Code
6 01
REVISION 4
AIRPLANE OPERATIONS MANUAL
EMERGENCY PROCEDURES
If pitch trim is not recovered: Consider landing at the nearest suitable airport. Approach and landing configuration: Landing Gear ................................................. DOWN Flaps .............................................................. 22° Airspeed......................................................... VREF 45 + 10 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.45. If pitch trim command is not reestablished and the airplane presents a NOSE DOWN tendency: Airspeed................................................................... REDUCE Below 250 KIAS: Flaps (at 20000 ft maximum).............................. 9° Below 180 KIAS: Flaps ................................................................... 22° Approach and landing configuration: Landing Gear ...................................................... DOWN NOTE: Gear extension should be delayed as long as possible. Flaps ................................................................... 22° Airspeed.............................................................. VREF 45 + 25 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.75.
Page
JUNE 20, 2002
1-03-14
Code
7 01
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
PITCH TRIM RUNAWAY EICAS WARNING: AUTOPILOT FAIL (may be presented) LIGHT: Master Warning EICAS CAUTION: AUTO TRIM FAIL (may be presented) LIGHT: Master Caution Below V1: Takeoff .....................................................................REJECT Above V1 or in flight: Quick Disconnect Button..........................................PRESS AND HOLD NOTE: Do not change flap setting. At a safe altitude: Pitch Trim Main System ...........................................OFF Pitch Trim Back Up System .....................................OFF Quick Disconnect Button..........................................RELEASE WARNING: DO NOT OPEN THE SPEED BRAKE. If control column forces are excessive, try to recover airplane control by turning one system on and trimming the airplane as necessary. Initiate with the Backup System. Leave the failed system off. Autopilot.........................................................................AS REQUIRED If neither system is operative: PITCH TRIM INOPERATIVE Procedure..................ACCOMPLISH
Page
1-03-14
Code
8 01
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
EMERGENCY PROCEDURES
FUEL AIRPLANE FUEL LOAD EICAS WARNING: CHECK ACFT LOAD or FUEL XFER CRITICAL LIGHT: Master Warning Thrust Levers ................................................................ REDUCE TO LONG RANGE SET Fuselage Transfer System ............................................ CHECK STATUS If fuel transfer from Fuselage Transfer System is observed on MFD Fuel Page proceed with flight normally. NOTE: The EICAS Warning will remain presented while any wing tank quantity is below 1000 kg and total fuselage tanks quantity is above 800 kg. If system is inoperative: Check remaining fuel and consider diversion. Avoid rapid maneuvers and flying in severe turbulence conditions. Before touchdown: Rate of Descent .................................................. MAXIMUM 450 ft/min Touch smoothly the runway surface. Reduce the engine thrust only after the touchdown.
FUEL LOW LEVEL EICAS WARNING: FUEL 1 (2) LO LEVEL LIGHT: Master Warning Thrust Levers ................................................................ REDUCE TO LONG RANGE SET Level the airplane and check both fuel quantities. If fuel quantity is sufficient, complete the flight normally. If fuel quantity is not sufficient, avoid pitch attitudes in excess of 10° nose down or 12° nose up attitude, uncoordinated maneuvers and negative g's. CROSSFEED OPERATION Procedure ........................................................... AS REQUIRED Land at the nearest suitable airport. Page
JANUARY 17, 2003
1-03-16
Code
1 01
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-16
Code
2 01
NOVEMBER 30, 2001
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
HYDRAULICS, LANDING GEAR AND BRAKES LANDING GEAR/LEVER DISAGREE EICAS WARNING: LG/LEVER DISAGREE LIGHT: Master Warning Airspeed ........................................................................ MAXIMUM 200 KIAS Landing Gear ................................................................ CYCLE If the message persists: In a retraction: Landing Gear ...................................................... DOWN Continue flight with landing gear down. Airspeed.............................................................. MAXIMUM 250 KIAS Land at the nearest suitable airport. Leave and avoid icing conditions. In an extension: ABNORMAL LANDING GEAR EXTENSION Procedure ................................ ACCOMPLISH
Page
JANUARY 17, 2003
1-03-18
Code
1 01
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-18
Code
2 01
NOVEMBER 30, 2001
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
ICE AND RAIN PROTECTION, OXYGEN ANTI-ICING CONDITIONS
INOPERATIVE
IN
ICING
EICAS WARNING: ICE COND-A/I INOP with any or all Anti-icing System EICAS CAUTION LIGHT: Master Warning Below V1: TAKEOFF ................................................................ REJECT On the ground, whenever the message is displayed, do not takeoff and perform the test below: Thrust Levers ........................................................... IDLE Ice Detection Override Knob.................................... AUTO Ice Detection Test Knob........................................... 1, THEN 2 Test knob must be held for 5 seconds in each test position. For each side separately, check that OPEN inscriptions in the antiicing buttons flash alternately and that ICE DET 1 (or 2) FAIL caution message and ICE CONDITION advisory message are displayed on the EICAS. If any OPEN inscription does not flash do not takeoff. Report to the maintenance personnel. If the message ICE COND-A/I INOP persists do not takeoff. Report to the maintenance personnel. If the message ICE COND-A/I INOP disappears within 60 seconds: TAKEOFF ........................................................... ACCOMPLISH In flight: Ice Detection Override Knob.................................... ALL If necessary, refer to the specific anti-icing system failure. If the message persists, exit and avoid icing conditions.
Page
REVISION 5
1-03-20
Code
1 01
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-20
Code
2 01
ORIGINAL
AIRPLANE OPERATIONS MANUAL
NAVIGATION, AUTOPILOT
FLIGHT
EMERGENCY PROCEDURES
INSTRUMENTS,
AUTOPILOT FAILURE EICAS WARNING: AUTOPILOT FAIL LIGHT: Master Warning Aural Warning: AUTOPILOT (only below 2500 ft radio altitude, when autopilot is disconnected) Autopilot ........................................................................ DISENGAGE Trim airplane as required. NOTE: If associated with autopilot hardover a sudden deviation from the expected flight path may occur.
Page
JANUARY 17, 2003
1-03-22
Code
1 01
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-22
Code
2 01
NOVEMBER 30, 2001
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
WARNING SYSTEMS STALL PROTECTION INOPERATIVE EICAS WARNING: SPS 1 (2) INOP LIGHT: Master Warning Associated Stall Protection System .............................. OFF Avoid skidding the airplane. If in icing conditions: Add 15 KIAS to go-around speed. Approach and landing configuration: Landing Gear ........................................................... DOWN Flaps ........................................................................ 22° Airspeed................................................................... VREF 45 + 15 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.55. If not in icing conditions: Add 5 KIAS to go-around speed. Approach and landing configuration: Landing Gear ........................................................... DOWN Flaps ........................................................................ 45° Airspeed................................................................... VREF 45 + 5 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.13.
Page
JUNE 20, 2002
1-03-24
Code
1 01
EMERGENCY PROCEDURES
AIRPLANE OPERATIONS MANUAL
STICK PUSHER FAILURE EICAS WARNING: SPS 1-2 INOP LIGHT: Master Warning EICAS CAUTION: STICK PUSHER FAIL LIGHT: Master Caution Control Column .............................................................PUSH FORWARD TO NEUTRAL Stall Protection is not available. Airspeed ........................................................................1.2 VSR MINIMUM
TAKEOFF CONFIGURATION WARNING EICAS WARNING: NO TAKEOFF CONFIG LIGHT: Master Warning Aural Warning: Voice Messages TAKEOFF-BRAKES, TAKEOFFFLAPS, TAKEOFF-SPOILERS TAKEOFF-TRIM or TAKEOFF-FUEL Do not takeoff. Airplane configuration.................................................CORRECT
Page
1-03-24
Code
2 01
JANUARY 17, 2003
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES AIR CONDITIONING, PRESSURIZATION
PNEUMATICS
AND
APU BLEED VALVE FAIL EICAS CAUTION: APU BLD VLV FAIL LIGHT: Master Caution If valve failed closed: Engine Bleed............................................................ AS REQUIRED If valve failed open and a duct leak exists: APU.......................................................................... SHUTDOWN
BLEED LOW TEMPERATURE EICAS CAUTION: BLD 1 (2) LOW TEMP LIGHT: Master Caution If temperature indication on MFD (ECS and Pneumatic Page) is in the green range or the pointer is out of view, disregard the message. Monitor the bleed temperature and report to the maintenance personnel. If the pointer on MFD indicates low temperature (white range): Associated Thrust Lever .......................................... ADVANCE Adjust associated Thrust Lever until the message disappears or until the pointer of the failed side reaches the green range or the remaining pointer. If the message persists or if the MFD is not available: Associated Bleed ..................................................... CLOSE Altitude ..................................................................... MAX 25000 ft MINIMUM MEA WARNING: IF IN ICING CONDITIONS, REFER TO SINGLE ENGINE OR SINGLE BLEED OPERATION IN ICING CONDITIONS PROCEDURE. If the message persists, avoid or exit icing conditions. NOTE: Ice Detection Override Knob must be set to ALL during at least 2 minutes either after exiting icing conditions or after ICE CONDITION advisory message has disappeared.
Page
REVISION 3
1-03-26
Code
1 02
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
BLEED VALVE CLOSED EICAS ADVISORY: BLD 1 (2) VLV CLSD If required and situation permitting: Associated Pack.......................................................OFF THEN ON Associated Bleed......................................................OPEN If it is not possible to open bleed valve: BLEED VALVE FAILURE Procedure .......................ACCOMPLISH
BLEED VALVE FAILURE EICAS CAUTION: BLD VLV 1 (2) FAIL LIGHT: Master Caution If BLD 2 VLV CLSD message is also displayed on the EICAS: Crossbleed ...............................................................OPEN Altitude .....................................................................MAX 25000 ft MINIMUM MEA If BLD 1 VLV CLSD message is also displayed on the EICAS: If APU is not serviceable: Crossbleed ..........................................................OPEN Altitude ................................................................MAX 25000 ft MINIMUM MEA If APU is serviceable: Crossbleed ..........................................................CLOSE APU.....................................................................START APU Bleed...........................................................OPEN Altitude ................................................................MAX 37000 ft MINIMUM MEA WARNING: IF IN ICING CONDITIONS, REFER TO SINGLE ENGINE OR SINGLE BLEED OPERATION IN ICING CONDITIONS PROCEDURE. If BLD 1(2) VLV CLSD message is not displayed on the EICAS: Monitor the system for the remainder of the flight.
Page
1-03-26
Code
2 02
REVISION 5
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
CROSSBLEED FAILURE EICAS CAUTION: CROSS BLD FAIL LIGHT: Master Caution If the valve has failed open, associated to a duct leakage or engine overtemperature: Both Engine Bleeds.................................................. CLOSE APU Bleed................................................................ CLOSE Altitude ..................................................................... MAXIMUM MEA OR 10000 ft Icing conditions ....................................................... EXIT/AVOID
CROSSBLEED SELECTED OFF EICAS CAUTION: CROSSBLD SW OFF LIGHT: Master Caution Crossbleed Knob........................................................... AUTO
ELECTRONIC BAY OVERTEMPERATURE EICAS CAUTION: ELEKBAY OVTEMP LIGHT: Master Caution Turn off the redundant system and equipment unessential for the present phase of flight. The following equipment is installed in the forward electronic compartment: − ADC − Transponder Mode S − Integrated Communication Unit − Aural Warning Computer − FMS − IRS − Passenger Address − Integrated Navigation Unit − Inverters − Dimmers − Backup Battery If the message remains, maintain a cross-check between main and standby instruments. In case a disagreement arises, assume the main instruments indication is unreliable and land at the nearest suitable airport. Page
REVISION 5
1-03-26
Code
3 02
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
HIGH STAGE VALVE FAILURE EICAS CAUTION: HS VLV 1 (2) FAIL Monitor bleed temperature. If the bleed temperature is too high: BLEED OVERTEMPERATURE Procedure............................................................AS REQUIRED If the bleed temperature is too low: BLEED LOW TEMPERATURE Procedure............................................................AS REQUIRED WARNING:
IF IN ICING CONDITIONS, REFER TO SINGLE ENGINE OR SINGLE BLEED OPERATION IN ICING CONDITIONS PROCEDURE.
HIGH ALTITUDE LANDING AND TAKEOFF FUNCTION EICAS CAUTION: HI ALT LDG-T/O NOTE: The use of the High Altitude function is prohibited. If message is displayed: HIGH ALT Button on MFD.............................................PRESS
PACK OVERHEAT EICAS CAUTION: PACK 1 (2) OVHT Associated Temperature & Mode Selector ...................AUTO/FULL COLD Cabin Temperature .......................................................MONITOR Associated Pack............................................................RESET If message remains: Associated Temperature & Mode Selector ...............................................................MANUAL/ FULL COLD Cabin Temperature ..................................................MONITOR Associated Pack.......................................................RESET If the message still remains: Associated Pack.......................................................OFF Altitude .....................................................................MAX 25000 ft MINIMUM MEA
Page
1-03-26
Code
4 02
REVISION 3
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
If both packs have been shutoff: Altitude ..................................................................... MEA OR 10000 ft, WHICHEVER IS HIGHER Pressurization Mode Selector .................................. MAN Pressurization Manual Controller ............................. AS REQUIRED If required: Pressurization Manual Controller........................ FULL UP NOTE: At least one bleed source, engines or APU, must be kept open.
PACK OVERLOAD EICAS CAUTION: PACK 1 (2) OVLD Associated Temperature & Mode Selector ................... 12 O’CLOCK Associated Pack ........................................................... OFF, THEN ON If the message remains on: Associated Pack ...................................................... OFF Altitude ..................................................................... MAX 25000 ft MINIMUM MEA Associated Engine Bleed ......................................... OPEN If both packs have been shutoff: Altitude ..................................................................... MEA OR 10000 ft, WHICHEVER IS HIGHER Pressurization Mode Selector .................................. MAN Pressurization Manual Controller ............................. AS REQUIRED If required: Pressurization Manual Controller........................ FULL UP NOTE: At least one bleed source, engines or APU, must be kept open.
Page
JANUARY 17, 2003
1-03-26
Code
5 02
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
PACK VALVE CLOSED EICAS ADVISORY: PACK 1 (2) VLV CLSD If required and situation permitting: Associated Pack.......................................................OFF, THEN ON If it is not possible to open pack valve: Altitude .....................................................................MAX 25000 ft MINIMUM MEA If both packs are closed: Altitude .....................................................................MEA OR 10000 ft WHICHEVER IS HIGHER
PACK VALVE FAILURE EICAS CAUTION: PACK 1 (2) VLV FAIL If valve failed closed (pack valve closed advisory message is on): Altitude .....................................................................MAX 25000 ft MINIMUM MEA If valve failed open and it is necessary to turn off associated air conditioning system: Crossbleed ...............................................................CLOSE Associated Bleed......................................................CLOSE APU Bleed (if left pack failed) ..................................CLOSE Altitude .....................................................................MAX 25000 ft MINIMUM MEA WARNING: IF IN ICING CONDITIONS, REFER TO SINGLE ENGINE OR SINGLE BLEED OPERATION IN ICING CONDITIONS PROCEDURE. If both packs have been shutoff: Altitude .....................................................................MEA OR 10000 ft, WHICHEVER IS HIGHER Pressurization Mode Selector ..................................MAN Pressurization Manual Controller .............................AS REQUIRED If required: Pressurization Manual Controller ........................FULL UP NOTE: At least one bleed source, engines or APU, must be kept open. Page
1-03-26
Code
6 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
PRESSURIZATION AUTOMATIC SYSTEM FAILURE/ CABIN DEPRESSURIZATION EICAS CAUTION: PRESN AUTO FAIL (may be presented) LIGHT: Master Caution Pressurization Manual Controller .................................. 11 O'CLOCK POSITION Pressurization Mode Selector ....................................... MAN Pressurization Manual Controller .................................. AS REQUIRED If unsuccessful: Altitude ..................................................................... MEA OR 10000 ft, WHICHEVER IS HIGHER Pressurization Manual Controller ............................. FULL DOWN Pressurization Mode Selector .................................. AUTO Pressurization Dump Button .................................... PRESS
RAM AIR VALVE FAILURE EICAS CAUTION: RAM AIR VLV FAIL LIGHT: Master Caution Air Conditioning System ................................................ MONITOR If the PACK 1 (2) OVLD or PACK 1 (2) OVHT caution message appears: Associated Pack ...................................................... OFF Altitude ..................................................................... MAX 25000 ft MINIMUM MEA If both packs have been shutoff: Altitude ..................................................................... MEA OR 10000 ft, WHICHEVER IS HIGHER Pressurization Mode Selector .................................. MAN Pressurization Manual Controller ............................. AS REQUIRED If necessary: Pressurization Manual Controller........................ FULL UP At least one bleed source, engines or APU, must be kept open. Page
REVISION 3
1-03-26
Code
7 02
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
LOSS OF PRESSURIZATION INDICATION AIRPLANES PRE-MOD. SB 145LEG-00-0007 Use the remaining indications to maintain cabin altitude below 10000 ft, according to the table below: AIRPLANE ALTITUDE (ft) 10000 11000 12000 13000 14000 15000 16000 17000 18000 19000 20000 21000 22000 23000 24000 25000 26000 27000 28000 29000 30000 31000 32000 33000 34000 35000 36000 37000 38000 39000
Page
1-03-26
CABIN ALTITUDE (ft) 800 1100 1300 1500 1700 2000 2200 2400 2600 2800 3100 3300 3500 3800 4000 4200 4500 4700 4900 5200 5400 5600 5900 6200 6400 6700 7000 7300 7700 8000
DIFFERENTIAL PRESSURE (psi) 4.2 4.4 4.7 4.9 5.2 5.4 5.6 5.8 6.0 6.2 6.4 6.6 6.7 6.8 7.0 7.1 7.2 7.4 7.5 7.6 7.7 7.8 7.8 7.9 8.0 8.0 8.0 8.1 8.1 8.1
Code
8 02
REVISION 7
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
AIRPLANES POST-MOD. SB 145LEG-00-0007 OR EQUIPPED WITH AN EQUIVALENT MODIFICATION FACTORY INCORPORATED Use the remaining indications to maintain cabin altitude below 10000 ft, according to the table below: AIRPLANE ALTITUDE (ft) 10000 11000 12000 13000 14000 15000 16000 17000 18000 19000 20000 21000 22000 23000 24000 25000 26000 27000 28000 29000 30000 31000 32000 33000 34000 35000 36000 37000 38000 39000 40000 41000
CABIN ALTITUDE (ft) 600 900 1100 1300 1500 1700 1900 2100 2300 2500 2700 3000 3200 3400 3600 3800 4000 4200 4500 4700 4900 5100 5400 5600 5800 6100 6400 6700 7100 7400 7700 8000
DIFFERENTIAL PRESSURE (psi) 4.3 4.5 4.8 5.0 5.3 5.5 5.7 6.0 6.2 6.4 6.6 6.7 6.9 7.0 7.2 7.3 7.5 7.6 7.7 7.8 7.9 8.0 8.1 8.1 8.2 8.2 8.3 8.3 8.3 8.3 8.3 8.4 Page
REVISION 7
1-03-26
Code
9 02
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-26
Code
10 02
REVISION 7
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
AUXILIARY POWER UNIT APU AUTOMATIC SHUTDOWN EICAS CAUTION: APU FAIL LIGHT: Master Caution If shutdown occurs with APU running: Do not try to restart the APU. Report to the maintenance personnel. If shutdown occurs during APU start cycle and provided there is no obvious safety hazard: APU START Procedure ........................................... AS REQUIRED If APU fails to restart, two more APU start attempts may be accomplished. If attempts are unsuccessful, report to the maintenance personnel. NOTE: Refer to APU STARTER LIMITS in AOM Limitations section between start attempts.
APU OIL LOW PRESSURE/OIL HIGH TEMPERATURE EICAS CAUTION: APU OIL LO PRESS or APU OIL HI TEMP LIGHT: Master Caution If the APU is not essential for the flight: APU.......................................................................... SHUTDOWN If APU is essential, monitor APU EGT and RPM. If the APU EGT enters the red or amber range, apply the APU OVERTEMPERATURE Procedure. If RPM enters red range: APU.......................................................................... SHUTDOWN
Page
REVISION 5
1-03-28
Code
1 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-28
Code
2 01
ORIGINAL
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
DOORS AND MISCELLANEOUS BAGGAGE/ACCESS DOOR OPEN EICAS CAUTION: BAGGAGE DOOR OPN or ACCESS DOORS OPN LIGHT: Master Caution Avoid rapid maneuvers. If it is not possible to maintain the pressurization, proceed: Altitude ..................................................................... MEA OR 10000 ft, WHICHEVER IS HIGHER Pressurization .......................................................... MONITOR
BIRD IMPACT Against windshield: CRACKED WINDSHIELD Procedure ...................... APPLY Against leading edge (wing or tail) or fuselage: Maneuverability may be reduced. Refer to the associated leading edge deicer failure procedure, if necessary. At a safe altitude, perform a controllability check step by step up to the landing configuration. Define a safe configuration and VREF for approach and landing. The use of a greater VREF will cause the landing distance to increase. Against engine: PRECAUTIONARY ENGINE SHUTDOWN Procedure (if necessary) .............. APPLY Land at the nearest suitable airport.
Page
REVISION 7
1-03-30
Code
1 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
EMERGENCY EXIT OPEN EICAS CAUTION: EMERG EXIT OPEN LIGHT: Master Caution Fasten Belts ..................................................................ON Verify door handle pushed in and remove passengers from the seats near the associated emergency exit. If emergency exit is not confirmed locked or it is not possible to maintain the pressurization: Altitude .....................................................................MEA OR 10000 ft, WHICHEVER IS HIGHER Cabin Pressure.........................................................MONITOR
IMPAIRED OR CRACKED WINDSHIELD Associated Windshield Heating.....................................OFF If only the outer layer (glass) is cracked, no action is required. If not, proceed as follows: Cockpit Door ............................................................CLOSE Altitude .....................................................................MEA OR BELOW 10000 ft, WHICHEVER IS HIGHER Cabin ∆P = 1 psi.......................................................SET NOTE: Pressurization Manual Controller must be used to reach and maintain cabin altitude steady while descending. Airspeed ...................................................................MAXIMUM 250 KIAS Smoke Goggle .........................................................DON In case both windshields are impaired: Cabin (below 10000 ft) ........................................DEPRESSURIZE Airspeed ..............................................................MAX 140 KIAS MINIMUM VREF Check no loose objects in the cockpit. If necessary: Direct Vision Window.....................................REMOVE Landing must be made by looking through Direct Vision Window. NOTE: Intercommunication will be impossible with window removed. Page
1-03-30
Code
2 01
REVISION 3
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
INTERNAL BAGGAGE ACCESS DOOR OPEN EICAS CAUTION: BAGG ACCESS OPN LIGHT: Master Caution Check doors pictorial on MFD Takeoff Page. If message is confirmed or if MFD is not available: Door .............................................................................. CLOSE AND LOCK
LANDING BELOW -40°C Before touchdown: Rate of descent........................................................ LESS THAN 300 ft/MIN After landing, report to the maintenance personnel.
LIGHTNING STRIKE REPORT In case of lightning strike, report the incident to the maintenance personnel, by filling the LIGHTNING STRIKE INCIDENT REPORT form, part I (see model on the next page). The part II of the LIGHTNING STRIKE INCIDENT REPORT form is reserved to the ground personnel, and is presented in the Aircraft Maintenance Manual.
Page
JANUARY 17, 2003
1-03-30
Code
3 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
EMB-135BJ LIGHTNING STRIKE INCIDENT REPORT Part I (to be completed by flight crew) Conditions at time of strike: • Operator:
Date of incident: Flight no.:
• ACFT S/N: • Route: From • Altitude:
To: Airspeed:
ft
• Flight phase:
Approach
kt
Climb
Level Flight
Other: • Weather: Cloud type % Cover Ceiling (ft) Top at (ft) OAT (°C) Rain
Sleet
Hail
• Was St. Elmo's fire visible before strike?
Snow Yes
None No
• Any effects on: DC power system: Flight controls: Engine: Avionics: Other (describe): • Any effects on personnel, such as: Flash blindness: Electrical shock:
Part I completed by:
Page
1-03-30
Code
4 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
OVERWEIGHT LANDING Approach and landing configuration: If in icing conditions: Landing Gear ........................................................... DOWN Flaps ........................................................................ 22° Airspeed................................................................... VREF 45 + 10 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45º BY 1.45. If not in icing conditions: Landing Gear ........................................................... DOWN Flaps ........................................................................ 45° Airspeed................................................................... VREF 45 CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45º BY 1.06. Before touchdown: Rate of Descent ....................................................... MAXIMUM 300 ft/min Touch smoothly the runway surface. Reduce the engine thrust only after the touchdown. After stopping: Maintenance Personnel ........................................... REPORT
Page
JUNE 20, 2002
1-03-30
Code
5 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
STRUCTURAL DAMAGE On evidence of structural damage: Airspeed under turbulence .......................................BELOW 200 KIAS Load Factor ..............................................................BELOW 2.0 Refer to Buffet Onset Envelope to obtain altitude and airspeed for the desired load factor. Aileron and Rudder Deflection .................................BELOW 30% If fuselage is damaged: Altitude .....................................................................MEA OR BELOW 10000 ft, WHICHEVER IS HIGHER Cabin ........................................................................DEPRESSURIZE When landing: Rate of descent ........................................................LESS THAN 300 ft/MIN
Page
1-03-30
Code
6 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
ELECTRICAL POWER, LIGHTING 115 V AC BUS OFF EICAS CAUTION: 115 VAC BUS OFF LIGHT: Master Caution AC Power ...................................................................... OFF, THEN ON If unsuccessful: AC Power ................................................................. OFF
APU CONTACTOR CLOSED EICAS CAUTION: APU CNTOR CLOSED LIGHT: Master Caution Bus Ties ........................................................................ OFF Battery 2 ........................................................................ OFF
BACK-UP BATTERY OFF BUS EICAS CAUTION: BKUP BATT OFF BUS LIGHT: Master Caution Backup Battery.............................................................. VERIFY ON If message remains, report to the maintenance personnel and no action is required.
BATTERY OFF BUS EICAS CAUTION: BATT 1 (2) OFF BUS LIGHT: Master Caution Affected Battery............................................................. AUTO If message remains, report to the maintenance personnel and no action is required.
Page
JANUARY 17, 2003
1-03-32
Code
1 02
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
DC BUS OFF EICAS CAUTION: DC BUS 1 (2) OFF LIGHT: Master Caution Bus Ties ........................................................................OVERRIDE If associated bus is still off: Bus Ties ...................................................................AUTO Remaining Buses ..........................................................CHECK If DC Bus 2 is off: Airspeed ...................................................................MAXIMUM 250 KIAS NOTE: The nose landing doors will open, therefore the pilot should expect noise increase. Icing Conditions .............................................................EXIT/AVOID
ELECTRICAL EMERGENCY ABNORMAL TRANSFER EICAS CAUTION: ELEC EMERG ABNORM LIGHT: Master Caution Essential Power.............................................................OFF APU Generator ..............................................................ON CAUTION: IF APU GENERATOR IS NOT AVAILABLE OR IF THE MESSAGE REMAINS, BATTERY DURATION WILL BE 40 MINUTES. Land at the nearest suitable airport.
EMERGENCY LIGHTS NOT ARMED EICAS CAUTION: EMERG LT NOT ARMD LIGHT: Master Caution Emergency Lighting Selector ........................................ARM If unsuccessful, check that Attendant Emergency Light Control Button is set to NORM.
ESSENTIAL BUS OFF OR SHED BUS OFF EICAS CAUTION: ESS BUS 1 (2) OFF or SHED BUS 1 (2) OFF Check Essential Buses. If message is confirmed and shed buses or only one essential bus is off, monitor the system for the remainder of the flight. Page
1-03-32
Code
2 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
If both essential buses are off: Bus Ties ................................................................... OFF If DC Bus 1 is energized (PFD 1 and MFD 2 energized): Battery 1.............................................................. OFF If DC Bus 2 is energized (PFD 2 and MFD 1 energized): Battery 2.............................................................. OFF
GENERATOR BEARING FAILURE EICAS ADVISORY: GEN 1 (2, 3, 4) BRG FAIL Report to the maintenance personnel.
GENERATOR OFF BUS EICAS CAUTION: GEN 1 (2, 3, 4) OFF BUS or APU GEN OFF BUS LIGHT: Master Caution Affected Generator ....................................................... OFF, THEN ON If the generator does not reset: APU Generator ........................................................ AS REQUIRED CAUTION: • IF ALL GENERATORS ARE OFF BUS, CABIN WILL DEPRESSURIZE. REFER TO LOSS OF ALL GENERATORS PROCEDURE. • BATTERY DURATION IS 40 MINUTES.
GENERATOR OVERLOAD EICAS CAUTION: GEN 1 (2, 3, 4) OVLD or APU GEN OVLD LIGHT: Master Caution Shed Buses................................................................... OFF If the message remains: Electrical Load (on affected generator).................... REDUCE If APU generator is not affected and any generator is overloaded: APU Generator ........................................................ ON
Page
JANUARY 17, 2003
1-03-32
Code
3 02
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-32
Code
4 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
ENGINE ABNORMAL ENGINE START Either on ground or in flight, abort engine start immediately when: − Fuel flow higher than 365 kph prior to light-up (ITT rise). CAUTION: EXCESSIVE FUEL FLOW GREATER THAN 365 KPH (800 PPH) PRIOR TO LIGHT-UP CAN CAUSE OVERTEMPERATURE, ENGINE DAMAGE OR AN ENGINE FIRE. − No light-up in 10 seconds after the first fuel flow indication. NOTE: The start should not be aborted if fuel flow drops to zero kph (pph) immediately after light-up. − − − − − − −
ITT rises rapidly toward start limit. ITT approaches start limit. N2 remains steady or decreases for more than 5 seconds. Any unusual noise or vibration occurs. Engine instruments indicate abnormal conditions. Visible burning on the exhaust pipe. Oil pressure does not reach at least 34 psi after the engine reaches stabilized idle.
To abort start: Associated Thrust Lever .......................................... IDLE Start/Stop Selector ................................................... STOP If fire occurs or engine does not shutdown: Fire Extinguishing Handle ........................................ PULL ENGINE DRY MOTORING Procedure ......................... ACCOMPLISH
Page
REVISION 7
1-03-34
Code
1 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-34
Code
2 01
REVISION 5
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
CHECK ENGINE PERFORMANCE EICAS ADVISORY: CHECK A1P (A1E) PERF Associated Engine Performance ............................. CHECK
ENGINE ABNORMAL VIBRATION Associated Thrust Lever ............................................... REDUCE TO KEEP VIBRATION WITHIN LIMITS CAUTION: CONTINUOUS VIBRATION DAMAGE THE ENGINE.
ABOVE
LIMITS
MAY
If vibration indication remains out of limits: PRECAUTIONARY ENGINE SHUTDOWN Procedure..................................... ACCOMPLISH
Page
REVISION 7
1-03-34
Code
2A 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
ENGINE AIRSTART Affected engine: One Electric Fuel Pump (A or B)..............................ON Ignition......................................................................AUTO Start/Stop Selector ...................................................STOP Engine Bleed ............................................................CLOSE Thrust Lever .............................................................IDLE Airspeed and Altitude ....................................................REFER TO AIRSTART ENVELOPE Perform an assisted start or windmilling, as required: CAUTION: IN ICING CONDITIONS DO NOT USE APU BLEED START, TO AVOID LOSS OF ANTI-ICE SYSTEM PERFORMANCE. Assisted Start: Crossbleed Start: N2 (operating engine) .........................................ABOVE 80% Crossbleed ..........................................................AUTO OR OPEN Engine Bleed (operating engine).........................OPEN For AE3007A1E engines only: N2 (inoperative engine)..................................BELOW 56% Start/Stop Selector ..............................................START, THEN RUN Engine Indication.................................................MONITOR Check ignition. Check ITT and N2 rising. Observe limits. Abort start immediately if an Abnormal Engine Start is detected. NOTE: For AE3007A1E engines only, if the engine airstart was unsuccessful, reset the FADEC of the inoperative engine and reattempt engine airstart. APU bleed start: APU.....................................................................START APU Bleed...........................................................OPEN Crossbleed ..........................................................AUTO OR OPEN Engine Bleed (operating engine).........................CLOSE For AE3007A1E engines only: N2 (inoperative engine)..................................BELOW 56% Start/Stop Selector ..............................................START, THEN RUN Page
1-03-34
Code
2B 01
REVISION 6
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
Engine Indication.................................................MONITOR Check ignition. Check ITT and N2 rising. Observe limits. Abort start immediately if an Abnormal Engine Start is detected. NOTE: For AE3007A1E engines only, if the engine airstart was unsuccessful, reset the FADEC of the inoperative engine and reattempt engine airstart. Windmilling Start: Airspeed ...................................................................ABOVE 260 KIAS Minimum N2 .............................................................10% For AE3007A1E engines only: N2 (inoperative engine)..................................BELOW 56% Start/Stop Selector ...................................................START, THEN RUN ITT and N2 ...............................................................MONITOR Observe limits. Abort start immediately if an Abnormal Engine Start is detected. NOTE: - Windmilling start will be slower than an assisted start. - For AE3007A1E engines only, if the engine airstart was unsuccessful, reset the FADEC of the inoperative engine and reattempt engine airstart. - Windmilling start with N2 above 30% and increasing, the loss of altitude may be minimized, by reducing airspeed. - Engine windmilling start should be performed while N2 is decreasing down to 10%. With N2 below 10% airstart will not be successful. - Residual ITT above 210°C may result in hot or hung start. - ITT peaks may occur during windmilling starts above 10000 ft with airspeed below 290 knots. In this case, the engine may operate above the ITT limit, up to 850ºC, for a maximum of 5 seconds. Abort the start if the engine remains operating above the ITT limit for more than 5 seconds. After Start: Affected Engine Bleed..............................................AS REQUIRED Crossbleed ...............................................................AUTO APU Bleed................................................................AS REQUIRED
Page
REVISION 6
1-03-34
Code
3 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
ENGINE AIRSTART ENVELOPE AE3007 ENGINES 30000 WINDMILLING START POSSIBLE AND ASSISTED START REGION
25000
ALTITUDE - ft
20000
15000
10000
ONLY ASSISTED START REGION
145CTA57 -25JUL2000
5000
0 0
50
100
150
200
250
300
350
INDICATED AIRSPEED - KIAS
NOTE: Shaded area may be below 1.23 VSR.
Page
1-03-34
Code
4 01
ORIGINAL
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
ENGINE ATS SHUTOFF VALVE OPEN EICAS CAUTION: E1 (2) ATS SOV OPN LIGHT: Master Caution Associated Bleed .......................................................... CLOSE Crossbleed .................................................................... CLOSE Exit and avoid icing conditions. WARNING: IF IN ICING CONDITIONS, REFER TO SINGLE ENGINE OR SINGLE BLEED OPERATION IN ICING CONDITIONS PROCEDURE.
ENGINE CONTROL FAILURE EICAS CAUTION: E1 (2) CTL FAIL (may be presented) CAUTION: DO NOT FADECS.
MANUALLY
ALTERNATE
ASSOCIATED
Verify the associated FADEC in control. Associated FADEC ....................................................... RESET If FADEC alternates automatically: Avoid quick movements of the associated Thrust Lever. NOTE: Thrust Lever movements may cause surge or an uncommanded engine shutdown. If the associated engine thrust is no longer controllable: PRECAUTIONARY ENGINE SHUTDOWN procedure ............................. AS REQUIRED If FADEC does not alternate automatically: Engine control is recovered. Continue the flight.
Page
REVISION 7
1-03-34
Code
5 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
ENGINE DRY MOTORING Dry motor the engine for a minimum of 30 seconds to clear it of unburned fuel prior to attempting another start. FADEC Control Knob ....................................................ALTN Check alternation of FADEC-in-control indication on the EICAS. CAUTION: IF FADEC DOES NOT ALTERNATE, DO NOT PROCEED WITH THE ENGINE DRY MOTORING AND REPORT TO THE MAINTENANCE PERSONNEL.
Ignition ...........................................................................OFF Check IGN OFF indication on EICAS display. Start/Stop Selector ........................................................START After 30 seconds: Start/Stop Selector ...................................................STOP Ignition Selector........................................................AUTO
ENGINE FAILURE Remaining Engine Thrust Rating ..................................CON Altitude...........................................................................MAX 25000 ft MINIMUM MEA ENGINE AIRSTART Procedure ....................................AS REQUIRED WARNING: IF IN ICING CONDITIONS, REFER TO SINGLE ENGINE OR SINGLE BLEED OPERATION IN ICING CONDITIONS PROCEDURE. NOTE: If in flight below 9700 ft, the air conditioning pack valves will close automatically. The APU may be used as pneumatic source by closing the remaining engine bleed valve.
Page
1-03-34
Code
6 01
REVISION 7
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
ENGINE FPMU NOT DISPATCHABLE EICAS CAUTION: E1 (2) FPMU NO DISP Do not Takeoff. Report to the maintenance personnel.
ENGINE FUEL FILTER IMPENDING BYPASS EICAS ADVISORY: E1 (2) FUEL IMP BYP If only one engine fuel filter is affected: Continue the flight and report to the maintenance personnel. If both engine fuel filters are affected: Land at the nearest suitable airport.
Page
REVISION 7
1-03-34
Code
6A 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-34
Code
6B 01
REVISION 5
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
ENGINE LIMITS EXCEEDANCE EICAS CAUTION: E1 (2) EXCEEDANCE LIGHT: Master Caution Do not Takeoff. Report to the maintenance personnel.
ENGINE NO TAKEOFF DATA EICAS CAUTION: ENG NO TO DATA LIGHT: Master Caution Enter takeoff data before takeoff.
ENGINE NOT DISPATCHABLE EICAS CAUTION: E1 (2) NO DISP LIGHT: Master Caution Report to the maintenance personnel.
ENGINE OIL FILTER IMPENDING BYPASS EICAS ADVISORY: E1 (2) OIL IMP BYP Continue the flight and report to the maintenance personnel.
ENGINE OIL HIGH PRESSURE Oil pressure, oil temperature, Oil level, engine vibration ......................................... MONITOR If oil temperature, and/or oil level, and/or engine vibration, exceeds normal operation range: Associated procedure .............................................. ACCOMPLISH Report to the maintenance personnel.
ENGINE OIL HIGH TEMPERATURE Associated Thrust Lever ............................................... REDUCE Reduce thrust lever and maintain the temperature within limits. If oil temperature remains high, above 25000 ft: Altitude ..................................................................... MAX 25000 ft MINIMUM MEA Monitor oil temperature for the remainder of the flight. If limits cannot be maintained, perform a precautionary engine shutdown to prevent engine damage. Page
REVISION 5
1-03-34
Code
7 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
ENGINE OIL LOW LEVEL Monitor oil pressure for the remainder of the flight. Consider performing a precautionary engine shutdown in order to preserve oil quantity so that engine may be restarted prior to landing.
ENGINE OIL LOW PRESSURE If flight conditions permit, reduce N2 below 88%, and monitor oil temperature.
ENGINE OUT EICAS CAUTION: ENG1 (2) OUT LIGHT: Master Caution If during takeoff, below V1: REJECTED TAKEOFF Procedure ...........................ACCOMPLISH If during takeoff, above V1 and associated with an engine flameout: TAKEOFF WITH ENGINE FAILURE Procedure ...........................................ACCOMPLISH If in flight: PRECAUTIONARY ENGINE SHUTDOWN Procedure .....................................ACCOMPLISH ENGINE AIRSTART Procedure ...............................AS REQUIRED
ENGINE OVERTEMPERATURE Associated Thrust Lever................................................REDUCE If the condition remains: Associated Bleed......................................................CLOSE Altitude .....................................................................MAX 25000 ft MINIMUM MEA If the conditions remains: PRECAUTIONARY ENGINE SHUTDOWN or ENGINE FIRE, SEVERE DAMAGE OR SEPARATION Procedure ..............................ACCOMPLISH
ENGINE REFERENCE ANTI-ICE DISAGREE EICAS CAUTION: ENG REF A/I DISAG LIGHT: Master Caution Check ice protection system selection against takeoff data entered. Page
1-03-34
Code
8 01
REVISION 3
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
ENGINE SHORT DISPATCHABLE EICAS ADVISORY: E1 (2) SHORT DISP Report to the maintenance personnel for dispatchability analysis.
ENGINE THRUST REVERSER FAILURE/DISAGREE EICAS CAUTION: ENG1 (2) REV FAIL ENG1 (2) REV DISAGREE LIGHT: Master Caution On ground: During takeoff: Before V1, abort takeoff. During landing: Affected Thrust Lever ......................................... IDLE In flight: N1 ............................................................................ CHECK If N1 is decreasing: Associated Thrust Lever ..................................... IDLE Airspeed.............................................................. MAXIMUM 200 KIAS PRECAUTIONARY ENGINE SHUTDOWN Procedure................................ ACCOMPLISH Land at the nearest suitable airport.
FADEC NOT DISPATCHABLE EICAS CAUTION: FADEC ID NO DISP LIGHT: Master Caution Report to the maintenance personnel.
LOSS OF ENGINE INDICATIONS CONDITION: Loss of Thrust Mode, ITT, N1 and N2 indications. If engine is operative but the indications are lost, proceed: Associated FADEC .................................................. RESET If engine indications are still not available: Associated FADEC ............................................. ALTN If engine indications are still not available: Monitor the remaining engine indications. PRECAUTIONARY ENGINE SHUTDOWN Procedure .......................... AS REQUIRED Page
REVISION 4
1-03-34
Code
9 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
ONE ENGINE INOPERATIVE APPROACH AND LANDING CONDITION: Loss of Thrust Mode, ITT, N1 and N2 indications. Inoperative Engine Thrust Lever ...................................IDLE Landing Gear.................................................................DOWN Thrust Rating.................................................................TAKEOFF MODE When landing is assured: Flaps.........................................................................22° Airspeed ...................................................................VREF 45 + 10 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.44.
ONE ENGINE INOPERATIVE GO-AROUND Quick Disconnect Button ...............................................PRESS Go Around Button..........................................................PRESS Operative Engine Thrust Lever .....................................MAX NOTE: Do not set inoperative engine thrust lever out of idle. Rotate to go-around attitude (10° nose up). Flaps..............................................................................9° With positive rate of climb: Landing Gear............................................................UP Minimum Airspeed ...................................................APPROACH CLIMB SPEED At level off height, proceed as for TAKEOFF WITH ENGINE FAILURE Procedure. NOTE: - Limiting bank angle to 5° towards operative engine improves climb performance. - During the GO-AROUND procedure, the DON´T SINK aural warning may sound. In this case monitor the sink rate and follow the GO-AROUND guidance.
Page
1-03-34
Code
10 01
REVISION 6
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
PRECAUTIONARY ENGINE SHUTDOWN Associated Thrust Lever ............................................... IDLE Associated Start/Stop Selector ..................................... STOP NOTE: Engine will not shutdown with the START/STOP Selector unless associated Thrust Lever is first moved to IDLE. If STOP is selected before Thrust Lever is retarded to IDLE, momentarily cycle START/STOP Selector to RUN and back to STOP. If engine shutdown does not occur: Fire Extinguishing Handle ........................................ PULL (DO NOT ROTATE) Remaining Engine Thrust Rating .................................. CON Verify N2 and ITT decreasing below IDLE values. APU............................................................................... START APU Bleed..................................................................... AS REQUIRED Crossbleed .................................................................... AS REQUIRED WARNING: IF IN ICING CONDITIONS, REFER TO SINGLE ENGINE OR SINGLE BLEED OPERATION IN ICING CONDITIONS PROCEDURE. NOTE: If in flight below 9700 ft, the air conditioning pack valves will close automatically. The APU may be used as pneumatic source by closing the remaining engine bleed valve.
THRUST LEVER FAILURE EICAS CAUTION: ENG1 (2) TLA FAIL LIGHT: Master Caution Associated FADEC ....................................................... RESET If Thrust Lever command is not available: Associated FADEC .................................................. ALTN If thrust lever still does not respond thrust can be partially controlled through the Thrust Rating Buttons. PRECAUTIONARY ENGINE SHUTDOWN Procedure .......................................... AS REQUIRED
Page
JANUARY 17, 2003
1-03-34
Code
11 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THRUST LEVER STOP FAILURE EICAS ADVISORY: E1 (2) IDL STP FAIL Be careful when reducing engines near IDLE. CAUTION: NEVER SET THRUST LEVERS BELOW IDLE INFLIGHT.
Page
1-03-34
Code
12 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
FIRE PROTECTION FIRE DETECTION FAILURE EICAS CAUTION: E1 (2) FIREDET FAIL or APU FIREDET FAIL If E1 (2) FIREDET FAIL message appears simultaneously with engine failure: ENGINE FIRE, SEVERE DAMAGE OR SEPARATION Procedure ............ ACCOMPLISH Engine or APU .............................................................. MONITOR If fire or overheat is suspected: ENGINE FIRE, SEVERE DAMAGE OR SEPARATION or APU FIRE Procedure ..................................... ACCOMPLISH
FIRE EXTINGUISHING INOPERATIVE EICAS CAUTION: E1 (2) EXTBTLA INOP, E1 (2) EXTBTLB INOP, APU EXTBTL INOP or BAGG EXTBTL INOP (if installed) On Engines: Only one discharge will be available from the remaining bottle, to protect both engines against fire. On APU: Consider shutting APU down (or not starting it) if bleed extraction or electrical generation is not essential. On Baggage Compartment: In flight: If associated with the BAGG SMOKE message, land at the nearest suitable airport. On the ground: Report to the maintenance personnel.
Page
REVISION 7
1-03-36
Code
1 02
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-36
Code
2 02
REVISION 7
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
FLIGHT CONTROLS AILERON SYSTEM INOPERATIVE EICAS CAUTION: AIL SYS 1 (2) INOP LIGHT: Master Caution Associated Aileron System ........................................... OFF Airspeed ........................................................................ MAXIMUM 250 KIAS If the remaining system fails: Remaining Aileron System....................................... OFF Quick Disconnect Button.......................................... PRESS Aileron is operating under mechanical reversion mode. Expect greater aileron control force. If required, both pilot should act together to control airplane. Avoid landing at airports with anticipated turbulence or crosswind. Perform a long final approach. Approach and landing configuration: Landing Gear ........................................................... DOWN Flaps ........................................................................ 22° Airspeed................................................................... VREF 45 + 10 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.45.
FLAP LOW ACTUATION SPEED EICAS ADVISORY: FLAP LOW SPEED Anticipate flap actuation.
Page
REVISION 1
1-03-38
Code
1 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
FLAP SYSTEM FAILURE EICAS CAUTION: FLAP FAIL LIGHT: Master Caution Flaps may be at intermediate positions. Maintain airspeed according to the following: FLAPS POSITION 1° to 9° 10° to 22° 23° to 45°
MAXIMUM AIRSPEED 250 KIAS 180 KIAS 145 KIAS
When landing maintain airspeed according to the following: FLAPS POSITION 0 to 8° 9° to 21° 22° to 44° 45°
MINIMUM AIRSPEED VREF 45 + 30 KIAS VREF 45 + 10 KIAS VREF 45 + 5 KIAS VREF 45
CAUTION: • IF FLAP FAILED BETWEEN 22° AND 45° POSITION EXIT OR AVOID ICING CONDITIONS. • TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.70 WHEN LANDING WITH FLAPS BETWEEN ZERO AND 8°. • TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.40 WHEN LANDING WITH FLAPS BETWEEN 9° AND 21°. • TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.20 WHEN LANDING WITH FLAPS BETWEEN 22° AND 44°. NOTE: - Depending on the flap position, EGPWS warnings may sound. If necessary, inhibit EGPWS by pulling its circuit breaker (D2 or J8). - If flap indication on EICAS is not available, use flap position marks on the wing.
Page
1-03-38
Code
2 01
REVISION 7
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
GUST LOCK FAILURE LIGHT: GUST LOCK (amber) On ground: Do not takeoff. Report to the maintenance personnel. In flight: Do not push control column full Nose Down. Avoid flying in turbulence conditions. Consider diversion. Avoid landing at airports with anticipated turbulence or crosswind. Report to the maintenance personnel.
PITCH TRIM SWITCH INOPERATIVE EICAS CAUTION: PTRIM CPT SW FAIL, PTRIM F/O SW FAIL, PTRIM BKP SW FAIL LIGHT: Master Caution On ground: Deenergize the airplane and energize it again. If message remains: Report to the maintenance personnel. In flight: Use another serviceable switch.
RUDDER HARDOVER PROTECTION FAILURE EICAS CAUTION: RUD HDOV PROTFAIL LIGHT: Master Caution On ground: Do not takeoff. In flight: Hardover protection is not available. Report to the maintenance personnel.
Page
REVISION 5
1-03-38
Code
3 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
RUDDER OVERBOOST EICAS CAUTION: RUDDER OVERBOOST LIGHT: Master Caution Rudder System 2...........................................................OFF If the message disappears: Continue flight with rudder system 2 off. Below 135 KIAS: Rudder System 2 ................................................ON If message remains: Rudder System 2......................................................ON Rudder System 1......................................................OFF Continue flight with the rudder system 1 off. Below 135 KIAS: Rudder System 1 ................................................ON
RUDDER SYSTEM INOPERATIVE EICAS CAUTION: RUDDER SYS 1 (2) INOP or RUDDER SYS 1-2 INOP If only one rudder system is affected: Affected Rudder System ..........................................OFF If RUDDER SYS 1-2 INOP message is displayed: Rudder System 2......................................................OFF If RUDDER SYS 1-2 INOP message is still displayed: Rudder System 1 ................................................OFF CAUTION: IF THE MESSAGE IS PRESENTED FOLLOWING A RUDDER RUNAWAY, DO NOT TURN ON THE SYSTEMS. Both Rudder Systems .........................................ON If RUDDER SYS 1-2 INOP message is still displayed: Expect greater rudder pedal force. If required, both pilots should act together to control the airplane. Consider the use of aileron to help in yaw control, and asymmetric thrust to control the airplane. Avoid landing at airports with anticipated turbulence, gusts or crosswind. If landing in icing conditions: Landing Gear..........................................DOWN Flaps.......................................................22° CONTINUES ON NEXT PAGE Page
1-03-38
Code
4 01
REVISION 7
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL CONTINUED FROM PREVIOUS PAGE
Airspeed................................................. VREF 45 + 10 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.45.
RUDDER/YAW TRIM RUNAWAY Quick Disconnect Button............................................... PRESS AND HOLD Rudder Systems 1 and 2............................................... OFF Yaw Trim Circuit Breaker (F12) .................................... PULL Quick Disconnect Button............................................... RELEASE Strongly push pedal opposite to the side of the uncommanded yaw, while applying ailerons to control roll. If necessary, turn on one rudder system at a time to identify the failed system. Prepare to overcome the yaw generated by the failed system. Continue the flight with the failed system off. If both systems remains inoperative: Expect greater rudder pedals force. Both pilots should act together to control the airplane, if required. Consider the use of aileron to help in yaw control, and asymmetric thrust to trim the airplane. Do not use yaw trim system for the remainder of the flight. Avoid landing at airports with anticipated turbulence or crosswind. Land at the nearest suitable airport. CAUTION: DO NOT TRY TO RESET THE RUDDER SYSTEMS.
Page
REVISION 7
1-03-38
Code
5 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
SPEED BRAKE LEVER DISAGREE EICAS CAUTION: SPBK LVR DISAGREE LIGHT: Master Caution Speed Brake Lever........................................................CLOSE
Page
1-03-38
Code
6 01
REVISION 5
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
FUEL APU FUEL LOW PRESSURE EICAS CAUTION: APU FUEL LO PRESS LIGHT: Master Caution Select another right electric fuel pump (2A, 2B or 2C) on the associated tank. If message remains, repeat the procedure. Report to maintenance personnel.
APU FUEL SHUTOFF VALVE CLOSED EICAS ADVISORY: APU FUEL SOV CLSD LIGHT: Master Caution If valve is open and APU is running normally, disregard the message. Report to the maintenance personnel.
APU FUEL SHUTOFF VALVE FAILED EICAS CAUTION: APU FUEL SOV INOP LIGHT: Master Caution Check that APU Fuel Shutoff Button is not pressed. If valve remains closed and it is not possible to restart the APU: APU Master Knob .................................................... OFF If APU is running normally, disregard the message. Report to the maintenance personnel.
ENGINE FUEL SHUTOFF VALVE CLOSED EICAS ADVISORY: E1 (2) FUEL SOV CLSD LIGHT: Master Caution Fire Extinguishing Handle ............................................. CHECK IN If engine is running normally, disregard the message. Report to the maintenance personnel. If valve remains closed and it is not possible to restart the affected engine: PRECAUTIONARY ENGINE SHUTDOWN Procedure..................................... ACCOMPLISH Land at the nearest suitable airport. Page
JANUARY 17, 2003
1-03-40
Code
1 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
ENGINE FUEL SHUTOFF VALVE FAILURE EICAS CAUTION: E1 (2) FUEL SOV INOP LIGHT: Master Caution Engine Fuel Indications .................................................MONITOR If the message has been presented during a fire procedure: Crossfeed.................................................................OFF Associated Fuel Pumps ...........................................OFF If valve is confirmed closed during normal operation (fuel flow decreasing to zero): Fire Extinguishing Handle ........................................CHECK IN If valve remains closed and it is not possible to restart the affected engine, land at the nearest suitable airport. PRECAUTIONARY ENGINE SHUTDOWN Procedure .....................................ACCOMPLISH If engine is running normally, disregard the message.
FUEL CROSSFEED FAILURE EICAS CAUTION: FUEL XFEED FAIL LIGHT: Master Caution Fuel Imbalance..............................................................MONITOR Asymmetric Thrust ........................................................AS REQUIRED
FUEL CROSSFEED MISCOMMAND EICAS CAUTION: FUEL XFEED MISCMD LIGHT: Master Caution Crossfeed Selector Knob ..............................................OFF Fuel Imbalance..............................................................CHECK Crossfeed Selector Knob ..............................................AS REQUIRED Check crossfeed selector knob properly positioned to correct wing fuel imbalance.
FUEL CROSSFEED OPEN EICAS ADVISORY: FUEL XFEED OPEN If not required, close crossfeed.
Page
1-03-40
Code
2 01
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
FUEL LOW PRESSURE EICAS CAUTION: E1 (2) FUEL LO PRESS LIGHT: Master Caution Select another electric fuel pump on the associated tank. If all pumps in one tank are inoperative: Altitude ..................................................................... MAX 25000 ft MINIMUM MEA NOTE: If required, Crossfeed may be open above 25000 ft. Avoid rapid thrust lever movements and set minimum required thrust.
FUEL LOW TEMPERATURE EICAS CAUTION: FUEL TANK LO TEMP or E1 (2) FUEL LO TEMP LIGHT: Master Caution WARNING: IF FUEL TANK LO TEMP MESSAGE IS PRESENTED, IN ANY CASE, OR E1 (2) FUEL LO TEMP IS PRESENTED WITHOUT ICING INHIBITOR, ENGINE FLAMEOUT MAY OCCUR. On ground: Low temperature in the engine (E1 or E2 FUEL LO TEMP): Before takeoff, check that fuel icing inhibitor has been added to the fuel. Low temperature in the tank (FUEL TANK LO TEMP): Check tank temperature. If message is confirmed or if MFD is not available, do not takeoff. In flight: Descend to lower altitude and monitor engine indications as long as the message remains. If the low temperature is in the tank (FUEL TANK LO TEMP) and MFD is available, tank temperature may be checked on the MFD Fuel Page, before descending.
Page
JANUARY 17, 2003
1-03-40
Code
3 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
FUEL TANK VENTILATION VALVE OPEN EICAS CAUTION: FUEL TK VENT OPEN LIGHT: Master Caution On ground: Do not takeoff. In flight: While there is fuel in aft auxiliary fuel tanks: Altitude ................................................................MAX 25000 ft MINIMUM MEA Airspeed ..............................................................MAXIMUM 300 KIAS Avoid pitch attitudes in excess of 5° nose up attitude, uncoordinated maneurvers and negative g's. Report to maintenance personnel.
FUEL TRANSFER SYSTEM CHECK EICAS CAUTION: FUEL XFER CHECK LIGHT: Master Caution Fuselage Tank Transfer Knob.......................................FUS 1 or FUS 2
FUEL TRANSFER SYSTEM INOPERATIVE EICAS CAUTION: FUEL XFER INOP or FUEL XFER 1 (2) INOP LIGHT: Master Caution On ground: Do not takeoff. Report to the maintenance personnel. In flight: Forward Pump Selector Button ................................ALTERNATE If message persists: Altitude ................................................................ABOVE 20000 ft If message persists: Fuselage Tank Transfer Knob ............................ALTERNATE FUS TK Fuel Quantity ............................................................MONITOR Check remaining fuel quantity available and consider diversion.
Page
1-03-40
Code
4 01
JUNE 20, 2002
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
FUSELAGE FUEL IMBALANCE EICAS CAUTION: FUSELAGE FUEL IMB LIGHT: Master Caution If fuselage fuel imbalance is confirmed: Fuselage Tank Transfer Knob ................................. OFF Check MFD Fuel page for auxiliary tanks total quantity. If any left side auxiliary tanks quantity decreases: Fuselage Tank Transfer Knob ............................ FUS 1 If any right side auxiliary tanks quantity decreases: Fuselage Tank Transfer Knob ............................ FUS 2 If auxiliary tanks quantity remains steady: Fuselage Tank Transfer Knob ............................ OFF
REFUELING COMPARTMENT DOOR OPEN EICAS CAUTION: FUELING DOOR OPN LIGHT: Master Caution On ground: Check the door for positive locking before takeoff. If the message remains, repair is required before takeoff. In flight: Report to the maintenance personnel.
Page
JANUARY 17, 2003
1-03-40
Code
5 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
SUSPECTED FUEL LEAK If FMS Fuel Remaining quantity is less than 660 lb above the MFD Total Fuel indication: If left wing presents lower level: Crossfeed Selector ........................................LOW1 If right wing presents lower level: Crossfeed Selector ........................................LOW2 Set engines at the same N1 and compare the Fuel Flow indications. If a discrepancy is noticed and is consistent with the imbalance (high fuel flow X and low level X), a fuel leakage may be occurring after the fuel flow sensor. Consider shutting down the engine on the same side of the presumed fuel leak in order to minimize fuel loss. Land at the nearest suitable airport. If no discrepancy is noticed, when the desired balance is achieved: Crossfeed Selector ........................................OFF Monitor Total Fuel Indication in MFD Fuel Page with FMS Fuel Remaining information. If FMS Fuel Remaining quantity is more than 660 lb above the MFD Total Fuel indication, a fuel leakage may be occurring before the fuel flow sensor. Proceed as follows: Crossfeed Selector..............................................OFF Throttle on Low Level Wing ................................IDLE Affected Engine Fire Handle ...............................PULL (DO NOT ROTATE) Land at the nearest suitable airport.
Page
1-03-40
Code
6 01
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
WING FUEL IMBALANCE EICAS CAUTION: WING FUEL IMBALANCE LIGHT: Master Caution If wing fuel imbalance is confirmed: CROSSFEED OPERATION Procedure ........................................................... ACCOMPLISH
WING TANKS OVERFLOW EICAS CAUTION: FUEL XFER OVERFLOW LIGHT: Master Caution Fuselage Tank Transfer Knob ...................................... OFF When required: Fuselage Tank Transfer Knob ................................. FUS 1 or FUS 2 Wing Fuel Tank Quantity ......................................... MONITOR Monitor wing fuel quantity and turn Fuselage Tank Transfer Knob OFF when wing fuel reaches 2400 kg. Report to the maintenance personnel.
Page
JANUARY 17, 2003
1-03-40
Code
7 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-40
Code
8 01
JANUARY 17, 2003
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
HYDRAULICS, LANDING GEAR & BRAKES ABNORMAL LANDING GEAR EXTENSION Landing Gear Lever ...................................................... DOWN Gear Electrical Override................................................ DOORS Wait 3 seconds: Gear Electrical Override........................................... GEAR Landing Gear Indication........................................... CHECK If any of the gear is not locked down: Landing Gear Lever ................................................. UP Gear Electrical Override........................................... NORMAL Wait 10 seconds. Free Fall Lever ......................................................... ACTUATE Actuate the free fall lever up to full uplock position. Landing Gear Lever ................................................. DOWN Landing Gear Indication........................................... CHECK If the failure persists: Free Fall Lever.................................................... CYCLE Cycle the free fall lever as long as necessary, but limited to 10 times, to lower the landing gear. Wait 20 seconds, with the lever in the uplock position, between each cycle. Verify lever at full uplock position after cycling. If the failure still persists: PARTIAL OR GEAR UP LANDING Procedure ................................ ACCOMPLISH
Page
ORIGINAL
1-03-42
Code
1 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
BOTH HYDRAULIC SYSTEMS FAILURE EICAS CAUTION: HYD SYS 1-2 FAIL, RUDDER SYS 1-2 INOP, AIL SYS 1-2 INOP EICAS ADVISORY: E1-2 HYD PUMP FAIL LIGHT: Master Caution INDICATION: Hydraulic pressure indication on MFD may be amber. Airspeed ........................................................................MAXIMUM 250 KIAS Check hydraulic systems fluid quantity: If any hydraulic system fluid quantity is in green range: Associated Electric Hydraulic Pump ...................ON If any hydraulic system fluid quantity is in amber range: Associated Electric Hydraulic Pump ...................OFF CAUTION: DO NOT OPEN THE SPEED BRAKE. If one system can be recovered, complete the appropriate procedure for one hydraulic system failure. If both systems remain inoperative: Quick Disconnect Button..........................................PRESS Both Electric Hydraulic Pumps .................................OFF NOTE: The nose landing gear doors will open, therefore the pilot should expect noise increase. ABNORMAL LANDING GEAR EXTENSION Procedure......................................ACCOMPLISH Use rudder for directional control on the ground. Rudder and aileron are operating under mechanical reversion mode. Expect greater rudder pedals and control wheels control forces. Both pilots should act together to control the airplane, if required. Pilots should minimize the use of rudder pedals to control lateral oscillations. Ailerons are better suitable to control yaw tendency. Also consider the use of asymmetric thrust to help in yaw control. Land at the nearest suitable airport. Avoid landings at airports with anticipated crosswind or turbulence. Perform a long final approach. Approach and landing configuration: Landing Gear ......................................................DOWN Flaps ...................................................................22° Airspeed ..............................................................VREF 45 + 10 KIAS EMERGENCY BRAKE TECHNIQUE Procedure .....................................ACCOMPLISH Do not attempt to taxi Page
1-03-42
Code
2 01
REVISION 6
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 2.67.
BRAKE DEGRADED EICAS CAUTION: BRAKE DEGRADED LIGHT: Master Caution Apply brakes normally. Brake effectiveness may be reduced and braking asymmetry may be felt. Approach and landing configuration: If in icing conditions: Landing Gear ........................................................... DOWN Flaps ........................................................................ 22° Airspeed................................................................... VREF 45 + 10 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.71. If not in icing conditions: Landing Gear ........................................................... DOWN Flaps ........................................................................ 45° Airspeed................................................................... VREF 45 CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.20. During landing run: Thrust Levers (if available)....................................... REVERSE
Page
REVISION 4
1-03-42
Code
3 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
BRAKES INOPERATIVE EICAS CAUTION: BRK OUTBD (INBD) INOP LIGHT: Master Caution If one pair of brakes is inoperative, apply brakes normally through the pedals. If both pair of brakes are inoperative: EMERGENCY BRAKING TECHNIQUE Procedure .....................................ACCOMPLISH In case of one or both pairs inoperative: If in icing conditions: Landing Gear............................................................DOWN Flaps.........................................................................22° Airspeed ...................................................................VREF 45 + 10 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 2.18. If not in icing conditions: Landing Gear............................................................DOWN Flaps.........................................................................45° Airspeed ...................................................................VREF 45 CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.49. During landing run: Thrust Levers ...........................................................REVERSE
Page
1-03-42
Code
4 01
REVISION 1
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
BRAKES OVERHEAT EICAS CAUTION: BRAKE OVERHEAT LIGHT: Master Caution If during landing and runway length is enough: Brake Pressure ........................................................ REDUCE Use of full reverse thrust is recommended. If after takeoff: Lower landing gear for cooling as soon as possible. Airspeed................................................................... BELOW 200 KIAS Retract gear when brakes temperature is at green range. If MFD is not available, retract gear after message is removed. Airspeed.............................................................. AS REQUIRED When on ground, park the airplane as soon as possible. Before next takeoff: Brakes Temperature ................................................ CHECK AT GREEN RANGE If Brakes Temperature Monitoring System is not available: Quick Turn Around Chart.................................... CHECK Wheel Thermal Plugs ......................................... CHECK NOTE: A positive way to check Wheel Thermal Plugs is to verify that none of tires is flat.
EMERGENCY BRAKING TECHNIQUE Pull the emergency brake handle carefully and continuously until the first airplane reaction. Use the parking brake light as a reference for brake application. Modulate brake application until the airplane achieve the desired deceleration. In case of airplane skidding, release the handle and pull it again as required. NOTE: Anti-skid protection is not available for emergency/parking brake.
Page
JANUARY 17, 2003
1-03-42
Code
5 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
EMERGENCY/PARKING BRAKE HANDLE DISAGREE INDICATION: BRAKE ON light illuminated with Emergency/Parking Brake handle not actuated. Park the airplane as soon as possible. Do not takeoff. Report to the maintenance personnel.
EMERGENCY/PARKING BRAKE LOW PRESSURE EICAS CAUTION: EMRG BRK LO PRES LIGHT: Master Caution If necessary to use the emergency/parking brake, apply it in advance. When parking the airplane, use wheel blocks.
GEAR LEVER CANNOT BE MOVED TO UP AFTER TAKEOFF CONDITION: Landing gear cannot be moved to up position after takeoff in the normal manner. Wait 10 seconds to verify if the LG AIR/GND FAIL message is presented. If the message is presented, do not move Landing Gear Lever. Flight may be continued at pilot’s discretion. If the message is not presented: Downlock Release Button ........................................PRESS Landing Gear Lever..................................................UP Landing Gear Lever will be released, permitting gear retraction.
HYDRAULIC ENGINE PUMP FAILURE EICAS ADVISORY: E1 (2) HYD PUMP FAIL Altitude...........................................................................AT OR BELOW 37000 ft Continue flight monitoring associated hydraulic system. Refer to HYDRAULIC SYSTEM 1 (2) FAILURE Procedure, if necessary.
HYDRAULIC PUMP SELECTED OFF EICAS ADVISORY: HYD PUMP SELEC OF Electric Hydraulic Pumps ..............................................AUTO Page
1-03-42
Code
6 01
JUNE 20, 2002
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
HYDRAULIC SHUTOFF VALVE CLOSED EICAS ADVISORY: E1 (2) HYDSOV CLSD If valve is not intentionally closed: Engine Pump Shutoff Button.................................... CHECK NOT PRESSED If button is not pressed and message persists, report to the maintenance personnel.
HYDRAULIC SYSTEM 1 FAILURE EICAS CAUTION: HYD SYS 1 FAIL, RUDDER SYS 1 INOP or AIL SYS 1 INOP EICAS ADVISORY: E1 HYD PUMP FAIL LIGHT: Master Caution INDICATION: Hydraulic pressure indication on MFD may be amber. Check hydraulic system fluid quantity: If hydraulic system fluid quantity is in green range: Electric Hydraulic Pump 1................................... ON If hydraulic system fluid quantity is in amber range: Electric Hydraulic Pump 1................................... OFF If hydraulic power is not recovered: Airspeed................................................................... MAXIMUM 250 KIAS Electric Hydraulic Pump 1........................................ OFF NOTE: As the nose landing gear doors will open, the pilot should expect a noise increasing during flight. For landing gear extension: ABNORMAL LANDING GEAR EXTENSION Procedure ................................ ACCOMPLISH Do not actuate left Thrust Reverser. Use rudder and differential braking for directional control on ground.
Page
REVISION 6
1-03-42
Code
7 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Approach and landing configuration: If in icing conditions: Landing Gear ......................................................DOWN Flaps ...................................................................22° Airspeed ..............................................................VREF 45 + 10 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 2.38. If not in icing conditions: Landing Gear ......................................................DOWN Flaps ...................................................................45° Airspeed ..............................................................VREF 45 CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.64. NOTE: The following systems will be inoperative: Inboard Spoiler, Outboard Brakes, LH Thrust Reverser, Landing Gear Extension, Steering and Nose Landing Gear Doors Retraction.
Page
1-03-42
Code
8 01
REVISION 6
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
HYDRAULIC SYSTEM 2 FAILURE EICAS CAUTION: HYD SYS 2 FAIL, RUDDER SYS 2 INOP or AIL SYS 2 INOP EICAS ADVISORY: E2 HYD PUMP FAIL LIGHT: Master Caution INDICATION: Hydraulic pressure indication on MFD may be amber. Check hydraulic system fluid quantity: If hydraulic system fluid quantity is in green range: Electric Hydraulic Pump 2................................... ON If hydraulic system fluid quantity is in amber range: Electric Hydraulic Pump 2................................... OFF If hydraulic power is not recovered: Airspeed................................................................... MAXIMUM 250 KIAS Electric Hydraulic Pump 2........................................ OFF Do not actuate right Thrust Reverser. CAUTION: DO NOT OPEN THE SPEED BRAKE. Approach and landing configuration: If in icing conditions: Landing Gear ...................................................... DOWN Flaps ................................................................... 22° Airspeed.............................................................. VREF 45 + 10 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 2.27. If not in icing conditions: Landing Gear ...................................................... DOWN Flaps ................................................................... 45° Airspeed.............................................................. VREF 45 CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.56.
Page
REVISION 6
1-03-42
Code
9 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
NOTE: - The Emergency/Parking Brake will be available only with the accumulator charge. - The following systems will be inoperative: Outboard Spoiler, Inboard Brakes, RH Thrust Reverser, and Emergency/Parking Brake.
HYDRAULIC SYSTEM LOW QUANTITY EICAS ADVISORY: HYD1 (2) LO QTY Continue flight monitoring associated hydraulic system. NOTE: Do not open the Speed Brake if hydraulic system 2 is affected. HYDRAULIC SYSTEM 1 (2) FAILURE Procedure........AS REQUIRED.
HYDRAULIC SYSTEM OVERHEAT EICAS CAUTION: HYD SYS 1 (2) OVHT LIGHT: Master Caution Associated Engine Hydraulic Pump ..............................SHUTOFF Associated Electric Hydraulic Pump..............................OFF Airspeed ........................................................................MAXIMUM 250 KIAS Recover system pressure each 15 minutes or when required, even if message is displayed. Turn off the affected hydraulic system again after 1 minute or when no service is required. Recover system pressure on approach and landing and turn it off when taxiing at low speeds.
Page
1-03-42
Code
10 01
REVISION 6
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
LANDING GEAR AIR/GROUND SYSTEM FAILURE EICAS CAUTION: LG AIR/GND FAIL LIGHT: Master Caution If not in icing conditions: Icing Conditions ....................................................... AVOID Approach and landing configuration: Landing Gear ...................................................... DOWN Flaps ................................................................... 45° Airspeed.............................................................. VREF 45 CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.34. If in icing conditions: Anti-icing system ...................................................... MONITOR If any anti-ice valve does not open or anti-ice failure messages appear, leave and avoid icing conditions. After exiting icing conditions, proceed as follows: Maximum Bank Angle.................................... 30° Minimum Airspeed for Flaps up or 9° ............ 190 KIAS Landing Configuration: Flaps......................................................... 22° Airspeed ................................................... VREF 45 + 10 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.73. Report to the maintenance personnel. NOTE: - Thrust Reversers, and Ground Spoiler, may not be available. Depending on the failed condition, Ground Idle may not be selectable. Refer to the associated abnormal procedures. - If message is presented on ground, one pair of brakes (below 10 kt ground speed) and Steering may not be available. Refer to the associated abnormal procedures.
Page
REVISION 1
1-03-42
Code
11 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
PARTIAL OR GEAR UP LANDING EICAS CAUTION: LG/LEVER DISAGREE LIGHT: Master Caution Burn fuel to reduce touchdown speed. Passengers/crew...........................................................PREPARE FOR EMERGENCY LANDING AND EVACUATION PROCEDURE Prior to approach: Inhibit EGPWS (D2 or J8) and Aural Warning System (B4 and E30) by pulling their circuit breakers. Emergency Lights.....................................................ON Electric Hydraulic Pumps .........................................OFF Engine Bleed ............................................................OFF Pressurization Dump Button.....................................PRESS If in icing conditions: Flaps ...................................................................22° If not in icing conditions: Flaps ...................................................................45° Landing Gear............................................................AS REQUIRED NOTE: The decision to land with all gear up or with any gear extended is left to pilots. The choice of configuration is based on the number of gear available, airplane load distribution, controllability and conditions of the landing field. Landing Briefing.............................................................PERFORM Apply thrust reverser (if installed) at touchdown. Ground spoilers, thrust reverser, steering and normal brakes will not operate if any main gear is up. Rudder is available to maintain runway centerline during initial landing phase. Maintain wings level as long as possible and use brakes and steering (if available) for directional control. After the airplane comes to a complete stop: Start/Stop Selector ...................................................STOP Electric Fuel Pumps .................................................OFF Fire Extinguishing Handles.......................................PULL AND ROTATE EMERGENCY EVACUATION Procedure............................................................ACCOMPLISH Page
1-03-42
Code
12 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
STEERING SYSTEM INOPERATIVE UNCOMMANDED SWERVING ON GROUND
OR
EICAS CAUTION: STEER INOP LIGHT: Master Caution Control the airplane using differential brakes and rudder. Steering Handwheel...................................................... DO NOT USE If unable to control the airplane, as an additional action: Steering Disengagement Button .............................. PRESS Consider the use of differential thrust reverser if serviceable.
Page
REVISION 7
1-03-42
Code
13 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-42
Code
14 01
ORIGINAL
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
ICE & RAIN PROTECTION, OXYGEN ANTI-ICING LOW CAPACITY EICAS WARNING: ICE COND-A/I INOP LIGHT: Master Warning EICAS CAUTION: A/ICE LOW CAPACITY LIGHT: Master Caution Thrust Lever .................................................................. ADVANCE Advance Thrust Lever to at least 55% N1 and wait for 5 seconds. If the message persists and is associated with Wing and/or Stabilizer Anti-Icing Failure messages: Associated System Anti-Icing Procedure................. ACCOMPLISH
ANTI-ICING ON WITHOUT ICING CONDITIONS EICAS CAUTION: NO ICE-A/ICE ON LIGHT: Master Caution Ice Detection Override Knob ......................................... AUTO If the message persists, check the overhead panel and turn off all unnecessary anti-icing system. If the message persists and is associated with Wing or Stabilizer AntiIcing System: Altitude ..................................................................... MAX 25000 ft MINIMUM MEA APU.......................................................................... START APU Bleed................................................................ OPEN Crossbleed............................................................... OPEN Engine Bleeds .......................................................... CLOSE
ANTI-ICING SWITCH OFF EICAS CAUTION: A/ICE SW OFF LIGHT: Master Caution Turn on all anti-icing system buttons.
Page
REVISION 4
1-03-44
Code
1 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
AOA SENSOR HEATING FAILURE EICAS CAUTION: AOA 1 (2) HEAT INOP Maintain airspeed according to the following: FLAPS POSITION UP 9° 22° 45°
MINIMUM AIRSPEED VREF 45 + 20 KIAS VREF 45 + 5 KIAS VREF 22 VREF 45
CLEAR ICE DETECTED EICAS CAUTION: CLR ICE 1 (2) LIGHT: CLR ICE 1 (2) Do not takeoff. Airplane de-icing is required. If there is no clear ice on the wing surface, disregard the message. Report to the maintenance.
CLEAR ICE DETECTION SYSTEM FAILURE EICAS CAUTION: CLR/I INOP 1 (2) Check physically if wing surface is free of clear ice before each flight. If clear ice is found, de-ice the airplane.
Page
1-03-44
Code
2 01
REVISION 4
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
ENGINE ANTI-ICING FAILURE EICAS WARNING: ICE COND-A/I INOP LIGHT: Master Caution EICAS CAUTION: E1 (2) A/ICE FAIL LIGHT: Master Warning Thrust Levers ................................................................ ADVANCE If the message persists: Ice Detection Override Knob.................................... ALL If the message persists: Engine Air Inlet Anti-Icing Button ........................ CYCLE If the message persists: Icing Conditions ............................................. AVOID/EXIT Two minutes after exiting icing conditions: Ice Detection Override Knob .................... AUTO NOTE: Ice Detection Override Knob must be set to ALL for at least 2 minutes either after exiting icing conditions or after ICE CONDITION advisory message has disappeared. In such condition, caution message NO ICE-A/I ON may be presented, and must be disregarded. Engine Vibration............................................................ MONITOR If vibration increases, advance thrust levers, one at a time, to obtain 60% N1 minimum for 5 seconds, and then return to the former setting. If vibration increases to unacceptable values or engine parameters indicate abnormal values, exit icing conditions.
ENGINE ANTI-ICING OVERPRESSURE EICAS ADVISORY: ENG A/ICE OVERPRES Continue the flight and report to the maintenance personnel.
Page
REVISION 4
1-03-44
Code
3 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
ICE DETECTOR FAIL EICAS CAUTION: ICE DET 1 (2) FAIL or ICE DETECTORS FAIL LIGHT: Master Caution Use visual cues (ice accretion on windshield and windshield wipers) and temperature criteria to determine whether icing conditions exist. When flying in icing conditions: Ice Detection Override Knob ....................................ALL After positively exiting icing conditions: Ice Detection Override Knob ....................................AUTO NOTE: - Icing conditions may exist inflight when Total Air Temperature (TAT) is 10°C or below and visible moisture in any form is present (such as clouds, fog with visibility of one mile or less, rain, snow, sleet, and ice crystals). - Ice Detection Override Knob must be kept at ALL for at least 2 minutes either after exiting icing conditions or after ICE CONDITION advisory message has disappeared. In such condition, caution message NO ICE-A/ICE ON may be presented, and must be disregarded.
CREW/PASSENGER OXYGEN LOW PRESSURE EICAS CAUTION: CREW (PAX) OXY LO PRESS LIGHT: Master Caution Check oxygen pressure on the MFD ECS page. If message is confirmed or if MFD is not available: Altitude...........................................................................MEA OR 10000 ft, WHICHEVER IS HIGHER
PITOT SENSORS HEATING FAILURE EICAS CAUTION: PITOT 1 (2, 3) INOP LIGHT: Master Caution Information on the instruments supplied by the affected system may be unreliable. Cross-check and do not use the affected system if a disagreement is found. If the Pitot 3 is the affected one, standby instruments and pressurization system may be affected. If necessary: ADC Button (Reversionary Panel)............................PRESS Page
1-03-44
Code
4 01
REVISION 3
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
SINGLE ENGINE OR SINGLE BLEED OPERATION IN ICING CONDITIONS Crossbleed .................................................................... OPEN Altitude .......................................................................... MEA OR BELOW 15000 ft, WHICHEVER IS HIGHER Above 15000 ft: Anti-icing system performance decreases. If it is not possible to descend below 15000 ft, failure messages may be presented. In this case, exit icing conditions and refer to the appropriate approach and landing procedure. Below 15000 ft: If an anti-icing system failure message is presented, refer to the associated anti-icing system failure procedure.
Page
NOVEMBER 30, 2001
1-03-44
Code
5 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
STABILIZER ANTI-ICING FAILURE EICAS WARNING: ICE COND-A/I INOP EICAS CAUTION: STAB A/ICE FAIL LIGHT: Master Warning and Master Caution Ice Detection Override Knob .........................................ALL Thrust Levers ................................................................ADVANCE If the failure persists: Stabilizer Anti-Icing Button .......................................CYCLE If even so the failure persists: Stabilizer Anti-Icing Button .......................................OFF Avoid or exit icing conditions. After exiting icing conditions: Ice Detection Override Knob ...............................AUTO Maximum Bank Angle ...................................................30° Minimum Airspeed for Flaps up or 9° ...........................................................190 KIAS Landing configuration: Flaps.........................................................................22° Airspeed ...................................................................VREF 45 + 15 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.55. If associated with Wing Anti-Icing System failure and if in icing conditions or if there is any uncertainty as to whether the wing surfaces are clear of ice prior to approach and landing, proceed: Landing configuration: Flaps ...................................................................22° Airspeed ..............................................................VREF 45 + 30 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.85.
Page
1-03-44
Code
6 01
JUNE 20, 2002
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
TAT SENSORS HEATING FAILURE EICAS CAUTION: TAT 1 (2) HEAT INOP LIGHT: Master Caution TAS and SAT indication may be unreliable.
WINDSHIELD HEATING FAILURE EICAS CAUTION: W/S 1 (2) HEAT FAIL LIGHT: Master Caution Associated Windshield Heating .................................... OFF If the message disappears, system may be turned on again after 15 seconds. If message persists: Continue normal flight. NOTE: After landing, prepare for loss of systems supplied by the electrical source associated with the failed windshield heating. For Windshield 2 failure, after landing proceed: Shed Buses......................................................... OFF For Windshield 1 failure, after landing proceed: Bus Ties .............................................................. OFF Generators 1 and 3............................................. OFF If both windshield heatings fail and windshields become impaired, refer to IMPAIRED OR CRACKED WINDSHIELD Procedure.
Page
JUNE 20, 2002
1-03-44
Code
7 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
WING ANTI-ICE ASYMMETRY EICAS WARNING: ICE COND-A/I INOP EICAS CAUTION: WG A/ICE ASYMETRY LIGHT: Master Warning and Master Caution Wing Anti-Icing ..............................................................OFF Maximum Bank Angle ...................................................30° Minimum Airspeed for Flaps up or 9°............................190 KIAS Avoid or exit icing conditions. With Wing Anti-Icing System inoperative in icing conditions or if there is any uncertainty as to whether the wing surfaces are clear of ice prior to approach and landing, proceed: Landing configuration: Flaps ...................................................................22° Airspeed ..............................................................VREF 45 + 30 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.85.
Page
1-03-44
Code
8 01
JUNE 20, 2002
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
WING ANTI-ICING FAILURE EICAS WARNING: ICE COND-A/I INOP EICAS CAUTION: WG A/ICE FAIL LIGHT: Master Warning and Master Caution Ice Detection Override Knob ......................................... ALL Thrust Levers ................................................................ ADVANCE If the failure persists: Wing Anti-Icing Button ............................................. CYCLE If even so the failure persists: Wing Anti-Icing Button ............................................. OFF Avoid or exit icing conditions. After exiting icing conditions: Ice Detection Override Knob............................... AUTO Maximum Bank Angle ................................................... 30° Minimum Airspeed for Flaps up or 9°........................................................... 190 KIAS If in icing conditions or if there is any uncertainty as to whether the wing surfaces are clear of ice prior to approach and landing, proceed: Landing configuration: Flaps ................................................................... 22° Airspeed.............................................................. VREF 45 + 30 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45º BY 1.85.
Page
JUNE 20, 2002
1-03-44
Code
9 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-44
Code
10 01
NOVEMBER 30, 2001
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
NAVIGATION, FLIGHT INSTRUMENTS, AUTOPILOT AILERON OUT OF TRIM EICAS CAUTION: AP AIL MISTRIM LIGHT: Master Caution If the message is displayed more than 10 seconds, proceed: Control Wheel ............................................................... HOLD FIRMLY Quick Disconnect Button............................................... PRESS Roll Trim........................................................................ AS REQUIRED Return the airplane to an in-trim condition, by trimming in the direction as requested by the EICAS indication. Autopilot ........................................................................ AS REQUIRED
AUTOPILOT TRIM FAILED EICAS CAUTION: AUTO TRIM FAIL LIGHT: Master Caution Control Column ............................................................. HOLD FIRMLY Quick Disconnect Button............................................... PRESS Pitch Trim ...................................................................... AS REQUIRED Trim the airplane. Autopilot ........................................................................ AS REQUIRED
CENTRAL MAINTENANCE COMPUTER FAILURE EICAS ADVISORY: CMC FAIL Report to the maintenance personnel.
CHECK IC SOFTWARE EICAS CAUTION: CHECK IC1 (2) SW LIGHT: Master Caution Do not takeoff and report to the maintenance personnel.
DAU AIRPLANE ID MISCOMPARE EICAS CAUTION: DAU AC ID MISCMP LIGHT: Master Caution Do not takeoff. Report to the maintenance personnel.
Page
JANUARY 17, 2003
1-03-46
Code
1 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
DAU FAILURE EICAS CAUTION: DAU 1 (2) A FAIL LIGHT: Master Caution EICAS ADVISORY: DAU 1 (2) (B) FAIL For DAU 1 A FAIL caution message, proceed: DAU 1 Reversion......................................................ON NOTE: The following indications and messages will not be available: - Indications: Engine 1 oil (temperature, pressure and level), Battery 1 temperature, fuel tank temperature, roll trim position, cabin temperature, Bleed 1 temperature. - Messages: BLEED 1 OVTEMP, E1 FUEL LO TEMP, FUEL TANK LO TEMP. For DAU 2 A FAIL caution message, proceed: DAU 2 Reversion......................................................ON NOTE: The following indications and messages will not be available: - Indications: Engine 2 oil (temperature, pressure and level), Battery 2 temperature, Hydraulic quantity 1 and 2, yaw trim position, cockpit temperature, Bleed 2 temperature. - Messages: BLEED 2 OVTEMP, E2 FUEL LO TEMP, HYD 1 LO QTY, HYD 2 LO QTY. If both channels of DAU 1 have failed, the messages and indications associated with the following systems will not be available: - All messages and indications: Oxygen, Steering, Pressurization, Landing Gear, Roll Trim, and the message EMERG LIGHT NOT ARMED. - Some messages and indications: Doors, Stall Protection, Electrical, Fire Protection, Fuel, APU, Power Plant, Thrust Reverser, Flap, Spoiler, Brakes, Air Conditioning, Ice And Rain Protection, Hydraulic. If both channels of DAU 2 have failed, the messages and indications associated with the following systems will not be available: - All messages and indications: Smoke, Hydraulic, Rudder, Yaw Trim. - Some messages and indications: Doors, Stall Protection, Electrical, Fire Protection, Fuel, APU, Power Plant, Thrust Reverser, Flap, Spoiler, Brakes, Air Conditioning, Ice And Rain Protection. For DAU 1 (2) B FAIL advisory message, report to the maintenance personnel. Page
1-03-46
Code
2 01
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
DAU MISCOMPARE EICAS CAUTION: DAU 1-2 ENG MISCOMP or DAU 1-2 SYS MISCOMP or DAU 1-2 WRN MISCOMP LIGHT: Master Caution Associated DAU Reversion........................................... ON NOTE: For each miscompare message and each side, check the following parameters before and after the reversion: - Engine: N1, N2, ITT. - System: Battery voltage and temperature, takeoff temperature, hydraulic pressure, oxygen pressure. - Warning: all warning messages, if any.
DAU REVERSION EICAS ADVISORY: DAU 1 (2) REVERSION If the reversionary condition is not required, press the associated DAU Reversionary Button to remove it.
DISPLAY FAILURE EICAS CAUTION: CHECK PFD 1 (2) message is presented if PFD is the failed display. LIGHT: Master Caution If PFD failed: Associated MFD Selector Knob ............................... PFD If EICAS failed: MFD Selector Knob (as required) ............................ EICAS If all main panel displays failed: Exit or avoid icing conditions. RMU......................................................................... AS REQUIRED Use RMU to access power plant or navigation data. Land at the nearest suitable airport.
DISPLAY FAN FAILURE EICAS ADVISORY: DU 1 (2, 3, 4, 5) FAN FAIL An overheat condition may arise in the associated display. In this case, it will be shut down automatically. Use reversionary capabilities.
Page
JANUARY 17, 2003
1-03-46
Code
3 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
FDAU FAIL EICAS ADVISORY: FDAU FAIL Report to the maintenance personnel for dispatchability analysis.
FD LATERAL MODE FAILURE EICAS CAUTION: LATERAL MODE OFF LIGHT: Master Caution At crew discretion, re-select the affected Flight Director or select the other. NOTE: This message will also be presented if the crew turns the Flight Director off. In this case, the message must be disregarded.
FD VERTICAL MODE FAILURE EICAS CAUTION: VERTICAL MODE OFF LIGHT: Master Caution At crew discretion, re-select the affected Flight Director or select the other. NOTE: This message will also be presented if the crew turns the Flight Director off. In this case, the message must be disregarded.
FLIGHT DATA RECORDER FAILURE EICAS CAUTION: DFDR FAIL LIGHT: Master Caution Report to the maintenance personnel.
IC AIR/GROUND CONDITION SIGNAL INOPERATIVE EICAS CAUTION: IC1 (2) WOW INOP LIGHT: Master Caution Do not take off.
IC CONFIGURATION FAILURE EICAS ADVISORY: IC1 (2) CONFIG FAIL Report to the maintenance personnel for dispatchability analysis.
Page
1-03-46
Code
4 01
JUNE 20, 2002
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
IC FAILURE/IC BUS FAILURE EICAS CAUTION: IC BUS FAIL message may be presented LIGHT: Master Caution The following features will be inoperative: - EICAS messages miscompare monitoring, - Takeoff speeds synchronization, - Check List Display synchronization, and - Flight Director mode synchronization. SG Button (affected side).............................................. PRESS
IC FAN FAILURE EICAS ADVISORY: IC 1 (2) FAN FAIL An overheat condition may arise in the associated IC. In this case, turn the IC off by pulling its respective circuit breaker (C3 or D32).
IC OVERHEAT EICAS CAUTION: IC 1 (2) OVERHEAT LIGHT: Master Caution Turn off the associated IC by pulling its circuit breaker (C3 or D32).
IC’S CONFIGURATION MISMATCH EICAS CAUTION: CHK IC CONFIG LIGHT: Master Caution EICAS ADVISORY: CONFIG MISMATCH Do not take off.
IRS ALIGNMENT EICAS ADVISORY: IRS 1 (2) ALN IRU Mode Select Switch ............................................... CHECK NAV This message is only presented during alignment phase or while the IRU mode select switch is set at ALIGN position.
IRS ALIGNMENT FAULT EICAS CAUTION: IRS 1 (2) ALN FAULT LIGHT: Master Caution Check and reenter present position. If necessary, reenter present position once again.
Page
REVISION 6
1-03-46
Code
5 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
IRS ATTITUDE MODE EICAS ADVISORY: IRS 1 (2) ATT MODE On the ground: IRU Mode Select Switch...........................................OFF Wait until POWER-OFF phase is finished (MSU annunciator lights extinguished). IRU Mode Select Switch...........................................NAV
IRS EXCESSIVE MOTION EICAS ADVISORY: IRS 1 (2) EXC MOTION Make sure the airplane is completely stationary. The IRU will restart a full alignment 30 seconds after the motion is stopped.
Page
1-03-46
Code
6 01
REVISION 1
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
IRS FAIL EICAS CAUTION: IRS 1 (2) FAIL LIGHT: Master Caution During power on or alignment phases: IRU Mode Select Switch .......................................... OFF Wait until POWER-OFF phase is finished (MSU annunciator lights extinguished). IRU Mode Select Switch .......................................... NAV In flight: Reversionary Panel IRS Button ............................... PRESS If cross-side IRU is not available: IRU Mode Select Switch ..................................... ATT Maintain wings level and constant airspeed until IRS 1 (2) ALN message is no longer displayed and attitude is recovered (approximately 20 seconds). Magnetic Heading ............................................... ENTER CAUTION: FOR IRS IN ATTITUDE MODE, NAVIGATION AND ATTITUDE OUTPUTS ARE NOT AS ACCURATE AS IN THE NAV MODE. MAGNETIC HEADING MUST BE ENTERED AND UPDATED PERIODICALLY FROM THE BEST AVAILABLE ALTERNATIVE SOURCE, THROUGH THE FMS CDU. NOTE: The Autopilot is available if the IRS 1 (2) ATT MODE message is displayed and the IRS 1 (2) ALN message is extinguished.
IRS NO MAGNETIC HEADING EICAS ADVISORY: IRS 1 (2) NO MAG HDG This message is presented when IRS is in attitude mode. Enter Magnetic Heading.
IRS NO PRESENT POSITION EICAS ADVISORY: IRS 1 (2) NO PPOS Enter Present Position.
Page
JUNE 20, 2002
1-03-46
Code
7 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
IRS ON BATTERY EICAS ADVISORY: IRS 1 (2) ON BATT Associated IRU will operate for 40 minutes.
IRS OVERHEAT EICAS CAUTION: IRS 1 (2) OVERHEAT Operate affected IRU until completion of the flight. If MSU FAULT annunciator is lighted, IRS 1 (2) FAIL message is presented or inertial data ceases to be transmitted by IRU: Associated IRS Reversionary Button .......................PRESS Affected IRU Mode Select Switch ............................OFF NOTE: The Autopilot is not available. If IRU is OFF, the airplane is near the end of the flight and additional attitude reference is necessary: IRU Mode Select Switch .....................................ATT CAUTION: FOR IRS IN ATTITUDE MODE, NAVIGATION AND ATTITUDE OUTPUTS ARE NOT AS ACCURATE AS IN THE NAV MODE. MAGNETIC HEADING MUST BE ENTERED AND UPDATED PERIODICALLY FROM THE BEST AVAILABLE ALTERNATIVE SOURCE, THROUGH THE FMS CDU.
Page
1-03-46
Code
8 01
NOVEMBER 30, 2001
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
IRS/MSU FAILURE ANNUNCIATION OPERATION PHASE
LIGHT
ALIGN
FAULT
POWER ON
ALIGNMENT
IN FLIGHT
− No light: − Check IRS CB’s. − Set mode select switch to ALIGN or NAV. − Press MSU Test switch. Annunciator bulb must be replaced if the other MSU annunciators do light.
− Flashes immediately after entry: − Check and reenter latitude or longitude. − Reenter same latitude or longitude. − Flashes at the end of alignment: − Enter latitude. − Check and reenter latitude. − Allow additional time for alignment.
− Flashes: − Select the remaining IRU by pressing the IRS Button on the associated reversionary panel. − If necessary set mode select switch to ATT.
−Set mode select
−Associated
− Select the remaining IRU by pressing the IRS Button on the associated reversionary panel. − If necessary set mode select switch to ATT.
switch to OFF for at least 3 sec. Then set mode select switch back to ALIGN or NAV. −If the annunciator remains lighted, call the maintenance personnel.
with ALIGN annunciation: −Recheck coordinates and reenter latitude. −Allow additional time for alignment. −Try new alignment. Set mode select switch to OFF for at least 3 sec, then to ALIGN, and enter present position. −If on ground, call the maintenance personnel.
(Continued)
Page
NOVEMBER 30, 2001
1-03-46
Code
9 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
IRS/MSU FAILURE ANNUNCIATION (Continued) OPERATION PHASE
LIGHT
ON BATT
BATT FAIL
POWER ON −Check IRS CB’s. −If the annunciator
ALIGNMENT
remains lighted, call the maintenance personnel. − Call the maintenance personnel.
*******
−Call
*******
the
maintenance personnel.
NO AIR
*******
IN FLIGHT − The IRU operates on backup DC power and will operate for 30 minutes.
******* − Operate IRU until completion of flight. − If fault annunciator is ON or inertial data ceases to be transmitted by IRU, select the remaining IRU and set mode select switch for affected IRU to OFF. If IRU is OFF, the airplane is near the end of the flight and additional attitude reference is needed, set mode select switch to ATT.
MESSAGE MISCOMPARISON Verify which message is being presented on EICAS. Copilot’s MFD Selector Knob ........................................EICAS Compare the messages displayed on the copilot’s MFD with the ones presented on the EICAS to check which is the discrepant message. Analyze the situation to check whether the discrepant message is spurious or not, and take the appropriate corrective action.
Page
1-03-46
Code
10 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
NAV/FLIGHT INSTRUMENTS FAILURE ANNUNCIATOR/ LOCATION ACTION FAILURE Use cross-side attitude by pressing ATT FAIL (red) the IRS button on associated reversionary panel or use standby attitude indicator. "X" (red) over Use cross-side airspeed by pressing IAS tape the ADC button on associated reversionary panel or use standby airspeed indicator. "X" (red) over Use cross-side altitude by pressing the altitude tape ADC button on associated reversionary panel or use standby altimeter. "X" (red) over PFD Select another sensor. course scale VS (red) Use cross-side vertical speed by pressing the ADC button on associated reversionary panel. Compare data with Standby Indicator. ROL, PIT, ATT, For altitude compare the PFD IAS, or ALT altimeters setting also. If required, use (amber) cross-side data by pressing the appropriate button on associated reversionary panel. RA (amber) Compare both radio altimeter indications. If required, consider only the lower indication. Otherwise, disregard Radio Altitude. RA1 (2) (amber) Radio altimeter automatic reversion has occurred. No action is required. PFD or EICAS Use the MFD Knob to present the Blank or "X"(red) required information on MFD. HDG FAIL (red) Use cross-side heading by pressing the IRS button on associated reversionary panel or use RMU or PFD standby attitude indicator. HDG (amber) MFD Compare data with the Magnetic Compass. After identifying the failed side, use cross-side data by pressing the IRS button on associated reversionary panel. MENU INOP Report to the maintenance personnel. MFD (amber) (Continued) Page
NOVEMBER 30, 2001
1-03-46
Code
11 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
NAV/FLIGHT INSTRUMENTS FAILURE (Continued) ANNUNCIATOR/ LOCATION FAILURE
ATT: CAGE (amber)
ISIS
ATT, ALT, SPD, M, HDG (red)
ACTION Press the CAGE push button in order to recover attitude indication. Caging the ISIS in flight will result in loss of attitude indication for up to 10 seconds and the amber message ATT 10s will be presented during this time. Until attitude indication is available again use the primary indication source. Use the primary indication source. Report to the maintenance personnel.
RADIO ALTIMETER FAIL EICAS ADVISORY: RAD ALT 1 (2) FAIL or RAD ALT FAIL If one Radio altimeter is lost (RAD ALT 1 (2) FAIL is presented): Automatic reversion .................................................CONFIRM Automatic reversion may be confirmed through the RA1 (2) amber annunciator presented on both PFDs.
Page
1-03-46
Code
12 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
STABILIZER OUT OF TRIM EICAS CAUTION: AP ELEV MISTRIM LIGHT: Master Caution Control Column ............................................................. HOLD FIRMLY Quick Disconnect Button............................................... PRESS Pitch Trim ...................................................................... AS REQUIRED Trim the airplane. Autopilot ........................................................................ AS REQUIRED
YAW DAMPER FAILURE EICAS CAUTION: YAW DAMPER FAIL LIGHT: Master Caution Yaw Damper ................................................................. DISENGAGE Autopilot may be reengaged at pilot’s discretion. If after reengagement the failure persists, continue the flight with autopilot disengaged. If flying above Mach 0.7 with Yaw Damper disengaged: Altitude ..................................................................... MAX 35000 ft MINIMUM MEA If flying at or below Mach 0.7 with Yaw Damper disengaged, no altitude restriction is applied.
Page
REVISION 7
1-03-46
Code
13 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-46
Code
14 01
ORIGINAL
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
WARNING SYSTEMS ERRONEOUS STALL PROTECTION ACTUATION Immediately and simultaneously: Quick Disconnect Button............................................... PRESS Both Stall Protection Systems....................................... CUTOUT Avoid skidding the airplane. If in icing conditions: Add 15 KIAS to go-around speed to prevent stall protection from being actuated. Approach and landing configuration: Landing Gear ........................................................... DOWN Flaps ........................................................................ 22° Airspeed................................................................... VREF 45 + 15 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.55. If not in icing conditions: Add 5 KIAS to go-around speed to prevent stall protection from being actuated. Approach and landing configuration: Landing Gear ........................................................... DOWN Flaps ........................................................................ 45° Airspeed................................................................... VREF 45 + 5 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.13.
Page
JANUARY 17, 2003
1-03-48
Code
1 02
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
ADVANCED STALL PROTECTION EICAS CAUTION: SPS ADVANCED LIGHT: Master Caution If altitude is above 25000 ft: Airspeed ...................................................................ABOVE 150 KIAS If in icing conditions: Add 15 KIAS to go-around speed to prevent stall protection from being actuated. Approach and landing configuration: Landing Gear............................................................DOWN Flaps.........................................................................22° Airspeed ...................................................................VREF 45 + 15 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.55. If not in icing conditions: Add 5 KIAS to go-around speed to prevent stall protection from being actuated. Approach and landing configuration: Landing Gear............................................................DOWN Flaps.........................................................................45° Airspeed ...................................................................VREF 45 + 5 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.13.
STICK PUSHER JAMMING EICAS CAUTION: STICK PUSHER FAIL LIGHT: Master Caution Elevator Disconnection Handle .....................................PULL Copilot must fly the airplane. Avoid landings at airports with anticipated turbulence or crosswinds.
Page
1-03-48
Code
2 02
JANUARY 17, 2003
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
EGPWS INOPERATIVE EICAS CAUTION: GPWS INOP or TERRAIN INOP LIGHT: Master Caution Monitor any trend toward terrain contact, excessive sink rate, marginal flight path and airplane configuration.
AURAL WARNING FAILURE EICAS CAUTION: AURAL WARN FAIL LIGHT: Master Caution Monitor airplane instruments.
WINDSHEAR DETECTION INOPERATIVE EICAS CAUTION: WINDSHEAR INOP LIGHT: Master Caution Avoid windshear.
Page
JANUARY 17, 2003
1-03-48
Code
3 02
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-48
Code
4 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROCEDURES
CAT II OPERATION HARDOVER If any unusual acceleration or motion is noticed on the airplane flight path the approach must be discontinued, and: Autopilot ................................................................... DISENGAGE MISSED APPROACH Procedure ............................ PERFORM AS REQUIRED Perform a normal missed approach procedure, unless the approach is continued under VMC and in visual contact with the runway so that the airplane position and attitude assure a safe landing. The possibility of continuing the approach using the flight director for guidance may also be considered.
SLOWOVER The Slowover consists in a smooth and slow airplane attitude change due to an autopilot system malfunction. If a Slowover tendency is confirmed: Autopilot ................................................................... DISENGAGE MISSED APPROACH Procedure ............................ PERFORM AS REQUIRED Perform a normal missed approach procedure, unless the approach is continued under VMC and in visual contact with the runway so that the airplane position and attitude assure a safe landing. The possibility of continuing the approach using the flight director for guidance may also be considered.
ENGINE FAILURE ON FINAL APPROACH OR DURING GO-AROUND ONE ENGINE INOPERATIVE GO-AROUND Procedure ................................. ACCOMPLISH
Page
SEPTEMBER 30, 2002
1-03-49
Code
1 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
AUTOPILOT MALFUNCTION BEFORE REACHING OUTER MARKER If the autopilot disengages or has to be disengaged, transfer autopilot and reengage it. The pilot on-side of the engaged autopilot may continue the approach. Check no failure light illuminated on the PFD and no EICAS message related to the autopilot system. If the autopilot disengages again: MISSED APPROACH Procedure.............................PERFORM AS REQUIRED Perform a normal missed approach procedure, unless the approach is continued under VMC and in visual contact with the runway so that the airplane position and attitude assure a safe landing. The possibility of continuing the approach using the flight director for guidance may also be considered. REACHING OUTER MARKER If the autopilot disengages or has to be disengaged, do not reengage the autopilot. MISSED APPROACH Procedure.............................PERFORM AS REQUIRED Perform a normal missed approach procedure, unless the approach is continued under VMC and in visual contact with the runway so that the airplane position and attitude assure a safe landing. The possibility of continuing the approach using the flight director for guidance may also be considered.
Page
1-03-49
Code
2 01
SEPTEMBER 30, 2002
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL DISPLAY WARNINGS DURING FINAL APPROACH
Discontinue the approach if any of the following warnings occur: • CAT 2 (not displayed or amber) • RAD ALT FAIL (cyan) • RA (red or amber) • GS (red or amber) • LOC (red or amber) • ILS (amber) • ATT FAIL (red) • ATT (amber) • PIT (amber) • ROL (amber) • HDG FAIL (red) • HDG (amber) • FD (red) Perform a normal MISSED APPROACH Procedure, unless the approach is continued under VMC and in visual contact with the runway so that the airplane position and attitude assure a safe landing. EXCESSIVE DEVIATION WARNING If warning occurs above 200 ft Radio Altitude: Monitor the ILS deviation to ensure that the airplane returns to the center beam. If not recovered up to 200 ft radio altitude: Discontinue the approach. If warning occurs below 200 ft Radio Altitude: Discontinue the approach. In both cases, perform a normal MISSED APPROACH Procedure, unless the approach is continued under VMC and in visual contact with the runway so that the airplane position and attitude assure a safe landing.
Page
SEPTEMBER 30, 2002
1-03-49
Code
3 01
ABNORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
ABNORMALITIES The following abnormalities are deviation from CAT ll normal range and must be called out: − Excessive LOC or GS deviations. − Airspeed 10 kt higher or 5 kt lower than the Landing Reference Speed (VREF 22). − Roll angle in excess of 15°. − Pitch angle below - 5° or above 5°. − Rate of descent in excess of 1200 ft/min.
Page
1-03-49
Code
4 01
SEPTEMBER 30, 2002
AIRPLANE OPERATIONS MANUAL
EMERGENCY PROFILES
REVISION 4
Code
1 01
Page
EMERGENCY PROFILES
1-03-60
EMERGENCY PROFILES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-03-60
Code
2 01
REVISION 4
AIRPLANE OPERATIONS MANUAL
ABNORMAL PROFILES
REVISION 4
Code
1 01
Page
ABNORMAL PROFILES
1-03-62
Code
2 01
Page
ABNORMAL PROFILES
1-03-62
AIRPLANE OPERATIONS MANUAL
REVISION 4
REVISION 4
AIRPLANE OPERATIONS MANUAL
Code
3 01
Page
ABNORMAL PROFILES
1-03-62
Code
4 01
Page
ABNORMAL PROFILES
1-03-62
AIRPLANE OPERATIONS MANUAL
REVISION 4
EMERGENCY EVACUATION
AIRPLANE OPERATIONS MANUAL
SECTION 1-11 EMERGENCY EVACUATION TABLE OF CONTENTS Page Block Introduction ................................................................................ 1-11-00 Emergency Evacuation Procedure............................................. 1-11-05 Provisions for Extended Over Water Operations....................... 1-11-10 Doors and Exits.......................................................................... 1-11-40 Emergency Rescue Charts ........................................................ 1-11-45
Page
REVISION 7
1-11-00
Code
1 01
EMERGENCY EVACUATION
AIRPLANE OPERATIONS MANUAL
INTRODUCTION This Section presents information which may be used, at operator discretion, to develop customized evacuation procedures.
Page
1-11-00
Code
2 01
ORIGINAL
AIRPLANE OPERATIONS MANUAL
EMERGENCY EVACUATION
EMERGENCY EVACUATION PROCEDURE CAPTAIN Parking Brake (if necessary) ......................................... APPLY Electric Fuel Pumps ...................................................... OFF Fire Extinguishing Handles ........................................... PULL APU Stop Button ........................................................... PRESS APU and Engine Fire Extinguishing Bottles (if necessary) ............................................... DISCHARGE Cabin Crew ................................................................... NOTIFY Emergency Lighting ...................................................... ON Evacuation .................................................................... INITIATE NOTE: - Cockpit door blow-out panels may be broken to be used as an alternative way to leave cockpit. - In case of the cabin dual pocket door becomes jammed, push or kick at the center until door breaks free and then restow it. - The fwd lavatory bi-fold door must be securely locked to ensure a free pathway. Before leaving the airplane: Batteries ................................................................... OFF FIRST OFFICER Cabin............................................................................. DEPRESSURIZE Tower ............................................................................ NOTIFY
Page
REVISION 4
1-11-05
Code
1 01
EMERGENCY EVACUATION
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-11-05
Code
2 01
ORIGINAL
AIRPLANE OPERATIONS MANUAL
EMERGENCY EVACUATION
PROVISIONS FOR EXTENDED OVER WATER OPERATIONS LH LIFE RAFT CABINET One storage compartment is located just forward of the aft lavatory bulkhead, aft of the forward facing seat. It is designed to accommodate a 12-passenger life raft.
LH LIFE RAFT CABINET
Page
REVISION 7
1-11-10
Code
1 01
EMERGENCY EVACUATION
AIRPLANE OPERATIONS MANUAL
DIVAN LIFE RAFT CABINET One storage compartment for a life raft is located inside the aft divan surround area. It is designed to accommodate a 6-passenger life raft.
DIVAN LIFE RAFT CABINET
Page
1-11-10
Code
2 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
EMERGENCY EVACUATION
LIFE LINE The life line is a rope that aids passengers to keep over the wing while boarding the life raft. It is installed in the upper emergency exit frame and can only be operated with the emergency exit open. The life line can be used with either life raft.
LIFE LINE Page
REVISION 7
1-11-10
Code
3 01
EMERGENCY EVACUATION
AIRPLANE OPERATIONS MANUAL
PROCEDURE AFTER DITCHING – – – – – – – – –
Open the overwing emergency exit; Pull the life line from the emergency exit frame; Engage the life line hook in the specified point on the fuselage; Remove one life raft from the stowage and take it to the emergency exit; Tie the retention rope of the life raft to the seat belt of the seat; nearest to the overwing emergency exit; Take the life raft outside of the airplane; Pull the retention rope to inflate the life raft; Direct passengers to board one at time; After all passengers are onboard, untie or cut the retention rope.
Page
1-11-10
Code
4 01
REVISION 7
EMERGENCY EVACUATION
AIRPLANE OPERATIONS MANUAL
DOORS AND EXITS There is one forward door (main), one over-wing exit and two cockpit windows, one at each side, that can be used for emergency evacuation.
DOORS AND EXITS LOCATION
Page
NOVEMBER 30, 2001
1-11-40
Code
1 01
EMERGENCY EVACUATION
AIRPLANE OPERATIONS MANUAL
MAIN DOOR The main door (airstair type) is located at the fore left side of the fuselage.
AIRSTAIR MAIN DOOR OPERATION (INSIDE CABIN) Page
1-11-40
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
EMERGENCY EVACUATION
AIRSTAIR MAIN DOOR OPERATION (OUTSIDE CABIN)
Page
NOVEMBER 30, 2001
1-11-40
Code
3 01
EMERGENCY EVACUATION
AIRPLANE OPERATIONS MANUAL
EMERGENCY EXIT EMERGENCY OVERWING EXIT One emergency exit hatch exist for passenger evacuation in the event of an emergency. It is located on right side of the aircraft, centered over the right wing.
EMERGENCY EXIT OPERATION (INSIDE CABIN) Page
1-11-40
Code
4 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
EMERGENCY EVACUATION
EMERGENCY EXIT OPERATION (OUTSIDE CABIN) Page
NOVEMBER 30, 2001
1-11-40
Code
5 01
EMERGENCY EVACUATION
AIRPLANE OPERATIONS MANUAL
COCKPIT EVACUATION Cockpit windows may be partially open on the ground, and may be totally removed in case of loss of visibility through the windshield or for cockpit emergency evacuation. If window removal is necessary, facilitate removal by moving the associated pilot seat backward. NOTE: Windows can not be opened from outside. A rope is positioned above each window to assist evacuation.
Page
1-11-40
Code
6 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
EMERGENCY EVACUATION
COCKPIT WINDOW REMOVAL AND EVACUATION PROCEDURE
Page
NOVEMBER 30, 2001
1-11-40
Code
7 01
EMERGENCY EVACUATION
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-11-40
Code
8 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
EMERGENCY EVACUATION
EMERGENCY RESCUE CHARTS The Emergency Rescue Charts present emergency equipment location as well as emergency evacuation schematic. These charts may be used, at operator discretion, to develop customized evacuation procedures.
Page
NOVEMBER 30, 2001
1-11-45
Code
1 01
EMERGENCY EVACUATION
1-11-45
AIRPLANE OPERATIONS MANUAL
NOVEMBER 30, 2001
EMERGENCY RESCUE CHART (1 OF 2)
Code
2 01
Page
AIRPLANE OPERATIONS MANUAL
Code
3 01
Page
EMERGENCY EVACUATION
1-11-45
EMERGENCY RESCUE CHART (2 OF 2)
NOVEMBER 30, 2001
EMERGENCY EVACUATION
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-11-45
Code
4 01
NOVEMBER 30, 2001
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
SECTION 1-10 EMERGENCY INFORMATION TABLE OF CONTENTS Page Block Introduction ................................................................................ 1-10-00 Emergency Equipment............................................................... 1-10-05 Passenger Oxygen Masks Location .......................................... 1-10-08 Passenger Life Jacket................................................................ 1-10-10 Fire Extinguisher ........................................................................ 1-10-15 Emergency Locator Transmitter (ELT) ...................................... 1-10-20 Lighting....................................................................................... 1-10-25 Oxygen....................................................................................... 1-10-25 Navigation and Communication ................................................. 1-10-25
Page
NOVEMBER 30, 2001
1-10-00
Code
1 01
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
INTRODUCTION This Section presents emergency information which may be used, at operator discretion to develop customized emergency procedures. Such procedures may be associated to contingencies not related to the airplane. Emergency equipment includes those items used during in-flight emergencies (such as first-aid kits and fire extinguishers), and to assist in the airplane evacuation (such as crash hatchet and escape ropes). The information presented herein is focused on its technical aspects. Being so, it is not mandatory.
Page
1-10-00
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
EMERGENCY INFORMATION
EMERGENCY EQUIPMENT EMERGENCY EQUIPMENT LOCATION (TYPICAL)
COCKPIT AREA (1 OF 3) Page
NOVEMBER 30, 2001
1-10-05
Code
1 01
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
COCKPIT AREA (2 OF 3) Page
1-10-05
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
EMERGENCY INFORMATION
COCKPIT AREA (3 OF 3) Page
NOVEMBER 30, 2001
1-10-05
Code
3 01
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
FRONT PASSENGER AREA (1 OF 3) Page
1-10-05
Code
4 01
NOVEMBER 30, 2001
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
FRONT PASSENGER AREA (2 OF 3)
Page
NOVEMBER 30, 2001
1-10-05
Code
5 01
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
FRONT PASSENGER AREA (3 OF 3)
Page
1-10-05
Code
6 01
NOVEMBER 30, 2001
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
REAR PASSENGER AREA (1 OF 2)
Page
NOVEMBER 30, 2001
1-10-05
Code
7 01
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
REAR PASSENGER AREA (2 OF 2) Page
1-10-05
Code
8 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
EMERGENCY INFORMATION
EQUIPMENT CHECKLIST COCKPIT AREA Flashlight....................................................................... CHECK RED LIGHT Life Vest ........................................................................ ON BOARD Hatchet.......................................................................... ON BOARD Smoke Goggle .............................................................. ON BOARD Oxygen Mask ................................................................ CHECK Protective Breathing Equipment (PBE) ......................... SEALED Fire Extinguisher ........................................................... CONDITION FRONT PASSENGER CABIN AREA Flashlight....................................................................... CHECK RED LIGHT The red light must be on or blinking. First-Aid Kit.................................................................... CONDITION Water Extinguisher (optional)........................................ CONDITION Protective Breathing Equipment (PBE) ......................... SEALED Fire Extinguisher ........................................................... CONDITION Portable Oxygen Cylinder ............................................. CONDITION Oxygen Box Deploy Tool............................................... ON BOARD Life Vest ........................................................................ ON BOARD
Page
REVISION 7
1-10-05
Code
9 01
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-10-05
Code
10 01
ORIGINAL
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
PASSENGER (TYPICAL)
OXYGEN
MASKS
LOCATION
Page
NOVEMBER 30, 2001
1-10-08
Code
1 01
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-10-08
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
EMERGENCY INFORMATION
PASSENGER LIFE JACKET LIFE JACKET OPERATION
Page
NOVEMBER 30, 2001
1-10-10
Code
1 01
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-10-10
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
EMERGENCY INFORMATION
FIRE EXTINGUISHER HALON FIRE EXTINGUISHER The 1.5 kg (3.3 lb) Halonite fire extinguisher should be used on classes B (oils, greases, flammable liquids) and C (electrical or electronic equipment, live electrical) fire. The 5.5 kg (12 lb) Halonite fire extinguisher should be used on class A (paper, wood, fabric, rubber), B and C fire.
Page
NOVEMBER 30, 2001
1-10-15
Code
1 01
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
FIRE EXTINGUISHER OPERATION
Precautions after fire extinguishing: − Look out for “flashback”; − Ventilate the compartment as promptly as possible.
Page
1-10-15
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
EMERGENCY INFORMATION
EMERGENCY LOCATOR TRANSMITTER (ELT) ELT 110-4 MODEL The ELT 110-4 Model, when activated, transmits a radio signal on frequencies of 121.5 and 243.0 MHz, to facilitate airplane location during search and rescue operations. The system comprises a transmitter with an ON/OFF switch and an impact switch installed in the lavatory right ceiling panel, an antenna located on the top rear and a remote panel located on the cockpit. ELT may be manually or automatically activated. In both cases a red light flashes on the cockpit panel to indicate the ELT activation. Manual activation may be performed when any switch is set to ON position. Automatic activation occurs when the transmitter switch is set to OFF position, the cockpit switch is set to ARM position and the airplane suffers a deceleration greater than 5 g's. In both cases (manual and automatic activation) the pilot may deactivate the ELT, performing the TEST/RESET function.
Page
NOVEMBER 30, 2001
1-10-20
Code
1 01
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
CONTROLS AND INDICATORS REMOTE PANEL 1 - ELT ALERT LIGHT (red) − Flashes when the ELT is transmitting. 2 - ELT SWITCH (guarded) ON ARM -
Activates the ELT. Allows the ELT to be automatically activated.
NOTE: - The TEST/RESET function is provided by pressing ON, waiting 1 second and then pressing ARM. - RESET function allows ELT deactivating, after a manual or automatic activation. - During TEST/RESET function, the ELT alert light flashes to indicate that the system is transmitting.
Page
1-10-20
Code
2 01
NOVEMBER 30, 2001
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
ELT 110-4 MODEL - REMOTE PANEL AND TRANSMITTER LOCATION Page
NOVEMBER 30, 2001
1-10-20
Code
3 01
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-10-20
Code
4 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
EMERGENCY INFORMATION
ELT 96 MODEL The ELT 96 Model, when activated, transmits a radio signal on frequencies of 121.5 MHz, 243.0 MHz and 406.0 MHz, to facilitate airplane location during search and rescue operations. The system comprises a transmitter, which also can be used in a portable mode, and an impact switch installed in the lavatory right ceiling panel, an antenna located on the top rear and a remote panel located on the cockpit. ELT may be manually or automatically activated. In both cases a red light flashes on the cockpit panel to indicate the ELT activation, provided the portable mode is not removed for ground operation. Manual activation may be performed either through the ELT front panel switch or remote switch in cockpit, in both cases setting the switch to MAN position. Automatic activation occurs when the ELT switch and the remote control switch are set to AUTO position and airplane suffers a deceleration as a function of acceleration/time conditions. In both cases (manual and automatic activation) the pilot may deactivate the ELT, performing the AUTO TEST/RESET function. PORTABLE MODE OPERATION To operate the ELT 96 in portable mode, perform the following procedures: − Release the quick-opening fireproof fasteners to remove the ELT from its compartment. − Disconnect the fixed antenna coaxial plug from the ANT connector. − Release the auxiliary antenna from its attaching clips and connect it to the ANT connector. − Set the switch to MAN/RESET position. − Hold or install the ELT vertically, preferably in a cleared area and as high as possible. NOTE: When using in temperatures below freezing, keep ELT inside your jacket with antenna outside for longest operations life.
Page
JUNE 20, 2002
1-10-20
Code
5 01
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
CONTROLS AND INDICATORS REMOTE PANEL 1 - ELT ALERT light (red) − Comes ON when the ELT is transmitting and flashes when a failure is detected during the test procedure. 2 - ELT SWITCH MAN - Activates the ELT manually. AUTO - Allows the ELT to be automatically activated. 3 - AUTO TEST/RESET BUTTON − When pressed allows the ELT to be checked. NOTE: The ELT test must be performed only pressing the AUTO TEST/RESET Button. − During AUTO TEST/RESET function, the ELT alert light illuminates during 2 seconds. − If a failure is detected during the test, the ELT alert light flashes. For confirmation repeat the operation. If the failure persists set the ELT Switch on transmitter panel to OFF position and report to the maintenance personnel. − Reset function allows deactivating the ELT, after a manual or automatic activation. TRANSMITTER PANEL 1 - ELT ALERT LIGHT (red) − Flashes when the ELT is transmitting. 2 - ELT SWITCH MAN/RESET - Activates the ELT. Reset function allows deactivating the ELT after a automatic activation. AUTO - Enables the remote control to automatic operation. OFF - Deactivates de ELT.
Page
1-10-20
Code
6 01
JUNE 20, 2002
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
ELT 96 MODEL - REMOTE AND TRANSMITTER PANEL LOCATIONS Page
JUNE 20, 2002
1-10-20
Code
7 01
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-10-20
Code
8 01
JUNE 20, 2002
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
LIGHTING Refer to AOM - VOLUME 2 - Section 2-6 - LIGHTING.
OXYGEN Refer to AOM - VOLUME 2 - Section 2-16 - OXYGEN.
NAVIGATION AND COMMUNICATION Refer to AOM - VOLUME 2 - Section 2-18 - NAVIGATION AND COMMUNICATION.
Page
NOVEMBER 30, 2001
1-10-25
Code
1 01
EMERGENCY INFORMATION
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-10-25
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
FLIGHT PLANNING
SECTION 1-05 FLIGHT PLANNING TABLE OF CONTENTS Block Page Introduction .........................................................................1-05-00 .. 02 Simplified Flight Planning (*)...............................................1-05-05 .. 01 Cruise - Flight Level Table (*) .............................................1-05-05 .. 16 Cruise - Altitude Capability Table (*)...................................1-05-05 .. 18 APU and Engine Fuel Consumption ...................................1-05-07 .. 01 Climb ..................................................................................1-05-10 .. 01 Cruise..................................................................................1-05-15 .. 01 Descent...............................................................................1-05-20 .. 01 Holding................................................................................1-05-25 .. 01 One Engine Inoperative Performance ................................1-05-30 .. 01 Inflight Diversion (*).............................................................1-05-45 .. 01
NOTE: Items marked with an asterisk (*) may not be present in this manual.
Page
REVISION 6
1-05-00
Code
1 01
FLIGHT PLANNING
AIRPLANE OPERATIONS MANUAL
INTRODUCTION This section presents climb, cruise, descent and holding performance data. In addition, simplified flight planning charts are included. There are four configurations for the flight planning performance data according to the following table: CONFIGURATIONS
AIRPLANE SERIAL NUMBER
CONFIG A
495, 528
CONFIG B
363, 412, 462, 484, 505, 516, 540, 549, 586
CONFIG C
555
CONFIG D
625 and on
Page
1-05-00
Code
2 01
REVISION 6
AIRPLANE OPERATIONS MANUAL
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
SIMPLIFIED FLIGHT PLANNING Simplified flight planning charts allow quick determination of estimated trip fuel and time from brake release to landing. The following phases are included: takeoff, climb, cruise, descent, approach and landing. Charts are provided for Long Range Cruise (LRC), Maximum Speed Cruise (MSC) and for Mach speeds 0.70, 0.72, 0.74, 0.76 and 0.78 at constant altitude. Alternate fuel, holding, reserve fuel and other allowances (APU usage and taxi) should be added to the trip fuel in order to obtain the total fuel required. To determine trip fuel enter trip ground distance, correct for wind condition and estimated landing weight, move as far as the line indicating cruise pressure altitude, and read the trip fuel. To determine trip time, enter trip ground distance, correct for wind condition, move as far as the referring cruise pressure altitude, and read the trip time. For winds greater than those shown, enter in the chart, directly, corrected ground distance, ignore wind correction reference line, to obtain the corrected ground distance, apply the following equation.
TAS CGD = GD × TAS + WIND Where: CGD: Corrected ground distance; GD: Ground distance; Head wind is negative; Tail wind is positive. The alternate fuel is determined by entering the LRC Simplified Flight Planning chart with the alternate distance and wind. The holding fuel is determined from the holding table in this section. Depending upon national regulations, the holding fuel is normally calculated so that the aircraft can hold for 30 min., at 1500 ft above the alternate airport.
Page
REVISION 4
1-05-05
Code
1 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
The reserve fuel is also dependant on national regulations and normally is the fuel required for flying 10% of the trip time (based on the latest fuel flow) or is equivalent to 5% of the trip fuel.
The allowances below may be used: PHASE OF FLIGHT
FUEL CONSUMPTION (lb/min)
TAXI .........................................................................................16.1 APU..........................................................................................2.73
EXAMPLE: Given: DESTINATION AIRPORT Trip Distance ...................................................................... 1400 NM Flight Level ........................................................................ FL 390 Cruise Speed...................................................................... LRC Wind ................................................................................... 30 knots (head wind) Estimated landing weight.................................................... 38000 lb. ALTERNATE AIRPORT Distance ............................................................................ 200 NM Flight Level ......................................................................... FL 200 Speed to alternate airport ................................................... LRC Wind ................................................................................... 0 Estimated landing weight at alternate ................................ 34300 lb. RESERVE FUEL ............................................................... 5% of trip fuel. HOLDING Time ................................................................................... 30 min. Altitude................................................................................ 5000 ft Estimated airplane weight at holding.................................. 33000 lb.
Page
1-05-05
Code
2 08
REVISION 4
AIRPLANE OPERATIONS MANUAL
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
RESULTS From Simplified Flight Planning Chart - Long Range Cruise: Trip Fuel ............................................................................ 7800 lb. From Simplified Flight Planning Chart - Long Range Cruise: Fuel to Alternate................................................................. 1400 lb. Reserve Fuel...................................................................... 390 lb (5% of Trip Fuel). From Holding Tables: Fuel consumption at 5000 ft............................................... 1422 lb/h. For 30 min of holding, fuel ................................................. 711 lb. To determine the TOTAL FUEL ON TAKEOFF, let’s consider 5 minutes for taxi and an APU consumption equal to 110 lb. TOTAL FUEL = TRIP FUEL + FUEL TO ALTERNATE + RESERVE FUEL + HOLDING + APU + TAXI TOTAL FUEL = 7800 + 1400 + 390 + 711 + 110 + 81 TOTAL FUEL = 10492 lb. From Flight Time Chart - Long Range Cruise: TRIP TIME ......................................................................... 230 minutes
Page
REVISION 4
1-05-05
Code
3 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL EMB-135BJ SIMPLIFIED FLIGHT PLANNING TRIP FUEL AE3007A1E ENGINE LONG RANGE CRUISE
LANDING WEIGHT - LB
FL370 FL390
REF. LINE
HEAD
WIND - KT
FL150 FL200 FL250 FL300 FL350 BASED ON: 240/290/M0.60 CLIMB M0.78/310/250 DESCENT
REF. LINE
TAIL
FUEL REQUIRED - LB
ISA CONDITION 15400 15000 14600 14200 13800 13400 13000 12600 12200 11800 11400 11000 10600 10200 9800 9400 9000 8600 8200 7800 7400 7000 6600 6200 5800 5400 5000 4600 4200 3800 3400 3000 2600 2200 1800 1400 1000 600 200 40786 -200 -600 38948 -1000 -1400 37111 -1800 -2200 -2600 35274 -3000 -3400 33436 -3800 31599 -4200 -4600 60 -5000 -5400 -5800 -6200 30 -6600 -7000 -7400 0 -7800 -8200 -8600 -30 -9000 -9400 -60 -9800 -10200 0
200
400
600
800
Page
1-05-05
1000
1200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
TRIP DISTANCE - NM
135BJAOMFAA002 - 05AUG2003
Code
4 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL EMB-135BJ SIMPLIFIED FLIGHT PLANNING TRIP FUEL AE3007A1E ENGINE MAXIMUM SPEED CRUISE
LANDING WEIGHT - LB
FL300 FL350 FL370
FL390
FL250
REF. LINE
HEAD
WIND - KT
FL150 FL200
BASED ON: 240/290/M0.60 CLIMB M0.78/310/250 DESCENT
REF. LINE
TAIL
FUEL REQUIRED - LB
ISA CONDITION 15400 15000 14600 14200 13800 13400 13000 12600 12200 11800 11400 11000 10600 10200 9800 9400 9000 8600 8200 7800 7400 7000 6600 6200 5800 5400 5000 4600 4200 3800 3400 3000 2600 2200 1800 1400 1000 600 200 40786 -200 -600 38948 -1000 -1400 37111 -1800 -2200 -2600 35274 -3000 -3400 33436 -3800 31599 -4200 -4600 60 -5000 -5400 -5800 -6200 30 -6600 -7000 -7400 0 -7800 -8200 -8600 -30 -9000 -9400 -60 -9800 -10200 0
200
135BJAOMFAA003 - 05AUG2003
400
600
800
1000
1200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
TRIP DISTANCE - NM
Page
REVISION 4
1-05-05
Code
5 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL EMB-135BJ SIMPLIFIED FLIGHT PLANNING TRIP FUEL AE3007A1E ENGINE MACH 0.70 CRUISE
LANDING WEIGHT - LB
FL300 FL350 FL370 FL390
REF. LINE
HEAD
WIND - KT
FL250 BASED ON: 240/290/M0.60 CLIMB M0.78/310/250 DESCENT
REF. LINE
TAIL
FUEL REQUIRED - LB
ISA CONDITION 15400 15000 14600 14200 13800 13400 13000 12600 12200 11800 11400 11000 10600 10200 9800 9400 9000 8600 8200 7800 7400 7000 6600 6200 5800 5400 5000 4600 4200 3800 3400 3000 2600 2200 1800 1400 1000 600 200 40786 -200 -600 38948 -1000 -1400 37111 -1800 -2200 -2600 35274 -3000 -3400 33436 -3800 31599 -4200 -4600 60 -5000 -5400 -5800 -6200 30 -6600 -7000 -7400 0 -7800 -8200 -8600 -30 -9000 -9400 -60 -9800 -10200 0
200
400
600
800
Page
1-05-05
1000
1200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
TRIP DISTANCE - NM
135BJAOMFAA004 - 05AUG2003
Code
6 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL EMB-135BJ SIMPLIFIED FLIGHT PLANNING TRIP FUEL AE3007A1E ENGINE MACH 0.72 CRUISE
LANDING WEIGHT - LB
FL300
FL350 FL370 FL390
REF. LINE
HEAD
WIND - KT
FL250 BASED ON: 240/290/M0.60 CLIMB M0.78/310/250 DESCENT
REF. LINE
TAIL
FUEL REQUIRED - LB
ISA CONDITION 15400 15000 14600 14200 13800 13400 13000 12600 12200 11800 11400 11000 10600 10200 9800 9400 9000 8600 8200 7800 7400 7000 6600 6200 5800 5400 5000 4600 4200 3800 3400 3000 2600 2200 1800 1400 1000 600 200 40786 -200 -600 38948 -1000 -1400 37111 -1800 -2200 -2600 35274 -3000 -3400 33436 -3800 31599 -4200 -4600 60 -5000 -5400 -5800 -6200 30 -6600 -7000 -7400 0 -7800 -8200 -8600 -30 -9000 -9400 -60 -9800 -10200 0
200
135BJAOMFAA005 - 05AUG2003
400
600
800
1000
1200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
TRIP DISTANCE - NM
Page
REVISION 4
1-05-05
Code
7 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL EMB-135BJ SIMPLIFIED FLIGHT PLANNING TRIP FUEL AE3007A1E ENGINE MACH 0.74 CRUISE
LANDING WEIGHT - LB
FL300
FL350 FL370 FL390
REF. LINE
HEAD
WIND - KT
FL250 BASED ON: 240/290/M0.60 CLIMB M0.78/310/250 DESCENT
REF. LINE
TAIL
FUEL REQUIRED - LB
ISA CONDITION 15400 15000 14600 14200 13800 13400 13000 12600 12200 11800 11400 11000 10600 10200 9800 9400 9000 8600 8200 7800 7400 7000 6600 6200 5800 5400 5000 4600 4200 3800 3400 3000 2600 2200 1800 1400 1000 600 200 40786 -200 -600 38948 -1000 -1400 37111 -1800 -2200 -2600 35274 -3000 -3400 33436 -3800 31599 -4200 -4600 60 -5000 -5400 -5800 -6200 30 -6600 -7000 -7400 0 -7800 -8200 -8600 -30 -9000 -9400 -60 -9800 -10200 0
200
400
600
800
Page
1-05-05
1000
1200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
TRIP DISTANCE - NM
135BJAOMFAA006 - 05AUG2003
Code
8 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL EMB-135BJ SIMPLIFIED FLIGHT PLANNING TRIP FUEL AE3007A1E ENGINE MACH 0.76 CRUISE
LANDING WEIGHT - LB
FL350 FL370
FL390
REF. LINE
HEAD
WIND - KT
FL300 BASED ON: 240/290/M0.60 CLIMB M0.78/310/250 DESCENT
REF. LINE
TAIL
FUEL REQUIRED - LB
ISA CONDITION 15400 15000 14600 14200 13800 13400 13000 12600 12200 11800 11400 11000 10600 10200 9800 9400 9000 8600 8200 7800 7400 7000 6600 6200 5800 5400 5000 4600 4200 3800 3400 3000 2600 2200 1800 1400 1000 600 200 40786 -200 -600 38948 -1000 -1400 37111 -1800 -2200 -2600 35274 -3000 -3400 33436 -3800 31599 -4200 -4600 60 -5000 -5400 -5800 -6200 30 -6600 -7000 -7400 0 -7800 -8200 -8600 -30 -9000 -9400 -60 -9800 -10200 0
200
135BJAOMFAA007 - 05AUG2003
400
600
800
1000
1200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
TRIP DISTANCE - NM
Page
REVISION 4
1-05-05
Code
9 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL EMB-135BJ SIMPLIFIED FLIGHT PLANNING TRIP FUEL AE3007A1E ENGINE MACH 0.78 CRUISE
LANDING WEIGHT - LB
FL300
FL390
REF. LINE
HEAD
WIND - KT
FL350 FL370 BASED ON: 240/290/M0.60 CLIMB M0.78/310/250 DESCENT
REF. LINE
TAIL
FUEL REQUIRED - LB
ISA CONDITION 15400 15000 14600 14200 13800 13400 13000 12600 12200 11800 11400 11000 10600 10200 9800 9400 9000 8600 8200 7800 7400 7000 6600 6200 5800 5400 5000 4600 4200 3800 3400 3000 2600 2200 1800 1400 1000 600 200 40786 -200 -600 38948 -1000 -1400 37111 -1800 -2200 -2600 35274 -3000 -3400 33436 -3800 31599 -4200 -4600 60 -5000 -5400 -5800 -6200 30 -6600 -7000 -7400 0 -7800 -8200 -8600 -30 -9000 -9400 -60 -9800 -10200 0
200
400
600
800
Page
1-05-05
1000
1200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
TRIP DISTANCE - NM
135BJAOMFAA008 - 05AUG2003
Code
10 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL EMB-135BJ SIMPLIFIED FLIGHT PLANNING TRIP TIME AE3007A1E ENGINE LONG RANGE CRUISE ISA CONDITION 480 460 440
FL200
BASED ON: 240/290/M0.60 CLIMB M0.78/310/250 DESCENT
420 400
FL250
FL150
FL300 FL350 FL370 FL390
380 360 340
FLIGHT TIME - MIN
320 300 280 260 240 220 200 180 160 140 120 100 80 60 40 20
WIND - KT LANDING WEIGHT - LB HEAD
0 -20
40785 -40 38948 -60 37111 -80 35274 -100
REF. LINE
33436 -120 31599 -140 -160 60 -180 -200 30 -220 -240 -2600
REF. LINE
-280
TAIL
-30 -300 -320 -60 -340 -360 0
200
400
600
800
1000
1200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
TRIP DISTANCE - NM 135BJAOMFAA009 - 05AUG2003
Page
REVISION 4
1-05-05
Code
11 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL EMB-135BJ SIMPLIFIED FLIGHT PLANNING TRIP TIME AE3007A1E ENGINE MAXIMUM SPEED CRUISE
ISA CONDITION 400
FL390
380 360
BASED ON: 240/290/M0.60 CLIMB M0.78/310/250 DESCENT
340 320
FL250, FL300, FL350 & FL370
300 280
FL150 FL200
FLIGHT TIME - MIN
260 240 220 200 180 160 140 120 100 80 60 40 20
LANDING WEIGHT - LB
0 -20 40785 -40 38948 -60 37111 -80 35274 -100
REF. LINE
33436 -120 31599 -140 -160
HEAD
60 -180 -200
WIND - KT
30 -220 -240 -2600
REF. LINE
-280
TAIL
-30 -300 -320 -60 -340 -360 0
200
400
600
800
1000
1200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
TRIP DISTANCE - NM 135BJAOMFAA010 - 05AUG2003
Page
1-05-05
Code
12 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL EMB-135BJ SIMPLIFIED FLIGHT PLANNING TRIP TIME AE3007A1E ENGINE MACH 0.70 CRUISE ISA CONDITION 460
FL370 & FL390
440 420 BASED ON: 240/290/M0.60 CLIMB M0.78/310/250 DESCENT
400 380
FL350
360
FL300
340
FLIGHT TIME - MIN
320
FL250
300 280 260 240 220 200 180 160 140 120 100 80 60 40 20
LANDING WEIGHT - LB
0 -20 40785 -40 38948 -60 37111 -80 35274 -100
REF. LINE
33436 -120 31599 -140 -160
HEAD
60 -180
WIND - KT
-200 30 -220 -240 0 -260
REF. LINE
-280
TAIL
-30 -300 -320 -60 -340 -360 0
200
400
600
800
1000
1200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
TRIP DISTANCE - NM 135BJAOMFAA011 - 05AUG2003
Page
REVISION 4
1-05-05
Code
13 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL EMB-135BJ SIMPLIFIED FLIGHT PLANNING TRIP TIME AE3007A1E ENGINE MACH 0.72 CRUISE
ISA CONDITION 460 440
FL370 & FL390
420 BASED ON: 240/290/M0.60 CLIMB M0.78/310/250 DESCENT
400 380
FL350
360
FL300
340
FLIGHT TIME - MIN
320 300 280
FL250
260 240 220 200 180 160 140 120 100 80 60 40 20
LANDING WEIGHT - LB
0 -20 40785 -40 38948 -60 37111 -80 35274 -100
REF. LINE
33436 -120 31599 -140 -160
HEAD
60 -180
WIND - KT
-200 30 -220 -240 -2600
REF. LINE
-280
TAIL
-30 -300 -320 -60 -340 -360 0
200
400
600
800
1000
1200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
TRIP DISTANCE - NM 135BJAOMFAA012 - 05AUG2003
Page
1-05-05
Code
14 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL EMB-135BJ SIMPLIFIED FLIGHT PLANNING TRIP TIME AE3007A1E ENGINE MACH 0.74 CRUISE ISA CONDITION 440 420
FL370 & FL390
400
BASED ON: 240/290/M0.60 CLIMB M0.78/310/250 DESCENT
380 360
FL350
340 320
FL300
FLIGHT TIME - MIN
300 280
FL250
260 240 220 200 180 160 140 120 100 80 60 40 20
LANDING WEIGHT - LB
0 -20 40785 -40 38948 -60 37111 -80 35274 -100
REF. LINE
33436 -120 31599 -140 -160
HEAD
60 -180
WIND - KT
-200 30 -220 -240 -2600
REF. LINE
-280
TAIL
-30 -300 -320 -60 -340 -360 0
200
400
600
800
1000
1200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
TRIP DISTANCE - NM 135BJAOMFAA013 - 05AUG2003
Page
REVISION 4
1-05-05
Code
15 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL EMB-135BJ SIMPLIFIED FLIGHT PLANNING TRIP TIME AE3007A1E ENGINE MACH 0.76 CRUISE
ISA CONDITION 420 400
FL370 & FL390
380
BASED ON: 240/290/M0.60 CLIMB M0.78/310/250 DESCENT
360 340
FL350
320 300
FL300
FLIGHT TIME - MIN
280 260
FL250
240 220 200 180 160 140 120 100 80 60 40 20
LANDING WEIGHT - LB
0 -20 40785 -40 38948 -60 37111 -80 35274 -100
REF. LINE
33436 -120 31599 -140 -160
HEAD
60 -180 -200
WIND - KT
30 -220 -240 -2600
REF. LINE
-280
TAIL
-30 -300 -320 -60 -340 -360 0
200
400
600
800
1000
1200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
TRIP DISTANCE - NM 135BJAOMFAA014 - 05AUG2003
Page
1-05-05
Code
16 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL EMB-135BJ SIMPLIFIED FLIGHT PLANNING TRIP TIME AE3007A1E ENGINE MACH 0.78 CRUISE ISA CONDITION 380 360
FL370 & FL390
340
BASED ON: 240/290/M0.60 CLIMB M0.78/310/250 DESCENT
320 300
FL350
280 260
FLIGHT TIME - MIN
240 220 200 180
FL300
160 140 120 100 80 60 40 20
LANDING WEIGHT - LB
0 -20 40785 -40 38948 -60 37111 -80 35274 -100
REF. LINE
33436 -120 31599 -140 -160
HEAD
60 -180 -200
WIND - KT
30 -220 -240 -2600
REF. LINE
-280
TAIL
-30 -300 -320 -60 -340 -360 0
200
400
600
800
1000
1200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
TRIP DISTANCE - NM 135BJAOMFAA015 - 05AUG2003
Page
REVISION 4
1-05-05
Code
17 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CRUISE - FLIGHT LEVEL TABLE The table below permits quick determination of the cruise flight level for minimum fuel consumption, based on the trip distance and takeoff weight. For each takeoff weight two different flight levels are calculated (A or B) based on the following assumptions: − Condition (A): The flight level was calculated based only on minimum fuel consumption. It may result on reduced time in leveled flight for short trip distances. CRUISE CLIMB UP
DESCENT A Short trip distance may result in no leveled flight
− Condition (B): The flight level was calculated based on a combination of minimum fuel consumption and at least 40% of the total flight time in cruise. CLIMB UP
CRUISE B
DESCENT At least 40% of total flight time
The tables data are presented for ISA condition, all engine operating and Maximum Speed Cruise schedule.
Page
1-05-05
Code
18 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
FLIGHT LEVEL - ALL ENGINES OPERATING AE3007A1E ENGINES, MAX SPEED CRUISE AND ISA CONDITIONS TOW (lb) 50000 48000 46000 44000 42000
COND 75
100
150
200
250
300
350
400
450
500
A
-
-
-
-
-
-
-
-
-
-
-
B
-
-
-
-
-
-
-
-
-
-
-
A
-
-
-
-
-
-
-
-
-
-
-
B
-
-
-
-
-
-
-
-
-
-
-
A
-
-
-
-
-
-
-
-
-
-
-
B
-
-
-
-
-
-
-
-
-
-
-
A
-
-
-
-
-
-
-
-
90
160
240
B
-
-
-
-
-
-
-
-
90
160
240
A
-
-
-
100
370
390
390
390
390
380
390
-
-
-
390
B 40000 38000 36000
TRIP DISTANCE (nm) 50
100
260
300
340
380
390
380
A
110 120 170
280
320
370
390
390
390
390
390
B
60
110 140
210
260
300
360
390
390
390
390
A
80
130 150
250
390
380
390
390
390
390
390
B
80
120 150
220
280
320
370
390
390
390
390
A
90
130 120
270
370
390
380
380
390
390
390
B
80
120 120
240
300
350
380
380
390
390
390
Page
REVISION 4
1-05-05
Code
19 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CRUISE - ALTITUDE CAPABILITY TABLE The table below permits quick determination of the altitude capability, based on the initial cruise weight. The table data are presented for various ISA conditions, all engines operating and Maximum Speed Cruise schedule. The established associated conditions are: - Flaps .................................... UP - Gears ................................... UP - Bleeds .................................. OPEN
CRUISE ALTITUDE CAPABILITY ALL ENGINES OPERATING AE3007A1E ENGINES, MAX SPEED CRUISE, CRUISE THRUST LIMITED
ISA + ºC Weight (lb)
-10
-5
0
5
10
15
20
25
30
35
50000
390
390
390
390
390
380
370
360
350
310
48000
390
390
390
390
390
390
380
370
360
340
46000
390
390
390
390
390
390
380
380
370
360
44000
390
390
390
390
390
390
390
380
370
360
42000
390
390
390
390
390
390
390
390
380
370
40000
390
390
390
390
390
390
390
390
390
380
38000
390
390
390
390
390
390
390
390
390
390
36000
390
390
390
390
390
390
390
390
390
390
34000
390
390
390
390
390
390
390
390
390
390
32000
390
390
390
390
390
390
390
390
390
390
30000
390
390
390
390
390
390
390
390
390
390
NOTE: The weight values refers to the initial cruise weight.
Page
1-05-05
Code
20 08
REVISION 4
FLIGHT PLANNING EMB-135BJ (lb)
AIRPLANE OPERATIONS MANUAL
APU AND ENGINE FUEL CONSUMPTION APU FUEL CONSUMPTION The table below shows the APU fuel consumption on the ground and during level flight at 5000 ft, 25000 ft, 37000 ft and 39000 ft altitudes. The data is calculated for different airspeeds, APU air bleeds and electrical loads.
APU FUEL CONSUMPTION Applicable to Sundstrand APU T-62T-40C14 (500R) ALTITUDE (ft)
AIRSPEED (KIAS)
0
0
APU AIR BLEED
APU GEN. LOAD
APU FUEL FLOW (lb/min)
No Load
No Load Max Load No Load Max Load No Load Max Load No Load Max Load No Load Max Load No Load Max Load No Load Max Load No Load Max Load No Load Max Load No Load Max Load No Load Max Load Max Load No Load Max Load Max Load No Load 300A Load No Load 300A Load
1.59 1.70 2.49 2.73 0.82 1.94 2.58 2.84 0.82 1.94 2.58 2.84 1.04 1.17 1.30 1.54 1.04 1.17 1.30 1.54 0.55 0.75 0.97 0.55 0.68 0.93 0.55 0.66 0.55 0.64
2 Packs No Load 140 2 Packs 5000 No Load 220 2 Packs No Load 140 2 Packs 25000 No Load 220 2 Packs No Load 140 37000
2 Packs No Load 220 2 Packs 140
39000
No Load 220
Page
REVISION 4
1-05-07
Code
1 02
FLIGHT PLANNING EMB-135BJ (lb)
AIRPLANE OPERATIONS MANUAL
ENGINE FUEL CONSUMPTION The following values established for taxi, take-off, approach and go around fuel consumption should be considered when calculating detailed flight plans.
FUEL CONSUMPTION ENGINE
PHASE OF FLIGHT
FUEL CONSUMPTION lb/min
AE3007 A1P, A1E
TAXI TAKE-OFF APPROACH AND LANDING GO AROUND
Page
1-05-07
16.01 105.8 40.79 105.8
Code
2 02
REVISION 4
AIRPLANE OPERATIONS MANUAL
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
CLIMB The climb planning tables show fuel consumption, distance, and time elapsed from the Sea Level to the top of climb. Data are shown for various weights, ISA deviations and cruise altitudes. Two climb schedule are presented: First set of tables presents the schedule climb speed according to the autopilot climb mode for airplanes equipped with EICAS versions up to 20.5 (Pre-Mod. SB 145LEG-31-0009), i.e.: − 240 KIAS for altitudes up to 10000 ft, increasing linearly to 290 KIAS at 12000 ft, maintaining 290 KIAS up to 21600 ft and 0.65 Mach above 21600 ft. Second set of tables presents the schedule climb speed according to the autopilot climb mode for airplanes equipped with EICAS versions 20.6 and on (Post-Mod. SB 145LEG-31-0009 or equipped with an equivalent modification factory incorporated), or as alternative climb schedule to be set manually, i.e.: − 240 KIAS for altitudes up to 8000 ft, increasing linearly to 270 KIAS at 14000 ft, maintaining 270 KIAS up to 25051 ft and 0.65 Mach above 25051 ft. The associated conditions are: − Thrust Mode ........................ CLB − Flaps.................................... UP − Gear..................................... UP − Bleeds.................................. OPEN − Anti-Ice ................................ OFF
Page
REVISION 7
1-05-10
Code
1 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-05-10
Code
2 08
REVISION 4
AIRPLANE OPERATIONS MANUAL
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AUTOPILOT CLIMB SCHEDULE FOR AIRPLANES EQUIPPED WITH EICAS VERSIONS UP TO 20.5 (PRE-MOD. SB 145LEG-31-0009)
Page
REVISION 7
1-05-10
Code
3 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-05-10
Code
4 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 5000 AND 6000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
5000 ft ISA + oC
WEIGHT lb
6000 ft ISA + oC
-20
-10
0
10
20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
146 6 2
152 7 2
158 7 2
166 7 2
184 9 2
175 8 2
183 8 2
190 8 2
199 9 2
222 11 3
48000
FUEL LB DISTANCE NM TIME MIN
139 6 2
144 6 2
150 7 2
157 7 2
175 9 2
166 7 2
173 8 2
180 8 2
189 8 2
210 10 2
46000
FUEL LB DISTANCE NM TIME MIN
131 6 1
137 6 1
143 6 2
149 7 2
165 8 2
158 7 2
164 7 2
171 8 2
179 8 2
199 10 2
44000
FUEL LB DISTANCE NM TIME MIN
124 5 1
130 6 1
135 6 1
141 6 1
156 8 2
149 7 2
155 7 2
162 7 2
169 8 2
188 9 2
42000
FUEL LB DISTANCE NM TIME MIN
118 5 1
123 5 1
128 6 1
133 6 1
147 7 2
141 6 2
147 6 2
153 7 2
160 7 2
177 9 2
40000
FUEL LB DISTANCE NM TIME MIN
111 5 1
116 5 1
120 5 1
126 5 1
139 7 2
133 6 1
139 6 1
144 6 2
151 7 2
167 8 2
38000
FUEL LB DISTANCE NM TIME MIN
105 4 1
109 5 1
113 5 1
119 5 1
130 6 1
125 5 1
131 6 1
136 6 1
142 6 2
157 8 2
36000
FUEL LB DISTANCE NM TIME MIN
98 4 1
102 4 1
107 5 1
111 5 1
122 6 1
118 5 1
123 5 1
128 6 1
134 6 1
147 7 2
34000
FUEL LB DISTANCE NM TIME MIN
92 4 1
96 4 1
100 4 1
104 5 1
114 6 1
110 5 1
115 5 1
120 5 1
125 6 1
137 7 2
32000
FUEL LB DISTANCE NM TIME MIN
86 4 1
90 4 1
93 4 1
98 4 1
107 5 1
103 4 1
108 5 1
112 5 1
117 5 1
128 6 1
30000
FUEL LB DISTANCE NM TIME MIN
80 3 1
84 4 1
87 4 1
91 4 1
99 5 1
96 4 1
100 4 1
104 5 1
109 5 1
119 6 1
Page
REVISION 4
1-05-10
Code
5 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 7000 AND 8000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000 FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
7000 ft ISA + oC
WEIGHT lb
8000 ft ISA + oC
-20
-10
0
10
20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
204 9 2
213 9 2
222 10 2
232 11 2
260 13 3
234 11 3
243 11 3
254 12 3
266 12 3
298 15 4
48000
FUEL LB DISTANCE NM TIME MIN
194 9 2
202 9 2
210 9 2
220 10 2
246 12 3
222 10 2
231 10 3
241 11 3
252 12 3
281 15 3
46000
FUEL LB DISTANCE NM TIME MIN
184 8 2
192 9 2
199 9 2
209 9 2
232 12 3
210 9 2
219 10 2
228 10 2
239 11 3
266 14 3
44000
FUEL LB DISTANCE NM TIME MIN
174 8 2
181 8 2
189 8 2
198 9 2
219 11 3
199 9 2
207 9 2
216 10 2
226 10 2
251 13 3
42000
FUEL LB DISTANCE NM TIME MIN
164 7 2
171 8 2
178 8 2
187 8 2
207 10 2
188 8 2
196 9 2
204 9 2
213 10 2
237 12 3
40000
FUEL LB DISTANCE NM TIME MIN
155 7 2
162 7 2
168 7 2
176 8 2
195 10 2
177 8 2
185 8 2
192 9 2
201 9 2
223 11 3
38000
FUEL LB DISTANCE NM TIME MIN
146 6 2
152 7 2
159 7 2
166 7 2
183 9 2
167 8 2
174 8 2
181 8 2
189 9 2
209 11 2
36000
FUEL LB DISTANCE NM TIME MIN
137 6 2
143 6 2
149 7 2
156 7 2
172 9 2
157 7 2
163 7 2
170 8 2
178 8 2
196 10 2
34000
FUEL LB DISTANCE NM TIME MIN
129 6 1
134 6 1
140 6 1
146 7 2
161 8 2
147 7 2
153 7 2
159 7 2
167 8 2
184 9 2
32000
FUEL LB DISTANCE NM TIME MIN
120 5 1
125 6 1
130 6 1
136 6 1
150 8 2
137 6 2
143 6 2
149 7 2
156 7 2
171 9 2
30000
FUEL LB DISTANCE NM TIME MIN
112 5 1
117 5 1
121 5 1
127 6 1
139 7 2
128 6 1
133 6 1
139 6 1
145 7 2
159 8 2
Page
1-05-10
Code
6 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 9000 AND 10000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
9000 ft ISA + oC
WEIGHT lb
10000 ft ISA + oC
-20
-10
0
10
20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
263 12 3
274 13 3
286 13 3
299 14 3
336 18 4
293 14 3
305 14 3
318 15 3
333 16 4
374 20 5
48000
FUEL LB DISTANCE NM TIME MIN
249 11 3
260 12 3
271 13 3
284 13 3
318 17 4
277 13 3
289 14 3
301 14 3
316 15 3
354 19 4
46000
FUEL LB DISTANCE NM TIME MIN
236 11 3
246 11 3
257 12 3
269 13 3
300 16 4
263 12 3
274 13 3
286 13 3
299 14 3
334 18 4
44000
FUEL LB DISTANCE NM TIME MIN
224 10 3
233 11 3
243 11 3
254 12 3
283 15 3
249 12 3
259 12 3
270 13 3
283 13 3
315 17 4
42000
FUEL LB DISTANCE NM TIME MIN
211 10 2
220 10 2
230 11 2
240 11 3
267 14 3
235 11 3
245 11 3
255 12 3
267 13 3
297 16 4
40000
FUEL LB DISTANCE NM TIME MIN
199 9 2
208 10 2
217 10 2
227 11 2
251 13 3
222 10 3
231 11 3
241 11 3
252 12 3
280 15 3
38000
FUEL LB DISTANCE NM TIME MIN
188 9 2
196 9 2
204 9 2
213 10 2
236 12 3
209 10 2
217 10 2
227 11 2
237 11 3
263 14 3
36000
FUEL LB DISTANCE NM TIME MIN
176 8 2
184 8 2
191 9 2
200 9 2
221 12 3
196 9 2
204 10 2
213 10 2
223 11 2
246 13 3
34000
FUEL LB DISTANCE NM TIME MIN
165 8 2
172 8 2
179 8 2
188 9 2
207 11 2
184 9 2
191 9 2
199 9 2
208 10 2
230 12 3
32000
FUEL LB DISTANCE NM TIME MIN
154 7 2
161 7 2
168 8 2
175 8 2
193 10 2
171 8 2
179 8 2
186 9 2
195 9 2
215 11 3
30000
FUEL LB DISTANCE NM TIME MIN
144 7 2
150 7 2
156 7 2
163 8 2
179 9 2
160 7 2
166 8 2
173 8 2
181 9 2
200 11 2
Page
REVISION 4
1-05-10
Code
7 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 11000 AND 12000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
11000 ft ISA + oC
WEIGHT lb
12000 ft ISA + oC
-20
-10
0
10
20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
323 16 4
337 16 4
351 17 4
368 18 4
415 23 5
356 18 4
372 19 4
388 19 4
407 21 5
463 26 6
48000
FUEL LB DISTANCE NM TIME MIN
306 15 4
319 15 4
333 16 4
349 17 4
392 22 5
338 17 4
352 18 4
368 18 4
386 20 4
437 25 5
46000
FUEL LB DISTANCE NM TIME MIN
290 14 3
303 15 3
315 15 4
331 16 4
371 20 5
320 16 4
334 17 4
348 17 4
365 19 4
413 24 5
44000
FUEL LB DISTANCE NM TIME MIN
274 13 3
286 14 3
298 14 3
313 15 3
350 19 4
303 15 4
316 16 4
329 16 4
345 18 4
389 22 5
42000
FUEL LB DISTANCE NM TIME MIN
259 12 3
270 13 3
282 14 3
295 14 3
329 18 4
286 14 3
298 15 3
311 15 3
326 17 4
366 21 5
40000
FUEL LB DISTANCE NM TIME MIN
244 12 3
255 12 3
266 13 3
278 14 3
310 17 4
269 13 3
281 14 3
293 15 3
307 16 3
345 20 4
38000
FUEL LB DISTANCE NM TIME MIN
230 11 3
240 11 3
250 12 3
262 13 3
291 16 4
254 13 3
265 13 3
276 14 3
289 15 3
323 18 4
36000
FUEL LB DISTANCE NM TIME MIN
216 10 2
225 11 3
235 11 3
246 12 3
273 15 3
238 12 3
248 12 3
259 13 3
271 14 3
303 17 4
34000
FUEL LB DISTANCE NM TIME MIN
202 10 2
211 10 2
220 11 2
230 11 3
255 14 3
223 11 3
233 11 3
243 12 3
254 13 3
283 16 3
32000
FUEL LB DISTANCE NM TIME MIN
189 9 2
197 9 2
205 10 2
215 10 2
238 13 3
208 10 2
217 11 2
226 11 3
237 12 3
264 15 3
30000
FUEL LB DISTANCE NM TIME MIN
176 8 2
183 9 2
191 9 2
200 10 2
221 12 3
194 10 2
202 10 2
211 10 2
221 11 2
245 14 3
Page
1-05-10
Code
8 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 13000 AND 14000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
13000 ft ISA + oC
WEIGHT lb
14000 ft ISA + oC
-20
-10
0
10
20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
392 20 5
409 21 5
427 22 5
450 24 5
516 31 6
429 23 5
448 24 5
468 25 5
493 27 6
572 36 7
48000
FUEL LB DISTANCE NM TIME MIN
372 19 4
388 20 4
405 21 5
426 23 5
488 29 6
406 22 5
424 23 5
443 24 5
467 26 5
540 34 7
46000
FUEL LB DISTANCE NM TIME MIN
352 18 4
367 19 4
383 20 4
403 21 5
460 28 6
385 21 5
402 22 5
420 23 5
442 24 5
509 32 6
44000
FUEL LB DISTANCE NM TIME MIN
333 17 4
347 18 4
363 19 4
381 20 4
434 26 5
364 20 4
380 20 4
397 21 5
417 23 5
480 30 6
42000
FUEL LB DISTANCE NM TIME MIN
314 16 4
328 17 4
342 18 4
360 19 4
408 24 5
343 18 4
359 19 4
374 20 4
394 22 5
451 28 6
40000
FUEL LB DISTANCE NM TIME MIN
296 15 3
309 16 4
323 17 4
339 18 4
384 23 5
324 17 4
338 18 4
353 19 4
371 20 4
424 26 5
38000
FUEL LB DISTANCE NM TIME MIN
279 14 3
291 15 3
304 16 3
319 17 4
360 21 4
304 16 4
318 17 4
332 18 4
349 19 4
398 25 5
36000
FUEL LB DISTANCE NM TIME MIN
262 13 3
273 14 3
285 15 3
299 16 3
337 20 4
286 15 3
298 16 3
312 17 4
327 18 4
372 23 5
34000
FUEL LB DISTANCE NM TIME MIN
245 13 3
256 13 3
267 14 3
280 15 3
315 19 4
268 14 3
279 15 3
292 16 3
307 17 4
348 22 4
32000
FUEL LB DISTANCE NM TIME MIN
229 12 3
239 12 3
249 13 3
261 14 3
293 17 4
250 13 3
261 14 3
272 15 3
286 16 3
324 20 4
30000
FUEL LB DISTANCE NM TIME MIN
213 11 2
222 11 3
232 12 3
243 13 3
273 16 3
233 12 3
243 13 3
253 14 3
266 14 3
301 19 4
Page
REVISION 4
1-05-10
Code
9 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 15000 AND 16000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
15000 ft ISA + oC
WEIGHT lb
16000 ft ISA + oC
-20
-10
0
10
20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
467 26 6
487 27 6
510 29 6
538 31 6
631 41 8
505 29 6
528 30 6
552 32 6
584 35 7
693 47 9
48000
FUEL LB DISTANCE NM TIME MIN
442 25 5
462 26 5
483 27 6
509 29 6
595 39 8
478 28 6
500 29 6
523 30 6
553 33 6
653 44 8
46000
FUEL LB DISTANCE NM TIME MIN
418 23 5
437 24 5
457 26 5
482 27 6
561 36 7
453 26 6
473 27 6
495 29 6
523 31 6
614 41 8
44000
FUEL LB DISTANCE NM TIME MIN
395 22 5
413 23 5
432 24 5
455 26 5
528 34 7
428 25 5
447 26 5
467 27 5
494 29 6
578 39 8
42000
FUEL LB DISTANCE NM TIME MIN
373 21 4
390 22 5
407 23 5
429 24 5
496 32 6
404 23 5
422 24 5
441 25 5
465 27 5
543 36 7
40000
FUEL LB DISTANCE NM TIME MIN
352 20 4
367 20 4
384 21 4
404 23 5
466 30 6
380 22 5
397 23 5
415 24 5
438 26 5
510 34 7
38000
FUEL LB DISTANCE NM TIME MIN
331 18 4
345 19 4
361 20 4
380 22 4
437 28 6
358 20 4
374 21 4
391 22 5
412 24 5
478 32 6
36000
FUEL LB DISTANCE NM TIME MIN
310 17 4
324 18 4
339 19 4
357 20 4
409 26 5
336 19 4
351 20 4
366 21 4
386 23 5
447 30 6
34000
FUEL LB DISTANCE NM TIME MIN
291 16 3
304 17 4
317 18 4
334 19 4
382 25 5
314 18 4
328 19 4
343 20 4
361 21 4
417 28 5
32000
FUEL LB DISTANCE NM TIME MIN
271 15 3
283 16 3
296 16 3
311 18 4
355 23 5
293 17 4
306 17 4
320 18 4
337 20 4
388 26 5
30000
FUEL LB DISTANCE NM TIME MIN
252 14 3
264 15 3
275 15 3
290 16 3
330 21 4
273 16 3
285 16 3
298 17 3
314 18 4
360 24 5
Page
1-05-10
Code
10 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 17000 AND 18000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
17000 ft ISA + oC
WEIGHT lb
18000 ft ISA + oC
-20
-10
0
10
20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
545 32 7
570 34 7
597 36 7
632 39 8
758 53 10
586 36 7
613 38 7
642 40 8
682 43 8
827 60 11
48000
FUEL LB DISTANCE NM TIME MIN
516 31 6
540 32 7
565 34 7
598 37 7
713 50 9
554 34 7
580 36 7
607 37 7
645 41 8
778 56 10
46000
FUEL LB DISTANCE NM TIME MIN
488 29 6
510 30 6
534 32 6
565 34 7
671 47 9
524 32 7
548 34 7
574 35 7
609 38 7
731 53 10
44000
FUEL LB DISTANCE NM TIME MIN
461 27 6
482 29 6
504 30 6
533 32 6
631 44 8
495 30 6
518 32 6
542 33 7
575 36 7
687 50 9
42000
FUEL LB DISTANCE NM TIME MIN
435 26 5
455 27 5
475 28 6
503 31 6
592 41 8
467 29 6
488 30 6
511 31 6
542 34 7
644 46 9
40000
FUEL LB DISTANCE NM TIME MIN
409 24 5
428 25 5
448 27 5
473 29 6
556 39 7
439 27 5
459 28 6
481 30 6
510 32 6
604 43 8
38000
FUEL LB DISTANCE NM TIME MIN
385 23 5
402 24 5
421 25 5
445 27 5
520 36 7
413 25 5
432 26 5
452 28 5
479 30 6
565 41 8
36000
FUEL LB DISTANCE NM TIME MIN
361 21 4
378 22 5
395 23 5
417 25 5
486 34 6
387 24 5
405 25 5
424 26 5
449 28 5
528 38 7
34000
FUEL LB DISTANCE NM TIME MIN
338 20 4
353 21 4
369 22 4
390 24 5
454 31 6
362 22 5
379 23 5
396 24 5
419 26 5
492 35 7
32000
FUEL LB DISTANCE NM TIME MIN
315 19 4
330 19 4
345 20 4
364 22 4
422 29 6
338 21 4
353 21 4
370 23 4
391 24 5
457 33 6
30000
FUEL LB DISTANCE NM TIME MIN
293 17 4
307 18 4
320 19 4
338 20 4
391 27 5
314 19 4
329 20 4
344 21 4
364 23 4
424 30 6
Page
REVISION 4
1-05-10
Code
11 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 19000 AND 20000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
19000 ft ISA + oC
WEIGHT lb
20000 ft ISA + oC
-20
-10
0
10
20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
627 40 8
657 42 8
688 44 8
734 48 9
900 68 12
669 43 9
701 46 9
735 48 9
786 53 10
976 76 13
48000
FUEL LB DISTANCE NM TIME MIN
593 37 7
621 39 8
651 41 8
693 45 8
846 63 11
633 41 8
663 43 8
695 45 9
742 50 9
916 71 13
46000
FUEL LB DISTANCE NM TIME MIN
561 35 7
587 37 7
615 39 7
654 42 8
794 59 11
598 39 8
626 41 8
656 43 8
700 47 9
859 66 12
44000
FUEL LB DISTANCE NM TIME MIN
529 33 7
554 35 7
580 37 7
617 40 8
745 56 10
564 36 7
591 38 7
619 40 8
660 44 8
805 62 11
42000
FUEL LB DISTANCE NM TIME MIN
499 31 6
522 33 6
547 35 7
581 38 7
698 52 9
532 34 7
557 36 7
583 38 7
621 41 8
754 58 10
40000
FUEL LB DISTANCE NM TIME MIN
470 30 6
491 31 6
514 32 6
547 35 7
654 49 9
500 32 6
524 34 7
549 36 7
584 39 7
705 54 10
38000
FUEL LB DISTANCE NM TIME MIN
441 28 6
462 29 6
483 30 6
513 33 6
611 45 8
470 30 6
492 32 6
515 33 6
548 36 7
659 50 9
36000
FUEL LB DISTANCE NM TIME MIN
414 26 5
433 27 5
453 29 6
481 31 6
571 42 8
440 28 6
461 30 6
483 31 6
514 34 6
615 47 8
34000
FUEL LB DISTANCE NM TIME MIN
387 24 5
405 25 5
424 27 5
450 29 5
532 39 7
412 26 5
431 28 5
451 29 6
480 32 6
573 44 8
32000
FUEL LB DISTANCE NM TIME MIN
361 23 5
378 24 5
395 25 5
419 27 5
494 36 7
384 25 5
402 26 5
421 27 5
447 30 5
532 40 7
30000
FUEL LB DISTANCE NM TIME MIN
336 21 4
351 22 4
367 23 4
389 25 5
458 34 6
357 23 5
374 24 5
391 25 5
415 27 5
493 37 7
Page
1-05-10
Code
12 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 21000 AND 22000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
21000 ft ISA + oC
WEIGHT lb -20
-10
0
10
22000 ft ISA + oC 20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
712 47 9
746 50 9
783 52 10
840 1058 58 85 10 15
751 51 10
787 54 10
826 57 10
889 1136 63 93 11 16
48000
FUEL LB DISTANCE NM TIME MIN
673 45 9
705 47 9
740 49 9
792 55 10
991 79 14
710 48 9
744 51 9
780 53 10
838 1062 59 87 11 15
46000
FUEL LB DISTANCE NM TIME MIN
636 42 8
666 44 8
698 47 9
747 51 9
928 74 13
670 46 9
702 48 9
736 50 9
790 56 10
993 81 14
44000
FUEL LB DISTANCE NM TIME MIN
600 40 8
628 42 8
658 44 8
704 48 9
869 69 12
632 43 8
662 45 8
694 47 9
744 52 9
929 76 13
42000
FUEL LB DISTANCE NM TIME MIN
565 37 7
592 39 7
620 41 8
663 45 8
813 64 11
595 40 8
623 42 8
654 45 8
700 49 9
868 71 12
40000
FUEL LB DISTANCE NM TIME MIN
531 35 7
557 37 7
583 39 7
623 43 8
760 60 11
559 38 7
586 40 7
614 42 8
658 46 8
811 66 11
38000
FUEL LB DISTANCE NM TIME MIN
499 33 6
523 35 7
548 36 7
584 40 7
710 56 10
525 36 7
550 37 7
577 39 7
617 43 8
757 61 11
36000
FUEL LB DISTANCE NM TIME MIN
468 31 6
490 32 6
513 34 6
547 37 7
661 52 9
492 33 6
515 35 7
540 37 7
577 40 7
705 57 10
34000
FUEL LB DISTANCE NM TIME MIN
437 29 6
458 30 6
480 32 6
511 35 6
615 48 9
460 31 6
482 33 6
505 34 6
539 38 7
655 53 9
32000
FUEL LB DISTANCE NM TIME MIN
408 27 5
427 28 5
447 30 6
476 32 6
571 45 8
429 29 6
449 30 6
470 32 6
502 35 6
608 49 9
30000
FUEL LB DISTANCE NM TIME MIN
379 25 5
397 26 5
415 27 5
442 30 5
529 41 7
398 27 5
417 28 5
437 30 5
466 32 6
562 45 8
Page
REVISION 4
1-05-10
Code
13 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 23000 AND 24000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
23000 ft ISA + oC
WEIGHT lb -20
-10
0
10
24000 ft ISA + oC 20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
786 55 10
824 57 11
865 60 11
933 1207 67 102 12 17
820 58 11
861 61 11
904 64 12
977 1278 72 110 13 19
48000
FUEL LB DISTANCE NM TIME MIN
742 52 10
778 54 10
817 57 10
880 1127 63 95 11 16
774 55 10
812 58 11
853 61 11
920 1192 68 103 12 17
46000
FUEL LB DISTANCE NM TIME MIN
700 49 9
734 51 9
770 54 10
829 1053 60 88 11 15
730 52 10
766 54 10
804 57 10
867 1112 64 95 11 16
44000
FUEL LB DISTANCE NM TIME MIN
660 46 9
692 48 9
726 51 9
780 56 10
984 82 14
688 49 9
721 51 9
757 54 10
815 1037 60 89 10 15
42000
FUEL LB DISTANCE NM TIME MIN
621 43 8
651 45 8
683 47 9
733 53 9
918 77 13
648 46 9
679 48 9
713 50 9
766 56 10
968 83 14
40000
FUEL LB DISTANCE NM TIME MIN
584 40 8
612 42 8
642 45 8
689 49 9
857 71 12
609 43 8
638 45 8
669 47 9
719 52 9
902 77 13
38000
FUEL LB DISTANCE NM TIME MIN
548 38 7
574 40 7
602 42 8
646 46 8
799 66 11
571 40 8
599 42 8
628 44 8
674 49 9
840 71 12
36000
FUEL LB DISTANCE NM TIME MIN
513 35 7
538 37 7
564 39 7
604 43 8
744 62 11
535 37 7
560 39 7
588 41 7
631 46 8
782 66 11
34000
FUEL LB DISTANCE NM TIME MIN
480 33 6
503 35 6
527 36 7
564 40 7
691 57 10
499 35 7
524 37 7
549 39 7
589 43 8
726 61 10
32000
FUEL LB DISTANCE NM TIME MIN
447 31 6
468 32 6
491 34 6
525 37 7
640 53 9
465 33 6
488 34 6
512 36 7
548 40 7
672 57 10
30000
FUEL LB DISTANCE NM TIME MIN
415 28 5
435 30 6
456 31 6
487 35 6
592 49 8
432 30 6
453 32 6
475 33 6
508 37 7
621 52 9
Page
1-05-10
Code
14 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 25000 AND 26000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
25000 ft ISA + oC
WEIGHT lb -19
-10
0
10
26000 ft ISA + oC 20
-18
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
859 62 11
897 65 12
943 1021 1348 68 77 119 12 13 20
899 66 12
935 69 12
982 1064 1416 73 81 128 13 14 21
48000
FUEL LB DISTANCE NM TIME MIN
811 58 11
846 61 11
889 64 11
961 1255 72 110 12 18
848 62 11
881 65 12
926 1002 1317 68 76 118 12 13 20
46000
FUEL LB DISTANCE NM TIME MIN
764 55 10
798 57 10
838 61 11
905 1170 68 103 12 17
799 59 11
830 61 11
872 64 11
942 1225 72 109 12 18
44000
FUEL LB DISTANCE NM TIME MIN
720 52 10
751 54 10
789 57 10
851 1090 63 95 11 16
752 55 10
781 57 10
821 60 11
885 1141 67 102 12 17
42000
FUEL LB DISTANCE NM TIME MIN
677 49 9
707 51 9
742 53 10
799 1016 59 88 10 15
707 52 10
735 54 10
771 57 10
831 1062 63 94 11 16
40000
FUEL LB DISTANCE NM TIME MIN
636 46 8
664 48 9
697 50 9
750 56 10
946 82 14
664 48 9
690 50 9
724 53 9
780 59 10
989 87 15
38000
FUEL LB DISTANCE NM TIME MIN
597 43 8
623 45 8
653 47 8
702 52 9
881 76 13
623 45 8
647 47 9
679 50 9
730 55 10
920 81 14
36000
FUEL LB DISTANCE NM TIME MIN
558 40 7
583 42 8
612 44 8
657 49 8
819 71 12
583 42 8
605 44 8
635 46 8
683 51 9
854 75 13
34000
FUEL LB DISTANCE NM TIME MIN
522 37 7
544 39 7
571 41 7
613 45 8
760 65 11
544 39 7
565 41 7
593 43 8
637 48 8
792 70 12
32000
FUEL LB DISTANCE NM TIME MIN
486 35 6
507 36 7
532 38 7
570 42 7
704 60 10
507 37 7
526 38 7
552 40 7
592 44 8
733 64 11
30000
FUEL LB DISTANCE NM TIME MIN
451 32 6
471 33 6
494 35 6
529 39 7
650 56 9
470 34 6
488 35 6
512 37 7
549 41 7
677 59 10
Page
REVISION 4
1-05-10
Code
15 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 27000 AND 28000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
27000 ft ISA + oC
WEIGHT lb -17
-10
0
10
28000 ft ISA + oC 20
-16
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
941 71 13
973 1023 1108 1481 73 77 86 136 13 14 15 22
984 1013 1065 1153 1545 75 78 82 91 144 14 14 14 16 24
48000
FUEL LB DISTANCE NM TIME MIN
886 66 12
917 69 12
963 1042 1376 73 81 126 13 14 21
926 71 13
953 1002 1083 1433 73 77 86 133 13 13 15 22
46000
FUEL LB DISTANCE NM TIME MIN
834 62 11
863 65 12
907 68 12
980 1279 76 116 13 19
871 66 12
897 68 12
943 1018 1331 72 80 123 13 14 20
44000
FUEL LB DISTANCE NM TIME MIN
785 59 11
812 61 11
853 64 11
920 1190 71 108 12 18
819 62 11
843 64 11
886 68 12
955 1237 75 114 13 19
42000
FUEL LB DISTANCE NM TIME MIN
738 55 10
763 57 10
801 60 11
864 1107 67 100 11 17
769 58 11
792 60 11
832 63 11
896 1150 70 106 12 17
40000
FUEL LB DISTANCE NM TIME MIN
693 51 9
716 53 10
752 56 10
810 1030 62 93 11 15
722 55 10
743 56 10
780 59 10
840 1069 66 98 11 16
38000
FUEL LB DISTANCE NM TIME MIN
649 48 9
671 50 9
705 53 9
758 58 10
957 86 14
676 51 9
696 53 9
731 56 10
786 61 11
993 91 15
36000
FUEL LB DISTANCE NM TIME MIN
607 45 8
628 47 8
659 49 9
708 54 9
888 80 13
632 48 9
651 49 9
683 52 9
734 57 10
922 84 14
34000
FUEL LB DISTANCE NM TIME MIN
567 42 8
586 43 8
615 46 8
660 51 9
824 74 12
590 44 8
607 46 8
637 48 8
684 53 9
854 77 13
32000
FUEL LB DISTANCE NM TIME MIN
527 39 7
545 40 7
572 42 8
614 47 8
762 68 11
549 41 8
565 43 8
593 45 8
636 49 8
790 71 12
30000
FUEL LB DISTANCE NM TIME MIN
490 36 7
506 37 7
531 39 7
569 43 8
703 62 10
509 38 7
524 39 7
550 41 7
589 46 8
728 66 11
Page
1-05-10
Code
16 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 29000 AND 30000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
29000 ft ISA + oC
WEIGHT lb -15
-10
0
10
30000 ft ISA + oC 20
-14
-10
0
10
20
50000
FUEL LB 1028 1053 1107 1199 1609 DISTANCE NM 80 82 87 97 153 TIME MIN 14 15 15 16 25
1072 1093 1150 1246 1676 86 87 92 103 162 15 15 16 17 26
48000
FUEL LB DISTANCE NM TIME MIN
966 75 13
990 1041 1126 1491 77 82 91 141 14 14 15 23
1007 1027 1080 1168 1551 80 82 86 96 149 14 14 15 16 24
46000
FUEL LB DISTANCE NM TIME MIN
909 71 13
931 73 13
979 1057 1384 76 85 130 13 14 21
946 75 13
965 1014 1096 1437 77 81 90 137 13 14 15 22
44000
FUEL LB DISTANCE NM TIME MIN
854 66 12
875 68 12
919 72 12
991 1285 79 120 13 20
888 70 12
906 72 13
952 1027 1333 76 84 127 13 14 21
42000
FUEL LB DISTANCE NM TIME MIN
801 62 11
821 64 11
863 67 12
929 1194 74 111 13 18
833 66 12
850 67 12
893 71 12
962 1237 78 117 13 19
40000
FUEL LB DISTANCE NM TIME MIN
751 58 10
770 60 11
809 63 11
870 1109 69 103 12 17
781 61 11
796 63 11
836 66 11
900 1148 73 108 12 18
38000
FUEL LB DISTANCE NM TIME MIN
703 54 10
721 56 10
757 59 10
814 1029 65 95 11 16
731 57 10
745 59 10
782 62 11
841 1065 68 100 12 16
36000
FUEL LB DISTANCE NM TIME MIN
657 51 9
673 52 9
707 55 10
759 60 10
954 88 14
682 53 10
696 55 10
731 57 10
785 63 11
987 93 15
34000
FUEL LB DISTANCE NM TIME MIN
613 47 8
628 48 9
659 51 9
708 56 10
884 81 13
636 50 9
649 51 9
681 53 9
731 59 10
914 85 14
32000
FUEL LB DISTANCE NM TIME MIN
570 44 8
584 45 8
613 47 8
658 52 9
817 75 12
591 46 8
603 47 8
633 50 9
679 55 9
844 79 13
30000
FUEL LB DISTANCE NM TIME MIN
529 40 7
542 41 7
569 44 8
609 48 8
753 69 11
548 43 8
559 44 8
587 46 8
629 51 9
778 72 12
Page
REVISION 4
1-05-10
Code
17 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 31000 AND 32000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
31000 ft ISA + oC
WEIGHT lb -13
-10
0
10
32000 ft ISA + oC 20
-12
-10
0
10
20
50000
FUEL LB 1116 1133 1192 1293 1746 DISTANCE NM 91 92 97 109 171 TIME MIN 16 16 17 18 28
1161 1172 1233 1341 1820 96 97 102 115 182 17 17 17 19 29
48000
FUEL LB 1048 1063 1118 1211 1613 DISTANCE NM 85 86 91 101 158 TIME MIN 15 15 16 17 25
1088 1099 1156 1255 1678 90 91 96 107 167 16 16 16 18 27
46000
FUEL LB DISTANCE NM TIME MIN
983 79 14
998 1049 1135 1492 81 85 95 145 14 15 16 23
1021 1031 1084 1175 1550 84 85 89 100 153 15 15 15 17 25
44000
FUEL LB DISTANCE NM TIME MIN
923 74 13
936 75 13
984 1063 1382 80 88 134 14 15 22
957 78 14
966 1016 1099 1434 79 83 93 141 14 14 16 23
42000
FUEL LB DISTANCE NM TIME MIN
865 69 12
878 70 12
922 74 13
995 1282 82 123 14 20
897 73 13
905 74 13
952 1028 1327 78 87 130 13 15 21
40000
FUEL LB DISTANCE NM TIME MIN
810 65 11
822 66 12
864 69 12
930 1188 77 114 13 19
839 68 12
847 69 12
890 73 12
961 1229 81 120 14 19
38000
FUEL LB DISTANCE NM TIME MIN
758 61 11
769 61 11
808 65 11
869 1101 72 105 12 17
784 64 11
792 64 11
832 68 12
897 1138 75 111 13 18
36000
FUEL LB DISTANCE NM TIME MIN
707 56 10
718 57 10
754 60 10
811 1020 67 97 11 16
732 59 10
739 60 11
777 63 11
836 1053 70 102 12 17
34000
FUEL LB DISTANCE NM TIME MIN
659 52 9
669 53 9
702 56 10
754 62 10
943 90 15
682 55 10
688 56 10
723 59 10
778 65 11
974 94 15
32000
FUEL LB DISTANCE NM TIME MIN
613 49 9
622 49 9
653 52 9
701 57 10
871 83 14
633 51 9
640 52 9
672 54 9
722 60 10
898 87 14
30000
FUEL LB DISTANCE NM TIME MIN
568 45 8
576 46 8
605 48 8
649 53 9
803 76 12
587 47 8
593 48 8
622 50 9
668 55 9
827 79 13
Page
1-05-10
Code
18 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 33000 AND 34000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
33000 ft ISA + oC
WEIGHT lb -10
-5
0
10
34000 ft ISA + oC 20
-9
-5
0
10
20
50000
FUEL LB 1212 1243 1275 1391 1898 DISTANCE NM 102 105 108 121 194 TIME MIN 18 18 18 20 31
1261 1287 1320 1444 1980 108 110 113 128 206 19 19 19 21 33
48000
FUEL LB 1136 1164 1194 1300 1745 DISTANCE NM 95 98 100 113 177 TIME MIN 17 17 17 19 28
1180 1204 1235 1347 1815 101 103 106 119 188 17 18 18 20 30
46000
FUEL LB 1064 1091 1119 1215 1609 DISTANCE NM 89 91 94 105 162 TIME MIN 15 16 16 17 26
1105 1127 1156 1257 1670 94 96 98 111 172 16 16 17 18 27
44000
FUEL LB DISTANCE NM TIME MIN
997 1022 1048 1136 1486 83 85 87 98 149 14 15 15 16 24
1034 1054 1081 1174 1539 88 89 92 103 157 15 15 16 17 25
42000
FUEL LB DISTANCE NM TIME MIN
933 77 13
957 79 14
981 1062 1374 82 91 137 14 15 22
967 82 14
986 1011 1096 1421 83 86 96 144 14 15 16 23
40000
FUEL LB DISTANCE NM TIME MIN
873 72 13
895 74 13
917 76 13
991 1271 85 126 14 20
904 76 13
922 78 13
945 1022 1313 80 89 133 14 15 21
38000
FUEL LB DISTANCE NM TIME MIN
815 67 12
836 69 12
857 71 12
925 1175 79 116 13 19
844 71 12
860 72 12
882 74 13
953 1213 83 122 14 20
36000
FUEL LB DISTANCE NM TIME MIN
761 63 11
780 64 11
799 66 11
861 1087 73 107 12 17
786 66 11
802 67 12
822 69 12
887 1120 77 112 13 18
34000
FUEL LB DISTANCE NM TIME MIN
708 58 10
726 60 10
744 61 11
801 1004 68 99 11 16
732 61 11
746 62 11
765 64 11
825 1034 71 103 12 17
32000
FUEL LB DISTANCE NM TIME MIN
658 54 9
674 55 10
691 57 10
743 63 11
926 91 15
679 56 10
693 58 10
710 59 10
765 66 11
953 95 15
30000
FUEL LB DISTANCE NM TIME MIN
609 50 9
624 51 9
640 52 9
687 58 10
852 83 14
629 52 9
641 53 9
657 55 9
707 61 10
876 87 14
Page
REVISION 4
1-05-10
Code
19 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 35000 AND 36000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
35000 ft ISA + oC
WEIGHT lb -8
-5
0
10
36000 ft ISA + oC 20
-7
-5
0
10
20
50000
FUEL LB 1315 1335 1369 1499 2070 DISTANCE NM 115 117 120 136 221 TIME MIN 20 20 20 22 35
1373 1387 1423 1559 2169 123 124 128 145 237 21 21 21 24 38
48000
FUEL LB 1228 1247 1279 1396 1891 DISTANCE NM 107 109 112 126 200 TIME MIN 18 19 19 21 32
1280 1293 1326 1448 1973 114 115 118 134 213 19 20 20 22 34
46000
FUEL LB 1148 1165 1195 1301 1734 DISTANCE NM 99 101 104 117 182 TIME MIN 17 17 18 19 29
1194 1206 1237 1347 1803 106 107 110 124 193 18 18 19 20 31
44000
FUEL LB 1073 1089 1117 1213 1595 DISTANCE NM 93 94 97 108 166 TIME MIN 16 16 16 18 27
1114 1125 1154 1254 1654 98 99 102 114 175 17 17 17 19 28
42000
FUEL LB 1002 1017 1043 1131 1470 DISTANCE NM 86 87 90 101 152 TIME MIN 15 15 15 17 24
1039 1050 1077 1168 1521 91 92 95 106 160 16 16 16 18 26
40000
FUEL LB DISTANCE NM TIME MIN
936 80 14
950 81 14
974 1054 1356 84 94 139 14 16 22
970 85 15
979 1004 1087 1400 86 88 98 147 15 15 16 24
38000
FUEL LB DISTANCE NM TIME MIN
873 75 13
886 76 13
908 78 13
982 1251 87 128 14 21
904 79 14
913 79 14
936 1012 1290 82 91 134 14 15 22
36000
FUEL LB DISTANCE NM TIME MIN
813 69 12
825 70 12
846 72 12
913 1155 80 118 13 19
841 73 13
849 74 13
871 76 13
940 1189 84 123 14 20
34000
FUEL LB DISTANCE NM TIME MIN
756 64 11
767 65 11
787 67 11
848 1065 74 108 12 17
781 68 12
789 68 12
809 70 12
872 1095 78 113 13 18
32000
FUEL LB DISTANCE NM TIME MIN
702 59 10
712 60 10
730 62 11
786 69 11
980 99 16
725 62 11
732 63 11
750 65 11
808 1008 72 103 12 17
30000
FUEL LB DISTANCE NM TIME MIN
649 55 10
659 56 10
675 57 10
727 63 11
901 91 15
670 58 10
677 58 10
693 60 10
746 66 11
Page
1-05-10
925 95 15
Code
20 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 37000 AND 38000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
37000 ft ISA + oC
WEIGHT lb -8
-5
0
10
38000 ft ISA + oC 20
-8
-5
0
10
20
50000
FUEL LB 1427 1448 1485 1629 2297 DISTANCE NM 131 133 137 155 258 TIME MIN 22 23 23 25 41
1503 1525 1564 1718 2515 143 145 149 169 297 24 25 25 28 47
48000
FUEL LB 1325 1345 1380 1508 2072 DISTANCE NM 121 123 126 143 230 TIME MIN 21 21 21 23 36
1388 1409 1445 1581 2219 131 133 136 154 256 22 23 23 25 41
46000
FUEL LB 1233 1252 1284 1399 1884 DISTANCE NM 112 114 117 131 206 TIME MIN 19 19 20 22 33
1287 1306 1339 1460 1993 120 122 125 141 226 21 21 21 23 36
44000
FUEL LB 1148 1166 1195 1300 1721 DISTANCE NM 104 105 108 121 187 TIME MIN 18 18 18 20 30
1194 1212 1243 1352 1807 111 112 115 130 202 19 19 19 21 32
42000
FUEL LB 1070 1086 1113 1208 1578 DISTANCE NM 96 97 100 112 170 TIME MIN 16 17 17 18 27
1110 1126 1155 1254 1648 102 104 107 119 182 18 18 18 20 29
40000
FUEL LB DISTANCE NM TIME MIN
996 1011 1037 1123 1449 89 90 93 104 155 15 15 16 17 25
1032 1047 1073 1163 1508 94 96 98 110 165 16 16 17 18 26
38000
FUEL LB DISTANCE NM TIME MIN
927 82 14
941 84 14
965 1043 1333 86 96 142 15 16 23
959 87 15
973 89 15
997 1079 1383 91 101 150 15 17 24
36000
FUEL LB DISTANCE NM TIME MIN
862 76 13
875 77 13
897 80 13
969 1227 89 130 15 21
890 81 14
903 82 14
926 1000 1269 84 94 137 14 15 22
34000
FUEL LB DISTANCE NM TIME MIN
800 71 12
812 72 12
833 74 12
898 1128 82 119 14 19
825 74 13
838 76 13
859 78 13
926 1166 86 125 14 20
32000
FUEL LB DISTANCE NM TIME MIN
742 65 11
753 66 11
771 68 12
831 1037 75 108 13 17
764 69 12
775 70 12
795 71 12
856 1070 79 114 13 18
30000
FUEL LB DISTANCE NM TIME MIN
685 60 10
695 61 10
713 63 11
767 69 12
705 63 11
716 64 11
734 66 11
789 73 12
951 99 16
Page
REVISION 4
1-05-10
980 104 17
Code
21 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 39000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT 12000FT, MAINTAINING 290 KIAS UP TO 21600 FT AND M = 0.65 ABOVE 21600 FT. CRUISE CONFIGURATION BLEED: OPEN
39000 ft ISA + oC
WEIGHT lb -8
10
20
50000
FUEL LB 1601 1625 1665 1837 DISTANCE NM 160 162 166 190 TIME MIN 27 27 28 31
-
48000
FUEL LB 1466 1487 1525 1673 2507 DISTANCE NM 144 146 150 170 310 TIME MIN 24 25 25 28 49
46000
FUEL LB 1350 1370 1404 1534 2163 DISTANCE NM 131 133 136 154 258 TIME MIN 22 22 23 25 41
44000
FUEL LB 1247 1266 1298 1413 1926 DISTANCE NM 120 121 124 140 225 TIME MIN 20 21 21 23 36
42000
FUEL LB 1155 1172 1202 1305 1737 DISTANCE NM 110 111 114 128 199 TIME MIN 19 19 19 21 32
40000
FUEL LB 1070 1086 1114 1207 1579 DISTANCE NM 101 102 105 117 179 TIME MIN 17 17 18 19 28
38000
FUEL LB DISTANCE NM TIME MIN
992 1007 1033 1117 1441 93 94 97 108 161 16 16 16 18 26
36000
FUEL LB DISTANCE NM TIME MIN
920 86 15
934 87 15
957 1034 1318 89 99 146 15 16 23
34000
FUEL LB DISTANCE NM TIME MIN
852 79 14
864 80 14
886 82 14
956 1207 91 133 15 21
32000
FUEL LB DISTANCE NM TIME MIN
787 72 12
799 74 13
819 75 13
882 1105 84 121 14 19
30000
FUEL LB DISTANCE NM TIME MIN
726 67 11
737 68 12
755 69 12
813 1011 77 110 13 18
Page
1-05-10
-5
0
Code
22 08
REVISION 4
AIRPLANE OPERATIONS MANUAL
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AUTOPILOT CLIMB SCHEDULE FOR AIRPLANES EQUIPPED WITH EICAS VERSIONS 20.6 AND ON (POST-MOD. SB 145LEG-31-0009 OR EQUIPPED WITH AN EQUIVALENT MODIFICATION FACTORY INCORPORATED) OR ALTERNATIVE MANUAL CLIMB SCHEDULE
Page
REVISION 7
1-05-10
Code
23 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-05-10
Code
24 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 5000 AND 6000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
5000 ft ISA + oC
WEIGHT lb
6000 ft ISA + oC
-20
-10
0
10
20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
146 6 2
152 7 2
159 7 2
166 7 2
184 9 2
175 8 2
183 8 2
190 8 2
199 9 2
222 11 3
48000
FUEL LB DISTANCE NM TIME MIN
139 6 2
144 6 2
150 7 2
158 7 2
175 9 2
166 7 2
173 8 2
180 8 2
189 8 2
210 10 2
46000
FUEL LB DISTANCE NM TIME MIN
131 6 1
137 6 1
143 6 2
149 7 2
165 8 2
158 7 2
164 7 2
171 8 2
179 8 2
199 10 2
44000
FUEL LB DISTANCE NM TIME MIN
124 5 1
130 6 1
135 6 1
141 6 1
156 8 2
149 7 2
155 7 2
162 7 2
170 8 2
188 9 2
42000
FUEL LB DISTANCE NM TIME MIN
118 5 1
123 5 1
128 6 1
134 6 1
147 7 2
141 6 2
147 6 2
153 7 2
160 7 2
177 9 2
40000
FUEL LB DISTANCE NM TIME MIN
111 5 1
116 5 1
120 5 1
126 6 1
139 7 2
133 6 1
139 6 1
144 6 2
151 7 2
167 8 2
38000
FUEL LB DISTANCE NM TIME MIN
105 4 1
109 5 1
113 5 1
119 5 1
130 6 1
125 5 1
131 6 1
136 6 1
142 6 2
157 8 2
36000
FUEL LB DISTANCE NM TIME MIN
98 4 1
102 4 1
107 5 1
112 5 1
122 6 1
118 5 1
123 5 1
128 6 1
134 6 1
147 7 2
34000
FUEL LB DISTANCE NM TIME MIN
92 4 1
96 4 1
100 4 1
105 5 1
114 6 1
110 5 1
115 5 1
120 5 1
125 6 1
137 7 2
32000
FUEL LB DISTANCE NM TIME MIN
86 4 1
90 4 1
93 4 1
98 4 1
107 5 1
103 4 1
108 5 1
112 5 1
117 5 1
128 6 1
30000
FUEL LB DISTANCE NM TIME MIN
80 3 1
84 4 1
87 4 1
91 4 1
99 5 1
96 4 1
100 4 1
104 5 1
109 5 1
119 6 1
FOR ANTI ICE ON, INCREASE (%): Fuel 11 8 Distance 11 5 Time 11 5
8 3 3
14 18 18
20 26 26
11 11 11
9 6 6
8 3 3
15 19 19
20 26 26
Page
REVISION 7
1-05-10
Code
25 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 7000 AND 8000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
7000 ft ISA + oC
WEIGHT lb
8000 ft ISA + oC
-20
-10
0
10
20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
204 9 2
213 9 2
222 10 2
233 11 2
260 13 3
234 11 3
244 11 3
254 12 3
266 12 3
298 15 4
48000
FUEL LB DISTANCE NM TIME MIN
194 9 2
202 9 2
211 9 2
221 10 2
246 12 3
222 10 2
231 10 3
241 11 3
253 12 3
282 15 3
46000
FUEL LB DISTANCE NM TIME MIN
184 8 2
192 9 2
200 9 2
209 10 2
232 12 3
210 9 2
219 10 2
228 10 2
239 11 3
266 14 3
44000
FUEL LB DISTANCE NM TIME MIN
174 8 2
181 8 2
189 8 2
198 9 2
219 11 3
199 9 2
207 9 2
216 10 2
226 10 2
251 13 3
42000
FUEL LB DISTANCE NM TIME MIN
164 7 2
171 8 2
178 8 2
187 8 2
207 10 2
188 8 2
196 9 2
204 9 2
214 10 2
237 12 3
40000
FUEL LB DISTANCE NM TIME MIN
155 7 2
162 7 2
168 7 2
176 8 2
195 10 2
177 8 2
185 8 2
192 9 2
202 9 2
223 11 3
38000
FUEL LB DISTANCE NM TIME MIN
146 6 2
152 7 2
159 7 2
166 8 2
183 9 2
167 8 2
174 8 2
181 8 2
190 9 2
209 11 2
36000
FUEL LB DISTANCE NM TIME MIN
137 6 2
143 6 2
149 7 2
156 7 2
172 9 2
157 7 2
163 7 2
170 8 2
178 8 2
196 10 2
34000
FUEL LB DISTANCE NM TIME MIN
129 6 1
134 6 1
140 6 1
146 7 2
161 8 2
147 7 2
153 7 2
159 7 2
167 8 2
184 9 2
32000
FUEL LB DISTANCE NM TIME MIN
120 5 1
125 6 1
130 6 1
137 6 1
150 8 2
137 6 2
143 6 2
149 7 2
156 7 2
171 9 2
30000
FUEL LB DISTANCE NM TIME MIN
112 5 1
117 5 1
121 5 1
127 6 1
139 7 2
128 6 1
133 6 1
139 6 1
145 7 2
159 8 2
FOR ANTI ICE ON, INCREASE (%): Fuel 11 9 Distance 11 6 Time 11 6
8 4 4
15 19 19
20 27 27
11 11 11
9 7 7
8 4 4
15 20 20
21 28 27
Page
1-05-10
Code
26 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 9000 AND 10000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
9000 ft ISA + oC
WEIGHT lb
10000 ft ISA + oC
-20
-10
0
10
20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
263 12 3
274 13 3
286 13 3
300 14 3
336 18 4
293 14 3
306 14 3
319 15 4
335 16 4
376 20 5
48000
FUEL LB DISTANCE NM TIME MIN
250 12 3
260 12 3
271 13 3
285 13 3
318 17 4
278 13 3
290 14 3
302 14 3
317 15 3
355 19 4
46000
FUEL LB DISTANCE NM TIME MIN
237 11 3
247 11 3
257 12 3
270 13 3
300 16 4
263 12 3
275 13 3
286 14 3
300 14 3
335 18 4
44000
FUEL LB DISTANCE NM TIME MIN
224 10 3
233 11 3
243 11 3
255 12 3
283 15 3
249 12 3
260 12 3
271 13 3
284 14 3
316 17 4
42000
FUEL LB DISTANCE NM TIME MIN
211 10 2
220 10 2
230 11 3
241 11 3
267 14 3
235 11 3
245 12 3
256 12 3
268 13 3
298 16 4
40000
FUEL LB DISTANCE NM TIME MIN
200 9 2
208 10 2
217 10 2
227 11 2
251 13 3
222 10 3
231 11 3
241 11 3
253 12 3
281 15 3
38000
FUEL LB DISTANCE NM TIME MIN
188 9 2
196 9 2
204 9 2
214 10 2
236 12 3
209 10 2
218 10 2
227 11 2
238 11 3
264 14 3
36000
FUEL LB DISTANCE NM TIME MIN
176 8 2
184 8 2
192 9 2
201 9 2
221 12 3
196 9 2
205 10 2
213 10 2
223 11 2
247 13 3
34000
FUEL LB DISTANCE NM TIME MIN
165 8 2
172 8 2
179 8 2
188 9 2
207 11 2
184 9 2
192 9 2
200 9 2
209 10 2
231 12 3
32000
FUEL LB DISTANCE NM TIME MIN
154 7 2
161 7 2
168 8 2
176 8 2
193 10 2
172 8 2
179 8 2
187 9 2
195 9 2
215 12 3
30000
FUEL LB DISTANCE NM TIME MIN
144 7 2
150 7 2
156 7 2
163 8 2
180 9 2
160 7 2
167 8 2
174 8 2
182 9 2
200 11 2
FOR ANTI ICE ON, INCREASE (%): Fuel 11 10 Distance 11 8 Time 11 7
8 4 4
15 20 20
21 29 28
11 11 11
10 8 8
9 5 5
16 21 21
22 30 29
Page
REVISION 7
1-05-10
Code
27 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 11000 AND 12000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
11000 ft ISA + oC
WEIGHT lb
12000 ft ISA + oC
-20
-10
0
10
20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
323 16 4
337 16 4
352 17 4
370 18 4
416 23 5
354 18 4
370 18 4
386 19 4
406 21 5
458 26 6
48000
FUEL LB DISTANCE NM TIME MIN
307 15 4
320 15 4
333 16 4
350 17 4
393 22 5
336 17 4
351 17 4
366 18 4
384 19 4
433 25 5
46000
FUEL LB DISTANCE NM TIME MIN
290 14 3
303 15 3
316 15 4
332 16 4
371 21 5
318 16 4
332 16 4
346 17 4
364 18 4
409 23 5
44000
FUEL LB DISTANCE NM TIME MIN
275 13 3
287 14 3
299 14 3
314 15 3
350 19 4
301 15 3
314 16 4
327 16 4
344 17 4
386 22 5
42000
FUEL LB DISTANCE NM TIME MIN
260 12 3
271 13 3
282 14 3
296 15 3
330 18 4
284 14 3
297 15 3
309 15 3
325 16 4
363 21 4
40000
FUEL LB DISTANCE NM TIME MIN
245 12 3
255 12 3
266 13 3
279 14 3
311 17 4
268 13 3
280 14 3
292 14 3
306 15 3
342 19 4
38000
FUEL LB DISTANCE NM TIME MIN
230 11 3
240 12 3
250 12 3
263 13 3
292 16 4
252 12 3
263 13 3
274 14 3
288 15 3
321 18 4
36000
FUEL LB DISTANCE NM TIME MIN
216 10 2
226 11 3
235 11 3
247 12 3
273 15 3
237 12 3
247 12 3
258 13 3
270 14 3
300 17 4
34000
FUEL LB DISTANCE NM TIME MIN
203 10 2
211 10 2
220 11 2
231 11 3
256 14 3
222 11 3
231 11 3
241 12 3
253 13 3
281 16 3
32000
FUEL LB DISTANCE NM TIME MIN
189 9 2
197 9 2
206 10 2
216 11 2
238 13 3
207 10 2
216 11 2
225 11 3
236 12 3
262 15 3
30000
FUEL LB DISTANCE NM TIME MIN
176 8 2
184 9 2
191 9 2
201 10 2
221 12 3
193 9 2
201 10 2
210 10 2
220 11 2
243 14 3
FOR ANTI ICE ON, INCREASE (%): Fuel 11 10 Distance 11 9 Time 11 9
9 6 6
16 22 21
23 31 31
12 12 11
11 10 9
10 7 7
17 23 22
24 33 32
Page
1-05-10
Code
28 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 13000 AND 14000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
13000 ft ISA + oC
WEIGHT lb
14000 ft ISA + oC
-20
-10
0
10
20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
386 20 5
403 21 5
421 22 5
443 23 5
502 29 6
419 22 5
438 23 5
457 24 5
482 26 6
549 33 7
48000
FUEL LB DISTANCE NM TIME MIN
366 19 4
382 19 4
399 20 5
419 22 5
475 28 6
397 21 5
415 22 5
433 23 5
456 24 5
518 31 7
46000
FUEL LB DISTANCE NM TIME MIN
347 18 4
362 18 4
378 19 4
397 21 5
448 26 6
376 20 4
393 21 5
410 22 5
431 23 5
489 29 6
44000
FUEL LB DISTANCE NM TIME MIN
328 17 4
342 17 4
357 18 4
375 19 4
422 25 5
356 19 4
371 19 4
388 20 4
408 22 5
461 28 6
42000
FUEL LB DISTANCE NM TIME MIN
310 16 4
323 16 4
337 17 4
354 18 4
398 23 5
336 18 4
351 18 4
366 19 4
385 21 4
434 26 5
40000
FUEL LB DISTANCE NM TIME MIN
292 15 3
305 15 4
318 16 4
334 17 4
374 22 5
317 17 4
330 17 4
345 18 4
363 19 4
408 24 5
38000
FUEL LB DISTANCE NM TIME MIN
275 14 3
287 15 3
299 15 3
314 16 4
351 20 4
298 16 4
311 16 4
324 17 4
341 18 4
383 23 5
36000
FUEL LB DISTANCE NM TIME MIN
258 13 3
269 14 3
281 14 3
295 15 3
329 19 4
280 15 3
292 15 3
304 16 3
320 17 4
358 21 5
34000
FUEL LB DISTANCE NM TIME MIN
242 12 3
252 13 3
263 13 3
276 14 3
307 18 4
262 14 3
273 14 3
285 15 3
299 16 3
335 20 4
32000
FUEL LB DISTANCE NM TIME MIN
226 11 3
235 12 3
245 12 3
257 13 3
286 17 4
244 13 3
255 13 3
266 14 3
279 15 3
312 19 4
30000
FUEL LB DISTANCE NM TIME MIN
210 11 2
219 11 3
228 12 3
240 12 3
266 15 3
227 12 3
237 12 3
248 13 3
260 14 3
290 17 4
FOR ANTI ICE ON, INCREASE (%): Fuel 12 11 Distance 12 10 Time 12 10
10 9 8
18 24 23
26 36 35
12 12 12
12 11 11
11 10 9
19 26 25
28 39 37
Page
REVISION 7
1-05-10
Code
29 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 15000 AND 16000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
15000 ft ISA + oC
WEIGHT lb
16000 ft ISA + oC
-20
-10
0
10
20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
453 24 5
473 26 6
494 27 6
522 29 6
598 37 8
488 27 6
510 28 6
533 30 6
563 32 7
649 42 8
48000
FUEL LB DISTANCE NM TIME MIN
430 23 5
449 24 5
468 25 5
494 27 6
564 35 7
462 26 6
483 27 6
504 28 6
533 30 6
612 39 8
46000
FUEL LB DISTANCE NM TIME MIN
407 22 5
424 23 5
443 24 5
467 26 5
532 33 7
437 24 5
457 25 5
477 27 6
504 29 6
577 37 7
44000
FUEL LB DISTANCE NM TIME MIN
384 21 5
401 22 5
419 23 5
441 24 5
501 31 6
413 23 5
432 24 5
451 25 5
476 27 6
543 35 7
42000
FUEL LB DISTANCE NM TIME MIN
363 20 4
379 20 4
395 21 5
416 23 5
472 29 6
390 22 5
407 23 5
425 24 5
449 25 5
511 33 7
40000
FUEL LB DISTANCE NM TIME MIN
342 18 4
357 19 4
373 20 4
392 22 5
443 27 6
367 20 4
384 21 5
401 22 5
422 24 5
480 31 6
38000
FUEL LB DISTANCE NM TIME MIN
322 17 4
336 18 4
350 19 4
369 20 4
416 26 5
346 19 4
361 20 4
377 21 4
397 22 5
450 29 6
36000
FUEL LB DISTANCE NM TIME MIN
302 16 4
315 17 4
329 18 4
346 19 4
389 24 5
324 18 4
339 19 4
354 20 4
372 21 4
421 27 5
34000
FUEL LB DISTANCE NM TIME MIN
283 15 3
295 16 3
308 17 4
324 18 4
363 22 5
304 17 4
317 17 4
331 18 4
348 20 4
393 25 5
32000
FUEL LB DISTANCE NM TIME MIN
264 14 3
275 15 3
287 15 3
302 17 4
338 21 4
283 16 3
296 16 4
309 17 4
325 18 4
366 23 5
30000
FUEL LB DISTANCE NM TIME MIN
245 13 3
256 14 3
267 14 3
281 15 3
314 19 4
264 14 3
275 15 3
287 16 3
302 17 4
340 22 4
FOR ANTI ICE ON, INCREASE (%): Fuel 13 12 Distance 13 12 Time 13 11
12 11 10
21 29 28
31 42 40
13 14 13
13 13 12
13 13 12
23 33 31
33 46 44
Page
1-05-10
Code
30 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 17000 AND 18000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
17000 ft ISA + oC
WEIGHT lb
18000 ft ISA + oC
-20
-10
0
10
20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
523 30 6
547 31 7
572 33 7
605 35 7
702 47 9
559 33 7
585 34 7
611 36 7
648 39 8
758 52 10
48000
FUEL LB DISTANCE NM TIME MIN
495 28 6
518 30 6
541 31 6
572 34 7
662 44 9
529 31 7
553 32 7
578 34 7
613 37 7
713 49 9
46000
FUEL LB DISTANCE NM TIME MIN
469 27 6
490 28 6
512 29 6
541 32 6
623 41 8
500 29 6
523 31 6
547 32 7
579 35 7
671 46 9
44000
FUEL LB DISTANCE NM TIME MIN
443 25 5
463 26 6
483 28 6
511 30 6
586 39 8
473 28 6
494 29 6
516 30 6
547 33 7
631 43 8
42000
FUEL LB DISTANCE NM TIME MIN
418 24 5
436 25 5
456 26 5
482 28 6
551 36 7
446 26 6
466 27 6
487 29 6
515 31 6
593 40 8
40000
FUEL LB DISTANCE NM TIME MIN
393 22 5
411 23 5
429 24 5
453 26 5
517 34 7
420 24 5
439 26 5
458 27 6
485 29 6
556 38 7
38000
FUEL LB DISTANCE NM TIME MIN
370 21 5
386 22 5
404 23 5
426 25 5
485 32 6
395 23 5
412 24 5
431 25 5
456 27 5
521 35 7
36000
FUEL LB DISTANCE NM TIME MIN
347 20 4
363 21 4
379 22 4
400 23 5
454 30 6
370 22 5
387 23 5
404 24 5
427 26 5
487 33 6
34000
FUEL LB DISTANCE NM TIME MIN
325 18 4
339 19 4
354 20 4
374 22 4
423 28 6
346 20 4
362 21 4
378 22 5
399 24 5
455 31 6
32000
FUEL LB DISTANCE NM TIME MIN
303 17 4
317 18 4
331 19 4
349 20 4
394 26 5
323 19 4
338 20 4
353 21 4
372 22 4
423 29 6
30000
FUEL LB DISTANCE NM TIME MIN
282 16 3
294 17 4
307 17 4
324 19 4
366 24 5
300 17 4
314 18 4
328 19 4
346 21 4
392 26 5
FOR ANTI ICE ON, INCREASE (%): Fuel 14 13 Distance 14 13 Time 14 13
14 14 13
25 37 35
36 50 47
14 15 14
14 14 13
14 15 14
28 41 38
40 55 52
Page
REVISION 7
1-05-10
Code
31 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 19000 AND 20000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
19000 ft ISA + oC
WEIGHT lb
20000 ft ISA + oC
-20
-10
0
10
20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
596 36 8
623 37 8
652 39 8
693 43 8
815 57 11
632 39 8
662 41 8
692 43 9
737 47 9
874 63 12
48000
FUEL LB DISTANCE NM TIME MIN
564 34 7
589 35 7
616 37 7
655 41 8
767 54 10
598 37 8
626 39 8
655 40 8
697 44 9
822 59 11
46000
FUEL LB DISTANCE NM TIME MIN
533 32 7
557 33 7
582 35 7
618 38 8
721 51 10
565 35 7
591 36 7
618 38 8
658 42 8
772 56 11
44000
FUEL LB DISTANCE NM TIME MIN
503 30 6
526 32 6
550 33 7
583 36 7
678 47 9
533 33 7
558 34 7
584 36 7
620 39 8
725 52 10
42000
FUEL LB DISTANCE NM TIME MIN
474 28 6
496 30 6
518 31 6
550 34 7
636 45 9
503 31 6
526 32 7
550 34 7
584 37 7
680 49 9
40000
FUEL LB DISTANCE NM TIME MIN
446 27 6
467 28 6
488 29 6
517 32 6
596 42 8
473 29 6
495 30 6
518 32 6
549 35 7
637 46 9
38000
FUEL LB DISTANCE NM TIME MIN
420 25 5
439 26 5
458 28 6
486 30 6
558 39 8
445 27 6
465 28 6
486 30 6
516 33 6
597 43 8
36000
FUEL LB DISTANCE NM TIME MIN
393 23 5
411 25 5
430 26 5
455 28 6
522 36 7
417 25 5
436 27 5
456 28 6
483 30 6
557 40 8
34000
FUEL LB DISTANCE NM TIME MIN
368 22 5
385 23 5
402 24 5
425 26 5
487 34 7
390 24 5
408 25 5
426 26 5
452 28 6
519 37 7
32000
FUEL LB DISTANCE NM TIME MIN
343 20 4
359 21 4
375 22 5
397 24 5
453 31 6
364 22 5
380 23 5
398 24 5
421 26 5
483 34 7
30000
FUEL LB DISTANCE NM TIME MIN
319 19 4
334 20 4
349 21 4
369 23 4
420 29 6
338 21 4
353 21 4
370 23 5
391 25 5
448 32 6
FOR ANTI ICE ON, INCREASE (%): Fuel 15 14 Distance 15 15 Time 15 14
15 17 15
30 45 42
44 62 58
15 16 15
15 16 15
16 18 16
32 48 45
51 72 67
Page
1-05-10
Code
32 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 21000 AND 22000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
21000 ft ISA + oC
WEIGHT lb
22000 ft ISA + oC
-20
-10
0
10
20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
670 42 9
701 44 9
734 47 9
783 51 10
936 70 13
708 46 9
742 48 9
777 50 10
831 1002 56 77 11 14
48000
FUEL LB DISTANCE NM TIME MIN
633 40 8
663 42 8
694 44 9
740 48 9
879 65 12
669 43 9
701 45 9
734 48 9
784 52 10
940 72 13
46000
FUEL LB DISTANCE NM TIME MIN
598 38 8
626 39 8
655 41 8
698 45 9
825 61 11
632 41 8
662 43 8
693 45 9
740 49 9
882 67 12
44000
FUEL LB DISTANCE NM TIME MIN
565 35 7
591 37 7
618 39 8
658 43 8
774 57 11
596 38 8
624 40 8
653 42 8
697 46 9
827 63 12
42000
FUEL LB DISTANCE NM TIME MIN
532 33 7
557 35 7
582 37 7
619 40 8
726 54 10
562 36 7
588 38 7
615 40 8
656 44 8
774 59 11
40000
FUEL LB DISTANCE NM TIME MIN
501 31 6
524 33 7
548 35 7
582 38 7
680 50 9
528 34 7
553 36 7
579 37 7
616 41 8
725 55 10
38000
FUEL LB DISTANCE NM TIME MIN
470 29 6
492 31 6
514 32 6
547 35 7
636 47 9
496 32 6
519 33 7
543 35 7
578 38 7
677 51 9
36000
FUEL LB DISTANCE NM TIME MIN
441 28 6
461 29 6
482 30 6
512 33 6
594 44 8
465 30 6
486 31 6
509 33 6
541 36 7
632 48 9
34000
FUEL LB DISTANCE NM TIME MIN
412 26 5
431 27 5
451 28 6
478 31 6
553 41 8
435 28 6
455 29 6
476 31 6
506 33 6
588 44 8
32000
FUEL LB DISTANCE NM TIME MIN
384 24 5
402 25 5
420 26 5
446 29 6
514 38 7
405 26 5
424 27 5
443 28 6
471 31 6
547 41 8
30000
FUEL LB DISTANCE NM TIME MIN
357 22 5
374 23 5
391 24 5
414 27 5
476 35 7
376 24 5
394 25 5
412 26 5
438 29 6
506 38 7
FOR ANTI ICE ON, INCREASE (%): Fuel 15 15 Distance 16 16 Time 15 15
17 19 17
35 52 48
52 76 70
16 16 16
16 17 16
17 20 18
38 57 53
55 82 75
Page
REVISION 7
1-05-10
Code
33 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 23000 AND 24000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
23000 ft ISA + oC
WEIGHT lb -20
-10
0
10
24000 ft ISA + oC 20
-20
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
748 50 10
783 52 10
821 55 10
880 1073 60 85 11 15
789 54 11
827 56 11
867 59 11
933 1151 66 94 12 17
48000
FUEL LB DISTANCE NM TIME MIN
707 47 9
740 49 10
775 51 10
830 1006 57 79 11 14
745 51 10
781 53 10
818 56 10
879 1077 62 88 11 16
46000
FUEL LB DISTANCE NM TIME MIN
667 44 9
698 46 9
731 49 9
783 54 10
942 74 13
703 48 9
736 50 10
772 52 10
828 1007 58 82 11 15
44000
FUEL LB DISTANCE NM TIME MIN
629 41 8
658 43 8
689 46 9
737 50 9
882 69 13
663 45 9
694 47 9
727 49 9
779 55 10
942 76 14
42000
FUEL LB DISTANCE NM TIME MIN
592 39 8
620 41 8
649 43 8
693 47 9
826 65 12
624 42 8
653 44 9
684 46 9
733 51 9
881 71 13
40000
FUEL LB DISTANCE NM TIME MIN
557 37 7
583 38 8
610 40 8
651 44 8
772 60 11
586 40 8
614 41 8
643 44 8
688 48 9
823 66 12
38000
FUEL LB DISTANCE NM TIME MIN
523 34 7
547 36 7
573 38 7
611 42 8
721 56 10
550 37 7
576 39 7
603 41 8
645 45 8
768 62 11
36000
FUEL LB DISTANCE NM TIME MIN
490 32 6
513 34 7
537 35 7
572 39 7
672 52 10
515 35 7
540 36 7
565 38 7
603 42 8
715 57 10
34000
FUEL LB DISTANCE NM TIME MIN
458 30 6
479 31 6
501 33 6
534 36 7
626 49 9
481 32 6
504 34 7
528 36 7
563 39 7
665 53 10
32000
FUEL LB DISTANCE NM TIME MIN
427 28 6
446 29 6
467 31 6
497 34 6
581 45 8
449 30 6
470 31 6
492 33 6
524 36 7
617 49 9
30000
FUEL LB DISTANCE NM TIME MIN
396 26 5
415 27 5
434 28 5
462 31 6
538 42 8
417 28 6
436 29 6
457 31 6
487 34 6
571 46 8
FOR ANTI ICE ON, INCREASE (%): Fuel 16 16 Distance 17 17 Time 16 16
18 21 20
42 65 59
59 90 82
17 17 17
17 18 17
20 23 21
48 74 68
61 95 86
Page
1-05-10
Code
34 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 25000 AND 26000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
25000 ft ISA + oC
WEIGHT lb -19
-10
0
10
26000 ft ISA + oC 20
-18
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
837 58 11
873 61 12
916 64 12
987 1236 72 104 13 18
881 63 12
915 66 12
960 1037 1312 69 77 114 13 14 20
48000
FUEL LB DISTANCE NM TIME MIN
790 55 11
824 57 11
864 60 11
930 1154 67 97 12 17
831 59 11
863 62 12
905 65 12
976 1223 72 106 13 18
46000
FUEL LB DISTANCE NM TIME MIN
744 52 10
776 54 10
814 57 11
875 1078 63 90 11 16
783 56 11
813 58 11
853 61 11
918 1140 68 98 12 17
44000
FUEL LB DISTANCE NM TIME MIN
701 49 9
731 51 10
766 53 10
823 1006 59 84 11 15
737 52 10
765 54 10
802 57 11
863 1064 64 91 11 16
42000
FUEL LB DISTANCE NM TIME MIN
660 46 9
688 48 9
721 50 9
773 56 10
939 78 14
693 49 9
720 51 10
754 54 10
810 60 11
992 85 15
40000
FUEL LB DISTANCE NM TIME MIN
620 43 8
646 45 9
677 47 9
726 52 10
877 73 13
651 46 9
676 48 9
708 50 9
760 56 10
924 79 14
38000
FUEL LB DISTANCE NM TIME MIN
581 40 8
606 42 8
635 44 8
680 49 9
817 68 12
610 43 8
634 45 8
664 47 9
712 52 9
861 73 13
36000
FUEL LB DISTANCE NM TIME MIN
544 38 7
568 39 7
595 41 8
636 46 8
760 63 11
571 40 8
593 42 8
621 44 8
665 49 9
800 68 12
34000
FUEL LB DISTANCE NM TIME MIN
508 35 7
530 37 7
555 38 7
594 42 8
706 58 10
533 38 7
554 39 7
580 41 8
620 45 8
743 63 11
32000
FUEL LB DISTANCE NM TIME MIN
474 33 6
494 34 6
517 36 7
552 39 7
655 54 10
497 35 7
515 36 7
540 38 7
577 42 8
688 58 10
30000
FUEL LB DISTANCE NM TIME MIN
440 30 6
458 31 6
480 33 6
513 37 7
606 50 9
461 32 6
478 34 6
501 35 7
535 39 7
636 54 9
FOR ANTI ICE ON, INCREASE (%): Fuel 17 18 Distance 18 19 Time 17 17
21 24 22
52 82 75
-
18 19 18
18 19 18
22 26 24
66 93
95 -
Page
REVISION 7
1-05-10
Code
35 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 27000 AND 28000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
27000 ft ISA + oC
WEIGHT lb
0
10
28000 ft ISA + oC
-17
-10
20
-16
-10
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
923 67 13
954 1001 1081 1378 70 74 82 122 13 13 15 21
965 72 13
994 1043 1126 1443 74 78 87 131 14 14 15 22
48000
FUEL LB DISTANCE NM TIME MIN
869 63 12
899 66 12
943 1017 1283 69 77 113 13 14 19
909 68 13
935 70 13
982 1058 1341 74 82 121 13 14 21
46000
FUEL LB DISTANCE NM TIME MIN
818 60 11
846 62 11
888 65 12
956 1195 72 105 13 18
855 64 12
880 66 12
923 69 12
994 1247 77 112 14 19
44000
FUEL LB DISTANCE NM TIME MIN
770 56 11
796 58 11
835 61 11
898 1113 68 98 12 17
804 60 11
827 61 11
868 65 12
933 1161 72 104 13 18
42000
FUEL LB DISTANCE NM TIME MIN
724 52 10
748 54 10
784 57 10
843 1037 63 91 11 16
755 56 10
777 58 11
815 61 11
875 1080 67 96 12 16
40000
FUEL LB DISTANCE NM TIME MIN
679 49 9
702 51 9
736 53 10
790 59 11
965 84 15
708 52 10
729 54 10
764 57 10
820 1005 63 89 11 15
38000
FUEL LB DISTANCE NM TIME MIN
637 46 9
658 48 9
690 50 9
740 55 10
898 78 13
664 49 9
683 50 9
716 53 10
767 59 10
935 83 14
36000
FUEL LB DISTANCE NM TIME MIN
596 43 8
615 44 8
645 47 9
691 52 9
835 72 13
620 46 9
638 47 9
669 49 9
717 55 10
868 77 13
34000
FUEL LB DISTANCE NM TIME MIN
556 40 8
574 41 8
602 43 8
644 48 9
775 67 12
579 43 8
595 44 8
624 46 8
668 51 9
805 71 12
32000
FUEL LB DISTANCE NM TIME MIN
517 37 7
535 38 7
560 40 7
599 45 8
717 62 11
539 39 7
554 41 8
581 43 8
621 47 8
745 65 11
30000
FUEL LB DISTANCE NM TIME MIN
480 34 7
496 36 7
520 37 7
556 41 7
662 57 10
500 37 7
514 38 7
539 40 7
576 44 8
688 60 10
FOR ANTI ICE ON, INCREASE (%): Fuel 18 19 Distance 19 20 Time 18 19
23 27 25
73 -
-
19 20 19
19 21 19
24 28 26
72 -
-
Page
1-05-10
Code
36 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 29000 AND 30000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
29000 ft ISA + oC
WEIGHT lb -15
-10
0
10
30000 ft ISA + oC 20
-14
-10
0
10
20
50000
FUEL LB 1009 1034 1086 1172 1508 DISTANCE NM 77 79 83 93 139 TIME MIN 14 14 15 16 23
1054 1074 1128 1219 1575 82 84 88 99 149 15 15 16 17 25
48000
FUEL LB DISTANCE NM TIME MIN
949 72 13
972 1021 1101 1399 74 78 87 129 14 14 15 22
990 1009 1060 1143 1459 77 79 83 92 137 14 14 15 16 23
46000
FUEL LB DISTANCE NM TIME MIN
892 68 13
914 70 13
959 1033 1300 73 81 119 13 14 20
930 72 13
948 74 13
995 1072 1354 78 86 126 14 15 21
44000
FUEL LB DISTANCE NM TIME MIN
838 64 12
859 65 12
901 69 12
969 1209 76 110 13 19
873 68 12
890 69 13
934 1005 1257 73 80 117 13 14 20
42000
FUEL LB DISTANCE NM TIME MIN
787 60 11
806 61 11
846 64 12
908 1124 71 102 12 17
819 63 12
835 64 12
876 68 12
941 1168 75 108 13 18
40000
FUEL LB DISTANCE NM TIME MIN
738 56 10
756 57 10
793 60 11
851 1045 66 95 12 16
767 59 11
782 60 11
821 63 11
881 1085 70 100 12 17
38000
FUEL LB DISTANCE NM TIME MIN
691 52 10
707 53 10
742 56 10
795 62 11
971 88 15
718 55 10
732 56 10
768 59 11
823 1007 65 92 11 16
36000
FUEL LB DISTANCE NM TIME MIN
646 49 9
661 50 9
693 52 9
743 58 10
901 81 14
671 51 9
684 52 10
717 55 10
768 61 11
934 86 14
34000
FUEL LB DISTANCE NM TIME MIN
602 45 8
616 46 9
646 49 9
692 54 9
835 75 13
625 48 9
637 49 9
668 51 9
715 57 10
865 79 13
32000
FUEL LB DISTANCE NM TIME MIN
560 42 8
573 43 8
601 45 8
643 50 9
772 69 12
581 44 8
592 45 8
621 48 9
665 52 9
800 73 12
30000
FUEL LB DISTANCE NM TIME MIN
519 39 7
532 40 7
557 42 8
596 46 8
713 64 11
539 41 8
549 42 8
576 44 8
616 48 9
737 67 11
FOR ANTI ICE ON, INCREASE (%): Fuel 20 20 Distance 21 21 Time 20 20
25 30 27
78 -
-
20 21 20
20 22 21
26 32 29
75 -
-
Page
REVISION 7
1-05-10
Code
37 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 31000 AND 32000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
31000 ft ISA + oC
WEIGHT lb -13
-10
0
10
32000 ft ISA + oC 20
-12
-10
0
10
20
50000
FUEL LB 1098 1114 1170 1267 1645 DISTANCE NM 87 89 94 105 158 TIME MIN 16 16 16 18 26
1142 1153 1212 1316 1720 93 94 99 111 169 17 17 17 19 28
48000
FUEL LB 1031 1046 1098 1187 1521 DISTANCE NM 82 83 87 98 146 TIME MIN 15 15 15 17 24
1071 1082 1136 1231 1587 87 87 92 103 155 16 16 16 18 26
46000
FUEL LB DISTANCE NM TIME MIN
967 77 14
981 1030 1112 1409 78 82 91 134 14 14 16 22
1004 1014 1065 1152 1467 81 82 86 96 143 15 15 15 17 24
44000
FUEL LB DISTANCE NM TIME MIN
907 72 13
921 73 13
966 1041 1307 76 85 124 14 15 21
942 76 14
951 76 14
998 1078 1358 80 90 131 14 15 22
42000
FUEL LB DISTANCE NM TIME MIN
851 67 12
863 68 12
906 71 13
975 1212 79 114 14 19
882 71 13
891 71 13
935 1008 1258 75 84 121 13 14 20
40000
FUEL LB DISTANCE NM TIME MIN
796 62 11
808 63 11
848 67 12
911 1125 74 106 13 18
825 66 12
833 67 12
875 70 12
942 1166 78 112 13 19
38000
FUEL LB DISTANCE NM TIME MIN
745 58 11
756 59 11
793 62 11
851 1043 69 98 12 16
772 61 11
779 62 11
817 65 12
879 1081 72 103 13 17
36000
FUEL LB DISTANCE NM TIME MIN
695 54 10
705 55 10
740 58 10
794 64 11
967 90 15
720 57 10
727 58 10
763 61 11
819 1001 67 95 12 16
34000
FUEL LB DISTANCE NM TIME MIN
648 50 9
657 51 9
689 54 10
739 60 10
895 83 14
671 53 10
677 54 10
710 56 10
762 63 11
925 88 15
32000
FUEL LB DISTANCE NM TIME MIN
602 47 9
611 47 9
641 50 9
686 55 10
827 77 13
623 49 9
629 50 9
660 52 9
708 58 10
854 81 14
30000
FUEL LB DISTANCE NM TIME MIN
558 43 8
566 44 8
594 46 8
635 51 9
762 70 12
577 45 8
583 46 8
611 48 9
655 53 9
787 74 12
FOR ANTI ICE ON, INCREASE (%): Fuel 21 21 Distance 22 23 Time 21 21
28 35 32
81 -
-
21 23 22
22 23 22
30 39 36
77 -
-
Page
1-05-10
Code
38 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 33000 AND 34000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
33000 ft ISA + oC
WEIGHT lb -10
-5
0
10
34000 ft ISA + oC 20
-9
-5
0
10
20
50000
FUEL LB 1194 1223 1254 1366 1799 DISTANCE NM 99 101 104 117 181 TIME MIN 18 18 18 20 30
1243 1267 1299 1418 1881 105 107 110 125 194 19 19 19 21 32
48000
FUEL LB 1118 1146 1174 1276 1655 DISTANCE NM 92 94 97 109 165 TIME MIN 16 17 17 19 27
1163 1186 1215 1323 1726 98 100 102 116 176 17 17 18 20 29
46000
FUEL LB 1048 1073 1100 1192 1527 DISTANCE NM 86 88 90 102 151 TIME MIN 15 16 16 17 25
1088 1109 1137 1235 1588 91 93 95 107 161 16 16 17 18 26
44000
FUEL LB DISTANCE NM TIME MIN
981 1005 1030 1115 1411 80 82 84 95 139 14 15 15 16 23
1018 1038 1064 1153 1464 85 87 89 100 147 15 15 15 17 24
42000
FUEL LB DISTANCE NM TIME MIN
918 75 13
941 77 14
964 1041 1305 79 88 128 14 15 21
952 79 14
971 81 14
995 1076 1352 83 93 135 14 16 22
40000
FUEL LB DISTANCE NM TIME MIN
859 70 13
880 72 13
902 73 13
972 1208 82 118 14 20
890 74 13
907 75 13
929 1004 1250 77 86 124 13 15 21
38000
FUEL LB DISTANCE NM TIME MIN
802 65 12
822 67 12
842 68 12
907 1118 76 109 13 18
831 68 12
847 70 12
868 72 13
935 1155 80 114 14 19
36000
FUEL LB DISTANCE NM TIME MIN
749 60 11
767 62 11
785 64 11
845 1034 71 100 12 17
774 64 11
789 65 12
809 67 12
871 1068 74 105 13 17
34000
FUEL LB DISTANCE NM TIME MIN
697 56 10
714 57 10
731 59 10
786 66 11
956 92 15
720 59 11
734 60 11
752 62 11
809 69 12
986 97 16
32000
FUEL LB DISTANCE NM TIME MIN
647 52 9
663 53 10
679 55 10
729 61 10
882 85 14
669 55 10
682 56 10
698 57 10
750 64 11
909 89 15
30000
FUEL LB DISTANCE NM TIME MIN
599 48 9
614 49 9
629 50 9
674 56 10
812 78 13
619 50 9
631 51 9
646 53 9
694 59 10
836 81 14
FOR ANTI ICE ON, INCREASE (%): Fuel 22 22 Distance 24 24 Time 23 23
33 43 40
74 -
-
23 26 24
25 29 27
36 50 46
79 -
-
Page
REVISION 7
1-05-10
Code
39 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 35000 AND 36000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
35000 ft ISA + oC
WEIGHT lb -8
-5
0
10
36000 ft ISA + oC 20
-7
-5
0
10
20
50000
FUEL LB 1296 1315 1348 1474 1971 DISTANCE NM 112 114 117 132 208 TIME MIN 20 20 20 22 34
1355 1368 1402 1533 2069 120 121 124 141 223 21 21 21 24 36
48000
FUEL LB 1210 1228 1259 1372 1801 DISTANCE NM 104 105 108 122 188 TIME MIN 18 18 19 21 31
1262 1275 1306 1424 1881 111 112 115 130 201 19 20 20 22 33
46000
FUEL LB 1131 1148 1176 1278 1652 DISTANCE NM 97 98 101 113 171 TIME MIN 17 17 17 19 28
1177 1189 1218 1324 1720 103 104 107 120 182 18 18 18 20 30
44000
FUEL LB 1057 1072 1099 1192 1520 DISTANCE NM 90 91 94 105 156 TIME MIN 16 16 16 18 26
1098 1109 1136 1233 1578 95 96 99 111 165 17 17 17 19 27
42000
FUEL LB DISTANCE NM TIME MIN
987 1002 1027 1111 1401 84 85 87 98 143 15 15 15 17 23
1025 1035 1060 1148 1451 89 89 92 103 151 16 16 16 17 25
40000
FUEL LB DISTANCE NM TIME MIN
922 78 14
935 79 14
958 1036 1293 81 91 131 14 15 22
956 82 14
965 83 15
989 1068 1337 85 95 138 15 16 23
38000
FUEL LB DISTANCE NM TIME MIN
860 72 13
872 73 13
894 75 13
964 1194 84 120 14 20
890 76 13
899 77 14
921 79 14
994 1232 88 127 15 21
36000
FUEL LB DISTANCE NM TIME MIN
801 67 12
813 68 12
833 70 12
897 1102 78 110 13 18
829 71 12
837 71 13
857 73 13
924 1136 82 116 14 19
34000
FUEL LB DISTANCE NM TIME MIN
745 62 11
756 63 11
774 65 11
833 1016 72 101 12 17
770 66 12
777 66 12
796 68 12
857 1047 76 106 13 18
32000
FUEL LB DISTANCE NM TIME MIN
691 57 10
701 58 10
718 60 10
772 67 11
936 93 15
714 61 11
721 61 11
738 63 11
794 70 12
963 97 16
30000
FUEL LB DISTANCE NM TIME MIN
639 53 9
648 54 10
664 55 10
713 61 11
860 85 14
660 56 10
666 56 10
683 58 10
733 64 11
885 89 15
FOR ANTI ICE ON, INCREASE (%): Fuel 24 27 Distance 28 33 Time 27 31
36 51 48
76 -
-
27 33 31
28 35 33
37 54 50
73 -
-
Page
1-05-10
Code
40 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 37000 AND 38000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
37000 ft ISA + oC
WEIGHT lb -8
-5
0
38000 ft ISA + oC
10
20
50000
FUEL LB 1409 1430 1466 1604 DISTANCE NM 128 130 134 152 TIME MIN 22 23 23 25
-8
-5
0
10
20
-
1485 1507 1544 1695 140 142 146 166 24 25 25 28
-
48000
FUEL LB 1308 1328 1361 1484 1980 DISTANCE NM 118 120 123 139 217 TIME MIN 21 21 21 23 35
1372 1392 1426 1559 128 130 133 151 22 22 23 25
-
46000
FUEL LB 1217 1235 1266 1377 1800 DISTANCE NM 109 111 114 128 195 TIME MIN 19 19 20 21 32
1271 1289 1321 1439 118 119 122 138 20 21 21 23
-
44000
FUEL LB 1133 1150 1178 1278 1644 DISTANCE NM 101 102 105 118 177 TIME MIN 18 18 18 20 29
1179 1197 1226 1332 1730 108 110 113 127 192 19 19 19 21 31
42000
FUEL LB 1055 1071 1097 1188 1508 DISTANCE NM 93 95 97 109 160 TIME MIN 16 17 17 18 26
1095 1112 1139 1234 1578 100 101 104 116 173 17 18 18 20 28
40000
FUEL LB DISTANCE NM TIME MIN
983 87 15
997 1022 1104 1386 88 90 101 146 15 16 17 24
1018 1033 1058 1145 1444 92 94 96 107 157 16 16 16 18 26
38000
FUEL LB DISTANCE NM TIME MIN
914 80 14
928 81 14
951 1026 1275 83 93 134 14 16 22
946 85 15
960 86 15
983 1062 1324 89 99 143 15 17 23
36000
FUEL LB DISTANCE NM TIME MIN
850 74 13
863 75 13
884 77 13
952 1173 86 122 15 20
878 79 14
891 80 14
913 82 14
984 1216 91 130 15 21
34000
FUEL LB DISTANCE NM TIME MIN
789 69 12
801 70 12
820 71 12
883 1080 79 112 13 18
814 73 13
826 74 13
846 75 13
911 1117 84 119 14 19
32000
FUEL LB DISTANCE NM TIME MIN
731 63 11
742 64 11
760 66 11
817 73 12
993 102 17
753 67 12
764 68 12
783 70 12
842 1025 77 108 13 18
30000
FUEL LB DISTANCE NM TIME MIN
675 58 10
685 59 10
702 61 11
754 67 11
911 94 15
695 61 11
705 62 11
723 64 11
776 71 12
939 99 16
FOR ANTI ICE ON, INCREASE (%): Fuel 27 29 Distance 32 37 Time 31 35
34 50 47
70 -
-
25 30 29
27 36 34
35 53 50
64 -
-
Page
REVISION 7
1-05-10
Code
41 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 39000 AND 40000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
39000 ft ISA + oC
WEIGHT lb -8
0
10
20
-8
-5
0
10
20
- 1646 - 163 28
50000
FUEL LB DISTANCE NM TIME MIN
-
-
-
-
-
-
-
48000
FUEL LB 1449 1470 1506 1655 DISTANCE NM 141 143 146 167 TIME MIN 24 25 25 28
-
-
-
-
-
-
46000
FUEL LB 1334 1353 1387 1516 DISTANCE NM 128 130 133 151 TIME MIN 22 22 23 25
-
1414 1434 1469 142 144 147 24 25 25
-
-
44000
FUEL LB 1232 1250 1281 1395 DISTANCE NM 117 119 122 137 TIME MIN 20 20 21 23
-
1296 1314 1346 1474 128 130 133 151 22 22 23 25
-
42000
FUEL LB 1141 1157 1186 1287 1667 DISTANCE NM 107 109 112 125 190 TIME MIN 19 19 19 21 31
1193 1210 1240 1351 116 118 121 137 20 20 21 23
-
40000
FUEL LB 1057 1072 1099 1190 1515 DISTANCE NM 99 100 103 115 170 TIME MIN 17 17 18 19 28
1101 1117 1144 1243 1608 106 108 110 124 189 18 19 19 21 30
38000
FUEL LB DISTANCE NM TIME MIN
980 91 16
994 1018 1101 1382 92 94 105 154 16 16 18 25
1017 1032 1057 1145 1454 97 99 101 113 168 17 17 17 19 27
36000
FUEL LB DISTANCE NM TIME MIN
908 84 15
921 85 15
944 1018 1265 87 97 139 15 16 23
940 89 16
954 91 16
977 1056 1323 93 104 151 16 17 24
34000
FUEL LB DISTANCE NM TIME MIN
840 77 13
853 78 14
873 80 14
941 1158 89 126 15 21
869 82 14
881 83 14
903 85 15
974 1206 95 136 16 22
32000
FUEL LB DISTANCE NM TIME MIN
777 71 12
788 72 13
807 74 13
869 1061 82 115 14 19
802 75 13
813 76 13
833 78 13
897 1101 87 123 15 20
30000
FUEL LB DISTANCE NM TIME MIN
716 65 11
727 66 11
744 67 12
800 75 13
970 104 17
738 69 12
749 70 12
767 71 12
825 1004 79 111 13 18
FOR ANTI ICE ON, INCREASE (%): Fuel 25 28 Distance 32 39 Time 31 36
36 57 53
-
-
24 31 29
29 42 40
33 53 50
Page
1-05-10
-
-5
40000 ft ISA + oC
-
Code
42 08
REVISION 7
-
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE: SEA LEVEL TO 41000 FT SPEED SCHEDULE:
240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 260 KIAS AT 12000 FT, MAINTAINING 260 KIAS UP TO 22800 FT AND M = 0.60 ABOVE 22800 FT. CRUISE CONFIGURATION BLEED: OPEN
41000 ft ISA + oC
WEIGHT lb -8
-5
0
10
20
50000
FUEL LB DISTANCE NM TIME MIN
-
-
-
-
-
48000
FUEL LB DISTANCE NM TIME MIN
-
-
-
-
-
46000
FUEL LB DISTANCE NM TIME MIN
-
-
-
-
-
44000
FUEL LB 1378 1398 1431 DISTANCE NM 143 145 149 TIME MIN 25 25 25
-
-
42000
FUEL LB 1257 1275 1306 1432 DISTANCE NM 128 130 133 152 TIME MIN 22 22 23 25
-
40000
FUEL LB 1153 1169 1198 1307 DISTANCE NM 116 117 120 136 TIME MIN 20 20 20 23
-
38000
FUEL LB 1060 1076 1102 1197 DISTANCE NM 105 107 109 123 TIME MIN 18 18 19 20
-
36000
FUEL LB DISTANCE NM TIME MIN
977 96 17
991 1015 1100 1395 97 100 112 166 17 17 19 27
34000
FUEL LB DISTANCE NM TIME MIN
900 88 15
913 89 15
935 1011 1263 91 102 148 16 17 24
32000
FUEL LB DISTANCE NM TIME MIN
829 80 14
841 81 14
861 83 14
929 1147 93 133 16 22
30000
FUEL LB DISTANCE NM TIME MIN
762 73 13
773 74 13
792 76 13
853 1043 85 120 14 19
FOR ANTI ICE ON, INCREASE (%): Fuel 25 27 Distance 33 40 Time 32 38
34 57 54
-
-
Page
REVISION 7
1-05-10
Code
43 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-05-10
Code
44 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
CRUISE MANEUVER CAPABILITY
52900 lb
20000 ft
48500 lb
44100 lb 25000 ft 139700 lb
35300 lb 30000 ft 30900 lb
35000 ft
26500 lb
39000 ft
135BJFAA004 - 08NOV2004
41000 ft
0.2
0.3
0.4
0.5
MACH
0.6
0.7
0.8
1.0 0.9
2.0 1.0
3.0 1.1
4.0 1.2
LOAD FACTOR Page
REVISION 7
1-05-15
Code
1 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-05-15
Code
2 08
REVISION 4
AIRPLANE OPERATIONS MANUAL
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
CRUISE TABLES The long range cruise and maximum speed cruise tables show N1, fuel flow, indicated airspeed, true airspeed, indicated Mach number, buffet margin and specific range. Data are presented for various weights and pressure altitudes. In the long range cruise schedule, all engines operating or one engine inoperative, the airplane is flown at a speed corresponding to a specific range equal to 99% of maximum specific range. It is used when range is the principal factor. In the maximum speed schedule, the airplane is flown in a speed resulting from maximum cruise power setting. It is used when minimum flight time is desired. Thrust selection in cruise condition is adjusted to CRZ mode. The climb to cruise transition should be made as follows: - After reaching the cruise level, allow the airplane to accelerate past 0.60M, before selecting cruise mode. - When in cruise mode, adjust thrust to keep N1 or cruise speed constant (whichever occurs first). The associated conditions are: - Flaps .................................... UP - Gear..................................... UP - Bleeds.................................. OPEN - Anti-Ice................................. OFF
Page
REVISION 4
1-05-15
Code
3 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
LONG RANGE CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE : 5000 FT TO 18000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000 18000
50000
N1 % 64.8 69.7 70.2 70.7 71.2 71.8 72.4 72.9 73.5 74.2 F FLOW lb/H/ENG 1227 1242 1229 1217 1206 1196 1186 1178 1170 1162 IAS KT 250 260 259 257 256 256 255 254 253 252 TAS KT 268 300 303 306 310 313 317 320 324 328 INDICATED MACH 0.413 0.470 0.476 0.483 0.490 0.498 0.506 0.514 0.522 0.530 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.55 2.51 SR NM/lb 0.109 0.121 0.123 0.126 0.128 0.131 0.133 0.136 0.139 0.141
48000
N1 % 64.4 68.9 69.4 69.9 70.4 71.0 71.5 72.1 72.7 73.3 F FLOW lb/H/ENG 1211 1202 1191 1180 1166 1155 1145 1136 1127 1119 IAS KT 250 256 255 254 252 251 250 249 248 248 TAS KT 268 295 298 302 305 308 311 315 319 323 INDICATED MACH 0.413 0.462 0.469 0.476 0.483 0.490 0.497 0.505 0.513 0.521 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.54 SR NM/lb 0.111 0.123 0.125 0.128 0.131 0.133 0.136 0.139 0.141 0.144
46000
N1 % 64.0 68.1 68.6 69.1 69.6 70.2 70.7 71.3 71.8 72.4 F FLOW lb/H/ENG 1195 1161 1149 1137 1126 1116 1106 1097 1086 1077 IAS KT 250 251 250 249 248 247 246 245 244 243 TAS KT 268 290 293 296 300 303 307 310 313 317 INDICATED MACH 0.413 0.454 0.461 0.468 0.475 0.482 0.490 0.497 0.504 0.512 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.112 0.125 0.128 0.130 0.133 0.136 0.139 0.141 0.144 0.147
44000
N1 % 63.6 67.2 67.7 68.3 68.8 69.3 69.8 70.4 71.0 71.5 F FLOW lb/H/ENG 1180 1122 1109 1097 1085 1074 1064 1055 1046 1037 IAS KT 250 247 246 245 244 243 242 241 240 239 TAS KT 268 285 288 291 294 298 301 305 308 312 INDICATED MACH 0.413 0.447 0.453 0.459 0.466 0.473 0.480 0.488 0.496 0.503 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.114 0.127 0.130 0.133 0.136 0.138 0.141 0.144 0.147 0.150
42000
N1 % 63.4 66.3 66.9 67.4 67.9 68.4 68.9 69.5 70.0 70.6 F FLOW lb/H/ENG 1158 1085 1073 1058 1046 1034 1023 1013 1004 995 IAS KT 249 243 242 240 239 238 237 236 235 234 TAS KT 267 280 284 286 289 292 295 299 302 306 INDICATED MACH 0.411 0.439 0.446 0.451 0.458 0.464 0.471 0.479 0.486 0.494 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.115 0.129 0.132 0.135 0.138 0.141 0.144 0.147 0.150 0.154
Page
1-05-15
Code
4 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
LONG RANGE CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE : 5000 FT TO 18000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000 18000
40000
N1 % 62.4 65.3 65.9 66.4 67.0 67.5 68.0 68.5 69.1 69.6 F FLOW lb/H/ENG 1121 1045 1032 1020 1008 997 984 974 964 954 IAS KT 244 238 237 236 235 234 232 231 230 229 TAS KT 262 275 278 281 284 287 290 293 296 300 INDICATED MACH 0.403 0.431 0.437 0.443 0.450 0.457 0.463 0.469 0.477 0.484 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.117 0.132 0.135 0.138 0.141 0.144 0.147 0.150 0.154 0.157
38000
N1 % 61.4 64.2 64.8 65.4 66.0 66.5 67.1 67.6 68.1 68.6 F FLOW lb/H/ENG 1084 1006 992 980 968 957 946 935 926 915 IAS KT 240 233 232 231 230 229 228 227 226 225 TAS KT 258 270 272 275 278 281 284 287 291 294 INDICATED MACH 0.396 0.422 0.428 0.434 0.441 0.447 0.454 0.461 0.468 0.474 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.119 0.134 0.137 0.140 0.144 0.147 0.150 0.154 0.157 0.161
36000
N1 % 60.3 63.1 63.7 64.3 64.9 65.4 66.0 66.6 67.1 67.6 F FLOW lb/H/ENG 1045 968 954 941 929 917 906 896 885 876 IAS KT 235 229 227 226 225 224 223 222 221 220 TAS KT 253 264 267 269 272 275 278 281 284 288 INDICATED MACH 0.388 0.414 0.420 0.425 0.431 0.438 0.444 0.451 0.458 0.465 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.121 0.137 0.140 0.143 0.147 0.150 0.154 0.157 0.161 0.164
34000
N1 % 59.2 62.0 62.6 63.1 63.7 64.3 64.9 65.4 66.0 66.6 F FLOW lb/H/ENG 1008 932 917 903 890 878 867 856 846 836 IAS KT 230 224 223 221 220 219 218 217 216 215 TAS KT 247 259 261 264 266 269 272 275 278 281 INDICATED MACH 0.381 0.406 0.411 0.417 0.422 0.428 0.434 0.441 0.448 0.454 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.123 0.139 0.143 0.146 0.150 0.153 0.157 0.161 0.164 0.168
32000
N1 % 58.1 60.7 61.4 62.0 62.5 63.1 63.6 64.2 64.8 65.4 F FLOW lb/H/ENG 971 893 880 867 853 840 829 818 807 797 IAS KT 226 219 218 217 215 214 213 212 211 210 TAS KT 242 253 256 258 261 263 266 269 272 275 INDICATED MACH 0.373 0.397 0.403 0.408 0.413 0.419 0.425 0.431 0.437 0.444 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.125 0.142 0.145 0.149 0.153 0.157 0.160 0.164 0.168 0.172
Page
REVISION 4
1-05-15
Code
5 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
LONG RANGE CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE : 19000 FT TO 28000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 19000 20000 21000 22000 23000 24000 25000 26000 27000 28000
50000
N1 % 74.9 75.6 76.3 77.0 77.8 78.6 79.4 80.1 80.7 81.4 F FLOW lb/H/ENG 1155 1149 1143 1138 1134 1130 1127 1124 1122 1121 IAS KT 251 250 250 249 248 247 247 246 245 245 TAS KT 332 336 341 345 349 354 359 363 368 373 INDICATED MACH 0.539 0.548 0.557 0.566 0.576 0.586 0.596 0.606 0.617 0.628 BUFFET MARGIN G 2.46 2.42 2.37 2.33 2.28 2.23 2.18 2.12 2.07 2.01 SR NM/lb 0.144 0.146 0.149 0.152 0.154 0.157 0.159 0.162 0.164 0.167
48000
N1 % 73.9 74.6 75.3 76.1 76.8 77.6 78.3 79.2 79.9 80.5 F FLOW lb/H/ENG 1112 1105 1099 1094 1089 1085 1081 1078 1076 1074 IAS KT 247 246 245 244 244 243 242 241 241 240 TAS KT 327 331 335 339 343 348 352 357 362 367 INDICATED MACH 0.529 0.538 0.547 0.556 0.566 0.576 0.585 0.596 0.606 0.617 BUFFET MARGIN G 2.50 2.46 2.41 2.37 2.32 2.27 2.22 2.17 2.12 2.06 SR NM/lb 0.147 0.150 0.152 0.155 0.158 0.160 0.163 0.166 0.168 0.171
46000
N1 % 73.0 73.7 74.3 75.0 75.8 76.5 77.3 78.1 78.9 79.6 F FLOW lb/H/ENG 1070 1062 1056 1050 1045 1040 1036 1034 1031 1030 IAS KT 242 241 241 240 239 238 238 237 236 236 TAS KT 321 325 329 333 337 342 346 351 356 361 INDICATED MACH 0.520 0.529 0.537 0.546 0.556 0.565 0.575 0.586 0.596 0.607 BUFFET MARGIN G 2.54 2.50 2.45 2.41 2.36 2.32 2.27 2.22 2.17 2.11 SR NM/lb 0.150 0.153 0.156 0.159 0.161 0.164 0.167 0.170 0.173 0.175
44000
N1 % 72.1 72.7 73.4 74.1 74.8 75.5 76.3 77.0 77.8 78.6 F FLOW lb/H/ENG 1029 1022 1015 1009 1003 998 994 989 985 983 IAS KT 238 237 236 236 235 234 233 232 232 231 TAS KT 315 319 323 327 331 336 340 344 349 354 INDICATED MACH 0.511 0.520 0.528 0.537 0.546 0.555 0.565 0.575 0.585 0.595 BUFFET MARGIN G 2.56 2.54 2.50 2.46 2.41 2.36 2.32 2.27 2.21 2.16 SR NM/lb 0.153 0.156 0.159 0.162 0.165 0.168 0.171 0.174 0.177 0.180
42000
N1 % 71.2 71.8 72.4 73.0 73.7 74.4 75.2 75.9 76.7 77.5 F FLOW lb/H/ENG 987 980 972 966 959 954 949 945 941 938 IAS KT 233 232 232 231 230 229 228 228 227 226 TAS KT 309 313 317 321 325 329 333 338 342 347 INDICATED MACH 0.502 0.510 0.518 0.526 0.535 0.544 0.554 0.563 0.573 0.583 BUFFET MARGIN G 2.56 2.56 2.54 2.50 2.45 2.41 2.36 2.31 2.26 2.21 SR NM/lb 0.157 0.160 0.163 0.166 0.169 0.172 0.176 0.179 0.182 0.185
Page
1-05-15
Code
6 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
LONG RANGE CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE : 19000 FT TO 28000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 19000 20000 21000 22000 23000 24000 25000 26000 27000 28000
40000
N1 % 70.2 70.8 71.4 72.0 72.6 73.3 74.0 74.8 75.5 76.3 F FLOW lb/H/ENG 946 938 931 924 917 911 906 901 897 893 IAS KT 229 228 227 226 225 224 224 223 222 221 TAS KT 303 307 311 315 318 322 327 331 335 340 INDICATED MACH 0.492 0.500 0.508 0.516 0.525 0.534 0.543 0.552 0.562 0.572 BUFFET MARGIN G 2.56 2.56 2.56 2.54 2.50 2.45 2.41 2.36 2.31 2.26 SR NM/lb 0.160 0.164 0.167 0.170 0.174 0.177 0.180 0.184 0.187 0.190
38000
N1 % 69.2 69.8 70.3 70.9 71.5 72.2 72.9 73.6 74.3 75.1 F FLOW lb/H/ENG 906 897 890 882 876 870 864 859 854 850 IAS KT 224 223 222 221 220 220 219 218 217 216 TAS KT 297 301 304 308 312 316 320 324 328 332 INDICATED MACH 0.482 0.489 0.497 0.505 0.514 0.523 0.532 0.541 0.550 0.559 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.55 2.50 2.46 2.41 2.37 2.32 SR NM/lb 0.164 0.167 0.171 0.174 0.178 0.182 0.185 0.189 0.192 0.196
36000
N1 % 68.2 68.7 69.3 69.9 70.5 71.1 71.7 72.4 73.1 73.8 F FLOW lb/H/ENG 867 858 850 843 836 829 823 818 812 807 IAS KT 219 218 217 216 216 215 214 213 212 212 TAS KT 291 294 298 302 305 309 313 317 321 325 INDICATED MACH 0.472 0.479 0.487 0.495 0.503 0.512 0.520 0.529 0.538 0.547 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.51 2.47 2.42 2.37 SR NM/lb 0.168 0.172 0.175 0.179 0.183 0.186 0.190 0.194 0.198 0.201
34000
N1 % 67.1 67.6 68.2 68.7 69.3 69.9 70.5 71.2 71.9 72.5 F FLOW lb/H/ENG 827 818 809 802 794 787 781 775 770 765 IAS KT 214 213 212 211 210 209 209 208 207 206 TAS KT 284 288 291 294 298 302 305 309 314 318 INDICATED MACH 0.461 0.468 0.476 0.483 0.491 0.499 0.508 0.516 0.526 0.535 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.52 2.47 2.43 SR NM/lb 0.172 0.176 0.180 0.184 0.188 0.192 0.196 0.200 0.204 0.208
32000
N1 % 66.0 66.5 67.0 67.6 68.1 68.7 69.3 69.9 70.6 71.3 F FLOW lb/H/ENG 788 778 770 762 754 747 740 734 729 724 IAS KT 209 208 207 206 205 204 203 203 202 201 TAS KT 278 281 284 287 291 294 298 302 306 310 INDICATED MACH 0.451 0.457 0.464 0.472 0.479 0.487 0.495 0.504 0.513 0.522 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.53 2.49 SR NM/lb 0.176 0.180 0.184 0.189 0.193 0.197 0.201 0.206 0.210 0.214
Page
REVISION 4
1-05-15
Code
7 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
LONG RANGE CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE : 29000 FT TO 37000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 29000 30000 31000 32000 33000 34000 35000 36000 37000
50000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
82.0 82.7 83.4 84.1 84.8 85.5 86.4 87.5 89.2 1121 1121 1122 1124 1129 1131 1134 1135 1137 244 243 243 242 242 242 241 240 237 379 384 389 395 402 407 413 418 422 0.640 0.652 0.664 0.676 0.690 0.703 0.717 0.728 0.736 1.95 1.89 1.83 1.76 1.69 1.62 1.54 1.47 1.39 0.169 0.171 0.174 0.176 0.178 0.180 0.182 0.184 0.186
48000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
81.1 81.8 82.5 83.2 83.9 84.6 85.3 86.2 88.0 1074 1074 1074 1075 1078 1081 1084 1087 1089 240 239 238 238 237 237 236 236 234 372 378 383 388 394 400 406 412 417 0.629 0.641 0.652 0.665 0.678 0.691 0.704 0.718 0.727 2.00 1.94 1.88 1.82 1.75 1.68 1.61 1.53 1.46 0.173 0.176 0.178 0.181 0.183 0.185 0.187 0.189 0.191
46000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
80.2 80.9 81.6 82.2 83.0 83.7 84.4 85.1 86.8 1027 1028 1026 1026 1028 1032 1034 1036 1046 235 235 234 233 233 233 232 231 231 366 371 376 381 387 393 399 405 413 0.618 0.630 0.641 0.652 0.665 0.679 0.692 0.705 0.720 2.06 2.00 1.94 1.88 1.81 1.74 1.67 1.60 1.52 0.178 0.181 0.183 0.186 0.188 0.191 0.193 0.195 0.197
44000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
79.3 80.0 80.6 81.3 82.0 82.7 83.4 84.1 85.6 982 981 980 979 979 981 984 986 995 230 230 229 229 228 228 227 227 226 359 364 369 374 379 385 392 397 405 0.606 0.618 0.629 0.640 0.652 0.666 0.679 0.692 0.706 2.11 2.06 2.00 1.93 1.87 1.81 1.74 1.67 1.59 0.183 0.186 0.188 0.191 0.194 0.196 0.199 0.201 0.204
42000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
78.3 79.0 79.6 80.3 81.0 81.7 82.4 83.1 84.6 936 934 933 932 931 932 935 937 945 226 225 225 224 223 223 223 222 222 352 357 362 367 372 378 384 389 397 0.594 0.605 0.617 0.628 0.640 0.652 0.666 0.679 0.693 2.16 2.11 2.05 1.99 1.93 1.87 1.81 1.74 1.67 0.188 0.191 0.194 0.197 0.200 0.202 0.205 0.208 0.210
Page
1-05-15
Code
8 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
LONG RANGE CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE : 29000 FT TO 37000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 29000 30000 31000 32000 33000 34000 35000 36000 37000
40000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
77.1 77.9 78.7 79.3 79.9 80.6 81.3 82.0 83.5 890 888 888 886 885 884 886 887 894 221 220 220 219 218 218 217 217 217 344 349 355 359 364 370 375 381 389 0.582 0.593 0.605 0.615 0.627 0.639 0.652 0.664 0.678 2.21 2.16 2.11 2.05 1.99 1.93 1.87 1.81 1.74 0.193 0.197 0.200 0.203 0.206 0.209 0.212 0.215 0.217
38000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
75.8 76.6 77.5 78.2 78.8 79.5 80.2 81.0 82.4 846 843 842 841 838 838 839 841 844 216 215 215 214 213 213 212 212 211 337 342 347 352 356 362 367 374 380 0.569 0.580 0.591 0.603 0.613 0.625 0.638 0.651 0.663 2.27 2.22 2.17 2.12 2.06 2.00 1.94 1.88 1.81 0.199 0.203 0.206 0.209 0.213 0.216 0.219 0.222 0.225
36000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
74.6 75.4 76.2 77.0 77.8 78.4 79.1 79.8 81.2 803 799 797 796 794 791 791 792 797 211 210 209 209 208 208 207 207 206 329 334 339 344 349 353 359 364 372 0.557 0.567 0.577 0.589 0.600 0.611 0.623 0.636 0.648 2.32 2.27 2.22 2.17 2.12 2.06 2.00 1.94 1.88 0.205 0.209 0.212 0.216 0.220 0.223 0.227 0.230 0.233
34000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
73.3 74.0 74.8 75.6 76.5 77.2 77.9 78.6 80.0 761 756 753 752 750 746 745 745 748 206 205 204 204 203 202 202 201 201 322 326 331 336 341 345 350 355 362 0.544 0.554 0.564 0.575 0.587 0.596 0.608 0.620 0.632 2.38 2.33 2.28 2.24 2.19 2.13 2.07 2.01 1.95 0.212 0.216 0.219 0.223 0.227 0.231 0.235 0.239 0.242
32000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
71.9 72.7 73.4 74.2 75.0 75.8 76.6 77.3 78.7 719 715 710 707 706 702 700 699 701 200 200 199 198 198 197 196 196 195 314 318 322 327 332 336 341 346 353 0.531 0.541 0.550 0.560 0.572 0.582 0.593 0.604 0.616 2.44 2.39 2.34 2.30 2.25 2.19 2.14 2.08 2.02 0.218 0.223 0.227 0.231 0.235 0.239 0.244 0.248 0.251
Page
REVISION 4
1-05-15
Code
9 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
LONG RANGE CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE : 38000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 38000 39000 40000 41000
50000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
91.0 91.4 1134 1099 233 224 425 419 0.741 0.730 1.32 1.27 0.187 0.190
-
-
48000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
89.9 91.3 90.8 1095 1106 1030 232 230 213 423 428 408 0.738 0.747 0.712 1.38 1.31 1.26 0.193 0.194 0.198
-
46000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
88.6 90.6 90.6 1053 1054 1041 230 227 222 419 424 424 0.731 0.739 0.739 1.45 1.37 1.31 0.199 0.201 0.203
-
44000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
87.3 89.3 90.3 89.8 1003 1008 1012 974 226 224 222 212 413 419 424 415 0.720 0.730 0.740 0.723 1.52 1.44 1.37 1.31 0.206 0.208 0.210 0.213
42000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
86.1 87.8 88.9 89.6 952 960 963 982 221 220 218 218 405 412 418 427 0.706 0.719 0.728 0.744 1.59 1.52 1.44 1.36 0.213 0.215 0.217 0.217
Page
1-05-15
Code
10 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
LONG RANGE CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES ALTITUDE : 38000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 38000 39000 40000 41000
40000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
84.9 86.5 87.6 88.6 900 908 917 924 216 215 215 214 396 404 412 419 0.691 0.704 0.719 0.731 1.67 1.59 1.52 1.44 0.220 0.222 0.225 0.227
38000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.8 85.3 86.3 87.3 850 857 865 875 211 210 210 210 387 395 403 412 0.675 0.689 0.703 0.718 1.74 1.67 1.60 1.52 0.228 0.230 0.233 0.235
36000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
82.6 84.1 85.1 86.1 800 806 813 823 205 205 205 205 378 386 393 402 0.660 0.673 0.687 0.702 1.81 1.75 1.68 1.61 0.236 0.239 0.242 0.244
34000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
81.4 82.9 83.9 84.9 752 757 763 770 200 200 199 199 369 376 384 392 0.644 0.657 0.670 0.684 1.89 1.83 1.76 1.69 0.245 0.248 0.251 0.254
32000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
80.1 81.6 82.6 83.6 705 709 714 719 195 194 194 193 360 366 374 381 0.628 0.640 0.653 0.666 1.97 1.90 1.84 1.78 0.255 0.259 0.262 0.265
Page
REVISION 7
1-05-15
Code
11 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MAXIMUM SPEED CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 5000 FT TO 18000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000 18000
50000
N1 % 64.8 75.9 76.6 77.3 78.0 78.8 79.5 80.3 81.1 81.9 F FLOW lb/h/ENG 1227 1674 1669 1666 1663 1660 1659 1658 1657 1658 IAS kt 250 320 320 320 320 320 320 320 320 320 TAS kt 268 368 373 379 384 390 395 401 407 413 INDICATED MACH 0.413 0.576 0.587 0.598 0.608 0.620 0.631 0.643 0.655 0.667 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.109 0.110 0.112 0.114 0.116 0.117 0.119 0.121 0.123 0.125
48000
N1 % 64.4 75.7 76.4 77.1 77.8 78.5 79.3 80.0 80.8 81.7 F FLOW lb/h/ENG 1211 1662 1657 1653 1650 1648 1646 1645 1644 1645 IAS kt 250 320 320 320 320 320 320 320 320 320 TAS kt 268 368 373 379 384 390 395 401 407 413 INDICATED MACH 0.413 0.576 0.587 0.598 0.608 0.620 0.631 0.643 0.655 0.667 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.111 0.111 0.113 0.114 0.116 0.118 0.120 0.122 0.124 0.126
46000
N1 % 64.0 75.5 76.2 76.9 77.6 78.3 79.1 79.8 80.6 81.5 F FLOW lb/h/ENG 1195 1650 1646 1642 1638 1636 1634 1632 1632 1632 IAS kt 250 320 320 320 320 320 320 320 320 320 TAS kt 268 368 373 379 384 390 395 401 407 413 INDICATED MACH 0.413 0.576 0.587 0.598 0.608 0.620 0.631 0.643 0.655 0.667 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.112 0.111 0.113 0.115 0.117 0.119 0.121 0.123 0.125 0.127
44000
N1 % 63.6 75.3 76.0 76.7 77.4 78.1 78.9 79.6 80.4 81.2 F FLOW lb/h/ENG 1180 1639 1635 1630 1627 1624 1622 1620 1620 1620 IAS kt 250 320 320 320 320 320 320 320 320 320 TAS kt 268 368 373 379 384 390 395 401 407 413 INDICATED MACH 0.413 0.576 0.587 0.598 0.608 0.620 0.631 0.643 0.655 0.667 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.114 0.112 0.114 0.116 0.118 0.120 0.122 0.124 0.126 0.128
42000
N1 % 63.2 75.2 75.8 76.5 77.2 77.9 78.7 79.4 80.2 81.0 F FLOW lb/h/ENG 1166 1629 1624 1620 1616 1613 1611 1609 1608 1608 IAS kt 250 320 320 320 320 320 320 320 320 320 TAS kt 268 368 373 379 384 390 395 401 407 413 INDICATED MACH 0.413 0.576 0.587 0.598 0.608 0.620 0.631 0.643 0.655 0.667 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.115 0.113 0.115 0.117 0.119 0.121 0.123 0.125 0.127 0.128
Page
1-05-15
Code
12 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MAXIMUM SPEED CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 5000 FT TO 18000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000 18000
40000
N1 % 62.8 75.0 75.7 76.4 77.0 77.7 78.5 79.2 80.0 80.8 F FLOW lb/H/ENG 1153 1619 1614 1610 1606 1603 1600 1598 1597 1597 IAS KT 250 320 320 320 320 320 320 320 320 320 TAS KT 268 368 373 379 384 390 395 401 407 413 INDICATED MACH 0.413 0.576 0.587 0.598 0.608 0.620 0.631 0.643 0.655 0.667 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.116 0.114 0.116 0.118 0.120 0.122 0.124 0.125 0.127 0.129
38000
N1 % 62.4 74.9 75.5 76.2 76.9 77.6 78.3 79.0 79.8 80.6 F FLOW lb/H/ENG 1140 1610 1605 1600 1596 1593 1590 1588 1587 1586 IAS KT 250 320 320 320 320 320 320 320 320 320 TAS KT 268 368 373 379 384 390 395 401 407 413 INDICATED MACH 0.413 0.576 0.587 0.598 0.608 0.620 0.631 0.643 0.655 0.667 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.118 0.114 0.116 0.118 0.120 0.122 0.124 0.126 0.128 0.130
36000
N1 % 62.1 74.7 75.3 76.0 76.7 77.4 78.1 78.9 79.6 80.4 F FLOW lb/H/ENG 1128 1601 1596 1591 1587 1583 1581 1579 1577 1576 IAS KT 250 320 320 320 320 320 320 320 320 320 TAS KT 268 368 373 379 384 390 395 401 407 413 INDICATED MACH 0.413 0.576 0.587 0.598 0.608 0.620 0.631 0.643 0.655 0.667 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.119 0.115 0.117 0.119 0.121 0.123 0.125 0.127 0.129 0.131
34000
N1 % 61.8 74.6 75.2 75.9 76.6 77.2 78.0 78.7 79.4 80.2 F FLOW lb/H/ENG 1117 1592 1587 1582 1578 1575 1572 1569 1568 1567 IAS KT 250 320 320 320 320 320 320 320 320 320 TAS KT 268 368 373 379 384 390 395 401 407 413 INDICATED MACH 0.413 0.576 0.587 0.598 0.608 0.620 0.631 0.643 0.655 0.667 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.120 0.116 0.118 0.120 0.122 0.124 0.126 0.128 0.130 0.132
32000
N1 % 61.5 74.5 75.1 75.7 76.4 77.1 77.8 78.5 79.3 80.1 F FLOW lb/H/ENG 1106 1584 1579 1574 1570 1566 1563 1561 1559 1558 IAS KT 250 320 320 320 320 320 320 320 320 320 TAS KT 268 368 373 379 384 390 395 401 407 413 INDICATED MACH 0.413 0.576 0.587 0.598 0.608 0.620 0.631 0.643 0.655 0.667 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.121 0.116 0.118 0.120 0.122 0.124 0.126 0.129 0.131 0.133
Page
REVISION 4
1-05-15
Code
13 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MAXIMUM SPEED CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 19000 FT TO 28000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 19000 20000 21000 22000 23000 24000 25000 26000 27000 28000
50000
N1 % 82.6 83.3 84.0 84.7 85.3 86.0 86.9 87.8 87.8 87.7 F FLOW lb/H/ENG 1659 1661 1664 1667 1672 1690 1713 1733 1679 1623 IAS KT 320 320 320 320 320 320 320 318 312 305 TAS KT 419 425 432 438 445 451 458 462 461 459 INDICATED MACH 0.680 0.692 0.706 0.719 0.733 0.747 0.761 0.771 0.772 0.772 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.50 2.36 2.23 2.13 2.04 SR NM/lb 0.126 0.128 0.130 0.131 0.133 0.134 0.134 0.133 0.137 0.141
48000
N1 % 82.4 83.1 83.8 84.5 85.1 85.8 86.7 87.8 87.7 87.7 F FLOW lb/H/ENG 1646 1647 1650 1653 1657 1675 1698 1734 1680 1624 IAS KT 320 320 320 320 320 320 320 319 313 306 TAS KT 419 425 432 438 445 451 458 464 463 460 INDICATED MACH 0.680 0.692 0.706 0.719 0.733 0.747 0.761 0.774 0.775 0.774 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.46 2.31 2.21 2.11 SR NM/lb 0.127 0.129 0.131 0.133 0.134 0.135 0.135 0.134 0.138 0.142
46000
N1 % 82.2 82.9 83.6 84.3 84.9 85.6 86.5 87.6 87.7 87.7 F FLOW lb/H/ENG 1633 1634 1636 1639 1643 1661 1683 1727 1681 1625 IAS KT 320 320 320 320 320 320 320 320 314 307 TAS KT 419 425 432 438 445 451 458 465 464 462 INDICATED MACH 0.680 0.692 0.706 0.719 0.733 0.747 0.761 0.776 0.777 0.777 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.40 2.29 2.19 SR NM/lb 0.128 0.130 0.132 0.134 0.135 0.136 0.136 0.135 0.138 0.142
44000
N1 % 82.0 82.7 83.4 84.1 84.7 85.5 86.3 87.4 87.7 87.7 F FLOW lb/H/ENG 1620 1621 1624 1626 1630 1647 1669 1712 1682 1626 IAS KT 320 320 320 320 320 320 320 320 315 308 TAS KT 419 425 432 438 445 451 458 465 466 463 INDICATED MACH 0.680 0.692 0.706 0.719 0.733 0.747 0.761 0.776 0.780 0.779 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.51 2.38 2.28 SR NM/lb 0.129 0.131 0.133 0.135 0.136 0.137 0.137 0.136 0.138 0.142
42000
N1 % 81.9 82.5 83.2 83.9 84.5 85.3 86.1 87.2 87.7 87.7 F FLOW lb/H/ENG 1608 1609 1611 1614 1617 1635 1656 1698 1682 1627 IAS KT 320 320 320 320 320 320 320 320 315 309 TAS KT 419 425 432 438 445 451 458 465 466 465 INDICATED MACH 0.680 0.692 0.706 0.719 0.733 0.747 0.761 0.776 0.780 0.782 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.50 2.38 SR NM/lb 0.130 0.132 0.134 0.136 0.137 0.138 0.138 0.137 0.138 0.143
Page
1-05-15
Code
14 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MAXIMUM SPEED CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 19000 FT TO 28000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 19000 20000 21000 22000 23000 24000 25000 26000 27000 28000
40000
N1 % 81.7 82.4 83.0 83.7 84.4 85.1 85.9 87.0 87.7 87.7 F FLOW lb/H/ENG 1597 1598 1600 1602 1605 1622 1643 1685 1683 1627 IAS KT 320 320 320 320 320 320 320 320 316 309 TAS KT 419 425 432 438 445 451 458 465 467 465 INDICATED MACH 0.680 0.692 0.706 0.719 0.733 0.747 0.761 0.776 0.782 0.782 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.50 SR NM/lb 0.131 0.133 0.135 0.137 0.139 0.139 0.139 0.138 0.139 0.143
38000
N1 % 81.5 82.2 82.8 83.5 84.2 85.0 85.8 86.9 87.7 87.7 F FLOW lb/H/ENG 1586 1587 1589 1591 1594 1610 1631 1672 1684 1628 IAS KT 320 320 320 320 320 320 320 320 317 311 TAS KT 419 425 432 438 445 451 458 465 469 466 INDICATED MACH 0.680 0.692 0.706 0.719 0.733 0.747 0.761 0.776 0.785 0.785 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.132 0.134 0.136 0.138 0.140 0.140 0.140 0.139 0.139 0.143
36000
N1 % 81.3 82.0 82.7 83.4 84.1 84.8 85.6 86.7 87.7 87.6 F FLOW lb/H/ENG 1576 1577 1578 1580 1583 1599 1620 1660 1684 1629 IAS KT 320 320 320 320 320 320 320 320 317 312 TAS KT 419 425 432 438 445 451 458 465 469 468 INDICATED MACH 0.680 0.692 0.706 0.719 0.733 0.747 0.761 0.776 0.785 0.787 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.133 0.135 0.137 0.139 0.140 0.141 0.141 0.140 0.139 0.144
34000
N1 % 81.1 81.9 82.5 83.2 83.9 84.7 85.5 86.6 87.7 87.6 F FLOW lb/H/ENG 1567 1567 1568 1570 1573 1589 1609 1649 1685 1629 IAS KT 320 320 320 320 320 320 320 320 318 312 TAS KT 419 425 432 438 445 451 458 465 470 468 INDICATED MACH 0.680 0.692 0.706 0.719 0.733 0.747 0.761 0.776 0.787 0.787 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.134 0.136 0.138 0.140 0.141 0.142 0.142 0.141 0.139 0.144
32000
N1 % 80.9 81.7 82.4 83.1 83.8 84.5 85.3 86.4 87.7 87.6 F FLOW lb/H/ENG 1558 1558 1559 1561 1563 1579 1599 1639 1685 1630 IAS KT 320 320 320 320 320 320 320 320 318 313 TAS KT 419 425 432 438 445 451 458 465 470 469 INDICATED MACH 0.680 0.692 0.706 0.719 0.733 0.747 0.761 0.776 0.787 0.790 BUFFET MARGIN G 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 SR NM/lb 0.135 0.137 0.138 0.140 0.142 0.143 0.143 0.142 0.139 0.144
Page
REVISION 4
1-05-15
Code
15 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MAXIMUM SPEED CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 29000 FT TO 37000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 29000 30000 31000 32000 33000 34000 35000 36000 37000
50000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
87.7 87.7 88.1 88.5 89.1 89.6 90.2 90.9 91.0 1568 1514 1480 1447 1420 1394 1371 1348 1263 298 292 286 281 275 270 265 260 251 456 454 453 453 452 451 451 450 444 0.771 0.770 0.772 0.775 0.777 0.779 0.782 0.784 0.775 1.95 1.86 1.77 1.69 1.61 1.52 1.45 1.37 1.33 0.146 0.150 0.153 0.156 0.159 0.162 0.164 0.167 0.176
48000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
87.7 87.7 88.1 88.5 89.0 89.6 90.2 90.8 91.0 1569 1515 1483 1449 1425 1399 1376 1350 1268 299 293 288 282 278 272 267 261 253 458 456 456 454 455 455 454 452 448 0.774 0.773 0.778 0.777 0.783 0.785 0.788 0.788 0.781 2.02 1.93 1.83 1.75 1.65 1.57 1.49 1.42 1.37 0.146 0.150 0.154 0.157 0.160 0.162 0.165 0.167 0.177
46000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
87.7 87.7 88.1 88.5 89.0 89.5 90.2 90.8 91.0 1570 1517 1484 1453 1427 1402 1379 1356 1270 300 295 289 284 279 274 269 263 254 459 459 458 457 457 456 456 455 450 0.776 0.778 0.781 0.783 0.786 0.788 0.791 0.794 0.784 2.10 2.00 1.90 1.81 1.72 1.63 1.54 1.46 1.42 0.146 0.151 0.154 0.157 0.160 0.163 0.165 0.168 0.177
44000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
87.7 87.7 88.0 88.5 89.0 89.5 90.1 90.8 90.9 1571 1517 1486 1455 1429 1405 1381 1358 1272 302 295 291 285 280 275 270 265 255 461 459 460 459 459 458 458 457 452 0.779 0.778 0.783 0.786 0.788 0.791 0.794 0.797 0.787 2.18 2.09 1.98 1.88 1.78 1.69 1.60 1.52 1.48 0.147 0.151 0.155 0.158 0.160 0.163 0.166 0.168 0.177
42000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
87.7 87.6 88.0 88.5 89.0 89.5 90.1 90.8 90.9 1572 1518 1486 1457 1432 1407 1384 1359 1277 303 296 291 286 281 276 271 266 257 463 460 460 461 460 460 459 459 455 0.782 0.781 0.783 0.789 0.791 0.794 0.797 0.800 0.794 2.28 2.18 2.07 1.96 1.86 1.76 1.67 1.58 1.53 0.147 0.152 0.155 0.158 0.161 0.163 0.166 0.169 0.178
Page
1-05-15
Code
16 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MAXIMUM SPEED CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 29000 FT TO 37000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 29000 30000 31000 32000 33000 34000 35000 36000 37000
40000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
87.6 87.6 88.0 88.5 89.0 89.5 90.1 90.3 90.8 1573 1519 1487 1457 1434 1410 1384 1338 1280 304 297 292 286 282 277 272 266 259 464 462 461 461 462 462 461 459 457 0.784 0.784 0.786 0.789 0.794 0.797 0.800 0.800 0.797 2.38 2.27 2.16 2.05 1.94 1.83 1.74 1.66 1.59 0.147 0.152 0.155 0.158 0.161 0.164 0.167 0.172 0.179
38000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
87.6 87.6 88.0 88.4 89.0 89.5 89.6 89.8 90.8 1573 1520 1489 1459 1434 1410 1364 1317 1279 304 298 293 287 282 277 272 266 260 464 464 463 462 462 462 461 459 459 0.784 0.787 0.789 0.792 0.794 0.797 0.800 0.800 0.800 2.50 2.38 2.26 2.15 2.04 1.93 1.83 1.74 1.66 0.147 0.152 0.155 0.159 0.161 0.164 0.169 0.174 0.179
36000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
87.6 87.6 88.0 88.4 88.9 89.1 89.2 89.3 90.3 1574 1520 1490 1461 1436 1397 1346 1297 1258 305 298 294 289 283 278 272 266 260 466 464 465 464 464 463 461 459 459 0.787 0.787 0.792 0.794 0.797 0.800 0.800 0.800 0.800 2.56 2.51 2.37 2.25 2.14 2.02 1.93 1.84 1.75 0.148 0.152 0.156 0.159 0.161 0.166 0.171 0.177 0.182
34000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
87.6 87.6 88.0 88.4 88.8 88.8 88.8 88.8 89.8 1575 1521 1490 1460 1434 1380 1328 1279 1239 306 299 294 289 284 278 272 266 260 467 465 465 464 465 463 461 459 459 0.789 0.789 0.792 0.794 0.800 0.800 0.800 0.800 0.800 2.56 2.56 2.51 2.39 2.24 2.14 2.04 1.95 1.86 0.148 0.153 0.156 0.159 0.162 0.168 0.174 0.179 0.185
32000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
87.6 87.6 88.0 88.4 88.5 88.5 88.4 88.4 89.3 1575 1522 1491 1462 1419 1364 1311 1261 1220 306 301 295 290 284 278 272 266 260 467 467 466 466 465 463 461 459 459 0.789 0.792 0.794 0.797 0.800 0.800 0.800 0.800 0.800 2.56 2.56 2.56 2.52 2.39 2.28 2.17 2.07 1.97 0.148 0.153 0.156 0.159 0.164 0.170 0.176 0.182 0.188
Page
REVISION 4
1-05-15
Code
17 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MAXIMUM SPEED CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 38000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 38000 39000 40000 41000
50000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
91.2 91.4 1178 1099 239 224 435 419 0.758 0.730 1.30 1.27 0.184 0.190
-
-
48000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
91.1 91.3 90.8 1183 1106 1030 242 230 213 440 428 408 0.767 0.747 0.712 1.34 1.31 1.26 0.186 0.194 0.198
-
46000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
91.1 91.2 90.6 1187 1112 1041 245 234 222 444 436 424 0.774 0.760 0.739 1.38 1.34 1.31 0.187 0.196 0.203
-
44000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
91.0 91.1 90.5 89.8 1191 1115 1047 974 247 236 226 212 448 440 431 415 0.780 0.767 0.752 0.723 1.43 1.39 1.35 1.31 0.188 0.197 0.206 0.213
42000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
91.0 91.0 90.3 89.6 1193 1120 1050 982 248 240 230 218 450 445 437 427 0.784 0.777 0.762 0.744 1.49 1.44 1.40 1.36 0.188 0.199 0.208 0.217
Page
1-05-15
Code
18 08
REVISION 7
AIRPLANE OPERATIONS MANUAL
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
MAXIMUM SPEED CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 38000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 38000 39000 40000 41000
40000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
90.9 91.0 90.3 89.5 1197 1122 1053 987 250 241 232 223 453 447 441 435 0.790 0.780 0.769 0.758 1.54 1.50 1.45 1.41 0.189 0.199 0.210 0.220
38000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
90.8 90.9 90.2 89.4 1200 1125 1056 989 251 243 234 225 455 451 445 439 0.793 0.787 0.776 0.765 1.61 1.56 1.51 1.47 0.190 0.200 0.211 0.222
36000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
90.8 90.9 90.1 89.3 1202 1128 1059 991 253 244 236 227 457 453 449 443 0.797 0.790 0.783 0.772 1.68 1.63 1.58 1.53 0.190 0.201 0.212 0.223
34000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
90.8 90.9 90.1 89.3 1200 1130 1060 994 254 246 238 230 459 455 451 447 0.800 0.793 0.786 0.779 1.77 1.71 1.66 1.60 0.191 0.201 0.213 0.225
32000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
90.3 90.8 90.1 89.2 1183 1132 1062 995 254 247 239 231 459 457 453 449 0.800 0.797 0.790 0.783 1.88 1.81 1.75 1.69 0.194 0.202 0.213 0.226
Page
REVISION 7
1-05-15
Code
19 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.70 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000
50000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.8 83.8 83.9 84.1 84.3 84.5 84.7 85.0 85.3 1350 1311 1274 1239 1207 1177 1149 1124 1102 280 274 269 263 257 251 246 240 235 418 416 414 413 411 409 407 405 404 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 2.23 2.13 2.04 1.95 1.86 1.78 1.70 1.62 1.54 0.155 0.159 0.163 0.166 0.170 0.174 0.177 0.180 0.183
48000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.5 83.5 83.6 83.7 83.8 84.0 84.2 84.5 84.8 1332 1292 1254 1218 1185 1154 1125 1099 1075 280 274 269 263 257 251 246 240 235 418 416 414 413 411 409 407 405 404 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 2.32 2.22 2.12 2.03 1.94 1.85 1.77 1.69 1.61 0.157 0.161 0.165 0.169 0.173 0.177 0.181 0.184 0.188
46000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.2 83.2 83.2 83.3 83.4 83.6 83.8 84.0 84.2 1315 1273 1234 1198 1164 1132 1102 1074 1049 280 274 269 263 257 251 246 240 235 418 416 414 413 411 409 407 405 404 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 2.42 2.32 2.21 2.12 2.02 1.93 1.84 1.76 1.68 0.159 0.163 0.168 0.172 0.177 0.181 0.185 0.189 0.192
44000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
82.9 82.9 82.9 83.0 83.0 83.1 83.3 83.5 83.7 1298 1256 1216 1179 1143 1110 1080 1051 1025 280 274 269 263 257 251 246 240 235 418 416 414 413 411 409 407 405 404 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 2.53 2.42 2.32 2.21 2.11 2.02 1.93 1.84 1.75 0.161 0.166 0.170 0.175 0.180 0.184 0.189 0.193 0.197
42000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
82.6 82.6 82.6 82.6 82.7 82.7 82.9 83.0 83.2 1282 1239 1199 1161 1124 1090 1059 1029 1001 280 274 269 263 257 251 246 240 235 418 416 414 413 411 409 407 405 404 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 2.56 2.54 2.43 2.32 2.21 2.11 2.02 1.93 1.84 0.163 0.168 0.173 0.178 0.183 0.188 0.192 0.197 0.201
Page
1-05-15
Code
20 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.70 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000
40000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
82.3 82.3 82.3 82.3 82.3 82.4 82.4 82.5 82.7 1267 1223 1182 1143 1106 1071 1039 1008 979 280 274 269 263 257 251 246 240 235 418 416 414 413 411 409 407 405 404 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 2.56 2.56 2.55 2.43 2.32 2.22 2.12 2.02 1.93 0.165 0.170 0.175 0.180 0.186 0.191 0.196 0.201 0.206
38000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
82.1 82.0 82.0 82.0 82.0 82.0 82.0 82.1 82.2 1252 1208 1167 1127 1089 1053 1020 988 959 280 274 269 263 257 251 246 240 235 418 416 414 413 411 409 407 405 404 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 2.56 2.56 2.56 2.56 2.45 2.34 2.23 2.13 2.03 0.167 0.172 0.178 0.183 0.189 0.194 0.200 0.205 0.210
36000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
81.8 81.7 81.7 81.7 81.7 81.6 81.6 81.7 81.7 1239 1194 1152 1111 1073 1036 1002 970 939 280 274 269 263 257 251 246 240 235 418 416 414 413 411 409 407 405 404 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 2.56 2.56 2.56 2.56 2.56 2.47 2.35 2.25 2.14 0.169 0.174 0.180 0.186 0.191 0.197 0.203 0.209 0.215
34000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
81.5 81.5 81.4 81.4 81.4 81.3 81.3 81.3 81.3 1226 1181 1138 1097 1058 1020 985 952 921 280 274 269 263 257 251 246 240 235 418 416 414 413 411 409 407 405 404 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 2.56 2.56 2.56 2.56 2.56 2.56 2.49 2.38 2.27 0.170 0.176 0.182 0.188 0.194 0.200 0.207 0.213 0.219
32000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
81.3 81.2 81.1 81.1 81.0 81.0 80.9 80.9 80.9 1214 1168 1125 1083 1043 1005 970 936 903 280 274 269 263 257 251 246 240 235 418 416 414 413 411 409 407 405 404 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 0.700 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.53 2.41 0.172 0.178 0.184 0.190 0.197 0.203 0.210 0.217 0.223
Page
REVISION 4
1-05-15
Code
21 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.70 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 36000 37000 38000 39000 40000 41000
50000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
85.8 87.4 89.0 91.0 1082 1070 1061 1055 230 224 219 214 402 401 401 401 0.700 0.700 0.700 0.700 1.47 1.40 1.33 1.27 0.186 0.188 0.189 0.190
-
-
48000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
85.1 86.4 87.9 89.8 90.6 1053 1039 1029 1020 1015 230 224 219 214 209 402 401 401 401 401 0.700 0.700 0.700 0.700 0.700 1.53 1.46 1.39 1.33 1.26 0.191 0.193 0.195 0.197 0.198
-
46000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
84.5 85.6 87.0 88.6 89.5 1026 1011 998 988 980 230 224 219 214 209 402 401 401 401 401 0.700 0.700 0.700 0.700 0.700 1.60 1.52 1.45 1.38 1.32 0.196 0.199 0.201 0.203 0.205
-
44000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.9 85.0 86.2 87.6 88.4 89.2 1000 983 969 957 948 940 230 224 219 214 209 204 402 401 401 401 401 401 0.700 0.700 0.700 0.700 0.700 0.700 1.67 1.59 1.52 1.45 1.38 1.31 0.201 0.204 0.207 0.210 0.212 0.213
42000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.4 84.3 85.4 86.7 87.4 88.0 976 957 942 928 917 907 230 224 219 214 209 204 402 401 401 401 401 401 0.700 0.700 0.700 0.700 0.700 0.700 1.75 1.67 1.59 1.51 1.44 1.37 0.206 0.210 0.213 0.216 0.219 0.221
Page
1-05-15
Code
22 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.70 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 36000 37000 38000 39000 40000 41000
40000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
82.9 83.8 84.8 85.9 86.5 87.2 953 933 916 901 888 876 230 224 219 214 209 204 402 401 401 401 401 401 0.700 0.700 0.700 0.700 0.700 0.700 1.84 1.75 1.67 1.59 1.52 1.44 0.211 0.215 0.219 0.223 0.226 0.229
38000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
82.3 83.2 84.1 85.3 85.8 86.3 931 910 891 875 860 847 230 224 219 214 209 204 402 401 401 401 401 401 0.700 0.700 0.700 0.700 0.700 0.700 1.94 1.84 1.76 1.67 1.59 1.52 0.216 0.221 0.225 0.229 0.233 0.237
36000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
81.8 82.7 83.6 84.6 85.1 85.6 910 888 868 850 834 820 230 224 219 214 209 204 402 401 401 401 401 401 0.700 0.700 0.700 0.700 0.700 0.700 2.04 1.95 1.85 1.77 1.68 1.60 0.221 0.226 0.231 0.236 0.240 0.245
34000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
81.4 82.2 83.0 84.0 84.5 84.9 891 868 847 828 810 794 230 224 219 214 209 204 402 401 401 401 401 401 0.700 0.700 0.700 0.700 0.700 0.700 2.16 2.06 1.96 1.87 1.78 1.70 0.225 0.231 0.237 0.242 0.248 0.253
32000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
80.9 81.7 82.5 83.4 83.9 84.3 873 848 826 806 788 770 230 224 219 214 209 204 402 401 401 401 401 401 0.700 0.700 0.700 0.700 0.700 0.700 2.30 2.19 2.09 1.99 1.89 1.80 0.230 0.237 0.243 0.249 0.255 0.260
Page
REVISION 7
1-05-15
Code
23 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.72 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000
50000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
84.6 84.6 84.7 84.8 84.9 85.1 85.3 85.6 85.9 1417 1374 1333 1295 1259 1226 1195 1167 1141 289 283 277 271 265 259 253 248 242 430 428 426 424 422 421 419 417 415 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 2.23 2.13 2.04 1.95 1.86 1.77 1.69 1.62 1.54 0.152 0.156 0.160 0.164 0.168 0.172 0.175 0.179 0.182
48000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
84.3 84.3 84.4 84.5 84.6 84.7 84.9 85.1 85.3 1400 1356 1314 1275 1238 1204 1172 1142 1115 289 283 277 271 265 259 253 248 242 430 428 426 424 422 421 419 417 415 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 2.32 2.22 2.12 2.03 1.94 1.85 1.76 1.68 1.61 0.154 0.158 0.162 0.166 0.171 0.175 0.179 0.182 0.186
46000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
84.0 84.0 84.1 84.1 84.2 84.3 84.4 84.6 84.8 1383 1338 1296 1256 1218 1183 1150 1119 1091 289 283 277 271 265 259 253 248 242 430 428 426 424 422 421 419 417 415 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 2.42 2.31 2.21 2.11 2.02 1.93 1.84 1.76 1.68 0.155 0.160 0.164 0.169 0.173 0.178 0.182 0.186 0.190
44000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.8 83.8 83.8 83.8 83.8 83.9 84.0 84.1 84.3 1367 1321 1278 1237 1199 1162 1128 1097 1067 289 283 277 271 265 259 253 248 242 430 428 426 424 422 421 419 417 415 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 2.53 2.42 2.31 2.21 2.11 2.02 1.93 1.84 1.75 0.157 0.162 0.167 0.171 0.176 0.181 0.186 0.190 0.194
42000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.5 83.5 83.5 83.5 83.5 83.5 83.6 83.7 83.8 1352 1305 1261 1220 1180 1143 1108 1075 1045 289 283 277 271 265 259 253 248 242 430 428 426 424 422 421 419 417 415 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 2.56 2.54 2.42 2.32 2.21 2.11 2.02 1.92 1.84 0.159 0.164 0.169 0.174 0.179 0.184 0.189 0.194 0.199
Page
1-05-15
Code
24 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.72 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000
40000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.3 83.2 83.2 83.2 83.1 83.2 83.2 83.3 83.4 1337 1290 1245 1203 1163 1125 1089 1055 1024 289 283 277 271 265 259 253 248 242 430 428 426 424 422 421 419 417 415 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 2.56 2.56 2.54 2.43 2.32 2.22 2.12 2.02 1.93 0.161 0.166 0.171 0.176 0.182 0.187 0.192 0.198 0.203
38000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.1 83.0 82.9 82.9 82.8 82.8 82.8 82.9 83.0 1323 1276 1230 1187 1146 1108 1071 1036 1004 289 283 277 271 265 259 253 248 242 430 428 426 424 422 421 419 417 415 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 2.56 2.56 2.56 2.56 2.45 2.34 2.23 2.13 2.03 0.162 0.168 0.173 0.179 0.184 0.190 0.196 0.201 0.207
36000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
82.9 82.8 82.7 82.6 82.5 82.5 82.5 82.5 82.5 1310 1262 1216 1172 1131 1091 1054 1018 985 289 283 277 271 265 259 253 248 242 430 428 426 424 422 421 419 417 415 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 2.56 2.56 2.56 2.56 2.56 2.47 2.35 2.25 2.14 0.164 0.170 0.175 0.181 0.187 0.193 0.199 0.205 0.211
34000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
82.7 82.5 82.4 82.3 82.3 82.2 82.1 82.1 82.1 1298 1249 1203 1158 1116 1076 1038 1001 967 289 283 277 271 265 259 253 248 242 430 428 426 424 422 421 419 417 415 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 2.56 2.56 2.56 2.56 2.56 2.56 2.49 2.38 2.27 0.166 0.171 0.177 0.183 0.189 0.195 0.202 0.208 0.215
32000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
82.4 82.3 82.2 82.1 82.0 81.9 81.8 81.8 81.8 1286 1237 1190 1145 1102 1061 1023 986 951 289 283 277 271 265 259 253 248 242 430 428 426 424 422 421 419 417 415 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 0.720 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.53 2.41 0.167 0.173 0.179 0.185 0.192 0.198 0.205 0.211 0.218
Page
REVISION 4
1-05-15
Code
25 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.72 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 36000 37000 38000 39000 40000 41000
50000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
86.5 87.9 89.5 91.2 1118 1103 1091 1082 237 231 226 221 413 413 413 413 0.720 0.720 0.720 0.720 1.47 1.40 1.33 1.27 0.185 0.187 0.189 0.191
-
-
48000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
85.7 87.0 88.4 90.3 90.8 1091 1074 1060 1049 1029 237 231 226 221 213 413 413 413 413 408 0.720 0.720 0.720 0.720 0.712 1.53 1.46 1.39 1.32 1.26 0.189 0.192 0.195 0.197 0.198
-
46000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
85.1 86.2 87.5 89.2 90.0 1065 1047 1031 1018 1008 237 231 226 221 216 413 413 413 413 413 0.720 0.720 0.720 0.720 0.720 1.60 1.52 1.45 1.38 1.32 0.194 0.197 0.200 0.203 0.205
-
44000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
84.5 85.5 86.8 88.1 88.9 89.6 1040 1020 1003 989 977 967 237 231 226 221 216 211 413 413 413 413 413 413 0.720 0.720 0.720 0.720 0.720 0.720 1.67 1.59 1.52 1.44 1.38 1.31 0.199 0.202 0.206 0.209 0.211 0.214
42000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
84.0 85.0 86.0 87.2 87.9 88.6 1017 996 977 961 947 935 237 231 226 221 216 211 413 413 413 413 413 413 0.720 0.720 0.720 0.720 0.720 0.720 1.75 1.67 1.59 1.51 1.44 1.37 0.203 0.207 0.211 0.215 0.218 0.221
Page
1-05-15
Code
26 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.72 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 36000 37000 38000 39000 40000 41000
40000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.5 84.4 85.4 86.5 87.1 87.7 994 972 952 935 919 906 237 231 226 221 216 211 413 413 413 413 413 413 0.720 0.720 0.720 0.720 0.720 0.720 1.84 1.75 1.67 1.59 1.51 1.44 0.208 0.212 0.217 0.221 0.225 0.228
38000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.1 83.9 84.8 85.8 86.4 86.9 973 950 929 910 893 878 237 231 226 221 216 211 413 413 413 413 413 413 0.720 0.720 0.720 0.720 0.720 0.720 1.93 1.84 1.76 1.67 1.59 1.52 0.212 0.217 0.222 0.227 0.231 0.235
36000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
82.6 83.4 84.3 85.2 85.7 86.2 954 929 907 886 868 852 237 231 226 221 216 211 413 413 413 413 413 413 0.720 0.720 0.720 0.720 0.720 0.720 2.04 1.95 1.85 1.77 1.68 1.60 0.217 0.222 0.228 0.233 0.238 0.242
34000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
82.2 82.9 83.8 84.7 85.1 85.5 935 909 886 865 845 827 237 231 226 221 216 211 413 413 413 413 413 413 0.720 0.720 0.720 0.720 0.720 0.720 2.16 2.06 1.96 1.87 1.78 1.70 0.221 0.227 0.233 0.239 0.244 0.249
32000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
81.8 82.5 83.3 84.1 84.6 85.0 918 891 867 844 823 804 237 231 226 221 216 211 413 413 413 413 413 413 0.720 0.720 0.720 0.720 0.720 0.720 2.30 2.19 2.09 1.99 1.89 1.80 0.225 0.232 0.238 0.245 0.251 0.257
Page
REVISION 7
1-05-15
Code
27 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.74 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000
50000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
85.5 85.6 85.6 85.7 85.7 85.9 86.1 86.3 86.7 1495 1448 1403 1361 1321 1284 1250 1218 1189 298 291 285 279 273 267 261 255 250 442 440 438 436 434 432 430 428 427 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 2.21 2.11 2.02 1.93 1.84 1.76 1.68 1.60 1.53 0.148 0.152 0.156 0.160 0.164 0.168 0.172 0.176 0.179
48000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
85.3 85.3 85.3 85.3 85.4 85.5 85.6 85.8 86.1 1478 1430 1384 1341 1301 1263 1228 1195 1164 298 291 285 279 273 267 261 255 250 442 440 438 436 434 432 430 428 427 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 2.30 2.20 2.10 2.01 1.92 1.83 1.75 1.67 1.59 0.149 0.154 0.158 0.163 0.167 0.171 0.175 0.179 0.183
46000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
85.0 85.0 85.0 85.0 85.1 85.1 85.2 85.4 85.6 1462 1413 1367 1323 1281 1243 1206 1172 1140 298 291 285 279 273 267 261 255 250 442 440 438 436 434 432 430 428 427 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 2.40 2.29 2.19 2.10 2.00 1.91 1.82 1.74 1.66 0.151 0.156 0.160 0.165 0.169 0.174 0.178 0.183 0.187
44000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
84.8 84.7 84.7 84.7 84.7 84.8 84.8 84.9 85.1 1446 1397 1350 1305 1263 1223 1186 1150 1118 298 291 285 279 273 267 261 255 250 442 440 438 436 434 432 430 428 427 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 2.51 2.40 2.29 2.19 2.09 2.00 1.91 1.82 1.74 0.153 0.157 0.162 0.167 0.172 0.177 0.182 0.186 0.191
42000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
84.6 84.5 84.4 84.4 84.4 84.4 84.5 84.5 84.6 1431 1381 1333 1288 1245 1204 1166 1130 1096 298 291 285 279 273 267 261 255 250 442 440 438 436 434 432 430 428 427 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 2.56 2.51 2.40 2.29 2.19 2.09 2.00 1.91 1.82 0.154 0.159 0.164 0.169 0.174 0.179 0.185 0.190 0.195
Page
1-05-15
Code
28 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.74 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000
40000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
84.3 84.3 84.2 84.1 84.1 84.1 84.1 84.1 84.2 1417 1366 1318 1272 1228 1187 1148 1111 1076 298 291 285 279 273 267 261 255 250 442 440 438 436 434 432 430 428 427 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 2.56 2.56 2.52 2.41 2.30 2.20 2.10 2.00 1.91 0.156 0.161 0.166 0.171 0.177 0.182 0.188 0.193 0.198
38000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
84.1 84.0 83.9 83.9 83.8 83.8 83.8 83.8 83.8 1404 1352 1303 1257 1212 1170 1130 1092 1057 298 291 285 279 273 267 261 255 250 442 440 438 436 434 432 430 428 427 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 2.56 2.56 2.56 2.54 2.42 2.31 2.21 2.11 2.01 0.157 0.163 0.168 0.174 0.179 0.185 0.190 0.196 0.202
36000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.9 83.8 83.7 83.6 83.5 83.5 83.4 83.4 83.4 1391 1339 1290 1242 1197 1154 1113 1075 1038 298 291 285 279 273 267 261 255 250 442 440 438 436 434 432 430 428 427 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 2.56 2.56 2.56 2.56 2.56 2.44 2.33 2.22 2.12 0.159 0.164 0.170 0.176 0.181 0.187 0.193 0.199 0.205
34000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.7 83.6 83.5 83.4 83.3 83.2 83.1 83.1 83.1 1379 1327 1277 1229 1183 1139 1098 1059 1021 298 291 285 279 273 267 261 255 250 442 440 438 436 434 432 430 428 427 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 2.56 2.56 2.56 2.56 2.56 2.56 2.47 2.35 2.25 0.160 0.166 0.172 0.177 0.184 0.190 0.196 0.202 0.209
32000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.6 83.4 83.3 83.1 83.0 82.9 82.8 82.8 82.7 1368 1315 1264 1216 1169 1125 1083 1043 1005 298 291 285 279 273 267 261 255 250 442 440 438 436 434 432 430 428 427 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 0.740 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.50 2.39 0.161 0.167 0.173 0.179 0.186 0.192 0.199 0.205 0.212
Page
REVISION 4
1-05-15
Code
29 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.74 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 36000 37000 38000 39000 40000 41000
50000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
87.3 88.6 90.3 1163 1144 1130 244 238 233 425 424 424 0.740 0.740 0.740 1.46 1.39 1.32 0.183 0.185 0.188
-
-
48000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
86.6 87.8 89.3 90.9 90.8 1136 1117 1100 1086 1029 244 238 233 227 213 425 424 424 424 408 0.740 0.740 0.740 0.740 0.712 1.52 1.45 1.38 1.31 1.26 0.187 0.190 0.193 0.195 0.198
-
46000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
85.9 87.0 88.3 90.0 90.5 1111 1090 1072 1056 1041 244 238 233 227 222 425 424 424 424 424 0.740 0.740 0.740 0.740 0.739 1.58 1.51 1.44 1.37 1.31 0.191 0.195 0.198 0.201 0.203
-
44000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
85.3 86.4 87.5 89.0 89.7 89.7 1087 1065 1045 1028 1013 971 244 238 233 227 222 212 425 424 424 424 424 415 0.740 0.740 0.740 0.740 0.740 0.723 1.65 1.58 1.50 1.43 1.36 1.31 0.195 0.199 0.203 0.206 0.209 0.213
42000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
84.8 85.7 86.8 88.0 88.7 89.3 1065 1041 1020 1001 985 970 244 238 233 227 222 217 425 424 424 424 424 424 0.740 0.740 0.740 0.740 0.740 0.740 1.73 1.65 1.57 1.50 1.43 1.36 0.199 0.204 0.208 0.212 0.215 0.219
Page
1-05-15
-
Code
30 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.74 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 36000 37000 38000 39000 40000 41000
40000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
84.3 85.2 86.2 87.3 87.9 88.4 1043 1018 996 976 958 942 244 238 233 227 222 217 425 424 424 424 424 424 0.740 0.740 0.740 0.740 0.740 0.740 1.82 1.73 1.65 1.58 1.50 1.43 0.203 0.208 0.213 0.217 0.222 0.225
38000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.9 84.7 85.7 86.6 87.1 87.6 1023 997 974 952 932 915 244 238 233 227 222 217 425 424 424 424 424 424 0.740 0.740 0.740 0.740 0.740 0.740 1.92 1.83 1.74 1.66 1.58 1.51 0.208 0.213 0.218 0.223 0.228 0.232
36000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.5 84.3 85.2 86.0 86.5 87.0 1004 977 952 930 909 890 244 238 233 227 222 217 425 424 424 424 424 424 0.740 0.740 0.740 0.740 0.740 0.740 2.02 1.93 1.84 1.75 1.67 1.59 0.211 0.217 0.223 0.228 0.234 0.238
34000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.1 83.8 84.7 85.5 85.9 86.3 986 958 932 908 886 866 244 238 233 227 222 217 425 424 424 424 424 424 0.740 0.740 0.740 0.740 0.740 0.740 2.14 2.04 1.94 1.85 1.77 1.68 0.215 0.222 0.228 0.234 0.239 0.245
32000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
82.7 83.4 84.2 85.0 85.4 85.7 969 940 913 889 865 844 244 238 233 227 222 217 425 424 424 424 424 424 0.740 0.740 0.740 0.740 0.740 0.740 2.27 2.17 2.07 1.97 1.88 1.79 0.219 0.226 0.232 0.239 0.245 0.251
Page
REVISION 7
1-05-15
Code
31 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.76 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000
50000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
86.7 86.7 86.7 86.8 86.8 87.0 87.2 87.6 88.0 1593 1541 1492 1446 1402 1361 1322 1287 1254 306 300 294 287 281 275 269 263 257 454 452 450 448 446 444 442 440 438 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 2.16 2.07 1.98 1.89 1.81 1.72 1.65 1.57 1.50 0.142 0.147 0.151 0.155 0.159 0.163 0.167 0.171 0.175
48000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
86.5 86.4 86.4 86.5 86.5 86.6 86.7 87.0 87.4 1576 1524 1474 1426 1382 1340 1300 1263 1229 306 300 294 287 281 275 269 263 257 454 452 450 448 446 444 442 440 438 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 2.25 2.16 2.06 1.97 1.88 1.80 1.71 1.64 1.56 0.144 0.148 0.153 0.157 0.161 0.166 0.170 0.174 0.178
46000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
86.2 86.2 86.2 86.2 86.2 86.2 86.3 86.5 86.8 1560 1507 1456 1408 1363 1320 1279 1241 1206 306 300 294 287 281 275 269 263 257 454 452 450 448 446 444 442 440 438 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 2.35 2.25 2.15 2.05 1.96 1.87 1.79 1.71 1.63 0.145 0.150 0.154 0.159 0.164 0.168 0.173 0.177 0.182
44000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
86.0 86.0 85.9 85.9 85.9 85.9 85.9 86.0 86.2 1545 1491 1440 1391 1344 1300 1259 1220 1184 306 300 294 287 281 275 269 263 257 454 452 450 448 446 444 442 440 438 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 2.46 2.35 2.25 2.15 2.05 1.96 1.87 1.78 1.70 0.147 0.151 0.156 0.161 0.166 0.171 0.176 0.180 0.185
42000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
85.8 85.7 85.7 85.6 85.6 85.6 85.6 85.6 85.7 1531 1476 1424 1374 1327 1282 1240 1200 1163 306 300 294 287 281 275 269 263 257 454 452 450 448 446 444 442 440 438 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 2.56 2.46 2.35 2.25 2.15 2.05 1.96 1.87 1.78 0.148 0.153 0.158 0.163 0.168 0.173 0.178 0.183 0.188
Page
1-05-15
Code
32 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.76 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000
40000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
85.6 85.5 85.4 85.3 85.3 85.3 85.2 85.3 85.3 1517 1461 1409 1358 1310 1265 1222 1181 1143 306 300 294 287 281 275 269 263 257 454 452 450 448 446 444 442 440 438 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 2.56 2.56 2.47 2.36 2.26 2.16 2.06 1.96 1.87 0.150 0.155 0.160 0.165 0.170 0.176 0.181 0.186 0.192
38000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
85.4 85.3 85.2 85.1 85.0 85.0 84.9 84.9 84.9 1504 1448 1394 1343 1295 1249 1205 1163 1124 306 300 294 287 281 275 269 263 257 454 452 450 448 446 444 442 440 438 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 2.56 2.56 2.56 2.49 2.38 2.27 2.17 2.07 1.97 0.151 0.156 0.161 0.167 0.172 0.178 0.183 0.189 0.195
36000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
85.2 85.1 85.0 84.9 84.8 84.7 84.6 84.6 84.6 1491 1435 1381 1329 1280 1233 1188 1146 1106 306 300 294 287 281 275 269 263 257 454 452 450 448 446 444 442 440 438 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 2.56 2.56 2.56 2.56 2.51 2.40 2.29 2.18 2.08 0.152 0.157 0.163 0.168 0.174 0.180 0.186 0.192 0.198
34000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
85.1 84.9 84.8 84.6 84.5 84.4 84.3 84.3 84.2 1480 1423 1368 1316 1266 1218 1173 1130 1089 306 300 294 287 281 275 269 263 257 454 452 450 448 446 444 442 440 438 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 2.56 2.56 2.56 2.56 2.56 2.54 2.42 2.31 2.20 0.153 0.159 0.164 0.170 0.176 0.182 0.188 0.195 0.201
32000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
84.9 84.7 84.6 84.4 84.3 84.2 84.1 84.0 83.9 1468 1411 1356 1303 1253 1205 1159 1115 1074 306 300 294 287 281 275 269 263 257 454 452 450 448 446 444 442 440 438 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 0.760 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.45 2.34 0.154 0.160 0.166 0.172 0.178 0.184 0.191 0.197 0.204
Page
REVISION 4
1-05-15
Code
33 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.76 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 36000 37000 38000 39000 40000 41000
50000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
88.4 89.8 1223 1202 251 245 436 436 0.760 0.760 1.43 1.36 0.178 0.181
48000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
-
-
87.8 89.0 90.5 1198 1175 1155 251 245 240 436 436 436 0.760 0.760 0.760 1.49 1.42 1.35 0.182 0.186 0.189
- 90.8 - 1029 - 213 - 408 - 0.712 - 1.26 - 0.198
-
46000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
87.1 88.3 89.7 1173 1149 1128 251 245 240 436 436 436 0.760 0.760 0.760 1.55 1.48 1.41 0.186 0.190 0.193
- 90.5 - 1041 - 222 - 424 - 0.739 - 1.31 - 0.203
-
44000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
86.5 87.6 88.8 90.3 90.3 89.7 1150 1124 1102 1082 1043 971 251 245 240 234 226 212 436 436 436 436 431 415 0.760 0.760 0.760 0.760 0.752 0.723 1.62 1.55 1.47 1.40 1.35 1.31 0.190 0.194 0.198 0.202 0.207 0.213
42000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
86.0 86.9 88.0 89.4 89.9 89.4 1128 1101 1077 1055 1036 977 251 245 240 234 229 218 436 436 436 436 436 427 0.760 0.760 0.760 0.760 0.760 0.744 1.70 1.62 1.54 1.47 1.40 1.36 0.193 0.198 0.202 0.207 0.210 0.218
Page
1-05-15
-
-
Code
34 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.76 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 36000 37000 38000 39000 40000 41000
40000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
85.4 86.4 87.3 88.5 89.1 89.4 1107 1079 1054 1031 1010 986 251 245 240 234 229 223 436 436 436 436 436 435 0.760 0.760 0.760 0.760 0.760 0.758 1.79 1.70 1.62 1.55 1.47 1.41 0.197 0.202 0.207 0.211 0.216 0.221
38000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
85.0 85.8 86.8 87.7 88.3 88.7 1087 1058 1031 1007 985 965 251 245 240 234 229 223 436 436 436 436 436 436 0.760 0.760 0.760 0.760 0.760 0.760 1.88 1.79 1.71 1.63 1.55 1.48 0.201 0.206 0.211 0.216 0.221 0.226
36000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
84.6 85.4 86.3 87.2 87.6 88.0 1068 1038 1011 985 962 940 251 245 240 234 229 223 436 436 436 436 436 436 0.760 0.760 0.760 0.760 0.760 0.760 1.98 1.89 1.80 1.72 1.64 1.56 0.204 0.210 0.216 0.221 0.227 0.232
34000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
84.2 85.0 85.8 86.6 87.0 87.4 1051 1019 991 965 940 917 251 245 240 234 229 223 436 436 436 436 436 436 0.760 0.760 0.760 0.760 0.760 0.760 2.10 2.00 1.91 1.82 1.73 1.65 0.208 0.214 0.220 0.226 0.232 0.238
32000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
83.9 84.6 85.4 86.1 86.5 86.9 1034 1002 973 945 919 895 251 245 240 234 229 223 436 436 436 436 436 436 0.760 0.760 0.760 0.760 0.760 0.760 2.23 2.13 2.03 1.93 1.84 1.75 0.211 0.218 0.224 0.231 0.237 0.243
Page
REVISION 7
1-05-15
Code
35 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.78 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000
50000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
-
-
-
-
-
-
48000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
-
-
-
-
-
- 88.7 88.9 89.2 - 1405 1364 1325 - 277 271 264 - 454 452 450 - 0.780 0.780 0.780 - 1.66 1.59 1.51 - 0.161 0.166 0.170
46000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
-
-
-
- 87.9 88.0 88.2 88.4 88.7 - 1478 1429 1384 1341 1302 - 289 283 277 271 264 - 458 456 454 452 450 - 0.780 0.780 0.780 0.780 0.780 - 1.90 1.82 1.73 1.66 1.58 - 0.155 0.159 0.164 0.168 0.173
44000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
-
-
-
- 87.6 87.7 87.8 87.9 88.1 - 1459 1410 1364 1320 1279 - 289 283 277 271 264 - 458 456 454 452 450 - 0.780 0.780 0.780 0.780 0.780 - 1.99 1.90 1.81 1.73 1.65 - 0.157 0.162 0.166 0.171 0.176
42000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
- 87.4 87.3 87.3 87.2 87.3 87.4 87.5 87.7 - 1607 1549 1494 1442 1392 1345 1300 1258 - 309 302 296 289 283 277 271 264 - 464 462 460 458 456 454 452 450 - 0.780 0.780 0.780 0.780 0.780 0.780 0.780 0.780 - 2.39 2.28 2.18 2.08 1.99 1.90 1.81 1.73 - 0.144 0.149 0.154 0.159 0.164 0.169 0.174 0.179
Page
1-05-15
-
- 89.7 - 1349 - 264 - 450 - 0.780 - 1.45 - 0.167
Code
36 08
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.78 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000
40000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
87.3 87.2 87.1 87.0 87.0 86.9 87.0 87.1 87.2 1654 1593 1534 1478 1425 1375 1327 1281 1238 315 309 302 296 289 283 277 271 264 466 464 462 460 458 456 454 452 450 0.780 0.780 0.780 0.780 0.780 0.780 0.780 0.780 0.780 2.56 2.51 2.40 2.29 2.19 2.09 2.00 1.90 1.82 0.141 0.146 0.150 0.155 0.161 0.166 0.171 0.176 0.182
38000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
87.1 87.0 86.9 86.8 86.7 86.6 86.6 86.7 86.7 1641 1579 1520 1463 1409 1358 1309 1263 1219 315 309 302 296 289 283 277 271 264 466 464 462 460 458 456 454 452 450 0.780 0.780 0.780 0.780 0.780 0.780 0.780 0.780 0.780 2.56 2.56 2.52 2.41 2.30 2.20 2.10 2.00 1.91 0.142 0.147 0.152 0.157 0.162 0.168 0.173 0.179 0.184
36000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
86.9 86.8 86.7 86.5 86.4 86.4 86.3 86.3 86.3 1628 1566 1506 1449 1395 1343 1293 1246 1201 315 309 302 296 289 283 277 271 264 466 464 462 460 458 456 454 452 450 0.780 0.780 0.780 0.780 0.780 0.780 0.780 0.780 0.780 2.56 2.56 2.56 2.55 2.43 2.32 2.22 2.12 2.02 0.143 0.148 0.153 0.159 0.164 0.170 0.175 0.181 0.187
34000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
86.8 86.6 86.5 86.3 86.2 86.1 86.0 85.9 85.9 1617 1554 1493 1436 1381 1328 1278 1230 1185 315 309 302 296 289 283 277 271 264 466 464 462 460 458 456 454 452 450 0.780 0.780 0.780 0.780 0.780 0.780 0.780 0.780 0.780 2.56 2.56 2.56 2.56 2.56 2.46 2.35 2.24 2.14 0.144 0.149 0.155 0.160 0.166 0.172 0.178 0.184 0.190
32000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
86.6 86.5 86.3 86.1 86.0 85.9 85.7 85.6 85.6 1605 1542 1481 1423 1367 1314 1263 1215 1169 315 309 302 296 289 283 277 271 264 466 464 462 460 458 456 454 452 450 0.780 0.780 0.780 0.780 0.780 0.780 0.780 0.780 0.780 2.56 2.56 2.56 2.56 2.56 2.56 2.49 2.38 2.27 0.145 0.150 0.156 0.162 0.167 0.173 0.180 0.186 0.192
Page
REVISION 4
1-05-15
Code
37 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.78 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 36000 37000 38000 39000 40000 41000
50000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
90.1 1314 258 448 0.780 1.38 0.170
-
-
-
-
-
48000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
89.5 90.8 1289 1262 258 252 448 447 0.780 0.780 1.44 1.37 0.174 0.177
-
- 90.8 - 1029 - 213 - 408 - 0.712 - 1.26 - 0.198
-
46000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
88.9 90.2 1264 1236 258 252 448 447 0.780 0.780 1.51 1.43 0.177 0.181
-
- 90.5 - 1041 - 222 - 424 - 0.739 - 1.31 - 0.203
-
44000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
88.4 89.5 90.8 1241 1212 1185 258 252 247 448 447 447 0.780 0.780 0.780 1.57 1.50 1.43 0.180 0.185 0.189
- 90.3 89.7 - 1043 971 - 226 212 - 431 415 - 0.752 0.723 - 1.35 1.31 - 0.207 0.213
42000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
87.9 88.9 90.1 1219 1188 1161 258 252 247 448 447 447 0.780 0.780 0.780 1.65 1.57 1.50 0.184 0.188 0.193
- 90.1 89.4 - 1044 977 - 230 218 - 437 427 - 0.762 0.744 - 1.40 1.36 - 0.209 0.218
Page
1-05-15
Code
38 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
MACH 0.78 CRUISE - ALL ENGINES OPERATING AE3007A1E ENGINES PRESSURE ALTITUDE: 36000 FT TO 41000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITIONS
WEIGHT (lb)
ALTITUDE (ft) 36000 37000 38000 39000 40000 41000
40000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
87.4 88.3 89.5 1198 1166 1137 258 252 247 448 447 447 0.780 0.780 0.780 1.73 1.65 1.57 0.187 0.192 0.197
- 89.9 89.4 - 1041 986 - 232 223 - 441 435 - 0.769 0.758 - 1.45 1.41 - 0.212 0.221
38000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
86.9 87.7 88.8 90.0 89.8 89.1 1178 1145 1115 1088 1045 981 258 252 247 241 234 225 448 447 447 447 445 439 0.780 0.780 0.780 0.780 0.776 0.765 1.82 1.74 1.65 1.58 1.51 1.47 0.190 0.195 0.201 0.206 0.213 0.224
36000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
86.4 87.2 88.1 89.3 89.6 89.0 1159 1125 1094 1065 1039 981 258 252 247 241 235 227 448 447 447 447 447 443 0.780 0.780 0.780 0.780 0.780 0.772 1.92 1.83 1.75 1.66 1.59 1.53 0.193 0.199 0.204 0.210 0.215 0.226
34000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
86.0 86.7 87.5 88.5 88.9 89.0 1141 1107 1075 1045 1017 987 258 252 247 241 235 230 448 447 447 447 447 447 0.780 0.780 0.780 0.780 0.780 0.779 2.04 1.94 1.85 1.76 1.68 1.60 0.196 0.202 0.208 0.214 0.220 0.226
32000
N1 % F FLOW lb/h/ENG IAS kt TAS kt INDICATED MACH BUFFET MARGIN G SR NM/lb
85.5 86.3 87.0 87.9 88.3 88.5 1125 1089 1056 1025 996 969 258 252 247 241 235 230 448 447 447 447 447 447 0.780 0.780 0.780 0.780 0.780 0.780 2.16 2.06 1.97 1.87 1.78 1.70 0.199 0.205 0.212 0.218 0.225 0.231
Page
REVISION 7
1-05-15
Code
39 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-05-15
Code
40 08
REVISION 4
AIRPLANE OPERATIONS MANUAL
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
DESCENT The descent table shows fuel consumption, distance and time from the top of descent to sea level for various cruise altitudes. The data are calculated for flight idle thrust setting, maintaining Mach 0.78 or 310 KIAS up to 12000 ft, decreasing linearly to 240 KIAS at 10000 ft and maintaining 240 KIAS below 10000 ft. There are two sets of data: - First set is calculated for all engines operating configuration, and - Second set is calculated for one engine inoperative configuration. The associated conditions are: - Flaps...................................... UP - Gear ...................................... UP - Bleeds ................................... OPEN - Anti-Ice .................................. OFF or ON
Page
REVISION 7
1-05-20
Code
1 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
DESCENT - ALL ENGINES OPERATING AE3007A1E ENGINES CRUISE CONFIGURATION BLEED : OPEN ANTI-ICE : OFF FLIGHT IDLE AIRSPEED : Mach 0.78 / 310 KIAS / 240 KIAS ISA CONDITIONS
WEIGHT (lb)
TOP OF DESCENT (ft) 5000 10000 15000 20000 25000 30000 35000 41000
50000
Fuel Distance Time
lb nm min
68 15 4
123 30 7
167 44 9
200 57 11
229 70 13
253 83 15
277 97 17
308 119 20
48000
Fuel Distance Time
lb nm min
67 15 4
121 30 7
164 43 9
196 55 11
224 68 13
248 81 15
271 95 16
301 116 19
46000
Fuel Distance Time
lb nm min
66 15 4
119 29 7
161 42 9
191 54 11
219 67 13
242 79 14
264 93 16
294 113 19
44000
Fuel Distance Time
lb nm min
65 14 3
117 29 7
157 41 9
187 53 11
213 65 12
236 77 14
258 90 16
287 110 18
42000
Fuel Distance Time
lb nm MIN
63 14 3
114 28 7
153 40 9
182 51 10
207 63 12
229 75 13
250 88 15
279 107 18
40000
Fuel Distance Time
lb nm min
62 14 3
111 27 6
149 39 8
177 50 10
201 61 12
222 72 13
242 85 15
270 104 17
38000
Fuel Distance Time
lb nm min
60 13 3
108 26 6
144 38 8
171 48 10
194 59 11
215 70 13
234 82 14
261 100 17
36000
Fuel Distance Time
lb nm min
58 13 3
105 26 6
140 37 8
165 46 9
187 57 11
207 67 12
226 79 14
252 97 16
34000
Fuel Distance Time
lb nm min
56 12 3
101 25 6
134 35 8
159 45 9
180 54 10
198 64 12
216 75 13
242 93 15
32000
Fuel Distance Time
lb nm min
54 12 3
97 24 6
129 34 7
152 43 9
172 52 10
190 61 11
207 72 13
231 89 15
30000
Fuel Distance Time
lb nm min
51 11 3
93 23 5
123 32 7
145 41 8
164 49 9
180 58 11
197 68 12
220 84 14
Page
1-05-20
Code
2 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
DESCENT - ALL ENGINES OPERATING AE3007A1E ENGINES CRUISE CONFIGURATION BLEED : OPEN ANTI-ICE : ON FLIGHT IDLE AIRSPEED : Mach 0.78 / 310 KIAS / 240 KIAS ISA CONDITIONS
WEIGHT (lb)
TOP OF DESCENT (ft) 5000 10000 15000 20000 25000 30000 35000 41000
50000
Fuel Distance Time
lb nm min
180 24 6
361 51 12
444 69 15
503 84 17
560 99 19
614 116 22
677 135 24
748 162 28
48000
Fuel Distance Time
lb nm min
180 24 6
362 51 12
443 68 15
501 83 17
556 98 19
609 114 21
671 133 24
741 160 27
46000
Fuel Distance Time
lb nm min
180 24 6
362 51 12
442 68 15
498 82 17
552 97 19
603 113 21
664 131 24
733 158 27
44000
Fuel Distance Time
lb nm min
179 24 6
362 51 12
440 68 15
495 81 17
547 96 19
596 111 21
655 129 23
724 155 27
42000
Fuel Distance Time
lb nm min
178 24 6
361 51 12
438 67 15
490 80 17
540 94 19
588 109 21
646 127 23
714 153 26
40000
Fuel Distance Time
lb nm MIN
177 24 6
359 51 12
434 67 15
484 79 16
533 93 18
579 107 20
635 124 23
702 149 26
38000
Fuel Distance Time
lb nm min
175 23 6
356 51 12
429 66 14
477 78 16
524 91 18
568 104 20
623 121 22
688 146 25
36000
Fuel Distance Time
lb nm min
173 23 6
352 50 12
423 65 14
469 76 16
514 89 18
556 102 19
609 118 22
673 142 25
34000
Fuel Distance Time
lb nm min
170 23 5
347 49 11
415 63 14
459 75 16
502 86 17
543 99 19
593 114 21
655 138 24
32000
Fuel Distance Time
lb nm min
167 22 5
341 48 11
406 62 14
448 73 15
488 84 17
527 95 18
576 111 20
636 133 23
30000
Fuel Distance Time
lb nm min
163 22 5
333 47 11
395 60 13
435 70 15
473 81 16
510 92 18
556 106 20
614 128 23
Page
REVISION 7
1-05-20
Code
3 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
DESCENT - ONE ENGINE INOPERATIVE AE3007A1E ENGINES CRUISE CONFIGURATION BLEED : OPEN ANTI-ICE : OFF FLIGHT IDLE AIRSPEED : Mach 0.78 / 310 KIAS / 240 KIAS ISA CONDITIONS
WEIGHT (lb)
TOP OF DESCENT (ft) 5000 10000 15000 20000 25000 30000 35000 41000
50000
Fuel Distance Time
lb nm min
32 14 3
58 28 7
78 41 9
93 53 11
106 65 12
118 77 14
128 90 16
142 109 18
48000
Fuel Distance Time
lb nm min
31 14 3
57 28 6
76 40 9
91 52 10
104 63 12
115 75 14
125 88 15
139 107 18
46000
Fuel Distance Time
lb nm min
31 14 3
56 27 6
75 39 8
89 50 10
101 62 12
112 73 13
122 86 15
136 104 17
44000
Fuel Distance Time
lb nm min
30 13 3
54 27 6
73 38 8
87 49 10
99 60 11
109 71 13
119 83 14
132 101 17
42000
Fuel Distance Time
lb nm min
29 13 3
53 26 6
71 37 8
84 48 10
96 58 11
106 69 12
116 81 14
128 98 16
40000
Fuel Distance Time
lb nm min
28 13 3
52 25 6
69 36 8
82 46 9
93 56 11
103 66 12
112 78 14
124 95 16
38000
Fuel Distance Time
lb nm min
28 12 3
50 24 6
67 35 8
79 44 9
90 54 10
99 64 12
108 75 13
120 92 15
36000
Fuel Distance Time
lb nm min
27 12 3
48 24 6
64 34 7
76 43 9
86 52 10
95 62 11
104 72 13
115 88 15
34000
Fuel Distance Time
lb nm min
26 11 3
47 23 5
62 32 7
73 41 8
83 50 10
91 59 11
99 69 12
111 84 14
32000
Fuel Distance Time
lb nm min
25 11 3
45 22 5
59 31 7
70 39 8
79 48 9
87 56 10
95 66 12
106 81 14
30000
Fuel Distance Time
lb nm min
24 10 3
43 21 5
56 30 6
66 37 8
75 45 9
83 53 10
90 62 11
100 76 13
Page
1-05-20
Code
4 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
DESCENT - ONE ENGINE INOPERATIVE AE3007A1E ENGINES CRUISE CONFIGURATION BLEED : OPEN ANTI-ICE : ON FLIGHT IDLE AIRSPEED : Mach 0.78 / 310 KIAS / 240 KIAS ISA CONDITIONS
WEIGHT (lb)
TOP OF DESCENT (ft) 5000 10000 15000 20000 25000 30000 35000 41000
50000
Fuel Distance Time
lb nm min
63 17 4
122 35 8
156 49 11
181 61 12
204 75 14
226 88 16
251 103 18
278 124 21
48000
Fuel Distance Time
lb nm min
62 17 4
121 34 8
153 48 10
178 60 12
201 73 14
222 86 16
246 101 18
273 121 20
46000
Fuel Distance Time
lb nm min
61 16 4
119 34 8
151 47 10
175 59 12
197 71 14
217 84 15
241 98 17
268 119 20
44000
Fuel Distance Time
lb nm min
60 16 4
117 33 8
148 46 10
171 58 12
192 70 13
213 82 15
235 96 17
261 116 20
42000
Fuel Distance Time
lb nm min
59 16 4
115 33 8
145 45 10
167 56 11
188 68 13
207 80 15
229 93 16
255 113 19
40000
Fuel Distance Time
lb nm min
58 15 4
113 32 7
142 44 10
163 55 11
183 66 13
201 77 14
223 90 16
248 109 19
38000
Fuel Distance Time
lb nm min
56 15 4
110 31 7
138 43 9
158 53 11
177 64 12
195 75 14
216 87 15
240 106 18
36000
Fuel Distance Time
lb nm min
55 15 4
107 30 7
134 42 9
153 51 11
171 62 12
189 72 13
208 84 15
232 102 17
34000
Fuel Distance Time
lb nm min
53 14 3
103 29 7
129 40 9
148 50 10
165 59 12
182 69 13
200 81 14
223 98 17
32000
Fuel Distance Time
lb nm min
51 14 3
100 28 7
124 39 8
142 47 10
159 57 11
174 66 12
192 77 14
214 94 16
30000
Fuel Distance Time
lb nm min
49 13 3
96 27 6
119 37 8
136 45 9
151 54 11
166 63 12
183 73 13
204 89 15
Page
REVISION 7
1-05-20
Code
5 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-05-20
Code
6 08
REVISION 7
AIRPLANE OPERATIONS MANUAL
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
HOLDING The holding tables show indicated airspeed, true airspeed, Mach number, N1, fuel flow and fuel consumption for various weights, altitudes, anti-ice on (without ice accretion) and off condition. Data are presented in ISA condition. There are two sets of data: - First set is calculated for all engines operating configuration, and - Second set is calculated for one engine inoperative configuration.
The associated conditions are: - Flaps .................................... UP - Gear..................................... UP - Bleeds.................................. OPEN - Airspeed............................... minimum fuel consumption speed - Anti-Ice................................. ON or OFF
Page
REVISION 7
1-05-25
Code
1 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
HOLDING - ALL ENGINES AE3007A1E ENGINES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF MINIMUM FUEL CONSUMPTION SPEED STANDARD ATMOSPHERE
WEIGHT (lb)
ALTITUDE (ft) 0
5000 10000 15000 20000 25000 30000 35000 41000
kt kt
50000
IAS TAS Mach N1 FFlow
180 179 0.272 % 55.2 lb/h/ENG 1035
176 188 0.290 58.7 983
173 199 0.313 62.7 944
171 213 0.342 66.6 917
171 231 0.379 70.3 901
174 255 0.426 74.6 897
179 286 0.487 78.9 908
187 326 0.567 83.1 940
* * * * *
kt kt
48000
IAS TAS Mach N1 FFlow
178 177 0.268 % 54.3 lb/h/ENG 1004
173 185 0.286 57.6 951
170 195 0.308 61.6 911
168 209 0.336 65.6 882
168 226 0.371 69.3 864
170 249 0.416 73.4 858
174 278 0.475 77.8 866
182 317 0.552 82.1 893
* * * * *
kt kt
46000
IAS TAS Mach N1 FFlow
175 174 0.265 % 53.3 lb/h/ENG 974
170 182 0.282 56.6 919
167 192 0.303 60.5 878
165 205 0.329 64.5 848
164 221 0.363 68.3 829
166 243 0.406 72.3 821
170 271 0.462 76.7 825
177 308 0.536 81.1 847
167 331 0.581 90.2 906
kt kt
44000
IAS TAS Mach N1 FFlow
173 172 0.261 % 52.3 lb/h/ENG 943
168 179 0.277 55.6 887
164 188 0.297 59.3 845
161 200 0.323 63.4 814
161 216 0.355 67.3 793
162 237 0.397 71.2 784
165 263 0.450 75.6 785
171 298 0.521 80.0 803
167 331 0.581 88.6 857
kt kt
42000
IAS TAS Mach N1 FFlow
165 176 0.273 54.5 856
161 185 0.292 58.1 813
158 196 0.316 62.3 780
157 211 0.347 66.2 759
158 231 0.387 70.0 747
161 256 0.438 74.5 746
166 289 0.505 78.8 760
167 331 0.581 87.0 811
170 169 0.258 % 51.3 lb/h/ENG 913
NOTE: MACH setting and FF lb/h/ENG remain constant, regardless of the temperature change.
Page
1-05-25
Code
2 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
HOLDING - ALL ENGINES AE3007A1E ENGINES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF MINIMUM FUEL CONSUMPTION SPEED STANDARD ATMOSPHERE
WEIGHT (lb)
ALTITUDE (ft) 0
5000 10000 15000 20000 25000 30000 35000 41000
kt kt
40000
IAS TAS Mach N1 FFlow
168 167 0.254 % 50.2 lb/h/ENG 884
162 173 0.269 53.5 825
158 181 0.287 56.9 781
155 192 0.310 61.0 747
153 206 0.339 65.0 724
154 224 0.377 68.9 711
156 248 0.426 73.2 708
161 280 0.490 77.6 717
167 331 0.581 85.6 768
kt kt
38000
IAS TAS Mach N1 FFlow
166 164 0.250 % 49.1 lb/h/ENG 854
160 170 0.264 52.4 795
155 178 0.282 55.7 749
152 188 0.304 59.7 715
150 201 0.331 63.8 690
150 218 0.367 67.7 675
151 241 0.414 71.8 670
155 271 0.474 76.3 676
164 326 0.572 84.3 724
kt kt
36000
IAS TAS Mach N1 FFlow
163 162 0.247 % 48.0 lb/h/ENG 826
157 167 0.260 51.2 765
152 174 0.276 54.5 718
148 184 0.297 58.3 682
146 196 0.324 62.4 657
145 212 0.357 66.4 640
147 233 0.401 70.4 633
150 262 0.459 75.0 636
158 313 0.552 82.9 676
kt kt
34000
IAS TAS Mach N1 FFlow
161 159 0.243 % 46.9 lb/h/ENG 797
154 164 0.256 49.9 736
149 171 0.271 53.2 687
145 180 0.291 56.9 650
142 191 0.316 61.1 623
141 206 0.348 65.0 606
142 226 0.389 69.0 596
145 252 0.444 73.6 597
152 301 0.531 81.5 630
kt kt
32000
IAS TAS Mach N1 FFlow
158 157 0.239 % 45.8 lb/h/ENG 770
152 161 0.251 48.6 707
146 167 0.266 52.0 657
142 175 0.284 55.4 619
139 186 0.308 59.6 591
137 200 0.338 63.7 572
138 218 0.377 67.6 561
140 243 0.428 72.1 559
146 289 0.511 80.0 586
kt kt
30000
IAS TAS Mach N1 FFlow
149 158 0.247 47.3 678
143 164 0.261 50.6 627
139 171 0.278 54.0 588
135 181 0.300 57.9 559
133 194 0.328 62.1 538
133 211 0.365 66.1 526
135 234 0.413 70.4 521
139 277 0.490 78.4 543
156 154 0.236 % 44.6 lb/h/ENG 743
NOTE: MACH setting and FF lb/h/ENG remain constant, regardless of the temperature change.
Page
REVISION 7
1-05-25
Code
3 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
HOLDING - ALL ENGINES AE3007A1E ENGINES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITHOUT ICE ACCRETION) STANDARD ATMOSPHERE
WEIGHT (lb)
ALTITUDE (ft) 0
5000 10000 15000 20000 25000 30000 35000 41000
kt kt
50000
IAS TAS Mach N1 FFlow
200 200 0.302 % 56.2 lb/h/ENG 1199
200 215 0.331 59.7 1138
200 231 0.363 63.6 1089
200 250 0.399 67.4 1051
200 270 0.440 71.0 1027
200 293 0.487 75.1 1016
200 318 0.541 79.3 1024
200 347 0.603 83.4 1052
* * * * *
kt kt
48000
IAS TAS Mach N1 FFlow
200 200 0.302 % 55.6 lb/h/ENG 1176
200 215 0.331 59.0 1114
200 231 0.363 62.9 1064
200 250 0.399 66.8 1025
200 270 0.440 70.2 999
200 293 0.487 74.2 987
200 318 0.541 78.5 991
200 347 0.603 82.6 1016
* * * * *
kt kt
46000
IAS TAS Mach N1 FFlow
200 200 0.302 % 55.0 lb/h/ENG 1153
200 215 0.331 58.3 1091
200 231 0.363 62.1 1040
200 250 0.399 66.1 1000
200 270 0.440 69.6 973
200 293 0.487 73.4 958
200 318 0.541 77.7 960
200 347 0.603 81.7 981
* * * * *
kt kt
44000
IAS TAS Mach N1 FFlow
200 200 0.302 % 54.3 lb/h/ENG 1131
200 215 0.331 57.6 1069
200 231 0.363 61.4 1017
200 250 0.399 65.3 977
200 270 0.440 68.9 948
200 293 0.487 72.6 931
200 318 0.541 76.9 931
200 347 0.603 80.9 948
* * * * *
kt kt
42000
IAS TAS Mach N1 FFlow
200 215 0.331 57.0 1048
200 231 0.363 60.7 996
200 250 0.399 64.6 954
200 270 0.440 68.2 924
200 293 0.487 71.8 906
200 318 0.541 76.1 903
200 347 0.603 80.2 917
* * * * *
200 200 0.302 % 53.6 lb/h/ENG 1111
NOTE: MACH setting and FF lb/h/ENG remain constant, regardless of the temperature change.
Page
1-05-25
Code
4 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
HOLDING - ALL ENGINES AE3007A1E ENGINES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITHOUT ICE ACCRETION) STANDARD ATMOSPHERE
WEIGHT (lb)
ALTITUDE (ft) 0
5000 10000 15000 20000 25000 30000 35000 41000
kt kt
40000
IAS TAS Mach N1 FFlow
200 200 0.302 % 52.9 lb/h/ENG 1091
200 215 0.331 56.3 1028
200 231 0.363 60.0 975
200 250 0.399 63.9 933
200 270 0.440 67.5 902
200 293 0.487 71.1 882
200 318 0.541 75.3 877
200 347 0.603 79.4 888
* * * * *
kt kt
38000
IAS TAS Mach N1 FFlow
200 200 0.302 % 52.3 lb/h/ENG 1073
200 215 0.331 55.7 1009
200 231 0.363 59.3 956
200 250 0.399 63.2 913
200 270 0.440 66.9 880
200 293 0.487 70.4 859
200 318 0.541 74.5 852
200 347 0.603 78.7 861
* * * * *
kt kt
36000
IAS TAS Mach N1 FFlow
200 200 0.302 % 51.7 lb/h/ENG 1055
200 215 0.331 55.2 991
200 231 0.363 58.7 937
200 250 0.399 62.6 894
200 270 0.440 66.3 860
200 293 0.487 69.7 838
200 318 0.541 73.7 829
200 347 0.603 78.0 835
* * * * *
kt kt
34000
IAS TAS Mach N1 FFlow
200 200 0.302 % 51.2 lb/h/ENG 1039
200 215 0.331 54.6 974
200 231 0.363 58.0 920
200 250 0.399 62.0 876
200 270 0.440 65.7 841
200 293 0.487 69.1 818
200 318 0.541 73.0 807
200 347 0.603 77.3 811
* * * * *
kt kt
32000
IAS TAS Mach N1 FFlow
200 200 0.302 % 50.6 lb/h/ENG 1023
200 215 0.331 54.0 958
200 231 0.363 57.5 904
200 250 0.399 61.4 859
200 270 0.440 65.1 824
200 293 0.487 68.5 799
200 318 0.541 72.2 786
200 347 0.603 76.7 788
* * * * *
kt kt
30000
IAS TAS Mach N1 FFlow
200 215 0.331 53.4 943
200 231 0.363 56.9 889
200 250 0.399 60.8 843
200 270 0.440 64.5 807
200 293 0.487 67.9 781
200 318 0.541 71.6 767
200 347 0.603 75.9 767
* * * * *
200 200 0.302 % 50.1 lb/h/ENG 1009
NOTE: MACH setting and FF lb/h/ENG remain constant, regardless of the temperature change.
Page
REVISION 7
1-05-25
Code
5 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-05-25
Code
6 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
HOLDING - ONE ENGINE INOPERATIVE AE3007A1E ENGINES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF MINIMUM FUEL CONSUMPTION SPEED STANDARD ATMOSPHERE
WEIGHT (lb)
ALTITUDE (ft) 0
5000 10000 15000 20000 25000 30000 35000 37000
kt kt
50000
IAS TAS Mach N1 FFlow
180 179 0.272 % 71.9 lb/h/ENG 1804
176 188 0.290 75.6 1777
173 199 0.313 80.0 1774
171 213 0.342 84.3 1792
171 231 0.379 88.7 1836
* * * * *
* * * * *
* * * * *
* * * * *
kt kt
48000
IAS TAS Mach N1 FFlow
178 177 0.268 % 70.8 lb/h/ENG 1737
173 185 0.286 74.5 1706
170 195 0.308 78.8 1697
168 209 0.336 83.1 1711
168 226 0.371 87.3 1748
170 249 0.416 93.6 1813
* * * * *
* * * * *
* * * * *
kt kt
46000
IAS TAS Mach N1 FFlow
175 174 0.265 % 69.7 lb/h/ENG 1670
170 182 0.282 73.4 1635
167 192 0.303 77.5 1623
165 205 0.329 81.9 1631
164 221 0.363 86.1 1663
166 243 0.406 92.5 1719
* * * * *
* * * * *
* * * * *
kt kt
44000
IAS TAS Mach N1 FFlow
173 172 0.261 % 68.6 lb/h/ENG 1605
168 179 0.277 72.3 1566
164 188 0.297 76.2 1549
161 200 0.323 80.6 1553
161 216 0.355 85.0 1578
162 237 0.397 90.6 1627
* * * * *
* * * * *
* * * * *
kt kt
42000
IAS TAS Mach N1 FFlow
165 176 0.273 71.1 1498
161 185 0.292 74.9 1476
158 196 0.316 79.3 1476
157 211 0.347 83.8 1495
158 231 0.387 88.7 1537
* * * * *
* * * * *
* * * * *
170 169 0.258 % 67.4 lb/h/ENG 1540
NOTE: MACH setting and FF lb/h/ENG remain constant, regardless of the temperature change.
Page
REVISION 7
1-05-25
Code
7 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
HOLDING - ONE ENGINE INOPERATIVE AE3007A1E ENGINES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF MINIMUM FUEL CONSUMPTION SPEED STANDARD ATMOSPHERE
WEIGHT (lb)
ALTITUDE (ft) 0
5000 10000 15000 20000 25000 30000 35000 37000
kt kt
40000
IAS TAS Mach N1 FFlow
168 167 0.254 % 66.1 lb/h/ENG 1477
162 173 0.269 69.8 1430
158 181 0.287 73.5 1405
155 192 0.310 78.0 1400
153 206 0.339 82.4 1414
154 224 0.377 86.9 1449
* * * * *
* * * * *
* * * * *
kt kt
38000
IAS TAS Mach N1 FFlow
166 164 0.250 % 64.8 lb/h/ENG 1415
160 170 0.264 68.5 1365
155 178 0.282 72.2 1335
152 188 0.304 76.4 1325
150 201 0.331 81.0 1334
150 218 0.367 85.2 1363
151 241 0.414 91.6 1415
* * * * *
* * * * *
kt kt
36000
IAS TAS Mach N1 FFlow
163 162 0.247 % 63.5 lb/h/ENG 1354
157 167 0.260 67.1 1300
152 174 0.276 70.9 1266
148 184 0.297 74.9 1252
146 196 0.324 79.4 1256
145 212 0.357 83.8 1279
147 233 0.401 90.1 1323
* * * * *
* * * * *
kt kt
34000
IAS TAS Mach N1 FFlow
161 159 0.243 % 62.1 lb/h/ENG 1295
154 164 0.256 65.7 1237
149 171 0.271 69.5 1199
145 180 0.291 73.3 1181
142 191 0.316 77.8 1180
141 206 0.348 82.4 1197
142 226 0.389 87.7 1233
* * * * *
* * * * *
kt kt
32000
IAS TAS Mach N1 FFlow
158 157 0.239 % 60.7 lb/h/ENG 1237
152 161 0.251 64.2 1175
146 167 0.266 67.9 1133
142 175 0.284 71.7 1110
139 186 0.308 76.2 1105
137 200 0.338 80.7 1116
138 218 0.377 85.4 1145
140 243 0.428 93.7 1196
* * * * *
kt kt
30000
IAS TAS Mach N1 FFlow
149 158 0.247 62.6 1114
143 164 0.261 66.3 1069
139 171 0.278 70.1 1042
135 181 0.300 74.3 1032
133 194 0.328 78.9 1038
133 211 0.365 83.3 1060
135 234 0.413 89.7 1102
* * * * *
156 154 0.236 % 57.8 lb/h/ENG 1127
NOTE: MACH setting and FF lb/h/ENG remain constant, regardless of the temperature change.
Page
1-05-25
Code
8 08
REVISION 7
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
HOLDING - ONE ENGINE INOPERATIVE AE3007A1E ENGINES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITHOUT ICE ACCRETION) STANDARD ATMOSPHERE
WEIGHT (lb)
ALTITUDE (ft) 0
5000 10000 15000 20000 25000 30000 35000 37000
kt kt
50000
IAS TAS Mach N1 FFlow
200 200 0.302 % 72.9 lb/h/ENG 2023
200 215 0.331 76.5 1989
200 231 0.363 80.9 1977
200 250 0.399 85.2 1991
* * * * *
* * * * *
* * * * *
* * * * *
* * * * *
kt kt
48000
IAS TAS Mach N1 FFlow
200 200 0.302 % 72.1 lb/h/ENG 1969
200 215 0.331 75.7 1934
200 231 0.363 80.0 1918
200 250 0.399 84.3 1927
* * * * *
* * * * *
* * * * *
* * * * *
* * * * *
kt kt
46000
IAS TAS Mach N1 FFlow
200 200 0.302 % 71.3 lb/h/ENG 1919
200 215 0.331 74.9 1880
200 231 0.363 79.2 1862
200 250 0.399 83.4 1866
200 270 0.440 87.4 1899
* * * * *
* * * * *
* * * * *
* * * * *
kt kt
44000
IAS TAS Mach N1 FFlow
200 200 0.302 % 70.6 lb/h/ENG 1870
200 215 0.331 74.2 1830
200 231 0.363 78.2 1808
200 250 0.399 82.5 1809
200 270 0.440 86.6 1836
* * * * *
* * * * *
* * * * *
* * * * *
kt kt
42000
IAS TAS Mach N1 FFlow
200 215 0.331 73.5 1782
200 231 0.363 77.4 1758
200 250 0.399 81.7 1754
200 270 0.440 85.8 1776
* * * * *
* * * * *
* * * * *
* * * * *
200 200 0.302 % 69.9 lb/h/ENG 1824
NOTE: MACH setting and FF lb/h/ENG remain constant, regardless of the temperature change.
Page
REVISION 7
1-05-25
Code
9 08
FLIGHT PLANNING EMB-135BJ CONFIG D (lb)
AIRPLANE OPERATIONS MANUAL
HOLDING - ONE ENGINE INOPERATIVE AE3007A1E ENGINES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITHOUT ICE ACCRETION) STANDARD ATMOSPHERE
WEIGHT (lb)
ALTITUDE (ft) 0
5000 10000 15000 20000 25000 30000 35000 37000
kt kt
40000
IAS TAS Mach N1 FFlow
200 200 0.302 % 69.2 lb/h/ENG 1780
200 215 0.331 72.8 1736
200 231 0.363 76.5 1710
200 250 0.399 80.9 1703
200 270 0.440 85.1 1720
* * * * *
* * * * *
* * * * *
* * * * *
kt kt
38000
IAS TAS Mach N1 FFlow
200 200 0.302 % 68.5 lb/h/ENG 1739
200 215 0.331 72.0 1693
200 231 0.363 75.8 1664
200 250 0.399 80.2 1655
200 270 0.440 84.3 1668
* * * * *
* * * * *
* * * * *
* * * * *
kt kt
36000
IAS TAS Mach N1 FFlow
200 200 0.302 % 67.7 lb/h/ENG 1700
200 215 0.331 71.4 1653
200 231 0.363 75.0 1622
200 250 0.399 79.5 1609
200 270 0.440 83.5 1618
* * * * *
* * * * *
* * * * *
* * * * *
kt kt
34000
IAS TAS Mach N1 FFlow
200 200 0.302 % 67.1 lb/h/ENG 1663
200 215 0.331 70.7 1614
200 231 0.363 74.3 1582
200 250 0.399 78.7 1567
200 270 0.440 82.7 1572
* * * * *
* * * * *
* * * * *
* * * * *
kt kt
32000
IAS TAS Mach N1 FFlow
200 200 0.302 % 66.4 lb/h/ENG 1629
200 215 0.331 70.0 1579
200 231 0.363 73.7 1544
200 250 0.399 77.9 1527
200 270 0.440 82.0 1529
200 293 0.487 86.1 1555
* * * * *
* * * * *
* * * * *
kt kt
30000
IAS TAS Mach N1 FFlow
200 215 0.331 69.4 1545
200 231 0.363 73.0 1509
200 250 0.399 77.1 1489
200 270 0.440 81.3 1489
200 293 0.487 85.4 1511
* * * * *
* * * * *
* * * * *
200 200 0.302 % 65.8 lb/h/ENG 1596
NOTE: MACH setting and FF lb/h/ENG remain constant, regardless of the temperature change.
Page
1-05-25
Code
10 08
REVISION 7
AIRPLANE OPERATIONS MANUAL
FLIGHT PLANNING EMB-135BJ CONFIG D (FAA)
ONE ENGINE INOPERATIVE PERFORMANCE CRUISE TABLES The one engine inoperative long range cruise tables show N1, fuel flow, indicated airspeed, true airspeed, indicated Mach number, buffet margin and specific range. Data are presented for various weights and altitudes. The associated conditions are: - Flaps .................................... UP - Gear..................................... UP - Bleeds.................................. OPEN - Anti-Ice................................. OFF
Page
REVISION 4
1-05-30
Code
1 11
FLIGHT PLANNING EMB-135BJ CONFIG D (FAA)
AIRPLANE OPERATIONS MANUAL
LONG RANGE CRUISE - ONE ENGINE INOPERATIVE AE3007A1E ENGINES ALTITUDE: 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITION
WEIGHT (lb)
ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000
50000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
82.3 85.7 86.4 87.1 87.9 88.5 89.3 90.0 90.8 2251 2220 2219 2216 2217 2217 2220 2224 2229 248 244 243 243 242 241 241 240 240 266 282 285 289 292 296 300 304 308 0.409 0.441 0.449 0.456 0.463 0.471 0.479 0.487 0.495 2.56 2.53 2.51 2.48 2.46 2.43 2.40 2.38 2.35 0.118 0.127 0.129 0.130 0.132 0.134 0.135 0.137 0.138
48000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
81.2 84.6 85.4 86.1 86.8 87.5 88.2 89.0 89.8 2162 2129 2128 2123 2122 2123 2125 2128 2133 243 240 239 238 238 237 237 236 236 261 277 281 284 287 291 295 299 303 0.402 0.434 0.441 0.448 0.455 0.463 0.471 0.479 0.487 2.56 2.56 2.54 2.51 2.48 2.45 2.43 2.40 2.38 0.121 0.130 0.132 0.134 0.135 0.137 0.139 0.140 0.142
46000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
80.0 83.5 84.3 85.0 85.7 86.5 87.2 87.9 88.6 2076 2040 2036 2032 2029 2031 2030 2031 2033 239 235 235 234 233 233 232 232 231 257 272 275 279 282 286 289 293 297 0.395 0.426 0.433 0.440 0.447 0.454 0.462 0.470 0.478 2.56 2.56 2.55 2.53 2.50 2.48 2.45 2.43 2.40 0.124 0.133 0.135 0.137 0.139 0.141 0.143 0.144 0.146
44000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
78.8 82.4 83.1 83.8 84.6 85.3 86.1 86.8 87.5 1991 1952 1946 1941 1939 1937 1936 1935 1936 235 231 230 229 229 228 228 227 226 252 267 270 273 277 280 284 287 291 0.388 0.418 0.425 0.431 0.438 0.446 0.453 0.460 0.468 2.56 2.56 2.56 2.55 2.53 2.50 2.48 2.45 2.42 0.127 0.137 0.139 0.141 0.143 0.145 0.147 0.148 0.150
42000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
77.6 81.4 82.0 82.7 83.4 84.1 84.8 85.6 86.4 1910 1865 1858 1852 1850 1846 1843 1841 1843 230 226 226 225 224 224 223 222 222 247 262 265 268 271 275 278 281 285 0.381 0.410 0.416 0.423 0.430 0.437 0.444 0.451 0.459 2.56 2.56 2.56 2.56 2.55 2.53 2.50 2.47 2.45 0.129 0.140 0.142 0.145 0.147 0.149 0.151 0.153 0.155
Page
1-05-30
Code
2 11
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (FAA)
AIRPLANE OPERATIONS MANUAL
LONG RANGE CRUISE - ONE ENGINE INOPERATIVE AE3007A1E ENGINES ALTITUDE: 5000 FT TO 17000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITION
WEIGHT (lb)
ALTITUDE (ft) 5000 10000 11000 12000 13000 14000 15000 16000 17000
40000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
76.4 80.2 80.9 81.5 82.2 82.9 83.6 84.3 85.1 1826 1780 1772 1765 1763 1757 1752 1751 1752 226 222 221 220 220 219 218 218 217 242 256 259 262 266 269 272 276 280 0.373 0.402 0.408 0.414 0.421 0.428 0.435 0.442 0.450 2.56 2.56 2.56 2.56 2.56 2.55 2.52 2.50 2.48 0.133 0.144 0.146 0.149 0.151 0.153 0.155 0.157 0.160
38000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
75.2 78.8 79.6 80.3 81.0 81.6 82.3 83.1 83.8 1745 1696 1687 1679 1677 1668 1663 1662 1660 221 217 216 215 215 214 213 213 212 237 251 254 257 260 263 266 270 273 0.365 0.393 0.399 0.405 0.413 0.418 0.425 0.433 0.440 2.56 2.56 2.56 2.56 2.56 2.56 2.55 2.53 2.51 0.136 0.148 0.151 0.153 0.155 0.158 0.160 0.162 0.165
36000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
74.0 77.3 78.1 78.9 79.7 80.3 81.0 81.8 82.4 1665 1613 1602 1594 1589 1581 1577 1575 1569 216 212 211 211 210 209 208 208 207 232 246 248 251 254 257 260 264 267 0.357 0.385 0.390 0.396 0.403 0.409 0.416 0.423 0.430 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.53 0.139 0.152 0.155 0.157 0.160 0.163 0.165 0.168 0.170
34000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
72.8 75.9 76.6 77.4 78.2 79.0 79.7 80.4 81.0 1588 1531 1519 1511 1505 1496 1492 1488 1480 211 207 206 206 205 204 204 203 202 227 240 242 245 248 251 254 258 260 0.350 0.376 0.381 0.387 0.394 0.399 0.406 0.413 0.419 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.55 0.143 0.157 0.159 0.162 0.165 0.168 0.170 0.173 0.176
32000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
71.4 74.5 75.1 75.8 76.6 77.3 78.2 79.0 79.6 1508 1451 1437 1430 1421 1413 1408 1401 1394 206 202 201 201 200 199 199 198 197 222 234 236 239 242 245 248 251 254 0.341 0.367 0.372 0.378 0.384 0.390 0.396 0.403 0.409 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 2.56 0.147 0.161 0.164 0.167 0.170 0.173 0.176 0.179 0.182
Page
REVISION 4
1-05-30
Code
3 11
FLIGHT PLANNING EMB-135BJ CONFIG D (FAA)
AIRPLANE OPERATIONS MANUAL
LONG RANGE CRUISE - ONE ENGINE INOPERATIVE AE3007A1E ENGINES ALTITUDE: 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITION
WEIGHT (lb)
ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000
50000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
91.1 91.6 92.1 92.6 93.0 93.4 2229 2183 2137 2080 2021 1966 239 233 228 220 212 201 311 309 307 302 295 285 0.503 0.501 0.500 0.493 0.484 0.470 2.31 2.20 2.10 1.97 1.83 1.66 0.140 0.142 0.144 0.145 0.146 0.145
-
-
-
48000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
90.6 91.5 92.0 92.4 92.9 93.4 93.7 2139 2188 2143 2091 2035 1988 1939 235 238 233 227 220 213 205 307 316 314 311 306 302 296 0.496 0.512 0.510 0.509 0.502 0.497 0.490 2.35 2.37 2.27 2.16 2.03 1.91 1.78 0.144 0.144 0.146 0.149 0.150 0.152 0.153
-
-
46000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
89.4 90.2 91.3 92.3 92.8 93.3 93.7 93.3 2036 2041 2049 2098 2047 2003 1956 1841 230 230 230 232 227 221 215 199 301 305 309 318 316 313 309 291 0.486 0.494 0.504 0.520 0.518 0.516 0.511 0.485 2.37 2.34 2.31 2.33 2.22 2.12 2.00 1.75 0.148 0.149 0.151 0.152 0.154 0.156 0.158 0.158
-
44000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
88.2 89.0 89.8 90.9 92.2 93.2 93.6 93.2 92.7 1939 1947 1947 1952 1960 2013 1969 1858 1741 226 226 225 224 224 227 222 209 192 295 299 303 307 312 321 319 306 286 0.476 0.486 0.493 0.502 0.511 0.530 0.528 0.508 0.479 2.39 2.37 2.34 2.31 2.28 2.30 2.19 1.98 1.71 0.152 0.154 0.156 0.157 0.159 0.160 0.162 0.165 0.164
42000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
87.1 87.8 88.5 89.4 90.5 91.7 93.0 93.1 92.7 1846 1845 1849 1857 1859 1865 1877 1869 1759 221 221 220 220 219 219 219 216 203 289 293 297 301 305 309 314 316 303 0.467 0.475 0.483 0.493 0.501 0.510 0.520 0.525 0.505 2.43 2.39 2.37 2.34 2.31 2.28 2.25 2.18 1.97 0.157 0.159 0.161 0.162 0.164 0.166 0.168 0.169 0.172
Page
1-05-30
Code
4 11
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (FAA)
AIRPLANE OPERATIONS MANUAL
LONG RANGE CRUISE - ONE ENGINE INOPERATIVE AE3007A1E ENGINES ALTITUDE: 18000 FT TO 26000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITION
WEIGHT (lb)
ALTITUDE (ft) 18000 19000 20000 21000 22000 23000 24000 25000 26000
40000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
85.9 86.6 87.3 88.0 88.9 90.0 91.2 92.5 92.6 1751 1749 1756 1754 1759 1768 1770 1781 1770 217 216 216 215 214 214 213 213 210 283 287 291 294 299 303 307 312 313 0.457 0.465 0.474 0.481 0.490 0.500 0.508 0.519 0.522 2.45 2.42 2.40 2.37 2.34 2.31 2.28 2.25 2.18 0.162 0.164 0.166 0.168 0.170 0.172 0.173 0.175 0.177
38000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
84.5 85.3 86.0 86.7 87.6 88.3 89.4 90.6 91.9 1656 1658 1657 1658 1665 1664 1673 1675 1685 211 211 210 210 210 209 209 208 208 277 280 284 288 292 296 301 304 309 0.447 0.455 0.463 0.471 0.480 0.488 0.498 0.506 0.516 2.47 2.45 2.42 2.39 2.38 2.34 2.31 2.28 2.25 0.167 0.169 0.171 0.174 0.176 0.178 0.180 0.182 0.184
36000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
83.2 84.0 84.7 85.5 86.1 86.9 87.7 88.7 89.9 1566 1569 1563 1567 1565 1569 1571 1579 1581 206 206 205 205 204 204 203 203 202 270 274 277 282 285 289 293 298 301 0.437 0.445 0.452 0.461 0.468 0.477 0.485 0.495 0.503 2.50 2.49 2.45 2.43 2.40 2.37 2.34 2.32 2.28 0.173 0.175 0.177 0.180 0.182 0.184 0.186 0.189 0.191
34000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
81.8 82.5 83.3 84.1 84.8 85.5 86.2 87.0 88.0 1478 1476 1473 1473 1472 1475 1475 1478 1485 202 201 200 200 199 199 198 198 198 264 267 271 274 278 282 286 290 294 0.426 0.434 0.441 0.449 0.457 0.465 0.473 0.482 0.492 2.53 2.51 2.48 2.46 2.43 2.41 2.37 2.34 2.32 0.178 0.181 0.184 0.186 0.189 0.191 0.194 0.196 0.198
32000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
80.3 81.0 81.8 82.5 83.3 84.0 84.8 85.5 86.3 1392 1386 1386 1381 1383 1380 1384 1383 1385 197 196 195 195 194 193 193 192 192 257 260 264 267 271 274 279 282 286 0.416 0.423 0.431 0.437 0.446 0.453 0.462 0.470 0.478 2.56 2.53 2.52 2.48 2.46 2.43 2.41 2.38 2.35 0.185 0.188 0.190 0.193 0.196 0.199 0.201 0.204 0.207
Page
REVISION 4
1-05-30
Code
5 11
FLIGHT PLANNING EMB-135BJ CONFIG D (FAA)
AIRPLANE OPERATIONS MANUAL
LONG RANGE CRUISE - ONE ENGINE INOPERATIVE AE3007A1E ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITION
WEIGHT (lb)
ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000
50000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
-
-
-
-
-
-
-
-
-
48000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
-
-
-
-
-
-
-
-
-
46000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
-
-
-
-
-
-
-
-
-
44000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
-
-
-
-
-
-
-
-
-
42000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
92.2 1651 187 283 0.476 1.70 0.172
-
-
-
-
-
-
-
-
Page
1-05-30
Code
6 11
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (FAA)
AIRPLANE OPERATIONS MANUAL
LONG RANGE CRUISE - ONE ENGINE INOPERATIVE AE3007A1E ENGINES ALTITUDE: 27000 FT TO 35000 FT CRUISE CONFIGURATION BLEED: OPEN ISA CONDITION
WEIGHT (lb)
ALTITUDE (ft) 27000 28000 29000 30000 31000 32000 33000 34000 35000
40000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
92.2 91.7 1668 1560 198 181 300 279 0.503 0.472 1.96 1.67 0.180 0.179
-
-
-
-
-
-
-
38000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
92.1 91.6 91.9 92.1 1678 1578 1535 1486 205 193 186 176 311 298 291 281 0.521 0.502 0.493 0.479 2.18 1.96 1.82 1.65 0.185 0.189 0.190 0.189
-
-
-
-
-
36000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
91.3 91.5 91.9 92.1 92.5 93.0 1591 1588 1548 1508 1478 1445 202 200 195 189 184 177 307 309 305 301 298 293 0.514 0.520 0.516 0.513 0.509 0.503 2.26 2.19 2.07 1.96 1.85 1.72 0.193 0.194 0.197 0.200 0.201 0.202
-
-
-
34000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
89.2 90.6 91.5 92.1 92.5 93.1 93.0 1486 1497 1501 1522 1496 1470 1397 197 197 196 197 193 188 178 298 303 307 314 312 311 299 0.500 0.511 0.520 0.534 0.534 0.533 0.516 2.28 2.26 2.22 2.21 2.11 2.01 1.82 0.201 0.203 0.205 0.206 0.209 0.211 0.214
-
-
32000
N1 % F FLOW lb/H/ENG IAS KT TAS KT INDICATED MACH BUFFET MARGIN G SR NM/lb
87.2 88.3 89.7 90.8 91.7 92.6 93.0 95.0 1391 1393 1401 1405 1414 1422 1418 1345 192 191 191 190 190 190 188 178 291 295 299 304 309 313 316 304 0.488 0.497 0.507 0.516 0.527 0.537 0.544 0.527 2.33 2.29 2.27 2.23 2.20 2.16 2.10 1.90 0.209 0.211 0.214 0.216 0.218 0.220 0.223 0.226
-
Page
REVISION 4
1-05-30
Code
7 11
FLIGHT PLANNING EMB-135BJ CONFIG D (FAA)
AIRPLANE OPERATIONS MANUAL
DRIFTDOWN TABLE In the event of an engine failure during cruise it will generally be necessary to reduce speed and descent to a lower altitude. Immediately after engine failure set maximum continuous N1 and allow the airplane to decelerate from the cruise speed to the initial drift down speed shown in the driftdown table. When this speed is achieved start the descend profile. The airplane should level off at the gross altitude and weight shown in the driftdown table. NET LEVEL OFF ALTITUDE Federal regulations require terrain clearance flight planning based on net performance which is the gross (or real) gradient performance degraded by 1.1%. To determine the net level off pressure altitude, enter with the gross weight, proceed to the ISA deviation and find the value within bracket. This is the net level off pressure altitude. The net level off pressure altitude must clear all en-route obstacle by at least 1000 ft.
Page
1-05-30
Code
8 11
REVISION 4
AIRPLANE OPERATIONS MANUAL
FLIGHT PLANNING EMB-135BJ CONFIG D (FAA)
DRIFTDOWN TABLE EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION BLEEDS OPEN/ANTI-ICE OFF WEIGHT (lb)
INITIAL DRIFTDOWN
START DRIFTDOWN
LEVEL OFF
SPEED
50000
50000
173
48000
48000
170
46000
46000
167
44000
44000
164
42000
42000
161
40000
40000
157
38000
38000
154
36000
36000
150
34000
34000
146
32000
32000
142
GROSS LEVEL OFF ALTITUDE - ft (NET LEVEL OFF ALTITUDE - ft) ISA
ISA + 10
ISA + 20
21680 (16330) 23047 (17805) 24315 (19685) 25500 (21290) 26315 (22545) 27370 (24100) 28935 (25240) 31080 (26390) 32830 (27550) 34230 (29380)
21600 (16195) 22945 (17650) 24250 (19560) 25430 (21190) 26250 (22450) 27330 (24035) 28555 (25170) 30620 (26330) 32375 (27525) 33960 (28935)
19995 (14985) 21255 (16355) 22575 (17860) 24080 (19580) 24955 (20795) 25985 (22260) 27097 (23740) 28440 (25035) 29905 (26235) 31435 (27495)
(KIAS)
Page
REVISION 4
1-05-30
Code
9 11
FLIGHT PLANNING EMB-135BJ CONFIG D (FAA)
AIRPLANE OPERATIONS MANUAL
HOLDING The holding tables show indicated airspeed, mach number, N1, fuel flow and fuel consumption for various weights and altitudes. Data are presented in ISA condition for all engines operating and one engine inoperative configuration. For both conditions, tables for anti-ice on (with and without ice accretion) and off are provided. The associated conditions are: - Flaps .................................... UP - Gears ................................... UP - Bleeds .................................. OPEN - Airspeed ............................... Minimum Fuel Consumption Speed - Anti-Ice................................. ON or OFF
Page
1-05-30
Code
10 11
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (FAA)
AIRPLANE OPERATIONS MANUAL
HOLDING - ONE ENGINE INOPERATIVE AE3007A1E ENGINES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF MINIMUM FUEL CONSUMPTION SPEED STANDARD ATMOSPHERE
ALTITUDE (ft) WEIGHT (lb) 0
50000
48000
46000
44000
42000
5000 10000 15000 20000 25000 30000 35000 39000
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
178 181 181 181 183 177 193 209 226 247 0.269 0.299 0.328 0.362 0.404 71.9 75.7 80.0 84.3 88.7 1802 1783 1781 1799 1847 1802 1783 1781 1799 1847
-
-
-
-
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
174 176 177 177 179 173 189 205 221 242 0.264 0.292 0.322 0.354 0.395 70.7 74.6 78.8 83.1 87.3 1732 1710 1705 1718 1758 1732 1710 1705 1718 1758
-
-
-
-
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
170 172 174 173 175 176 169 184 201 216 236 258 0.258 0.285 0.316 0.347 0.386 0.431 69.6 73.4 77.5 81.9 86.1 92.2 1663 1637 1630 1637 1670 1729 1663 1637 1630 1637 1670 1729
-
-
-
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
167 168 171 170 171 172 165 179 197 211 230 252 0.252 0.278 0.310 0.339 0.377 0.422 68.4 72.3 76.3 80.6 85.0 90.4 1595 1566 1556 1559 1585 1637 1595 1566 1556 1559 1585 1637
-
-
-
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
163 164 166 166 166 168 161 175 191 206 224 247 0.246 0.271 0.301 0.332 0.368 0.413 67.2 71.1 74.9 79.3 83.8 88.6 1528 1496 1482 1481 1501 1547 1528 1496 1482 1481 1501 1547
-
-
-
NOTE: MACH setting and FF lb/H/ENG remain constant, regardless of the temperature change.
Page
REVISION 4
1-05-30
Code
11 11
FLIGHT PLANNING EMB-135BJ CONFIG D (FAA)
AIRPLANE OPERATIONS MANUAL
HOLDING - ONE ENGINE INOPERATIVE AE3007A1E ENGINES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: OFF MINIMUM FUEL CONSUMPTION SPEED STANDARD ATMOSPHERE
ALTITUDE (ft) WEIGHT (lb) 0
40000
38000
36000
34000
32000
30000
5000 10000 15000 20000 25000 30000 35000 39000
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
159 159 161 162 162 164 157 170 185 201 218 240 0.240 0.264 0.293 0.324 0.358 0.402 65.8 69.7 73.6 78.0 82.4 86.8 1461 1427 1409 1405 1419 1457 1461 1427 1409 1405 1419 1457
-
-
-
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
155 155 157 158 158 159 160 154 165 180 197 212 233 255 0.235 0.257 0.285 0.317 0.349 0.391 0.437 64.4 68.3 72.3 76.5 81.0 85.2 91.5 1395 1358 1337 1331 1339 1369 1423 1395 1358 1337 1331 1339 1369 1423
-
-
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
151 151 152 155 154 155 156 150 160 174 192 207 226 249 0.229 0.250 0.276 0.309 0.340 0.379 0.426 62.9 66.9 70.9 74.9 79.4 83.8 89.8 1330 1291 1266 1258 1261 1284 1330 1330 1291 1266 1258 1261 1284 1330
-
-
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
147 147 147 149 150 150 152 146 156 169 185 201 219 242 0.223 0.243 0.268 0.299 0.331 0.368 0.415 61.4 65.4 69.4 73.4 77.9 82.4 87.5 1266 1225 1197 1184 1184 1201 1240 1266 1225 1197 1184 1184 1201 1240
-
-
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
144 142 143 144 145 145 147 147 142 151 163 178 195 212 234 256 0.217 0.236 0.259 0.289 0.322 0.357 0.402 0.450 59.8 63.8 67.8 71.7 76.2 80.7 85.3 91.9 1202 1159 1129 1112 1109 1120 1152 1203 1202 1159 1129 1112 1109 1120 1152 1203
-
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
140 138 138 139 141 140 142 143 137 146 157 172 189 205 225 248 0.211 0.229 0.251 0.279 0.313 0.345 0.388 0.436 58.1 62.0 66.1 70.1 74.3 78.9 83.3 89.6 1139 1095 1062 1042 1036 1041 1065 1108 1139 1095 1062 1042 1036 1041 1065 1108
-
NOTE: MACH setting and FF lb/H/ENG remain constant, regardless of the temperature change. Page
1-05-30
Code
12 11
REVISION 4
FLIGHT PLANNING EMB-135BJ CONFIG D (FAA)
AIRPLANE OPERATIONS MANUAL
HOLDING - ONE ENGINE INOPERATIVE AE3007A1E ENGINES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITHOUT ICE ACCRETION) STANDARD ATMOSPHERE
ALTITUDE (ft) WEIGHT (lb) 0
50000
48000
46000
44000
42000
5000 10000 15000 20000 25000 30000 35000 39000
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
200 200 200 200 200 200 215 231 250 270 0.302 0.331 0.363 0.399 0.440 72.9 76.5 80.9 85.2 89.3 1872 1851 1850 1870 1915 1872 1851 1850 1870 1915
-
-
-
-
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
200 200 200 200 200 200 215 231 250 270 0.302 0.331 0.363 0.399 0.440 72.1 75.7 80.0 84.3 88.3 1820 1797 1792 1808 1848 1820 1797 1792 1808 1848
-
-
-
-
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
200 200 200 200 200 200 215 231 250 270 0.302 0.331 0.363 0.399 0.440 71.3 74.9 79.2 83.4 87.4 1771 1745 1738 1750 1784 1771 1745 1738 1750 1784
-
-
-
-
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
200 200 200 200 200 200 215 231 250 270 0.302 0.331 0.363 0.399 0.440 70.6 74.2 78.2 82.5 86.6 1724 1696 1686 1694 1724 1724 1696 1686 1694 1724
-
-
-
-
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
200 200 200 200 200 200 215 231 250 270 0.302 0.331 0.363 0.399 0.440 69.9 73.5 77.4 81.7 85.8 1679 1649 1636 1641 1666 1679 1649 1636 1641 1666
-
-
-
-
NOTE: MACH setting and FF lb/H/ENG remain constant, regardless of the temperature change.
Page
REVISION 4
1-05-30
Code
13 11
FLIGHT PLANNING EMB-135BJ CONFIG D (FAA)
AIRPLANE OPERATIONS MANUAL
HOLDING - ONE ENGINE INOPERATIVE AE3007A1E ENGINES CRUISE CONFIGURATION BLEED: OPEN ANTI-ICE: ON (WITHOUT ICE ACCRETION) STANDARD ATMOSPHERE
ALTITUDE (ft) WEIGHT (lb) 0
40000
38000
36000
34000
32000
30000
5000 10000 15000 20000 25000 30000 35000 39000
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
200 200 200 200 200 200 215 231 250 270 0.302 0.331 0.363 0.399 0.440 69.2 72.8 76.5 80.9 85.1 1637 1605 1590 1591 1613 1637 1605 1590 1591 1613
-
-
-
-
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
200 200 200 200 200 200 215 231 250 270 0.302 0.331 0.363 0.399 0.440 68.5 72.0 75.8 80.2 84.3 1596 1563 1546 1544 1562 1596 1563 1546 1544 1562
-
-
-
-
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
200 200 200 200 200 200 200 215 231 250 270 293 0.302 0.331 0.363 0.399 0.440 0.487 67.7 71.4 75.0 79.5 83.5 87.6 1559 1524 1504 1500 1514 1548 1559 1524 1504 1500 1514 1548
-
-
-
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
200 200 200 200 200 200 200 215 231 250 270 293 0.302 0.331 0.363 0.399 0.440 0.487 67.0 70.7 74.3 78.7 82.7 86.8 1523 1487 1465 1459 1469 1499 1523 1487 1465 1459 1469 1499
-
-
-
IAS KT TAS KT MACH FF lb/H/ENG FC lb/H
200 200 200 200 200 200 200 215 231 250 270 293 0.302 0.331 0.363 0.399 0.440 0.487 1490 1452 1429 1420 1428 1453 1490 1452 1429 1420 1428 1453
-
-
-
IAS KT TAS KT MACH N1 % FF lb/H/ENG FC lb/H
200 200 200 200 200 200 200 215 231 250 270 293 0.302 0.331 0.363 0.399 0.440 0.487 65.8 69.4 73.0 77.1 81.3 85.4 1458 1420 1395 1384 1389 1411 1458 1420 1395 1384 1389 1411
-
-
-
NOTE: MACH setting and FF lb/H/ENG remain constant, regardless of the temperature change.
Page
1-05-30
Code
14 11
REVISION 4
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
SECTION 1-12 GROUND SERVICING TABLE OF CONTENTS Page Block INTRODUCTION ....................................................................... 1-12-00 EXTERNAL CONNECTIONS .................................................... 1-12-05 TOWING .................................................................................... 1-12-10 PARKING/MOORING ................................................................ 1-12-15 COLD WEATHER OPERATION................................................ 1-12-20 FUEL SYSTEM SERVICING ..................................................... 1-12-25 ENGINE OIL SERVICING.......................................................... 1-12-30 APU OIL SERVICING ................................................................ 1-12-35 HYDRAULIC/LANDING GEAR SERVICING ............................. 1-12-40 OXYGEN SERVICING ............................................................... 1-12-45 WATER/TOILET SERVICING ................................................... 1-12-50
Page
REVISION 5
1-12-00
Code
1 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-12-00
Code
2 01
ORIGINAL
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
INTRODUCTION General guidelines are provided herein related to the ground handling and servicing of the airplane. They are intended to make flight crews familiar with the ordinary aspects of the subject, as those tasks described herein normally are the responsibility of the maintenance personnel. For further instructions pertaining the subjects covered herein refer to the Aircraft Maintenance Manual.
Page
NOVEMBER 30, 2001
1-12-00
Code
3 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-12-00
Code
4 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
EXTERNAL CONNECTIONS CONNECTING ELECTRICAL POWER SUPPLY A 28 V DC external power supply source can be connected to the aircraft through the receptacle installed on the left side of the fuselage nose. It is recommended that the external power source be capable of supplying at least 300 amperes. Connecting a lower capacity source may lead to electrical problems and therefore should not avoided. Before energizing the aircraft, it must be assured that aircraft systems are in a safe condition, and that energizing will not cause any injury to persons or damage to equipment. It must also be assured that external power output voltage is 28 V DC. When using an AC fed external power source, a ground connection between the hangar structure and the power source, and another one between the power source and the aircraft are necessary.
CONNECTING ELECTRICAL POWER SUPPLY Page
NOVEMBER 30, 2001
1-12-05
Code
1 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
CONNECTING THE PNEUMATIC START UNIT The pneumatic start unit is connected to the aircraft through the receptacle on the right side of the rear fuselage. The output of the unit must be set between 40 and 45 psi. This pressure allows the opening of the valve to let external air in.
Page
1-12-05
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
PNEUMATIC START UNIT CONNECTION
Page
NOVEMBER 30, 2001
1-12-05
Code
3 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
AIR CONDITIONING GROUND CONNECTION An external conditioned air-source can be connected to the airplane to supply hot or cold air directly into the cabin. The operation consists of connecting the source and starting supply to the aircraft. Supplied air pressure must not exceed 356 mm H2O (14 o o in H2O), maximum air temperature must not exceed 71 C (160 F) and 3 3 maximum flow must not exceed 3,5 m /min (122 ft /min, 92 lbm/min). The use of external conditioned air does not require any setting of the aircraft systems since the external conditioned air goes directly to the distribution ducts. However, it is recommended that the main door be left open when external air is being used, to prevent inadequate external source operation and to avoid cabin bump.
Page
1-12-05
Code
4 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
AIR CONDITIONING GROUND CONNECTION
Page
NOVEMBER 30, 2001
1-12-05
Code
5 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
STATIC GROUNDING There are three grounding points on the aircraft. Two of them are installed on the lower surface of each wing leading edge and one is aft of the nose landing gear. To ground the aircraft properly, proceed as follow: − Make sure that the aircraft is parked adjacent to an approved grounding point. NOTE: - For general grounding, use a 4-AWG extra-flexible special PVC-insulated, low voltage cable, and a PL-055-type plug (specification MS 3493). - To ground the refueling nozzle or the oxygen charger adapter, use a 3/32"-diameter steel cable (specification MILW-83343, MIL-W-5424 or MIL-W-1511) with plug (specification MIL-C-83413/4) and an alligator clip. − Examine the static ground cable for damage and to make sure that the end-fittings are correctly attached. CAUTION: USE THE GROUNDING POINTS SHOWN IN FIGURE ABOVE ONLY. THE USE OF OTHER POINTS MAY RESULT IN POOR GROUNDING. − Connect the static ground cable plug to one of the grounding points on the lower surface of each wing leading edge and the other end to an earth grounding point. − Connect the static grounding cable of the ground support equipment to an earth grounding point. − Connect static grounding cable plug of ground support equipment to one of the aircraft grounding points. − Connect the applicable ground support equipment.
Page
1-12-05
Code
6 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
STATIC GROUDING
Page
NOVEMBER 30, 2001
1-12-05
Code
7 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-12-05
Code
8 01
NOVEMBER 30, 2001
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
TOWING Ground towing is normally accomplished by using ground support equipment P/N 01-1201-0000 (tow bar) and 01-0582-0010 (towbar attachment) coupled to the landing gear. The tow bar incorporates breakable sections (fuse) with the purpose of causing the tow bar to break in case of any towing abnormality, to protect the aircraft structure or the nose landing gear from damage. Maximum towbar fuse push/pull design force is 4418 kgf (9740 lbf). Maximum design torque is 4300 N.m (3171.5 lbf.ft). o Maximum nosewheel displacement during towing is 170 to the left or to the right. The maximum recommended wind speeds for aircraft Towing, Pivoting, Turning and Taxi are: WEIGHT (Kg) 13000 RUNWAY Dry Wet Snow Covered Ice Covered
55 47 32 21
18500 WIND SPEED (KIAS) 64 54 37 24
22270 65 60 41 27
NOTE: Towing without the towbar is prohibited, except to airplanes that is towed using LEKTRO towbarless tug vehicle model AP8750A-AL with GSE 298 pawl adapter. The main landing gear has hard points to attach winch, cables or bars for towing the aircraft fore and aft in abnormal conditions such as in soft mud, snow etc.
TOWING PREPARATION The following precautions apply when towing the aircraft: − Tow the aircraft with the hydraulic system 1 and 2 depressurized. In case it is suspected that Emergency/Parking Brake has no accumulator charge to supply power for an eventual actuation, turn electric hydraulic pump #2 for a few seconds and then turn electric hydraulic pump off again. NOTE: Turning on an electric hydraulic pump using batteries only can discharge the batteries. The use of the APU generator to supply electrical power is recommended.
Page
NOVEMBER 30, 2001
1-12-10
Code
1 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
CAUTION: TOW THE AIRCRAFT WITH THE HYDRAULIC SYSTEM 1 DEPRESSURIZED, TO PREVENT STEERING SYSTEM FROM BEING ACTUATED. IF IT IS NECESSARY TO TOW THE AIRCRAFT WITH THE SYSTEM 2 PRESSURIZED, DO NOT ACTUATE STEERING. − Disengage the steering system through the Steering Disengage Button located on the control wheel (pilot or copilot). The STEER INOP message appears on the EICAS. − During the towing operations, a technician must stay in the cockpit to set the emergency/parking brake, if necessary. − Make sure that the landing gear safety pins are correctly installed.
TOWING OPERATION Towing operation is accomplished following the steps below: − Remove the lock pin from the guide pin on tow bar assemblies. − Install tow bar on the nose landing gear. − Put the guide pin into the towing point of the nose landing gear. − Lock the guide pin with the lock pin. − Install the other side of tow bar assemblies to the tractor. − Remove the wheel chocks. − Release the emergency/parking brake. After towing operation is finished: − Apply the emergency/parking brake or install the wheel chocks, as required. − Make sure that landing gear safety pins are correctly installed. − Make sure that nose wheel displacement are below the maximum operational limit . − Remove tow bar. − Remove the lock pin from the guide pin on the tow bar assembly. − Remove the guide pin from the towing point of the nose landing gear. − Remove the tow bar assembly from the nose landing gear. NOTE: Steering handle actuation with nose wheels beyond their operational limits may cause damage to the nose wheel steering system.
Page
1-12-10
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
TOWING EQUIPMENT Page
NOVEMBER 30, 2001
1-12-10
Code
3 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
HAZARD AREAS
Page
1-12-10
Code
4 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
PARKING Instructions contained herein cover only normal parking, i.e. the parking between flights and the overnight stop. In case of prolonged parking, or parking in an extremely adverse weather condition, assistance of a maintenance technician is required.
PREPARATION Make sure there is a minimum distance from other parked aircraft to permit the aircraft movement and that there is a minimum distance of 4.5 meters between APU exhaust port and an adjacent aircraft fuel tank vent. NOTE: The aircraft must be sheltered in the hangar when there are wind velocities of 65 knots or more. If the aircraft is exposed to winds exceeding 65 knots, an inspection according to TASK 05-50-04-200-802-A (AMM) should be carried out. For winds exceeding 30 knots, it is recommended to park the aircraft headed into the wind whenever possible.
PARKING Normal parking is performed according to the procedure below: − Make sure that the safety pins are installed to each landing gear. CAUTION: IF THE RELATED LANDING GEAR SAFETY PINS ARE NOT INSTALLED, INJURY TO PEOPLE AND/OR DAMAGE TO THE AIRCRAFT/EQUIPMENT MAY OCCUR. NOTE: Before parking the aircraft, move it approximately three meters in a straight line to remove all torsional stresses applied to the landing gear components and tires during a turn. − Ground the aircraft. − If there is ice or snow in the parking area, put mat, thick sand or other applicable material under the tires, to prevent them from freezing. CAUTION: IF THE BRAKES ARE TOO HOT, DO NOT APPLY PARKING BRAKES UNTIL THEY ARE COOLER. THIS WILL PREVENT BRAKE DISCS FROM BONDING.
Page
NOVEMBER 30, 2001
1-12-15
Code
1 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
− − − − −
Set the emergency/parking brake. Retract the flaps if they are extended. Set the gust lock lever. Put the chocks against the landing gear wheels. To prevent the courtesy light from discharging the battery, pull the COURTESY LIGHT (A22) circuit breaker. − Install the covers to the pitot tubes, total-air-temperature (TAT) sensor, tail cone, nose cowl, ice detector, engine/APU air intakes and exhaust nozzles, and anemometrical static ports.
RETURN TO SERVICE − Remove the chocks from the landing gear wheels. − Remove the covers from the pitot tubes, TAT sensor, tail cone, nose cowl, ice detector, engine/APU air intakes and exhaust nozzles, and anemometrical static ports. − Make sure that the control handle of the landing gear is at the down position. − Make sure that the safety pins are installed to each landing gear. CAUTION: MAKE SURE THE SAFETY PINS ARE REMOVED BEFORE TAXYING THE AIRCRAFT FOR TAKEOFF. − Unground the aircraft. − Release the emergency/parking brake. − Release the gust lock lever.
Page
1-12-15
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
MOORING Mooring is necessary when the weather conditions are bad or unknown. The area where the aircraft is to be parked in and moored must be paved and level, with ground tiedown anchors available.
MOORING THE AIRPLANE
Page
NOVEMBER 30, 2001
1-12-15
Code
3 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
The following table gives the surface conditions and wind velocities at which mooring is necessary; Wind Limitation Table Surface Condition Ice Snow Wet Concrete Dry Concrete
Wind Velocity 30 Kt 50 Kt 55 Kt 60 Kt
To moor the aircraft, proceed as follows: − Tow the aircraft to a parking area where there are tiedown anchors available. − Carry out the normal parking procedure. − Install the tiedown rings (two), one in each primary brace strut of the main landing gear. − Attach a nylon rope to the tiedown ring with a bowline knot, and then attach the other end of the rope to the tiedown anchor on the ground by knotting it with a bowline knot. See the corresponding illustration on the previous page.
Page
1-12-15
Code
4 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
COLD WEATHER OPERATION COLD SOAK PREPARATION The procedures below should be applied in the event of extended airplane exposure at low temperatures. In the event that the airplane is off the maintenance base, the crew should ensure that all actions have been accomplished: − Put the wheel chocks against the landing gear wheels. − For an icy ramp, leave Emergency/Parking Brakes applied. Otherwise, Emergency/Parking Brakes must not be applied to avoid freezing of the brakes. − Set pitch trim to at least 4 degrees nose UP after landing in icing conditions to prevent melting snow accumulating and freezing between control surfaces. − Install protective covers on engines and APU inlets/outlets, pitot, TAT probes, and wheels. − Drain water and waste from all water tanks, if cold soak temperature o o is expected to be below 0 C (32 F). − Remove the batteries if temperatures are expected to be below o o -20 C (-4 F). This protects the batteries and ensures starting capability of the APU upon installation. − All doors and windows must be closed to avoid snow and humidity from entering into the airplane.
Page
ORIGINAL
1-12-20
Code
1 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
APPLICATION OF DEICING AND ANTI-ICING FLUIDS ANTI-ICING AND DEICING FLUIDS When airplane surfaces are contaminated by frozen precipitation or frost before departure, they must be deiced. When the risk of freezing precipitation exists at dispatch or freezing precipitation is actually taking place, the airplane must be anti-iced. While deicing removes ice, anti-icing protects against additional icing for a certain period of time, called hold-over time. A combination of both anti-icing and deicing may be performed based on the judgement of the flight crew and procedures developed by the operator. Deicing and anti-icing fluids lower the freezing point of frozen precipitation thus delaying the accumulation of contamination on the airplane. When applied to a clean surface, the fluid forms a thin layer that has a lower freezing point in precipitation. The fluid is highly soluble in water, thus the precipitation or ice melts on contact with fluid. These fluids also delay the onset of frost on airplane surfaces. As the ice melts, the fluid dilutes with the water, thereby causing the mixture to become less effective or to run off. Ice can begin to form again after enough dilution has occurred and freezing point begins to rise. Deicing/anti-icing fluids are not intended to provide icing protection during flight. The fluid must flow-off the surface during takeoff, or they may cause undesirable performance effects. EMBRAER performed flight tests to investigate the effects of approved fluids on performance and handling characteristics. These tests demonstrated these fluids did not have a measurable effect on takeoff and climb performance. Fluids are generally mixtures of glycol, water, inhibitors, thickening agents and wetting agents. Glycol lowers the freezing point and prevents the formation of ice contamination at temperatures below freezing. The wetting agent allows the fluid to conform to the airplane surfaces. The inhibitors prevent corrosion and increase the flash point. The thickening agent, normally propylene glycol with polymers, enables the coating of fluid to remain on airplane surfaces for longer periods. Type I Fluid is unthickened, while fluids from Type II to IV are thickened. Type I Fluid characteristically forms a thin wetting film which provides relatively limited holdover time, and provides protection against refreezing when no precipitation is present.
Page
1-12-20
Code
2 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
A deicing fluid may be pure heated water, or a mixture of heated water and type I, II and IV fluids. Heating is applied to a minimum o temperature of 60 C to assure maximum deicing efficiency. Anti-icing fluids include undiluted type III fluid or types I, II and IV fluids in a mixture with water or undiluted. Type I fluid is diluted with water to result in a freezing point o approximately 10 C below ambient temperature. No additional holdover time is obtained by increasing the concentration of this fluid in the fluid/water mixture. However, increasing the concentration of fluids II and IV in a fluid/water mixture results in an additional holdover time. Fluid type III should be applied undiluted only. The holdover time of the type IV fluid is greater than that of type II, which in its turn has a longer holdover time than type III fluid. Type I fluid is normally pink or reddish orange in color, type II fluid is normally straw-colored, type III is bright yellow and type IV is green. Type IV is an enhanced-performance fluid and offers significant operational advantages in terms of holdover times. However, thickened fluids may dry out during flight and residues may collect in aerodynamically quiet areas. The residues may turn to a gel which can freeze in flight, potentially restricting the movement of flight controls. Operators are reminded to frequently inspect control surfaces, gaps and tab hinges for signs of residual gel. If an approved fluid during actual use shows gelling, poor water wash off or unusual dry-out, EMBRAER should be notified. THE USE OF HOLDOVER TIMES Holdover times for the fluids are derived for each specific fluid brand, under various temperatures, fluid concentration and precipitation category. Note that the lower limit of the published holdover time is used to indicate the estimated time of protection during moderate precipitation, and the upper limit indicates the estimated time during light precipitation. Heavy conditions are not covered. Therefore, crew experience and airline orientation is required to clearly settle what is heavy, moderate or light. It is very important to determine the appropriate holdover time for the prevailing environmental conditions, and apply them on the line.
Page
REVISION 7
1-12-20
Code
3 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
Holdover times should be seen as rough approximations. They simply reflect the average, estimated time an anti-icing fluid should prevent the formation of frozen contaminants on the protected surfaces. Actual holdover times can be reduced or extended due to many factors influencing fluid effectiveness, such as high wind velocity, jet blast, heavy precipitation rates or high moisture content. Recommended practice is to use holdover times in conjunction with a pre-takeoff contamination check to ascertain that frozen deposits have not started to accumulate on treated surfaces. In the airplane, only a small portion of the wing is visible from the cockpit. Conducting a pre-takeoff contamination check requires a crew member to visually inspect the wing surfaces/leading edge and the engine by looking through an appropriate cabin window. The pilot-incommand must ask for the assistance of trained and qualified ground personnel to assist in the pre-takeoff check, so that empennage and fuselage, which are not visible from the cockpit or cabin, can also be inspected. If contamination is suspected, the airplane should be returned for additional deicing or anti-icing. For practical results, the holdover time must be equal to or greater than the estimated time from start of anti-icing to start of takeoff based on existing weather conditions. Ensure that deicing and anti-icing are performed at the latest possible time before taxiing to the takeoff position. Always takeoff before holdover time expires, so as to minimize the period when the airplane stays in line for takeoff and is exposed to contamination. Hold-over time should not be considered an exact figure. It is just an average time, which can be reduced by many factors affecting the fluid effectiveness. In the case of ice build-up after deicing/anti-icing fluid application, do not assume that ice will be blown off during takeoff roll. Ask for deicing/anti-icing fluid reapplication. If the hold-over time expires, carry out a pre-takeoff contamination check and another deicing/anti-icing fluid application is required. No holdover time guidelines exist for the conditions of snow pellets, snow grains, ice pellets, moderate and heavy freezing rain and rail. In such, takeoffs in snow pellets, snow grains, ice pellets or hail must be preceded by a careful contamination check shortly before takeoff. Takeoff in conditions of moderate and heavy freezing rain are not approved.
Page
1-12-20
Code
4 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
DEICING AND ANTI-ICING PROCEDURES Application of deicing and anti-icing fluid must be done by trained and qualified personnel. It is the pilot’s responsibility to decide whether or not to accept the airplane for flight. Therefore, it is essential that pilots understand not only how the fluid works and how it is applied, but also the flight crew must be able to determine if the airplane is safe for flight following treatment. Deicing is required to clean airplane surfaces contaminated by ice, snow, frost or slush. Anti-icing is required to prevent ice accumulation. If both anti-icing and deicing are required, the procedure may be performed in either one or two-step process depending on weather conditions, available equipment, available fluids and the holdover time. However, a two-step deicing/anti-icing fluid application is recommended to be performed so that the residues accumulation in the critical areas is minimized. In two separate steps, the airplane is first deiced using heated water only, or a heated mixture of deicing fluid and water. After completion of the deicing operation, anti-icing is performed with diluted or undiluted anti-icing fluid. The second step must be applied before residual liquids from the first deicing step freezes, typically within three minutes. This is especially important where only heated water is used to deicing. Mixing fluids in a two-step procedure may only be performed if approved by the fluid manufacturer. It is important to keep in mind that in case of a one-step deicing/antiicing procedure, holdover time starts to run from the beginning of the procedure. With a two-step procedure, the holdover time starts to run at the beginning of the second step. Under no circumstances should an airplane that has been previously anti-iced receive a further spray of anti-icing fluid directly on top of the anti-icing contaminated film. If an additional protection is necessary before flight, a complete deicing/anti-icing procedure must be performed. Residues from previous treatment must be flushed off first. All fluids must be used in accordance with the manufacturers recommendations.
Page
REVISION 7
1-12-20
Code
5 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
GROUND DEICING STRATEGY The flight crew must understand the overall deicing and anti-icing strategies and insure that the procedures are performed properly to assure themselves that they have a safe airplane for flight. All soft snow can be mechanically removed by using brooms, soft hand scrappers or rubber scrappers. Do not use tools to scrape or scratch compacted snow from the airframe surfaces or from the gaps between fixed or movable surfaces. Flaps should be up and ailerons in the neutral position, parking brake and gust lock set. Setting pitch trim to at least 4 degrees nose up will help in removing contaminants. All doors should be closed. For effective deicing, the following guidelines are recommended: Wings – Stabilizer: Spray from the tip inboard to the root, sweeping from the leading edge in the aft direction. No frozen contamination is allowed on the wing upper surface or the horizontal stabilizer lower surface. Vertical surfaces: start at the top and then work down. The rudder should be in the neutral position. Fuselage – Remove all snow accumulating on the nose to avoid snow blowing back during takeoff and restricting pilot´s visibility. Fluid should be sprayed along the top centerline of the fuselage and then outboard, letting the fluid cascade down and across the windows. Fluid must not be sprayed directly onto windows and window seals, doors and doors seals, air conditioning scoops or NACA air inlets. A thin layer of hoar frost on the fuselage is permitted, but only to the point you can still see the airplane markings. Landing gear and wheel bays – application of fluid in this area must be kept to a minimum. Do not allow water or fluid mixture spray on wheels and brakes to avoid damage to carbon brakes. For this part of the airplane, it is preferable to clear snow or slush using a brush. Engines – deposits of snow should be mechanically removed from engine intakes using either brooms, soft hand scrapers or rubber scrappers. Frozen deposits adhering to either the lower surface of the intake or to the fan blades should be removed by the applying hot air or by the use of a gentle fan spray of heated deicing fluid. To ensure the safety of ground personnel and passengers, this should be carefully coordinated with the flight crew.
Page
1-12-20
Code
6 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
It is also important to examine and remove all ice attached to the surface close to the pitot and static sensors, static ports, TAT probes, AOA sensors, and ice detectors. However, deicing or anti-icing fluid should not be applied directly to these devices. The fluids should be sprayed along the top of the sensors, allowing the fluid to cascade down across the sensor and deice it. GROUND ANTI-ICING STRATEGY Once the airplane has been fully deiced, then it is time to consider the prevention of any further ice contamination prior to takeoff by application of an anti-icing treatment. To prevent frozen contamination on airplane surfaces, the anti-icing operation requires that fluids be distributed uniformly over surfaces. In order to control uniformity, all horizontal surfaces must be visually checked during fluid application. The correct amount is indicated by fluid just beginning to drip off the leading edge. The following surfaces must be protected: wing upper surface and leading edge, horizontal stabilizer upper surface and leading edge, elevator upper surface, vertical stabilizer and rudder, fuselage upper surface. On the wings, the best results are obtained by starting the spraying at the highest part of the wing section and proceeding towards the leading and trailing edges. On vertical surfaces, start at the top and work down. A check for fluid coverage and residual ice is required immediately following application of the deicing/anti-icing fluids and should be accomplished by a qualified person. It is possible that fluid may not flow evenly over the protected surfaces. It is essential that the wings, horizontal and vertical stabilizer are properly coated with fluid. It is also important that the fluid be applied symmetrically to both wings so as to ensure that the aerodynamic effect of the fluid remaining is the same on both sides of the airplane.
Page
REVISION 7
1-12-20
Code
7 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
APPROVED DEICING/ANTI-ICING FLUIDS Only Deicing/Anti-icing fluids certified under specifications below are approved to be used in the EMB-135BJ airplane models: Deicing/Anti-icing Fluid
Specification
Type I
SAE AMS 1424
Types II, III and IV
SAE AMS 1428
Refer to the fluid manufacturer's recommendations for fluid mixture, if applicable, and holdover times. NOTE: For approved fluid manufacturers, refer to AMM 20-30-06/2.
Page
1-12-20
Code
8 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
FUEL SYSTEM SERVICING PRESSURE REFUELING Pressure refueling is performed by accessing an adapter and a panel located on the right wing-to-fuselage fairing. The adapter is assembled with a valve operated by the opening movement of the fueling nozzle shut-off valve, which is manually controlled. It is possible to refuel the wing tanks only or the wing plus auxiliary (fuselage) tanks. Refer to the Section 2-8 - Fuel System for detailed description of the system. − Statically ground the aircraft. − Energize the aircraft or set the Power Selection switch to BATTERY. NOTE: In cold weather it is necessary to drain the fuel tanks prior to refueling. Drain the fuel tanks again prior to departure, if the aircraft has been parked for more than 2 hours. − Open refueling access door on the right side of the fuselage. − Make sure that the WING tank refueling lights are extinguished. − Make sure that the FUS 1 and FUS 2 refueling lights are illuminated. − Make sure that the DEFUELING light is extinguished. − Make sure that the FUS ISOLATION lights are illuminated. − Make sure that the SELECTED-fuel-quantity indicator shows zero. WING ONLY REFUELING − Set the tanks selection toggle switch in WING ONLY position. − Set the quantity selection toggle switch to WING position. − Test the quantity indicator. − Make sure that WING quantity selection light is illuminated. − Set the desired wing tank fuel quantity. − Remove the protection cover from the pressure refueling adapter. − Connect the fuel nozzle to the pressure refueling adapter. − Pressurize the system (35 - 50 psig). − Make sure that WING, FUS 1 and FUS 2 tank refueling lights are illuminated and the refueling flow is stopped. − Set the REFUELING switch to the OPEN position and make sure that the WING refueling lights are extinguished. − Make sure that the WING refueling lights illuminate, when the desired fuel level is reached. NOTE: For airplanes equipped with High Level Exceeding Indication, if the “STOP RFL” red light illuminates, stop immediately the refueling operation relieving the pressure of the fueling source and refer to the HLEI dispatch procedure. Page
REVISION 6
1-12-25
Code
1 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
− Set the REFUELING switch to the CLOSED position. − Make sure that the selected quantity was fueled. After the refueling has been completed: − Remove the fuel nozzle from the pressure refueling adapter. − Install the protection cover to the pressure refueling adapter. − Deenergize the aircraft if necessary. WING + FUS TANKS REFUELING − Set the selection toggle switch in WING + FUS position. − Make sure that FUS 1 and FUS 2 tanks refueling lights are extinguished. − Make sure that FUS ISOLATION lights are extinguished. − Test the quantity indicator to each tank (FUS 1, FUS 2 and WING). − Make sure that respective quantity selection light is illuminated. − Set the desired FUS 1 or/and FUS 2 and WING fuel quantity, in this order. NOTE: - Set the wing tank fuel quantity above 4800 kg (10580 lb). The fuel quantity selection switch must be kept in WING position before starting the refueling operation and until the end of wing refueling. - It is recommended to refuel FUS 1 and FUS 2 systems with the same fuel quantity. However, an asymmetric refueling of the Auxiliary Tanks may be performed as far as it is assured that the airplane’s CG is kept within the CG envelope presented in the Limitations Section during all flight phases. - The maximum allowed fuel load in each auxiliary system is: Airplanes S/N up to 591 and Pre-Mod. SB 145LEG-28-0010: 1460 kg (3219 lb), with 800 kg (1764 lb) in the forward tank and 660 kg (1455 lb) in the aft tank. Airplanes S/N 625 and on or Post-Mod. SB 145LEG-28-0010: 1570 kg (3461 lb), with 900 kg (1984 lb) in the forward tank and 670 kg (1477 lb) in the aft tank. After completing the previous steps: − Remove the protection cover from the pressure refueling adapter. − Connect the fuel nozzle to the pressure refueling adapter. − Pressurize the system (35 - 50 psig). NOTE: Verify the refueling pressure. The correct refueling pressure assures the proper system functioning. − Make sure that WING, FUS 1 and FUS 2 tank refueling lights are illuminated and the refueling flow has stopped.
Page
1-12-25
Code
2 01
REVISION 6
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
− Set the REFUELING switch to the OPEN position and make sure that the WING refueling lights are extinguished and the FUS 1 and FUS 2 refueling lights remain illuminated, indicating that wing refueling has started. − Make sure that the WING refueling lights are illuminated and the FUS 1 and FUS 2 refueling lights are extinguished, when wing refueling is completed and the refueling of the auxiliary tanks starts. − Make sure that the FUS 1 and FUS 2 refueling lights illuminate, when the desired fuel level is reached. NOTE: For airplanes equipped with High Level Exceeding Indication, if the “STOP RFL” red light illuminates, stop immediately the refueling operation relieving the pressure of the fueling source and refer to the HLEI dispatch procedure. − Set the REFUELING switch to the CLOSED position. − Set the tanks selection toggle switch to WING ONLY position. NOTE: Make sure about the correct refueling pressure After the refueling has been completed: − Remove the fuel nozzle from the pressure refueling adapter. − Install the protection cover to the pressure refueling adapter. − Deenergize the aircraft if necessary. − Check the Wing and FUS Tanks fuel quantities and imbalance (refer to section 1-01-36 Fuel System Limitations for approved values). If refueling cannot be accomplished (system stops refueling): − Use the WINGS TO AUXILIARY TANKS - FUEL TRANSFER OPERATION Procedure in order to refuel the auxiliary tanks, transferring fuel from wings to fuselage tanks. Check the Wing and FUS Tanks fuel quantities and imbalance (refer to section 1-01-36 Fuel System Limitations for approved values). − Set the Tanks Selection toggle switch to WING ONLY position and restart the wing refueling procedure to their maximum capacity. NOTE: If the Power Selection switch has been used at the BATTERY position, set it back to the NORMAL position and close the switch guard. − Remove the grounding cable from the aircraft. WARNING: MAKE SURE THAT ALL THE SWITCH GUARDS ON THE REFUELING PANEL ARE IN THE CLOSED POSITION. − Close access door.
Page
REVISON 6
1-12-25
Code
3 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
REFUELING/DEFUELING CONTROL PANEL
Page
1-12-25
Code
4 01
REVISION 4
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
GRAVITY REFUELING Gravity refueling the wing tanks is performed through the filler caps installed on the upper wing surface. Prior to refueling, the fueling nozzle must be grounded through the grounding point at each under wing surface. The operation consists in opening the filler cap and inserting the fueling nozzle into the filler port. Fuel quantity may be checked through the EICAS indication or through the magnetic measuring sticks should there occur a failure of the normal indication system. During the gravity refueling, the auxiliary tanks refueling is performed transferring fuel from wing tanks. Do this procedure as follow: WING TO AUXILIARY TANKS - FUEL TRANSFER OPERATION − Energize the aircraft. − Open refueling access door on the right side of the fuselage. − Set WING + FUS on TANKS SELECTION switch and make sure that FUS ISOL VALVES lights are extinguished. − Set the DEFUELING switch to the OPEN position and make sure that the defueling OPEN light illuminates. − Set MFD 1 or 2 to the FUEL page and use the MFD to monitor the fuel quantities. NOTE: - It is recommended to refuel FUS 1 and FUS 2 systems with the same fuel quantity. - For airplanes S/N up to 591 and Pre-Mod. SB 145LEG-280010, not equipped with increased fuel capacity system: - The maximum allowed fuel load in each auxiliary system is 1460 kg (3219 lb), with 800 kg (1764 lb) in the forward tank and 660 kg (1455 lb) in the aft tank. - The load difference between forward and aft tanks of each system must be within the limits of the chart presented on section 1-01-36 Fuel System limitations.
Page
REVISION 4
1-12-25
Code
5 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
- For airplanes S/N 625 or Post-Mod. SB 145LEG-28-0010, equipped with increased fuel capacity system: - The maximum allowed fuel load in each auxiliary system is 1570 kg (3461 lb), with 900 kg (1984 lb) in the forward tank and 670 kg (1477 lb) in the aft tank. - The load difference between forward and aft tanks of each system must be within the limits of the chart presented on section 1-01-36 Fuel System limitations. CAUTION: DAMAGE TO THE FUEL PUMP WILL OCCUR IF IT OPERATES WITH NO FUEL (DRY OPERATION). THUS, TURN THE PUMP OFF BEFORE THE TANK IS EMPTY. Transfer fuel from the RH wing tank to auxiliary tanks as follow: − Make sure that XFEED switch is OFF. − Set the PUMP SEL switch to the fuel pump to be used. NOTE: When transferring from TANK 1, make sure that the XFEED Switch is positioned to LOW 2. − Set the applicable PUMP PWR WING TANK 2 switch to ON position, on the fuel control panel, and wait approximately 15 seconds. − Remove the access panel located at galley, to get access to the maintenance fuel transfer panel. − On maintenance fuel transfer panel, set the switch to the tanks that will receive fuel. Monitor the transference through the quantities of the tanks and, when the necessary fuel quantity has been transferred, move the PUMP PWR TANK 1 or 2 switch back to OFF. NOTE: For airplanes equipped with High Level Exceeding Indication, if the “STOP RFL” red light illuminates stop immediately the transfer and refer to the HLEI dispatch procedure.
Page
1-12-25
Code
6 01
REVISION 4
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
After transferring has been completed: − On maintenance fuel transfer panel, set the switch to the NORM position. Repeat this procedure to transfer fuel from wing to the desired auxiliary tank. When the transfers are completed: − Set the DEFUELING switch to the CLOSED position and make sure its light is extinguished. − Set WING ONLY on TANKS SELECTION switch and make sure that FUS ISOL VALVES lights illuminate. − Close the access door. − Deenergize the airplane.
Page
REVISION 3
1-12-25
Code
7 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
MAINTENANCE FUEL TRANSFER PANEL (AIRPLANES S/N UP TO 591) Page
1-12-25
Code
8 01
REVISION 4
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
MAINTENANCE FUEL TRANSFER PANEL (AIRPLANES S/N 625 AND ON) Page
REVISION 4
1-12-25
Code
8A 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-12-25
Code
8B 01
REVISION 4
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
FUEL SYSTEM CONTROL AND INDICATORS
Page
REVISION 3
1-12-25
Code
9 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
FUEL QUALITY CONTROL Before accepting delivery from the fuel supplier, a check should be made with the purpose of ensuring that fuel intended for use in the aircraft is fit use. Fuel should be considered unsatisfactory for use if a sample shows: − trace of sediments; − globules of water; − cloudiness; and − positive reaction to water detector test. A visual inspection to a sample should be accomplished to ensure that it does not contain excessive sediment. Generally, aviation turbine fuel is clean, and its color is appropriate to its grade (normally undyed and clear). Apart from cases where water is evidently present in the form of globules, only an appropriate check can be conclusive to indicate the presence of water in a fuel sample. Both free and suspended water may be present in aviation jet fuel. The water finding paste or paper test method is used to show the presence of free water. The chemical water detector test method is designed to detect suspended water and should therefore be used in addition to the paste/paper method when checking fuels. NOTE: In cold weather it is necessary to drain the fuel tanks prior to refueling. Drain the fuel tanks again prior to departure, if the aircraft has been parked for more than 2 hours.
Page
1-12-25
Code
10 01
REVISION 6
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
PRESSURE DEFUELING Pressure defueling the auxiliary tanks shall be performed by transferring fuel to the wings first, and then performing wing pressure defueling. − Statically ground the aircraft. − Energize the aircraft or set the Power Selection switch to BATTERY. − Open refueling access door on the right side of the fuselage. − Make sure that the defueling OPEN light is extinguished. − Connect the fuel nozzle to the pressure refueling adapter. − Set the DEFUELING switch to the OPEN position and make sure that the defueling OPEN light illuminates. − Apply suction (4 psig MAX) to the nozzle or set the Electric Fuel Pumps switches to the ON position. NOTE: To defuel the LH tank, set the cross-feed switch to the LOW 2 position. − When desired remaining fuel quantity is reached, set the DEFUELING switch to the CLOSED position and make sure its light is extinguished. CAUTION: TO PREVENT DAMAGE DO NOT PERMIT THE DRY OPERATION OF THE FUEL PUMPS DURING DEFUELING. − Set the Electric Fuel Pumps and X-FEED switches to the OFF position. − Disconnect the fuel nozzle from the pressure-refueling adapter. − Install the protection cover to the pressure-refueling adapter. − Deenergize the aircraft if necessary. NOTE: If Power Selection switch has been used at the BATTERY position, set it back to the NORMAL position and close the switch guard. − Remove the grounding cable from the aircraft. WARNING: MAKE SURE ALL THE SWITCH GUARDS ARE AT THE CLOSED POSITION ON THE REFUELING PANEL. − Close access door. Page
JUNE 20, 2002
1-12-25
Code
11 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
GRAVITY DEFUELING Gravity defueling is accomplished through the defueling port installed on the wing stub. The auxiliary tanks gravity defueling shall be performed by first transferring fuel to the wing tank and then performing the wing gravity defueling operation. Gravity defueling is accomplished by installing the defueling valve to the defueling port and putting the other hose end into the defueling cart. The aircraft must be previously grounded. Opening the shutoff valve will cause the defueling operation to initiate. When the desired remaining quantity is reached, closing the valve will stop defueling. After the defueling operation is completed, the defueling valve must be removed from the defueling port, and the defueling cap must be closed.
Page
1-12-25
Code
12 01
JUNE 20, 2002
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
GRAVITY DEFUELING EQUIPMENT Page
REVISION 1
1-12-25
Code
13 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
AUXILIARY TANKS TO WING - FUEL TRANSFER OPERATION The procedure can be performed on the ground for gravity defueling purpose. − Energize the aircraft. CAUTION: TO PREVENT DAMAGE DO NOT PERMIT THE DRY OPERATION OF THE FUEL PUMPS DURING DEFUELING. NOTE: To start the fuel transfer, fuel quantity in each wing must be less then 1900 kg (4190 lb). − Set MFD 1 or 2 to the FUEL page, to monitor the fuel quantity that is transferred. − Set the FWD PUMP SEL push-button (pump A or B) on the Fuel Control Panel. − Set the FUSTKXFER switch (FUS 1 or FUS 2) on the Fuel Control Panel. − Make sure that the “T” indication appears on the MFD panel. NOTE: Fuel transfer will occur while the fuel quantity is below 2400 kg (5290 lb) in each wing. − When desired fuel quantity on the auxiliary tanks is reached, set the FUSTKXFER switch to OFF. NOTE: For airplanes equipped with High Level Exceeding Indication, if the “STOP RFL” red light illuminates stop immediately the transfer and refer to the HLEI dispatch procedure. − Deenergize the aircraft.
Page
1-12-25
Code
14 01
REVISION 4
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
FUEL TANK DRAINING Fuel tanks must be drained periodically every 7 calendar days to remove free water and contaminants from the tank bottom. To open the drain valve, insert the draining device in the valve and execute a one-quarter counterclockwise turn. After draining all the points, close the access panels safely.
Page
REVISION 1
1-12-25
Code
15 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
FUEL DRAINING POINTS Page
1-12-25
Code
16 01
REVISION 4
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
REFUELING WITH AN ENGINE RUNNING Refueling the aircraft with an engine running is not recommended. Apart from the risk of fire, there is the risk posed for maintenance and other personnel required to move around the airplane. There may be circumstances in which an Airport Authority agrees with a detailed procedure that offers an acceptable level of safety to all parties involved. This would, however, be a matter between the Airport Authority and the individual operator. Therefore, contact the Airport Authority prior to performing this operation and/or obtain the necessary approval from the operations inspector. To refuel the aircraft with an engine running, proceed as follows: − Disembark passengers (refer to the “Deplaning or Boarding with One Engine Running” procedure ahead). − The aircraft must be parked in an area designated by the Airport Authority, with free access to fire fighting equipment and personnel. − Keep the main door open and the stairs deployed. − Shut down the right engine. − Set the left engine to idle power. − At least one pilot must remain in the cockpit during the refueling. This pilot is responsible for informing all flight and ground crews that the airplane is being refueled and the engine is running. − During the refueling procedure, do not turn on switches, except those required to operate the fuel system. Set all airplane systems before initiating refueling, in order to avoid moving controls during refueling. Sparks of any kind must be avoided. The use of mobile phones must not be allowed. − Smoking is prohibited during the refueling, both inside and outside the cabin. − Only pressure refueling is recommended and, to avoid the possibility of fuel spillage, fueling should be limited to 90% of the tank capacity. − In the case of fuel spillage, shut down the operating engine.
Page
JUNE 20, 2002
1-12-25
Code
17 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
DEPLANING OR BOARDING WITH ONE ENGINE RUNNING The following precautions are recommended: − At least one pilot must remain in the cockpit. − Turn the left engine off. − Set the right engine to idle power. − Provide safety precautions for passengers on the ground. Isolate the right side of the airplane so that no passenger can gain access to this area.
REFUELING WITH PASSENGERS ON BOARD OR EMBARKING/DISEMBARKING The following precautions are recommended: − At least one pilot must remain in the cockpit during the refueling procedure. This pilot is responsible for informing all the flight and ground crews that the airplane is being refueled with passengers on board or embarking/disembarking; − Engines must be off; − Crew, staff, and passengers must be warned that refueling will take place; − “Fasten Seat Belts” signs must be off; − “No Smoking” signs must be on together with interior lights to enable the emergency exits to be noticed; − Passengers must be instructed to unfasten their seat belts and refrain from smoking; − Sufficient qualified personnel must be on board and be prepared for immediate emergency evacuation; − If the presence of fuel vapors is detected inside the airplane, or any other hazard arises during refueling, fueling must be interrupted immediately; − Aisles and emergency doors must be kept unobstructed, as well as the ground area beneath the exits.
Page
1-12-25
Code
18 01
JUNE 20, 2002
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
HIGH LEVEL EXCEEDING INDICATION (HLEI) For airplanes equipped with High Level Exceeding Indication, if a refueling automatic shutoff failure occurs and the fuel level in the failed tank reaches over the maximum quantity for that tank, the “STOP RFL” red light will illuminate. Stop immediately the refueling operation releaving the pressure of the fueling truck. For dispatch the aircraft the following procedures should be done. WING ONLY REFUELING − Check the wing tanks for the highest fuel quantity indication. − Equalize the wing tanks fuel quantity removing fuel from the wing tank with the highest volume. NOTE: The removal of the exceeding fuel shall be done by transferring it from the wing to the fuselage tanks, pressure defueling or gravity defueling procedures. − Check if the HLEI light is extinguished. − In case of the HLEI light remain illuminated remove fuel from both wing tanks until the quantity be equal to the indicated on the “Fuel Temperature versus Wing Tanks Fuel Quantity” table. NOTE: - If required for dispatch, replenish the wing tanks through the gravity refueling procedure. - The pressure refueling system shall be considered inoperative. − Check the fuel quantity and balancing, for all tanks.
Page
REVISION 4
1-12-25
Code
19 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
FUEL TEMPERATURE VERSUS WING TANKS FUEL QUANTITY TABLE
FUEL TEMPERATURE (°C) -40 -35 -30 -25 -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 52
WING TANK FUEL INDICATION kg 2530 2520 2510 2490 2480 2470 2460 2450 2440 2430 2420 2400 2390 2380 2370 2360 2350 2340 2330 2320
lb 5570 5550 5520 5500 5480 5450 5430 5400 5380 5350 5330 5300 5280 5250 5230 5200 5180 5150 5130 5120
NOTE: The fuel temperature data shall be taken from the Fuel Page on the MFD.
Page
1-12-25
Code
20 01
REVISION 4
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL WING + FUS TANKS REFUELING
− Check if all the auxiliary tanks fuel quantities are within the values presented on the above table: − If yes, set the Refueling Mode switch to WING ONLY and follow the procedure for HLEI Wings Only Refueling. − If no, procedure according to the next steps. FUEL TEMPERATURE QUANTITY TABLE
VERSUS
AUXILIARY
TANKS
FUEL
AUXILIARY TANKS FUEL QUANTITY INDICATON FUEL TEMPERATURE (°C) -40 -35 -30 -25 -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 52
FORWARD kg 800 800 790 790 790 780 780 780 770 770 770 770 760 760 760 750 750 750 740 740
lb 1760 1760 1740 1740 1740 1720 1720 1720 1700 1700 1700 1700 1670 1670 1670 1650 1650 1650 1630 1630
AFT kg 660 660 650 650 650 640 640 640 630 630 630 630 620 620 620 610 610 610 600 600
lb 1450 1450 1430 1430 1430 1410 1410 1410 1390 1390 1390 1390 1370 1370 1370 1340 1340 1340 1320 1320
NOTE: The fuel temperature data shall be taken from the Fuel Page on the MFD. Page
REVISION 4
1-12-25
Code
21 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
− Check the highest difference of fuel quantity between the pair of auxiliary tanks (FWD1 with FWD2 and AFT1 with AFT2). − Revove fuel from the tank with the highest volume until the equalization of the pair. NOTE: The removal of the exceeding fuel from auxiliary tanks shall be done by gravity defueling or draining procedures. − Check the HLEI light is extinguished, if not, repeat the two steps above for the other pair of auxiliary tanks. − Check the HLEI light is extinguished, if not, remove fuel from all the auxiliary tanks until the volume is equal or less to the values presented on the "Fuel Temperature versus Auxiliary Fuel Tanks Quantity” table. − Check the HLEI light is extinguished, if not, set the Refueling Mode switch to WING ONLY and follow the procedure for HLEI Wings Only Refueling. NOTE: - If required for dispatch, replenish the tanks through the gravity refueling procedure. - The pressure refueling system shall be considered inoperative. − Check the fuel quantity and balancing, for all tanks.
Page
1-12-25
Code
22 01
REVISION 4
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
FUEL SYSTEM ICING INHIBITORS As Fuel System Icing Inhibitors (FSII), use: - Ethylene Glycol Monomethyl Ether (EGME), which obeys MIL-I-27686 (NATO S-748), ASTM-D-4171 or GOST 8313; or - Di-Ethylene Glycol Monomethyl Ether (Di-EGME), which obeys MIL-I-85470A.
BIOCIDE FUEL ADDITIVES As Biocide Fuel additive, use Biobor (MIL-S-53021A) or Kathon FP 1.5 Biocide product AR.
CORROSION/LUBRICITY ADDITIVES As Corrosion/Lubricity additive, use the Qualified Product List of MIL-I-25017. NOTE: Obey the fluid manufacturer’s specifications to find the additive proportions for each fuel .
Page
REVISION 6
1-12-25
Code
23 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-12-25
Code
24 01
REVISION 4
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
ENGINE OIL SERVICING The engine oil tank features an oil level sight gage and an oil level/low level warning sensor. To check oil level in the engine, open its access door and observe the sight glass. It must never exceed the FULL mark. Oil consumption up to and including 6.8 ounces per hour (0.21 quarts per hour or 200 cc per hour) is considered normal. Rates of consumption in excess of this value is considered high. High oil consumption indicates something is not functioning properly or possibly a leak which should be addressed by maintenance personnel when convenient. In the absence of other problems associated with the high oil consumption rate there is no mandatory action. Engine oil consumption rates can increase as engine hours/cycles increase. To fill the tank with oil, remove the filler cap and carefully pour oil through the filler neck observing that the FULL mark on the sight glass is not exceeded. There is an O-ring on the filler cap that must be checked for dents, cracks or breakage. If this O-ring is damaged, it must be replaced. After filling the tank, put the filler cap back in place and make sure that it is properly installed and tightened. NOTE: The Minimum Dispatch Oil Quantity is 8 quarts before engine start or 6 quarts after engine start.
APPROVED ENGINE OIL TYPES SPECIFICATION
MIL-L 23699D
MIL-L-7808K
COMMERCIAL PRODUCT
SUPPLIER
Aeroshell 1/Royco Turbine Oil 500 Exxon Turbo Oil 2380 Mobil Jet II Mobil Jet Oil 254 Mobil RM 284A
Shell/Royal Lubricants Exxon Mobil Oil Corpor. Mobil Oil Corpor.
Page
NOVEMBER 30, 2001
1-12-30
Code
1 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
CAUTION: • IF MIXED WITH OTHER OILS, MOBIL JET OIL 254 CAN CAUSE WASHING OR SHEDDING OR CARBON DEPOSITS LEFT BY THOSE OILS. THIS CLEANING PROCESS CAN LEAD TO OIL SYSTEM PROBLEMS, SUCH AS BLOCKED PASSAGEWAYS AND SCREENS. CHANGING FROM EXXON 2380, MIL JET II OR AEROSHELL/ROYCO 500, TO MOBIL JET 254 SHOULD ONLY BE DONE WHEN THE ENGINE IS NEW OR OVERHAULED • USE OF NON-APPROVED OIL COULD RESULT IN DAMAGE AND PREMATURE ENGINE FAILURE. • IF OIL BRANDS ARE CHANGED, IT SHOULD BE ACCOMPLISHED GRADUALLY USING THE “TOP OFF” METHOD. • DO NOT MIX MIL-L-23669D AND MIL-L-7808K. • USE OF MIL-L-7808 TYPE OIL SHOULD BE LIMITED TO ONLY THOSE TIMES WHEN OPERATING IN EXTREME COLD WITHOUT PREHEAT CAPABILITY ° ° (-40 F TO -65 F) OR WHEN MIL-L-7808K IS THE ONLY TYPE OF OIL AVAILABLE.
Page
1-12-30
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
ENGINE OIL FILLING AND OIL LEVEL CHECK Page
NOVEMBER 30, 2001
1-12-30
Code
3 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-12-30
Code
4 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
APU OIL SERVICING APU oil tank servicing is done through the access at the aircraft tail cone which, when open, provides access to a sight glass and an oil filler cap. The sight glass has a FULL indication which must never be exceeded.
APPROVED APU OIL TYPES SPECIFICATION
MIL-L 7808
MIL-L-23699
COMMERCIAL PRODUCT Brayco 880 B.P. Aero Turbine Oil 15 Castrol 3C Castrol Castrol 325 Aeroshell Turbine Oil 390 Castrol 5000 Exxon or Esso Turbo Oil 2380
SUPPLIER -
Castrol Shell Castrol Exxon/Esso
-
Hatcol 3611 Mobil Jet Oil II Mobil Jet Oil 254 Royco 899 Royco or Aeroshell Turbine Oil 555
Mobil Oil Corpor. Mobil Oil Corpor. Royal Lubricants Royal Lubricants/Shell
Royco or Aeroshell Turbine Oil 500
Royal Lubricants/Shell
CAUTION: • DO NOT FILL THE APU OIL TANK WITH AN OIL OF A DIFFERENT BRAND FROM THAT WHICH IS IN THE TANK, EVEN IF THE SPECIFICATION IS THE SAME (REFER TO THE PLACARD ATTACHED TO THE ACCESS DOOR). • DO NOT ALLOW THE OIL LEVEL TO EXCEED THE "FULL" MARK ON THE SIGHT PLUG. AN OVERFILLED TANK WILL RESULT IN OIL FOAMING, HIGH TEMPERATURE, AND LOW OIL PRESSURE.
Page
NOVEMBER 30, 2001
1-12-35
Code
1 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
APU OIL FILLING AND OIL LEVEL CHECK
Page
1-12-35
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
HYDRAULIC SYSTEM SERVICING HYDRAULIC FLUID LEVEL CHECK Gain access through the panel located aft of the wing fairing (on both sides of the aircraft). On the hydraulic fluid level indicator, make sure the needle pointer is between the 4.5 and 5.5 liter marks (normal range). The shaded region is the dispatchability range. If the pointer is below the refill mark, fill the reservoir until you have the correct full level mark. Low oil level in the reservoir can be a sign that there is a leak in the system. After servicing the hydraulic system, close the related hydraulic fluid reservoir access panel. If level indicator is inoperative, it is still possible to check fluid level, but a maintenance technician is required to do the job. CAUTION: USE ADEQUATE GOGGLES AND RUBBER GLOVES WHILE SERVICING HYDRAULIC SYSTEM. IN CASE HYDRAULIC FLUID COMES IN CONTACT WITH THE SKIN, FLUSH THE AFFECTED AREA WITH WATER. IN CASE HYDRAULIC FLUID COMES IN CONTACT WITH THE EYES, FLUSH THEM WITH WATER AND SEEK MEDICAL ATTENTION.
Page
NOVEMBER 30, 2001
1-12-40
Code
1 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
CHECK OF HYDRAULIC FLUID LEVEL Page
1-12-40
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
LANDING GEAR SERVICING MAIN AND NOSE LANDING GEAR SHOCK ABSORBER PRESSURE The main and nose landing gear shock absorber sometimes need nitrogen to be filled. Nitrogen is filled through a charging valve installed at the landing gear. Filling pressure is a function of the piston height, as checked in the charts below (there are separate charts for nose and main landing gears).
MAIN LANDING GEAR SERVICING Page
NOVEMBER 30, 2001
1-12-40
Code
3 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
NOSE LANDING GEAR SERVICING
TIRE PRESSURE Nose Tire Pressure: 84 +2/-2 psi Main Tire Pressure: 160 +4/-4 psi
Page
1-12-40
Code
4 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
BRAKE WEAR INDICATOR Checking the brake wear indicators is required during walk-arounds, as prescribed in the approved Airplane Flight Manual, according to the following procedure: − Operate the emergency/parking brake handle and visually verify all pistons (2) of the brake assembly for operation. Brake wear indicator positions must be inspected with brake pressurized (brake applied). − Inspect the brake wear indicators for visible cracks. − Inspect the brake wear indicators length. The length of the brake wear indicator for a new brake is 22.86 mm (0.90 in). When the indicator rod is flat with the hexagonal insert, the brakes are full worn out and should be replaced. − If one or more of the brake wear indicators does not come out of the piston housing, the brake assembly must be replaced.
Page
NOVEMBER 30, 2001
1-12-40
Code
5 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
BRAKE WEAR INDICATION
Page
1-12-40
Code
6 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
OXYGEN SERVICING The oxygen system is filled from an external service panel located on the right side of the aircraft nose. The service panel is common for the crew oxygen system and the passenger oxygen system. It has independent fill valve and pressure gauges for each system. A 50-cu.ft crew oxygen cylinder and one or two 77-cu.ft passenger oxygen cylinders are installed on the right side of the cockpit/passenger cabin partition for use in emergency. The crew oxygen system is designated for pilot, copilot and observer. The passenger oxygen system configuration with one 77-cu.tf cylinder is available for up 14 passenger cabin occupants and the passenger oxygen system configuration with two 77-cu.ft cylinders is available for up 20 passenger cabin occupants. Their pressure can be checked on the EICAS, inside the cockpit, or in the service panel. The minimum oxygen pressure in the crew oxygen system for dispatch is: − Crew made up of pilot and copilot: 1130 psi − Crew made up of pilot, copilot and observer: 1570 psi. The minimum oxygen pressure in the passenger oxygen system for dispatch is 1250 psi. Portable oxygen cylinders are distributed along the cabin for passenger and flight attendant emergencies. The minimum pressure for dispatch is 1200 psi. Dispatching pressures were calculated for an ambient temperature of 21°C (70°C). For other temperatures, a correction chart is available at Section 2-16. The Protective Breathing Equipment (PBE) are available in the cockpit and passenger cabin. WARNING: HIGH-PRESSURE OXYGEN CAN CAUSE SUDDEN COMBUSTION BY CONTACT WITH OIL, GREASE, SOLVENTS, HYDROCARBONS IN GENERAL, CLOTH FIBERS, METAL CHIPS, ETC. QUALIFIED PERSONNEL ONLY MUST HANDLE AND SERVICE THE OXYGEN EQUIPMENT.
Page
NOVEMBER 30, 2001
1-12-45
Code
1 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
OXYGEN SERVICING
Page
1-12-45
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
WATER/TOILET SERVICING AFT LAVATORY´S WATER TANK SERVICING NOTE: For airplanes up to S/N 685. Filling and draining of the water tank of aft lavatory is done through a panel installed on the lower right side of the wing-to-fuselage fairing aft section. NOTE: - Use only potable water to fill the water tank. - The quality of water depends on the appropriate cleaning and maintenance of water tank. To drain the water tank, remove the cap from the water overflow nipple, pull the handle to the open position and put the drain toggle switch in the open position. Draining is recommended when freezing or icing conditions are forecast after the last flight and parking overnight. To fill the tank of water (50 liters - 13.2 US gallons) make sure that the drain toggle switch is in the closed position, remove the caps from the water filling nipple and from the water overflow nipple. Install the water service cart to the water filling nipple and pull the handle to the open position. The tank is full when water starts to flow through the overflow nipple.
Page
REVISION 7
1-12-50
Code
1 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
WATER TANK DRAINING AND FILLING Page
1-12-50
Code
2 01
REVISION 5
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
GALLEY´S WATER TANK AND AFT LAVATORY´S WATER TANK SERVICING NOTE: For airplanes S/N 686 and on. Filling and draining of the water tanks of galley (15 liters - 3.9 US gallons) and aft lavatory (35 liters - 9.2 US gallons) are done through two panels, one installed on the forward right side of the airplane; the other installed on the lower right side of the wing-to-fuselage fairing aft section. Both the Galley (FWD) and Lavatory (AFT) are serviced in the same manner. Airplane power is not required to service the airplane (only for reading quantity indications). WATER FILLING PROCEDURE: − Open the Water Service Panel doors. − Remove the protective caps from the FILL and VENT/OVERFLOW ports. − Connect the coupling from the Water Service Cart to the FILL port connection. − Fill the system with potable water until water starts to flow from the VENT/OVERFLOW port. − Disconnect the water source from the FILL port. − Allow all residual water to completely drain from both FILL and VENT/OVERFLOW ports. − Re-install both the FILL and VENT/OVERFLOW ports protective caps. − Close the Service Panel doors. To verify the quantity of water, power the A/C and push the appropriate switch selection on the Quantity Indication Panel.
Page
REVISION 7
1-12-50
Code
3 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
WATER DRAINING PROCEDURE: NOTE: It is recommended to drain the Water System if the airplane is expected to stay overnight in an ambient below the freezing point of water. The Water System is drained from both the Galley and Lavatory water service panels located forward and aft respectively and are serviced in the same manner. Airplane power is not required to service the airplane. To drain each tank: − Open the Water Service Panel doors. − Remove the protective caps from both the FILL and VENT/OVERFLOW ports. − Pull the “T” handle to open the drain valves in either the Galley or the Lavatory cabinets. − Allow all water to drain from the system prior to re-placing the protective caps. − Close the drain valves by pushing the “T” handle to its stop position. − Re-install both the FILL and VENT/OVERFLOW port caps. − Close the Water Service Panel doors.
Page
1-12-50
Code
4 01
REVISION 5
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
WATER TANK DRAINING AND FILLING Page
REVISION 5
1-12-50
Code
5 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
FORWARD LAVATORY´S WATER SYSTEM NOTE: Optional for airplanes S/N 686 and on. The water storage tank must be filled with potable water. Airplane power is not required to service the water tank. Two procedures can be used to service the water tank: WATER FILLING PROCEDURE ONE: − Access the forward lavatory inside airplane; − Remove the access panel from the vanity cabinet, under the sink; − Remove the FILL cap from the water tank; − Pull and extend the FILL funnel from the water tank; − FILL water tank (10 liters, 2.6 U.S. gallons capacity); − Push and stow the FILL funnel into the water tank; − Install FILL cap on the water tank; − Install the access panel on vanity cabinet. WATER FILLING PROCEDURE TWO: − Access the forward lavatory inside airplane; − Remove the access panel from the vanity cabinet, under the sink; − Disconnect hose from water tank (quick disconnect fitting); − Pull and open the slide out drawer in the vanity cabinet, to access water tank; − Remove securing strap from water tank and remove water tank; − Service water tank as necessary; − Install water tank and securing strap on the slide out drawer; − Connect the hose to the water tank (quick disconnect coupling); − Close the slide out drawer in the vanity cabinet; − Install the access panel on vanity cabinet.
Page
1-12-50
Code
6 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
FORWARD LAVATORY WATER TANK
Page
REVISION 5
1-12-50
Code
7 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
WATER DRAIN OPERATION PROCEDURE. NOTE: It is recommended to drain the Water System if the aircraft is expected to stay overnight in an ambient below the freezing point of water. − Access the forward lavatory inside airplane; − Remove the access panel from the vanity cabinet, under the sink; − On the water system manifold, put the water DRAIN valve to OPEN position. Allow a couple minutes for water to back drain to the water tank; − Disconnect hose from water tank (quick disconnect coupling); − Pull and open the slide out drawer in the vanity cabinet, to access water tank; − Remove securing strap from water tank and remove water tank; − Remove water tank and DRAIN outside airplane; − Install water tank on slide out drawer and secure with strap; − Connect the hose to water tank (quick disconnect coupling); − On the water system manifold, put the water DRAIN valve to CLOSED position; − Close the slide out drawer in the vanity cabinet; − Install the access panel on vanity cabinet. NOTE: - Airplane power is not required to service the water tank. - Both the FILL and VENT/OVERFLOW ports are electrically energized whenever the airplane is powered. Therefore, CAUTION is advised when handling both the FILL and VENT/OVERFLOW protective caps. This CAUTION applies to both the System’s fill and draining procedures.
Page
1-12-50
Code
8 01
REVISION 5
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
REVISION 4
1-12-50
Code
9 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
FORWARD LAVATORY TOILET NOTE: Optional for airplanes S/N 686 and on. The recirculating toilet is a light weight, compact, completely self contained unit, with electrically operated flush. The toilet uses ordinary tap water, and a germicidal deodorant as a flush fluid. The unit requires only external connection to 24-28 VDC electrical power. The toilet assembly is designed for permanent installation in the airplane, requiring only the removal of the waste tank when servicing is desired.
FORWARD TOILET SERVICING Servicing the forward toilet waste tank is accomplished as follows: NOTE: The toilet waste tank is a self contained unit. It must be removed from the airplane and drained at proper facility. − Access the forward lavatory inside airplane; − Remove the access panel from the toilet shroud cabinet; − Disconnect the flush hose (quick disconnect coupling) and drain residual flush fluid; − Close the knife valve at the bottom of the toilet bowl; − Press the two pres-lot fasteners on each side of the knife actuator valve to unlock the tank; − Grab the carry handle on the toilet tank and pull the toilet tank out of the toilet shroud cabinet, and remove from the airplane; − At proper facility outside the airplane, service the toilet tank according to service procedure placard on toilet tank; − At the forward lavatory inside the airplane, install the toilet tank in the toilet shroud cabinet; − Press the two pres-lot fasteners to the first detent to secure the tank; − Connect the flush hose (quick disconnect coupling) to toilet tank; − Install the access panel on the toilet shroud cabinet.
Page
1-12-50
Code
10 01
REVISION 4
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
FORWARD TOILET WASTE TANK
Page
REVISION 4
1-12-50
Code
11 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
TOILET SERVICING Toilet waste disposal servicing is accomplished by accessing a panel at the rear right side of the fuselage. A sanitary service unit must be connected to the airplane service panel.
TOILET SERVICING Page
1-12-50
Code
12 01
REVISION 5
AIRPLANE OPERATIONS MANUAL
GROUND SERVICING
Servicing the toilet waste tank is accomplished as follows: NOTE: Commercial deodorants and disinfectants can be added to the waste tank, but the tank definitive volume must not contain such material. − Open waste-service-panel door. − Remove the protective cap from the toilet rinse nipple. − Release the handle and open the cap of the waste drain valve. − Connect the lavatory dumping coupling of the lavatory servicing dolly to the waste drain valve. − Connect the lavatory filling coupling to the rinse nipple. − Push the lever of the waste drain-valve actuator to open its internal flapper valve. Do not operate the coupling handle; its operation is not necessary. − Pull and lock the drain control handle to open the holding-tank drain valve. − Continue the tank drainage until the waste flow stops. − Flush with water through the rinse nipple for approximately 3 minutes. − Release the control cable. − Fill the waste holding tank with 15 liters (4 gal) of water. − Pull and lock the drain control handle to open the holding-tank drain valve. − Release the drain control handle after all liquid is drained. − Fill the waste holding tank with a maximum of 7.5 liters (2 gal) of water and then add: − 57 grams (2 oz.) of Monogram MC-2000 germicidal deodorant, or; − 170 grams (6 oz.) of Mirabowl "Q" germicidal deodorant. − Disconnect the lavatory dumping and filling couplings. − Close the cap and latch the handle of the waste drain valve. The flapper valve will close automatically when the cap is closed. − Install the cap on the toilet rinse nipple. NOTE: The access door will close only if the waste drain valve is correctly closed. − Close waste-service-panel door.
Page
REVISION 4
1-12-50
Code
13 01
GROUND SERVICING
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-12-50
Code
14 01
REVISION 4
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
SECTION 1-01 LIMITATIONS TABLE OF CONTENTS Page Block Introduction ................................................................................ 1-01-00 General ...................................................................................... 1-01-01 Weight and Center of Gravity..................................................... 1-01-05 Operational Limitations .............................................................. 1-01-10 Systems: Enhanced Ground Proximity Warning System (EGPWS) .... 1-01-30 Electrical ............................................................................... 1-01-32 Fuel ....................................................................................... 1-01-36 APU....................................................................................... 1-01-38 Powerplant ............................................................................ 1-01-40 Pneumatic, Air Conditioning and Pressurization................... 1-01-48 Ice and Rain Protection......................................................... 1-01-50 Oxygen.................................................................................. 1-01-52 Navigation, Communication and Autopilot ............................ 1-01-56 FMS ...................................................................................... 1-01-60 CAT II Operation ........................................................................ 1-01-65
Page
REVISION 7
1-01-00
Code
1 02
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
INTRODUCTION The airplane must be operated in accordance with the limitations presented in this Section. These limitations also apply to operations in accordance with an approved Supplement or Appendix to the AFM, except as modified by such Supplement or Appendix. The information contained in this section is derived from the Approved Airplane Flight Manual. Flight crewmembers should have all limitations committed to memory (except tables and charts). Some items may not be included herein, as they may be identified in a panel/placard or annunciated by some kind of alarm/warning. Compliance to the Emergency and Abnormal Procedures will also assure that certain limitations are complied with. In the event that a limitation in this manual disagrees with the AFM limitation, the AFM must prevail. In the event that a placard or instrument marking disagrees with the limitations shown in this manual, the more restrictive limitation must prevail.
Page
1-01-00
Code
2 02
REVISION 4
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
GENERAL MINIMUM CREW Minimum Flight Crew .................................................... PILOT AND COPILOT
KINDS OF OPERATION This airplane may be flown day and night in the following conditions, when the appropriate equipment and instruments required by airworthiness and operating regulations are approved, installed and in an operable condition: − Visual (VFR); − Instrument (IFR); − Icing conditions.
MAXIMUM NUMBER OF SEATS (NON-AFM) The maximum number of available seats is 19 on the EMB-135 BJ. It includes 2 seats for pilots, 1 optional seat for attendant, 1 for cockpit observer, and up to 15 passenger seats.
Page
SEPTEMBER 30, 2002
1-01-01
Code
1 01
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-01-01
Code
2 01
NOVEMBER 30, 2001
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
WEIGHT AND CENTER OF GRAVITY EMB-135BJ MODEL - TAKEOFF WITH FLAPS 9° MAXIMUM WEIGHT (lb) AIRPLANE MODEL EMB-135BJ S/N up to 591 and Pre-Mod SB 145LEG-28-0010 S/N 625 and on or Post-Mod SB 145LEG-28-0010
Max. Max. Max. Max. Ramp Takeoff Landing Zero Fuel Weight Weight Weight Weight (MRW) (MTOW) (MLW) (MZFW) 49096
48942
40786
35274
49758
49604
40786
35274
To comply with the performance and operating limitations of the regulations, the maximum allowable takeoff and landing operational weights may be equal to, but not greater than design limits. The takeoff weight (weight at brake release or at start of takeoff run) is the lowest among MTOW and the following weights, presented in the applicable engine supplement: − Maximum takeoff weight for altitude and temperature determined from Maximum Takeoff Weight - Climb Limited chart. − Maximum takeoff weight, as limited by runway length and determined from Maximum Takeoff Weight - Field Length Limited chart. − Maximum takeoff weight, as limited by brake energy and determined from Maximum Takeoff Weight - Brake Energy Limited chart. − Maximum takeoff weight, as limited by obstacle clearance, enroute, and landing operating requirements. The landing weight is the lowest among MLW and the following weights, presented in the applicable engine supplement: − Maximum approach and landing weight for altitude and temperature determined from Maximum Landing Weight - Climb Limited charts. − Maximum landing weight, as limited by runway length and determined from Maximum Landing Weight - Field Length Limited chart. Page
REVISION 4
1-01-05
Code
1 02
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
CENTER OF GRAVITY ENVELOPE EMB-135BJ S/N UP TO 591 AND PRE-MOD SB 145LEG-28-0010 (TAKEOFF WITH FLAPS 9°) INFLIGHT LIMITS (FLAPS AND GEAR UP) TAKEOFF AND LANDING LIMITS 54000 52000
26.9%
50000
35%
MRW
22.4% MTOW
48000 46296 lb
46000 44000
17.3%
WEIGHT - lb
42000
MLW
40786 lb
40786 lb
40000 15% 38000 36067 lb
36000
MZFW
35274 lb 34000 32000
31967 lb 30864 lb
135BJFAA002 - 24OCT2002
30000 15% 28000
29350 lb 28660 lb 30%
35%
26000 0
10
30
40
50
CG POSITION - %MAC
Page
1-01-05
20
Code
2 02
REVISION 4
60
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
EMB-135BJ S/N 625 AND ON OR POST-MOD SB 145LEG-28-0010 (TAKEOFF WITH FLAPS 9°)
INFLIGHT LIMITS (FLAPS AND GEAR UP) TAKEOFF AND LANDING LIMITS 52000 27.5%
35%
MRW
50000
MTOW
22.4%
48000 46296 lb
46000 44000
17.3% 42000
MLW
40786 lb
40786 lb
WEIGHT - lb
40000 15%
38000 36067 lb
36000
MZFW
35274 lb 34000 31967 lb 30865 lb
32000 30000
15% 135BJFAA006 - 29OCT2002
28000
29350 lb 28660 lb 35% 30%
26000 24000 0
10
20
30
40
50
60
CG POSITION - %MAC
Page
REVISION 4
1-01-05
Code
3 02
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
LOADING The airplane must be loaded in accordance with the information contained in the Weight and Balance Manual (WB-135/1562). NOTE: The RH side mid-cabin divider must not be installed if the closest divan seat position to the divider is occupied for taxi, takeoff and landing.
Page
1-01-05
Code
4 02
REVISION 3
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
OPERATIONAL LIMITATIONS OPERATIONAL ENVELOPE AIRPLANES PRE-MOD. SB 145LEG-00-0007 45000 40000
-21.5°C
-65°C 39000 ft
35000
ALTITUDE - ft
30000 ISA + 35°C
25000 20000 15000 10000
8500 ft
5000
• -1000 ft
0 -54°C
52°C
-40°C
135BJFAA001 - 19NOV2003
-5000 -70 -60 -50 -40 -30 -20 -10
0
10 20 30 40 50 60
STATIC AIR TEMPERATURE - °C
TAKEOFF, LANDING
•
NOTE: - In the event of a landing below -40°C, the airplane may not takeoff without further maintenance inspection. - Minimum Total Air Temperature above 25000 ft is -45°C. Page
REVISION 7
1-01-10
Code
1 02
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
AIRPLANES POST-MOD. SB 145LEG-00-0007 OR EQUIPPED WITH AN EQUIVALENT MODIFICATION FACTORY INCORPORATED 45000 -65°C 40000
-21.5°C 41000 ft
35000
ALTITUDE - ft
30000 ISA + 35°C
25000 20000 15000 10000
8500 ft
5000
• -1000 ft
0 -54°C
52°C
-40°C
135BJFAA041 - 15OCT2004
-5000 -70 -60 -50 -40 -30 -20 -10
0
10 20 30 40 50 60
STATIC AIR TEMPERATURE - °C
TAKEOFF, LANDING
•
NOTE: - In the event of a landing below -40°C, the airplane may not takeoff without further maintenance inspection. - Minimum Total Air Temperature above 25000 ft is -45°C.
Page
1-01-10
Code
2 02
REVISION 7
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
REVISION 7
1-01-10
Code
2A 02
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
AIRSPEEDS LANDING GEAR OPERATION/EXTENDED SPEED (VLO AND VLE) VLO for retraction ...........................................................200 KIAS VLO for extension...........................................................250 KIAS VLE ............................................................................250 KIAS NOTE: - VLO for retraction is the maximum speed at which the landing gear can be safely retracted. - VLO for extension is the maximum speed at which the landing gear can be safely extended. - VLE is the maximum speed at which the airplane can be safely flown with the landing gear extended and locked.
Page
1-01-10
Code
2B 02
REVISION 7
LIMITATIONS
AIRPLANE OPERATIONS MANUAL MAXIMUM OPERATING SPEED (1) 45000
(2)
40000
35000
MMO=0.80
ALTITUDE - ft
30000
25000
20000
VMO
15000
135BJFAA003 - 30DEC2004
10000
5000
0 200 210 220 230 240 250 260 270 280 290 300 310 320 330 340 350
AIRSPEED - KIAS
NOTE: 1) The VMO/MMO may not be deliberately exceeded in any regime of flight (climb, cruise or descent). 2) Only applicable to airplanes Post-Mod. SB 145LEG-00-0007 or equipped with an equivalent modification factory incorporated. Page
REVISION 7
1-01-10
Code
3 02
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
MANEUVERING SPEED (VA) VA .................................................................................200 KIAS NOTE: Maneuvers that involve angle of attack near the stall or full application of rudder, elevator, and aileron controls should be confined to speeds below VA. In addition, the maneuvering flight load factor limits, presented in this Section, should not be exceeded.
FLIGHT CONTROLS ELECTROMECHANICAL GUST LOCK Each time electromechanical gust lock lever is set to unlocked position elevator movement must be checked. This check must be performed at least 10 seconds after positioning the gust lock lever to the unlocked positon by moving the control column from the full up stop to the full down stop and back to the full up stop position. MAXIMUM FLAP EXTENDED SPEED (VFE) Flaps 9° .........................................................................250 KIAS Flaps 22° .......................................................................200 KIAS Flaps 22° (In icing conditions and yaw damper disengaged) ..................................180 KIAS Flaps 45° .......................................................................145 KIAS MAXIMUM FLAP EXTENDED ALTITUDE Maximum Altitude for Flap Extension............................20000 ft PITCH TRIM Maximum Airspeed after Takeoff/During Climb without Retrimming ...............160 KIAS
TAILWIND Maximum Takeoff and Landing Tailwind Component.......10 kt
DIRECT VISION WINDOW (AFM PROCEDURES) Maximum recommended speed to remove direct vision windows is 140 KIAS. Page
1-01-10
Code
4 02
REVISION 5
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
UNPRESSURIZED FLIGHT (NON-AFM) Maximum altitude for operation after an in-flight depressurization, is 10000 ft MSL unless MEA or otherwise required. Maximum altitude for dispatch for an unpressurized flight is 10000 ft.
TURBULENT AIR PROCEDURES)
PENETRATION
SPEED
(AFM
At or below 10000 ft ...................................................... 200 KIAS Above 10000 ft .............................................................. 250 KIAS/0.63M, WHICHEVER IS LOWER
MAXIMUM RECOMMENDED CROSSWIND (NON-AFM) Embraer aerodynamics analysis have resulted in the following maximum recommended crosswinds for takeoff and landing: Dry runway ............................................................... 30 kt Wet runway .............................................................. 30 kt
MANEUVERING FLIGHT LOAD FACTORS These corresponding accelerations limit the bank angle during turns and limit the pull-up maneuvers. LOAD FACTOR LIMIT
FLAPS UP
Positive Negative
2.51 g -1.00 g
FLAPS DOWN (9°, 22° and 45°) 2.00 g 0g
Page
REVISION 4
1-01-10
Code
5 02
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
RUNWAY Runway Slope ...............................................................-2% TO +2% Runway Surface Type ...................................................PAVED
Page
1-01-10
Code
6 02
REVSION 4
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
ENHANCED GROUND PROXIMITY WARNING SYSTEM (EGPWS) The following limitations are applicable to the Enhanced Ground Proximity Warning System (EGPWS): − The Allied-Signal Enhanced Ground Proximity Warning System Pilot’s Guide, Document Number 060-4241-000, March 1997 edition (or later revision of the manual) or certification authority accepted Operating Manual, must be immediately available to the flight crew. − Allied-Signal Application Software version 202 and Configuration Software version 202 or later must be installed. − Navigation is not to be predicated on the use of the Terrain Awareness Display. − The EGPWS data base, displays, and alerting algorithms currently do not account for man-made obstructions. − Pilot should inhibit the Terrain Awareness Alerting and Display function by pressing the TERRAIN SYS OVRD button when within 15 NM of takeoff, approach, or landing at an airport when any of the following conditions apply: - The airport has no approved instrument approach procedure. - The airport is not included in the Allied Signal data base. - The longest runway is less than 1070 m (3500 ft) in length. − Terrain Awareness Alerting and Display functionality must be manually inhibited when below the transition altitude while flying QFE on approach into an airport which is more than 200 ft above or below sea level (not applicable to software version 216 and on). − Pilots are authorized to deviate from their current Air Traffic Control (ATC) clearance to the extent necessary to comply with an EGPWS warning. − The Terrain Display is intended to be used as a situational tool only and may not provide the accuracy and/or fidelity on which to solely base terrain avoidance maneuvering.
Page
REVISION 7
1-01-30
Code
1 01
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
− In the event that accuracy of the airplane position data from the FMS becomes inadequate for navigation (Dead Reckoning Mode), the Terrain Awareness Alerting and Display functions must be inhibited. This will not affect the basic GPWS functions (modes 1 to 7). If the FMS is restored after a period of inadequacy, the Terrain Awareness may be enabled by pressing again the TERRAIN SYS OVRD button. − In case of a conflict between the terrain alerts and an auto-poppedup picture, pilots must check the sweeping marker movement on the horizontal line below the terrain picture. If the marker is frozen, the MFD terrain indication must be deselected on MFD bezel panel. − In case of a conflict between the terrain alerts and an auto-poppedup picture, pilots must check the MFD 2 terrain information. If the terrain picture bus fail is not annunciated (TERR amber annunciation), the MFD 2 must be used as terrain picture reference.
Page
1-01-30
Code
2 01
REVISION 5
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
ELECTRICAL Maximum Load on Main Generator .............................. 400 A Maximum Load on APU Generator: Up to 30000 ft .......................................................... 400 A Above 30000 ft......................................................... 300 A Maximum Battery Temperature .................................... 70°C
Page
NOVEMBER 30, 2001
1-01-32
Code
1 01
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-01-32
Code
2 01
NOVEMBER 30, 2001
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
FUEL USABLE FUEL EMB-135BJ S/N UP TO 591 AND PRE-MOD SB 145LEG-28-0010 TANK WING TANK FUS 1 (Left side)
FUS 1 (Right side)
FWD 1 AFT 1 FWD 2 AFT 2
USABLE FUEL
TOTAL
844.9 US Gal (5703.4 lb) 279 US Gal limited to1764 lb 217 US Gal limited to1455 lb 279 US Gal limited to1764 lb 217 US Gal limited to1455 lb
1689.64 US Gal (11406.76 lb) 496 US Gal limited to 3219 lb
496 US Gal limited to 3219 lb
EMB-135BJ S/N 625 AND ON OR POST-MOD SB 145LEG-28-0010 TANK WING TANK FUS 1 (Left side)
FUS 2 (Right side)
FWD 1 AFT 1 FWD 2 AFT 2
USABLE FUEL
TOTAL
844.9 US Gal (5703.4 lb) 294 US Gal limited to1984 lb 217 US Gal limited to 1477 lb 294 US Gal limited to1984 lb 217 US Gal limited to 1477 lb
1689.64 US Gal (11406.76 lb) 511 US Gal limited to 3461 lb
511 US Gal limited to 3461 lb
FUEL TANKS MAXIMUM PERMITTED IMBALANCE The maximum permitted imbalance between the wing tanks is 800 lb. For the maximum permitted imbalance between the FWD tank and AFT tank of each system, see the following load charts applicable to your airplane:
Page
REVISION 6
1-01-36
Code
1 02
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
AIRPLANES S/N UP TO 591 AND PRE-MOD SB 145LEG-28-0010
AFT TANK (lb)
FUSELAGE TANKS LOAD CHART I 1600 1400 1200 1000 800 600 400 200 0 0
200
400
600
800
1000 1200 1400 1600 1800 2000
FWD TANK (lb) 135B J A OM112002A - 18S EP 2003
NOTE: The fuselage tanks fuel load must be within the closed area of the chart. AIRPLANES S/N 625 AND ON OR POST-MOD SB 145LEG-28-0010
AFT TANK (lb)
FUSELAGE TANKS LOAD CHART II 1600 1400 1200 1000 800 600 400 200 0 0
200 400 600
800 1000 1200 1400 1600 1800 2000 2200 FWD TANK (lb)
135B J A OM112002B - 18S EP 2003
NOTE: The fuselage tanks fuel load must be within the closed area of the chart. Page
1-01-36
Code
2 02
REVISION 4
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
UNUSABLE FUEL TANK
UNUSABLE FUEL
TOTAL
WING TANK (All electric fuel pumps operating)
5.8 US Gal (39 lb)
11.6 US Gal (78 lb)
WING TANK (Any electric fuel pump inoperative) FUS 1 FWD 1 (Left side) AFT 1 FUS 2 FWD 2 (Right side) AFT 2
Up to 54 US Gal (364.5 lb)
Up to 108 US Gal (729 lb)
3.6 US Gal (24 lb) 4.6 US Gal (31 lb) 3.6 US Gal (24 lb) 4.6 US Gal (31 lb)
8.2 US Gal (55 lb) 8.2 US Gal (55 lb)
NOTE: - When the EICAS fuel quantity is zero in level flight, any fuel remaining in the tanks can not be used safely in flight. - The unusable fuel values above have been determined for an adopted fuel density of 6.751 lb/US Gal. - When performing pressure refueling, the usable fuel quantity in each wing tank may be reduced by 13.2 US Gal maximum.
FUEL SPECIFICATION Brazilian Specification ................................................... QAV1 ASTM Specification....................................................... D1655-JET A AND JET A-1 American Specification ................................................. MIL-T-83133AJP8
FUEL TANK TEMPERATURE Minimum ....................................................................... -40°C Maximum ...................................................................... 52°C NOTE: If fuel does not contain an icing inhibitor, the temperature of fuel leaving FCOC must be above 4°C (refer to FUEL LOW TEMPERATURE Procedure).
Page
REVISION 6
1-01-36
Code
3 02
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-01-36
Code
4 02
REVISION 4
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
AUXILIARY POWER UNIT OPERATIONAL LIMITS APU Model PARAMETER ALTITUDE FOR START OPERATION ALTITUDE ROTOR SPEED EGT: START CONTINUOUS
T-62T-40C14 MIN MAX 30000 ft 39000 ft (3) 108% (1) 884°C 680°C (2)
NOTE: 1) The APU will be automatically shut down at 104% rotor speed. 2) The APU EGT may be exceeded up to 717ºC for 5 minutes maximum. 3) Above 37000 ft APU bleed usage is not allowed. 4) Minimum battery temperature for APU start is -20ºC.
APU STARTER LIMITS Cooling period between each starting attempt: Between Three Consecutive Attempts................ 1 MINUTE OFF Between Two Series of Three Consecutive Attempts ......................... 30 MINUTES OFF
Page
REVISION 7
1-01-38
Code
1 02
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-01-38
Code
2 02
REVISION 5
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
POWER PLANT WARNING: ALL FOUR FADECS INSTALLED ON THE AIRPLANE MUST BE THE SAME PART NUMBER. INCORRECT ENGINE OPERATION CAN RESULT FROM USING FADECS WITH TWO DIFFERENT PART NUMBERS.
OPERATIONAL LIMITS (ROLLS-ROYCE AE3007A1E) PARAMETER N1 N2 ITT: START ALL TAKEOFF MODES MAX CONTINUOUS OIL PRESSURE: BELOW 88% N2
MIN -
MAX 100.0% 103.7% (12)
-
800°C (10) 992°C (1) 970°C (2) 935°C
34 psi
21°C (5)
95 psi (4)(7) 110 psi (4)(8) 95 psi (7) 110 psi (8) 126°C
-
1.8 IPS (6) 1.1 IPS (6)
AT OR ABOVE 88% N2 48 psi (3) OIL TEMPERATURE VIBRATION: LP SPOOL HP SPOOL
NOTE: 1) Temperatures between 971°C and 992°C are time limited to 90 seconds. 2) Time limited to 5 minutes (including the transient allowance). 3) Operation below 48 psi down to 34 psi is permitted during 5 minutes maximum. 4) May be exceeded during starts if oil temperature is below 21°C. The engine must remain at IDLE until the oil pressure is less than 95 psi (110 psi for airplanes Post-Mod. SB 145LEG-73-0004 or equipped with an equivalent modification factory incorporated). 5) Minimum oil temperature for starting is -40°C for lubrication oil specified by MIL-L-23699D and -54°C for lubrication oil specified by MIL-L-7808K. Page
REVISION 7
1-01-40
Code
1 02
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
6) Vibration in the amber range below 2.5 IPS is time limited to 5 minutes during the takeoff or go-around phases or 10 seconds during the remainder flight phases. 7) Operation in oil pressure amber range between 96 and 115 psi is permitted in all operational modes and time limited to 5 minutes or between 116 and 155 psi in all operational modes time limited to 2 minutes. Total time above 95 psi may not exceed 5 minutes. 8) For airplanes Post-Mod. SB 145LEG-73-0004 or equipped with an equivalent modification factory incorporated the upper limit of the oil pressure green range is 110 psi. Operation in oil pressure amber range is permitted between 111 and 115 psi in all operational modes time limited to 5 minutes, or between 116 and 155 psi in all operational modes time limited to 2 minutes. Total time above 110 psi may not exceed 5 minutes. 9) Maximum N2 for engine airstart is 56%. 10) During start the ITT limit of 800°C may be exceeded for up to 5 seconds to a maximum temperature of 850°C. 11) Any engine exceedance or peak must be monitored and logged by the crew. 12) For airplanes Post-Mod. SB 145LEG-73-0006 or equipped with an equivalent modification factory incorporated, the N2 limit is 105.0%. TAKEOFF THRUST MODE Only ALT T/O-1, T/O and E T/O modes are allowed for takeoff.
STARTER LIMITS Dry Motoring Continuous Operation ..............................5 MINUTES ON, 20 MINUTES OFF Starting Cycle: First to Fourth Cycles ...............................................1 MINUTE ON, 1 MINUTE OFF Fifth Cycle ................................................................1 MINUTE ON, 20 MINUTES OFF
Page
1-01-40
Code
2 02
REVISION 7
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
AUTOMATIC TAKEOFF THRUST CONTROL SYSTEM (ATTCS) ATTCS must be operative to select ALT T/O-1, T/O or E T/O modes. Airplanes equipped with EICAS 18.5 or previous versions must perform a Thrust Assurance Check at least once a week by selecting T/O RSV mode (pushing Thrust Levers toward MAX) and checking engine parameters. Airplanes equipped with EICAS 19 or later approved versions do not require the Thrust Assurance Check.
THRUST REVERSER Thrust reversers are intended for use during rejected takeoff or landing only. Do not attempt a go-around procedure after deployment of the thrust reversers following a landing. Selection of thrust reversers in flight or their preselection before touchdown is prohibited.
ENGINE WARM-UP Prior to takeoff, the engines must be allowed to run at low thrust to stabilize the engine temperatures before takeoff thrust is adjusted. After start, the engines must run at idle or taxi thrust during at least 4 minutes for cold engines or 2 minutes for warm engines. NOTE: - To increase N2 above 83% the engine oil temperature must be at 40°C minimum. In lieu of this limit, it is acceptable to either run the engine for at least 8 minutes or complete a static run-up to 88% N2, stabilize, and check to ensure that oil pressure is equal or less than 83 psi. - The engine is considered cold if it has been shutdown for more than 90 minutes.
ENGINE COOL DOWN The engines must run for at least 1 minute at idle or taxi thrust before shutdown.
Page
REVISION 7
1-01-40
Code
3 02
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-01-40
Code
4 02
REVISION 3
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
PNEUMATIC, AIR PRESSURIZATION
CONDITIONING
AND
PRESSURIZATION AIRPLANES PRE-MOD. SB 145LEG-00-0007 Maximum differential pressure...................................... 8.1 psi Maximum differential overpressure............................... 8.4 psi Maximum differential negative pressure ....................... -0.3 psi AIRPLANES POST-MOD. SB 145LEG-00-0007 OR EQUIPPED WITH AN EQUIVALENT MODIFICATION FACTORY INCORPORATED Maximum differential pressure...................................... 8.4 psi Maximum differential overpressure............................... 8.6 psi Maximum differential negative pressure ....................... -0.3 psi
Page
REVISION 7
1-01-48
Code
1 01
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-01-48
Code
2 01
ORIGINAL
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
ICE AND RAIN PROTECTION OPERATION IN ICING CONDITIONS Maximum Temperature for Anti-Icing Operation................ 10°C Minimum Temperature for Manual Anti-Icing Operation.... -40°C Single engine or single bleed maximum altitude operation in icing conditions ............................. 15000 ft Holding Configuration: Landing Gear ................................................................ UP Flaps ............................................................................. UP Minimum Airspeed ........................................................ 200 KIAS NOTE: - There is no temperature limitation for anti-icing system automatic operation. - Use Static Air Temperature (SAT) on ground or for takeoff operations and Total Air Temperature (TAT) for operations in flight. - Icing conditions may exist whenever the Static Air Temperature (SAT) on the ground or for takeoff, or Total Air Temperature (TAT) in flight, is 10°C or below and visible moisture in any form is present (such as clouds, fog with visibility of one mile or less, rain, snow, sleet, and ice crystals). - Icing conditions may also exist when the SAT on the ground and for takeoff is 10°C or below when operating on ramps, taxiways, or runways where surface snow, ice, standing water, or slush may be ingested by the engines, or freeze on engines, nacelles, or engine sensor probes. - Notwithstanding ice detector monitoring, the crew remains responsible for monitoring icing conditions and for manual activation of the ice protection system if icing conditions are present and the ice detection system is not activating the ice protection system. - The clear ice detection system will sense clear ice accumulation only in the inboard area of the upper wing surface. It does not detect the presence of frost or snow and it is unable to sense ice accumulations on other parts of the wing or airplane. The operator must ensure that the airplane surfaces are free of frost, snow and ice accumulation prior to takeoff.
Page
REVISION 6
1-01-50
Code
1 02
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
CAUTION: • ON GROUND, DO NOT RELY ON VISUAL ICING EVIDENCE OR ICE DETECTOR ACTUATION TO TURN ON THE ANTI-ICING SYSTEM. USE THE TEMPERATURE AND VISUAL MOISTURE CRITERIA AS SPECIFIED ABOVE. DELAYING THE USE OF THE ANTI-ICING SYSTEM UNTIL ICE BUILD-UP IS VISIBLE FROM THE COCKPIT MAY RESULT IN ICE INGESTION AND POSSIBLE ENGINE DAMAGE OR FLAME-OUT. • DO NOT USE APU BLEED AS PNEUMATIC SOURCE FOR ANTI-ICING SYSTEM.
WINDSHIELD WIPER OPERATION (IF APPLICABLE) Maximum Airspeed for Windshield Wiper Operation ......... 170 KIAS
FLIGHT CONTROLS APPROACH AND LANDING FLAPS Flaps 45° operation is not allowed in icing conditions and after ice encounter, except for airplanes S/N 145686, 145770 and on or PostMod. SB 145LEG-27-0010.
Page
1-01-50
Code
2 02
REVISION 6
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
OXYGEN OZONE CONCENTRATION The tables below show the airplane altitude limitations due to ozone concentration in atmosphere. NOTE: - EMB-135 BJ airplanes Post-Mod. SB 145LEG-21-0007 or equipped with an equivalent modification factory incorporated are not subjected to this limitation. - These tables are based on FAA ADVISORY CIRCULAR 120.38. - The tables show altitude limitations calculated for constant ozone concentration, cabin stabilized at 8000 ft, and both recirculation fans turned on. - For conditions other than those specified in item 2 above, an optimized flight plan must be approved by regulatory agencies. - For longitudes, the following apply: W = Western E
= Eastern
Reference = 100°W longitude
Page
REVISION 7
1-01-52
Code
1 01
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
NORTH AMERICA - MAXIMUM OZONE CRITERIA FLIGHT LEVEL LATITUDE 80°N 75°N 70°N 65°N 60°N 55°N 50°N 45°N 40°N 35°N
FLIGHT LEVEL LATITUDE 80°N 75°N 70°N 65°N 60°N 55°N 50°N 45°N 40°N 35°N
1-01-52
JAN W 350 370 390 400 400 -
E 320 320 340 340 350 360 370 390 -
JUL
FEB W 330 340 370 400 360 -
AUG
W 340 340 350 360 -
E W 330 340 340 350 390 360 400 380 400 400 -
Page
Code
2 01
E 320 320 320 320 330 340 360 370 380 -
MAR W 320 330 340 360 370 370 -
E 310 320 320 320 330 340 340 360 390 -
SEP
E W 380 390 400 400 400 -
APR W 320 320 320 320 340 380 -
E 310 310 320 320 320 330 330 340 360 -
OCT
MAY W 320 320 320 330 340 400 -
E 300 310 310 320 320 320 330 360 390 -
NOV
JUN W 330 340 340 350 370 -
E 320 320 330 330 330 350 360 390 -
DEC
E W E W E W E 390 380 340 340 380 380 360 350 390 380 380 350 400 380 390 400 380 370 360 390 400 400 390 380 380 400 400 400 390 400 -
REVISION 7
LIMITATIONS
AIRPLANE OPERATIONS MANUAL NORTH AMERICA - TWA OZONE CRITERIA
NOTE: Values below are the altitude limitations which the airplane is allowed to fly more than 3 continuous hours. FLIGHT LEVEL LATITUDE 80°N 75°N 70°N 65°N 60°N 55°N 50°N 45°N 40°N 35°N 30°N 25°N 20°N
FLIGHT LEVEL LATITUDE 80°N 75°N 70°N 65°N 60°N 55°N 50°N 45°N 40°N 35°N 30°N 25°N 20°N
JAN W 310 320 330 330 330 330 370 -
E 270 270 290 290 290 290 310 310 330 350 -
JUL W 290 290 300 310 320 -
E 250 270 270 290 310 310 310 330 350 390 -
FEB W 290 310 320 350 330 310 370 -
E 250 270 270 250 270 290 290 310 310 350 -
AUG W 330 330 330 330 350 -
E 290 310 320 330 330 330 330 350 390 -
MAR W 300 300 310 310 310 310 330 -
E 250 250 260 270 290 290 290 310 310 350 390 -
SEP W 330 330 350 370 -
E 290 310 310 310 330 330 330 370 -
APR W 290 270 250 250 270 310 350 -
E 250 250 250 250 250 270 270 290 310 330 -
OCT W 320 320 330 350 370 -
E 290 290 310 310 310 330 350 350 370 -
MAY W 250 250 250 270 290 310 370 -
E 250 250 250 250 250 250 270 290 310 330 370 390 -
NOV W 330 330 330 330 350 390 -
E 290 290 290 290 290 310 330 330 350 390 -
JUN W 300 310 310 310 310 330 390 -
DEC W 310 320 330 350 350 350 -
Page
REVISION 7
1-01-52
E 250 250 270 270 270 290 310 310 330 370 400 -
E 290 290 290 300 310 310 330 330 330 370 -
Code
3 01
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
SOUTH AMERICA - MAXIMUM OZONE CRITERIA FLIGHT LEVEL LATITUDE 80°S 75°S 70°S 65°S 60°S 55°S 50°S 45°S 40°S 35°S
FLIGHT LEVEL LATITUDE 80°S 75°S 70°S 65°S 60°S 55°S 50°S 45°S 40°S 35°S
1-01-52
JAN W 340 340 350 360 -
FEB
E W 330 340 340 350 390 360 400 380 400 400 -
JUL W 350 370 390 400 400 -
E 320 320 340 340 350 360 370 390 -
Page
Code
4 01
E W 380 390 400 400 400 -
AUG W 330 340 370 400 360 -
MAR
E 320 320 320 320 330 340 360 370 380 -
MAY
JUN
E W E W E W E 390 380 340 340 380 380 360 350 390 380 380 350 400 380 390 400 380 370 360 390 400 400 390 380 380 400 400 400 390 400 -
SEP W 320 330 340 360 370 370 -
APR
E 310 320 320 320 330 340 340 360 390 -
OCT W 320 320 320 320 340 380 -
E 310 310 320 320 320 330 330 340 360 -
NOV W 320 320 320 330 340 400 -
E 300 310 310 320 320 320 330 360 390 -
DEC W 330 340 340 350 370 -
E 320 320 330 330 330 350 360 390 -
REVISION 7
LIMITATIONS
AIRPLANE OPERATIONS MANUAL SOUTH AMERICA - TWA OZONE CRITERIA
NOTE: Values below are the altitude limitations which the airplane is allowed to fly more than 3 continuous hours. FLIGHT LEVEL LATITUDE 80°S 75°S 70°S 65°S 60°S 55°S 50°S 45°S 40°S 35°S 30°S 25°S 20°S
FLIGHT LEVEL LATITUDE 80°S 75°S 70°S 65°S 60°S 55°S 50°S 45°S 40°S 35°S 30°S 25°S 20°S
JAN W 290 290 300 310 320 -
E 250 270 270 290 310 310 310 330 350 390 -
JUL W 310 320 330 330 330 330 370 -
E 270 270 290 290 290 290 310 310 330 350 -
FEB W 330 330 330 330 350 -
E 290 310 320 330 330 330 330 350 390 -
AUG W 290 310 320 350 330 310 370 -
E 250 270 270 250 270 290 290 310 310 350 -
MAR W 330 330 350 370 -
E 290 310 310 310 330 330 330 370 -
SEP W 300 300 310 310 310 310 330 -
E 250 250 260 270 290 290 290 310 310 350 390 -
APR W 320 320 330 350 370 -
E 290 290 310 310 310 330 350 350 370 -
OCT W 290 270 250 250 270 310 350 -
E 250 250 250 250 250 270 270 290 310 330 -
MAY W 330 330 330 330 350 390 -
E 290 290 290 290 290 310 330 330 350 390 -
NOV W 250 250 250 270 290 310 370 -
E 250 250 250 250 250 250 270 290 310 330 370 390 -
JUN W 310 320 330 350 350 350 -
DEC W 300 310 310 310 310 330 390 -
Page
REVISION 7
1-01-52
E 290 290 290 300 310 310 330 330 330 370 -
E 250 250 270 270 270 290 310 310 330 370 400 -
Code
5 01
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
JAPAN - MAXIMUM OZONE CRITERIA FLIGHT LEVEL LATITUDE 43°N 36°N 32°N
FLIGHT LEVEL LATITUDE 43°N 36°N 32°N
JAN
FEB
MAR
APR
MAY
JUN
350 400 -
340 -
340 380 -
350 390 -
340 -
400 -
JUL
AUG
SEP
OCT
NOV
DEC
-
-
-
-
-
380 -
JAPAN - TWA OZONE CRITERIA NOTE: Values below are the altitude limitations which the airplane is allowed to fly more than 3 continuous hours. FLIGHT LEVEL LATITUDE 43°N 36°N 32°N
FLIGHT LEVEL LATITUDE 43°N 36°N 32°N
JAN
FEB
MAR
APR
MAY
JUN
290 330 -
290 310 -
300 310 390
310 320 370
270 330 -
310 390 -
JUL
AUG
SEP
OCT
NOV
DEC
350 -
-
350 -
350 -
350 -
310 390 -
Page
1-01-52
Code
6 01
REVISION 7
LIMITATIONS
AIRPLANE OPERATIONS MANUAL AUSTRALIA - MAXIMUM OZONE CRITERIA FLIGHT LEVEL LATITUDE 43°S 36°S 32°S
FLIGHT LEVEL LATITUDE 43°S 36°S 32°S
JAN
FEB
MAR
APR
MAY
JUN
-
-
-
-
-
380 -
JUL
AUG
SEP
OCT
NOV
DEC
350 400 -
340 -
340 380 -
350 390 -
340 -
400 -
AUSTRALIA - TWA OZONE CRITERIA NOTE: Values below are the altitude limitations which the airplane is allowed to fly more than 3 continuous hours. FLIGHT LEVEL LATITUDE 43°S 36°S 32°S
FLIGHT LEVEL LATITUDE 43°S 36°S 32°S
JAN
FEB
MAR
APR
MAY
JUN
350 -
-
350 -
350 -
350 -
310 390 -
JUL
AUG
SEP
OCT
NOV
DEC
290 330 -
290 310 -
300 310 390
310 320 370
270 330 -
310 390 -
Page
REVISION 7
1-01-52
Code
7 01
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
WESTERN EUROPE - MAXIMUM OZONE CRITERIA FLIGHT LEVEL LATITUDE 52°N 47°N 39°N
FLIGHT LEVEL LATITUDE 52°N 47°N 39°N
JAN
FEB
MAR
APR
MAY
JUN
390 400 -
350 370 -
350 360 390
330 350 350
350 370 360
380 370 -
JUL
AUG
SEP
OCT
NOV
DEC
400 -
-
-
-
-
400 -
WESTERN EUROPE - TWA OZONE CRITERIA NOTE: Values below are the altitude limitations which the airplane is allowed to fly more than 3 continuous hours. FLIGHT LEVEL LATITUDE 52°N 47°N 39°N
FLIGHT LEVEL LATITUDE 52°N 47°N 39°N
JAN
FEB
MAR
APR
MAY
JUN
330 330 390
310 320 350
310 310 330
270 310 310
290 310 310
310 310 330
JUL
AUG
SEP
OCT
NOV
DEC
320 330 390
350 370 -
350 390 -
370 390 -
350 370 -
330 330 350
Page
1-01-52
Code
8 01
REVISION 7
LIMITATIONS
AIRPLANE OPERATIONS MANUAL AFRICA - MAXIMUM OZONE CRITERIA FLIGHT LEVEL LATITUDE 52°S 47°S 39°S
FLIGHT LEVEL LATITUDE 52°S 47°S 39°S
JAN
FEB
MAR
APR
MAY
JUN
400 -
-
-
-
-
400 -
JUL
AUG
SEP
OCT
NOV
DEC
390 400 -
350 370 -
350 360 390
330 350 350
350 370 360
380 370 -
AFRICA - TWA OZONE CRITERIA NOTE: Values below are the altitude limitations which the airplane is allowed to fly more than 3 continuous hours. FLIGHT LEVEL LATITUDE 52°S 47°S 39°S
FLIGHT LEVEL LATITUDE 52°S 47°S 39°S
JAN
FEB
MAR
APR
MAY
JUN
320 330 390
350 370 -
350 390 -
370 390 -
350 370 -
330 330 350
JUL
AUG
SEP
OCT
NOV
DEC
330 330 390
310 320 350
310 310 330
270 310 310
290 310 310
310 310 330
Page
REVISION 7
1-01-52
Code
9 01
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-01-52
Code
10 01
REVISION 7
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
NAVIGATION EQUIPMENT INERTIAL REFERENCE SYSTEM Airplane must not be moved until all attitude and heading information presented on PFD is valid. Alignment Limitations: - Maximum latitude for alignment ........78.25° Northern and Southern - IRS alignment will complete only after a valid aircraft present position (latitude and longitude) is received. - Time to Alignment:
ALIGNMENT TIME - minutes.....
20
15
10
5
0 0
5
10
15
20
25
30
35
40
45
50
55
60
65
70
75
80
ALIGNMENT LATITUDE - degrees Northern and Southern
Page
REVISION 5
1-01-56
Code
1 02
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
- The airplanes may not be operated within the following North and South magnetic polar cut-out regions: MAGNETIC CUT-OUT REGIONS
North
South
LATITUDE
LONGITUDE
Between 70°N and 82°N North of 82°N Between 60°S and 82°S South of 82°S
Between 90°W and 120°W Between 0° and 180°W/E Between 120°E and 160°E Between 0° and 180°W/E
NOTE: Within the magnetic polar cut-out regions IRS heading data is not available.
INSTRUMENT LANDING SYSTEM (ILS) This limitation applies to airplanes equipped with Mod. L of the Honeywell Primus II NV-850 Navigation Receiver Module P/N 7510134-831; which is part of the Honeywell Primus II RNZ-851 Integrated Navigation Unit P/N 7510100-831, -832, -833 and -834. When crossing the Outer Marker on glideslope, the altitude must be verified with the value on the published procedure. For airplanes with a single operating glideslope receiver, the approach may be flown using normal procedures no lower than Localizer Only Minimum Descent Altitude (MDA). For airplanes with two operating glideslope receivers, the airplane may be flown to the published minimums for the approach using normal procedures if both glideslope receivers are tuned to the approach and both crew members are monitoring the approach using independent data and displays.
RADAR Do not operate weather radar during refueling, near fuel spills or people.
COMMUNICATION EQUIPMENT HF -
Do not rely on ADF indications shown on PFD while transmitting in HF. Do not transmit through HF Radio during aircraft fueling. Page
1-01-56
Code
2 02
REVISION 5
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
AUTOPILOT The following limitations are applicable to the Autopilot: Minimum Engagement Height After Takeoff................. 500 ft Autopilot coupled approaches approved down to 200 ft AGL. Malfunction altitude loss: Cruise....................................................................... up to 80 ft Maneuver ................................................................. up to 100 ft ILS Approach ........................................................... 15 ft Descent below Minimum Descent Altitude on a non precision approach with autopilot engaged is prohibited. Single engine go-around with autopilot engaged is prohibited. Approach mode selection during Localizer capture is allowed only when airplane is inbound. NOTE: Coupled go-around height loss may be 40 ft. Maximum Operation Altitude with Yaw Damper Disengaged (Mach > 0.7)........................... 35000 ft
Page
REVISION 7
1-01-56
Code
3 02
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-01-56
Code
4 02
REVISION 3
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
FMZ2000 FLIGHT MANAGEMENT SYSTEM The following limitations are applicable to the FMS: - The Honeywell Flight Management System (FMS) Pilot's Operating Manual, Honeywell Publication Number A28-1146-133-00, February 1999 edition (or later revision of the manual) for the software version NZ5.2 (or later approved version) or FAA accepted Operating Manual, must be immediately available to the flight crew whenever navigation is predicated on the use of the FMS. The software status stated in the Pilot's Manual must match that displayed on the FMS Control Display Unit (CDU). - FMS instrument approaches must be accomplished in accordance with approved instrument approach procedures that are retrieved from the FMS navigation data base. The FMS data base must incorporate the current update cycle. - Use of FMS guidance for conducting instrument approach procedures is prohibited with the FMS operating in the degrade or dead-reckoning mode, (DGR or DR annunciation set on PFD). - Operation above 72° 30.0' north latitude and below 59° 30.0' south latitude is prohibited due to unreliable magnetic heading. - The pilot must review the complete transition-approach, comparing the waypoints and altitudes displayed on the FMS with those on the published procedure prior to activation to insure that the correct procedure and transition are selected. - The Flight Director must be coupled to the LNAV mode (autopilot coupled or not coupled), to accomplish GPS only approaches. - When using FMS guidance for conducting instrument approach procedures that do not include a GPS reference in the title of the published procedure, the flight crew must verify that the procedure specified navaid and associated avionics are operational. - For airplanes equipped with single FMS, when using FMS guidance for conducting instrument approach procedures, the procedure navaid must be tuned and valid, and the raw data must be displayed in the cockpit, under the following conditions: - For VOR approaches (where the procedure specified navaid is a VOR only navaid - no DME capability) and NDB approaches, without GPS (GPS failed or RAIM out of limits or unavailable). - For any instrument approach (other than a GPS stand alone approach), outside the Brazilian Airspace, with GPS as the navigation sensor.
Page
REVISION 6
1-01-60
Code
1 02
LIMITATIONS
-
-
-
-
-
-
-
AIRPLANE OPERATIONS MANUAL
ILS, LOC, LOC-BC, LDA, SDF and MLS approaches, using the FMS for guidance, are prohibited. FMS missed approaches using the CDU Mode Select Button are prohibited. When flying to an airport where GPS (non-overlay) is the intended approach, prior to dispatch, the crew is required to verify that the predictive RAIM at the destination ETA is within the approach criteria. This information (RAIM AVAILABLE), is displayed on the PREDICTIVE RAIM page, accessed via the GPS STATUS page. When the approach at the destination is based on GPS and an alternate airport is required by the applicable operating rules, the alternate must be served by an approach based on a navigation aid other than GPS. The navigation aid must be operational and the aircraft must have operational equipment capable of using that navigation aid. IFR non-precision approach approval is limited to published approaches within the Brazilian airspace. Approaches to airports in other airspace are not approved unless authorized by the appropriate governing authority. During oceanic, enroute and terminal area operation with DGR or DR annunciated on the PFD, the flight crew must verify the FMS position using VOR/DME raw data or other appropriate means. The aircraft must have other navigation equipment installed and operating, appropriate to the route of flight. IFR enroute and terminal navigation is prohibited unless the pilot verifies the currency of the data base or verifies each selected waypoint for accuracy by reference to current approved data. Operation above 72° 30.0' north latitude and below 59° 30.0' south latitude is prohibited due to unreliable magnetic heading, unless an Inertial Reference System (IRS) is installed and operating as a sensor to the FMS. The fuel flow and fuel used presented on the FMS are supplementary information only. The flight crew must use fuel information primarily from the MFD and EICAS display.
Page
1-01-60
Code
2 02
REVISION 5
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
CAT II OPERATION MINIMUM EQUIPMENT REQUIRED The performance of CAT II approaches requires that the following equipment and instruments be in proper operating conditions: − 2 Inertial Reference Systems; − 1 Yaw Damper System; − 2 Flight Director Systems; − 2 Primary Flight Displays (PFD); − Windshield Wipers or FX-302 Rain Repellent Coating application; − 2 VHF/NAV Systems; − 1 VHF/COMM System; − Both Engines; − Cat II Checklist Logic; − 1 Electrical Trim System; − 1 Radio Altimeter; − 1 Enhanced Ground Proximity Warning System (EGPWS); − 1 Air Data System (ADS); − 1 Standby Attitude Indicator; − 1 Standby Airspeed Indicator; − 1 Standby Altimeter. NOTE: CAT II operation with Autopilot engaged is to be performed by the pilot who has the Flight Director coupled to the Autopilot.
Page
REVISION 3
1-01-65
Code
1 01
LIMITATIONS
AIRPLANE OPERATIONS MANUAL
AUTOPILOT SYSTEM Minimum Decision Height (DH) .....................................100 ft NOTE:
Although the radio altitude setting may be adjusted down to 80 ft, if requested by an ILS CAT II Approved Chart, the Decision Height (DH) is limited to 100 ft above ground level.
Minimum Use Height (MUH) .........................................50 ft Runway Visual Range (RVR) ........................................365 m (1200 ft) Maximum Tailwind.........................................................10 kt Maximum Crosswind .....................................................25 kt NOTE: Coupled go-around height loss may be 40 ft.
APPROACH AND LANDING FLAPS CAT II approach and landing must be performed with flaps 22°.
Page
1-01-65
Code
2 01
REVISION 5
LOADING
AIRPLANE OPERATIONS MANUAL
SECTION 1-07 LOADING TABLE OF CONTENTS Page Block Introduction ................................................................................ 1-07-00 External Dimensions .................................................................. 1-07-10 Cabin Cross Section .................................................................. 1-07-20 Interior Arrangement .................................................................. 1-07-30 Carry-on Baggage...................................................................... 1-07-40 Baggage Door ............................................................................ 1-07-50 Baggage Compartment.............................................................. 1-07-60 Cargo Nets ................................................................................. 1-07-70 Live Animals Transportation ...................................................... 1-07-80
Page
NOVEMBER 30, 2001
1-07-00
Code
1 01
LOADING
AIRPLANE OPERATIONS MANUAL
INTRODUCTION This Section contains airplane dimensions, interior arrangement data for loading purposes and loading capacity information in the passenger cabin and baggage compartment. Instructions for loading and unloading the airplane and live animals transportation are also included in this Section.
Page
1-07-00
Code
2 01
NOVEMBER 30, 2001
LOADING
AIRPLANE OPERATIONS MANUAL
EXTERNAL DIMENSIONS EMB-135BJ THREE VIEW DRAWING
Page
NOVEMBER 30, 2001
1-07-10
Code
1 01
LOADING
AIRPLANE OPERATIONS MANUAL
EMB-135BJ GROUND CLEARANCES
Vertical Clearance Fuselage Angle Main Door Main Door Open (1st step) Main Landing Gear Door Nacelle Baggage Door Tail Boom Wing Tip Tailskid Angular Clearance
Page
1-07-10
Maximum
Minimum
1°6´25”
0°51´32”
1.64 m 5 ft 5 in 0.48 m 1 ft 7 in 0.27 m 11 in 2.39 m 7 ft 10 in 1.73 m 5 ft 8 in 6.71 m 22 ft 3 in 3.51 m 11 ft 6 in
1.59 m 5 ft 3 in 0.38 m 1 ft 3 in 0.15 m 6 in 2.27 m 7 ft 5 in 1.63 m 5 ft 4 in 6.59 m 21 ft 7 in 3.40 m 11 ft 2 in
15°54’49”
14°56’46”
Code
2 01
NOVEMBER 30, 2001
LOADING
AIRPLANE OPERATIONS MANUAL
EMB-135BJ DOOR CLEARANCES
Page
NOVEMBER 30, 2001
1-07-10
Code
3 01
LOADING
AIRPLANE OPERATIONS MANUAL
EMB-135BJ DOOR CLEARANCES
Page
1-07-10
Code
4 01
NOVEMBER 30, 2001
LOADING
AIRPLANE OPERATIONS MANUAL
CABIN CROSS SECTION
Page
NOVEMBER 30, 2001
1-07-20
Code
1 01
LOADING
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALY
Page
1-07-20
Code
2 01
NOVEMBER 30, 2001
LOADING
AIRPLANE OPERATIONS MANUAL
INTERIOR ARRANGEMENT EMB-135BJ CONFIGURATION OPTION 1
13 seats
Page
NOVEMBER 30, 2001
1-07-30
Code
1 01
LOADING
AIRPLANE OPERATIONS MANUAL
EMB-135BJ CONFIGURATION OPTION 1 SEATS ROW 1 2 3 4 5 6 7 8 9 10
PASSENGER SEATS 1, 2 3 4 5, 6 7, 8 9 10 11 12 13
BALANCE ARM (m) (in) 7.503 295.39 9.135 359.65 9.272 365.04 10.380 408.66 12.070 475.20 13.908 547.56 14.100 555.12 14.813 583.19 15.499 610.20 15.636 615.59
PASSENGER AVERAGE CG: 11.713 m / 461.14 in.
Balance Arm m (in) GALLEY
5.360 (211.02)
LH FWD CLOSET
6.415 (252.56)
RH FWD CLOSET
6.270 (246.85)
LH CLOSET
6.895 (271.46)
RH CLOSET
6.895 (271.46)
CREDENZA
11.741 (462.24)
BAGGAGE COMPARTMENT
18.570 (731.10)
Page
1-07-30
Code
2 01
JUNE 20, 2002
LOADING
AIRPLANE OPERATIONS MANUAL
EMB-135BJ CONFIGURATION OPTION 2
15 seats
Page
JUNE 20, 2002
1-07-30
Code
3 01
LOADING
AIRPLANE OPERATIONS MANUAL
EMB-135BJ CONFIGURATION OPTION 2 SEATS ROW 1 2 3 4 5 6 7 8 9 10 11 12
PASSENGER SEATS 1, 2 3 4 5, 6 7, 8 9 10 11 12 13 14 15
BALANCE ARM (m) (in) 7.120 280.31 8.754 344.65 8.809 346.81 9.830 387.01 11.490 452.36 12.283 483.58 13.020 512.60 13.897 547.13 14.116 555.75 14.773 581.61 15.539 611.77 15.730 619.29
PASSENGER AVERAGE CG: 11.587 m / 456.18 in.
Balance Arm m (in) GALLEY
5.360 (211.02)
RH FWD CLOSET
6.270 (246.85)
LH FWD CLOSET
6.415 (252.56)
CREDENZA
10.669 (420.04)
BAGGAGE COMPARTMENT
18.570 (731.10)
Page
1-07-30
Code
4 01
JUNE 20, 2002
LOADING
AIRPLANE OPERATIONS MANUAL
EMB-135BJ CONFIGURATION OPTION 3
12 seats
Page
JUNE 20, 2002
1-07-30
Code
5 01
LOADING
AIRPLANE OPERATIONS MANUAL
EMB-135BJ CONFIGURATION OPTION 3 SEATS ROW 1 2 3 4 5 6 7 8 9 10
PASSENGER SEATS 1, 2 3, 4 5 6 7 8 9 10 11 12
BALANCE ARM (m) (in) 7.503 295.39 9.068 357.01 9.830 387.01 10.712 421.73 13.020 512.60 13.920 548.03 14.105 555.31 14.821 583.50 15.537 611.69 15.643 615.87
PASSENGER AVERAGE CG: 11.728 m / 461.71 in.
Balance Arm m (in) GALLEY
5.360 (211.02)
RH FWD CLOSET
6.270 (246.85)
LH FWD CLOSET
6.415 (252.56)
LH CLOSET
6.895 (271.46)
RH CLOSET
6.895 (271.46)
CREDENZA
11.454 (450.94)
BAGGAGE COMPARTMENT
18.570 (731.10)
Page
1-07-30
Code
6 01
JUNE 20, 2002
LOADING
AIRPLANE OPERATIONS MANUAL
EMB-135BJ CONFIGURATION OPTION 4
14 seats
Page
REVISION 4
1-07-30
Code
7 01
LOADING
AIRPLANE OPERATIONS MANUAL
EMB-135BJ CONFIGURATION OPTION 4 SEATS ROW 1 2 3 4 5 6 7
PASSENGER SEATS 1, 2 3, 4 5, 6 7, 8 9, 10 11, 12 13, 14
BALANCE ARM (m) (in) 7.409 291.7 9.040 355.9 10.030 394.9 11.021 433.9 11.986 471.9 13.734 540.7 15.359 604.7
PASSENGER AVERAGE CG: 10.464 m / 441.96 in.
Balance Arm m (in) GALLEY
5.801 (228.4)
RH FWD CLOSET
6.270 (246.85)
LH FWD CLOSET
6.505 (256.1)
BAGGAGE COMPARTMENT
18.570 (731.10)
Page
1-07-30
Code
8 01
REVISION 4
LOADING
AIRPLANE OPERATIONS MANUAL
EMB-135BJ CONFIGURATION OPTION 5
13 seats
Page
REVISION 4
1-07-30
Code
9 01
LOADING
AIRPLANE OPERATIONS MANUAL
EMB-135BJ CONFIGURATION OPTION 5 SEATS ROW 1 2 3 4 5 6 7 8 9
PASSENGER SEATS 1, 2 3, 4 5, 6 7, 8 9 10 11 12 13
BALANCE ARM (m) (in) 7.539 296.80 8.947 352.24 10.485 412.80 11.908 468.80 13.863 545.80 13.990 550.79 14.702 578.82 15.413 606.81 15.235 599.80
PASSENGER AVERAGE CG: 11.612 m / 457.17 in.
Balance Arm m (in) GALLEY
5.846 (230.16)
ENTERTAINMENT COMPARTMENT RACK
5.796 (228.21)
FWD LAVATORY
6.519 (256.65)
CREDENZA
11.195 (440.74)
BAGGAGE COMPARTMENT
18.570 (731.10)
Page
1-07-30
Code
10 01
REVISION 6
LOADING
AIRPLANE OPERATIONS MANUAL
EMB-135BJ CONFIGURATION OPTION 6
13 seats
Page
REVISION 4
1-07-30
Code
11 01
LOADING
AIRPLANE OPERATIONS MANUAL
EMB-135BJ CONFIGURATION OPTION 6 SEATS ROW 1 2 3 4 5 6 7 8 9
PASSENGER SEATS 1, 2 3, 4 5, 6 7, 8 9 10 11 12 13
BALANCE ARM (m) (in) 7.539 296.80 8.947 352.24 10.485 412.80 11.908 468.80 13.863 545.80 13.990 550.79 14.702 578.82 15.413 606.81 15.235 599.80
PASSENGER AVERAGE CG: 11.612 m / 457.17 in.
Balance Arm m (in) GALLEY
5.846 (230.16)
ENTERTAINMENT COMPARTMENT RACK
5.796 (228.21)
FWD CLOSET
6.519 (256.65)
CREDENZA
11.195 (440.74)
BAGGAGE COMPARTMENT
18.570 (731.10)
Page
1-07-30
Code
12 01
REVISION 6
LOADING
AIRPLANE OPERATIONS MANUAL
CARRY-ON BAGGAGE Carry-on volumes may be stowed in the available furniture compartments as closets, wardrobes and stowage compartments, when existing. There is no specific requirement for underseat carry-on volumes; however a maximum of 9.0 kg (20.0 lb) is allowable, provided the volume is properly restrained to avoid sliding.
Page
NOVEMBER 30, 2001
1-07-40
Code
1 01
LOADING
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-07-40
Code
2 01
NOVEMBER 30, 2001
LOADING
AIRPLANE OPERATIONS MANUAL
BAGGAGE DOOR The baggage door, located on the rear left side of the fuselage, is 1.00 meter (39.4 in) wide and 1.11 meters (43.7 in) high. The baggage door is manually operated from the outside. The initial opening movement (displacement of the door inward) and final closing and latching movement (displacement of the door outward) are achieved by means of a door locking mechanism controlled by an external handle which is stowed in the lower half of the door.
Page
NOVEMBER 30, 2001
1-07-50
Code
1 01
LOADING
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-07-50
Code
2 01
NOVEMBER 30, 2001
LOADING
AIRPLANE OPERATIONS MANUAL
BAGGAGE COMPARTMENT DESCRIPTION The baggage compartment is located in the rear part of the fuselage. The EMB-135BJ is fitted with a “class-C” baggage compartment. Airplanes with the “class-C” baggage compartment have the following systems installed: • Baggage Compartment Smoke Detection System. • Baggage Compartment Fire Extinguishing System. • Baggage Compartment Ventilation System. Although no dedicated temperature control is available (the “class-C” baggage compartment is heated by passenger cabin air flowing into it), the baggage ventilation system provides an adequate environment for carrying live animals in the compartment. The following cargo nets may be installed in the baggage compartment: • One Baggage Door Anti-Blockage Barrier. • One Cargo Arresting Net (vertical restraint).
EMB-135 BJ BAGGAGE COMPARTMENT LIMITS 3
Baggage Compartment Available Volume .................. 6.8 m (240 cu.ft) 2 2 Maximum Floor Distributed Load .......................... 390 Kg/m (80 lb/ft ) Total Maximum Capacity ............................................. 454 Kg (1000 lb)
Page
JUNE 20, 2002
1-07-60
Code
1 01
LOADING
AIRPLANE OPERATIONS MANUAL
BAGGAGE COMPARTMENT ACCESS DOOR The Baggage Compartment Access Door is installed in the aft lavatory bulkhead which separates the passenger cabin from the baggage compartment. The door has a peephole (one way into the baggage area) and a latch mechanism which allows to be opened from within the baggage compartment.
Page
1-07-60
Code
2 01
NOVEMBER 30, 2001
LOADING
AIRPLANE OPERATIONS MANUAL
BAGGAGE AND CARGO LOADING Baggage and cargo should be equally distributed in the baggage compartment to avoid load concentration. High density volumes must be tied down, unless the floor distributed 2 2 load is less than 125 Kg/m (25.6 lb/ft ). Volumes with sharp edges should be fixed to the floor or conveniently protected to prevent vertical and lateral movements, in order to prevent structural damages. To load the baggage compartment with the maximum capacity of 454 kg, no more than two person can be at the airplane cone, one inside the baggage compartment and the other inside the rear electronic compartment. CAUTION: IF THE CONDITIONS ABOVE ARE NOT OBSERVED, AIRPLANE TILTING (TAIL DOWN) MAY OCCUR. Before loading or unloading the baggage compartment, the Cargo Loading/Unloading Ramp (also known as Door Jamb Barrier) must be lowered in order to protect the baggage door latching mechanism.
Page
NOVEMBER 30, 2001
1-07-60
Code
3 01
LOADING
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-07-60
Code
4 01
NOVEMBER 30, 2001
LOADING
AIRPLANE OPERATIONS MANUAL
CARGO NETS BAGGAGE DOOR ANTI-BLOCKAGE BARRIER The anti-blockage barrier net secures the baggage and prevents the cargo door from jamming when this is in the closed position (the door slides inboard before opening upward). The net attaches to two pulley assemblies which attach to the net beam assembly. The net beam assembly is attached to an upper attach bracket. A cargo net adapter attaches the cargo door safety net to the upper attach bracket. Decals on the net assembly indicate orientation (FWD, AFT, UPSIDE, or RH/LH). Straps on the cargo safety net attach to anchor plates on the cargo loading/unloading ramp (door jamb barrier). The cargo door safety net is held to the cargo compartment floor by six anchor plates tiedown fittings. Two shock lanyard assemblies extend the door jamb barrier assembly when the baggage door is opened.
Page
NOVEMBER 30, 2001
1-07-70
Code
1 01
LOADING
AIRPLANE OPERATIONS MANUAL
ANTI-BLOCKAGE BARRIER NET INSTALLATION Page
1-07-70
Code
2 01
NOVEMBER 30, 2001
LOADING
AIRPLANE OPERATIONS MANUAL
ANTI-BLOCKAGE BARRIER NET INSTALLATION
Page
NOVEMBER 30, 2001
1-07-70
Code
3 01
LOADING
AIRPLANE OPERATIONS MANUAL
CARGO ARRESTING NET The cargo arresting net (tie-down) provides vertical restraint to the baggage and cargo. It is attached to the cargo compartment floor by means of five anchor plates. Adjustable straps and pigtails allow the cargo arresting net to extend and retract. Decals on the cargo net assembly indicate orientation (FWD, AFT, UPSIDE, or RH/LH) of the net in the cargo compartment.
Page
1-07-70
Code
4 01
NOVEMBER 30, 2001
LOADING
AIRPLANE OPERATIONS MANUAL
LIVE ANIMALS TRANSPORTATION This section presents the general conditions for live animal transportation in the EMB-135BJ Class C Baggage Compartment. The main references that regulates and states methods and procedures to handling, appropriate packaging, legal aspects for animal transportation, etc. are the IATA Live Animal Regulations and SAE AIR1600. GENERAL RECOMMENDATIONS Generically, animals should be protected from stressing situations, like excessive noise, solar radiation, draft, high or low temperatures. The containers should be appropriate for the type of animal to be transported, as recommended by IATA Live Animal Regulations. Animals shall be handled with great care, to minimize the stress associated to handling. While waiting for the shipment, animals should be maintained in a waiting room with temperature control and protected from noise and draught. The adverse climatic conditions could cause additional stress to the animals. The ambient should be dark to make the animals more calm and comfortable while waiting for shipment. Animals of different species, specially which are natural enemies, such as cats and dogs, must be kept apart one from another. On the other hand, animals of the same species would be more calm if kept together. Animals shall be loaded just before departure and unloaded just after arrival, in order to minimize the exposition to high or low temperatures on ground, where the baggage compartment ventilation is not completely effective. Specially in the hot season, it should be preferable to schedule the animal shipment for the night period, when the temperatures are lower than during the day. For the more sensitive animals, such as little birds, that would not resist to high temperatures, this is an important requirement. In addition, these animals would be too susceptible to low temperatures achieved during long cruise flights, so it could be necessary to limit the flight cruise altitude to reduce the temperature drop in the baggage compartment and protect them. The containers should not be placed near the compartment floor, in order to isolate the animals from low temperatures in that region. The recommendations for animal load limitations should be observed, in order to prevent animals being exposed to adverse environmental conditions. Page
NOVEMBER 30, 2001
1-07-80
Code
1 01
LOADING
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-07-80
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
TABLE OF CONTENTS INTRODUCTION DOCUMENT PURPOSE.................................................. 1-09-02 ....01 PREAMBLE...................................................................... 1-09-02 ....03 DEFINITIONS AND SYMBOLOGY.................................. 1-09-02 ....05 ATA Chapter 21 - AIR CONDITIONING EXTERNAL GROUND CONNECTOR CHECK VALVE ................................................................ 1-09-21 ....01 BAGGAGE COMPARTMENT VENTILATION SYSTEM.................................................. 1-09-21 ....02 GASPER FAN .................................................................. 1-09-21 ....03 RECIRCULATION FANS ................................................. 1-09-21 ....04 RECIRCULATION FAN VALVES..................................... 1-09-21 ....05 AIR DISTRIBUTION VALVES.......................................... 1-09-21 ....06 RAM AIR VALVES ........................................................... 1-09-21 ....07 RAM AIR CHECK VALVES.............................................. 1-09-21 ....09 FORWARD ELECTRONIC COMPARTMENT VENTILATION SYSTEM.................................................. 1-09-21 ....10 PRESSURIZATION CONTROL SYSTEM ....................... 1-09-21 ....11 OUTFLOW VALVES ........................................................ 1-09-21 ....13 CABIN PRESSURE ACQUISITION MODULE (CPAM)... 1-09-21 ....20 AIR CONDITIONING PACK SYSTEMS .......................... 1-09-21 ....22 COCKPIT AND CABIN AUTOMATIC TEMPERATURE CONTROL SYSTEMS ......................... 1-09-21 ....23 COCKPIT AND CABIN MANUAL TEMPERATURE CONTROL SYSTEMS ......................... 1-09-21 ....24 ATTENDANT’S (GALLEY) TEMPERATURE CONTROL ........................................... 1-09-21 ....24 COCKPIT AND CABIN TEMPERATURE INDICATION SYSTEMS .................................................. 1-09-21 ....25
Page
REVISION 6
1-09-00
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL ATA Chapter 22 - AUTOFLIGHT
AUTOPILOT/FLIGHT DIRECTOR FUNCTIONS .............1-09-22.... 01 FLIGHT GUIDANCE CONTROLLER PANEL ..................1-09-22.... 02 TOUCH CONTROL STEERING BUTTON (TCS SYNC BUTTONS)...................................................1-09-22.... 03 GO-AROUND BUTTONS.................................................1-09-22.... 04 ATA Chapter 23 - COMMUNICATIONS COMMUNICATION SYSTEMS (VHF, HF, UHF) .............1-09-23.... 01 ACARS SYSTEM .............................................................1-09-23.... 02 SELECTIVE CALL SYSTEM (SELCAL)...........................1-09-23.... 03 PASSENGER ADDRESS SYSTEM .................................1-09-23.... 04 ALERTING SYSTEMS (AUDIO/VISUAL).........................1-09-23.... 05 PRE-RECORDED PASSENGER ANNOUNCEMENT SYSTEM...........................................1-09-23.... 07 PASSENGER CABIN/LAVATORY SPEAKERS...............1-09-23.... 08 PUSH TO TALK (PTT) (BUTTON ON GLARESHIELD PANEL CONTROL WHEEL)..................1-09-23.... 09 FLIGHT DECK SPEAKERS .............................................1-09-23.... 09 FLIGHT DECK HANDHELD MICROPHONES.................1-09-23.... 10 BOOM MICROPHONES ..................................................1-09-23.... 11 FLIGHTDECK DOOR MONITORING SYSTEM ..............1-09-23.... 12 COCKPIT VOICE RECORDER SYSTEM........................1-09-23.... 13 RADIO MANAGEMENT UNITS (RMU’S).........................1-09-23.... 13 TUNING BACKUP CONTROL HEAD ..............................1-09-23.... 14 ATA Chapter 24 - ELECTRICAL POWER GENERATOR CURRENT INDICATIONS........................1-09-24.... 01 GENERATOR VOLTAGE INDICATIONS ........................1-09-24.... 01 INVERTER .......................................................................1-09-24.... 02 ENGINE DRIVEN GENERATORS...................................1-09-24.... 03 ENGINE DRIVEN GENERATOR BEARINGS (ONLY FOR GENERATOR MODEL 30086-11)...............1-09-24.... 05 APU STARTER GENERATOR ........................................1-09-24.... 06 EXTERNAL POWER SYSTEM........................................1-09-24.... 06
Page
1-09-00
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA Chapter 25 - EQUIPMENT AND FURNISHINGS EYE LOCATOR................................................................ 1-09-25 ....01 FLIGHT CREW SEATS ................................................... 1-09-25 ....01 PRIMARY OBSERVER SEAT (INCLUDING ASSOCIATED EQUIPMENT) .......................................... 1-09-25 ....03 FLIGHT ATTENDANT SEAT ASSEMBLY (SINGLE OR DUAL POSITION) ...................................... 1-09-25 ....05 SUNVISORS .................................................................... 1-09-25 ....07 COCKPIT CONVENIENCE ITEM(S) ............................... 1-09-25 ....07 LIGHTED/MECHANICAL CHECKLIST............................ 1-09-25 ....08 CHART HOLDERS .......................................................... 1-09-25 ....08 PASSENGER SEATS AND BELTS................................. 1-09-25 ....09 INTERNAL BAGGAGE ACCESS DOOR......................... 1-09-25 ....10 LAVATORY BULKHEAD PEEPHOLE ............................. 1-09-25 ....11 GALLEY WASTE RECEPTACLES ACCESS DOORS/COVERS............................................................ 1-09-25 ....12 EXTERIOR LAVATORY DOOR ASHTRAYS .................. 1-09-25 ....13 CARGO RESTRAINT SYSTEMS .................................... 1-09-25 ....14 PASSENGER CONVENIENCE ITEM(S) ......................... 1-09-25 ....15 FLIGHT DECK/ATTENDANT FLASHLIGHT AND HOLDER ASSEMBLIES................... 1-09-25 ....16 PYROTECHNIC SIGNAL DEVICES ................................ 1-09-25 ....16 EMERGENCY MEDICAL EQUIPMENT (INCLUDING EMERGENCY MEDICAL KIT, FIRST AID KIT AND AUTOMATED EXTERNAL DEFIBRILLATOR ................. 1-09-25 ....17 "FASTEN SEAT BELTS WHILE SEATED" SIGN OR PLACARD ........................................................ 1-09-25 ....17 EMERGENCY LOCATOR TRANSMITTER (ELT)........... 1-09-25 ....18 FLOTATION EQUIPMENT (CREW AND PASSENGER)............................................ 1-09-25 ....18
Page
REVISION 6
1-09-00
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
ATA Chapter 26 - FIRE PROTECTION APU FIRE DETECTION SYSTEM ...................................1-09-26.... 01 LAVATORY SMOKE DETECTION SYSTEM...................1-09-26.... 02 BAGGAGE COMPARTMENT SMOKE DETECTION SYSTEM.....................................................1-09-26.... 03 E1 (OR 2) EXTBTLA (OR B) INOP CAUTION MESSAGES ....................................................1-09-26.... 04 APU FIRE EXTINGUISHING SYSTEM............................1-09-26.... 06 APU EXTBTL INOP CAUTION MESSAGE .....................1-09-26.... 06 BAGGAGE COMPARTMENT FIRE EXTINGUISHER SYSTEM...............................................1-09-26.... 07 PORTABLE FIRE EXTINGUISHERS...............................1-09-26.... 08 LAVATORY FIRE EXTINGUISHER SYSTEMS...............1-09-26.... 09 GALLEY FIRE EXTINGUISHER SYSTEM ......................1-09-26.... 10 ATA Chapter 27 - FLIGHT CONTROLS AILERON DAMPERS .......................................................1-09-27.... 01 ROLL TRIM POSITION INDICATION ..............................1-09-27.... 02 AILERON DISCONNECTION LIGHT...............................1-09-27.... 03 PEDALS ADJUSTMENT MECHANISM ...........................1-09-27.... 04 YAW TRIM POSITION INDICATIONS.............................1-09-27.... 06 ELEVATOR DISCONNECTION LIGHT ...........................1-09-27.... 07 SPS/ICE SPEEDS ADVISORY MESSAGE .....................1-09-27.... 08 STICK SHAKERS.............................................................1-09-27.... 08 PITCH TRIM POSITION INDICATION.............................1-09-27.... 09 FLAP CHANNELS ............................................................1-09-27.... 10 GUST LOCK SYSTEM.....................................................1-09-27.... 12
Page
1-09-00
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA Chapter 28 - FUEL SUMP DRAIN VALVES.................................................... 1-09-28 ....01 FUELING RECEPTACLE CAP ........................................ 1-09-28 ....02 WING TANK ELECTRIC FUEL BOOSTER PUMPS.......................................................... 1-09-28 ....03 WING TANK ELECTRIC FUEL BOOSTER PUMP OPERATING INDICATIONS ................................ 1-09-28 ....05 FORWARD AUXILIARY TANK ELECTRIC FUEL TRANSFER PUMPS.............................................. 1-09-28 ....06 FORWARD AUXILIARY TANK ELECTRIC FUEL TRANSFER PUMPS OPERATING INDICATIONS ......... 1-09-28 ....09 AFT AUXILIARY TANK ELECTRIC FUEL TRANSFER PUMPS ........................................................ 1-09-28 ....11 AFT AUXILIARY TANK ELECTRIC FUEL TRANSFER OPERATING INDICATIONS............................................ 1-09-28 ....13 AFT AUXILIARY TANK PRESSURIZED FUEL TRANSFER SYSTEMS ......................................... 1-09-28 ....15 AFT AUXILIARY TANK PRESSURIZED FUEL TRANSFER SYSTEM OPERATING INDICATIONS ....... 1-09-28 ....17 FORWARD AUXILIARY TANK PRESSURIZED FUEL TRANSFER SYSTEM OPERATING INDICATIONS .................................................................. 1-09-28 ....20 AFT AUXILIARY TANK FUEL TRANSFER OPERATING INDICATIONS............................................ 1-09-28 ....21 APU FUEL SHUTOFF VALVE ......................................... 1-09-28 ....22 PRESSURE DEFUELING/REFUELING SYSTEM .......... 1-09-28 ....24 DEFUELING SHUTOFF VALVE(S) ................................. 1-09-28 ....30 FUEL QUANTITY INDICATOR (REFUELING PANEL) ..................................................... 1-09-28 ....31 WING TANK FUEL QUANTITY INDICATIONS (EICAS AND MFD) .................................. 1-09-28 ....32 FORWARD AUXILIARY TANK FUEL QUANTITY INDICATIONS (EICAS AND MFD) .................................. 1-09-28 ....33 AFT AUXILIARY TANK FUEL QUANTITY INDICATIONS (EICAS AND MFD) .................................. 1-09-28 ....34
Page
REVISION 6
1-09-00
Code
5 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
DIRECT QUANTITY MEASURING STICKS....................1-09-28.... 34 FUEL TANK TEMPERATURE INDICATION SYSTEM.....................................................1-09-28.... 35 FUEL 1 (OR 2) LO LEVEL MESSAGES ..........................1-09-28.... 35 E1 (OR E2) FUEL LO PRESS MESSAGES ....................1-09-28.... 36 APU FUEL LOW PRESS SWITCH..................................1-09-28.... 37 FUEL XFER INOP MESSAGE .........................................1-09-28.... 38 AFT AUXILIARY TANK RELIEF VALVES........................1-09-28.... 40 FUSELAGE FUEL IMB MESSAGE..................................1-09-28.... 41 CHECK ACFT LOAD MESSAGE.....................................1-09-28.... 45 AFT AUXILIARY TANK TRANSFER ISOLATION VALVES .......................................................1-09-28.... 46 FORWARD AUXILIARY TANK REFUELING ISOLATION VALVE..........................................................1-09-28.... 49 AFT AUXILIARY TANK REFUELING ISOLATION VALVE..........................................................1-09-28.... 50 FORWARD AUXILIARY TANK REFUELING VENTILATION ELECTRICAL SHUTOFF VALVES............................................................................1-09-28.... 51 CROSS TRANSFER SHUTOFF VALVE ..............................................................................1-09-28.... 52 ATA Chapter 29 - HYDRAULIC POWER GSE COUPLINGS (EXTERNAL) .....................................1-09-29.... 01 ELECTRIC HYDRAULIC PUMP SYSTEMS ....................1-09-29.... 04 RESERVOIR REFILLING CHECK VALVES ....................1-09-29.... 06 PRESSURE GROUND CONNECTION CHECK VALVES ..............................................................1-09-29.... 08 HYDRAULIC FLUID QUANTITY INDICATIONS (INCLUDING LOW LEVEL WARNING) ...........................1-09-29.... 10 RESERVOIR QUANTITY GAGES ...................................1-09-29.... 12 HYDRAULIC PRESSURE INDICATIONS........................1-09-29.... 14
Page
1-09-00
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA Chapter 30 - ICE AND RAIN PROTECTION WING ANTI-ICING SYSTEM........................................... 1-09-30 ....01 WING ANTI-ICING VALVES............................................ 1-09-30 ....01 WING ANTI-ICING VALVE OPEN LIGHT ....................... 1-09-30 ....05 STABILIZER ANTI-ICING SYSTEM ................................ 1-09-30 ....05 STABILIZER ANTI-ICING VALVE ................................... 1-09-30 ....06 STABILIZER ANTI-ICING VALVE OPEN LIGHT............. 1-09-30 ....06 ENGINE ANTI-ICING SYSTEMS..................................... 1-09-30 ....07 ENGINE ANTI-ICING VALVES ........................................ 1-09-30 ....09 ENGINE ANTI-ICING VALVE OPEN LIGHT ................... 1-09-30 ....12 PITOT PROBE HEATING SYSTEMS.............................. 1-09-30 ....13 AOA SENSOR HEATING SYSTEMS .............................. 1-09-30 ....13 TAT PROBE HEATING SYSTEMS ................................. 1-09-30 ....14 WINDSHIELD WIPERS ................................................... 1-09-30 ....15 WINDSHIELD HEATING SYSTEMS ............................... 1-09-30 ....16 ICE DETECTORS............................................................ 1-09-30 ....16 CLEAR ICE DETECTOR SYSTEM (EMB-135BJ)........... 1-09-30 ....17 CLEAR ICE INDICATION LAMPS (EMB-135BJ) ............ 1-09-30 ....18 ATA Chapter 31 - INDICATING/RECORDING SYSTEMS CLOCKS .......................................................................... 1-09-31 ....01 FLIGHT DATA RECORDER (FDR) SYSTEM ................. 1-09-31 ....02 INTEGRATED COMPUTER CONFIGURATION MODULES (IM-600)......................................................... 1-09-31 ....03 AURAL WARNING UNIT ................................................. 1-09-31 ....04 MASTER WARNING LIGHTS/BUTTONS ....................... 1-09-31 ....04 MASTER CAUTION LIGHTS/BUTTONS ........................ 1-09-31 ....05
Page
REVISION 6
1-09-00
Code
7 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL ATA Chapter 32 - LANDING GEAR
LANDING GEAR CONTROL LEVER LATCH SYSTEM..............................................................1-09-32.... 01 BRAKE TEMPERATURE INDICATIONS.........................1-09-32.... 02 BRAKE PRESSURE TRANSDUCERS ............................1-09-32.... 04 ACCUMULATOR LOW PRESSURE SWITCH ................1-09-32.... 05 BRAKE ON LIGHTS.........................................................1-09-32.... 06 EXTERNAL STEERING DISENGAGEMENT SWITCH ...........................................................................1-09-32.... 07 CONTROL WHEEL STEERING DISENGAGE BUTTONS ........................................................................1-09-32.... 08 LANDING GEAR PROXIMITY SWITCHES .....................1-09-32.... 09 ATA Chapter 33 - LIGHTS COCKPIT/FLIGHT DECK/FLIGHT COMPARTMENT AND INSTRUMENT PANEL LIGHTING SYSTEMS ........1-09-33.... 01 CABIN INTERIOR ILLUMINATION SYSTEM ..................1-09-33.... 02 COCKPIT STERILE LIGHT..............................................1-09-33.... 04 PASSENGER SIGNS .......................................................1-09-33.... 05 COURTESY AND STAIRS LIGHTING SYSTEM .............1-09-33.... 06 COMPARTMENT LIGHTS (NOSE, TAIL, ETC)...............1-09-33.... 06 LANDING LIGHTS ...........................................................1-09-33.... 07 TAXI LIGHT......................................................................1-09-33.... 07 NAVIGATION LIGHTS .....................................................1-09-33.... 08 WING INSPECTION LIGHTS ..........................................1-09-33.... 10 LOGO LIGHTS .................................................................1-09-33.... 10 STROBE LIGHTS.............................................................1-09-33.... 11 RED BEACON LIGHTS....................................................1-09-33.... 12 BAGGAGE DOOR EXTERNAL LIGHT............................1-09-33.... 13 EMERGENCY LIGHTING SYSTEM (BATTERY POWERED)...................................................1-09-33.... 13 PHOTOLUMINESCENT FLOOR PROXIMITY EMERGENCY ESCAPE PATH MARKING SYSTEM.......1-09-33.... 14
Page
1-09-00
Code
8 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA Chapter 34 - NAVIGATION MAIN PANEL DISPLAYS ................................................. 1-09-34 ....01 TAT INDICATION ............................................................ 1-09-34 ....02 SAT INDICATION ............................................................ 1-09-34 ....02 STANDBY ATTITUDE INDICATION (ON INTEGRATED STANDBY INSTRUMENT (ISIS) OR ON DEDICATED INSTRUMENT) ................... 1-09-34 ....03 HEAD-UP GUIDANCE SYSTEM (HGS) .......................... 1-09-34 ....04 STANDBY MAGNETIC COMPASS ................................. 1-09-34 ....05 INERTIAL REFERENCE SYSTEM (IRS)......................... 1-09-34 ....06 RADIO ALTIMETER SYSTEM......................................... 1-09-34 ....07 ALTITUDE ALERTER FUNCTION .................................. 1-09-34 ....09 ALTITUDE PRESELECT FUNTION ................................ 1-09-34 ....10 VOR/ILS SYSTEM ........................................................... 1-09-34 ....11 GROUND PROXIMITY WARNING SYSTEM (GPWS) OR ENHANCED GPWS (EGPWS) ................................. 1-09-34 ....12 WEATHER RADAR SYSTEM.......................................... 1-09-34 ....16 STORMSCOPE................................................................ 1-09-34 ....17 TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM .......................................................................... 1-09-34 ....18 DISTANCE MEASURING EQUIPMENT (DME) SYSTEMS ........................................................................ 1-09-34 ....20 ATC TRANSPONDERS AND AUTOMATIC ALTITUDE REPORTING SYSTEMS ............................... 1-09-34 ....21 ADF SYSTEM .................................................................. 1-09-34 ....21 GLOBAL POSITIONING SYSTEM .................................. 1-09-34 ....22 FLIGHT MANAGEMENT SYSTEM.................................. 1-09-34 ....23 ATA Chapter 35 - OXYGEN OXYGEN PRESSURE INDICATION SYSTEMS ............. 1-09-35 ....01 PASSENGER OXYGEN SYSTEM................................... 1-09-35 ....02 PORTABLE OXYGEN UNITS (BOTTLE AND MASK) ..................................................... 1-09-35 ....04 PROTECTIVE BREATHING EQUIPMENT (PBE) ........... 1-09-35 ....05
Page
REVISION 6
1-09-00
Code
9 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL ATA Chapter 36 - PNEUMATIC
ENGINE BLEED SYSTEMS.............................................1-09-36.... 01 APU BLEED SYSTEM......................................................1-09-36.... 08 BLD APU LEAK WARNING MESSAGE...........................1-09-36.... 10 ATA Chapter 38 - WATER/WASTE POTABLE WATER SYSTEMS ........................................1-09-38.... 01 LAVATORY WASTE SYSTEMS (INCLUDING WHEELCHAIR ACCESSIBLE LAVATORIES) .................1-09-38.... 02 ATA Chapter 45 - CENTRAL MAINTENANCE COMPUTER CENTRAL MAINTENANCE COMPUTER (CMC) ............1-09-45.... 01 ATA Chapter 49 - AUXILIARY POWER UNIT AUXILIARY POWER UNIT (APU)....................................1-09-49.... 01 APU BLEED AIR SYSTEM...............................................1-09-49.... 02 APU OIL LO PRESS CAUTION MESSAGE ....................1-09-49.... 02 APU OIL HI TEMP CAUTION MESSAGE........................1-09-49.... 03 APU FAIL CAUTION MESSAGE .....................................1-09-49.... 03 APU HOURMETER FUNCTION ......................................1-09-49.... 04 ATA Chapter 52 - DOORS MAIN DOOR HYDRAULIC ACTUATION SYSTEM .........1-09-52.... 01 C&D AEROSPACE FLIGHT DECK SECURITY DOOR ...........................................................1-09-52.... 02 DOORS WARNING SYSTEM (DOOR POSITION INDICATION ON MFD AND EICAS)................................1-09-52.... 03 ATA Chapter 56 - WINDOWS WINDSHIELD...................................................................1-09-56.... 01
Page
1-09-00
Code
10 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA Chapter 73 - ENGINE FUEL AND CONTROL FULL AUTHORITY DIGITAL ELECTRONIC CONTROLS (FADEC) ..................................................... 1-09-73 ....01 ENGINE FUEL TEMPERATURE SENSORS .................. 1-09-73 ....03 E1 (2) FUEL IMP BYP ADVISORY MESSAGES ............. 1-09-73 ....05 FUEL FILTERS ................................................................ 1-09-73 ....08 FUEL FLOW INDICATIONS ............................................ 1-09-73 ....09 ATA Chapter 74 - IGNITION IGNITION SYSTEM CHANNELS..................................... 1-09-74 ....01 ATA Chapter 77 - ENGINE INDICATING HP VIBRATION INDICATION.......................................... 1-09-77 ....01 ATA Chapter 78 - ENGINE EXHAUST THRUST REVERSER...................................................... 1-09-78 ....01 ENG1 (2) REV DISAGREE MESSAGES......................... 1-09-78 ....02 ATA Chapter 79 - ENGINE OIL LOW OIL PRESSURE SWITCHES ................................. 1-09-79 ....01 OIL LEVEL INDICATION SYSTEMS ............................... 1-09-79 ....02 OIL PARTICLE SENSORS .............................................. 1-09-79 ....02 E1 (2) OIL IMP BYP MESSAGES.................................... 1-09-79 ....03 OIL FILTERS.................................................................... 1-09-79 ....04
ATA Chapter 80 - STARTING STARTER CONTROL VALVE ......................................... 1-09-80 ....01
Page
REVISION 6
1-09-00
Code
11 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-09-00
Code
12 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
DOCUMENT PURPOSE This document is intended to assist airline operations and maintenance organizations in developing procedures required to operate the aircraft in the various non-standard configurations allowed by the approved Master Minimum Equipment List - MMEL. A MMEL is published for each airplane model, written in very brief format and presenting only the main remarks to dispatch the airplane. In order to accomplish such remarks, it is necessary to establish adequate maintenance and operational procedures, so the airplane may be properly prepared and operated. It is the operator's responsibility to develop a company MEL with procedures, using the MMEL as a guide to obtain approval of this company MEL from the assigned authorities to determine that: a) Adequate procedures have been developed, and b) The company MEL is not less restrictive than the MMEL. In order to help Legacy’s Operators to construct their own MEL, Embraer is publishing the MEL-135/1905 that merging the FAA MMEL with the FAA DDPM at their current revision status (Revision 10 and Revision 6, respectively). By publishing this document, EMBRAER is not inferring that the procedures herein presented are the only valid alternatives for the MMEL items. The operator may, in many cases, develop procedures which more closely meet his needs. Variables such as airplane configuration, airline routes, special operational procedures and the own airlines maintenance practices may affect a given procedure. Because of the above explained, it is emphasized that the information contained in this publication is presented for guidance purposes only. Before publishing any dispatch procedure in its own manual, each operator should review the procedures, to assure that they are adequate for his particular operation, and should submit them to the local authority inspector for approval. NOTE: The EMB-135BJ airplanes mentioned in this manual are related to those airplanes equipped with winglets, auxiliary fuel tanks (two forward and two aft fuel tanks) and personalized interior arrangement. For all other “LEGACY”, equipped with personalized interior arrangement but not equipped with winglets or auxiliary fuel tanks, they should be considered as a standard EMB-135 airplanes for the purpose of MEL.
Page
REVISION 6
1-09-02
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-09-02
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
PREAMBLE The Airworthiness Regulations require that all equipment installed on an airplane in compliance with the Airworthiness Standards and the Operating Rules must be operative. However, the Rules also permit the publication of a Minimum Equipment List (MEL) where compliance with certain equipment requirements is not necessary in the interests of safety under all operating conditions. Experience has shown that with the various levels of redundancy designed into airplane, operation of every system or installed component may not be necessary when the remaining operative equipment can provide an acceptable level of safety. A Master Minimum Equipment List (MMEL) is developed by the Airworthiness Authority, with participation by the aviation industry, to improve airplane utilization and thereby provide more convenient and economic air transportation for the public. The Airworthiness Authority approved MMEL includes those items of equipment related to airworthiness and operating regulations and other items of equipment which the Administrator finds may be inoperative and yet maintain an acceptable level of safety by appropriate conditions and limitations; it does not contain obviously required items such as wings, flaps, and rudders. The MMEL is the basis for development of individual operator MELs which take into consideration the operator’s particular airplane equipment configuration and operational conditions. Operator MELS, for administrative control, may include items not contained in the MMEL; however, relief for administrative control items must be approved by the Administrator. An operator’s MEL may differ in format from the MMEL, but cannot be less restrictive than the MMEL. The individual operator’s MEL, when approved and authorized, permits operation of the airplane with inoperative equipment. Equipment not required by the operation being conducted and equipment in excess of Airworthiness Regulations requirements are included in the MEL with appropriate conditions and limitations. The MEL must not deviate from the Airplane Flight Manual Limitations, Emergency Procedures or with Airworthiness Directives. It is important to remember that all equipment related to the airworthiness and the operating regulations of the airplane not listed on the MMEL must be operative.
Page
REVISION 6
1-09-02
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
Suitable conditions and limitations in the form of placards, maintenance procedures, crew operating procedures and other restrictions as necessary are specified in the MEL to ensure that an acceptable level of safety is maintained. The MEL is intended to permit operation with inoperative items of equipment for a period of time until repairs can be accomplished. It is important that repairs be accomplished at the earliest opportunity. In order to maintain an acceptable level of safety and reliability, the MMEL establishes limitations on the duration of and conditions for operation with inoperative equipment. The MEL provides for release of the airplane for flight with inoperative equipment. When an item of equipment is discovered to be inoperative, it is reported by making an entry in the Airplane Maintenance Record/Logbook as prescribed by Airworthiness Regulations. The item is then either repaired or may be deferred per the MEL or other approved means acceptable to the Administrator prior to further operation. MEL conditions and limitations, do not relieve the operator from determining that the airplane is in condition for safe operation with items of equipment inoperative. When these requirements are met, an Airworthiness Release, Airplane Maintenance Record/Logbook entry, or other approved documentation is issued as prescribed by Airworthiness Regulations. Such documentation is required prior to operation with any item of equipment inoperative. Operators are responsible for exercising the necessary operational control to ensure that an acceptable level of safety is maintained. When operating with multiple inoperative items, the interrelationships between those items and the effect on airplane operation and crew workload will be considered. Operators are to establish a controlled and sound repair program including the parts, personnel, facilities, procedures, and schedules to ensure timely repair. WHEN USING THE MEL, COMPLIANCE WITH THE STATED INTENT OF THE PREAMBLE, DEFINITIONS, AND THE CONDITIONS AND LIMITATIONS SPECIFIED IN THE MEL IS REQUIRED.
Page
1-09-02
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
DEFINITIONS AND SYMBOLOGY 1) System numbers are based on Air Transport Association (ATA) number 100. 2) “Item” (column 1) means the equipment component or system, listed in the Item Column. 3) The number in column 2 indicates the number (quantity) of listed items normally installed on the airplane. This number reflects the airplane type certificated configuration, and therefore, required for all flight operations, except as provided in columns 3 and 4. Dashsymbol in column 2 indicates a variable number (quantity) of the item installed, depending on the airplane configuration. NOTE: Operator’s MEL must indicate the actual number installed and actual number for dispatch, in case of the dispatch column is variable. 4) References given in column 4, for example (see 28-43-00) and (see AFM limitations), are to bring attention to certain interrelationships between the subject item and other MMEL items or AFM material. These references are intended to assist with compliance, but do not relieve the operator of responsibility for determining such interrelationships as stated in the Preamble. 5) The number (quantity) of items that may be inoperative is stated in column 4, unless 0 in column 3 indicates that none are required. The provisos included in the column 4 shall be complied for operation with the item inoperative. 6) “Note” in column 4 indicates additional information and references for crewmember or maintenance consideration. Notes are not part of the provisos. 7) “As required by local regulations” means that the listed item of equipment is subject to certain provisions (restrictive or permissive) expressed in the local operating aviation regulations. The number of items required by the regulations must be operative. Items installed in excess of those required may be inoperative in the operator’s MEL, if not otherwise required by the MMEL.
Page
REVISION 6
1-09-02
Code
5 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
8) “Inoperative” means a condition in which a listed item of equipment is malfunctioning to the extent that it does not accomplish its intended purpose, or is not consistently functioning within its designed operating limits or tolerances. Unless individually permitted to be inoperative, a component or function of a system which is inoperative, implies that the system is inoperative (warning/caution systems associated with the inoperative system must be operative unless relief is specifically authorized by the MMEL). 9) Each inoperative item must be placarded to inform crewmembers of the equipment condition. As much as possible, placards should be located adjacent to the control or indication of the affected item, however, unless otherwise specified herein, placard wording and location will be determined by the operator. 10) “VFR” (Visual Flight Rules) is as defined in the operational regulations. This precludes a pilot from filling an Instrument Flight Rules (IFR) flight plan. 11) “VMC” (Visual Meteorological Conditions) - The atmospheric environment is such that would allow the flight to proceed under visual flight rules applicable to the flight. This does not preclude a pilot from filing an IFR flight plan and then conducting the flight in accordance with visual flight requirements. 12) “IMC” (Instrument Meteorological Conditions) - Meteorological conditions expressed in terms of visibility, distance from cloud, and ceiling are less than the minimum specified for Visual Meteorological Conditions. 13) “Icing Conditions” means an atmospheric environment that may cause ice to form on the airplane or in the engines. 14) “Visible Moisture” means an atmospheric environment containing water in any form that can be seen in natural or artificial light; for example: clouds, fog, rain, sleet, hail, or snow. 15) “Secured” and “Deactivated” mean that the specified component must be put into an acceptable condition for safe flight.
Page
1-09-02
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
16) “Passenger Convenience Items” means those items related to passenger convenience, comfort or entertainment such as, but not limited to, galley equipment, movie equipment, ash trays, stereo equipment, overhead reading lamps, etc. 17) “Flight hours” for MMEL purposes means the time from the moment the airplane leaves the surface of the earth until it touches it at the next point of landing (i.e., takeoff to landing time). “Flight hours” is identical to “time in service”, as defined in the Airworthiness Regulations. 18) “Flight day” - a 24-hour period (from midnight to midnight) during which at least one flight is scheduled for the affected airplane. 19) “Day of discovery” is the calendar day the equipment was found to be malfunctioning. 20) Repair Intervals: a letter designator is inserted adjacent to Column 2. All deferred MMEL items must be repaired at or prior the repair times established by the following letter designators: -
Category A - Items in this category must be repaired within the time interval specified in the remarks column.
-
Category B - Items in this category must be repaired within three consecutive calendar days (72 hours), excluding the day the malfunction was recorded in the logbook. For example, if it were recorded at 10 am. on December, 11th, the three day interval would begin at midnight the 11th and end at midnight the 14th.
-
Category C - Items in this category must be repaired within tem consecutive calendar days (240 hours), excluding the day the malfunction was recorded in the logbook. For example, if it were recorded at 10 am. on December, 11th, the ten day interval would begin at midnight the 11th and end at midnight the 21st.
-
Category D - Items in this category must be repaired within one hundred and twenty consecutive calendar days (2880 hours), excluding the day the malfunction was recorded in the logbook. For example, if it were recorded at 10 am. on March, 05th, the 120 day interval would begin at midnight the 05th and end at midnight on July , 05th.
Page
REVISION 6
1-09-02
Code
7 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
21) “Excess Items” means those items that have been installed that are in excess of those required by the Airworthiness Regulations. 22) "(M)" symbol indicates a requirement for a specific maintenance procedure which must be accomplished prior to operation with the listed item inoperative. Normally these procedures are accomplished by maintenance personnel; however, other personnel may be qualified and authorized to perform certain functions. Procedures requiring specialized knowledge or skill, or requiring the use of tools or test equipment should be accomplished by maintenance personnel. The satisfactory accomplishment of all maintenance procedures, regardless of who performs them, is the responsibility of the operator. Appropriate procedures are required to be published as part of the operator's manual or MEL. 23) "(O)" symbol indicates a requirement for a specific operations procedure which must be accomplished in planning for and/or operating with the listed item inoperative. Normally these procedures are accomplished by the flight crew; however, other personnel may be qualified and authorized to perform certain functions. The satisfactory accomplishment of all procedures, regardless of who performs them, is the responsibility of the operator. Appropriate procedures are required to be published as part of the operator's manual or MEL. 24) Three asterisks (***) in column 1 indicates an item which is not required by the Airworthiness Regulations, but may have been installed in the airplane. It should be noted that neither this definition nor the use of this symbol provide authority to install or remove an item from an aircraft. 25) The “/” symbol indicates “and/or”. 26) A vertical bar (change bar) in the margin indicates a change, addition or deletion in the adjacent text for the current revision of that page only. The change bar is dropped at the next revision of that page. 27) A change bar adjacent to the page number indicates that the page was renumbered only and that no change was made in the text.
Page
1-09-02
Code
8 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
28) “Combustible material” is defined as being a material which is capable of catching fire and burning. When an MMEL item specifies that only non-combustible materials shall be carried, it is operator’s responsibility to determine that all material (including packages, containers, contents, etc.) in the compartment is of a non-combustible nature. If it cannot be determined whether any proposed cargo is non-combustible, it must not be loaded in the compartment.
Page
REVISION 6
1-09-02
Code
9 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-09-02
Code
10 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 21 AIR CONDITIONING 21-22-04 EXTERNAL GROUND CONNECTOR CHECK VALVE Number installed Number required for dispatch
-22-04 External Ground Connector Check Valve
B
1
0
C
1
0
(M) (O) May be inoperative open provided flight is conducted in an unpressurized configuration. May be inoperative closed.
Placard Air Conditioning/Pneumatic Panel "GROUND CONNECTION CHECK VALVE OPEN". OPERATIONAL PROCEDURES Refer to Item 21-31-03 for unpressurized configuration. MAINTENANCE PROCEDURES Refer to Item 21-31-03 for outflow valves secured open, if required.
Page
REVISION 6
1-09-21
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
21-22-06 BAGGAGE COMPARTMENT VENTILATION SYSTEM Number installed Number required for dispatch
-22-06 Baggage *** Compartment Ventilation System
C
1
0
(M) May be inoperative provided: a) Ventilation system remains closed, and b) Live animals are not carried in the cargo compartment.
Placard Fire Detection/Extinguishing Panel "VENTILATION SYSTEM INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Deactivate Baggage Recirculation Fan as follows: − On the circuit breaker panel, open the MISCELLANEOUS/BAGGAGE RECIRC FAN circuit breaker and attach a do-not-close tag on it. − Open access 272DR, Rear Electronic Compartment Access Hatch. Gain access to the rear electronic compartment and locate the baggage recirculation fan (See Figure on AMM PART I 21-27-00). − Disconnect and stow electrical connector of the fan. − Close BAGGAGE RECIRC FAN circuit breaker. An alternate method to deactivate baggage compartment fan is pulling and collaring BAGGAGE RECIRC FAN circuit breaker. The Baggage Fire Extinguishing Button will not illuminate during system test, however EICAS message BAGG SMOKE and extinguishing system will remain operate normally.
Page
1-09-21
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
21-23-03 GASPER FAN Number installed Number required for dispatch
-23-03 Gasper Fan
C
1
0
May be inoperative on ground with the avionics buses energized provided: a) If doors are open: both packs operate normally, and remain in continuous operation, and ambient temperature is below ISA + 25 °C, and b) If doors are closed: At least one pack operates normally and remains in continuous operation, and ambient temperature ground is below ISA + 32 °C. NOTE 1: Avionics buses energized on the ground are limited to 10 minutes if doors are open and both packs are not operating. NOTE 2: Conditions above are applicable to ground operation only. There is no restriction to in-flight operation with gasper fan inoperative. NOTE 3: Doors referred to above include main, service and cargo compartment doors.
Placard Gasper Fan Button "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-21
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
21-24-01 RECIRCULATION FANS Number installed Number required for dispatch
-24-01 Recirculation Fans 1) Airplanes equipped with conventional electromechanical standby instruments 2) Airplanes equipped with Integrated Standby Instrument System (ISIS)
C
2
0
(M) May be inoperative provided failed fan is deactivated.
C
2
1
(M) Recirculation Fan 1 may be inoperative provided: a) Failed fan is deactivated, b) Pack 2 operates normally, and c) Ambient temperature on the ground is below ISA + 25 °C.
C
2
0
(M) May be inoperative provided: a) Failed fan is deactivated, and b) Pack 1 operates normally.
Placard Recirculation Button "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Recirculation Fan deactivated: Pull and safety the affected recirculation fan circuit breaker, COCKPIT RECIRC (J14) and/or CABIN RECIRC (J21).
Page
1-09-21
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
21-24-02 RECIRCULATION FAN VALVES Number installed Number required for dispatch
-24-02 Recirculation Fan Valves
C
2
0
C
2
0
(M) May be inoperative open provided associated recirculation fan is verified to operate normally. (M) May be inoperative closed provided associated recirculation fan is deactivated and considered inoperative.
Placard Air Conditioning/Pneumatic Control Panel "RECIRCULATION FAN VALVE OPEN". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES − Perform SUBTASK 21-20-00-710-001-A00 (AMM) for recirculation fan operational check. − Refer to Item 21-24-01 for recirculation fan deactivation.
Page
REVISION 6
1-09-21
Code
5 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
21-24-03 AIR DISTRIBUTION VALVES Number installed Number required for dispatch
-24-03 Air Distribution Valves
C
2
1
(M) One may be inoperative provided remaining valve is deactivated in open position.
Placard Air Conditioning/Pneumatic DISTRIBUTION VALVE STUCK CLOSED".
Control
Panel
"AIR
OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Cold Air Distribution Valve Stuck Closed (T24 ± 2°C): To open the cold air distribution valve: − Change the passenger cabin air temperature to cold until the cold air distribution valve opens. − Check normal passenger cabin airflow from the upper ducts. − Pull and safety the DISTR VALVES circuit brake (F27). − Control the passenger cabin temperature as required thought cockpit/attendant’s control panel. NOTE: Air distribution valve is stuck closed if there is few or no airflow in passenger cabin associated with excessive airflow in the cockpit.
Page
1-09-21
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
21-25-01 RAM AIR VALVES Number installed Number required for dispatch
-25-01 Ram Air Valves 1) Airplanes equipped with conventional electromechanical standby instruments
C
2
1
C
2
0
(M)(O) One may be inoperative provided: a) Associated air conditioning pack remains off, b) Affected ram air valve is verified to be in emergency ram air position, and c) Flight is conducted at or below FL 250. (M)(O) May be inoperative provided: a) Both packs remain off, b) Flight is conducted in an unpressurized configuration, c) Ram air valves are verified to be in emergency ram air position, and d) Ambient temperature on ground is below ISA + 21 °C.
(continued) Page
REVISION 6
1-09-21
Code
7 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
21-25-01 RAM AIR VALVES (CONTINUED) Number installed Number required for dispatch
-25-01 Ram Air Valves (continued) 2) Airplanes equipped with Integrated Standby Instrument System (ISIS)
C
2
1
(M)(O) Either ram air valve may be inoperative provided: a) Associated pack remains off, b) Remaining pack and associated recirculation operate normally and remain in continuous operation on the ground, c) Associated ram air valve is verified to be in emergency ram air position, d) Flight is conducted at or below FL 250, and e) Ambient temperature on the ground is below ISA + 25 °C.
Placard affected Air Conditioning Pack Button "INOP". OPERATIONAL PROCEDURES Failure of One Ram Air Valve: Conduct flight at or below 25000 ft. Associated Air Conditioning Pack must be OFF. Failure of Both Ram Air Valves: Conduct flight at or below 10000 ft. Both Air Conditioning Packs must be OFF. Refer to Item 21-31-03 for unpressurized configuration.
Page
1-09-21
Code
8 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
MAINTENANCE PROCEDURES Refer to Item 21-31-03 for both outflow valves secured open (perform this step only in case of both Ram Air Valve failure). Ram Air Valve in Emergency Ram Air position: − Perform SUBTASK 32-63-00-860-001-A00 (AMM) to simulate AIR (this step must be performed only in case of failure of both Ram Air Valves). − Open RAM AIR Valve Circuit Breaker. − Gain access to the affected Ram Air Valve and disconnect the electrical connector of the Ram Air Valve actuator (AMM 21-25-01 Figure 401). − Tie the electrical connector close to a wire clamp. − Close access to the Ram Air Valve. − Close RAM AIR Valve Circuit Breaker. − Close Air/Ground Circuit Breakers. − In this locked position, there will be a Ram Air failure indication on EICAS during ground operation.
21-25-02 RAM AIR CHECK VALVES Number installed Number required for dispatch
-25-02 Ram Air Check Valves
C
2
0
(M) (O) May be inoperative open provided flight is conducted in an unpressurized configuration.
Placard Air Conditioning/Pneumatic Control Panel "RAM AIR INOP OPEN". OPERATIONAL PROCEDURES Refer to Item 21-31-03 for unpressurized configuration. MAINTENANCE PROCEDURES Refer to Item 21-31-03 for outflow valves secured open, if required.
Page
REVISION 6
1-09-21
Code
9 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
21-26-00 FORWARD ELECTRONIC COMPARTMENT VENTILATION SYSTEM Number installed Number required for dispatch
-26-00 Forward Electronic Compartment Ventilation System 1) Exhaust Fan/NACA Cover Linear Actuators
C
2
1
One exhaust fan or one NACA Cover Linear Actuator may be inoperative.
Placard Air Conditioning/Pneumatic Control Panel "FWD ELEC COMPT VENT INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-21
Code
10 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
21-30-00 PRESSURIZATION CONTROL SYSTEM Number installed Number required for dispatch
-30-00 Pressurization Control System 1) Automatic Mode
C
1
0
2) Manual Mode
C
1
0
3) Automatic and Manual Modes
C
2
0
(M)(O) May be inoperative provided: a) Manual mode operates normally, b) Electropneumatic outflow valve is secured closed, and c) Cabin differential pressure indication, cabin rate of change indication, and cabin altitude indication operate normally. (M)(O) May be inoperative provided: a) Automatic mode operates normally, b) Pneumatic outflow valve is secured closed, and c) Cabin differential pressure indication operates normally. (M)(O) May be inoperative provided: a) Flight is conducted in an unpressurized configuration, and b) Both outflow valves are secured open.
Placard Pressurization Mode Selector Button "MAN INOP", or "AUTO INOP", or "AUTO/MAN INOP".
Page
REVISION 6
1-09-21
Code
11 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
OPERATIONAL PROCEDURES Operation in Manual Mode: If automatic control of the pressurization system is not possible, manual control of cabin pressure can be maintained via the pneumatic outflow valve using the following procedures: − Rotate the Manual Pressurization knob clockwise to the one o’clock position. − Wait 15 seconds. − Select MAN with the guarded pressurization mode selector button. − Rotate the knob clockwise to increase cabin altitude, rotate it counter-clockwise to decrease cabin altitude. − Monitor cabin differential pressure to ensure it remains within limits. Unpressurized Configuration: Refer to Item 21-31-03 for unpressurized configuration. MAINTENANCE PROCEDURES Refer to Item 21-31-03 for electropneumatic/pneumatic outflow valves secured closed or secured open.
Page
1-09-21
Code
12 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
21-31-03 OUTFLOW VALVES Number installed Number required for dispatch
-31-03 Outflow Valves 1) Electropneumatic C
1
0
C
1
0
3) Electropneumatic C and Pneumatic
2
0
2) Pneumatic
(M)(O) May be inoperative provided: a) Valve is secured closed, b) Manual pressurization control mode operates normally, and c) Cabin differential pressure indication, cabin rate of change indication, and cabin altitude indication operate normally. (M)(O) May be inoperative provided: a) Valve is secured closed, b) Automatic pressurization control mode operates normally, and c) Cabin differential pressure indication operates normally. (M)(O) May be inoperative provided: a) Flight is conducted in an unpressurized configuration, and b) Both outflow valves are secured open.
Placard Pressurization Mode Selector Button "MAN INOP" if pneumatic outflow valve is inoperative, or "AUTO INOP" if electropneumatic outflow valve is inoperative, or "AUTO/MAN INOP" if both outflow valves are inoperative.
Page
REVISION 6
1-09-21
Code
13 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
OPERATIONAL PROCEDURES Unpressurized Configuration: Outflow Valves...............................................................OPEN Outflow valves may be kept open through one of the following ways: Pressurization Dump Button.....................................PRESSED OR Pressurization Mode Selector Button .......................PRESSED Manual Controller Knob............................................UP OR Using the Opening Tool Kit (refer to maintenance procedures). OR Removing the valves. Bleed Air Buttons...........................................................AS REQUIRED If air conditioning packs are going to be used, maintain the Bleed Air Buttons at pressed position (bleed open), otherwise, set them to released position (bleed closed). Pack Buttons .................................................................AS REQUIRED If air conditioning packs are going to be used, maintain the Pack Buttons at pressed position (pack valve open), otherwise, set them to released position (pack valve closed). Recirculation Fans.........................................................AS REQUIRED Altitude...........................................................................10000 FT
Page
1-09-21
Code
14 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
REVISION 6
1-09-21
Code
15 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
MAINTENANCE PROCEDURES Electropneumatic Outflow Valve Secured Closed: − Gain access to the electropneumatic outflow valve located in the rear pressure bulkhead. − Perform AMM TASK 21-31-03-000-801-A electropneumatic outflow valve.
to
remove
the
− Safety the valve in the closed position, as shown in outflow valves figure. − Open fitting 1 (see outflow valves figure) and plug tube and valve with plugs P/N AN 806-D5 and P/N AN 929-5. − Perform AMM TASK 21-31-03-400-801-A electropneumatic outflow valve.
to
install
the
− Install removed access panel. Pneumatic Outflow Valve Secured Closed: − Gain access to the pneumatic outflow valve located in the rear pressure bulkhead. − Perform AMM TASK 21-31-04-000-801-A to remove the pneumatic outflow valve. − Safety the valve in the closed position, as shown in outflow valves figure. − Open fitting 2, 3 and 4 (see outflow valves figure) and plug tubes and valve with plugs P/N AN 806-D5 and P/N AN 929-5. − Perform AMM TASK 21-31-04-400-801-A to install the pneumatic outflow valve. − Install removed access panel.
Page
1-09-21
Code
16 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
OUTFLOW VALVES
Page
REVISION 6
1-09-21
Code
17 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
Both Outflow Valves Secured Open: − Gain access to the both outflow valves located in the rear pressure bulkhead. − Using both hands, open one of the valves by pressing the poppet and insert the opening tool (GSE 282) so as to fit it in the valve axle guide (see Outflow Valve Secured Open figure). − Assure the opening tool is fitted on the axle in order to avoid valve closing. − Repeat the procedure for the remaining outflow valve. NOTE: To remove the Opening Tool from the valve assembly, just pull it out.
Page
1-09-21
Code
18 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
OUTFLOW VALVE SECURED OPEN
Page
REVISION 6
1-09-21
Code
19 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
21-32-01 CABIN PRESSURE ACQUISITION MODULE (CPAM) Number installed Number required for dispatch
C 1
0
1) 10000 ft warning C 1
0
2) Cabin Differential Pressure Indication
C 1
0
3) Cabin Rate of Change Indication
C 1
0
4) Cabin Altitude Indication
C 1
0
-32-01 Cabin Pressure Acquisition Module (CPAM)
Page
1-09-21
(M)(O) May be inoperative provided flight is conducted in an unpressurized configuration. (O) May be inoperative provided flight is conducted at or below 10000 ft MSL. (O) May be inoperative provided: a) Cabin altitude and cabin rate of change indication operates normally, and b) A chart is provided to convert cabin altitude into differential pressure. May be inoperative provided: a) Automatic pressurization control mode operates normally, and b) Cabin differential pressure indication and cabin altitude indication are operating normally. (O) May be inoperative provided: a) Cabin differential pressure indication operates normally, b) A chart is provided to convert cabin differential pressure into cabin altitude indication, and c) Automatic pressurization control mode operates normally.
Code
20 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
Placard Digital Controller "CABIN ALT WARN INOP", or "CABIN DIFF PRESS IND INOP", or "CABIN ALT IND INOP", or "CABIN RATE OF CHANGE IND INOP". OPERATIONAL PROCEDURES Use the table below to convert cabin differential pressure into cabin altitude and vice versa: AIRPLANE CABIN DIFFERENTIAL ALTITUDE (ft) ALTITUDE (ft) PRESSURE (psi) 10000 800 4.1 11000 1100 4.4 12000 1300 4.7 13000 1500 4.9 14000 1700 5.2 15000 2000 5.4 16000 2200 5.6 17000 2400 5.8 18000 2600 6.0 19000 2800 6.2 20000 3100 6.4 21000 3300 6.6 22000 3500 6.7 23000 3800 6.9 24000 4000 7.0 25000 4200 7.1 26000 4500 7.3 27000 4700 7.4 28000 4900 7.5 29000 5200 7.6 30000 5400 7.7 31000 5600 7.8 32000 5900 7.8 33000 6200 7.9 34000 6400 8.0 35000 6700 8.0 36000 7000 8.0 37000 7300 8.1 38000 7700 8.1 39000 8000 8.1 Unpressurized Configuration Flight: Refer to Item 21-31-03 for unpressurized configuration flight. MAINTENANCE PROCEDURES Refer to Item 21-31-03 for outflow valves secured open, if required. Page
REVISION 6
1-09-21
Code
21 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
21-51-00 AIR CONDITIONING PACK SYSTEMS Number installed Number required for dispatch
-51-00 Air Conditioning Pack Systems 1) Airplanes equipped with conventional electromechanical stand-by instruments
C 2
1
(O) One may be inoperative provided flight is conducted at or below FL 250.
C 2
0
(M) (O) May be inoperative provided: a) Both ram air valves operate normally, b) Flight is conducted in an unpressurized configuration, and c) Ambient temperature on the ground is below ISA + 21 °C.
2) Airplanes equipped with Integrated Standby Instrument System (ISIS)
C 2
1
(O) One may be inoperative provided: a) Remaining Pack and its associated Recirculation Fan operates normally, b) Ambient temperature on the ground is below ISA + 25 °C, and c) Flight is conducted at or below FL 250.
Placard affected Air Conditioning Pack Button "INOP".
Page
1-09-21
Code
22 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
OPERATIONAL PROCEDURES Unpressurized Configuration (airplanes electromechanical standby instruments):
with
conventional
Refer to Item 21-31-03 for unpressurized configuration. In this condition, ambient temperature, on the ground, must be below ISA + 21°C. Operational Check of Pack and Recirculation Fan (airplanes with ISIS): The recirculation fan operates only when the RECIRC switch is ON and the related pack valve is open. Set the RECIRC switch to ON and check that the airflow through the cockpit general outlets increases. MAINTENANCE PROCEDURES Ram Air Valves Operational Check (airplanes with conventional electromechanical standby instruments): Perform TASK 21-25-01-700-801-A (AMM) for ram air valves operational check.
21-60-04 COCKPIT AND CABIN AUTOMATIC TEMPERATURE CONTROL SYSTEMS Number installed Number required for dispatch
-60-04 Cockpit and Cabin Automatic Temperature Control Systems
C 2
0
May be inoperative provided associated manual temperature control mode operates normally.
Placard associated Temperature Control Mode Knob "AUTO INOP". OPERATIONAL PROCEDURES Associated Temperature Control Mode Selector .......... MAN Monitor cabin or cockpit temperature and control it by using the associated Temperature Adjusting Knob. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-21
Code
23 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
21-60-05 COCKPIT AND CABIN MANUAL TEMPERATURE CONTROL SYSTEMS Number installed Number required for dispatch
-60-05 Cockpit and Cabin Manual Temperature Control Systems
C 2
0
May be inoperative provided associated automatic temperature control mode operates normally.
Placard associated Temperature Control Mode Knob "MAN INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
21-60-06 ATTENDANT’S (GALLEY) TEMPERATURE CONTROL Number installed Number required for dispatch
-60-06 Attendant’s (galley) Temperature Control
C 1
0
May be inoperative provided Passenger Cabin Temperature And Mode Selector Knob operates normally.
Placard Attendant’s Temperature Control "INOPERATIVE". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-21
Code
24 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
21-61-02 COCKPIT AND CABIN TEMPERATURE INDICATION SYSTEMS Number installed Number required for dispatch
-61-02 Cockpit and Cabin Temperature Indication Systems
C 2
0
Placard Air Conditioning and Pneumatic Control Panel "CABIN TEMP IND INOP" or "CKPT TEMP IND INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-21
Code
25 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-09-21
Code
26 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 22 AUTOFLIGHT 22-10-00 AUTOPILOT/FLIGHT DIRECTOR FUNCTIONS Number installed Number required for dispatch
-10-00 Autopilot/Flight Director Functions 1) Autopilot Function
B
1
0
2) Flight Director Function
C 1
0
3) Yaw Damper Function
B
0
1
May be inoperative provided enroute or approach procedures do not require its use. May be inoperative provided enroute or approach procedures do not require its use. May be inoperative provided enroute or approach procedures do not require its use. NOTE: Autopilot will not engage with yaw damper inoperative.
Placard Flight Guidance Controller "AP/FD/YD INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-22
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
22-11-01 FLIGHT GUIDANCE CONTROLLER PANEL Number installed Number required for dispatch
-11-01 Flight Guidance Controller Panel 1) Flight Level Change (FLC) Engage Button
C 1
0
May be inoperative provided procedures do not require its use.
Placard Flight Guidance Controller Panel "FLIGHT LEVEL CHANGE (FLC) BUTTON INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-22
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
22-11-08 TOUCH CONTROL STEERING BUTTON (TCS SYNC BUTTONS) Number installed Number required for dispatch
C 2 -11-08 Touch Control Steering Button (TCS Sync Buttons)
0
May be inoperative in the deactivated condition.
Placard Flight Guidance Controller Panel "LEFT OR RIGHT OR BOTH TCS BUTTON INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-22
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
22-11-09 GO-AROUND BUTTONS Number installed Number required for dispatch
-11-09 Go-Around Buttons
C 2
0
May be inoperative provided: a) Enroute or approach procedures do not require its use, and b) Affected button is failed in the deactivated condition. NOTE: In case of dual failure, only automatic engagement of Windshear Escape Guidance Mode by positioning the TLA above 78 degrees operates normally.
Placard Flight Guidance Controller Panel "LEFT or RIGHT or BOTH GA BUTTON INOP". OPERATIONAL PROCEDURES CAT I Operation: None. CAT II Operation: Go-Around Button Check: For CAT II operation, at least one go-around button must be operative. Before engine start, press the operative Go-Around Button and check that the Takeoff Submode become available on the EADI. MAINTENANCE PROCEDURES None.
Page
1-09-22
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 23 COMMUNICATIONS 23-00-00 COMMUNICATION SYSTEMS (VHF, HF, UHF) Number installed Number required for dispatch
00-00 Communications Systems (VHF, HF, UHF) D 1) Very High Frequency (VHF) Communication System
-
Any in excess of those required by FAR may be inoperative provided it is not powered by an essential bus and do not required for emergency procedures.
D -
-
Any in excess of those required by FAR may be inoperative.
C -
1
(O) May be inoperative while conducting operations that require two Long Range Communication Systems (LRCS) provided: a) SATCOM (High or Low Gain) Data Link system operates normally, and b) SATCOM Data Link communication operates normally over the intended route of the flight.
3) Ultra High D Frequency (UHF) Communication System
-
Any in excess of those required by FAR may be inoperative provided it is not powered by an essential bus and not required for emergency procedures.
2) High Frequency (HF) Communication System
Placard associated control panel "VHF or HF or UHF INOP". Page
REVISION 6
1-09-23
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES None.
23-20-01 ACARS SYSTEM Number installed Number required for dispatch
-20-01 ACARS System ***
***
ACARS Printer
C -
0
D -
0
C -
0
D -
0
(O) May be inoperative provided alternate procedures are established and used. May be inoperative provided procedures do not require its use. (O) May be inoperative provided alternate procedures are established and used. May be inoperative provided procedures do not require its use.
Placard ACARS Panel or Printer "INOP". OPERATIONAL PROCEDURES Alternate procedures must be created according to each operator’s characteristics in order to establish communications between flight crew and ground station. MAINTENANCE PROCEDURES None.
Page
1-09-23
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
23-21-01 SELECTIVE CALL SYSTEM (SELCAL) Number installed Number required for dispatch
-21-01 Selective Call *** System (SELCAL)
C -
0
(O) May be inoperative provided alternate procedures are established and used.
D -
0
May be inoperative provided procedures do not require its use.
Placard SELCAL Panel "SELCAL INOP". OPERATIONAL PROCEDURES Alternate procedures must be created according to each operator’s characteristics in order to establish communications between ground station and flight crew. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-23
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
23-30-01 PASSENGER ADDRESS SYSTEM Number installed Number required for dispatch
-30-01 Passenger Address System 1) Passenger Configuration
a) Lavatory Speakers
B
1
0
(O) May be inoperative provided: Alternate normal and emergency procedures and/or operating restrictions are established and used. NOTE: Any station function(s) that operate normally may be used.
C 1
0
(O) May be inoperative provided: a) PA not required by FAR, and b) Alternate, normal and emergency procedures and/or operating restrictions are established and used. NOTE: Any station function(s) that operate normally may be used.
C 1
0
(O) May be inoperative provided alternate procedures are established and used.
Placard Digital Audio Panels "PAX ADRS INOP". OPERATIONAL PROCEDURES Alternate normal and emergency procedures must be created according to each operator characteristics in order to establish communications between flight crew and passengers, when required. MAINTENANCE PROCEDURES None.
Page
1-09-23
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
23-31-02 ALERTING SYSTEMS (AUDIO/VISUAL) Number installed Number required for dispatch
-31-02 Alerting Systems (Audio/Visual) 1) Passenger Configuration a) Flight Deck Call Visual Alerting System
B
1
0 May be inoperative provided the flight deck audio alerting system operates normally. NOTE: The flight deck audio alerting must always be operative.
b) Flight Attendant Visual Alerting System
B
1
0 (O) May be inoperative provided: a) PA System operates normally, b) If affected light is used for lavatory smoke detector alerting, an alternate lavatory smoke alert (audio or visual) is installed and operates normally, and c) Alternate normal for contacting flight attendants are established and used. NOTE: 1) Passenger to Attendant Call System is considered a passenger convenience item. NOTE: 2) Any visual alerting system function(s) that operates normally may be used. (continued)
Page
REVISION 6
1-09-23
Code
5 06
MINIMUM EQUIPMENT LIST
23-31-02
AIRPLANE OPERATIONS MANUAL
ALERTING SYSTEMS (CONTINUED)
(AUDIO/VISUAL)
Number installed Number required for dispatch
-31-02 Alerting Systems (Audio/Visual) (continued) B c) Flight Attendant Audio Alerting System
-
0 May be inoperative provided: a) PA System operates normally. b) If affected chime is used for lavatory smoke alert (audio or visual) is installed and operates normally, and c) Alternate procedures for contacting flight attendants are established and used. NOTE: 1) Passenger to Attendant Call System is considered a passenger convenience item. NOTE: 2) Any audio alerting system function(s) that operates normally may be used.
Placard CABIN or CAB EMER Buttons on ICU Panel "LIGHT INOP". Placard CABIN Button on ICU Panel or PILOT light in the attendants handset. Placard CABIN Button and ICU Panel or PILOT light in the attendants handset "CHIME INOP". OPERATIONAL PROCEDURES Alternate procedures must be created according to each operator characteristics in order to alert the attendant when is required. MAINTENANCE PROCEDURES None.
Page
1-09-23
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
23-32-02 PRE-RECORDED PASSENGER ANNOUCEMENT SYSTEM Number installed Number required for dispatch
-32-02 Pre-recorded *** Passenger Announcement System
C 1
0
(O) May be inoperative provided alternate procedures are established and used.
Placard Entertainment System Panel "INOP". OPERATIONAL PROCEDURES Alternate procedures must be created according to each operator characteristics in order instruct the passengers. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-23
Code
7 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
23-33-01 PASSENGER CABIN/LAVATORY SPEAKERS Number installed Number required for dispatch
-33-01 Passenger Cabin/ Lavatory Speakers
C -
-
May be inoperative provided any seat from which a passenger cannot clearly hear a passenger address announcement is not occupied.
C -
0
May be inoperative provided Passenger Address System is considered inoperative.
Placard Digital Audio Panels "PAX SPEAKERS INOP". OPERATIONAL PROCEDURES Alternate normal and emergency procedures must be created according to each operator characteristics in order to establish communications between flight crew and passengers, when required. MAINTENANCE PROCEDURES None.
Page
1-09-23
Code
8 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
23-51-03 PUSH TO TALK (PTT) (BUTTON ON GLARESHIELD PANEL CONTROL WHEEL) Number installed Number required for dispatch
-51-03 Push To Talk (PTT) C 4 Buttons on Glareshield Panel Control Wheel
2
Two may be inoperative provided one button at each pilot’s station operates normally.
Placard affected PTT Button "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
23-51-04 FLIGHT DECK SPEAKERS Number installed Number required for dispatch
-51-04 Flight Deck Speakers
C 2
0
May be inoperative provided headsets operate normally.
Placard Digital Audio Panels "FLT DECK SPEAKERS INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-23
Code
9 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
23-51-07 FLIGHT DECK HANDHELD MICROPHONES Number installed Number required for dispatch
-51-07 Flight Deck Handheld Microphones
C -
0
May be inoperative provided associated boom microphones operate normally.
***
1) Touchtone Type (DTMF)
C -
0
May be inoperative provided associated microphones operate normally.
***
2) Touchtone C Keypad Functions (DTMF)
0
May be inoperative provided alternate procedures are established and used.
D -
0
May be inoperative provided procedures do not require its use.
Placard pilot’s Jack Panels "HAND MIC INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-23
Code
10 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
23-51-12 BOOM MICROPHONES Number installed Number required for dispatch
-51-12 Boom Microphones 1) Cockpit Voice A A Recorder Equipped To Record Boom Microphones per FAR 121.359 (g), 135.151 (d), or 125.227 (e) *** Cockpit Voice D Recorder Not Equipped to Record Boom Microphone
0
May be inoperative provided: a) Flight Data Recorder (FDR) operates normally, and b) Repairs are made within three flight days.
0
Placard associated Digital Audio Panel or Pilot’s Jack "BOOM MIC INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-23
Code
11 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
23-70-00 FLIGHTDECK DOOR MONITORING SYSTEM Number installed Number required for dispatch
-70-00 Flightdeck Door *** Monitoring System
C -
0
(O) May be inoperative provided: a) An alternative means of viewing the area on the cabin side of the flightdeck door from the flightdeck is available and functional, and b) Alternate procedures are established and used. NOTE: Any portion of the system which operates normally may be used.
Placard Flightdeck Door Monitoring System "INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES None.
Page
1-09-23
Code
12 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
23-71-00 COCKPIT VOICE RECORDER SYSTEM Number installed Number required for dispatch
-71-00 Cockpit Voice Recorder System
A
1
0
May be inoperative provided: a) Flight Data Recorder (FDR) operates normally, and b) Repairs are made within three flight days.
Placard Voice Recorder Panel "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
23-80-00 RADIO MANAGEMENT UNITS (RMU’S) Number installed Number required for dispatch
-80-00 Radio Management Units (RMU’s) 1) NAV/Comm C 2 Tuning Function 2) Memory Function C 2
1 0
May be inoperative provided tuning function operates normally.
Placard associated RMU Bezel "NAV/COM TUN INOP" or "MEM FUNC INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-23
Code
13 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
23-81-02 TUNING BACKUP CONTROL HEAD Number installed Number required for dispatch
-81-02 Tuning Backup Control Head
C 1
0
May be inoperative provided both Radio Management Units operate normally.
Placard Tuning Backup Control Head Panel "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-23
Code
14 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 24 ELECTRICAL POWER 24-20-01 GENERATOR CURRENT INDICATIONS Number installed Number required for dispatch
-20-01 Generator Current Indications
C
4
2
(O) One may be inoperative on each side provided: a) Associated voltage indication operates normally, and b) Remaining generator on the same side operates normally.
Placard affected Generator Button "CURRENT IND INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES None.
24-20-02 GENERATOR VOLTAGE INDICATIONS Number installed Number required for dispatch
-20-02 Generator Voltage Indications
C
4
2
One may be inoperative on each side provided associated current indication operates normally.
Placard affected Generator Button "VOLT IND INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-24
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
24-20-03 INVERTER Number installed Number required for dispatch
A
-20-03 Inverter
Placard AC PWR Button "GPWS/TCAS INOP".
1
0
"INOP"
May be inoperative provided: a) GPWS/Windshear is considered inoperative, b) TCAS powered by 115 V AC is considered inoperative, and c) Repairs are made within two flight days. and
placard
PFD
Bezel
NOTE: TCAS may be electric fed by either inverter or DC Bus. Only TCAS powered by the inverter is considered inoperative. OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-24
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
24-31-01 ENGINE DRIVEN GENERATORS Number installed Number required for dispatch
-31-01 Engine Driven Generators 1) Airplanes equipped with conventional ElectroMechanical Standby Instruments
B
4
3
(M) (O) One may be inoperative provided APU generator operates normally and is used to replace the affected generator during takeoff and landing.
2) Airplanes equipped with Integrated Standby Instruments
B
4
3
(M) (O) One may be inoperative provided APU generator operates normally and is used to replace affected generator during the entire flight.
Placard affected Generator Button "INOP". OPERATIONAL PROCEDURES According to the MMEL remarks.
Page
REVISION 6
1-09-24
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
MAINTENANCE PROCEDURES These procedures are to help maintenance to identify the faulty generator, that carries all loads and avoid dispatch the airplane with the good generator (zero load) inoperative. The following maintenance procedures should be accomplished only if flight crew report a continuous contactor switching noise with an unusual generating indication and no associated EICAS message. In this case, the faulty generator is absorbing all the load while operating in parallel with other in good condition. In this condition, the voltage and current indication on MFD Electrical page of the faulty generator indicates that it is carrying all loads, while the voltage and current indication on MFD Electrical page of the good generator indicates zero load. In this failure mode, the unloaded generator remains connected to the DC Bus. Its line contactor cycles and there is no GEN OFF BUS message. In order to identify the faulty generator, proceed as follows: − BUS TIES Switch .....................................................OFF − All GEN Button .........................................................ON − Voltage and Current (All Generators - on MFD).......CHECK If there is any generator carrying all the load: − Affected GEN Button................................................OFF − BUS TIES Switch .....................................................ON − Voltage and Current (Remaining 3 Generators - on MFD)........................CHECK If the 3 remaining generators are operating normally, disconnect the affected generator of the respective DC Bus by releasing its button on the Electric System Panel. Additionally, pull and safety affected generator GEN 1 (2, 3 or 4) POR and GEN 1 (2, 3 or 4) OUTVOLT circuit breakers: GENERATOR 1 2 3 4
Page
1-09-24
CIRCUIT BREAKERS E8 and E9 Left DC Distribution Box E8 and E9 Right DC Distribution Box D8 and D9 Left DC Distribution Box D8 and D9 Right DC Distribution Box
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
24-31-02 ENGINE DRIVEN GENERATOR BEARINGS (ONLY FOR GENERATOR MODEL 30086-11) Number installed Number required for dispatch
A -31-02 Engine Driven Generator Bearings (Only for Generator Model 30086-11)
4
3
Advisory message GEN BRG FAIL may be presented for one generator provided: a) Caution message GEN OFF BUS for the affected generator was not presented during the previous flight, and b) Repairs are made within 20 flight hours.
Placard affected Generator Button "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-24
Code
5 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
24-34-01 APU STARTER GENERATOR Number installed Number required for dispatch
-34-01 APU Starter Generator 1) Starter Function
C 1
0
May be inoperative provided APU is considered inoperative and not used.
2) Generator Function C 1
0
May be inoperative provided engine driven generators operate normally.
In case of Generator Function failure, placard APU Starter Generator Button "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
24-40-00 EXTERNAL POWER SYSTEM Number installed Number required for dispatch
-40-00 External Power System
C 1
0
1) GPU AVAIL Lights
C 2
0
Placard GPU Button "GPU SYS INOP" or "GPU AVAIL LIGHT INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-24
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 25 EQUIPMENT AND FURNISHINGS 25-11-00 EYE LOCATOR Number installed Number required for dispatch
-11-00 Eye Locator
C 1
0
Placard on windshield central frame top "EYE LOCATOR REMOVED". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
25-11-01 FLIGHT CREW SEATS Number installed Number required for dispatch
-11-01 Flight Crew Seats C 2 1) Vertical Power Seat Adjustment Systems
2) Manual Vertical Adjustments
C 2
0
0
(O)(M) May be inoperative provided: a) System is deactivated, and b) Manual seat adjustment operates normally. (M) May be inoperative provided: a) Seat(s) are locked in a position that permits normal pilots visibility, b) Full flight control movement is available, and c) Position of seat is acceptable to flight crew.
(continued)
Page
REVISION 6
1-09-25
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
25-11-01 FLIGHT CREW SEATS (CONTINUED) Number installed Number required for dispatch
-11-01 Flight Crew Seats (continued) 3) Lumbar Supports
C 2
0
4) Armrests 5) Recline Functions
C 4 C 2
0 0
6) Lateral Adjustments
C 2
0
7) Aft/Fore Adjustment Levers (Airplanes equipped with 2 adjustment levers per seat)
D 4
2
May be inoperative in retracted position or seat is acceptable to affected crewmember. May be inoperative provided seat is acceptable to affected crewmember. May be inoperative with the seat at the central position provided fore/aft adjustments are operative and seat is acceptable to affected crewmember. One lever per seat may be inoperative or broken provided: a) The remaining lever on seat operates normally, and b) The inoperative or broken lever on affected seat does not pose a hazard to the crew or interfere with proper seat operation.
Placard the affected seat control "INOP". OPERATIONAL PROCEDURES In case of vertical power seat adjustment failure, use the manual system to adjust the seat. MAINTENANCE PROCEDURES May be flight crewmember accomplished. In case of vertical power seat adjustment failure, pull and safety the associated SEAT ADJUST circuit breaker (E5 or E28).
Page
1-09-25
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
25-11-02 PRIMARY OBSERVER SEAT (INCLUDING ASSOCIATED EQUIPMENT) Number installed Number required for dispatch
-11-02 Primary Observer Seat (Including associated equipment)
A
1
0
A
1
0
May be inoperative provided: a) A passenger seat in the passenger cabin is made available to an FAA inspector for the performance of official duties, and b) Repair are made within two flight days. May be inoperative provided: a) Required minimum safety equipment (safety belt and oxygen) is available, b) Seat is acceptable to an FAA inspector for the performance of official duties, and c) Repairs are made within two flight days. NOTE 1): These provisos are intended to provide for occupancy of the above seat by an FAA inspector when the minimum safety equipment (oxygen and safety belt) is functional and the inspector determines the conditions to be acceptable. NOTE 2): The pilot-incommand will determine if the minimum safety equipment is functional for other persons authorized to occupy observer seat.
Page
REVISION 6
1-09-25
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
Placard Observer’s Seat "OBSERVER’S SEAT INOP - DO NOT OCCUPY". If required, placard one Passenger Seat "RESERVED". If only Audio Panel is inoperative, placard it "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES If the Oxygen System Pressure is insufficient for three cockipt occupants, the observer seat must be considered inoperative.
Page
1-09-25
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
25-11-04
MINIMUM EQUIPMENT LIST
FLIGHT ATTENDANT SEAT (SINGLE OR DUAL POSITION)
ASSEMBLY
Number installed Number required for dispatch
-11-04 Flight Attendant Seat Assembly (single or dual position) 1) Required Flight Attendant Seats
B
-
-
(M)(O) One seat position or assembly (dual position) may be inoperative provided: a) Affected seat position or seat assembly is not occupied, b) Flight Attendant displaced by inoperative seat occupies the passenger seat which is most accessible to the inoperative seat, so as to most effectively perform assigned duties, c) Alternate procedures are established and used as published in crewmember manuals, d) Folding type seat stows automatically or is secured in the retracted position, and e) Passenger seat assigned to flight attendant is placarded “FOR CABIN ATTENDANT USE ONLY”. NOTE: 1) An automatic folding seat that will not stow automatically is considered inoperative. (continued)
Page
REVISION 6
1-09-25
Code
5 06
MINIMUM EQUIPMENT LIST
25-11-04
AIRPLANE OPERATIONS MANUAL
FLIGHT ATTENDANT SEAT ASSEMBLY (SINGLE OR DUAL POSITION) (CONTINUED) Number installed Number required for dispatch
-11-04 Flight Attendant Seat Assembly (single or dual position) (continued) NOTE: 2) A seat position with an inoperative or missing restraint system is considered inoperative. NOTE: 3) Individual operators, when operating with inoperative seats, will consider the locations and combinations of seats to ensure that the proximity to exits and distribution requirements of the applicable FAR are met.
Placard Attendant’s Seat "INOP - DO NOT OCCUPY". Placard assigned passenger seat "FOR FLIGHT ATTENDANT ONLY". OPERATIONAL PROCEDURES Flight Attendant will occupy the passenger seat closest to her/his duty station. Upon completion of before takeoff cabin announcements and cabin inspection, Flight Attendant will notify the captain that it is ready for departure. Captain will allow the Cabin Attendant to be seated before takeoff roll. All other Cabin Attendant procedures remain the same. MAINTENANCE PROCEDURES May be flight crewmember accomplished. The seat may be secured in the stowed position by using seat belt/shoulder harness or secured with baggage tape or equivalent.
Page
1-09-25
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
25-12-01 SUNVISORS Number installed Number required for dispatch
-12-01 Sunvisors
C 2
0
May be inoperative or missing provided there are no visual restrictions to flight crew.
If not missed, placard the affected sunvisor "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
25-12-02 COCKPIT CONVENIENCE ITEM(S) Number installed Number required for dispatch
-12-02 Cockpit Convenience Item(s)
C -
0
Cockpit convenience items, as expressed in this MMEL are those items related to crewmember convenience or comfort such as, but not limited to: cap holders, ash trays, footrests, etc. Items addressed elsewhere in this document shall not be included.
OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-25
Code
7 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
25-12-03 LIGHTED/MECHANICAL CHECKLIST Number installed Number required for dispatch
-12-03 Lighted/Mechanical *** Checklist
C -
0
Placard the affected Mechanical Checklist Panel "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
25-12-04 CHART HOLDERS Number installed Number required for dispatch
-12-04 Chart Holders
C -
2
May be inoperative or missing provided one is available at each pilot station.
If not missing, placard the affected Chart Holder "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-25
Code
8 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
25-21-05 PASSENGER SEATS AND BELTS Number installed Number required for dispatch
-21-05 Passenger Seats
C
-
-
May be inoperative provided: a) Seat does not block an Emergency Exit, b) Seat does not restrict any passenger form access to the main aircraft aisle, and c) The affected seat(s) are blocked and placarded "DO NOT OCCUPY". NOTE: 1) A seat with an inoperative seat belt is considered inoperative. NOTE: 2) Inoperative seats do not affect the required number of flight attendants.
1) Recline Mechanism
NOTE: 3) Affected seat(s) may include the seat(s) behind and/or adjacent outboard seats. May be inoperative and seat occupied provided seat is secured in the up-right position.
Placard the associated seat "DO NOT OCCUPY" or "DO NOT STOW BAGGAGE UNDER THIS SEAT". OPERATIONAL PROCEDURES As required to meet MMEL remarks. MAINTENANCE PROCEDURES As required to meet MMEL remarks.
Page
REVISION 6
1-09-25
Code
9 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
25-26-08 INTERNAL BAGGAGE ACCESS DOOR Number installed Number required for dispatch
-26-08 Internal Baggage Access Door
C
C
1
1
0
0
(O) Door frame may be damaged, and/or lock may be inoperative preventing door locking, and/or sealing fitness may be impaired provided procedures are established and used to ensure the associated compartment remains empty , or is verified to contain only empty cargo handling equipment, ballast (ballast may be loaded in UDLs), and/or Fly Away Kits. NOTE: Operator MELs must define which items are approved for inclusion in the Fly Away Kits, and which materials can be used as ballast. Door handle and/or lock may be inoperative preventing door opening.
Placard "INTERNAL BAGGAGE ACCESS DOOR INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES None.
Page
1-09-25
Code
10 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
25-27-02 LAVATORY BULKHEAD PEEPHOLE Number installed Number required for dispatch
-27-02 Lavatory Bulkhead Peephole
D
1
0
C
1
0
May be inoperative provided: a) Only view capability is obstructed, and b) Bulkhead peephole is in place and not broken. (M) May be broken, missing or removed provided the hole is blocked by an acceptable means.
OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Perform TASK 25-27-02-300-801-A (AMM) to repair the forward baggage compartment partition.
Page
REVISION 6
1-09-25
Code
11 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
25-30-01 GALLEY WASTE RECEPTACLES ACCESS DOORS/COVERS Number installed Number required for dispatch
C -30-01 Galley Waste Receptacles Access Doors/Covers
-
-
(M)(O) May be inoperative provided: a) The container is empty and the access is secured to prevent waste introduction into the compartment, and b) Procedures are established to ensure that sufficient galley waste receptacles are available to accommodate all waste that may be generated on a flight.
Placard Waste Door Assembly "INOP". OPERATIONAL PROCEDURES According to MMEL remarks. MAINTENANCE PROCEDURES As required to secure the door in the closed position.
Page
1-09-25
Code
12 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
25-40-00 EXTERIOR LAVATORY DOOR ASHTRAYS Number installed Number required for dispatch
-40-00 Exterior Lavatory Door Ashtrays A 1) Airplanes with more than one lavatory door ashtrays installed A 2) Airplanes with only one lavatory door ashtray installed
-
-
One may be missing provided it is replaced within 10 calendar days.
1
0
May be missing provided it is replaced within 3 calendar days.
Register in the appropriate logbook for maintenance actions. OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-25
Code
13 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
25-50-01 CARGO RESTRAINT SYSTEMS Number installed Number required for dispatch
-50-01 Cargo Restraint Systems
1) Horizontal Net
C
-
-
May be inoperative or missing provided acceptable cargo loading limits from an Approved Cargo Loading Manual, Cargo Handling Manual, or Weight and Balance Document are observed.
C
-
-
May be inoperative provided baggage compartment remains empty
C
1
0
May be inoperative or missing provided acceptable cargo loading limits from an Approved Cargo Loading Manual, Cargo Handling Manual, or Weight and Balance Document are observed. NOTE 1: Baggage compartment loaded up to 2182 lb does not require the use of horizontal net.
2) Door Safety Net
Page
1-09-25
C
1
0
NOTE 2: Baggage compartment equipped with reinforced liners (airplanes Post-Mod. SB 145-25-0261 or equipped with an equivalent factory modification incorporated) does not require the use of horizontal net. May be inoperative or missing provided cargo restraint net (horizontal net) is available and used.
Code
14 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
Register in the appropriate logbook for reinstallation actions. OPERATIONAL PROCEDURES As required to meet MMEL remarks. MAINTENANCE PROCEDURES None.
25-60-02 PASSENGER CONVENIENCE ITEM(S) Number installed Number required for dispatch
-60-02 Passenger Convenience Item(s)
-
0
Passenger convenience items, as expressed in this MMEL, are those related to passenger convenience, comfort, or entertainment such as, but not limited to: galley equipment, movie equipment, ash trays, stereo equipment, overhead reading lamps. Items addressed elsewhere in this document shall not be included. (M) or (O) procedures may be required and included in the Air Carrier’s appropriate document. NOTE: 1) Exterior Lavatory Door ash trays are not considered convenience items. NOTE: 2) The acoustic curtain is considered a passenger convenience item.
Placard affected item "INOP". OPERATIONS PROCEDURES As defined by each operator. MAINTENANCE PROCEDURES As defined by each operator. Page
REVISION 6
1-09-25
Code
15 06
MINIMUM EQUIPMENT LIST
25-60-05
AIRPLANE OPERATIONS MANUAL
FLIGHT DECK/ATTENDANT AND HOLDER ASSEMBLIES
FLASHLIGHT
Number installed Number required for dispatch
C -60-05 Flight Deck/ Attendant Flashlight and Holder Assemblies
-
-
May be inoperative or missing provided affected crewmember has a flashlight or equivalent characteristics readily available.
Placard affected Flight Deck/Attendant Flashlight Holder Assembly "INOP" or "REMOVED". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
25-60-07 PYROTECHNIC SIGNAL DEVICES Number installed Number required for dispatch
-60-07 Pyrotechnic Signal Devices Placard Pyrotechnic "REMOVED".
D
Signal
-
-
Device
Any in excess of that required by FAR may be inoperative or missing. or
assembly
"INOP"
or
OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-25
Code
16 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
25-60-09
MINIMUM EQUIPMENT LIST
EMERGENCY MEDICAL EQUIPMENT (INCLUDING EMERGENCY MEDICAL KIT, FIRST AID KIT AND AUTOMATED EXTERNAL DEFIBRILLATOR) Number installed Number required for dispatch
-60-09 Emergency Medical D Equipment (Including Emergency Medical Kit, First Aid Kit and Automated External Defibrillator)
-
-
Any in excess of those required by FAR may be incomplete or missing provided required distribution is maintained.
Register in the appropriate document for necessary actions. OPERATIONAL PROCEDURES None. MAINTENANCE OPERATIONS None.
25-60-10 "FASTEN SEAT BELTS WHILE SEATED" SIGN OR PLACARD Number installed Number required for dispatch
-60-10 "Fasten Seat Belts While Seated" Sign or Placard
C
-
-
One or more signs or placards may be illegible or missing provided a legible sign or placard is readable from each occupied passenger seat.
OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-25
Code
17 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
25-61-01 EMERGENCY LOCATOR TRANSMITTER (ELT) Number installed Number required for dispatch
-61-01 Emergency Locator *** Transmitter (ELT)
D
-
-
Any in excess of that required by FAR may be inoperative or missing.
Placard ELT panel "ELT INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
25-64-02
FLOTATION EQUIPMENT PASSENGER)
(CREW
AND
Number installed Number required for dispatch
-64-02 Flotation Equipment D (Crew and Passenger)
-
-
Any in excess of that required by FAR may be inoperative or missing.
OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-25
Code
18 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 26 FIRE PROTECTION 26-12-00 APU FIRE DETECTION SYSTEM Number installed Number required for dispatch
-12-00 APU Fire Detection System
C 1
0
May be inoperative provided APU is considered inoperative and not used.
Placard APU Control Panel "APU FIRE DET INOP - DO NOT USE APU". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-26
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
26-14-00 LAVATORY SMOKE DETECTION SYSTEM Number installed Number required for dispatch
-14-00 Lavatory Smoke Detection System
C -
0
(O) May be inoperative provided an alternate procedure is established and used to detect smoke in the lavatory.
Placard Lavatory Door "INOPERATIVE - DO NOT ENTER", if applicable. OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES As Legacy presents a passenger capacity of less that 20, it is not required to be equipped with a lavatory smoke detector system. No maintenance procedure is required.
Page
1-09-26
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
26-15-00 BAGGAGE COMPARTMENT SMOKE DETECTION SYSTEM Number installed Number required for dispatch
-15-00 Baggage Compartment Smoke Detection System
C 1
0
(O) May be inoperative provided procedures are established and used to ensure the associated compartment remains empty, or is verified to contain only empty cargo handling equipment, ballast (ballast may be loaded in ULDs), and/or Fly Away Kits. NOTE: Operator MELs must define which items are approved for inclusion in the Fly Away Kits, and which materials can be used as ballast.
Placard Fire Detection/Extinguishing Panel "BAGG SMOKE DET INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-26
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
26-21-02 E1 (OR 2) EXTBTLA (OR B) INOP CAUTION MESSAGES Number installed Number required for dispatch
-21-02 E1 (or 2) EXTBTLA (or B) INOP Caution Messages
B
2
1
(M) May be inoperative provided an alternate procedure is used once each flight day to verify that associated extinguisher bottle is operational.
Placard on associated Engine Fire Detection/Extinguishing Panel "E1 (or 2) EXTBTLA (or B) INOP MESSAGE NOT AVAIL". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Engine Fire Extinguishing System Functional Check: Perform TASK 26-21-00-700-801-A extinguishing system functional check.
(AMM)
for
engine
fire
For airplanes Pre-Mod. SB 145-26-0007, if the EICAS message are triggered only when flying above FL 240, going off below such altitude, it may be a spurious message associated with an improper operation of the fire extinguishing bottle pressure switch. In this case, replace the task above by the following check: − Perform once a continuity and isolation check on the wiring from the GS0827DC to the pin # A-14/ connector J1018 (DAU-2) and from GS0826DC to the pin # A-14/ connector J1020 (DAU-2). Wiring Manual (WM) references 26-21-50 and 26-21-51. Check no fault found.
Page
1-09-26
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
Engine Fire Extinguishing Bottles Pressure Check: The respective manometers of the affected extinguisher bottles must be checked before the first flight of each calendar day. For dispatch purpose the fire extinguisher bottles minimum pressure must be higher then values presented on the table below. Temperature °C
°F
Gauge Pressure Indication Minimum Pressure (psi)
-54 to -40
-65 to -40
300
-29
-20
350
-18
0
400
-7
20
450
4
40
500
16
60
550
21 to 27
70 to 80
600
38
100
700
49
120
800
60
140
900
Page
REVISION 6
1-09-26
Code
5 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
26-22-00 APU FIRE EXTINGUISHING SYSTEM Number installed Number required for dispatch
-22-00 APU Fire Extinguishing System
C 1
0
(O) May be inoperative provided APU is considered inoperative and not used.
Placard APU Panel "APU FIRE EXTING INOP - DO NOT USE APU". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES None.
26-22-01 APU EXTBTL INOP CAUTION MESSAGE Number installed Number required for dispatch
-22-01 APU EXTBTL INOP Caution Message
C 1
0
C 1
0
(M) May be inoperative provided an alternate procedure is used once each flight day to verify that APU extinguisher bottle is operational. May be inoperative provided APU is considered inoperative and not used.
Placard APU Fire Detection/Extinguishing Panel "APU EXTBTL INOP NOT AVAIL". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Perform TASK 26-22-00-700-801-A or 26-22-00-700-802-A (AMM) for testing the APU Fire Extinguishing System.
Page
1-09-26
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
26-23-00 BAGGAGE COMPARTMENT FIRE EXTINGUISHER SYSTEM Number installed Number required for dispatch
-23-00 Baggage Compartment Fire Extinguisher System
C 1
0
May be inoperative provided cargo compartment remains empty. NOTE: Does not preclude the carriage of empty cargo containers, pallets, ballast, etc.
Placard Fire Detection/Extinguishing Panel "BAGG EXTG INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-26
Code
7 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
26-23-01 PORTABLE FIRE EXTINGUISHERS Number installed Number required for dispatch
-23-01 Portable Fire Extinguishers
D -
-
Any in excess of those required by FAR may be inoperative or missing, provided: a) The inoperative fire extinguisher is tagged inoperative, removed from the installed location, and placed out of sight so it can not be mistaken for a functional unit, and b) Required distribution is maintained.
Placard the associated portable fire extinguisher "REMOVED", near its normal storage place.
"INOP"
or
OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-26
Code
8 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
26-25-00 LAVATORY FIRE EXTINGUISHER SYSTEMS Number installed Number required for dispatch
-25-00 Lavatory Fire Extinguisher Systems
C -
-
For each lavatory, the lavatory fire extinguisher system may be inoperative provided Lavatory Smoke Detector system operates normally.
C -
-
(M) (O) For each lavatory, the lavatory fire extinguisher system may be inoperative provided: a) Lavatory waste receptacle is empty, b) Lavatory door is locked, closed and placarded, "INOPERATIVE - DO NOT ENTER", and c) Lavatory is used only by crewmembers. NOTE: 1) These provisos are not intended to prohibit lavatory use or inspections by crewmembers. NOTE: 2) A lavatory fire extinguisher system is not required for all-cargo operations.
Placard lavatory door "INOPERATIVE - DO NOT ENTER", if applicable.
Page
REVISION 6
1-09-26
Code
9 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
OPERATIONAL PROCEDURES Lavatory Smoke Detector System Test: TEST Button..................................................................PRESS Check that the following test indications are activated: − SMOKE red alarm light on the lavatory smoke detector panel. − Horn activated on lavatory smoke detector panel. − LAV SMOKE warning message on EICAS. − Normal operation green light extinguished. HORN RESET Button ...................................................PRESS MAINTENANCE PROCEDURES Check that lavatory waste receptacle is empty.
26-25-01 GALLEY FIRE EXTINGUISHER SYSTEM Number installed Number required for dispatch
-25-01 Galley Fire C 1 *** Extinguisher System
0
Placard galley door "GALLEY EXTG INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-26
Code
10 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 27 FLIGHT CONTROLS 27-10-01 AILERON DAMPERS Number installed Number required for dispatch
-10-01 Aileron Dampers
C 2
0
(M) May be inoperative provided: a) The affected damper(s) is deactivated and, b) Visual inspection of the affected PCA rod ends and fittings are performed according to the latest approved revision of the AD 99-05-04.
Placard Aileron Damper "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Aileron Damper Deactivation: Perform TASK 27-12-03 (RAMP) for Aileron Damper Deactivation. Aileron Damper Visual Inspection: Perform the visual inspection of the affected PCA rod ends and fittings according to the lasted approved revision of the AD 99-05-04.
Page
REVISION 6
1-09-27
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
27-14-00 ROLL TRIM POSITION INDICATION Number installed Number required for dispatch
-14-00 Roll Trim Position Indication
C 1
0
(O) May be inoperative provided: a) Roll trim is verified to be centered before each departure, and b) Yaw trim position indication operates normally.
Placard Roll Trim Switch "POSITION INDICATION INOP". OPERATIONAL PROCEDURES Aileron in Neutral Position check: − − − − − − − −
Airplane ....................................................... DEENERGIZED Control Wheels............................................ NEUTRAL POSITION Ailerons ....................................................... NEUTRAL POSITION Airplane ....................................................... ENERGIZE Roll Trim Switch .......................................... RELEASED Electric Hydraulic Pumps ............................ ON Control Wheels............................................ NEUTRAL POSITION Ailerons ....................................................... NEUTRAL POSITION
MAINTENANCE PROCEDURES None.
Page
1-09-27
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
27-15-00 AILERON DISCONNECTION LIGHT Number installed Number required for dispatch
-15-00 Aileron C 1 Disconnection Light
0
(O) May be inoperative provided a check is made before each takeoff to verify that both ailerons are connected.
Placard AIL DISC Caution Light "INOP". OPERATIONAL PROCEDURES Aileron Mechanical Interconnection check: Left Control Wheel ........................................... HOLD FIRMLY IN NEUTRAL POSITION Right Control Wheel......................................... TRY TO TURN LEFT AND RIGHT If relative movement between both control wheels is not observed, then the aileron mechanical interconnection is connected. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-27
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
27-21-03 PEDALS ADJUSTMENT MECHANISM Number installed Number required for dispatch
-21-03 Pedal Adjustment Mechanisms
C 2
0
(M)(O) May be inoperative provided rudder pedals can be adjusted to suit individual pilot requirements and is acceptable to the flight crewmember.
Placard associated Pedal Adjustment Switch "INOP". OPERATIONAL PROCEDURES With seats adjusted, check pedals for full travel. If the extreme pedal positions can not be reached, readjust the seat or report to the maintenance personnel for pedal adjustment. MAINTENANCE PROCEDURES − − − −
Make sure that the aircraft is safe for maintenance. Do not do other tasks on the rudder system. Make sure the CB0383 (E5) is opened. Remove cockpit underfloor access hatch 123BL (AMM 06-41-01/101). − In the interconnection pedal assembly, locate the pedal regulator guide. Inside the guide there will be a pedal regulator spindle. Using an 1/4" wrench, turn slowly clockwise or counterclockwise to move the rudder pedal assembly forward or rearward to suit the pilot requirements. NOTE: Make sure that the 1/4" wrench fits in the protruded end of the spindle to avoid any damage to the component.
Page
1-09-27
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
RUDDER ADJUSTMENT MECHANISM BELLCRANK
Page
REVISION 6
1-09-27
Code
5 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
− Once finished the adjustment, install cockpit underfloor access hatch 123BL (AMM 06-41-01/101). − Close CB0383 (E5) and return the aircraft back to service.
27-24-01 YAW TRIM POSITION INDICATIONS Number installed Number required for dispatch
-24-01 Yaw Trim Position Indications
C 1
0
(O) May be inoperative provided: a) Yaw trim is verified to be centered before each departure, and b) Roll trim position indication operates normally.
Placard YAW TRIM Knob "INOP". OPERATIONAL PROCEDURES Rudder in Neutral Position check: − − − − − − − −
Airplane ....................................................... DEENERGIZED Rudder Pedals............................................. NEUTRAL POSITION Rudder......................................................... NEUTRAL POSITION Airplane ....................................................... ENERGIZE Yaw Trim Knob............................................ RELEASED Electric Hydraulic Pumps ............................ ON Rudder Pedals............................................. NEUTRAL POSITION Rudder......................................................... NEUTRAL POSITION
MAINTENANCE PROCEDURES None.
Page
1-09-27
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
27-35-00 ELEVATOR DISCONNECTION LIGHT Number installed Number required for dispatch
-35-00 Elevator C 1 Disconnection Light
0
(O) May be inoperative provided a check is made before each takeoff to verify that both elevators are connected.
Placard ELEV DISC Light "INOP". OPERATIONAL PROCEDURES Elevator Mechanical Interconnection check: Left Control Column ......................................... HOLD FIRMLY IN NEUTRAL Right Control Column....................................... TRY TO MOVE FORWARD AND BACKWARD If relative movement between both control columns is not observed, then the elevator mechanical interconnection is connected. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-27
Code
7 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
27-36-01 SPS/ICE SPEEDS ADVISORY MESSAGE Number installed Number required for dispatch
-36-01 SPS/ICE SPEEDS Advisory Message
C 1
0
May be inoperative provided airplane is not operated in known or forecast icing conditions.
C 1
0
(O) May be inoperative provided AFM abnormal procedure "ADVANCED STALL PROTECTION" is followed.
Placard SPS/ICE SPEEDS Message "INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES None.
27-36-03 STICK SHAKERS Number installed Number required for dispatch
-36-03 Stick Shaker
B
2
1
Placard Stall Protection System Panel "SHAKER 1 (or 2) INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-27
Code
8 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
27-40-01 PITCH TRIM POSITION INDICATION Number installed Number required for dispatch
-40-01 Pitch Trim Position Indication
B
1
0
(O) May be inoperative provided stabilizer is set by means of markings on vertical stabilizer prior to each departure.
Placard near Pitch Trim Cut-out Buttons "POSITION IND INOP". OPERATIONAL PROCEDURES Check that stabilizer is correctly set according to CG position by looking at pitch trim marks on vertical stabilizer. NOTE: The thick marks represent, respectively, 4° nose down (top of the scale), neutral, and 10° nose up (bottom of the scale) and each intermediate marks represent a 2° variation (See Figure).
PITCH TRIM MARKS MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-27
Code
9 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
27-53-00 FLAP CHANNELS Number installed Number required for dispatch
-53-00 Flap Channels
B
2
1
(M)(O) One may be inoperative provided with FLAP LOW SPEED advisory message present provided: a) There are no obstacles in the Takeoff Flight Path above Level Off Height, and b) Motor and brakes of failed channel are deactivated. NOTE: Flaps will operate at half speed.
Placard near Flap Selector Lever "CHANNEL 1 (or 2) INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES Flap Channel deactivation: − Gain access to the Flap Electronic Control Unit (FECU) through the wing fairing rear panel. − Disconnect and stow the affected electrical connector: P1101 (Channel 1) or P1102 (Channel 2). − Perform TASK 45-45-00-970-801-A (AMM) for the CMC downloading with the MFD maintenance page. Log the CMC message and the operational conditions associated with the occurrence. Reset of the Flap Electronic Control Unit for airplanes equipped with FECU PN 363100-1009: Airplanes equipped with FECU P/N 363100-1009 can trigger the "SPS ADVANCED" message when operating with one flap channel inoperative. In order to eliminate or avoid this message the following procedure should be accomplished before each flight:
Page
1-09-27
Code
10 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
− With the aircraft on the ground and energized, command the Flaps to the zero position. − Reset the Flap Electronic Control Unit (FECU) as follow: − Open the Circuit Breaker Flap1 (F16) and Flap 2 (F19) on the Circuit Breaker Panel. − Check that "FLAP LOW SPEED" message will disappear and "FLAP FAIL" message will come into view on the EICAS. − Close the Circuit Breaker Flap1 (F16) and Flap 2 (F19) on the Circuit Breaker Panel. The "FLAP FAIL" message will disappear and "FLAP LOW SPEED" message will come into view. − Reset the Integrated Computer (IC) as follow: − Open the Circuit Breaker IC 1 (C3) and IC 2 (D31) on the Circuit Breaker Panel and disconnect (release) the Backup Battery push button on the Electrical Overhead Panel. Make sure that the white strip bar is on. − The MFD’s, PFD’s and the EICAS display will show a red “X”. − Close the Circuit Breaker IC 1 (C3) and IC 2 (D31) on the Circuit Breaker Panel and connect (press) the Backup Battery push button on the Electrical Overhead Panel. Make sure that the white strip bar is off. − Check that the MFD’s, PFD’s and the EICAS display are operating normally. − Make sure that the “SPS ADVANCED” and “FLAP FAIL” messages are not displayed on EICAS. NOTE: Reset procedure shall be repeated if the flaps were commanded before initiating taxi out.
Page
REVISION 6
1-09-27
Code
11 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
27-70-00 GUST LOCK SYSTEM Number installed Number required for dispatch
-70-00 Gust Lock System 1) Mechanical System
C 1
0
2) ElectroMechanical System
C 1
0
a) GUST LOCK Amber Lights
C 2
1
(M)(O) May be inoperative provided system is secured unlocked. NOTE: Appropriate measures should be taken to prevent damage from gusts while on the ground. (M)(O) May be inoperative provided: a) System is deactivated unlocked such that locking pins cannot engage the elevator, and b) GUST LOCK amber lights are masked. NOTE: Appropriate measures should be taken to prevent damage from gusts while on the ground.
For airplanes equipped with Mechanical Gust Lock System: Placard Gust Lock Lever "INOP". For airplanes equipped with Electromechanical Gust Lock System: Placard Gust Lock Lever "INOP" and/or placard affected Gust Lock Amber Light "LIGHT INOP". OPERATIONAL PROCEDURES Carefully check elevators are free to move from full forward to full rearward positions. Obtain confirmation from maintenance personnel to check surface full travel.
Page
1-09-27
Code
12 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
MAINTENANCE PROCEDURES For airplanes equipped with Mechanical Gust Lock System: − Gain access to the Gust Lock system (Refer to AMM 06-4101/101). − Check the connecting rod 1 for proper attachment (See Figure). − Check the crank 1, tension spring and gust lock torque tube for distortion, proper movement and loosing parts. − Check the connecting rod 2 for proper attachment. NOTE: If any connecting rod or related attachment are found damaged, remove the part. − Check the elevator right forward torque tube for distortion, proper movement and loosing parts. NOTE: − To avoid damage to the flight control system when the gust lock is disengaged, the aircraft must be parked in areas not subjected to gust, such as inside a hangar. − Perform TASK 5-50-04-200-802-A before the reactivation of the Gust Lock system. − Perform TASK 5-50-04-200-802-A before takeoff if the airplane has been exposed to wing gusts on ground with the Gust Lock system inoperative.
Page
REVISION 6
1-09-27
Code
13 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
MECHANICAL GUST LOCK SYSTEM
Page
1-09-27
Code
14 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
For airplanes equipped with Electromechanical Gust Lock System: − Pull the Air/Ground D circuit breaker (A29) and attach a DO-NOTCLOSE tag to it. − Move the gust lock lever to unlocked position (full forward). − If the lever does not move: − Perform TASK 27-71-06-900-801-A (AMM) to manually unlock the electromechanical Gust Lock. − If the solenoid rod cannot be moved: − Perform TASK 27-71-06-000-801-A (AMM) to remove the Gust Lock solenoid. − After moving the Gust Lock lever to unlocked position, perform TASK 27-71-06-400-801-A (AMM) to install the Gust Lock solenoid. − Move the control column backward and forward full stroke. − If the control column cannot be moved: − Perform TASK 27-71-00-200-801-A (AMM) to do a detailed visual inspection on the electromechanical Gust Lock mechanism. Check for broken, locked or jammed parts. − Perform TASK 27-71-01-000-801-A (AMM) to remove the electromechanical Gust Lock actuator located at the tail torque box. − Perform TASK 27-71-07-400-801-A (AMM) to install the Gust Lock actuator locking device to keep the locking pins in the unlocked position. − Try to move the Gust Lock lever to locked position with the column in the full forward position, making sure that locking does not occur. − Pull and collar the Gust Lock circuit breaker (F24). − The GUST LOCK Amber Lights will illuminate and must be masked. − Push back in the Air/Ground D circuit breaker (A29) and remove the DO-NOT-CLOSE tag from it. NOTE: − To avoid damage to the flight control system when the gust lock is disengaged, the aircraft must be parked in areas not subjected to gust, such as inside a hangar. − Perform TASK 5-50-04-200-802-A before the reactivation of the Gust Lock system. − Perform TASK 5-50-04-200-802-A before takeoff if the airplane has been exposed to wing gusts on ground with the Gust Lock system inoperative.
Page
REVISION 6
1-09-27
Code
15 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-09-27
Code
16 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 28 FUEL 28-11-02 SUMP DRAIN VALVES Number installed Number required for dispatch
-11-02 Sump Drain Valves
C -
-
(M) One per fuel tank system (WING or FUS 1 or FUS 2) may be inoperative provided: a) There is no evidence of leakage, and b) No water contamination in the other associated tank is verified before the first departure of each flight day.
Placard affected Drain Valve Panel "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Check visually the affected valve for no evidence of leakage and no water contamination in the other associated tank. Refer to Ramp Maintenance Manual 12-11-03.
Page
REVISION 6
1-09-28
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
28-11-05 FUELING RECEPTACLE CAP Number installed Number required for dispatch
-11-05 Fueling Receptacle Cap
C 1
0
(M) May be inoperative (missing) provided: a) Refueling receptacle is visually checked for contamination before each refueling, and b) No leakage can be detected after refueling is completed.
Placard near refueling receptacle "CAP REMOVED". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Before refueling check the receptacle. Make sure there is no contamination. After refueling make sure there is no evidence of leakage.
Page
1-09-28
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
28-21-01 WING TANK ELECTRIC FUEL BOOSTER PUMPS Number installed Number required for dispatch
-21-01 Wing Tank Electric Fuel Booster Pumps
C 6
4
(M) (O) One pump per tank may be inoperative provided: a) Remaining two pumps operate normally, b) If the pumps 1C and 2C are inoperative, the message ELEC EMERG ABNORMAL must be verified to operate normally before departure, c) Affected electric fuel booster pump is deactivated, and d) AFM limitations regarding unusable fuel are accounted for.
Placard affected Fuel Pump Selector Knob "PUMP A (or B or C) INOP". OPERATIONAL PROCEDURES ELEC EMERG ABNORMAL message check: If GPU is available: − GPU .................................................................... ON − ESSENTIAL POWER Button .............................. PRESS − ELEC EMERG ABNORMAL Message ............... CHECK ON − ESSENTIAL POWER Button .............................. RELEASE − ELEC EMERG ABNORMAL Message ............... CHECK OFF
Page
REVISION 6
1-09-28
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
If GPU is not available: − APU or ENGINE (only one) .................................START − APU or ENGINE Generator.................................ON − ESSENTIAL POWER Button ..............................PRESS − ELEC EMERG ABNORMAL Message................CHECK ON − ESSENTIAL POWER Button ..............................RELEASE − ELEC EMERG ABNORMAL Message................CHECK OFF If any electric fuel booster pump is inoperative, the unusable fuel quantity in the associated wing raises as presented in the table below. Therefore, additional fuel should be considered for flight planning purposes. EMB-135/145 LR/LU/BJ
AIRPLANE MODEL Unusable fuel quantity
Up to 203 liters (364 lb)
MAINTENANCE PROCEDURES Electric Fuel Booster Pump Deactivation procedure: In the DC distribution boxes, open and safety the affected Electric Fuel Booster Pump circuit breakers: DISTRIBUTION BOX LEFT SIDE
RIGHT SIDE
PUMP 1A 1C 2B 1B 2A 2C
CIRCUIT BREAKER A3 C4 A4 A2 A3 C4
NOTE: Some airplanes may present a different circuit breaker positioning configuration. Specific configurations may be found in the Aircraft Maintenance Manual (AMM).
Page
1-09-28
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
28-21-02 WING TANK ELECTRIC FUEL BOOSTER PUMP OPERATING INDICATIONS Number installed Number required for dispatch
-21-02 Wing Tank Electric Fuel Booster Pump Operating Indications
C 6
4
(M) One per side may be inoperative provided associated pump is verified to operate normally before departure.
Placard affected Fuel Pump Selector Knob "PUMP A (or B or C) IND. INOP". OPERATIONAL PROCEDURES Electric Fuel Booster Pump normal operation check: − − − − − −
− −
− −
Airplane .................................................................... ENERGIZE Wing Tanks.............................................................. NOT EMPTY Associated Engine ................................................... START MFD Fuel Page........................................................ SET Affected Pump ......................................................... SELECT Perform the following check: • No MFD pump operation indication. • No caution message FUEL LO PRESS displayed on the EICAS. • No CAUTION light or aural caution alarm. Affected Pump Circuit Breaker ................................ PULL Perform the following check: • Associated caution message displayed on the EICAS. • Master Caution light blinking. • Aural Warning sounding. • MFD indication changing to another pump. Affected Pump Circuit Breaker ................................ CLOSE Check the airplane returning to the original condition.
MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-28
Code
5 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
28-21-03 FORWARD AUXILIARY TANK ELECTRIC FUEL TRANSFER PUMPS Number installed Number required for dispatch
-21-03 Forward Auxiliary Tank Electric Fuel Transfer Pumps
B
4
D 4
0
0
(M) (O) May be inoperative provided: a) Affected FUS Auxiliary Fuel System(s) (forward plus aft tank) contain no more than 1764 lb (800 kg) total, b) Any fuel in the affected FUS Auxiliary Fuel System(s) is considered unusable, is treated as ballast fuel, and is included in the calculation of takeoff weight and CG position for takeoff, and c) Affected electric fuel transfer pumps are deactivated. (M) May be inoperative provided: a) Forward and Aft Tanks of the affected FUS Auxiliary Fuel System remain empty, and b) Affected electric fuel transfer pumps are deactivated.
Placard affected Forward Auxiliary Tank Electric Fuel Transfer Pump "A (B) FUS 1(2) INOP". If two forward auxiliary tank electric fuel transfer pumps in one FUS fail, placard "FUS 1(2) INOP".
Page
1-09-28
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
OPERATIONAL PROCEDURES Check of Forward Auxiliary Tank Electric Fuel Pumps Operation and Indication: NOTE: It is only possible to turn on the forward auxiliary tank electric fuel transfer pump when the wing fuel quantity is less than 4189 lb. If the wing fuel quantity is more than 4189 lb, perform a defueling procedure according with DDPM maintenance procedure 28-21-03. − − − − −
Airplane ............................................................... ENERGIZE Fuel in the wing ................................................... LESS THAN 4189 lb MFD Fuel Page................................................... SET FUS 1 or FUS 2 .................................................. SELECT Forward Auxiliary Tank Electric Pump (A or B)... SELECT Check MFD forward auxiliary tank electric pump indication. − FUS 1 or FUS 2 .................................................. TURN OFF Pre-flight Fuel Quantity and Balance Check: a) Dispatch with one forward auxiliary tank electric fuel transfer pump inoperative. When dispatch the airplane with one Forward Auxiliary Tank Electric Transfer Pump inoperative, check if the fuel quantity in WING tanks (and remaining FUS tanks, if applicable) is adequate to reach a suitable airport if remaining pump fails any time. A previous flight plan is required for this condition. NOTE: If during flight the remaining forward auxiliary tank electric pump of affected FUS fuel system fails, check the affected FUS tanks total fuel quantity after remaining pump fails. If the fuel total quantity is greater than 1764 lb, plan to land the airplane before fuel quantity in any WING tank reaches 2204 lb. b) Dispatch with two forward auxiliary tank electric fuel transfer inoperative from the same forward auxiliary tank. Any fuel in the affected FUS Fuel System is considered unusable and must be treated as ballast fuel. Include the remaining fuel of the affected FUS tanks in the calculation of takeoff weight and C.G. position for takeoff. If in the unable FUS tank system remain more than 1764 lb total quantity fuel, perform defueling procedure.
Page
REVISION 6
1-09-28
Code
7 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
MAINTENANCE PROCEDURES Deactivate Pumps Procedure: When one Forward Auxiliary Tank Electric Transfer Fuel Pump fails, deactivate it in accordance with Maintenance Manual procedure 28-26-01. Auxiliary Tanks Defueling Procedure: Defueling procedure for inoperative FUS tank system is performed through the drains of FUS tanks system (see figure). Perform defueling procedure as follows:
− −
Put the draining device below the drain valve. Open the drain valve with the draining device. To do this, push the draining device and give it a one-quarter turn counterclockwise. − Drain enough fuel until to reach the dispatch condition and close the drain valve. To do this, give it a one-quarter turn in the opposite direction. NOTE: Forward Auxiliary Tank must be loaded with 309 lb moreover than aft tank.
Page
1-09-28
Code
8 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
28-21-04 FORWARD AUXILIARY TANK ELECTRIC FUEL TRANSFER PUMPS OPERATING INDICATIONS Number installed Number required for dispatch
-21-04 Forward Auxiliary Tank Electric Fuel Transfer Pumps Operating Indications
C 4
0
D 4
0
(M) May be inoperative provided: a) Associated pump is verified to operate normally before departure, and b) EICAS messages FUEL XFER INOP and FUSELAGE FUEL IMB are verified to operate normally. May be inoperative provided Forward and Aft Tanks of the affected FUS Auxiliary Fuel System remain empty.
Placard "FWD AUX TK XFER PUMPS IND INOP". OPERATIONAL PROCEDURES Check of associated Forward Auxiliary Electric Fuel Transfer pump operation: NOTE: It is only possible to turn on the forward auxiliary tank electric fuel transfer pump when the wing fuel quantity is less than 4189 lb. If the wing fuel quantity is more than 4189 lb, perform a defueling procedure according with DDPM item 28-21-03. − − − − −
Airplane ............................................................... ENERGIZE Fuel in the wing ................................................... LESS THAN 4189 lb MFD Fuel Page................................................... SET FUS 1 or FUS 2 .................................................. SELECT Forward Auxiliary Tank Electric Pump (A or B)... SELECT Check if Forward Auxiliary Tank Fuel Quantity Indication on MFD or EICAS runs normally indicating fuel transfer operation. − FUS 1 or FUS 2 .................................................. TURN OFF
Page
REVISION 6
1-09-28
Code
9 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
MAINTENANCE PROCEDURES Check of FUEL XFER INOP and FUSELAGE FUEL IMB messages: Refer to DDPM item 28-21-08 to check FUEL XFER INOP and FUSELAGE FUEL IMB messages. Forward Auxiliary Tanks Defueling Procedure: Refer to DDPM maintenance procedure 28-21-03 for defueling operation.
Page
1-09-28
Code
10 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
28-21-05 AFT AUXILIARY TANK ELECTRIC FUEL TRANSFER PUMPS Number installed Number required for dispatch
-21-05 Aft Auxiliary Tank Electric Fuel Transfer Pumps
B
2
0
(M) (O) May be inoperative provided: a) Affected FUS Auxiliary Fuel System(s) are not used, b) Affected FUS Auxiliary Fuel System(s) (forward plus aft tank) contain no more than 1764 lb (800 kg) total, c) Any fuel in the affected FUS Auxiliary Fuel System is considered unusable, is treated as ballast fuel, and is included in the calculation of Takeoff weight and C.G. position for takeoff, and d) Affected electric fuel transfer pumps are deactivated.
D 2
0
(M) May be inoperative provided: a) Forward and Aft Tanks of the affected FUS Auxiliary Fuel System remain empty, and b) Affected electric fuel transfer pumps are deactivated.
Placard "FUS 1 (2) INOP" if Aft Auxiliary Tank Electric Transfer Pump in one FUS fail.
Page
REVISION 6
1-09-28
Code
11 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
OPERATIONAL PROCEDURES According the MMEL remarks. NOTE: Before the flight, fuel quantity and balance must be checked. Forward tank must be loaded with 309 lb moreover than aft tank. MAINTENANCE PROCEDURES Deactivate Pumps Procedure: Deactivate affected aft auxiliary tank electrical pump according with Ramp Maintenance Manual 28-26-01. Aft Auxiliary Tanks Defueling Procedure: Refer to DDPM maintenance procedure 28-21-03 for defueling operation. NOTE: - When dispatching airplane with FUS 1(2) inoperative, no more than 1764 lb must be maintained in the affected FUS Auxiliary Fuel System (considering forward plus aft auxiliary tank). If in the unable FUS tank system contain more than 1764 lb, perform defueling procedure. - Forward Auxiliary Tank must be loaded with 309 lb moreover than aft tank.
Page
1-09-28
Code
12 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
28-21-06 AFT AUXILIARY TANK ELECTRIC FUEL TRANSFER OPERATING INDICATIONS Number installed Number required for dispatch
-21-06 Aft Auxiliary Tank Electric Fuel Transfer Pumps Operating Indications
C 2
0
(M) May be inoperative provided: a) Associated pump is verified to operate normally before departure, and b) EICAS messages FUEL XFER INOP and FUSELAGE FUEL IMB are verified to operate normally.
D 2
0
May be inoperative provided Forward and Aft Tanks of the affected FUS Auxiliary Fuel System remain empty.
Placard "AFT TK XFER IND INOP". OPERATIONAL PROCEDURES Check of associated Aft Auxiliary Tank Electric Fuel Transfer pump operation: NOTE: It is only possible to turn on the aft auxiliary tank electric fuel transfer pump when the wing fuel quantity is less than 4189 lb. If the wing fuel quantity is more than 4189 lb, perform a defueling procedure according with DDPM item 28-21-03. − − − −
Airplane ............................................................... ENERGIZE Fuel in the wing ................................................... LESS THAN 4189 lb MFD Fuel Page................................................... SET FUS 1 or FUS 2 .................................................. SELECT Check if Aft Auxiliary Tank Fuel Quantity Indication on MFD or EICAS runs normally indicating fuel transfer operation. − FUS 1 or FUS 2 .................................................. TURN OFF
Page
REVISION 6
1-09-28
Code
13 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
MAINTENANCE PROCEDURES Check of FUEL XFER INOP and FUSELAGE FUEL IMB messages: Refer to DDPM item 28-21-08 to check FUEL XFER INOP and FUSELAGE FUEL IMB messages. Aft Auxiliary Tanks Defueling Procedure: Refer to DDPM maintenance procedure 28-21-03 for defueling operation.
Page
1-09-28
Code
14 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
28-21-07 AFT AUXILIARY TANK PRESSURIZED FUEL TRANSFER SYSTEMS Number installed Number required for dispatch
-21-07 Aft Auxiliary Tank Pressurized Fuel Transfer Systems
B
2
0
(M) (O) May be inoperative provided: a) Affected FUS Auxiliary Fuel System(s) are not used, b) Flight is conducted in an unpressurized configuration, at or below 10000 ft MSL, c) Affected FUS Auxiliary Fuel System(s) (forward plus aft tank) contain no more than 1784 lb (800 kg) total, and d) Any fuel in the affected FUS Auxiliary Fuel Systems is considered unusable, is treated as ballast fuel, and is included in the calculation of Takeoff weight and C.G. position for takeoff. (O) May be inoperative provided: a) Forward and Aft Tanks of the affected FUS Auxiliary Fuel System remain empty, and b) Flight is conducted in an unpressurized configuration, at or below 10000 ft MSL.
Placard "PRESSURIZED FUEL XFER SYS 1(2) INOP". Page
REVISION 6
1-09-28
Code
15 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
OPERATIONAL PROCEDURES Check of Aft Auxiliary Tank Electric Fuel Transfer Pumps to Operation and Indication on MFD: NOTE: It is only possible to operate the auxiliary tank electric fuel transfer pumps when the wing fuel quantity is less than 4189 lb or when the switch WING, on Maintenance Panel located behind of captain seat, is moved up (it transfer fuel during only for 10 seconds to perform testing on FUS selected). − Airplane ...............................................................ENERGIZE − Fuel in the wing ...................................................LESS THAN 4189 lb − MFD Fuel Page ...................................................SET − FUS 1 or FUS 2...................................................SELECT − Forward Auxiliary Tank Electric Pump (A or B)...SELECT Check MFD aft auxiliary tank electric fuel transfer pump indication. − FUS 1 or FUS 2...................................................TURN OFF Flight in Unpressurized Configuration: − Outflow Valves ....................................................OPEN Outflow valves may be kept open through one of the following ways: − Pressurization Dump Button ..........................PRESSED OR − Pressurization Mode Selector Button.............PRESSED − Manual Controller Knob .................................UP − Bleed Air Buttons.................................................AS REQUIRED − Pack Buttons .......................................................AS REQUIRED − Recirculation Fans...............................................AS REQUIRED − Altitude ................................................................10000 FT MAINTENANCE PROCEDURES Defueling Procedure: Refer to DDPM Maintenance Procedure 28-21-03. NOTE: - When dispatching airplane with FUS 1(2) inoperative, no more than 1764 lb must be maintained in the affected FUS Auxiliary Fuel System (considering forward plus aft auxiliary tank). If in the unable FUS tank system contain more than 1764 lb, perform defueling procedure. - Forward Auxiliary Tank must be loaded with 309 lb moreover than aft tank.
Page
1-09-28
Code
16 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
28-21-08 AFT AUXILIARY TANK PRESSURIZED FUEL TRANSFER SYSTEM OPERATING INDICATIONS Number installed Number required for dispatch
-21-08 Aft Auxiliary Tank Pressurized Fuel Transfer System Operating Indications
C 2
0
D 2
0
(M) (O) May be inoperative provided: a) Associated aft vent/relief shutoff valve operates normally, b) Both Air Conditioning Packs operate normally, and c) EICAS messages FUEL XFER INOP and FUSELAGE FUEL IMB are verified to operate normally. May be inoperative provided Forward and Aft Tanks of the affected FUS Auxiliary Fuel System remain empty.
Placard "PRESSURIZED FUEL XFER SYS OP INDICATION INOP". OPERATIONAL PROCEDURES Air Conditioning Packs Check: − Airplane .................................................................... ENERGIZE − Bleed 1(2) or APU.................................................... OPEN − Pack 1 ...................................................................... ON Check if air flow is cycling normally. − Pack 1 ...................................................................... OFF − Pack 2 ...................................................................... ON Check if air flow is cycling normally. − Pack 2 ...................................................................... OFF
Page
REVISION 6
1-09-28
Code
17 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
MAINTENANCE PROCEDURES Auxiliary Tanks Defueling Procedure: Refer to DDPM procedure 28-21-03 for defueling operation. Check of Aft Vent Valve and Relief Shutoff Valve: To check if Aft Vent Valve from one FUS is operating normally, verify if the message FUEL TANKS VENT OPEN is not displayed on EICAS after fueling operation. During fueling operation or, when the air conditioned packs are turned off or, when the airplane is not energized, or when airplane is in flight unpressurized below than 10000 ft, the Aft Auxiliary Tank Vent Valve must be on open position. To check if Relief Shutoff Valve operates normally, refer to AMM TASK 28-14-00-700-801–A. Check of FUEL XFER INOP and FUSELAGE FUEL IMB messages: a) To check if FUEL XFER INOP message displays normally on EICAS: − Pull the circuit breakers on overhead panel from the associated system to deactivate transfer pumps. − Any auxiliary tank must have some remain fuel quantity to be transferred. − Move up WING switch (see figure below), on Maintenance Panel located behind of captain seat. b) To check if FUSELAGE FUEL IMB message displays normally on EICAS: − Move the switch to select FUS 1(2) (see figure below), on Maintenance Panel located behind of captain seat. It simulates an imbalance condition between forward and aft tank from the FUS selected.
Page
1-09-28
Code
18 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
MAINTENANCE PANEL
Page
REVISION 6
1-09-28
Code
19 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
28-21-09 FORWARD AUXILIARY TANK PRESSURIZED FUEL TRANSFER SYSTEM OPERATING INDICATIONS Number installed Number required for dispatch
-21-09 Forward Auxiliary Tank Pressurized Fuel Transfer System Operating Indications
C 2
0
D 2
0
(M) (O) May be inoperative provided: a) Associated Forward Auxiliary Tank fuel quantity indicator operates normally, b) Associated Fuel Transfer System operates normally, and c) EICAS messages FUEL XFER INOP and FUSELAGE FUEL IMB are verified to operate normally. May be inoperative provided Forward and Aft Tanks of the affected FUS Auxiliary Fuel System remain empty.
Placard "FWD AUX TANK FUEL XFER OP INDICATION INOP". OPERATIONAL PROCEDURES Check of Forward Auxiliary Tank Fuel Quantity Indication: Check if Forward Auxiliary Tank Fuel Quantity Indication on MFD or EICAS operates normally. Check of Forward Auxiliary Tank Fuel Transfer Indication: Check if Forward Auxiliary Tank Fuel Quantity Indication on MFD or EICAS runs normally indicating fuel transfer operation. MAINTENANCE PROCEDURES Auxiliary Tanks Defueling Procedure: Refer to DDPM Maintenance procedure 28-21-03 for defueling operation. Check of FUEL XFER INOP and FUSELAGE FUEL IMB messages: Refer to DDPM 28-21-08 to check FUEL XFER INOP and FUSELAGE FUEL IMB messages. Page
1-09-28
Code
20 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
28-21-10 AFT AUXILIARY TANK FUEL TRANSFER OPERATING INDICATIONS Number installed Number required for dispatch
-21-10 Aft Auxiliary Tank Fuel Transfer System Operating Indications
C 2
0
(M) (O) May be inoperative provided: a) Associated Aft Auxiliary Tank fuel quantity indicator operates normally, b) Associated Fuel Transfer System operates normally, and
D 2
0
c) EICAS messages FUEL XFER INOP and FUSELAGE FUEL IMB are verified to operate normally. May be inoperative provided Forward and Aft Tanks of the affected FUS Auxiliary Fuel System remain empty.
Placard "AFT AUX TANK FUEL XFER OP INDICATION INOP". OPERATIONAL PROCEDURES Check of Aft Auxiliary Tank Fuel Quantity Indication and Fuel Transfer System Operation: NOTE: It is only possible to check the Fuel Transfer System operation when the wing fuel quantity is less than 4189 lb or when the switch WING, on Maintenance Panel located behind of captain seat, is moved up (it transfer fuel during only for 10 seconds to perform testing on FUS selected). − − − −
Airplane ............................................................... ENERGIZE Fuel in the wing ................................................... LESS THAN 4189 lb MFD Fuel Page................................................... SET FUS 1 or FUS 2 .................................................. SELECT Check that aft auxiliary tank electric fuel transfer pump indication and quantity indication on MFD runs normally indicating fuel transfer operation. − FUS 1 or FUS 2 .................................................. TURN OFF
Page
REVISION 6
1-09-28
Code
21 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
MAINTENANCE PROCEDURES Auxiliary Tanks Defueling Procedure: Refer to DDPM maintenance procedure 28-21-03 for defueling operation. Check of FUEL XFER INOP and FUSELAGE FUEL IMB messages: Refer to DDPM item 28-21-08 to check FUEL XFER INOP and FUSELAGE FUEL IMB messages.
28-22-01 APU FUEL SHUTOFF VALVE Number installed Number required for dispatch
-22-01 APU FUEL Shutoff Valve
C
1
0
(M)(O) May be inoperative provided: a) APU is considered inoperative, and b) Valve is secured closed.
Placard APU Panel "APU FUEL SHUTOFF VALVE INOP - DO NOT USE APU". OPERATIONAL PROCEDURES According to the MMEL remarks.
Page
1-09-28
Code
22 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
MAINTENANCE PROCEDURES APU Fuel Shutoff Valve secured closed: − − −
Gain access to the valve (AMM - Chapter 28). Remove, insulate and stow the electrical connector. Manually close the valve, through the override lever, locking with a wire. − Pull and safety the APU FUEL SOV circuit breaker (C31).
Page
REVISION 6
1-09-28
Code
23 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
28-23-00 PRESSURE DEFUELING/REFUELING SYSTEM Number installed Number required for dispatch
-23-00 Pressure Defueling/ C Refueling System
1
0
(M) May be inoperative provided airplane is defueled/ refueled by gravity. NOTE: 1) If an overfill condition occurs, it must be corrected prior to departure. NOTE: 2) Does not preclude ventral or auxiliary tanks refueling by fuel transfer procedures on the ground.
Placard Refueling Panel "PRESSURE DEFUELING/REFUELING INOP". OPERATIONAL PROCEDURES Operational procedure associated with overfilling condition. Overfilling Condition: An overfilling condition exists if during the pressure refueling operation there are: − Fuel leakage through the tank ventilation point, or − Illumination of the STOP RFL red light(s) on the refueling panel associated with the fuel tank quantity above the values presented in table 1 (wing tank) or table 2 (auxiliary tanks - EMB-135BJ). NOTE: The STOP RFL light(s) are applicable only to airplanes equipped with High Level Exceeding Indication System.
Page
1-09-28
Code
24 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
Wing Tank Fuel Consumption Procedure: The following procedure should be performed on ground if the corresponding maintenance defueling procedure is not practical or possible to be done. Overfilling in One Tank: With the crossfeed selector knob in LOW1 position (right wing tank overfilling) or in the LOW2 position (left wing tank overfilling) run both engines in IDLE: − During 15 minutes, or − Until the fuel quantity indicated on EICAS/MFD is at or below the values presented in table 1. Overfilling in Both Tanks: With the crossfeed selector knob in OFF position, run both engines in IDLE: − During 30 minutes, or − Until the fuel quantity indicated on EICAS/MFD is at or below the values presented in table 1. Check the fuel balancing between the tanks. MAINTENANCE PROCEDURES Maintenance condition.
procedures
not
associated
with
overfilling
Wing Tank Gravity Refueling Procedure: Perform TASK 12-11-02-600-801-A (AMM) for Fuel Tank Gravity Refueling. Wing Tank Gravity Defueling Procedure: Perform TASK 12-11-01-600-802-A (AMM) for Wing Tank Gravity Defueling. Wing-to-Auxiliary Tanks Fuel Transfer Procedure (EMB-135BJ): Set the MFD 1 (or 2) to the FUEL page (AMM 34-22-00/1) and use the MFD to monitor the fuel quantity which is transferred. A. Transfer the Fuel from the RH Tank to Auxiliary Tanks: − Make sure that the XFEED switch is OFF. − On the fuel control panel, set the fuel-pump selector switch to the fuel pump to be used. − On the circuit breakers panel, open the circuit breakers related to the others pumps that you did not set and attach DO-NOT-CLOSE tag to them.
Page
REVISION 6
1-09-28
Code
25 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
CAUTION: DAMAGE TO THE FUEL PUMP WILL OCCUR IF IT OPERATES WITH NO FUEL (DRY OPERATION). THUS, TURN THE PUMP OFF BEFORE THE TANK IS EMPTY. −
Set the PUMP PWR WING TANK 2 switch to the ON position, and wait approximately 15 seconds. − (For aircraft without maintenance fuel transfer panel) On the FUEL Relay Box, open the applicable circuit breakers and attach DO-NOT-CLOSE tags to them, as related to the tanks that will receive the fuel, as follows: − To transfer to forward tank 1: FWD REF 1. − To transfer to forward tank 2: FWD REF 2. − To transfer to aft tank 1:AFT REF 1. − To transfer to aft tank 2:AFT REF 2. NOTE: Make sure that the WING REF 2 circuit breaker is closed. −
Monitor the decrease of the quantity in the tanks and, when you have the necessary fuel quantity transferred, move the PUMP PWR TANK 2 switch back to OFF.
B. Transfer the Fuel from the LH Tank to Auxiliary Tanks: − Set the XFEED switch in LOW2 position. − On the fuel control panel, set the fuel-pump selector switch to the fuel pump to be used. − On the circuit breakers panel, open the circuit breakers related to the others pumps that you did not set and attach DO-NOT-CLOSE tag to them. CAUTION: DAMAGE TO THE FUEL PUMP WILL OCCUR IF IT OPERATES WITH NO FUEL (DRY OPERATION). THUS, TURN THE PUMP OFF BEFORE THE TANK IS EMPTY. −
Set the PUMP PWR WING TANK 1 switch on the ON position, and wait approximately 15 seconds. − (For aircraft without maintenance fuel transfer panel) On the FUEL Relay Box, open the applicable circuit breakers and attach DO-NOT-CLOSE tags to them, as related to the tanks that will receive the fuel, as follows: − To transfer to forward tank 1: FWD REF 1. − To transfer to forward tank 2: FWD REF 2. − To transfer to aft tank 1: AFT REF 1. − To transfer to aft tank 2: AFT REF 2. NOTE: Make sure that the WING REF 1 circuit breaker is closed.
Page
1-09-28
Code
26 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
−
Monitor the decrease of the quantity in the LH tank and, when you have the necessary fuel quantity transferred, move the PUMP PWR TANK 1 switch back to OFF. − Set the XFEED switch to OFF position. C. When Fuel Transference is Finished: − (For aircraft without maintenance fuel transfer panel) On the fuel Relay Box, close the circuit breaker that you opened in steps above and remove DO-NOT-CLOSE tag from it. − Move the defueling switch back to the closed position and lower the switch guard. Make sure that the DEFUELING light goes off. − Close access door 191BR (AMM 06-41-01/101). − Deenergize the aircraft (TASK 20-40-01-860-801-A (AMM)). Maintenance procedures associated with overfilling condition. Overfilling Condition: An overfilling condition exists if during the pressure refueling operation there are: − Fuel leakage through the tank ventilation point, or − Illumination of the STOP RFL red light(s) on the refueling panel associated with the fuel tank quantity above the values presented in table 1 (wing tank) or table 2 (auxiliary tanks - EMB-135BJ). NOTE: The STOP RFL light(s) are applicable only to airplanes equipped with High Level Exceeding Indication System. Wing Tank Defueling procedure: Remove excess fuel from the wing tanks until the fuel quantity is at or below the values presented in table 1 through one of the following procedure: − Perform TASK 12-11-01-600-802-A (AMM) for Wing Tank Gravity Defueling. − For airplanes equipped with High Level Exceeding Indication System, if an overfilling conditions was indicated by the illumination of the STOP RFL red light, the pressure defueling system is operating normally and the wing defueling may be done through TASK 12-11-01-600-802-A (AMM) Wing Tank Pressure Defueling. Check the fuel balancing between the tanks.
Page
REVISION 6
1-09-28
Code
27 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
TABLE 1 - WING TANK FUEL QUANTITY LIMIT (NOT APPLICABLE TO GRAVITY REFUELING OPERATION) COCKPIT/REFUELING PANEL INDICATION FUEL TEMP (°C)
FUEL TANK QUANTITY (kg) WING (ER) 2030 2030 2020 2010 2000 1990 1980 1970 1960 1950 1940 1930 1930 1920 1910 1900 1890 1880 1870 1870
-40 -35 -30 -25 -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 52
WING (LR and BJ) 2530 2520 2510 2490 2480 2470 2460 2450 2440 2430 2420 2400 2390 2380 2370 2360 2350 2340 2330 2320
FUEL TANK QUANTITY (lb) WING (ER) 4480 4460 4440 4420 4400 4380 4360 4340 4320 4300 4280 4260 4240 4220 4200 4180 4160 4140 4120 4120
WING (LR and BJ) 5570 5550 5520 5500 5480 5450 5430 5400 5380 5350 5330 5300 5280 5250 5230 5200 5180 5150 5130 5120
Check fuel tank temperature on MFD Fuel Page before using the table. NOTE: Refueling Completion by gravity is allowed if required.
Page
1-09-28
Code
28 06
REVISION 6
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
Auxiliary Tanks Defueling Procedure (EMB-135BJ): Remove excess fuel from the affected auxiliary tanks until the quantity is below the limits presented in table 2. Refer to DDPM maintenance procedure 28-21-03 for Auxiliary Tank Defueling Operation. Check the fuel balancing between the tanks. TABLE 2 - AUXILIARY TANKS FUEL QUANTITY LIMIT COCKPIT/REFUELING PANEL INDICATION FUEL TEMP
FUEL TANK QUANTITY
(°C)
(*)FWD (kg)
AFT (kg)
AFT (lb)
-40
800
(*)FWD (lb) (**)FWD (kg) (**)FWD (lb) 1760
870
1920
660
1450
-35
800
1760
870
1920
660
1450
-30
790
1740
860
1890
650
1430
-25
790
1740
860
1890
650
1430
-20
790
1740
860
1890
650
1430
-15
780
1720
850
1870
640
1410
-10
780
1720
850
1870
640
1410
-5
780
1720
840
1850
640
1410
0
770
1700
830
1850
630
1390
5
770
1700
830
1830
630
1390
10
770
1700
830
1830
630
1390
15
770
1700
830
1830
630
1390
20
760
1670
820
1810
620
1370
25
760
1670
820
1810
620
1370
30
760
1670
810
1780
620
1370
35
750
1650
810
1780
610
1340
40
750
1650
810
1780
610
1340
45
750
1650
800
1760
610
1340
50
740
1630
800
1760
600
1320
52
740
1630
800
1760
600
1320
Check fuel tank temperature on MFD Fuel Page before using the table. (*)EMB-135BJ model S/N up to 591 and Pre-Mod. SB 145LEG-28-0010. (**)EMB-135BJ model S/N 625 and on or Post-Mod. SB 145LEG-28-0010.
Page
REVISION 6
1-09-28
Code
29 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
28-23-07 DEFUELING SHUTOFF VALVE(S) Number installed Number required for dispatch
-23-07 Defueling Shutoff Valve(s)
C
-
0
(M) May be inoperative provided valve is secured closed.
Placard Refueling Panel "DEFUELING SHUTOFF VALVE INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Defueling Shutoff Valve secured closed: − − −
Gain access to the valve (AMM - Chapter 28). Disconnect, insulate and stow the electrical connector. Manually close the valve, through the override lever, locking with a wire. − Pull and safety the DEFUELING circuit breaker (G31).
Page
1-09-28
Code
30 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
28-23-08 FUEL QUANTITY INDICATOR (REFUELING PANEL) Number installed Number required for dispatch
-23-08 Fuel Quantity Indicator (Refueling Panel)
C
1
0
(M) May be inoperative provided airplane is refueled by gravity. NOTE: Does not preclude ventral or auxiliary tanks refueling by fuel transfer procedures on the ground.
Placard Refueling Panel "QUANTITY INDICATOR INOP". OPERATIONAL PROCEDURES Monitor fuel quantity indication on MFD and EICAS. MAINTENANCE PROCEDURES Fuel Tank Gravity Refueling Procedure: Perform TASK 12-11-02-600-801-A (AMM) for Fuel Tank Gravity Refueling. Wing-to-Auxiliary Tanks Fuel Transfer Procedure (EMB-135BJ): Refer to item 28-23-00 for Wing-to-auxiliary Tanks Fuel Transfer procedure.
Page
REVISION 6
1-09-28
Code
31 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
28-40-00 WING TANK FUEL QUANTITY INDICATIONS (EICAS AND MFD) Number installed Number required for dispatch
B -40-00 Wing Tank Fuel Quantity Indications (EICAS and MFD)
4
2
(M) (O) Indications for one tank may be inoperative provided: a) Fuel quantity in associated wing tank is verified by an alternate means, b) Both fuel flow indications and fuel used indications are available, and are monitored throughout flight, and c) Forward and Aft Tanks of both FUS1 and FUS 2 Auxiliary Fuel Systems remain empty.
Placard MFD or PFD Bezel "FUEL QTY IND. INOP".
Page
1-09-28
Code
32 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
OPERATIONAL PROCEDURES If the Fuel Quantity Gauging and Indication System of one wing is inoperative, the associated indication will present dashes on the EICAS display. On the MFD Fuel Page, both the associated tank indication and the TOTAL fuel quantity will present dashes. The EICAS caution message FUEL IMBALANCE may be also presented. Wing tanks fuel quantity can be measured on ground, through the Direct Measuring Stick System, described on the AOM EMB-135/1542 - Description System - Volume II - Section 2-08-15. In flight, the aircraft Remaining Fuel Quantity can be determined through the information from the: Flight Card required/Filled Fuel, FMS fuel data, Fuel Used (FU) of the MFD Fuel Page and the Fuel Flow (FF) of the EICAS/RMU/EFIS. When one wing tank fuel quantity indication is inoperative, both the Fuel Flow (FF) and the Fuel Used (FU) shall be monitored throughout the whole flight. MAINTENANCE PROCEDURES Auxiliary Tanks Defueling Procedure: Refer to DDPM maintenance procedure 28-21-03 for defueling operation.
28-40-01
FORWARD AUXILIARY TANK FUEL QUANTITY INDICATIONS (EICAS AND MFD) Number installed Number required for dispatch
-40-01 Forward Auxiliary Tank Fuel Quantity Indications (EICAS and MFD)
B
4
0
(M) May be inoperative provided Forward and Aft Tanks of the affected FUS Auxiliary Fuel System remain empty.
Placard "FWD TANK QTY IND FUS1(2) INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Refer to DDPM maintenance procedure 28-21-03 for defueling operation.
Page
REVISION 6
1-09-28
Code
33 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
28-40-02 AFT AUXILIARY TANK FUEL QUANTITY INDICATIONS (EICAS AND MFD) Number installed Number required for dispatch
-40-02 Aft Auxiliary Tank Fuel Quantity Indications (EICAS and MFD)
B
4
0
(M) May be inoperative provided Forward and Aft Tanks of the affected FUS Auxiliary Fuel System remain empty.
Placard "AFT TANK QTY IND FUS1(2) INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Refer to DDPM maintenance procedure 28-21-03 for defueling operation.
28-42-01 DIRECT QUANTITY MEASURING STICKS Number installed Number required for dispatch
-42-01 Direct Quantity Measuring Sticks
C 4
0
(O) May be inoperative provided fuel quantity is determined by other means.
Placard Refueling Panel "DIRECT QTY MEASURING STICKS INOP". OPERATIONAL PROCEDURES Check the remaining sources of fuel quantity information such as fuel quantity indications on EICAS and MFD fuel page, fuel quantity indicator in refueling panel and fuel loaded. MAINTENANCE PROCEDURES None.
Page
1-09-28
Code
34 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
28-43-00 FUEL TANK TEMPERATURE INDICATION SYSTEM Number installed Number required for dispatch
-43-00 Fuel Tank Temperature System
C 1
0
May be inoperative provided Total Air Temperature (TAT) is used as an indication of fuel temperature and is limited to -40 °C.
Placard MFD Bezel "FUEL TANK TEMP. IND. INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
28-44-00 FUEL 1 (OR 2) LO LEVEL MESSAGES Number installed Number required for dispatch
-44-00 FUEL 1 (or 2) LO LEVEL Messages
B
2
0
(O) May be inoperative provided fuel quantity indication is available and is monitored throughout flight.
Placard EICAS Bezel "FUEL 1 (or 2) LO LEVEL MESSAGE INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-28
Code
35 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
28-45-01 E1 (OR E2) FUEL LO PRESS MESSAGES Number installed Number required for dispatch
-45-01 E1 (or E2) FUEL LO B PRESS Messages
2
0
(O) May be inoperative provided associated fuel pump automatic function operates normally.
Placard EICAS Bezel "FUEL 1 (or 2) LO PRESS MESSAGE INOP". OPERATIONAL PROCEDURES Fuel Booster Pump Automatic Function Operation check: − Airplane ....................................................................ENERGIZE − Associated Engine....................................................START − MFD Fuel Page ........................................................SET − 1A (2A) Fuel Pump...................................................SELECT The MFD shows A for WING1 (WING2). − 1A (2A) Fuel Pump Circuit Breaker A1 (A34)...........OPEN On the MFD, the indication of the related tank changes to B, C, and OFF intermittently. − 1A (2A) Fuel Pump Circuit Breaker A1 (A34)...........CLOSE The A indication comes into view on the MFD again. − Repeat the steps above for 1B (2B) and 1C (2C) fuel pumps. Ensure that on the MFD the indication of the related tank changes to A, C and OFF intermittently and A, B and OFF intermittently. Register on appropriate logbook for maintenance actions. MAINTENANCE PROCEDURES None.
Page
1-09-28
Code
36 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
28-45-02 APU FUEL LOW PRESS SWITCH Number installed Number required for dispatch
-45-02 APU Fuel Low Press Switch
C 1
0
(O) May be inoperative provided APU is considered inoperative and not used.
C 1
0
(O) May be inoperative provided engine 2 fuel low pressure indication is operating normally and is used to check APU fuel pressure.
Placard APU Control Panel "APU FUEL LO PRESS SWITCH INOP DO NOT USE APU". OPERATIONAL PROCEDURES Engine 2 Fuel Low Pressure Indication check: − − − − −
− − − − −
Airplane ....................................................... ENERGIZE Engine 2 ...................................................... START MFD Fuel Page........................................... SET 2A Fuel Pump ............................................. SELECT Perform the following check: − MFD shows A for tank 2. − No caution message FUEL LO PRESS displayed on the EICAS. − No caution light or no aural caution alarm. 2A Fuel Circuit Breaker (A34) ..................... PULL Check the indication of the related tank changes to B, C and OFF intermittently on the MFD. 2A Fuel Circuit Breaker (A34) ..................... CLOSE Select the 2B fuel pump and repeat the procedure. Select the 2C fuel pump and repeat the procedure.
MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-28
Code
37 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
28-45-03 FUEL XFER INOP MESSAGE Number installed Number required for dispatch
-45-03 FUEL XFER INOP Message
B
1
0
(M) (O) May be inoperative and both FUS Auxiliary Systems used provided: a) Both FUS Auxiliary Fuel Systems operate normally, b) EICAS message CHECK AIRCRAFT LOAD is verified to operate normally, and c) Fuel transfer is monitored through EICAS and/or MFD Fuel Page during flight.
D 1
0
May be inoperative provided Forward and Aft Tanks of both FUS Auxiliary Fuel Systems remain empty.
Placard on frontal panel "FUEL XFER INOP MESSAGE NOT AVAILABLE ON EICAS". OPERATIONAL PROCEDURES Check of selected FUS Auxiliary Fuel System Quantity Indication: Check on MFD or EICAS if Aft and Forward Auxiliary Tank Fuel Quantity Indication from selected system operates normally. Check of selected FUS Auxiliary Tank Fuel System Transfer Indication: Check on MFD or EICAS if Aft and Forward Auxiliary Tank Fuel Quantity Indication runs normally indicating fuel transfer operation. Check on MFD if pumps and transfer indication from selected system are operating normally.
Page
1-09-28
Code
38 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
MAINTENANCE PROCEDURES Auxiliary Tanks Defueling Procedure: Refer to item DDPM 28-21-03 – Maintenance Procedure for defueling operation. Check of CHECK ACFT LOAD on EICAS: To check if CHECK ACFT LOAD message on EICAS operates normally, it is necessary two conditions: a) At least one wing tank must contain less than 2205 lb. To enforce this condition, refer to TASK 28-10-00-910-801-A (AMM) Wing to Wing Fuel Transfer. b) Auxiliary Tank Fuel System must contain more than 1764 lb total fuel quantity or, one of auxiliary tank quantity fuel indication is inoperative. To enforce this condition, or refuel both Auxiliary Tank System to reach a total fuel quantity greater than 1764 lb either select the switch FUS1 (2), located on the Maintenance Panel behind captain seat, to any position and then move it immediately to the opposite side. This simulates for each FUS selected during 10 seconds a fuel load of 1323 lb in forward auxiliary tank and 441 lb in the aft auxiliary tank.
Page
REVISION 6
1-09-28
Code
39 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
28-45-04 AFT AUXILIARY TANK RELIEF VALVES Number installed Number required for dispatch
-45-04 Aft Auxiliary Tank Relief Valves
B
2
0
D 2
0
(M) (O) May be inoperative and affected FUS Auxiliary Fuel System used provided, while transferring fuel from the affected FUS Auxiliary Fuel System: a) Valves is failed closed or secured closed, b) Altitude remains at or below FL 250, and c) Airspeed remains at or below 300 KIAS. (M) May be inoperative failed in any position provided Forward and Aft Tanks of the affected FUS Auxiliary Fuel System remain empty.
Placard "AFT AUXILIARY TANK 1(2) RELIEF VALVE INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES Auxiliary Tanks Defueling Procedure: Refer to DDPM maintenance procedure 28-21-03 for defueling operation.
Page
1-09-28
Code
40 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
28-45-05 FUSELAGE FUEL IMB MESSAGE Number installed Number required for dispatch
-45-05 FUSELAGE FUEL IMB Message
B
1
0
(M) (O) May be inoperative provided: a) Only one FUS Auxiliary Fuel Systems is used and contains no more than 1190 lb (540 kg) (forward plus aft tank), and b) Forward and aft tanks of the other FUS Auxiliary System remain empty.
B
1
0
(M) (O) May be inoperative and both FUS Auxiliary Fuel Systems used provided both systems (forward plus aft tanks) contain no more than 1499 lb (680 kg).
(Continued)
Page
REVISION 6
1-09-28
Code
41 06
MINIMUM EQUIPMENT LIST
28-45-05
AIRPLANE OPERATIONS MANUAL
FUSELAGE FUEL (CONTINUED)
IMB
MESSAGE
Number installed Number required for dispatch
-45-05 FUSELAGE FUEL IMB Message (continued)
B
1
0
(M) (O) May be inoperative provided: a) Only one FUS Auxiliary Fuel Systems is used and contains no more than 3219 lb (1460 kg) (forward plus aft tank), b) Forward and aft tanks of the other FUS Auxiliary Fuel System remain empty, c) DELTA CORRECTION function (Automatic Balance Control) is verified to operate normally, d) Selected FUS Auxiliary Fuel System is verified to operate normally, e) EICAS message FUEL XFER INOP is verified to operate normally, and f) Fuel transfer is monitored through EICAS and/or MFD Fuel Page during flight.
(Continued)
Page
1-09-28
Code
42 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
28-45-05
FUSELAGE FUEL (CONTINUED)
MINIMUM EQUIPMENT LIST
IMB
MESSAGE
Number installed Number required for dispatch
-45-05 FUSELAGE FUEL IMB Message (continued)
B
1
0
(M) (O) May be inoperative and both FUS Auxiliary Fuel Systems used provided: a) Both FUS Auxiliary Fuel Systems contain no more than 3219 lb (1460 kg) (forward plus aft tanks), b) DELTA CORRECTION function (Automatic Balance Control) is verified to operate normally, c) Both FUS Auxiliary Fuel Systems are verified to operate normally, d) EICAS message FUEL XFER INOP is verified to operate normally, and e) Fuel transfer is monitored through EICAS and/or MFD Fuel Page during flight.
D 1
0
May be inoperative provided Forward and Aft Tanks of both FUS Auxiliary Fuel Systems remain empty.
Placard "FUSELAGE FUEL IMB MESSAGE NOT AVAILABLE ON EICAS". OPERATIONAL PROCEDURES Check of selected FUS Auxiliary Fuel System Quantity Indication: Check on MFD or EICAS if Aft and Forward Auxiliary Tank Fuel Quantity Indication from selected system operates normally.
Page
REVISION 6
1-09-28
Code
43 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
Check of selected FUS Auxiliary Tank Fuel System Transfer Indication: Check on MFD or EICAS if Aft and Forward Auxiliary Tank Fuel Quantity Indication runs normally indicating fuel transfer operation. Check on MFD if pumps and transfer indication from selected system are operating normally. MAINTENANCE PROCEDURES Auxiliary Tanks Defueling Procedure: Refer to DDPM maintenance procedure 28-21-03 for defueling operation. Check of FUEL XFER INOP: Refer to DDPM maintenance procedure 28-21-08. Check of Automatic balance Correction (DELTA CORRECTION): Before perform this check, both Auxiliary Tank Fuel System must be balanced and each wing must contain less than 4189 lb. − − − − − − −
− − − − −
Select the FUS1 transfer system. Observe that the transference from both auxiliary tanks starts. Open the AFT1 pump CB, inhibiting the fuel transference from this tank. Observe that the transference stops when the difference between FWD and AFT tanks is approximately 529 lb. Rearm the AFT pump CB and re-start the FUS1 transfer system. Observe that only the transference from AFT1 tank starts. Observe that the transference from both auxiliary tanks starts when the FWD1 tank fuel quantity is approximately 309 lb higher than the AFT1 tank fuel quantity. Open the applicable FWD1 pump CB, according to the selected on the Fuel Panel, inhibiting the fuel transference from this tank. Observe that the transference stops when the difference between FWD and AFT tanks is approximately 88 lb. Rearm the applicable FWD1 pump CB and re-start the FUS1 transfer system. Observe that only the transference from FWD1 tank starts. Observe that the transference from both auxiliary tanks starts when the FWD1 tank fuel quantity is approximately 309 lb higher than the AFT1 tank fuel quantity.
Page
1-09-28
Code
44 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
28-45-06 CHECK ACFT LOAD MESSAGE Number installed Number required for dispatch
-45-06 CHECK ACFT LOAD Message
B
1
0
(M) (O) May be inoperative provided both FUS Auxiliary Fuel Systems (forward plus aft tanks) contain no more than 1764 lb (800 kg).
D 1
0
May be inoperative provided Forward and Aft Tanks of both FUS Auxiliary Fuel Systems remain empty.
Placard "CHECK ACFT LOAD MESSAGE INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES Auxiliary Tanks Defueling Procedure: Refer to DDPM maintenance procedure 28-21-03 for defueling operation. NOTE: Any fuel in the affected FUS Fuel System is considered unusable and must be treated as ballast fuel. Include the remaining fuel of the affected FUS tanks in the calculation of takeoff weight and C.G. position for takeoff. If in the unable FUS tank system remain more than 1764 lb (800 kg) total quantity fuel, perform defueling procedure.
Page
REVISION 6
1-09-28
Code
45 06
MINIMUM EQUIPMENT LIST
28-45-07
AIRPLANE OPERATIONS MANUAL
AFT AUXILIARY TANK ISOLATION VALVES
TRANSFER
Number installed Number required for dispatch
-45-07 Aft Auxiliary Tank Transfer Isolation Valves
B
2
1
(M) (O) One may be inoperative and one FUS Auxiliary Fuel System may be used provided Forward and Aft Tanks of the other FUS Auxiliary Fuel System remain empty.
B
2
1
(M) (O) One may be inoperative provided: a) Affected FUS Auxiliary Fuel System is not used, b) Affected FUS Auxiliary Fuel System (forward plus aft tank) contains no more than 1764 lb (800 kg), c) Any fuel in the affected FUS Auxiliary Fuel System is considered unusable, is treated as ballast fuel, and is included in the calculation of Takeoff weight and C.G. position for takeoff, and d) Valve is secured closed.
(Continued)
Page
1-09-28
Code
46 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
28-45-07
MINIMUM EQUIPMENT LIST
AFT AUXILIARY TANK TRANSFER ISOLATION VALVES (CONTINUED) Number installed Number required for dispatch
-45-07 Aft Auxiliary Tank Transfer Isolation Valves (continued)
B
2
0
(M) (O) May be inoperative provided: a) Both FUS Auxiliary Fuel Systems (forward plus aft tanks) contain no more than 1764 lb (800 kg), b) Any fuel in the FUS Auxiliary Fuel Systems is considered unusable, is treated as ballast fuel, and is included in the calculation of Takeoff weight and C.G. position for takeoff, and c) Valves are secured closed.
D 2
0
May be inoperative provided Forward and Aft Tanks of both FUS Auxiliary Fuel Systems remain empty.
Placard "AFT AUX TANK XER ISOL VALVE INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES Aft Auxiliary Tank Refueling Isolation Valve secured closed: − − −
Gain access to the valve (AMM - Chapter 28). Remove, insulate and stow the electrical connector. Position and safety with a lock wire the valve position indicator (override lever) at the closed position.
Page
REVISION 6
1-09-28
Code
47 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
Auxiliary Tanks Defueling Procedure: Refer to DDPM maintenance procedure 28-21-03 for defueling operation. NOTE: Any fuel in the affected FUS Fuel System is considered unusable and must be treated as ballast fuel. Include the remaining fuel of the affected FUS tanks in the calculation of takeoff weight and C.G. position for takeoff. If the affected FUS tank system remain with more than 1764 lb total quantity fuel, perform defueling procedure.
Page
1-09-28
Code
48 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
28-45-08 FORWARD AUXILIARY TANK REFUELING ISOLATION VALVE Number installed Number required for dispatch
-45-08 Forward Auxiliary Tank Refueling Isolation Valve
C 1
0
(M) (O) May be inoperative provided: a) Fuel distribution between Forward and Aft tanks is verified to be correct, and b) Valve is secured closed. NOTE: Refueling of FUS Auxiliary Systems cannot be accomplished with this valve secured closed.
Placard "FWD AUX XFER ISOL VALVE INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES Forward Auxiliary Tank Refueling Isolation Valve secured closed: − − −
Gain access to the valve (AMM - Chapter 28). Remove, insulate and stow the electrical connector. Position and safety with a lock wire the valve position indicator (override lever) at the closed position. Auxiliary Tanks Defueling Procedure: Refer to DDPM maintenance procedure 28-21-03 for defueling operation. NOTE: Refueling of FUS Auxiliary Systems can not be accomplished if this valve is inoperative secured closed.
Page
REVISION 6
1-09-28
Code
49 06
MINIMUM EQUIPMENT LIST
28-45-09
AIRPLANE OPERATIONS MANUAL
AFT AUXILIARY ISOLATION VALVE
TANK
REFUELING
Number installed Number required for dispatch
-45-09 Aft Auxiliary Tank Refueling Isolation Valve
C 1
0
(M) (O) May be inoperative provided: a) Fuel distribution between Forward and Aft tanks is verified to be correct, and b) Valve is secured closed. NOTE: Refueling of FUS Auxiliary Systems cannot be accomplished with this valve secured closed.
Placard "AFT AUX TANK REFUEL ISOL VALVE INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES Aft Auxiliary Tank Refueling Isolation Valve secured closed: − − −
Gain access to the valve (AMM - Chapter 28). Remove, insulate and stow the electrical connector. Manually close the valve, through the override lever, locking with a wire.
Auxiliary Tanks Defueling Procedure: Refer to DDPM maintenance procedure 28-21-03 for defueling operation. NOTE: Refueling of FUS Auxiliary Systems can not be accomplished if this valve is inoperative secured closed.
Page
1-09-28
Code
50 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
28-45-10 FORWARD AUXILIARY TANK REFUELING VENTILATION ELECTRICAL SHUTOFF VALVES Number installed Number required for dispatch
C 2 -45-10 Forward Auxiliary Tank Refueling Ventilation Electrical Valve
0
(M) (O) May be inoperative provided: a) Fuel distribution between forward and aft tanks is verified to be correct, and b) Affected valve is secured closed. NOTE: Refueling of FUS Auxiliary Systems cannot be accomplished with this valve secured closed.
Placard "FWD AUX TANK VENT VALVE INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES Forward Auxiliary Tank Refueling Ventilation Electrical Shutoff Valve secured closed: − − −
Gain access to the valve (AMM - Chapter 28). Disconnect, insulate and stow the electrical connector. Manually close the valve, through the override lever, locking with a wire.
Auxiliary Tanks Defueling Procedure: Refer to DDPM maintenance procedure 28-21-03 for defueling operation. NOTE: Refueling of FUS Auxiliary Systems can not be accomplished if this valve is inoperative secured closed.
Page
REVISION 6
1-09-28
Code
51 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
28-45-11 CROSS TRANSFER SHUTOFF VALVE Number installed Number required for dispatch
-45-11 Cross Transfer Shutoff Valve
B
1
0
(M) (O) May be inoperative provided: a) Valve is secured closed, and b) Fuel transfer and wing fuel balance are monitored through EICAS and/or MFD Fuel Page during flight.
D 1
0
(M) May be inoperative provided: a) Valve is secured closed, and b) Forward and Aft Tanks of both FUS Auxiliary Fuel Systems remain empty.
Placard "XFER SHUTOFF VALVE INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES Cross Transfer Shutoff Valve secured closed: − − −
Gain access to the valve (AMM - Chapter 28). Disconnect, insulate and stow the electrical connector. Manually close the valve, through the override lever, locking with a wire.
Auxiliary Tanks Defueling Procedure: Refer to DDPM maintenance procedure 28-21-03 for defueling operation. NOTE: Refueling of FUS Auxiliary Systems can not be accomplished if this valve is inoperative secured closed.
Page
1-09-28
Code
52 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 29 HYDRAULIC POWER 29-10-02 GSE COUPLINGS (EXTERNAL) Number installed Number required for dispatch
-10-02 GSE Couplings (External)
C 6
0
(M) May be inoperative open provided the failed external coupling (or the associated plumbing) is isolated from the hydraulic system.
Placard the affected Plumbing "GSE COUPLING ISOLATED OR REMOVED". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Perform TASK 29-10-02-000-801-A (AMM) for GSE Pressure Coupling removal and install plugs MS21913D8 (or MS21913J8) and MS21913J5 on hydraulic lines (See figure).
Page
REVISION 6
1-09-29
Code
1 06
MINIMUM EQUIPMENT LIST
Page
1-09-29
AIRPLANE OPERATIONS MANUAL
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
REVISION 6
1-09-29
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
29-10-05 ELECTRIC HYDRAULIC PUMP SYSTEMS Number installed Number required for dispatch
-10-05 Electric Hydraulic Pump Systems 1) AUTO Functions
C 2
0
(O) May be inoperative provided: a) Manual function operates normally, b) Associated pump selector is ON for takeoff and landing, and c) Four generators are available.
2) Manual Functions C 2
0
(O) May be inoperative provided AUTO and OFF positions for associated pump selector are verified to operate normally.
Placard affected Electric Hydraulic Pump Control Knob "AUTO INOP" or "ON INOP". OPERATIONAL PROCEDURES In case of the automatic function failure, the affected pump must be turned off during cruise after gear retraction and back on prior to landing gear extension. OFF and AUTO Position check (Manual Function Inoperative): With associated engine shutdown: − − − − − −
Associated ELEC PUMP Knob.................... OFF MFD 1 or 2 .................................................. HYD PAGE MFD Pump Status Indication ...................... CHECK OFF Associated ELEC PUMP Knob.................... AUTO MFD Pump Status Indication ...................... CHECK ON Associated Engine....................................... START
Page
1-09-29
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
During associated engine START: − − − −
N2 ............................................................... BELOW 56% MFD Pump Status Indication ...................... CHECK ON N2 ............................................................... ABOVE 56% MFD Pump Status Indication ...................... CHECK OFF
After associated engine START: − Associated ENG PUMP SHUTOFF Button.......................................................... PRESS − MFD Pump Status Indication ...................... CHECK ON − Associated ENG PUMP SHUTOFF Button.......................................................... RELEASE − MFD Pump Status Indication ...................... CHECK OFF MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-29
Code
5 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
29-10-14 RESERVOIR REFILLING CHECK VALVES Number installed Number required for dispatch
-10-14 Reservoir Refilling Check Valves
C 2
0
(M) May be inoperative open provided failed valve is removed and plumbing plugged.
C 2
0
May be inoperative closed.
Placard the affected Plumbing "CHECK VALVE REMOVED". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Perform TASK 29-10-14-000-801-A (AMM) for Check Valve removal and install plug MS21913D4 or MS21913J4 on hydraulic line (See figure).
Page
1-09-29
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
Page
REVISION 6
1-09-29
Code
7 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
29-10-16 PRESSURE GROUND CONNECTION CHECK VALVES Number installed Number required for dispatch
-10-16 Pressure Ground Connection Check Valves
C 2
0
(M) May be inoperative open provided the failed valve is removed and plumbing plugged.
C 2
0
May be inoperative closed.
Placard the affected Plumbing "CHECK VALVE REMOVED". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Perform TASK 29-10-16-000-801-A (AMM) for Check Valve removal and install plugs MS21913J6 and O’ring NAS1612-6 on hydraulic line (See figure).
Page
1-09-29
Code
8 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
Page
REVISION 6
1-09-29
Code
9 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
29-30-00 HYDRAULIC FLUID QUANTITY INDICATIONS (INCLUDING LOW LEVEL WARNING) Number installed Number required for dispatch
-30-00 Hydraulic Fluid C 2 Quantity Indications (Including low level warning)
1
(M) One may be inoperative provided: a) Associated fluid quantity is verified to be normal before each departure, and b) Hydraulic pressure indication is available and is monitored throughout flight.
Placard MFD Bezel "HYD QTY IND INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES Perform TASK 12-13-01-600-801-A (AMM) for Hydraulic Fluid Quantity check.
Page
1-09-29
Code
10 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
REVISION 6
1-09-29
Code
11 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
29-30-01 RESERVOIR QUANTITY GAGES Number installed Number required for dispatch
-30-01 Reservoir Quantity Gages
C 2
0
(O) May be inoperative provided: a) Fluid quantity is verified by other means before each departure, and b) Pressure indication is operating normally.
Placard affected Gage "INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES Alternate Fluid Quantity check: − Gain access to the affected reservoir (193BL or 193CR panel) (See figures 1 and 2 in the 1-08-30 subsection for positive identification). − Remove the vent filter (cut the lockwire and remove both screws). − Ensure Landing Gear/Main Door and Emergency/Parking Brake accumulators have a pre-charge of nitrogen only (refer to AMM TASK 32-44-02-700-801-A SUBTASK 32-44-02-720-001-A00 and TASK 52-12-00-200-801-A SUBTASK 52-12-00-220-001-A00). − Insert a small rod in the vent filter hole deep enough to contact the piston head (in order to measure piston displacement). − Make sure piston displacement is at or below 30 mm. − If displacement is above 30 mm, perform TASK 12-13-01-600-802-A (AMM) to replenish the reservoir. − Install and lockwire the vent filter.
Page
1-09-29
Code
12 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
Page
REVISION 6
1-09-29
Code
13 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
29-30-02 HYDRAULIC PRESSURE INDICATIONS Number installed Number required for dispatch
-30-02 Hydraulic Pressure Indications
C 2
1
(O) One may be inoperative provided associated hydraulic fluid quantity indication operates normally.
Placard MFD Bezel "HYD SYS 1 (OR 2) PRESS IND INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES None.
Page
1-09-29
Code
14 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
ATA CHAPTER PROTECTION
30
ICE
MINIMUM EQUIPMENT LIST
AND
RAIN
30-11-00 WING ANTI-ICING SYSTEM Number installed Number required for dispatch
-11-00 Wing Anti-icing System
C 1
0
May be inoperative provided airplane is not operated in known or forecast icing conditions.
Placard Ice Protection Panel "WING SYSTEM INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
30-11-01 WING ANTI-ICING VALVES Number installed Number required for dispatch
-11-01 Wing Anti-icing Valves
C 2
0
(M) May be inoperative provided: a) Valve is secured closed, and b) Airplane is not operated in known or forecast icing conditions.
Placard above Wing Anti-icing Button "INOP". OPERATIONAL PROCEDURES None.
Page
REVISION 6
1-09-30
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
MAINTENANCE PROCEDURES Wing/Stabilizer Anti-ice Valve secured closed: For Airplanes Pre-Mod. SB 145-30-0021: − Gain access to the valve through respective access panels (191EL - LH side, or 191FR - RH side. See AMM 6-41-01). − With the position indicator in the STOW position, loosen the lock bolt. − Rotate the valve to the LOCK position (Align the position indicator hole with the cover assembly threaded hole by using a 1/4” socket or end wrench on the exposed valve shaft). − Retighten the lock bolt and torque it until there is a 0.25 to 1.25 mm gap between the under side of the bolt head and the top surface of the position indicator.
WING/STABILIZER ANTI-ICE VALVE (PRE-MOD. SB 145-30-0021)
Page
1-09-30
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
For Airplanes Post-Mod. SB 145-30-0021: − Gain access to the valve through respective access panels (191EL - LH side, or 191FR - RH side. See AMM 6-41-01). − With the anti-icing valve deenergized, the actuator pressure is vented to ambient and the valve is in the closed position. The position indicator is directed to “CL” on the valve housing. − Remove the chained lock screw to vent servo and install the screw in the threaded hole (see figure) with the position indicator directed to “CL”. − Rotate the valve to the LOCK position (Align the position indicator hole with the cover assembly threaded hole by using a 1/4” socket or end wrench on the exposed valve shaft). − Bottom screw in boss and wrench the lock screw to locked position to a maximum of 8 ft-lb. − For quick reference, locking instructions are printed on the valve instruction plate.
WING/STABILIZER ANTI-ICE VALVE (POST-MOD. SB 145-30-0021)
Page
REVISION 6
1-09-30
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
WING ANTI-ICE VALVE LOCATION (PRE-MOD. AND POST-MOD. SB 145-30-0021)
Page
1-09-30
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
30-11-02 WING ANTI-ICING VALVE OPEN LIGHT Number installed Number required for dispatch
-11-02 Wing Anti-icing Valve OPEN Light
C 1
0
C 1
0
(M) May be inoperative provided system is verified to operate normally. May be inoperative provided airplane is not operated in known or forecast icing conditions.
Placard above Wing Anti-Icing Button "OPEN LIGHT INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Perform TASK 30-11-00-700-802-A (AMM) for wing thermal anti-icing system operational check.
30-12-00 STABILIZER ANTI-ICING SYSTEM Number installed Number required for dispatch
-12-00 Stabilizer Anti-icing System
C 1
0
May be inoperative provided airplane is not operated in known or forecast icing conditions.
Placard Ice Protection Panel "STAB. SYSTEM INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-30
Code
5 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
30-12-01 STABILIZER ANTI-ICING VALVE Number installed Number required for dispatch
-12-01 Stabilizer Anti-icing Valve
C
1
0
(M) May be inoperative provided: a) Valve is secured closed, and b) Airplane is not operated in known or forecast icing conditions.
Placard above Stabilizer Anti-icing Button "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Refer to item 30-11-01 for valve secured closed procedure. To gain access to this valve, remove access panel 322AL (see AMM 6-42-00).
30-12-02 STABILIZER ANTI-ICING VALVE OPEN LIGHT Number installed Number required for dispatch
-12-02 Stabilizer Anti-icing Valve OPEN Light
C 1
0
C 1
0
(M) May be inoperative provided system is verified to operate normally. May be inoperative provided airplane is not operated in known or forecast icing conditions.
Placard above Stabilizer Anti-Icing Button "OPEN LIGHT INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Perform TASK 30-12-00-700-803-A (AMM) for horizontal stabilizer thermal anti-icing system operational check.
Page
1-09-30
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
30-21-00 ENGINE ANTI-ICING SYSTEMS Number installed Number required for dispatch
-21-00 Engine Anti-icing Systems
C 2
1
One may be inoperative provided airplane is not operated in known or forecast icing conditions.
B
0
May be inoperative for day VMC provided airplane is not operated in known or forecast icing conditions.
2
Placard Ice Protection Panel "ENGINE SYSTEM INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-30
Code
7 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-09-30
Code
8 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
30-21-01 ENGINE ANTI-ICING VALVES Number installed Number required for dispatch
-21-01 Engine Anti-icing Valves
C 2
0
(M) (O) May be inoperative provided valve is secured open. NOTE 1: On airplanes equipped with EICAS version prior to 16.5, the message E1 (2) A/ICE FAIL may be present. NOTE 2: On airplanes equipped with EICAS version 16.5 or subsequent, the messages ENG1 (2) A/ICE FAIL and/or ENG A/ICE OVERPRESS may be present.
C 2
1
One may be inoperative closed provided airplane is not operated in known or forecast icing conditions.
Placard above Engine Anti-icing Button "INOP". OPERATIONAL PROCEDURES For airplanes equipped with AE3007A, AE3007A1/1, AE3007A1, AE3007A1E, AE3007A1/3 and AE3007A1P engines (AE3007A and AE3007A1/1 engines intermix operation is also permitted): The following procedures must be accomplished when dispatching the airplane with one or both engine anti-icing valves locked open: NOTE: The Ice Detection Override Knob must be set to ENG to inhibit the message E1 (2) A/ICE FAIL on EICAS. If the message still persists, report to the maintenance personnel. Takeoff Data Setting: During takeoff data setting, select the ANTI-ICE ON or OFF according the following criteria: If OAT is at or below 10°C → Use Reference Anti-Ice ON. If OAT is above 10°C → Use Reference Anti-Ice OFF.
Page
REVISION 6
1-09-30
Code
9 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
Takeoff Weights Corrections: The takeoff weight correction should be accomplished according one of the following criteria: − Run the Runway Analysis Software with "Valve Locked" option, or − Reduce the MTOW by: a) 794 lb (AE3007A, AE3007A1/1 or AE3007A1). b) 587 lb (AE3007A1E). c) 508 lb (AE3007A1/3 or AE3007A1P). NOTE: − In case of discrepancies between the MTOW calculated thought Runway Analysis Software and the MTOW reduced by xx lb (depending on the engine) the value given by Software must prevail. − For airplanes equipped with AE3007A, AE3007A1/1 and AE3007A1, only T/O-1 mode is allowed for takeoff with engine anti-ice valve locked open. − For airplanes equipped with AE3007A1/3 or AE3007A1P, only T/O mode is allowed for takeoff with engine anti-ice valve locked open. − For airplanes equipped with AE3007A1E, only T/O and E T/O modes are allowed for takeoff with engine anti-ice valve locked open. Speeds Corrections: There are no speed corrections associated with engine anti-ice valve locked. Enroute and Landing Weights Corrections: Use applicable AFM supplement performance charts to calculate enroute and landing weights when operating with engine anti-ice locked open. MAINTENANCE PROCEDURES Engine Anti-ice Valve secured open: − Remove the following access panels (AMM 6-43-00/101): • 412AT (Upper cowling of the LH powerplant) and • 422AT (Upper cowling of the RH powerplant); − Loosen both lock screws (approximately one turn); − Press and rotate the manual override pin 270° as indicated to lock valve in the open position; − Tighten both lock screws. The message ENG A/ICE OVERPRESS may be present. Page
1-09-30
Code
10 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ENGINE ANTI-ICING VALVE
Page
REVISION 6
1-09-30
Code
11 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
30-21-02 ENGINE ANTI-ICING VALVE OPEN LIGHT Number installed Number required for dispatch
-21-02 Engine Anti-icing Valve OPEN Light
C 2
1
(M) One may be inoperative provided system is verified to operate normally.
C 2
1
One may be inoperative provided airplane is not operated in known or forecast icing conditions.
Placard above Engine Anti-Icing Buttons "OPEN LIGHT INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Perform TASK 30-21-00-700-802-A (AMM) for engine thermal antiicing system functional check. NOTE: Disregard the affected Engine Anti-Icing Valve Open Light illumination during task execution (notes on steps 3 and 11).
Page
1-09-30
Code
12 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
30-31-00 PITOT PROBE HEATING SYSTEMS Number installed Number required for dispatch
-31-00 Pitot Probe Heating Systems
C
3
2
One may be inoperative provided airplane is not operated visible moisture or in known or forecast icing conditions.
Placard above Pitot Tube Heating Button "PITOT HEAT INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
30-32-01 AOA SENSOR HEATING SYSTEMS Number installed Number required for dispatch
-32-01 AOA Sensor Heating Systems
B
2
1
May be inoperative provided airplane is not operated in known or forecast icing conditions.
Placard above AOA Heating Button "AOA HEAT INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-30
Code
13 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
30-33-01 TAT PROBE HEATING SYSTEMS Number installed Number required for dispatch
-33-01 TAT Probe Heating Systems
C
2
1
One may be inoperative provided airplane is not operated known or forecast icing conditions.
Placard above TAT Heating Button "TAT HEAT INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-30
Code
14 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
30-41-00 WINDSHIELD WIPERS Number installed Number required for dispatch
-41-00 Windshield Wipers 1) Airplanes Not Equipped with Rain Repellent Coating (RRC)
C
2
0
a) Low Speed
C
2
0
b) High Speed
C
2
0
c) Parking Mode C
2
0
2 2
0 0
d) Timer Mode 2) Airplanes Equipped with Rain Repellent Coating (RRC)
C D
May be inoperative provided airplane is not operated in precipitation within 5 nautical miles of the airport of takeoff or intended landing. May be inoperative provided high speed operates normally. May be inoperative provided low speed operates normally. (O) May be inoperative provided blades can be positioned providing an acceptable field of vision to the flight crew.
Placard Windshield Wiper Selector Knob "INOP" or "LOW INOP" or "HIGH INOP" or "TIMER INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-30
Code
15 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
30-42-02 WINDSHIELD HEATING SYSTEMS Number installed Number required for dispatch
-42-02 Windshield Heating Systems
C
2
1
(M) One may be inoperative provided: a) Affected windshield heating system is deactivated, and b) Airplane is not operated in known or forecast icing conditions.
Placard Windshield Heating Control Panel "SYSTEM INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES May be flight Crewmember accomplished. Pull and safety the WSHLD TEMP circuit breaker associated with the inoperative windshield (G13 or J20).
30-80-00 ICE DETECTORS Number installed Number required for dispatch
-80-00 Ice Detectors
C
2
1
Placard Ice Detection Override Knob "ICE DET 1 (or 2) INOP". OPERATIONAL PROCEDURES Set the Ice Detection Override Knob to ALL position at the first visible or anticipated icing condition. NOTE: Icing conditions may exist inflight when Total Air Temperature (TAT) is 10°C or below and visible moisture in any form is presented (such as clouds, fog with visibility of one mile or less, rain, snow, sleet, and ice crystals). MAINTENANCE PROCEDURES None.
Page
1-09-30
Code
16 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
30-81-01
CLEAR ICE (EMB-135BJ)
MINIMUM EQUIPMENT LIST
DECTECTOR
SYSTEM
Number installed Number required for dispatch
-81-01 Clear Ice Detector *** System
1) Clear Ice Indication Lights
C
1
0
C
2
0
May be inoperative provided wing upper surface is verified to be free of clear ice prior to departure. (O) May be inoperative provided the EICAS clear ice messages operate normally.
Placard Clear Ice Detector Control Panel "CLEAR ICE DETECT SYS INOP". OPERATIONAL PROCEDURES According to the maintenance procedure below. MAINTENANCE PROCEDURES A physical (hands-on) check must be done on the upper wing surface to ensure that there is no clear ice built up on the wing. The check may be accomplished by either the maintenance personnel or the flight crew. This inspection must be accomplished after the airplane is refueled and as near the departure as possible. Perform the check as follows: − The check must be performed on the upper surface of the wing, close to the wing-to-fuselage junction, in the region where the clear ice detector is installed. − Position a ladder close to the wing leading edge. Check for the presence of ice by feeling the upper wing surface along and aft the front spar. − Check the wing surface in the area over the clear-ice sensor and on the anti-slip stripes. The sharp parts of the granules in the stripes and the clear-ice sensor screw heads must be touched. They have a consistent rough texture. The anti-slip stripes and the Exit direction arrow may be used as visual reference as well. − If clear ice is found, de-ice the airplane.
Page
REVISION 6
1-09-30
Code
17 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
30-81-02 CLEAR ICE INDICATION LAMPS (EMB-135BJ) Number installed Number required for dispatch
-81-02 Clear Ice Indication Lamps
C
2
0
(O) May be inoperative provided the EICAS clear ice messages operate normally before each flight.
Placard Clear Ice Indication Lamps "INOP". OPERATIONAL PROCEDURES CLR/I INOP 1 (2) EICAS messages check: Perform the following test before engines start: Ice Detection Override Knob.......................... AUTO Ice Detection Test Knob ................................ 1 Test knob must be held at least 10 seconds in this position. Check that CLR/I INOP 1 and CLR/I INOP 2 caution messages are displayed on the EICAS. NOTE: If Ice Detection Test Knob 2 is selected, these messages will not be displayed on the EICAS. MAINTENANCE PROCEDURES None.
Page
1-09-30
Code
18 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 31 INDICATING/RECORDING SYSTEMS 31-21-01 CLOCKS Number installed Number required for dispatch
-21-01 Clocks 1) Copilot’s Clock
C 1
0
May be inoperative provided pilot’s clock operates normally.
2) Pilot’s Clock
A
0
May be inoperative provided:
1
a) Flight Data Recorder (FDR) is considered inoperative, b) Copilot’s clock operates normally, and c) Repairs are made within three flight days. Placard affected Clock "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-31
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
31-30-01 FLIGHT DATA RECORDER (FDR) SYSTEM Number installed Number required for dispatch
C -
1
Any in excess of those required by FAR may be inoperative.
A
-
0
1) FDR Recording Parameters required by FAR
A
-
-
2) FDR Recording Parameters not required by FAR
A
-
-
May be inoperative provided: a) Cockpit Voice Recorder (CVR) operates normally, b) Airplane is not dispatched from a designated airport as listed in the operator’s MEL unless: 1) The FDR failure occurs after pushback but prior to takeoff, or 2) The FDR repair is attempted but was not successful, c) In those cases where repair is attempted but not successful, the aircraft may be dispatched on a flight or series of flights until the next designated airport where repair must be accomplished prior to dispatch, and d) Repairs are made within three flight days. May be inoperative provided: a) Cockpit Voice Recorder (CVR) operates normally, and b) Repair are made within 20 calendars days. May be inoperative provided repairs are made prior to the completion of the next heavy maintenance visit.
-30-01 Flight Data Recorder (FDR) System
Page
1-09-31
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
Placard near Clock’s Multiple Selector "FDR INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
31-42-02 INTEGRATED COMPUTER CONFIGURATION MODULES (IM-600) Number installed Number required for dispatch
-42-02 Integrated Computer Configuration Modules (IM-600)
B
2
1
One may be inoperative with the EICAS message IC 1 (2) CONFIG FAIL displayed provided the EICAS messages CONFIG MISMATCH or CHK IC CONFIG are not displayed.
OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-31
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
31-51-00 AURAL WARNING UNIT Number installed Number required for dispatch
-51-00 Aural Warning Unit 1) Channels C 2
1
Report to the maintenance personnel. OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
31-51-02 MASTER WARNING LIGHTS/BUTTONS Number installed Number required for dispatch
-51-02 MASTER Warning Lights/Buttons 1) Lights
2) Alarm Cancel Functions
C 2
1
C 2
1
One may be inoperative provided master warning aural alert operates normally.
Placard associated Light "LIGHT INOP" or "ALARM CANCEL INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-31
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
31-51-03 MASTER CAUTION LIGHTS/BUTTONS Number installed Number required for dispatch
-51-03 MASTER Caution Lights/Buttons 1) Lights
2) Alarm Cancel Functions
C 2
1
C 2
1
One may be inoperative provided master caution aural alert operates normally.
Placard associated Light "LIGHT INOP" or "ALARM CANCEL INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-31
Code
5 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-09-31
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 32 LANDING GEAR 32-33-02 LANDING GEAR CONTROL LEVER LATCH SYSTEM Number installed Number required for dispatch
B -33-02 Landing Gear Control Lever Latch System
1
0
(M)(O) May be inoperative in the latched position provided: a) Downlock release mechanism operates normally, and b) LG AIR/GND FAIL message is not present.
Placard Landing Gear Control Lever "LATCH SYSTEM INOP". OPERATIONAL PROCEDURES After takeoff, use the Downlock Release button to actuate the Landing Gear Lever to UP. MAINTENANCE PROCEDURES Override Mechanism check: − Install safety pins on the three LG legs. − Pull the overhead panel landing gear circuit breakers A30 "CMD" and E21 "DOOR CMD". − Try to move the landing gear lever up. The landing gear lever shall be latched in the down position. − Press the down lock release button and try to move the landing gear lever to UP. The lever should move to UP position. − Return the LG control lever to Down position. − Restore the airplane to normal condition. NOTE: Visually check the landing gear shock absorbers for condition and leakage.
Page
REVISION 6
1-09-32
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
32-40-01 BRAKE TEMPERATURE INDICATIONS Number installed Number required for dispatch
-40-01 Brake Temperature C 4 Indications
3
C 4
0
(O) May be inoperative provided Quick Turn Around Chart in AFM is complied with.
Placard MFD Bezel "BRAKE XX IND INOP" or "BRAKE INDICATIONS INOP". The airplane may be dispatched after either the Operational or the Maintenance procedures below be accomplished. OPERATIONAL PROCEDURES In order to deactivate two or all Brake Temperature Sensors, pull and collar the affected sensor circuit breaker: TEMPERATURE SENSOR RH and LH Inboard RH and LH Outboard
CIRCUIT BREAKER E19 E16
See Quick Turn Around Weight Chart on AFM Section 5 - Performance.
Page
1-09-32
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
MAINTENANCE PROCEDURES In order to deactivate each affected Brake Temperature Sensor independently, follow the steps below: − Pull the affected Brake Temperature Sensor circuit breaker and attach a DO-NOT-CLOSE tag to it: TEMPERATURE SENSOR RH and LH Inboard RH and LH Outboard
CIRCUIT BREAKER E19 E16
− Open the access panel 193AL. Refer to the AMM 06-41-01/101. − Disconnect the electrical connector associated to the failed Brake Temperature Sensor: TEMPERATURE SENSOR CONNECTOR
LH OUTBD P1075
LH INBD P1077
RH INBD P1076
RH OUTBD P1078
− Secure the harness associated with the disconnected connector with an appropriate tie-wrap in order to prevent it from moving freely within the fairing area. − Install a cap (P/N MS90376-16Y or P/N NAS820-16A) in the electrical connector. Lock wire can be used to hold the cap in its place, if there is no confidence that it will be held during the aircraft operation. − Install a cap (P/N MS90376-12RB or P/N NAS831-12C) in the affected Brake Temperature Signal Conditioner. − Push back in the affected Brake Temperature Sensor circuit breaker (E16 or E19) and remove the DO-NOT-CLOSE tag from it. NOTE: If two or more Brake Temperature Sensors are disconnected, see Quick Turn Around Weight Chart on AFM Section 5 Performance.
Page
REVISION 6
1-09-32
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
32-41-08 BRAKE PRESSURE TRANSDUCERS Number installed Number required for dispatch
-41-08 Brake Pressure Transducers
B
4
3
(M) May be inoperative with the BRAKE DEGRADED caution message present provided: a) Only the respective PRESS TRANSDUCER FAIL message is presented on the brake system portion of the CMC, b) External leakage is not present, and c) Affected brake pressure transducer is deactivated.
Register as appropriate for maintenance actions. OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Brake Pressure Transducer deactivation: − For brake pressure transducer access refer TASK 32-41-08-000801-A (AMM). − Gain access to the affected pressure transducer. − Disconnect and stow the electrical connector. − Make sure there is no evidence of leakage on the pressure port connection.
Page
1-09-32
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
32-44-05 ACCUMULATOR LOW PRESSURE SWITCH Number installed Number required for dispatch
-44-05 Accumulator Low Pressure Switch
C 1
0
May be inoperative provided accumulator charge is verified to be normal once each flight day.
Placard on EICAS Bezel "EMRG BR LO PRES MESSAGE INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Emergency/Parking Brake Accumulator Charge check: To check the Emergency/Parking Brake accumulator charge refer to SUBTASK 32-44-02-720-001-A00 (AMM).
Page
REVISION 6
1-09-32
Code
5 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
32-44-07 BRAKE ON LIGHTS Number installed Number required for dispatch
-44-07 BRAKE ON Lights 1) Cockpit light
B
1
0
2) Ramp light
C 1
0
May be inoperative provided emergency/parking brake system operates normally.
Placard affected Light "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Parking Brake System check: − Shut engines down and chock the airplane. − Use APU or GPU as electrical power supply. − Set both Thrust Levers at IDLE position. − Turn on hydraulic system 2 electric pump. − Cycle Parking Brake handle, while a second person checks that the brake actuating pistons of all brake assemblies are in operation. − Release Parking Brakes. − Advance Thrust levers to MAX position. − Check that the Voice Message TAKEOFF BRAKES does not sound and the EICAS message NO TAKEOFF CONFIG is not presented. − Apply Parking Brake and check that the Voice Message TAKEOFF BRAKES sounds and the EICAS Message NO TAKEOFF CONFIG is presented. − Retard power lever and turn off the hydraulic pump.
Page
1-09-32
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
32-50-00 EXTERNAL STEERING DISENGAGEMENT SWITCH Number installed Number required for dispatch
-50-00 External Steering *** Disengagement Switch
C
1
0
(O) May be inoperative provided nose wheel steering operates normally.
Placard External Steering Disengagement Switch "INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-32
Code
7 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
32-50-02 CONTROL WHEEL STEERING DISENGAGE BUTTONS Number installed Number required for dispatch
C -50-02 Control Wheel Steering Disengage Buttons
2
1
(M) Pilot’s disengage button may be inoperative provided copilot’s disengage button operates normally.
Placard on the pilot’s console near the steering handle "PILOT CONTROL WHEEL STEERING DISENGAGE BUTTON INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Copilot’s Control Wheel Steering Disengage Button check: − Perform SUBTASK 32-50-00-841-001-A00 (AMM) for airplane preparation. − Press the copilot steering disengage button (STEER DISC) on the control wheel. − Check STEER INOP caution message comes into view. − Move the pedals from full right to full left and check RUDDER movement associated with no steering command. Make sure that the wheels do not move when the pedal is operated. − Press the steering handle to reconnect the steering. − Check STEER INOP caution message goes out of view.
Page
1-09-32
Code
8 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
32-60-00 LANDING GEAR PROXIMITY SWITCHES Number installed Number required for dispatch
-60-00 Landing Gear Proximity Switches
B 19 13
(M) One up lock proximity switch and one down lock proximity switch may be inoperative in each landing gear leg. NOTE: Proximity switches include: air/ground, up lock, down lock, 7-degree-steering and nose-landing-gear doorsequence.
Register as appropriate for maintenance actions. OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Proximity Switch check: To check the proximity switch refer to TASK 32-63-05-700-801-A (AMM).
Page
REVISION 6
1-09-32
Code
9 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-09-32
Code
10 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 33 LIGHTS 33-10-00 COCKPIT/FLIGHT DECK/FLIGHT COMPARTMENT AND INSTRUMENT PANEL LIGHTING SYSTEMS Number installed Number required for dispatch
-10-00 Cockpit/Flight Deck/Flight Compartment and Instrument Panel Lighting Systems
C
-
-
Individual lights may be inoperative provided remaining lights are: a) Sufficient to clearly illuminate all required instruments, controls and others devices for which their are provided, b) Positioned so that direct rays are shielded from flight crewmember's eyes, and c) Lighting configuration and intensity is acceptable to the flight crew.
Placard associated Light or Switch "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-33
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
33-20-00 CABIN INTERIOR ILLUMINATION SYSTEM Number installed Number required for dispatch
-20-00 Cabin Interior Illumination System 1) Airplane Without C Photoluminescent Emergency Escape Path Marking System
-
-
Individual lights may be inoperative provided remaining lighting is sufficient for cabin attendant to perform assigned duties.
C 2) Airplane With Photoluminescent Emergency Escape Path Marking System
-
-
(M)(O) Individual lights including up to 10 per cent of the ceiling and sidewall lamps may be inoperative provided: a) Remaining lighting is sufficient for cabin attendant to perform assigned duties, b) No more than 2 adjacent ceiling and sidewall lamps in the longitudinal or lateral direction are inoperative, c) Ceiling and sidewall lamps in the region of the galley, cabinets and life-raft stowage areas are operative, and d) Overhead lighting at entry must operate in the ON and BRIGHT setting.
Page
1-09-33
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
Placard the Cabin Lighting Control Buttons, at the Attendant's Panel "INOP - DO NOT TURN ON". OPERATIONAL PROCEDURES According to the maintenance procedure below. MAINTENANCE PROCEDURES May be flight crewmember accomplished. The overhead ceiling and sidewall lighting may contain inoperative lights not to exceed more than 10 percent of the total quantity, and no more than two adjacent lamps in the longitudinal or lateral direction may be inoperative. Adjacent lamps are those next to or diagonally opposing lamps. The figure below represents possible scenarios with three adjacent row of lighting. Other scenarios are possible and the figure is for guidance only. Inoperative lamps bulbs are marked with “X”. Each column represents a single overhead bulb. All inoperative lamps must be clear of galley, cabinets and life-raft storage areas.
Page
REVISION 6
1-09-33
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
33-21-02 COCKPIT STERILE LIGHT Number installed Number required for dispatch
-21-02 Cockpit Sterile *** Light
C
-
0
(O) May be inoperative provided alternate procedures are established and used.
Placard Sterile Light Button "INOP". OPERATIONAL PROCEDURES Notify cabin attendant that sterile light is inoperative and use the service interphone system to advise when the cockpit is to be shut out. MAINTENANCE PROCEDURES None.
Page
1-09-33
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
33-23-00 PASSENGER SIGNS Number installed Number required for dispatch
-23-00 Passenger Signs
C
-
-
C
-
-
(M)(O) No passenger or attendant seat may be occupied from which a "No Smoking/Fasten Seat Belt" sign is not readily legible, or that seat must be blocked and placarded "DO NOT OCCUPY". (O) If one or more "No Smoking/ Fasten Seat Belt" signs are inoperative, the affected passenger seat(s), or cabin attendant's seat may be occupied provided: a) The passenger address system operates normally and can be clearly heard throughout the cabin during flight, and b) The passenger address system is used to notify the cabin attendant and passengers when seat belts should be fastened and when smoking is prohibited.
Placard the seats affected by the inoperative signs "DO NOT OCCUPY". OPERATIONAL PROCEDURES Prior to each flight the Captain must verify that the Passenger Address system operates normally and the Flight Attendant is briefed that this system must be used to notify the Flight Attendant and passengers when seats belts must be used, and smoking is prohibited.
Page
REVISION 6
1-09-33
Code
5 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
MAINTENANCE PROCEDURES Verify that NO SMOKING/FASTEN SEAT BELT sign is readily available for affected seat. If the sign is not readily available, block seat(s) and placard “DO NOT OCCUPY”.
33-26-00 COURTESY AND STAIRS LIGHTING SYSTEM Number installed Number required for dispatch
-26-00 Courtesy and Stairs C Lighting System
1
0
May be inoperative provided sufficient light is available at the stairs region.
Placard Courtesy Lights Panel "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
33-30-00 COMPARTMENT LIGHTS (NOSE, TAIL, ETC) Number installed Number required for dispatch
-30-00 Compartment Lights (Nose, Tail, Baggage, etc)
C
-
0
Placard associated Light "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-33
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
33-41-00 LANDING LIGHTS Number installed Number required for dispatch
-41-00 Landing Lights
1) Nose Landing Gear Automatic Extinguishing Function
C
3
2
One may be inoperative for night operations.
C
3
0
May be inoperative for day operations.
C
1
0
(O) May be inoperative provided light is manually turned off after gear retraction.
Placard affected Landing Light Switch "INOP". OPERATIONAL PROCEDURES Flight crew to extinguish light manually after gear retraction. MAINTENANCE PROCEDURES None.
33-42-00 TAXI LIGHT Number installed Number required for dispatch
-42-00 Taxi Light
1) Automatic Extinguishing Function
C C
2 2
1 0
C
2
0
C
1
0
May be inoperative provided nose landing light is operating normally. May be inoperative for day operations. (O) May be inoperative provided light is manually turned off on gear retraction.
Placard Taxi Lights Switch "ONE or BOTH LT INOP". OPERATIONAL PROCEDURES Flight crew to extinguish light manually after gear retraction. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-33
Code
7 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
33-43-00 NAVIGATION LIGHTS Number installed Number required for dispatch
-43-00 Navigation Lights
C
-
4
C
-
0
(O) Any light may be inoperative provided one green light, one red light and two white lights operate normally. May be inoperative for day operations.
In case of both systems failure, placard Navigation Light Switch "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Wingtip Lights (Green & Red): Set the NAV LIGHT switch, on the maintenance panel (behind the pilot’s seat), to the NORM or STBY position to select the system which is operative (See Figure). White Lights (only applicable to airplanes equipped with Four White Navigation Lights): May be flight crewmember accomplished. Set the NAV LIGHT switch, on the aft ramp hail panel (See Figure), to the NORM or STBY position, in case one or both of the tail navigation lights in use become(s) inoperative.
Page
1-09-33
Code
8 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
NAVIGATION LIGHTS CONTROL PANELS
Page
REVISION 6
1-09-33
Code
9 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
33-44-00 WING INSPECTION LIGHTS Number installed Number required for dispatch
-44-00 Wing Inspection Lights
C
2
0
May be inoperative provided ground deicing procedures do not require their use.
Placard INSP Light Switch "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
33-46-00 LOGO LIGHTS Number installed Number required for dispatch
-46-00 Logo Lights ***
D
2
0
Placard LOGO Light Switch "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-33
Code
10 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
33-47-03 STROBE LIGHTS Number installed Number required for dispatch
-47-03 Strobe Lights
C
-
0
May be inoperative for day operations.
Placard STROBE Switch "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-33
Code
11 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
33-47-05 RED BEACON LIGHTS Number installed Number required for dispatch
-47-05 Red Beacon Lights (EMB-135/140/145)
C
2
0
(O) May be inoperative provided: a) Beacon switch is positioned to ON prior to engine start, and b) Strobe lights operate normally.
C
-
0
May be inoperative for day operations provided beacon switch is positioned to ON prior to engine start. NOTE: The rotating beacon switch should be positioned to ON before engine starting to turn the FDR on.
Placard RED BCN Light Switch "INOP". OPERATIONAL PROCEDURES Before Starting Engines or APU: Strobe Switch ................................................... AS REQUIRED For night operation, use strobe lights as a beacon to warn the ground personnel. For day operation, strobe lights are not required. Red Beacon Switch .......................................... ON Set Red Beacon Switch to ON position before engine start to turn FDR on. Check carefully if the engines area is clear before starting engines. MAINTENANCE PROCEDURES Warn all the ground people that the Red Beacon Light is inoperative and that the Strobe lights may be used as a beacon. NOTE: The rotating beacon switch should be positioned to ON before engine starting to turn the FDR on.
Page
1-09-33
Code
12 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
33-48-00 BAGGAGE DOOR EXTERNAL LIGHT Number installed Number required for dispatch
-48-00 Baggage Door *** External Light
C
-
0
Placard Baggage Door External Switch "LIGHT INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
33-50-00 EMERGENCY LIGHTING SYSTEM (BATTERY POWERED) Number installed Number required for dispatch
-50-00 Emergency Lighting System (BatteryPowered) 1) External Lights
C
-
0
May be inoperative for day operations.
2) Floor Proximity Strips
C
-
-
Up to two individual strips may be inoperative provided: a) They are not adjacent, and b) They are not used as na exit locator (amber light).
Placard Emergency Light Switch "SYSTEM INOP". OPERATIONAL PROCEDURES Up to two individual Floor Proximity strips may be inoperative provided they are not adjacent. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-33
Code
13 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
33-50-01 PHOTOLUMINESCENT FLOOR PROXIMITY EMERGENCY ESCAPE PATH MARKING SYSTEM Number installed Number required for dispatch
-50-01 Photoluminescent Floor Proximity Emergency Escape Path Marking System
C
-
-
Up to 10 per cent of any 48 inch section may be damaged or missing.
OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-33
Code
14 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 34 NAVIGATION 34-22-01 MAIN PANEL DISPLAYS Number installed Number required for dispatch
-22-01 Main Panel Displays B 1) MFD Bezel
C
5
4
(M) (O) Non-flying pilot’s MFD may be inoperative.
2
1
One may be inoperative provided opposite MFD works normally.
Placard the affected Display "INOP". The airplane may be dispatched after either the Operational or the Maintenance procedure below be accomplished. OPERATIONAL PROCEDURES If the non-flying pilot PFD display becomes inoperative, revert the onside MFD display to PFD display, switching the MFD Selector Knob on the Reversionary Panel to PFD position. NOTE: The flying pilot PFD and MFD must be operative. MAINTENANCE PROCEDURES If the EICAS display or either the flying pilot MFD or PFD display becomes inoperative, exchange its entire Display Unit with non-flying pilot MFD Display Unit. Perform TASK 34-22-01-000-801-A (AMM) for Display Unit removal and TASK 34-22-01-400-801-A (AMM) for installation. NOTE: The flying pilot PFD and MFD must be operative.
Page
REVISION 6
1-09-34
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
34-22-02 TAT INDICATION Number installed Number required for dispatch
-22-02 TAT Indication
C
2
1
Placard MFD Bezel "TAT INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
34-22-03 SAT INDICATION Number installed Number required for dispatch
-22-03 SAT Indication
C
2
1
Placard MFD Bezel "SAT INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-34
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
34-24-01
MINIMUM EQUIPMENT LIST
STANDBY ATTITUDE INDICATION (ON INTEGRATED STANDBY INSTRUMENT (ISIS) OR ON DEDICATED INSTRUMENT) Number installed Number required for dispatch
-24-01 Standby Attitude Indication (on Integrated Standby Instrument (ISIS) or on dedicated instrument)
C
-
0
May be inoperative provided not required by FAR.
B
-
0
May be inoperative provided: a) Operations are conducted in Day VMC only, and b) Operations are not conducted into known or forecast VFR-on-Top conditions.
Placard Standby Attitude Indicator "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-34
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
34-25-00 HEAD-UP GUIDANCE SYSTEM (HGS) Number installed Number required for dispatch
-25-00 Head-Up Guidance *** System (HGS)
D
-
0
May be inoperative provided approach minimums or operating procedures do not require its use. NOTE: Any mode which operates normally may be used.
Placard Head-Up Guidance System Control Panel (HCP) "HGS INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-34
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
34-25-01 STANDBY MAGNETIC COMPASS Number installed Number required for dispatch
-25-01 Standby Magnetic Compass
B
1
0
B
1
0
B
1
0
(O) May be inoperative provided any combination of three gyro or INS (IRU) stabilized Compass Systems are operative. (O) May be inoperative provided: a) Any combination of two gyro or INS (IRU) stabilized Compass Systems operate normally, and b) Airplane is operating with Dual Independent Navigation Capability and under Positive Radar Control by ATC on the enroute portion of the flight. May be inoperative for flights that are entirely within areas of magnetic unreliability provided at least two Stabilized Directional Gyro Systems are installed, operate normally, and used in conjunction with approved Free Gyro Navigation Techniques.
Placard Standby Magnetic Compass "INOP". OPERATIONAL PROCEDURES As required to meet the MMEL remarks. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-34
Code
5 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
34-27-00 INERTIAL REFERENCE SYSTEM (IRS) Number installed Number required for dispatch
-27-00 Inertial Reference *** System
D
-
0
May be inoperative provided: a) IRS is not used as primary navigation or attitude source, and b) For airplanes equipped with an additional IRS dedicated to the HGS, the HGS is considered inoperative and not used.
Placard IRS Mode Selector Unit Panel "IRS INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-34
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
34-31-00 RADIO ALTIMETER SYSTEM Number installed Number required for dispatch
-31-00 Radio Altimeter System 1) Single Radio Altimeter Installation
2) Dual Radio Altimeter Installation
A
1
0
C
2
1
A
2
0
(M)(O) May be inoperative provided: a) Approach Minimums or operating procedures do not require its use, b) GPWS/EGPWS is considered inoperative, c) TCAS is considered inoperative, d) Radio Altimeter is deactivated, and e) Repairs are made within two flight days. (M) (O) Radio Altimeter 2 may be inoperative provided: a) Approach Minimums or operating procedures do not require its use, and b) Radio Altimeter 2 is deactivated. (M) (O) Radio Altimeter 1 or both may be inoperative provided: a) Approach Minimums or operating procedures do not require its use, b) GPWS/EGPWS is considered inoperative, c) TCAS is considered inoperative if both Radio Altimeters are inoperative, d) Affected Radio Altimeter(s) is deactivated, and e) Repairs are made within two flight days.
Page
REVISION 6
1-09-34
Code
7 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
Placard in Clear View of the Pilots or PFD Bezel "RA* or RA 1 or RA 2 or RA 1 AND RA 2 INOP". OPERATIONAL PROCEDURES Equipment affected by Radio Altimeter deactivation: − RA* or RA 1 circuit breaker pulled: − GPWS/EGPWS inoperative. − WINDSHEAR inoperative. − TCAS inoperative (For airplanes equipped with dual RA, the TCAS will be inoperative only if RA 1 and RA 2 are lost simultaneously). − RA 2 circuit breaker pulled: − None. MAINTENANCE PROCEDURES Radio Altimeter deactivated: Pull and safety affected Radio Altimeter circuit breaker: RADIO ALTIMETER RA* RA 1 RA 2
CIRCUIT BREAKER D14 D14 D21
* Applicable for airplanes equipped with only one Radio Altimeter.
Page
1-09-34
Code
8 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
34-31-01 ALTITUDE ALERTER FUNCTION Number installed Number required for dispatch
-31-01 Altitude Alerter Function
A
1
0
(O) May be inoperative provided: a) Autopilot altitude hold is operative, and b) Enroute Operations do not require its use, and c) Repairs are made within three flight days.
Placard on PFD Bezel "ALTITUDE ALERT INOP". OPERATIONAL PROCEDURES Normal altitude call out and visual alerts (change in colors provided above the altitude display on both PFD’s) shall be used. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-34
Code
9 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
34-31-02 ALTITUDE PRESELECT FUNCTION Number installed Number required for dispatch
-31-02 Altitude Preselect Function
A
1
0
(O) May be inoperative provided: a) Autopilot with altitude hold is operative, b) Enroute operations do not require its use, c) Alternate procedures are established and used, d) Flight Level Change (FLC) mode is considered inoperative and is not used, e) Go Around buttons on the thrust levers are considered inoperative and not used, and f) Repairs are made within three flight days.
Placard adjacent to ASEL knob on Flight Guidance Controller "ASEL INOP". OPERATIONAL PROCEDURES Operational alternate procedures: − Normal altitude call out should be used. The pilot will be responsible to manually select the desired altitude during climb and descent operation. The altitude hold mode shall be used at the desired altitude. − Autopilot must be disengaged during go-around procedure. − Flight Level Change mode and go-around buttons must not be used and should be considered inoperative. NOTE:
− −
Altitude alerter annunciation or altitude preselected information must be disregard by the crewmembers. Dashes on the Altitude Preselect display will be understand as zero feet altitude by the Flight Director.
Page
1-09-34
Code
10 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
Altitude Hold Mode check: On ground, with airplane energized, press the ALT HOLD mode and check that current altitude is presented in the PFD. MAINTENANCE PROCEDURES None.
34-32-00 VOR/ILS SYSTEM Number installed Number required for dispatch
-32-00 VOR/ILS System 1) Instrument Landing System (ILS) 2) Marker Beacon Systems
C C
2 2
-
C
2
-
As required by FAR. May be inoperative provided Approach Minimums do not require its use. May be inoperative provided Approach Minimums do not require its use.
Placard in Clear View of the Pilots or PFD Bezel "VOR/ILS INOP", "ILS INOP" or "MARKER BEACON INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-34
Code
11 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
34-41-00 GROUND PROXIMITY WARNING SYSTEM (GPWS) OR ENHANCED GPWS (EGPWS) Number installed Number required for dispatch
-41-00 Ground Proximity Warning System (GPWS) or Enhanced GPWS (EGPWS)
1) Modes 1 to 4
A
-
0
C
-
0
A
-
0
C
-
0
(O) May be inoperative provided: a) Alternate procedures are established and used, and b) Repairs are made within two flight days. (O) May be inoperative provided: a) It is not required by FAR, and b) Alternate procedures are established and used. (O) May be inoperative provided: a) Alternate procedures are established and used, and b) Repairs are made within two flight days. (O) May be inoperative provided: a) It is not required by FAR, and b) Alternate procedures are established and used.
(continued) Page
1-09-34
Code
12 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
34-41-00 GROUND PROXIMITY WARNING SYSTEM (GPWS) OR ENHANCED GPWS (EGPWS) (CONTINUED) Number installed Number required for dispatch
-41-00 Ground Proximity Warning System (GPWS) or Enhanced GPWS (EGPWS) (continued) 2) Test Mode
A
1
0
C
-
0
B
2
0
C
-
0
4) Advisory Callouts C
-
0
3) Glide Slope Deviation (Mode 5)
***
May be inoperative provided: a) GPWS is considered inoperative, and b) Repairs are made within two flight days. (O) May be inoperative provided: a) It is not required by FAR, and b) GPWS is considered inoperative.
(O) May be inoperative provided it is not required by FAR. (O) May be inoperative provided alternate procedures are established and used.
(continued)
Page
REVISION 6
1-09-34
Code
13 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
34-41-00 GROUND PROXIMITY WARNING SYSTEM (GPWS) OR ENHANCED GPWS (EGPWS) (CONTINUED) Number installed Number required for dispatch
-41-00 Ground Proximity Warning System (GPWS) or Enhanced GPWS (EGPWS) (continued) *** 5) Windshear Warning and Flight Guidance System (Windshear Mode)
*** ***
6) Aural Alerts (EGPWS only) 7) Visual Display (EGPWS only)
C
-
0
C
-
0
C
-
0
C
-
0
(O) May be inoperative provided: a) Alternate procedures are established and used, and b) Windshear Detection and Avoidance System operates normally. (O) May be inoperative provided: a) Alternate procedures are established and used, and b) Takeoffs and landings are not conducted in known or forecast windshear conditions.
Placard GPWS Lights "GPWS INOP".
Page
1-09-34
Code
14 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
OPERATIONAL PROCEDURES Landing Gear Aural Warning check: − − − − −
Airplane .................................................................... ENERGIZE Thrust Levers ........................................................... IDLE LDG GEAR circuit breakers (A6 and A28)............... PULL LANDING GEAR Voice Message ............................ CHECK Return the airplane to its normal configuration.
Operational alternate procedures: − On takeoff, call “Sink Rate” if negative climb occurs before reaching 1500 ft AGL. − Maintain increased awareness of flight path and proximity to terrain. − On Approach, make normal deviation callouts if any approach fails to meet the “Stabilized Approach Criteria Profiles”. − If windshear mode is inoperative, maintain increased awareness of flight path and search for clues which may indicate the presence of windshear. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-34
Code
15 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
34-42-00 WEATHER RADAR SYSTEM Number installed Number required for dispatch
-42-00 Weather Radar System 1) Stabilization Function
C
1
-
As required by FAR.
B
1
0
May be inoperative provided: a) Antenna sweep is parallel to airplane pitch axis, and b) Antenna tilt operates normally.
***
2) Lightning Sensor System
C
-
0
***
3) Windshear Detection and Avoidance System
C
-
0
C
-
0
C
2
1
***
4) Control Panels (Only airplanes equipped with two panels)
(O) May be inoperative provided: a) Alternate procedures are established and used, and b) Windshear Warning and Guidance System operates normally. (O) May be inoperative provided: a) Alternate procedures are established and used, and b) Takeoffs and landings are not conducted in known or forecast windshear conditions.
Placard Weather Radar Control Panel "INOP" or "STABILIZATION INOP".
Page
1-09-34
Code
16 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES Antenna Sweep check: − Gain access to the radar antenna. − Check if the sweep mechanism is aligned with the aircraft longitudinal axis (control mark in the sweep mechanism gear aligned with the reference mark in the antenna structure). − Turn the Radar Mode Control Knob to SBY to disable the stabilization function.
34-42-01 STORMSCOPE Number installed Number required for dispatch
-42-01 Stormscope C 1 - As required by FAR. *** Placard Weather Radar Control Panel "TURBULENCE DET INOP" OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-34
Code
17 06
MINIMUM EQUIPMENT LIST
34-43-00
AIRPLANE OPERATIONS MANUAL
TRAFFIC ALERT AND AVOIDANCE SYSTEM
COLLISION
Number installed Number required for dispatch
-43-00 Traffic Alert and Collision Avoidance System (TCAS I)
Traffic Alert and Collision Avoidance System (TCAS II)
B
-
0
C
-
0
B
-
0
C
-
0
(M) May be inoperative provided: a) System is deactivated and secured, and b) Enroute or approach procedures do not require its use. (M) May be inoperative provided the system is deactivated and secured. (M) May be inoperative provided: a) System is deactivated and secured, and b) Enroute or approach procedures do not require its use. (M) (O) May be inoperative provided: a) Not required by FAR, b) System is deactivated and secured, and c) Enroute or approach procedures do not require its use.
(continued)
Page
1-09-34
Code
18 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
34-43-00
MINIMUM EQUIPMENT LIST
TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM (CONTINUED) Number installed Number required for dispatch
-43-00 Traffic Alert and Collision Avoidance System (continued) 1) Combined Traffic C Alert (TA) and Resolution Advisory (RA) Dual Display System(s)
2) Resolution Advisory (RA) Display System(s)
3) Traffic Alert Display System(s)
2
1
C
2
1
C
-
0
C
-
0
May be inoperative on the non-flying pilot side provided: a) TA and RA visual display is operative on the flying pilot side, and b) TA and RA audio function is operative on flying pilot side. May be inoperative on nonflying pilot side.
(O) May be inoperative provided: a) Traffic Alert (TA) visual display and audio functions are operative, b) TA only mode is selected by the crew, and c) Enroute or approach procedures do not require its use. (O) May be inoperative provided: a) RA visual display and audio functions are operative, and b) Enroute or approach procedures do not require its use.
Page
REVISION 6
1-09-34
Code
19 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
Placard RMU or MFD Bezel Display or Panel "TCAS INOP". OPERATIONAL PROCEDURES RA or TA visual and audio function check: Perform TCAS System test to ensure that RA or TA display and audio functions are operative. MAINTENANCE PROCEDURES Traffic Alert and Collision Avoidance System deactivation: May be flight crewmember accomplished. Pull and safety affected TCAS circuit breaker: MODEL TCAS I TCAS II TCAS 2000
CIRCUIT BREAKER J6 J6 D3
34-51-00 DISTANCE MEASURING EQUIPMENT (DME) SYSTEMS Number installed Number required for dispatch
-51-00 Distance Measuring D Equipment (DME) Systems
-
-
Any in excess of those required by FAR may be inoperative.
Placard PFD Bezel "DME INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-34
Code
20 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
34-52-00 ATC TRANSPONDERS AND AUTOMATIC ALTITUDE REPORTING SYSTEMS Number installed Number required for dispatch
-52-00 ATC Transponders and Automatic Altitude Reporting Systems
B
-
0
D
-
1
May be inoperative provided: a) Enroute operations do not require its use, and b) Prior to flight, approval is obtained from ATC facilities having jurisdiction over the planned route of flight. Any in excess of those required by FAR may be inoperative.
Placard RMU Panel "XPDR INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES None.
34-53-00 ADF SYSTEM Number installed Number required for dispatch
-53-00 ADF System
C
-
-
As required by FAR.
Placard RMU Bezel "ADF INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-34
Code
21 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
34-56-00 GLOBAL POSITIONING SYSTEM Number installed Number required for dispatch
-56-00 Global *** Positioning System
C
-
0
C
-
0
(O) May be inoperative provided alternate procedures are established and used. May be inoperative provided procedures do not require its use.
Placard GPS Panel "INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES None.
Page
1-09-34
Code
22 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
34-60-00 FLIGHT MANAGEMENT SYSTEM Number installed Number required for dispatch
-60-00 Flight *** Management System
1) Navigation Databases
C
-
1
C
-
0
D
-
0
C
-
-
One is required if IRS is used as primary navigation or attitude source. (O) May be inoperative provided alternate procedures are established and used. May be inoperative provided procedures do not require its use. NOTE: Airplanes equipped with EGPWS and operating without FMS will lose the Terrain Clearance Floor mode. A TERRAIN INOP message will be presented on the EICAS. (O) May be out of currency provided: a) Current Aeronautical Charts are used to verify Navigations Fixes prior to dispatch, b) Procedures are established and used to verify status and suitability of Navigation Facilities used to define route of flight, and c) Approach Navigation Radios are manually tuned and identified.
***
2) Joystick Controller
C
-
-
Page
REVISION 6
1-09-34
Code
23 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
Placard FMS Panel "INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES None. NOTE: − The AH-900 AHRS complete alignment requires a valid input of the airplane’s present position from the FMS or through the MDF 1. the present position input through MFD 1 is possible only if the IM-600 has been properly configured (airplanes equipped with EICAS 18 and on). − Airplanes equipped with EGPWS and operating without FMS will loss the terrain clearance floor mode. A TERRAIN INOP message will be presented on the EICAS.
Page
1-09-34
Code
24 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 35 OXYGEN 35-11-00 OXYGEN PRESSURE INDICATION SYSTEMS Number installed Number required for dispatch
-11-00 Oxygen Pressure Indication Systems B
2
1
(O) One may be inoperative provided an approved procedure is used before each departure to ensure that the oxygen supply is at or above the minimum required for flight.
B 2) Passenger Oxygen Pressure Indication System
2
1
(O) One may be inoperative provided an approved procedure is used before each departure to ensure that oxygen supply is at or above the minimum required for flight.
1) Crew Oxygen Pressure Indication Systems
Placard MFD Bezel "OXY PRESS IND INOP". OPERATIONAL PROCEDURES Check if the gage reading, on the oxygen service panel, is at or above the minimum required for dispatch (refer to the AOM 135/1542Section 2-16-25 Minimum Oxygen Pressure for Dispatch). MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-35
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
35-20-00 PASSENGER OXYGEN SYSTEM Number installed Number required for dispatch
-20-00 Passenger Oxygen System
B
1
0
(O) May be inoperative provided: a) Altitude limitations and portable oxygen supplies comply with FAR requirements, b) All air conditioning packs operate normally, c) Pressurization system operates normally, and d) Passengers are appropriately briefed.
1) Automatic Presentation System
C 1
0
(M)(O)May be inoperative provided: a) Manual deployment system operates normally, and b) Flight is conducted at or below FL 300.
2) Passenger Dispensing Units
C -
0
(M)(O)May be inoperative without flight altitude restriction provided: a) Affected seats are placarded and blocked to prevent occupancy, and b) Units operate normally at all usable lavatory and flight attendant locations.
Placard Passenger Oxygen Panel "PAX OXY DEPLOY INOP" or "PAX OXY INOP".
Page
1-09-35
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
OPERATIONAL PROCEDURES If automatic deployment is inoperative and it is necessary to deploy passenger oxygen masks, position the Passenger Oxygen Selector knob to MAN. OR According to the MMEL remarks. MAINTENANCE PROCEDURES Perform TASK 35-20-00-700-801-A (AMM) for manual deployment system operational check. OR According to the MMEL remarks.
Page
REVISION 6
1-09-35
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
35-30-01 PORTABLE OXYGEN UNITS (BOTTLE AND MASK) Number installed Number required for dispatch
-30-01 Portable Oxygen Units (Bottle and Mask)
C -
-
(M) Any in excess of those required by FAR may be unserviceable or missing provided: a) Required distribution of serviceable bottles is maintained throughout airplane, and b) Bottles not properly serviced are replaced, serviced, or removed at the next available maintenance facility.
Placard associated Bottle and Mask "INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES −
May be flight crewmember accomplished.
−
Inoperative bottles and masks are placarded inoperative, removed from the installed location and placed out of sight so they cannot be mistaken for a functional unit.
−
Inoperative bottles and masks are replaced, serviced or removed at the next base maintenance facility.
Page
1-09-35
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
35-30-03
PROTECTIVE (PBE)
BREATHING
MINIMUM EQUIPMENT LIST
EQUIPMENT
Number installed Number required for dispatch
-30-03 Protective Breathing D Equipment (PBE)
-
Any in excess of those required by FAR may be inoperative.
Placard on the affected equipment storage compartment "REMOVED". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-35
Code
5 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-09-35
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 36 PNEUMATIC 36-11-05 ENGINE BLEED SYSTEMS Number installed Number required for dispatch
-11-05 Engine Bleed Systems
C 2
1
C 2
1
(M)(O) Left engine bleed system may be inoperative provided: a) Left engine bleed valve is secured closed, b) APU bleed is operating normally and supplying bleed air, c) Crossbleed valve is closed, and d) Airplane is not operated in known or forecast icing conditions. (M)(O) Left engine bleed system may be inoperative provided: a) Left engine bleed valve is secured closed, b) When APU is not supplying bleed air, flight is conducted at or below FL 250, and c) Airplane is not operated in known or forecast icing conditions.
(continued)
Page
REVISION 6
1-09-36
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
36-11-05 ENGINE BLEED SYSTEMS (CONTINUED) Number installed Number required for dispatch
-11-05 Engine Bleed Systems (continued) C 2
1
C 2
0
(M)(O) Right engine bleed system may be inoperative provided: a) Right engine bleed valve is secured closed, b) Flight is conducted at or below FL 250, and c) Airplane is not operated in known or forecast icing conditions. (M)(O) May be inoperative provided: a) Engine bleed valves are secured closed, b) APU bleed is operating normally and supplying bleed air, c) Flight is conducted at or below 18000 ft MSL, and d) Airplane is not operated in known or forecast icing conditions. NOTE: For airplanes equipped with ISIS, at least Pack 2 and Recirculation Fan 2 must be operative or Pack 1 must be operative.
(continued)
Page
1-09-36
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
36-11-05 ENGINE BLEED SYSTEMS (CONTINUED) Number installed Number required for dispatch
-11-05 Engine Bleed Systems (continued) C 2
0
(M)(O) May be inoperative provided: a) Engine bleed valves are secured closed, b) Flight is conducted at or below 10000 ft MSL, c) Flight is conducted in na unpressurized configuration, d) Airplane is not operated in known or forecast icing conditions, and e) Ambient temperature on the ground is below ISA + 21 °C. NOTE: This configuration is not applicable for airplanes equipped with ISIS.
Placard the affected Bleed Air Button "INOP". OPERATIONAL PROCEDURES When the Left Engine Bleed Shutoff Valve is inoperative and the Right Engine Bleed Shutoff Valve and the APU Bleed Shutoff Valve are operating normally and supplying bleed air, flight should be conducted at or below FL 370. When the Left Engine Bleed Shutoff Valve and the APU Bleed Shutoff Valve are inoperative and the Right Engine Bleed Shutoff Valve is operating normally and supplying bleed air, flight should be conducted at or below FL 250.
Page
REVISION 6
1-09-36
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
When the Right Engine Bleed Shutoff Valve is inoperative and the Left Engine Bleed Shutoff Valve is operating normally and supplying bleed air, flight should be conducted at or below FL 250. When Both Engine Bleed Shutoff Valves are inoperative and the APU Bleed Shutoff Valve is operating normally and supplying bleed air, flight should be conducted at or below 18000 ft. When Both Engine Bleed Shutoff Valves and the APU bleed Shutoff Valve are inoperative, flight should be conducted at or below 10000 ft. Refer to Item 21-31-03 for unpressurized configuration flight. On the ground, ambient temperature must be below ISA + 21°C. MAINTENANCE PROCEDURES NOTE: For MMEL dispatch purposes, the Engine Bleed System is comprised of: Engine Bleed Shutoff Valve (EBV) or Pressure Regulator Shutoff Valve (P-RSOV), Fan Air Valve, Fan Air Thermostat, Pre-Cooler and Bleed Temperature Sensors, Differential Pressure Switch, High Stage Valve, High Stage Position Switch and Bleed Air Check Valve. Engine Bleed Shutoff Valve secured closed: − Gain access to the affected valve (AMM - Chapter 36). − Disconnect, insulate and stow the electrical connector. − Remove the locking screw from the actuator housing. It has a retaining cable. − Turn the valve to the closed position. The locking crank has a hex head so you can put a wrench on it to turn the valve. − Install the locking screw in the hole in the actuator housing that is nearest to the locking crank.
Page
1-09-36
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ENGINE BLEED SHUTOFF VALVE
Page
REVISION 6
1-09-36
Code
5 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
Engine Bleed Pressure Regulator Shutoff Valve secured closed: − Remove the following access panels: 414DB (LH pylon) or 424DB (RH pylon). − Verify that the pneumatic system is de-pressurized and that the solenoid is de-energized. − Loosen the position indicator lock screw. − Slide the lock into the recess of the cover plate. A rotation of the screw may be necessary to center the lock in the recess of the cover plate. − Torque the position indicator lock screw to 11 to 13 lb-in.
ENGINE BLEED PRESSURE REGULATOR SHUTOFF VALVE
Page
1-09-36
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
REVISION 6
1-09-36
Code
7 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
36-12-01 APU BLEED SYSTEM Number installed Number required for dispatch
-12-01 APU Bleed System
C 1
0
(M)(O) May be inoperative provided: a) APU bleed shutoff valve is secured closed, and b) APU bleed is not used.
Placard APU Bleed Button "INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES APU Bleed Shutoff Valve secured closed: − Gain access to the valve (AMM - Chapter 36). − Remove, insulate and stow the electrical connector. − Check valve closed indication.
Page
1-09-36
Code
8 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
APU BLEED SHUTOFF VALVE
Page
REVISION 6
1-09-36
Code
9 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
36-20-00 BLD APU LEAK WARNING MESSAGE Number installed Number required for dispatch
-20-00 BLD APU LEAK Warning Message
C 1
0
May be inoperative provided APU is considered inoperative and not used.
Placard EICAS Bezel "BLD APU LEAK MESSAGE INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-36
Code
10 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 38 WATER/WASTE 38-10-00 POTABLE WATER SYSTEMS Number installed Number required for dispatch
-10-00 Potable Water System
C -
-
(M) Individual components may be inoperative provided: a) Associated components are deactivated or isolated, and b) Associated components are verified not to have leaks. NOTE: Any portion of the system, which operates normally, may be used.
C -
-
(M) May be inoperative provided: a) System is drained, and b) Procedures are established to ensure that system is not serviced.
Placard External Potable Water Service Door "DO NOT SERVICE". Register as appropriate for maintenance actions. OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES − Deactivate or isolate the associated inoperative components. − If system is leaking, it must be drained. Ground service must be contact to drain system. − If tank can not be drained, accomplish AMM TASK 38-10-05-790801-A for the tank valve leakage test.
Page
REVISION 6
1-09-38
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
38-30-00 LAVATORY WASTE SYSTEMS (INCLUDING WHEELCHAIR ACCESSIBLE LAVATORIES) Number installed Number required for dispatch
-30-00 Lavatory Waste Systems (Including Wheelchair Accessible Lavatories)
C -
-
(M) Individual components may be inoperative provided: a) Associated components are deactivated or isolated, and b) Associated components are verified not to have leaks. NOTE: Any portion of the system which operates normally may be used.
C -
-
(M)(O) Associated lavatory system(s) may be inoperative provided: a) Associated components are deactivated or isolated to prevent leaks, and
b) Associated lavatory door(s) is secured closed and placarded inoperative. NOTE: These provisions are not intended to prohibit inspections by crewmembers. Placard Lavatory Door "LAVATORY INOPERATIVE". Register as appropriate for maintenance actions.
Page
1-09-38
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
OPERATIONAL PROCEDURES − Inspections of the lavatory by crewmembers. − Flight attendant must be briefed that the lavatory is locked and may not be used. − Advise Ground Service Personnel not to service Lavatory waste system. MAINTENANCE PROCEDURES − Deactivate or isolate the associated inoperative components. In case of Toilet Overservicing, perform AMM TASK 05-50-12-700801-A within 10 FC. − If system is leaking, it must be drained. Ground service must be contact to drain system. In case of Toilet Overservicing, AMM TASK 05-50-12-700-801-A must be performed prior to the next flight. − May be flight crewmember accomplished: Lock lavatory door and install "LAVATORY INOPERATIVE" placard on lavatory door.
Page
REVISION 6
1-09-38
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-09-38
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 45 CENTRAL MAINTENANCE COMPUTER 45-45-01 CENTRAL MAINTENANCE COMPUTER (CMC) Number installed Number required for dispatch
-45-01 Central Maintenance Computer (CMC)
C 1
0
(M) May be inoperative provided maintenance procedures do not require its use.
Register as appropriate for maintenance personnel actions. OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-45
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-09-45
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 49 AIRBORNE AUXILIARY POWER 49-00-00 AUXILIARY POWER UNIT (APU) Number installed Number required for dispatch
-00-00 Auxiliary Power Unit (APU)
C 1
0
(M) (O) May be inoperative provided: a) APU is deactivated, and b) Procedures are not dependent upon its use.
Placard APU Control Panel "INOP". OPERATIONAL PROCEDURES A Pneumatic Start Unit is required for engine start when APU is inoperative. Refer to TASK 20-40-03-860-801-A (AMM) to connect the Pneumatic Start Unit. If no Pneumatic Start Unit is available, at least one engine should be kept running during turn-around (refer to AOM Section 1-12-25 Refueling with an Engine Running and Deplaning or Boarding with One Engine Running procedures). MAINTENANCE PROCEDURES May be flight crewmember accomplished. Pull and safety the APU CONTROL circuit breakers, (C30) on the Circuit Breaker panel and the (E6) on the Left DC distribution box.
Page
REVISION 6
1-09-49
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
49-52-02 APU BLEED AIR SYSTEM Number installed Number required for dispatch
-52-02 APU Bleed Air System
C 1
0
(O) May be inoperative provided APU bleed shutoff valve remains closed during APU operation.
Placard APU Bleed Button "INOP". OPERATIONAL PROCEDURES Refer to Item 49-00-00 to engine start when APU bleed is inoperative. The APU bleed shutoff valve must remain closed during APU operation. MAINTENANCE PROCEDURES None.
49-70-01 APU OIL LO PRESS CAUTION MESSAGE Number installed Number required for dispatch
-70-01 APU OIL LO PRESS Caution Message
C 1
0
May be inoperative provided APU is used on ground only.
Placard APU Control Panel "USE ONLY ON GROUND". Placard EICAS Bezel "APU OIL LO PRESS MESSAGE INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-49
Code
2 06
REVISION 6
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
49-70-02 APU OIL HI TEMP CAUTION MESSAGE Number installed Number required for dispatch
-70-02 APU OIL HI TEMP Caution Message
C 1
0
May be inoperative provided APU is used on ground only.
Placard APU Control Panel "USE ONLY ON GROUND". Placard EICAS Bezel "APU OIL HI TEMP MESSAGE INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
49-70-03 APU FAIL CAUTION MESSAGE Number installed Number required for dispatch
-70-03 APU FAIL Caution Message
C 1
0
May be inoperative provided APU is used on ground only.
Placard APU Control Panel "USE ONLY ON GROUND". Placard EICAS Bezel "APU FAIL MESSAGE INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-49
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
49-74-01 APU HOURMETER FUNCTION Number installed Number required for dispatch
-74-01 APU Hourmeter Function
C 1
0
(M) May be inoperative provided alternate procedures are used to accomplish hourmeter function.
Register in the appropriate document for the necessary actions. OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES The operator shall develop appropriate procedures according to its airplane utilization to control APU operating hours.
Page
1-09-49
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 52 DOORS 52-12-00
MAIN DOOR SYSTEM
HYDRAULIC
ACTUATION
Number installed Number required for dispatch
-12-00 Main Door Hydraulic B Actuation System
1
0
(M) May be inoperative provided damping function operates normally.
Placard on Door Panel (Entrance and Exterior) "DOOR ACTUATION INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Damper Function checking: Lift the door manually up to its mid closed position, and then let the door to come down. Check that door moves down slowly, with damping. NOTE: Care should be taken to avoid that the door coming down without damping.
Page
REVISION 6
1-09-52
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
52-51-00 C&D AEROSPACE FLIGHT DECK SECURITY DOOR Number installed Number required for dispatch
-51-00 C&D Aerospace *** Flight Deck Security Door (FAR 25.795 Compliant) 1) Door Latch A
1
0
2) Flight Deck Door A Panel Pressure Relief Latch
1
0
3) Dead Bolt
1
0
C
May be inoperative provided: a) Door Dead Bolt is operative, b) Door Dead Bolt is used to lock and unlock the door, and c) Repairs are made within two flight days. May be inoperative in the latched position provided repairs are made within two flight days.
Placard affected item “INOP”. OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
1-09-52
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
52-70-00 DOORS WARNING SYSTEM (DOOR POSITION INDICATION ON MFD AND EICAS) Number installed Number required for dispatch
-70-00 Doors Warning System (Door Position Indication on MFD and EICAS) 1) Main Door
B
1
0
(O) May be inoperative provided door is verified closed and latched before each departure.
2) Baggage Door
C
1
0
(O) May be inoperative provided door is verified closed and latched before each departure.
3) Emergency Access Hatch
C
1
0
(M) May be inoperative provided affected hatch is verified closed and latched before each departure.
4) Access Hatches
C
3
0
(M) May be inoperative provided affected hatch is verified closed and latched before each departure.
5) Fueling Door
C
1
0
(M) May be inoperative provided door is verified closed and latched before each departure.
6) Internal Baggage C Access Door
1
0
(O) May be inoperative provided: a) Door is verified closed and latched before each departure, and b) Door remains closed during the entire flight.
Placard MFD and EICAS Bezel "AFFECTED DOOR WARNING IND INOP". Page
REVISION 6
1-09-52
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
OPERATIONAL PROCEDURES Carefully check all doors closed and latched before each departure. Main door internal check must be done by using a flashlight to confirm that all the red marks of each door are aligned (see figure). NOTE: This procedure requires the usage of a flashlight to help visualizing the red marks alignment precisely. The Internal Baggage Access Door must remain closed during the entire flight. MAINTENANCE PROCEDURES Carefully check all doors closed and latched before each departure. Main and baggage doors must be checked aligned with the fuselage and the handles must be stowed.
Page
1-09-52
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
AIRSTAIRS MAIN DOOR RED MARKS
Page
REVISION 6
1-09-52
Code
5 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-09-52
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 56 WINDOWS 56-10-01 WINDSHIELD Number installed Number required for dispatch
-10-01 Windshield 1) Glass Plies
C
2
1
(M)(O) One window outer glass ply may be cracked or delaminated provided: a) Visibility through affected window is acceptable, b) Vision is not impaired through remaining windows, c) Heat to affected window is deactivated, and d) Airplane is not operated in known or forecast icing conditions.
Placard associated Windshield Heating Button "DEACTIVATED". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES Pull and safety the WSHLD TEMP circuit breaker associated with the cracked windshield (G13 or J20).
Page
REVISION 6
1-09-56
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-09-56
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 73 ENGINE FUEL AND CONTROL 73-22-01 FULL AUTHORITY DIGITAL ELECTRONIC CONTROLS (FADEC) Number installed Number required for dispatch
-22-01 Full Authority Digital A Electronic Controls (FADEC)
4
0
(M) May be dispatched with the EICAS advisory messages E1 (2) CTL A (B) DEGRADED or E1 (2) SHORT DISP presented and/or with category C and D FADEC faults presented on CMC/FADEC download provided: a) EICAS caution messages ENG NO TO DATA, E1 (2) CTL A (B) FAIL, E1 (2) CTL FAIL, or E1 (2) NO DISP are not present on EICAS for takeoff, b) Repairs are made in accordance with times established by engine manufacturer, and a) No extensions are authorized. NOTE: The intent of the 0 in the number required for dispatch column is to show that dispatch is allowed with some faults present in all four FADEC’s.
Placard Power Plant Control Panel "FADEC XX DEFERRED BY MEL/TLD".
Page
REVISION 6
1-09-73
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
OPERATIONAL PROCEDURES According to the MMEL remarks. The table below shows FADEC faults annunciated by EICAS message associated with dispatch permissions.
EICAS MESSAGE
MESSAGE LEVEL
REPAIR INTERVAL CATEGORY
REPAIR INTERVAL
E1(2) CTL A(B) FAIL E1(2) CTL A(B) DEGRAD E1(2) NO DISP (∗) E1(2) SHORT DISP (∗)
Caution Advisory Caution Advisory
A0 B A0 B
No Dispatch 3 Calendar Days No Dispatch 3 Calendar Days
(∗) For airplanes equipped with EICAS Version 16 and on. For dispatchable FADEC faults category C and D, that are presented only in the CMC, refer to Rolls Royce AE3007A Series Maintenance Manual, Systems Description Section 05-14-00. MAINTENANCE PROCEDURES According to the MMEL remarks.
Page
1-09-73
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
73-32-01 ENGINE FUEL TEMPERATURE SENSORS Number installed Number required for dispatch
-32-01 Engine Fuel Temperature Sensors
C 2
0
(O) May be inoperative provided temperature of fuel in the tank remains above 4 °C throughout the flight.
C 2
0
(O) May be inoperative with fuel tank temperature below 4 °C provided icing inhibitor is added to the fuel.
Placard EICAS Bezel "E1 (or 2) LO TEMP MESSAGE INOP". OPERATIONAL PROCEDURES Ensure that icing inhibitor is added to the fuel. If an icing inhibitor has not been added, refer to MFD fuel page and ensure temperature of fuel in the tank remains above 4°C throughout the flight. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-73
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-09-73
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
73-33-01 E1 (2) FUEL IMP BYP ADVISORY MESSAGES Number installed Number required for dispatch
-33-01 E1 (2) FUEL IMP BYP Advisory Messages
C 2
1
(M) One may be inoperative provided: a) Fuel low temperature messages operate normally, b) Malfunction is verified to be in the fuel-filter electrical/mechanical impending-bypass indicator or its associated wiring, and c) Fuel-filter mechanical actual-bypass indicator is checked not extended before each departure.
Placard EICAS Bezel "E1 (or 2) FUEL IMP BYP MESSAGE INOP". OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES −
Energize the airplane with a DC Power Supply (TASK 20-40-01-860801-A – AMM). − Pull the START 2 circuit breakers (B12 and B23 respectively) and attach DO-NOT-CLOSE tags to them. − Open the associated engine lower cowling door (TASK 71-12-01000-801-A – AMM). − Use the following check procedures as a troubleshooting reference: Visual indicators (pop-up buttons) check: − Check that both the electrical/mechanical impending-bypass indicator and the mechanical actual-bypass indicator (See Figure) have their respective pop-ups buttons not protruded.
Page
REVISION 6
1-09-73
Code
5 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
Electrical connector (wiring) check: − Disconnect the electrical connector from the electrical/mechanical impending-bypass indicator (See Figure) and wait at least 10 seconds. − Check that EICAS advisory message E1 (2) FUEL IMP BYP is displayed. − Connect the electrical connector to the electrical/mechanical impending-bypass indicator. − Check that EICAS advisory message E1 (2) FUEL IMP BYP goes out of view. Electrical/mechanical impending-bypass indicator (switch) check: − Check that the resistance between pins B and C in the electrical/mechanical impending-bypass indicator is not greater than 10 ohms. − Check that the resistance between the indicator shell and pins B and C, one at a time, is not lower than 1000 ohms. After checking: − Close the engine lower cowling door (TASK 71-12-01-400-801-A – AMM). − Push in the START 1 and START 2 circuit breakers (B12 and B23 respectively) back and remove the DO-NOT-CLOSE tags from them. − Remove the DC Power Supply (TASK 20-40-01-860-801-A – AMM).
Page
1-09-73
Code
6 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
FUEL FILTER BYPASS INDICATORS
Page
REVISION 6
1-09-73
Code
7 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
73-33-02 FUEL FILTERS Number installed Number required for dispatch
A
-33-02 Fuel Filters
2
1
(M) One E1 (2) FUEL IMP BYP advisory message may be displayed per engine provided: a) Associated fuel-filter mechanical actual-bypass indicator is checked not extended before each departure, and b) Fuel filter is replaced within ten flight hours.
Register as appropriate for maintenance actions. OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Associated fuel-filter mechanical actual-bypass indicator is checked not extended before each flight.
Page
1-09-73
Code
8 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
73-40-03 FUEL FLOW INDICATIONS Number installed Number required for dispatch
-40-03 Fuel Flow Indications
C 2
1
(O) One may be inoperative provided: a) Associated engine parameters are monitored throughout the flight, and b) Associated fuel quantity indications operate normally.
Placard EICAS Bezel "FUEL FLOW INOP". OPERATIONAL PROCEDURES Monitor remaining engine parameters within normal values. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-73
Code
9 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-09-73
Code
10 06
REVISION 6
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
ATA CHAPTER 74 IGNITION 74-20-00 IGNITION SYSTEM CHANNELS Number installed Number required for dispatch
-20-00 Ignition System Channels
B 4
3
(O) One may be inoperative provided engine is started by positioning the ignition selector knob to ON.
Placard Power Plant Control Panel on overhead panel, close to the Ignition Selector Knob of the affected engine "ONE CHANNEL INOP". OPERATIONAL PROCEDURES − Before starting the affected engine, select Ignition Selector Knob ON. − Upon reaching 14% N2 during start, check green label IGN AB on EICAS. − After normal engine start cycle completed, check steady engine parameters. − Select Ignition Selector Knob AUTO (blank indication on EICAS). MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-74
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-09-74
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 77 ENGINE INDICATING 77-41-02 HP VIBRATION INDICATION Number installed Number required for dispatch
-41-02 HP Vibration Indication
C 2
1
One may be inoperative provided tactile or audible indications allow the vibrating engine to be identified.
Placard EICAS Bezel "HP VIB INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES None.
Page
REVISION 6
1-09-77
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-09-77
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 78 ENGINE EXHAUST 78-30-00 THRUST REVERSER Number installed Number required for dispatch
-30-00 Thrust Reversers ***
C
2
1
(M)(O) Any door actuation, lock or control on one thrust reverser may be inoperative provided: a) Thrust reverser is not used, and b) System is deactivated and secured stowed.
Placard Control Pedestal "THRUST REVERSER INOP". OPERATIONAL PROCEDURES When operating with one thrust reverser secured stowed, the FADEC of the operative side will only command reverse thrust if the associated Thrust Lever is requesting reverse thrust and the Thrust Lever of the affected side is set to idle. MAINTENANCE PROCEDURES Perform TASK 78-31-01-980-801-A (AMM) for the affected thrust reverser stowage. In case of thrust reverser hydraulic system leakage, perform TASK 78-31-01-980-803-A (AMM) before performing TASK 78-31-01-980801-A (AMM).
Page
REVISION 6
1-09-78
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
78-34-00 ENG1 (2) REV DISAGREE MESSAGES Number installed Number required for dispatch
-34-00 ENG1 (2) REV *** DISAGREE Messages
C
2
1
(M)(O) May be inoperative on one thrust reverser provided: a) Thrust reverser is not used, and b) System is deactivated and secured stowed.
OPERATIONAL PROCEDURES According to the MMEL remarks. MAINTENANCE PROCEDURES Perform TASK 78-31-01-980-801-A (AMM) for thrust reverser stowage.
Page
1-09-78
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 79 ENGINE OIL 79-32-01 LOW OIL PRESSURE SWITCHES Number installed Number required for dispatch
-32-01 Low Oil Pressure Switches
C 2
0
May be inoperative provided: a) Oil pressure indication is available and is monitored throughout the flight, and b) Engine oil quantity is serviced each flight day.
Placard EICAS Bezel "E1 (or 2) OIL LOW PRESS MESSAGE INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Perform TASK 12-12-01-600-801-A (AMM) for oil quantity servicing.
Page
REVISION 6
1-09-79
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
79-33-01 OIL LEVEL INDICATION SYSTEMS Number installed Number required for dispatch
-33-01 Oil Level Indication Systems
C 2
0
(M) May be inoperative provided engine oil quantity is serviced each flight day.
Placard MFD Bezel "OIL1 (or 2) IND INOP". OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Perform TASK 12-12-01-600-801-A (AMM) for oil quantity servicing.
79-34-01 OIL PARTICLE SENSORS Number installed Number required for dispatch
-34-01 Oil Particle Sensors C 2
0
(M) May be inoperative provided the oil tank mag plug is visually checked each flight day.
Register as appropriate for maintenance actions. OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Perform the visual check on the affected oil tank magnetic plug. Refer to TASKS 79-34-01-000-801-A and 79-34-01-400-801-A (AMM) for plug removal and installation.
Page
1-09-79
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
79-35-01 E1 (2) OIL IMP BYP MESSAGES Number installed Number required for dispatch
-35-01 E1 (2) OIL IMP BYP C 2 Messages
0
(M) May be inoperative provided: a) Visual indicator(s) are checked each flight day and neither is found extended, and b) The CMC is checked each flight day and the ENG OIL DEBRIS maintenance message is not presented. NOTE: The affected E1 (2) OIL IMP BYP advisory message may be displayed.
Register as appropriate for maintenance actions. OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Open the affected engine lower cowling and verify the visual indicator inside housing.
Page
REVISION 6
1-09-79
Code
3 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
79-35-02 OIL FILTERS Number installed Number required for dispatch
-35-02 Oil Filters
A
2
1
(M) One E1 (2) OIL IMP BYP advisory message may be displayed for one engine provided: a) Maintenance procedures do not require its replacement, and b) Oil filter element is replaced in less than 20 flight hours.
Register as appropriate for maintenance actions. OPERATIONAL PROCEDURES None. MAINTENANCE PROCEDURES Perform TASK 79-30-00-200-802 (ROLLS ROYCE AE3007A Series Maintenance).
Page
1-09-79
Code
4 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
MINIMUM EQUIPMENT LIST
ATA CHAPTER 80 STARTING 80-10-02 STARTER CONTROL VALVE Number installed Number required for dispatch
-10-02 Starter Control Valve
B
2
1
(M) (O) One may be inoperative closed provided: a) Associated EICAS Caution message E1 (2) ATS SOV OPN operates normally, and b) Manual override start procedures are used.
Placard EICAS Bezel or Powerplant Control Panel "STARTER CONTROL VALVE INOP". OPERATIONAL PROCEDURES Manual Override Start Procedure: − Ensure communications are in place with maintenance personnel operating the Starter Control Valve manually. − When ready to start, perform a normal start. − Ensure maintenance personnel are notified when engine N2 comes to the IDLE. − Ensure ground personnel are clear after start. MAINTENANCE PROCEDURES Manual Override Start Procedure: − Use the rear (ramp) interphone system for communications between persons on the ramp and in the cockpit. − Perform TASK 80-10-02-980-801-A (AMM) to start the affected engine using Starter Control Valve Manual Override procedure. − When the task is complete and all personnel and equipment are clear of the airplane, notify the cockpit.
Page
REVISION 6
1-09-80
Code
1 06
MINIMUM EQUIPMENT LIST
AIRPLANE OPERATIONS MANUAL
EICAS Caution Message E1(2) ATS SOV OPN check: − Access the Starter Control Valve by performing TASK 80-10-02980-801-A (AMM). − Airplane. ...................................................... ENERGIZE − EICAS Override Switch (cockpit) ................ OVRD − Starter Control Valve ................................... OPEN Tell the ground personnel to open the Starter Control Valve. − Check Caution Message E1(2) ATS SOV OPN displayed on the EICAS. − EICAS Override Switch ............................... NORM
Page
1-09-80
Code
2 06
REVISION 6
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
SECTION 1-02 NORMAL PROCEDURES TABLE OF CONTENTS Page Block Introduction ................................................................................ 1-02-00 Checklist..................................................................................... 1-02-01 Normal Procedures External Safety Inspection .................................................... 1-02-05 Internal Safety Inspection...................................................... 1-02-09 Power Up .............................................................................. 1-02-13 Before Start - First Flight....................................................... 1-02-17 Before Start - Through Flight ................................................ 1-02-21 Cleared to Start..................................................................... 1-02-25 Push-Back Operation............................................................ 1-02-27 After Start.............................................................................. 1-02-29 Before Takeoff ...................................................................... 1-02-33 Cleared Into Position............................................................. 1-02-37 Takeoff and After Takeoff Technique ................................... 1-02-41 After Takeoff ......................................................................... 1-02-45 Climb Technique ................................................................... 1-02-47 Fuel Transfer Technique....................................................... 1-02-48 Descent................................................................................. 1-02-49 Descent Technique ............................................................... 1-02-53 Approach............................................................................... 1-02-57 Before Landing...................................................................... 1-02-61 Landing Technique ............................................................... 1-02-65 After Landing......................................................................... 1-02-69 Shutdown .............................................................................. 1-02-73 Leaving the Airplane ............................................................. 1-02-77
Page
REVISION 6
1-02-00
Code
1 02
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Supplementary Procedures Environmental ....................................................................... 1-02-79 Operation in Icing Conditions ........................................ 1-02-79 Turbulent Air Penetration............................................... 1-02-79 Volcanic Ash.................................................................. 1-02-79 Lightning Strike.............................................................. 1-02-79 Pressurization in Manual Mode ..................................... 1-02-79 Navigation ............................................................................. 1-02-80 FMS ............................................................................... 1-02-80 RVSM ............................................................................ 1-02-80 Engine ................................................................................... 1-02-81 Engine Start with Batteries ............................................ 1-02-81 Cross Start..................................................................... 1-02-81 Engine Start Assisted by APU ....................................... 1-02-81 Single Engine Taxi......................................................... 1-02-81 CAT II Operation ................................................................... 1-02-83 Maintenance Inspections Performed by the Flight Crew....... 1-02-86 Profiles ....................................................................................... 1-02-95
Page
1-02-00
Code
2 02
REVISION 5
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
INTRODUCTION The operating procedures defined in this section have been defined with the purpose of providing expanded normal procedures that should be used by trained flight crew to ensure that the airplane is in a proper condition and correctly configured for each phase of flight. The source document for all procedures contained herein is the approved Airplane Flight Manual (AFM). In the event that any procedure disagrees with the AFM, the AFM will prevail. In the event that any of the procedures are missing or unusable, operations may be continued provided the approved AFM is available for use. The normal procedures established are based on the assumption that all equipment is operating normally. It is the crew’s responsibility to verify proper system response. In case improper indications are observed, verification of the appropriate controls position, checking of circuit breakers and testing of the related system should be performed to determine whether the condition affects dispatch or compliance with the MMEL, and whether any requires maintenance action is required. ∗ Items marked with an asterisk are to be performed at least once a day, by flight crew or maintenance personnel, at the operator’s discretion.
Page
REVISION 4
1-02-00
Code
3 02
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
AREAS OF RESPONSIBILITY - TASK SHARING Operating procedures and flight crew duties in this manual are organized according to the area of responsibility concept. Areas of responsibility are areas of the cockpit panels and consoles that are operated by a specific pilot. These areas exist for the sake of crew coordination and a pilot must always advise the other pilot if he is intending to operate something at the other pilot's Area of Responsibility. Duties are also assigned according to the mission phase. Pre-flight and post-flight duties are shared between the pilot-in-command (CPT) and the copilot (F/O), while in-flight phases are shared between the flying pilot (PF) and the non-flying pilot (PNF), or for both pilots (C/F). The pilot-in-command retains final responsibility and authority for all actions directed and performed throughout the flight. The sequence of normal procedures is derived from a scan-flow, for the sake of standardization. However, certain items may derive from the scan-flow to be handled in the most logical sequence if required by the associated condition.
Page
1-02-00
Code
4 02
REVISION 4
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
The following figure depicts each flight crew member’s area of responsibility, along with the scan-flow sequence.
The numbers show the recommended scan flow sequence and area of responsibility for the captain. The letters show the recommended scan flow sequence and area of responsibility for the copilot.
Page
REVISION 4
1-02-00
Code
5 02
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
In-flight, the responsibilities are as follows: PF is in charge of: • Throttles; • Controlling the flight path and speed; • Airplane configuration; • Navigation. PNF is in charge of: • Check List reading; • Carrying out the required actions at their areas of responsibility; • Engine Shut down (Coordinated with the PF); • ATC communications. The normal procedures rely on the checklist philosophy as a follow up and as a means of confirming that the airplane is in proper configuration for that phase of operation. All the normal procedures are to be carried out using the Challenge and Respond technique. The in-flight reading of the items is done by the PNF. They are responded by the PNF himself with the exception of the BEFORE LANDING phase when the PF must respond; the on-ground reading of the items is done by the copilot and responded by the copilot except in the phases prior to takeoff and the shutdown phase, when the items are responded by the pilot who has performed the action. The "Leaving the airplane" actions and responding can be done by any of the pilots. However, it is recommended that both pilots check these items.
Page
1-02-00
Code
6 02
REVISION 4
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
NORMAL CHECKLIST EXTERNAL SAFETY INSPECTION Wheel Chocks .......................IN PLACE ----------------NOSE SECTION----------------Access Doors and Panels .....SECURED Static Ports............................NO OBSTRUCT Sensors and Pitot Tubes .......CONDITION, NO OBSTRUCT Windshield Wipers ................CONDITION Air Inlets ................................NO OBSTRUCT Radome.................................SECURED Nose Gear.............................CHECK Static Discharger ...................CONDITION Hydraulic Compartment.........NO LEAKS Oxy Press Green Disc ...........CHECK IN PLACE ---------------------FUSELAGE-------------------Access Doors and Panels .....SECURED Fueling Compartment Door ...SECURED Inspection Lights ...................CONDITION Air Inlets and Outlets .............NO OBSTRUCT Red Beacon ..........................CONDITION Fuel Tanks Draining ..............PERFORM Antennas ...............................CONDITION Ram Air Inlet .........................NO OBSTRUCT Fluid Drain Holes ...................NO LEAKS -----------------------WINGS----------------------Landing Lights .......................CONDITION Emergency Lights..................CONDITION Wing Leading Edge ...............CONDITION
Access Doors and Panels..... SECURED Direct Measuring Sticks ........ PUSHED IN Air Inlets, Outlets and Vents . NO OBSTRUCT Vortilons and Vortex Gen ...... NUMBER AND CONDITION Nav and Strobe Lights .......... CONDITION Static Discharger .................. NUMBER AND CONDITION Flight Control Surface & Fair. CONDITION Main Gear............................. CHECK --------------TAIL CONE SECTION------------Air Inlets and Outlets ............ NO OBSTRUCT Antennas .............................. CONDITION Access Doors and Panels..... SECURED Pylons................................... CONDITION Engines ................................ CHECK Thrust Reverser Doors.......... FLUSH WITH NACELLE Horizontal Stabilizer .............. CONDITION Logo Lights ........................... CONDITION Flight Control Surfaces ......... CONDITION Static Dischargers................. NUMBER AND CONDITION APU ...................................... CONDITION Pressurization Static Ports.... NO OBSTRUCT Baggage Door....................... LATCHED/ LOCK PANEL CLOSED Fluid Drain Holes .................. NO LEAKS
Page Code
JUNE 20, 2002
1-02-01
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
NORMAL CHECKLIST INTERNAL SAFETY INSPECTION ----------------COCKPIT----------------Manuals & Documents....... ON BOARD Cockpit Emergency Equip.. CKD Overhead/Main/Pedestal Panels ............................... CKD Radar................................. OFF ELT.................................... ARMED IRS 1 & 2 ........................... OFF Gear .................................. DOWN Passenger Oxygen ............ AUTO Gust Lock .......................... LOCKED Speed Brake...................... CLOSED Parking Brake .................... ON Flaps.................................. 0° Free Fall ............................... CKD ----------PASSENGER CABIN----------Cabin Emergency Equip .... CKD PBE indicator..................... GREEN Emergency Exit.................. CLOSED AND LATCHED Overwing Fueling Caps...... SECURED PAX Seats and Belts ......... CONDITION Galley and Toilet ................ CONDITION Lav Smoke Det System ..... CKD Baggage Compart Access Door................................... CLOSED AND LATCHED Pocket Door....................... OPEN AND LOCKED POWER UP APU START WITH BATTERIES Internal Safety Inspection... COMPLETED Batteries 1 & 2 ................... AUTO Avionics Master 1 or 2 ....... ON ∗ Batteries Voltage............... CKD
Avionics Master 1 & 2 ........ OFF Pump Power ...................... ON ∗ Fire Detection.................... CKD APU Master ....................... ON/WAIT 3 SECS/START/ THEN ON Avionics Master 1 & 2 ........ ON Push Button Lights............. CKD -----------------After 3 minutes----------------APU Bleed ......................... OPEN Air Cond Panel................... AS REQ APU START WITH GPU Internal Safety Inspection .. COMPLETED Batteries 1 & 2 .................. AUTO Avionics Master 1 or 2 ....... ON GPU Voltage...................... CKD Avionics Master 1 & 2 ........ OFF GPU................................... ON Pump Power ...................... ON ∗ Fire Detection.................... CKD APU Master ....................... ON/WAIT 3 SECS/START/ THEN ON GPU................................... OFF Avionics Master 1 & 2 ........ ON Push Button Lights............. CKD -------------------After 3 minutes--------------APU Bleed ......................... OPEN Air Cond Panel................... AS REQ GPU POWER (NO APU) Internal Safety Inspection .. COMPLETED Batteries 1 & 2 ................... AUTO Avionics Master 1 or 2 ....... ON GPU Voltage...................... CKD GPU................................... ON
Page Code
1-02-01
2 01
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
NORMAL CHECKLIST BEFORE START CVR .........................CKD ............. CPT
CLEARED TO START Windows ......................CLSD ...............C/F
Electrical Panel ........SET.............. CPT
Red Beacon .................ON ...................CPT
Emergency Lights ....CKD&ARMD CPT
Pump Power.................ON ...................CPT
♦
Fuel Panel & Qty......SET/_lb/kg ... CPT
♦
Power Plant Panel....SET.............. CPT
Electrical Panel ............SET .................CPT
∗
Elec Hyd Pumps ......CKD&OFF.... CPT
FADEC.........................RESET/ALT .....CPT
♦
Pax Signs.................ON ............... CPT
Elec Hyd Pumps...........AUTO...............CPT
Ice Protection Panel.SET.............. CPT
Windshield Heating ......AS REQ ...........CPT
Air Cond Panel.........SET.............. CPT Oxy Press & Masks..CKD/100% ... C/F
Air Conditioning/APU....SET .................CPT BEFORE TAKEOFF
Radar .......................STBY ........... C/F
Pax Announcement ......COMPLETED....CPT
Autopilot...................CKD ............. CPT
Takeoff Briefing ............COMPLETED....CPT
IRS 1 & 2 .................NAV ............. C/F
PC Power .....................OFF .................CPT
♦
Flight Instruments ....SET&X-CKD CPT
Ice Detection Test ........AS REQ ...........CPT
♦
Speed Bugs .............SET.............. CPT
Flight Director...............SET .................CPT
♦
Trims........................CKD&SET.... CPT
Brakes Temperature.....CKD .................CPT
♦
Parking Brake ..........ON ............... CPT
Flaps ............................__°SET ............CPT Flight Controls ..............CKD .................CPT
♦
RMU & FMS.............SET.............. CPT
♦
Stall Protection Sys ..CKD ............. CPT
♦
Pressurization ..........SET.............. CPT
♦
♦
AFTER START
CLEARED INTO POSITION Transponder.................TA/RA ..............CPT
Safety Pins...............ON BOARD.. F/O
Gust Lock.....................UNLOCKED.....CPT
EICAS Messages .....CKD ............. CPT
Takeoff Configuration ...CKD .................CPT
Pax Briefing..............COMPLETED. CPT
EICAS Messages .........CKD .................CPT
ON THROUGH FLIGHTS CHECKLIST Page Code
JANUARY 17, 2003
1-02-01
3 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
NORMAL CHECKLIST AFTER TAKEOFF
AFTER LANDING
Windshield Heating ...... AS REQ...........PNF Air Cond Panel............. SET .................PNF Altimeters..................... SET&X-CKD ....C/F Thrust Rating ............... CLB .................PNF Landing gear ................ UP ...................PNF Flaps............................ 0°.....................PNF Pressurization .............. CKD.................PNF APU.............................. AS REQ...........PNF --------------------Above 10000 ft-----------------
Windshield Heating ......... OFF ..............F/O
PC Power ..................... AS REQ...........PNF DESCENT Windshield Heating....... ON...................PNF Speed Bugs.................. SET .................PNF Pressurization............... CKD.................PNF Approach Briefing ......... COMPLETED....PNF --------------------Below 10000 ft----------------PC Power ..................... OFF .................PNF Pax Signs ..................... ON...................PNF Pax Announcement ...... COMPLETED ..PNF Pocket Door.................. OPN & LOCK ..PNF APPROACH Altimeters ..................... SET&X-CKD ....C/F Approach Aids .............. SET& X-CKD ...C/F
Flaps............................... 0°..................F/O APU ................................ AS REQ........F/O Transponder ................... STBY............F/O Gust Lock ....................... LOCKED ......F/O SHUTDOWN GPU/APU ....................... SET ..............CPT Shed Buses .................... SET ..............CPT Pump Power ................... SET ..............CPT Red Beacon .................... OFF ..............CPT Start/Stop Selector.......... STOP ...........CPT Elec Hyd Pumps ............. OFF ..............CPT Air Cond Panel................ SET ..............CPT Pax Signs........................ OFF ..............CPT Parking Brake ................. ON................CPT LEAVING THE AIRPLANE IRS 1 & 2 ........................ OFF ..............C/F Avionics Master 1 & 2 ..... OFF ..............CPT Emergency Lights ........... OFF ..............CPT External & Internal Lights OFF ..............CPT
BEFORE LANDING
Radar.............................. OFF ..............C/F
Landing Gear ............... DOWN.............PF Flaps ............................ ___°SET ..........PF Fuel Transfer ................ OFF .................PNF Autopilot & Yaw Damp ... OFF .................PF
GPU/APU ....................... OFF ..............CPT Pump Power ................... OFF ..............CPT Air Cond Panel................ SET ..............CPT Batteries 1 & 2 ................ OFF ..............CPT
Page Code
1-02-01
4 01
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
NORMAL PROCEDURES EXTERNAL SAFETY INSPECTION When approaching the airplane, take time to watch the area where the airplane is parked. Evaluate if there is room for the taxi-out or push back maneuver. Make sure that there will be enough clearance throughout the maneuver. Also take time to have a look at the airplane as a whole from a reasonable distance. See if the airplane looks good, level and normal. Experience shows that this "initial look" can reveal details that will otherwise go unnoticed such as fluid spots on the ground, unexpected things attached to the airplane, bent or unaligned airframe components, etc. Make sure that the airplane has the chocks and safety pins on as required. If not, advise the ground staff immediately. The External Safety Inspection must be carried out prior to the first flight of the day or whenever the crew-airplane combination changes. The external lights must be turned on for inspection with the exception of the ones that may be a nuisance to other people in the vicinity of the airplane. The lights must be checked and switched off before commencing the walk around. The first officer normally accomplishes the external safety inspection, although either or both crew members may complete it. The inspection can be done according to list below: Wheel Chocks............................................................... IN PLACE NOSE SECTION Access Doors and Panels ............................................. SECURED Static Ports.................................................................... NO OBSTRUCTION Sensors and Pitot Tubes............................................... CONDITION, NO OBSTRUCTION Windshield Wipers(If applicable) .................................. CONDITION Air Inlets ........................................................................ NO OBSTRUCTION Page
REVISION 3
1-02-05
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Radome.........................................................................SECURED Nose Gear .....................................................................CHECK Check if the nose wheel position indication mark is within the nose wheel position indication scale limits. Wheels and Tires .....................................................CONDITION Tires should not be worn past the bottom of the tire grooves. Tires .........................................................................CHECK PRESSURE Check tire pressure within the gray range (84 ± 2 psi). Gear Struts/Wheelwell/Doors...................................CONDITION, NO LEAKS Shock Absorber Extension.......................................CHECK Check minimum extension according to the table below: CG Position (%) Minimum Extension (mm)
17
20
25
28
32
35
56
51
47
51
57
62
Ground Locking Pin..................................................REMOVED Gear Uplock Hook....................................................UNLOCKED If the uplock hook is in the LOCKED position, cycle the freefall lever to reposition the uplock to the UNLOCKED position. Static Discharger ...........................................................CONDITION Landing and Taxi Lights ................................................CONDITION Hydraulic Compartment (right side)...............................NO LEAKS Oxygen Pressure Green Disc (right side)......................CHECK IN PLACE FUSELAGE Access Doors and Panels .............................................SECURED Fueling Compartment Door (right side) .........................SECURED Inspection Lights ...........................................................CONDITION Air Inlets and Outlets .....................................................NO OBSTRUCTION ∗ Fuel Tanks Draining ......................................................PERFORM Red Beacon...................................................................CONDITION Antennas .......................................................................CONDITION Ram Air Inlet..................................................................NO OBSTRUCTION Fluid Drain Holes ...........................................................NO LEAKS Page
1-02-05
Code
2 01
REVISION 5
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
∗ Emergency/Parking Brake Hydraulic Accumulator ....... DISCHARGE AND CHECK The pressure from the Emergency/Parking Brake hydraulic accumulator must be fully released at least once a day. To accomplish this task proceed as follows: − Park the airplane where there is no slope; − Put chocks at the landing gear wheels; − Release the parking brake. Make sure that the airplane will not move; − Open the access panel and hold the oil discharge valve open until the hydraulic accumulator is fully discharged; − Wait for 3 (three) minutes and, after this interval, make sure that the precharge of nitrogen shown on the pressure gage is 2000 PSI at the ambient temperature of 21.1°C (70°C). For other ambient temperatures, refer to the graph shown beside the valve; − Turn the hydraulic pump on to recharge the hydraulic accumulator; − Apply the parking brake. CAUTION: • DISCHARGING THE HYDRAULIC ACCUMULATOR WILL MAKE THE EMERGENCY/PARKING BRAKE INOPERATIVE. • PERFORM THIS PROCEDURE AIRPLANE ENERGIZED.
WITH
THE
WINGS Landing Lights............................................................... CONDITION Emergency Lights ......................................................... CONDITION Wing Leading Edge....................................................... CONDITION Access Doors and Panels ............................................. SECURED Direct Measuring Sticks ................................................ PUSHED IN Air Inlets, Outlets and Vents.......................................... NO OBSTRUCTION Vortilons and Vortex Generators................................... NUMBER AND CONDITION Navigation and Strobe Lights ........................................ CONDITION Static Dischargers ......................................................... NUMBER AND CONDITION
Page
REVISION 5
1-02-05
Code
3 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Flight Control Surfaces and Fairings .............................CONDITION Flaps must be retracted and spoilers closed. Main Gear......................................................................CHECK Wheels and Tires .....................................................CONDITION Check tire pressure within the gray range (160 ± 4 psi). Gear Struts/Wheelwells............................................CONDITION, NO LEAKS Shock Absorber Extension.......................................CHECK Check 48 mm minimum shock absorber extension. Ground Locking Pins ................................................REMOVED Brake Wear Indicators .............................................CHECK Wear indicators should be no less than flush with the housing. Gear Uplock Hook....................................................UNLOCKED If the uplock hook is in the LOCKED position, cycle the freefall lever to reposition the uplock to the UNLOCKED position. TAIL CONE SECTION Air Inlets and Outlets .....................................................NO OBSTRUCTION Antennas .......................................................................CONDITION Access Doors and Panels .............................................SECURED Pylons............................................................................CONDITION Engines..........................................................................CHECK Check engines for leaks and obstructions in the air inlets. Thrust Reverser Doors ..................................................FLUSH WITH NACELLE Horizontal Stabilizer.......................................................CONDITION Logo Lights (Optional Item) ...........................................CONDITION Flight Control Surfaces..................................................CONDITION Static Dischargers .........................................................NUMBER AND CONDITION APU ...............................................................................CONDITION Pressurization Static Ports ............................................NO OBSTRUCTION Baggage Door ...............................................................LATCHED/ LOCK PANEL CLOSED Fluid Drain Holes ...........................................................NO LEAKS
Page
1-02-05
Code
4 01
REVISION 5
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
INTERNAL SAFETY INSPECTION The Internal Safety Inspection must be carried out by the copilot prior to the first flight of the day, when the airplane is due to return to service after maintenance, or whenever the crew-airplane combination changes. The internal safety inspection should be accomplished with electrical power supplied from APU or GPU. In the event that APU or GPU are not available, batteries may be used. NOTE: When using the batteries try to be fast as possible to save them.
COCKPIT Airplane Manual & Documents...................................... .ON BOARD Check for regulations in countries intended to flight and company policy for the required on-board operational documents. Typically the company has an approved Airplane Operating Manual with required operational information that must be on board. Additionally an approved MEL as well as navigation and approach charts. The QRH must be on board. Data such as runway analyses, driftdown analyses (if applicable), enroute diversion data and any other flight analysis must also be on board. Even if the predicted enroute meteorological information does not foresee inflight icing conditions, landing analysis for both flaps 45° and flaps 22° must be carried on board. Make sure that documents which are legally required to be on board are really on board, such as: - Certificate of Airworthiness. - Copy of the Insurance Policy. - Airplane weighing document. - The Cabin Crew, except for specific cases when the passenger documents must legally be handed to the Captain, handles documents such as General Declaration and passenger documentation.
Page
JANUARY 17, 2003
1-02-09
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Cockpit Emergency Equipment .....................................CHECKED Check for the availability, status and proper location of the following equipment: -
Escape ropes; Oxygen masks; Smoke goggles; Portable Breathing Equipment (PBE); Fire extinguishers; Crash Axe; Flashlights; Life vests.
Overhead/Main and Control Pedestal Panels ...............CHECKED Verify all circuit breakers IN at the overhead panel, behind the CPT seat and behind the F/O seat. If any CB is pulled verify the reason for it and if there is any operational implication advise the other pilot. Switches and knobs on the overhead panel must be set as follows: IFE............................................................................IN PC Power .................................................................AS REQUIRED Generators ...............................................................IN GPU..........................................................................OUT APU GEN .................................................................IN BATT 1 & 2...............................................................OFF Essential Power........................................................GUARDED OUT Bus Ties & Shed Buses ...........................................AUTO Shed Buses must be set to OVRD to operate the recirculation fans and to activate the IFE control switch system when the electrical system is energized by the APU generator. AC Power .................................................................IN Back-up ....................................................................IN Avionics Master 1 & 2...............................................OUT Emergency Lights.....................................................OFF Fire Extinguishing Handle 1 .....................................IN Fuel Crossfeed.........................................................OFF Fuselage Tank Transfer Knob .................................OFF Pump Power 1 & 2 ...................................................OFF Exterior Lights ..........................................................OFF APU Fire Extinguishing ............................................GUARDED OUT Page
1-02-09
Code
2 01
JUNE 20, 2002
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
APU Master.............................................................. OFF APU Fuel Shutoff ..................................................... GUARDED OUT Ignitions.................................................................... AUTO Start/Stop Selectors ................................................. STOP Fire Extinguishing Handle 2 ..................................... IN Ailerons & Rudders Shutoff...................................... IN Engine Pump Shutoff ............................................... GUARDED OUT Electric Hydraulic Pumps ......................................... OFF Logo Light ................................................................ OFF Dome Light............................................................... AS REQUIRED Pax Signs ................................................................. OFF Ice Protection Buttons.............................................. IN Sensors.................................................................... IN Windshield Heating .................................................. OUT Ice Detection Override Knob.................................... AUTO Recirculation & Gasper ............................................ IN Packs 1 & 2.............................................................. OFF Engine & APU Bleed ................................................ OUT Windshield Wipers (If Applicable)............................ OFF Switches on the main panel must be set as follows: IRS ........................................................................... OFF MFD Reversion ........................................................ NORMAL ADC, SG Reversion ................................................. OUT ELT .......................................................................... ARMED DAU 1 & 2 ................................................................ OUT Radar ............................................................................ OFF Gear Lever .................................................................... DOWN Passenger Oxygen........................................................ AUTO Gust Lock ...................................................................... LOCKED CAUTION: NEVER MOVE CONTROL SURFACES SUCH AS FLAPS AND SPOILERS WITHOUT FIRST MAKING SURE THAT THE AREA IS CLEAR. Speed Brake ................................................................. CLOSED
Page
REVISION 7
1-02-09
Code
3 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Parking Brake................................................................ON If the airplane is to be pushed back for start and if start is to be performed with the APU, the crew may leave the parking brake released as long as the chocks are in place. NOTE: To prevent hydraulic fluid transfer between systems: To apply the parking brake first press the brake pedals to full deflection, then pull the emergency/parking brake handle. To release the parking brake, first press the brake pedals to full deflection then release the emergency/parking brake handle. Flaps Selector Lever .....................................................UP Make sure that the selected position is consistent with the position observed during external inspection. If not, be aware that, once the aircraft is energized, if the handle is lifted from the detent, the flaps will move to the commanded position. Free Fall Lever Compartment .......................................CHECKED The OVERRIDE switch must be in the NORMAL position and guarded. The FREE FALL lever must be full down. NOTE: If, during the external inspection, one of the gear uplock hooks is found mispositioned, the free fall lever may be pulled for uplock hook repositioning. This procedure must be carried out with gear pins in place.
PASSENGER CABIN Cabin Emergency Equipment........................................CHECKED Protective Breathing Equipment Indicator .....................GREEN Emergency Exit .............................................................CLOSED AND LATCHED Overwing Fueling Caps .................................................SECURED Passenger Seats and Belts ...........................................CONDITION Galley and Toilet............................................................CONDITION Baggage Compartment Access Door............................CLOSED AND LOCKED Pocket Door...................................................................OPEN AND LOCKED Curtains .........................................................................STOWED
Page
1-02-09
Code
4 01
REVISION 4
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
POWER UP APU START RECOMMENDATIONS For APU start and operation the following is recommended: Starting cycle: After First Attempt..............................................60 SECONDS OFF After Second Attempt.........................................60 SECONDS OFF After Third Attempt.............................................30 MINUTES OFF In case of an unsuccessful APU start or if BATT 1 OFF BUS followed by APU GEN OFF BUS messages are displayed on EICAS, the APU master switch must be set to OFF position and time intervals as stated above shall be observed before the next start attempt. If during start ignition is not detected at about 30% engine speed, the starter generator is de-energized. When the engine decelerates to about 5% engine speed, the starter is automatically re-energized for another start attempt (Swing Start). Swing Start is limited to one time per start attempt.
Page
REVISION 5
1-02-13
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
APU START WITH BATTERIES Internal Safety Inspection ..............................................COMPLETED Batteries 1 & 2 ...............................................................AUTO Immediately after the batteries are switched ON the aural message ”AURAL UNIT OK” can be heard. Avionics Master 1 or 2...................................................ON In order to save the batteries, only one of the avionics master should be turned on. The battery voltage can be checked on the MFD. If the battery voltage is below 24 V, report to the maintenance personnel or try to recharge the affected battery by using the APU generator for at least 30 minutes. If the battery voltage is below 19 V it must be removed from the aircraft to be recharged by maintenance. Minimum voltage for APU start attempt is 23.5 V. In cold soak conditions the battery temperature must be checked. If the battery is colder than -20ºC it must be warmed before use. Once the batteries are on, the pilot must concentrate on starting up the APU shortly, so as to save the batteries. Avoid, for example, taking time to adjust the seat or to look at documents. Plan to do these things after starting the APU and its generator is on. Release the BACKUP Battery Button momentarily and check if ISIS remains operating normally. Avionics Master 1 & 2....................................................OFF Once the battery charge is checked, Avionics Master 1 & 2 must be switched OFF before starting the APU. Pump Power ..................................................................ON Select one of the TANK 2 electric fuel pumps and switch the Pump Pwr Tank 2 to on. However, if TANK 1 has more fuel than TANK 2, use XFEED and select one of the TANK 1 pumps plus the Pump Pwr Tank 1 instead.
Page
1-02-13
Code
2 01
REVISION 5
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
∗ Fire Detection ............................................................... CHECKED Press and hold (for at least 2 seconds) the Fire Detection Test button while observing the following events: EICAS messages: Warning: APU FIRE, ENG 1 (2) FIRE, BAGG SMOKE Caution: APU FIREDET FAIL, E1 (2) FIREDET FAIL Fire Extinguisher handles illuminated. BAGG EXTG button illuminated. Aural fire warning. NOTE: - On the ground, if Fire Detection Test button is held for more than 10 seconds with the APU running, it will cause automatic APU shutdown. - If it is necessary to repeat the test, wait at least 6 seconds to press the test button. - If Fire Detection Test button is held for less than 2 seconds the BAGG EXTG button may remain illuminated. Should this happen, repeat the test. APU Master................................................................... ON/WAIT 3 SECONDS/ START/THEN ON Turn the knob to ON, wait 3 seconds, and then momentarily to START. Monitor APU EGT and RPM increasing within limits. The APU generator will come on line after RPM exceeds 95%. NOTE: Do not start the APU before 30 seconds after airplane energization to prevent disturbances in the IRS initialization. Avionics Master 1 & 2 .................................................. ON Switch the avionics master to ON. Verify APU voltage and amperage on electrical page. Amperage may be greater than 400 A (APU GEN OVLD may appears on the EICAS) at first while the APU recharge the batteries. Do not bring any additional load on line until amperage is below 400 A. Allow a few seconds for the APU GEN OVLD message to disappear before switching the avionics master to ON.
Page
JUNE 20, 2002
1-02-13
Code
3 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Push Button Lights ........................................................CHECKED Moving the switch to the TEST position will illuminate all the bars and button annunciators. The fire handles, APU fire extinguish button, BAGG EXTG button, electromechanical GUST LOCK indication lights, GPU AVAIL annunciator and digital pressurization control button will not illuminate and will not be tested. Turn the NAV lights ON, be it day time or night time. NAV lights ON show the ramp personnel that the airplane is powered up, and also make wingtips and tail end more visible to people driving vehicles in the proximity of the airplane. The LOGO light may also be switched ON during night time. Allow 3 minutes for the APU to warm up before adding pneumatic load. APU Bleed .....................................................................OPEN Air Cond Panel ..............................................................AS REQUIRED Should it be necessary to climatize the airplane: - Both Packs ON; - XBLEED to OPEN; - Set both temperature controls to AUTO. If Pack 2 control by galley or vip seats controller is desired, select the corresponding knob to ATTD. Recirculation fans and gaspers will be ON; - Shed Buses must be set to OVRD to operate the recirculation fans and to activate the IFE control switch system when the electrical system is energized by the APU generator.
Page
1-02-13
Code
4 01
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
APU START WITH GPU Internal Safety Inspection.............................................. COMPLETED Batteries 1 & 2............................................................... AUTO Immediately after the batteries are switched ON the aural message ”AURAL UNIT OK” can be heard. If the battery voltage is lower than 19 V, it must be removed to be recharged, regardless of the fact that the GPU is going to power the aircraft. If the battery is colder than -20º C it must be warmed before use. Avionics Master 1 or 2................................................... ON GPU Voltage ................................................................. CHECKED Check the ELEC page on the MFD if voltage is within 28.0 V (-2.0 V +1.0 V). Avionics Master 1 & 2 ................................................... OFF Once the GPU voltage is checked, Avionics Master bars 1 & 2 must be switched OFF. GPU .............................................................................. ON When the GPU switch is selected, the “GPU AVAIL” message on it goes off and its yellow stripe lights up. PUMP PWR .................................................................. ON Switch on one of the TANK 2 electric fuel pumps. However, if TANK 1 has more fuel than TANK 2, use XFEED and switch one of the TANK 1 pumps instead.
Page
REVISION 3
1-02-13
Code
5 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
∗ Fire Detection................................................................CHECKED Press and hold (for at least 2 seconds) the Fire Detection Test button while observing the following: EICAS messages: Warning: APU FIRE, ENG 1 (2) FIRE, BAGG SMOKE Caution: APU FIREDET FAIL, E1 (2) FIREDET FAIL Fire Extinguisher handles illuminated. BAGG EXTG button illuminated. Aural fire warning. NOTE: - On the ground, if Fire Detection Test button is held for more than 10 seconds with the APU running, it will cause automatic APU shutdown. - If it is necessary to repeat the test, wait at least 6 seconds to press the test button. - If Fire Detection Test button is held for less than 2 seconds the BAGG EXTG button may remain illuminated. Should this happen, repeat the test. APU Master ...................................................................ON/WAIT 3 SECONDS/ START/THEN ON Turn the knob to ON, wait 3 seconds, and then momentarily to START. Monitor APU EGT and RPM increasing within limits. The APU generator will come on line after RPM exceeds 95%. GPU...............................................................................OFF Crew must deselect the GPU as soon as the APU is running and stable to prevent the ground crew from disconnecting it while still selected, which causes an unwanted transient. Avionics Master 1 & 2 ...................................................ON Switch the avionics master to ON. Verify APU voltage and amperage on electrical page. Amperage may be greater than 400 A (APU GEN OVLD may appears on the EICAS) at first while the APU recharge the batteries. Do not bring any additional load on line until amperage is below 400 A. Allow a few seconds for the APU GEN OVLD message to disappear before switching the avionics master to ON.
Page
1-02-13
Code
6 01
REVISION 4
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
Push Button Lights ........................................................ CHECKED Moving the switch to the TEST position will illuminate all the bars and button annunciators. The fire handles, APU fire extinguish button, BAGG EXTG button, electromechanical GUST LOCK indication lights, GPU AVAIL annunciator and digital pressurization control button will not illuminate and will not be tested. Turn the NAV lights ON, be it daytime or nighttime. NAV lights ON show the ramp personnel that the airplane is powered up, and also make wingtips and tail end more visible to people driving vehicles in the proximity of the airplane. The LOGO light may also be switched ON during nighttime. Allow 3 minutes of APU warm up before adding pneumatic load. APU Bleed..................................................................... OPEN Air Cond Panel .............................................................. AS REQUIRED Should it be necessary to cool down the cabin: - Both Packs ON; - XBLEED to OPEN; - Set both temperature controls to AUTO. If Pack 2 control by galley or vip seats controller is desired, select the corresponding knob to ATTD. Recirculation fans and gaspers will be ON; - Shed Buses must be set to OVRD to operate the recirculation fans and to activate the IFE control switch system when the electrical system is energized by the APU generator.
Page
JANUARY 17, 2003
1-02-13
Code
7 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
GPU POWER (NO APU) When APU is unserviceable, it is recommended that an external Ground Power Unit (GPU) be used in conjunction with an external pneumatic source. Starts relying on the airplane batteries as the sole source of electrical power are possible but they put a heavy stress on them because of the amount of time required to power the airplane systems. If the batteries are not properly charged spurious messages and indications may occur as battery voltages drop below minimum acceptable levels. Internal Safety Inspection ..............................................COMPLETED Batteries 1 & 2 ..............................................................AUTO Immediately after the batteries are switched ON the aural message ”AURAL UNIT OK” can be heard. If the battery voltage is lower than 19 V, it must be removed to be recharged, regardless of the fact that the GPU is going to power the aircraft. If the battery is colder than -20º C it must be warmed before use. GPU Voltage..................................................................CHECKED Check in the ELEC page, on the MFD, if the voltage is within 28.0 V (-2.0 V +1.0 V). GPU...............................................................................ON When GPU button is selected, the “GPU AVAIL” message on it goes off and its yellow stripe lights up.
Page
1-02-13
Code
8 01
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
BEFORE START - FIRST FLIGHT To begin the cockpit preparation the EXTERNAL SAFETY INSPECTION and the INTERNAL SAFETY INSPECTION must have been completed and the airplane must be powered up.
CVR............................................................................... CHECKED Press the CVR TEST button and check the STATUS LED illuminated for about one second. Electrical Panel ............................................................. SET Turn the Batteries 1 & 2 knob to AUTO. Immediately after the batteries are switched ON the aural message ”AURAL UNIT OK” can be heard. Check if: − All four generator buttons and the APU generator button are pressed; − The ESSENTIAL POWER button is guarded and not pressed; − The BUS TIES selector is set to AUTO; − The SHED BUSES selector is set to OVRD in case of the galley ovens and recirculation fans are to be used and check also if the source of electrical power is the APU. If the source is a GPU, then set the selector to AUTO; − The AC PWR, BACKUP and AVIONICS MASTER buttons are pressed; Emergency Lights ......................................................... CHECKED & ARMED Check if the emergency lights go on and the EMERG LT NOT ARMD appears on the EICAS when the emergency lights switch is set to the ON position. Leave it in the ARM position afterwards.
Page
REVISION 3
1-02-17
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Fuel Panel & Quantity....................................................SET___lb/kg Confirm if onboard fuel quantity matches required fuel for the intended flight. Select the fuel pumps according to the alternating policy in use. If the APU is running, feed it from the tank that has more fuel. Reset the used fuel readout on the MFD. Check the Fuselage Tank Transfer System, according to the procedure as follows: Select FUS 1 on overhead fuel panel, and keep in this position for at least 10 seconds. Check MFD Fuel Page for pump indications. AFT tank must display pump A indication and FWD tank must display pump A or B indication. Alternate pump and check if the other pump (A or B) is displayed in FWD tank. Repeat the procedure for FUS 2 system. Turn Fuselage Transfer System off. Perform an outside visual check on fuel drains for any fuel leakage. Assure that each system FWD tank has 140 ± 30 kg (310 ± 70 lb) more fuel than the respective AFT tank. NOTE: - During the test the EICAS Caution FUEL XFER OVERFLOW may be presented. - The test must be performed only if there is fuel in auxiliary tanks. Power Plant Panel .........................................................SET Turn both Ignition knobs to AUTO. As a general guideline, the lower thrust rating should always be used if the airplane’s performance for the prevailing ambient conditions and the intended departure runway allows it. Proceed as follows to enter the takeoff data: - Select the T/O page on the MFD. - Press the STORE button once and verify the white mark besides T/O MODE, which means that it is prompting for the selection of takeoff mode. - Use the DEC/INC knob to select the takeoff mode. Press the STORE button one more time and the white mark will move to the REF TO TEMP line.
Page
1-02-17
Code
2 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
- Use the DEC/INC knob again to select the reference local temperature. Each movement of the knob will change the reference temperature by 1°C. Press the STORE button one more time and the white mark will move to the A-ICE mode selection line. - Use the DEC/INC knob to select ANTI-ICE ON or OFF. Press the STORE a last time and the TAKEOFF DATA entry is complete. - Also verify on the MFD T/O page that the level of lubricating oil in each engine is in the normal range. Ref. Anti-Ice Policy: the following criteria must be observed when setting ref. Anti-ice to ON or to OFF: Whenever temperature on ground is at or below 10°C and there is visible moisture in the air, it must be assumed that icing conditions are present. Under these circumstances the use of engine anti-ice (anti-ice override switch to ENG) is mandatory. The EMB 135 BJ anti-ice system is such that if any ice is detected at a speed above 25 kt the whole ice protection system goes ON. If chances are that ice will be encountered during takeoff then REF A/ICE must be set to ON so that the FADEC allows a ITT margin for the anti-ice ON condition. If REF A/ICE is set to ON then the takeoff performance-limited weight must be based on the anti-ice ON condition. ∗ Electric Hydraulic Pumps.............................................. CHECKED & OFF The electric hydraulic pumps should never be switched ON if the battery is the sole source of electrical power. If the batteries are the sole source of electrical power, wait until the APU or a GPU is available before switching ON the electric hydraulic pumps. Select the MFD HYD page and switch both electric hydraulic pumps to AUTO. Verify that the indicated pressures are within 2900 ± 200 psi. Check also the hydraulic fluid level of systems 1 and 2 are within normal range. After both pumps have been checked, turn them OFF. Pax Signs ...................................................................... ON Switch the FSTN BELTS and NO SMKG signs ON.
Page
REVISION 7
1-02-17
Code
3 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Ice Protection Panel ......................................................SET Make sure that the ENG, WING and STAB buttons are pressed. The SENSORS buttons must also be pressed. The WINDSHIELD buttons need to be pressed only if windshield defogging or deicing is required. The ICE DETECTION OVERRIDE knob must be in AUTO. Air Conditioning Panel ...................................................SET If air conditioning is desired and if the APU has been running for more than 3 minutes open the CROSSBLEED and select both PACKS to ON. The recirculation fans (RECIRC button) must be ON. If PACK 2 only is capable of keeping a comfortable cabin temperature, PACK 1 can be left OFF until after both engines are running (after going through the After Start Checklist) in order to reduce the external noise in the vicinity of the main passenger door for better passenger comfort. Oxygen Press & Masks .................................................CHECKED /100% Both pilots must check their respective masks for supply of oxygen and for microphone functionality. The masks must be set to 100% oxygen. The MFD ECS page must be checked for crew/passenger available oxygen pressure. The minimum oxygen pressure values for dispatch are: CREW OXYGEN Pilot and Copilot Pilot, Copilot and Observer
Min Press (at 21°C) 1100 psi 1500 psi
PAX OXYGEN Airplane equipped with one cylinder Airplane equipped with two cylinders (optional)
Min Press (at 21°C) 1730 psi 1250 psi
Carry out the test as follows: - Select the MASK position on the Audio Panel; - Set the mask to 100%; - Select SPKR on the Audio Panel and set the volume to midrange; Page
1-02-17
Code
4 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
- Select HOT MIC on the control wheel communication switch; - Actuate the test button on the mask stowage location. Check that the blinker changes color; (*) - The OXY ON flag must appear on the stowage box; (*) - For EROS masks: While maintaining the RESET TEST lever (TEST/SHUTOFF sliding control) depressed, check that the blinker changes color momentarily, and then depress the PRESS-TO-TEST regulator for 1 second; or For Puritan Bennett or B/E Aerospace masks: Set the regulator’s control knob to EMERGENCY and momentarily actuate the test button on the mask stowage location; - Check that the blinker changes color; - The OXY ON flag must appear on the box; (*) - The sound of oxygen flowing must be heard momentarily on the speaker, thereby assuring the microphone electrical integrity; - Set the mask to 100%; (*) - After finishing the test, select the BOOM position on the Audio Panel. (*)
Applicable only to Puritan Bennett or B/E Aerospace masks.
If there is an observer on the jump seat, check the observer oxygen mask as follows: - Select the MASK position on the observer Audio Panel; - Set the mask to 100%; - Select SPKR on the Audio Panel and set the volume to midrange; - Select HOT MIC on the control wheel communication switch; - For EROS masks: Depress the PRESS-TO-TEST regulator for 1 second; or For Puritan Bennett or B/E Aerospace masks: Turn the regulator knob to the EMERGENCY position momentarily and then turn back the knob to 100% position; - The sound of oxygen flowing must be heard momentarily on the speaker, thereby assuring the microphone electrical integrity; - After finishing the test, select the BOOM position on the Audio Panel.
Page
JUNE 20, 2002
1-02-17
Code
5 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Radar.............................................................................STANDBY Both pilots must select RADAR to SBY on their panels. If there is just one radar panel, then the CPT must do it. Autopilot.........................................................................CHECKED The CPT assigned for the flight must carry out the AUTOPILOT check as follows: - Release the GUST LOCK, bring the control column to its midcourse position between full up and full down; - Select the AP to his side and engage it, verifying the "AP" and "YD" indications on the PFD; - Press the AP/PUSHER/TRIM button on the control wheel and verify the disengagement of the AP and the disappearance of the respective indications on the PFD; - Set the gust lock again. IRS.................................................................................NAV The initial alignment must be performed by setting the MSU switch to NAV. Make sure that the airplane is not moved or bumped during the alignment process. Alignment time varies with latitude. It is necessary to enter the airplane present position through the FMS CDU to complete the initial alignment. NOTE: The IRS knob should never be moved to ATT on ground. If for any reason it is set to ATT, restart the alignment process from scratch by setting the knob to OFF then back to NAV. Flight Instruments..........................................................SET & X-CHECKED Both pilots must select the following information on their Display Control panel: - PFD format (full compass format or arc format); - PFD source (NAV or FMS); - Bearing pointer source (VOR, ADF or FMS); - Select DH on the PFD as appropriate. In addition, they must reset the chronometer and set, if necessary, the current GMT in the clock. On the Reversionary Panels, Both pilots must check that their respective MFD Selector Knobs are set to NORM. They also must set their respective altimeters to the local QNH and select an initial course as per the expected departure procedure. The CPT must also set the HDG bug according to the intended runway heading. Page
1-02-17
Code
6 01
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
After the integrated standby instruments system(ISIS) initialization, compare its indication with the main attitude indicators and set the local QNH. Then compare its readout with the main altitude tapes. Check no ALT or SPD flags displayed. NOTE: The airplane must not be moved during the first 90 seconds after power-up, while the ISIS is undergoing alignment. Moving the airplane during this period can cause in-flight attitude indication errors, that are not noticeable on ground. Once these actions are complete, the pilots must carry out an instrument crosscheck as follows: - Both AIRSPEED TAPES not showing speed; - EADI’s level and flag-free; - Both ALTIMETERS with their QNH set, and reading consistent with altitudes. If the crew already has the predeparture clearance, they can select the initial assigned altitude on the ASEL; - Both VERTICAL SPEED INDICATORS showing zero; - EHSI’s with the courses selected according to the intended departure procedure, showing the same magnetic heading, flag-free and with the heading bug set to the intended runway heading. NOTE: In case of heading split, check if there are ferrous structures or other magnetic interference sources close to the airplane, and/or move the airplane to a different location. Speed Bugs................................................................... SET Set V1, VR, and V2 on the MFD as per the runway analysis. Set the VAP bug to Vref 45º plus 5 knots (or plus wind correction, whichever is greater) so, if an air return is to be carried out, the final approach speed is already set. The wind correction added to the VAP is limited to 15 Kt. The VFS (Final Segment Speed) is shown at the upper left corner on the PFD and is set through the SPD button.
Page
JANUARY 17, 2003
1-02-17
Code
7 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Trims .............................................................................CHECKED Verify that the aileron, rudder, main and backup pitch trims are operating properly both ways up to the 3 seconds automatic stop; leave the aileron and rudder trims to the neutral and set the pitch trim to the units required for takeoff according to the CG position. PITCH 8 TRIM UNITS LESS CG THAN POSITION 25 (%)
7
6
5
4
27
30
32
35
Parking Brake................................................................ON Check that the PARKING BRAKE is ON and the corresponding ON light is lighted. If the EMRG BRK LO PRESS shows on the EICAS then switch on the electric hydraulic pump 2 momentarily to repressurize the accumulator. RMU & FMS ..................................................................SET On the RMU, the PF assigned for the flight must set the COMM and NAV frequencies as appropriate for the expected SID or departure procedure. The use of the VHF COMM sets must follow the arrangement described below: COMM 1: ATC COMM 2: Company frequency, ATIS, VOLMET, etc. COMM 3 (if available): Distress (121.5) and air-to-air broadcast. Verify if the ATC/TCAS window is in SBY. Select the ABOVE function. Test the TCAS by placing the yellow cursor box over the code. Press the RMU test button for 5 to 7 seconds until the test OK message on the RMU and “TCAS TEST, PASSED” aural annunciation is heard. If desired enter the flight number or CALL SIGN on the appropriated window into the RMU. Verify that BACK-UP TUNING is set to NORMAL and is copying RMU2. In addition, The PF must enter all the data into the FMS, including PAX number and cargo data. So the FMS initialization including the check if the DATABANK is still valid, check for correct date and Page
1-02-17
Code
8 01
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
time and check for possible messages related to the status of the FMS. Also if the flight plan needs to be entered, it can be done now. It is recommended to use the FMS in dual mode. In case of single operation the flight plan must be copied by the PF from his FMS to the other so as to ensure consistency among flight plans. Stall Protection System ................................................. CHECKED The IRS should be aligned. CUTOUT 1 and 2 buttons must be guarded and not illuminated and QUICK DISCONNECT BUTTON must be released. Carry out the Stall Protection System test as follows: - Pull the control column all the way back and momentarily press the SPS TEST button (the TEST button must not be kept pressed beyond the shaker actuation). Both the stick shaker and the stick pusher will actuate and an aural warning will be heard. - Lightly counteract the control column tendency to move forward. - The test takes about 5 seconds and is valid if the amber light on the TEST button extinguishes. Pressurization ............................................................... SET Set the system to the destination airport elevation and verify that the DUMP and AUTOMAN switches are guarded and were not pushed (if they have been pushed the white mark on the buttons will be lit). The manual controller knob must be set to the green mark (DN position) to enable automatic pressurization control. If flying to an airport above 8000 ft: Pressurization ..........................................................8000 ft NOTE: In airports with pressure altitude between 8000 ft and 8500 ft, the cabin altitude displayed in EICAS will be amber. Manual Controller.......................................................... FULL DOWN Safety Pins .................................................................... ON BOARD Verify that the safety pins are on board, behind the CPT seat. EICAS Messages .......................................................... CHECKED The CPT should check if there are any critical message on the EICAS which may effect the engine starting.
Page
REVISION 5
1-02-17
Code
9 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Passenger Briefing ........................................................COMPLETED The passenger briefing must be carried out by the CREW and must cover the items on Passenger Briefing Card, as follows: - Fasten seat belts and all shoulder harnesses; - Seats back must be in upright position; - Seats must be positioned outboard (against the sidewall); - Headrest must be in the up position for aft facing seat and in the down position for the forward facing seats; - Legrest must be in down position; - Divan must be in the seating position; - All tables and monitors must be stowed; - Extinguish all smoking materials; - Passenger must inform the crew before entering in the baggage compartment. - The baggage compartment door must be kept opened while there is anyone inside.
Page
1-02-17
Code
10 01
REVISION 3
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
BEFORE START - THROUGH FLIGHT
Fuel Panel & Quantity ................................................... CHECKED __lb/kg The CPT must alternate the fuel pumps, reset the used fuel reading and check the fuel on board is not less than the required fuel for the next flight. The copilot must also reset the used fuel reading on his MFD. Power Plant Panel......................................................... SET As a general guideline, the lower thrust rating should always be used if the airplane’s performance for the prevailing ambient conditions and the intended departure runway allows it. Proceed as follows to enter the takeoff data: - Select the T/O page on the MFD. - Press the STORE button once and verify the white mark besides T/O MODE, which means that it is prompting for the selection of takeoff mode. - Use the DEC/INC knob to select the takeoff mode. Press the STORE button one more time and the white mark will move to the REF TO TEMP line. - Use the DEC/INC knob again to select the reference local temperature. Each movement of the knob will change the reference temperature by 1°C. Press the STORE button one more time and the white mark will move to the A-ICE mode selection line. - Use the DEC/INC knob to select ANTI-ICE ON or OFF. Press the STORE a last time and the TAKEOFF DATA entry is complete. - Also verify on the MFD T/O page that the level of lubricating oil in each engine is in the normal range. Pax Signs ...................................................................... ON Once all disembarking passengers have left the airplane, the FSTN BELTS sign must be switched ON again. The NO SMKG sign should be already ON. If not, it must be switched ON at this time.
Page
JANUARY 17, 2003
1-02-21
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Flight Instruments..........................................................X-CHECKED Both pilots must set their respective altimeters, including the ISIS, to the local QNH or QFE. They must also select an initial course as per the expected departure procedure. The CPT must also set the HDG bug according to the intended runway heading. Once these actions are completed, the pilots must carry out an instrument crosscheck as follows: - Both AIRSPEED TAPES not showing speed; - EADI’s level and flag-free; - Both ALTIMETERS with their QNH set, and reading consistent altitudes; - Both VERTICAL SPEED INDICATORS showing zero; - EHSI’s with the courses selected according to the intended departure procedure, showing the same magnetic heading, flag-free and with the heading bug set to the intended runway heading; - If the crew already has obtained predeparture clearance, they can select the initial assigned altitude on the ASEL; if the clearance is not available yet, the requested altitude minus 100 ft or yet the most probable altitude can be set; - The 100 ft decrement is a reminder that the selected altitude has not been authorized by ATC yet. Speed Bugs ...................................................................SET Set V1, VR, and V2 on the MFD as per the runway analysis. Set the VAP bug to Vref 45º plus 5 knots (or plus wind correction, whichever is greater) so, if an air return is to be carried out, the final approach speed is already set. The wind correction added to the VAP is limited to 15 Kt. The VFS (Final Segment Speed) is shown at the upper left corner on the PFD and is set through the SPD button.
Page
1-02-21
Code
2 01
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
Trims ............................................................................. SET Set the pitch trim to the units required for takeoff according to the CG position. PITCH 8 TRIM UNITS LESS CG THAN POSITION 25 (%)
7
6
5
4
27
30
32
35
Parking Brake ............................................................... ON The CPT must verify on the MFD that the brake temperature is within the green range. If so, then he can apply the parking brake; otherwise, the parking brake must be left released until the brakes cool down as appropriate. If the brake temperature is in the yellow range, the next flight cannot commence since the accelerate-stop performance would fall short of the published performance. RMU & FMS .................................................................. SET The PF assigned for the flight must select the applicable COMM and NAV frequencies for the intended departure and select ABOVE and a proper range on the TCAS. Also, the PF must enter all the data into the FMS, including PAX number and cargo data. So the FMS initialization including the check if the DATABANK is still valid, check for correct date and time and check for possible messages related to the status of the FMS. Also if the flight plan needs to be entered, it can be done now. It is recommended to use the FMS in dual mode. In case of single operation the flight plan must be copied by the PF from his FMS to the other so as to ensure consistency among flight plans. Stall Protection System ................................................. CHECKED
Carry out the Stall Protection System test as follows: - Pull the control column all the way back and momentarily press the SPS TEST button (the TEST button must not be kept pressed beyond the shaker actuation). Both the stick shaker and the stick pusher will actuate and an aural warning will be heard.
Page
REVISION 3
1-02-21
Code
3 01
NORMAL PROCEDURES
-
AIRPLANE OPERATIONS MANUAL
Lightly counteract the control column tendency to move forward. The test takes about 5 seconds and is valid if the amber light on the TEST button extinguishes.
Pressurization................................................................SET Select the elevation of the destination airport. If flying to an airport above 8000 ft: Pressurization .....................................................8000 FT NOTE: In airports with pressure altitude between 8000 and 8500 ft, the cabin altitude display in EICAS will be amber. EICAS Messages ..........................................................CHECKED The CPT should check if there are any critical message on the EICAS which may effect the engine starting.
Page
Code
4 01 1-02-21 (Pages 5 and 6 deleted)
REVISION 6
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
CLEARED TO START Make sure that APU BLEED is ON and that CROSS BLEED is OPEN or AUTO. Also make sure both ENGINE BLEEDS are CLOSED. Engine start cannot be performed with an open baggage compartment. Danger areas must be clear during start. It is recommended that audio communication with the ground crew is used instead of signaling, if this service is available. Windows ....................................................................... CLOSED
Red Beacon .................................................................. ON The red beacon must be ON whenever the airplane is moved as part of a flight operation, or when an engine is being operated. Pump Power.................................................................. ON Observe the alternation of the fuel pumps for each flight. Make sure both tanks have pumps ON. NOTE: Make sure that both thrust levers are in idle before start engines.
Page
REVISION 5
1-02-25
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
ENGINE START Whenever possible, initiate the engine starting procedure with the right engine. The START/RUN/STOP switch activates the starter air-control valve. Rotating the START/RUN/STOP switch to START position signals the initiate start sequence to the FADEC. When released, the START/RUN/STOP switch returns to central RUN position. Ignition is activated when N2 is at approximately 14% N2. Fuel is injected when N2 is at approximately 31.5% (28.5% for airplanes equipped with FADEC B7.4 and on) or 12 seconds after ignition is activated. With ignition in AUTO, only the FADEC in control activates the ignition system. FADEC in control is alternated every subsequent ground start. Only one ignition channel is activated on grounds starts, which are alternated every subsequent start. If ignition is set to OFF, FADEC neither activates ignition nor actuates the fuel valve to open, thus allowing dry motoring. However, a dry motoring procedure must not be performed if one of the FADECs is declared incapable. There is no automatic shutdown by the FADEC for an overtemperature on start. For this reason, the pilot must keep his hands on START/RUN/STOP switch. The start cycle ends at approximately 57% N2, which can be observed when IGNITION A or B annunciation on EICAS disappears. After starting is completed, engine stabilizes at about 64% N2 and 24% N1. CAUTION: ABORT THE ENGINE START BY SELECTING THE START/STOP SELECTOR TO STOP IF AN ABNORMAL ENGINE START IS DETECTED. NOTE: - Starts are faster if ITT is below 210°C. - Light-ups at 28% N2 will be achieved with systems meeting minimum performance requirements. If light-ups are occurring below 28%, the airplane should be scheduled for maintenance to avoid disruptions to passenger service. If any start limit is exceeded prior to aborting a start, do not attempt further starts and report to the maintenance personnel. If a hung start, or no start occurs, do the Dry Motor procedure before attempting another start. Page
1-02-25
Code
2 01
REVISION 6
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
REVISION 6
1-02-25
Code
3 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
ENGINE START PROCEDURE One Fuel Pump .............................................................ON NOTE: Alternate fuel pumps on each engine starting. Crossfeed ......................................................................AS REQUIRED Start Selector.................................................................START and then RUN Turn the start selector to START momentarily and then to RUN, and start the stopwatch. Increase in N2 ...............................................................CHECKED Verify increase in N2 RPM within 5 seconds of start selection. Make sure N2 accelerates normally. IGN A (B) annunciation .................................................CHECKED Observe the annunciation IGN A (B) at about 14% N2. ITT .................................................................................CHECKED Observe ITT indications raise at about 31.5% N2. IGN A (B) annunciation .................................................CHECKED OFF Verify the annunciation IGN A (B) go OFF at about 57% N2. Engine parameters ........................................................CHECKED Verify that the engine stabilizes at about 64% N2 and 24% N1. Verifies ITT and oil pressure for normal indications. Repeat the procedure for the other engine.
Page
1-02-25
Code
4 01
REVISION 6
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
PUSH-BACK OPERATION NOTE: For push-back and start make sure that: - No person or object in the danger areas; - Doors and panels closed; - Push-back path clear; - Steering disengage. If the Push-back procedure is required, the ground equipment must be cleared and the ramp communication established. The STEERING must be disengaged by the CPT, by pressing the trigger on the yoke, or by the ground personnel, by putting the external Steering Disengagement Switch in the disengaged position, prior to the pushback. After that, the CPT must verify that the STEERING INOP message is shown on the EICAS. If the disengagement is done by the trigger on the yoke, as an extra safety measure, the CPT's left hand must be kept away from the STEERING HANDWHEEL during push-back to prevent any unwanted steering command in case the steering is mistakenly left active (trigger not set to deactivation). NOTE: Steering handle actuation with nose wheels beyond their operational limits may cause damage to the nose wheel steering system. After Push-back, the CPT must ask the ramp personnel for a positive confirmation that the area is clear and then the STEERING must be engaged by the CPT through STEERING HANDWHEEL or by the ground personnel by putting the external Steering Disengagement Switch in the engaged position.
Page
JANUARY 17, 2003
1-02-27
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-02-27
Code
2 01
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
AFTER START Electrical Panel ............................................................. SET If the SHED BUSES are set to OVRD, switch them to AUTO. FADEC .......................................................................... RESET/ALTN This swapping of the FADECs is important because it ensures that both the controlling and the standby FADECs are properly set. Elec. Hydraulic Pumps .................................................. AUTO The copilot must set the electric hydraulic pumps to AUTO after start. Windshield Heating ....................................................... AS REQUIRED Turn on windshield heating if defogging is required or if in icing conditions. Air Conditioning/APU .................................................... SET If takeoff is to be performed with T/O mode (for AE3007A1P engines) or T/O and E T/O (for AE3007A1E engines), the copilot should select both air conditioning packs to ON (if not yet so). The CROSSBLEED switch should be set to OPEN and the engine BLEED buttons shall remain CLOSED. NOTE: In icing conditions the engine BLEEDs must be OPEN and CROSSBLEED set to AUTO. If takeoff is to be performed with ALT T/O-1, the APU bleed should be deselected and engine BLEEDs should be used during takeoff. In this case, both BLEED buttons must be set to OPEN and set the CROSSBLEED to AUTO. Due to extend the APU´s life, it is not recommended a cool period time when shutting the APU down. APU should be shut down while loaded, that is, with APU BLEED and APU GEN ON, or immediately after the load is removed. NOTE: - The steering handle engagement actuation with the Nose wheels beyond their operational limits may cause damage to the Nose Wheel Steering System. - Do not start taxiing before receiving confirmation from the ground crew that the airplane is free to taxi. Then acknowledge that and switch OFF the cockpit dome lights. - It is recommended that the taxi light be ON during taxi even during daytime. Page
REVISION 7
1-02-29
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-02-29
Code
2 01
REVISION 2
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
BEFORE TAKEOFF The reading of these procedures is normally called for by the CPT when the preflight clearance is already available, the briefing is already complete and if there is cabin attendant when the cabin has been already reported for departure. These actions must be carried out during taxi when clear of any congested area. The flight controls must be checked one more time close to the holding point if after a prolonged taxi under cold soak conditions or in any weather that may possibly cause flight control problems due to freezing or due to accumulation of snow or slush. Leave the gust lock LOCKED for the beginning of the taxi. The available thrust with gust lock LOCKED is normally enough to start the taxi. The taxi light must be ON whenever the airplane is taxiing. As a general guideline the taxi light switch can be associated with the Emergency/Parking Brake handle: whenever the parking brake is released the taxi light must be turned ON and vice versa. The CPT must ask the F/O to smoothly brake the airplane during taxi to verify the availability of braking at the right station. Avoid pressing the brake pedals continuously if the airplane tends to accelerate excessively. Alternate between brakes released and brakes applied instead. This technique helps keeping the brakes cool and is particularly important on hot days. NOTE: - Ensure a “cold” engine operates at least 4 minutes before takeoff power is applied. An engine is considered “cold” if it has not been run in the previous 90 minutes. - Ensure a “warm” engine operates at least 2 minutes before takeoff power is applied. An engine is considered “warm” if is has been run in the previous 90 minutes. - To increase N2 above 83% the engine oil temperature must be at 40°C minimum.
Page
JANUARY 17, 2003
1-02-33
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Passenger Announcement ............................................COMPLETED This announcement is performed by the CREW in order to inform the passengers that the cabin must be in takeoff configuration according to Pax Briefing. Takeoff Briefing .............................................................COMPLETED It is recommended that the briefing be performed before engine start if there is time for that and if there is enough information about the cleared departure procedure. If briefing is performed before engine start and there are clearance amendments afterwards or if there are any new facts that may cause significant changes in the departure procedure, the briefing must be amended. NOTE: It is highly recommended that the briefing be performed with the active participation of both pilots. Techniques such as reading back or posing questions to each other enhance this participation. Briefings consisting of mechanical repetition of a memorized speech without having the mind set on the subject are useless. PC Power System .........................................................OFF The PC Power System must be turned off until the airplane reaches 10000 ft. Ice Detection Test .........................................................AS REQUIRED The ice detection test must be carried out once a day (not necessarily at the first flight of the day) when icing conditions are forecast. The test may be carried out completely on the ground, or in 2 separate phases (first phase on the ground and second phase in flight), depending on weather conditions and crew discretion. For ice protection test information, refer to AOM Supplementary Procedures, Environmental, section 1-02-79. Flight Director ................................................................SET The PF assigned for the flight verifies that the AUTOPILOT is selected to his side then presses the FD button and selects GO AROUND by pressing the respective button at the thrust lever head. He then checks that the flight director bar on T/O mode became visible on the PFD. If a SID is to be followed using the FMS, select FMS on PFD.
Page
1-02-33
Code
2 01
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
Brakes Temperature ..................................................... CHECKED Verify on the MFD HYD page that the brakes temperature are within the green range. Takeoff cannot be attempted with brake temperatures outside the green range. Flaps ............................................................................. ___° SET The copilot moves the flap to the setting consistent with the intended takeoff configuration and performance. The flap position must be indicated on the EICAS. The flap must be checked for deflection consistent with the takeoff performance being considered. Flight Controls ............................................................... CHECKED The copilot releases the gust lock and checks AILERON and ELEVATOR free travel. Once this check is complete, the copilot must once again apply the gust lock. Then, with the airplane taxiing on a straight line or standing still, the CPT checks the RUDDER by pressing the steering disengage button on the control wheel and moving the pedals from full right to full left, and pressing the steering handle to reconnect the steering. NOTE: Allow time for engines warm up as per the recommended engine operating procedures before departure. If the engines are cold (haven´t run for the previous 90 minutes) a 4 minute warm up time is required. If the engines are warm, then a 2 minute warm up period is sufficient. To increase N2 to above 83% the engine oil temperature must be at least 40°C.
Page
JANUARY 17, 2003
1-02-33
Code
3 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-02-33
Code
4 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
CLEARED INTO POSITION External Lights must be turned on by the CPT prior to entering the runway: LDG 1, NOSE, LDG 2, TAXI (if not ON yet) and STROBE. It is advisable to have strobe lights ON whenever entering or crossing an active runway. Transponder.................................................................. TA/RA The copilot should verify that the TCAS is set to ABOVE and that a proper range has been selected. He must also check that the transponder code is the correct one and is set to TA/RA. Gust Lock ...................................................................... UNLOCKED The elevator movement must be checked after the gust lock lever is in the unlocked position. For airplanes equipped with electromechanical gust lock system the elevator movement must be checked at least 10 seconds after positioning the Gust Lock Lever to the unlocked position by moving the control column from the full up stop to the full down stop and back to the full up stop position. Takeoff Configuration.................................................... CHECKED The copilot must press the takeoff configuration test button once runway line up is authorized. The “TAKEOFF OK” aural message should be heard. If any other announcement is heard, the airplane is out of the normal configuration, and must be properly configured prior to takeoff. EICAS Messages .......................................................... CHECKED The CPT should make sure that there are no CAUTION or WARNING messages on the EICAS. If there is any ADVISORY message, evaluate the associated condition and its effects on the takeoff.
Page
JANUARY 17, 2003
1-02-37
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-02-37
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
TAKEOFF AND AFTER TAKEOFF TECHNIQUE When copilot is the PF and it is a STATIC TAKEOFF, the CPT lines up the airplane on the runway, applies brakes and calls out “YOUR CONTROLS“; the copilot responds by applying the brakes too and calling out “MY CONTROLS“. When copilot is the PF and it is a ROLLING TAKEOFF, the CPT lines up the airplane on the runway and calls out “YOUR CONTROLS“; the copilot responds by calling out “MY CONTROLS“ without braking the airplane. The PF moves the throttles to the THRUST SET detent with care not to pass it and calls out: “CHECK THRUST“. The PNF verifies that the N1 reached is the target N1 and that the engine parameters are normal. If all is normal, he responds by calling out “THRUST CHECKED“. The PNF must also verify, when appropriate, that ATTCS is armed and calling out “ATTCS ARMED“. As soon as the speed tape starts indicating speed the PNF calls out “SPEED ALIVE“; as the airplane accelerates past 80 KIAS the PNF calls out “EIGHTY KNOTS“ and the PF verifies that his speed tape is consistent calling out “CHECKED“. If the PF is the copilot, as the thrust levers reach the Thrust Set Detent, the PF moves his left hand from the levers and holds the control wheel with his two hands. The CPT on his turn moves his right hand to the thrust levers so as to be ready if an RTO becomes necessary. At V1 the CPT moves his right hand away from the thrust levers. The copilot must immediately report any abnormality that can jeopardize the safety of the flight in a loud and clear voice. If the CPT decides to abort the takeoff he must call out “ABORT“ in a loud and clear voice also. As the airplane passes V1 the PNF calls out “VEE ONE“. As the airplane passes VR the PNF calls out “ROTATE“.
Page
NOVEMBER 30, 2001
1-02-41
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Once a positive rate of climb is attained the PNF calls out: “POSITIVE RATE” and the PF verifies positive rate and calls out “GEAR UP”. The PNF commands gear up and wait until the three gear legs indicate up and locked, then calls out “GEAR IS UP”. Do not apply brakes after becoming airborne. The main wheels will stop automatically. The PF shall maintain the pitch as indicated by the Flight Director or 15° if the takeoff is being performed on raw data. Once the acceleration altitude is reached the PNF should call out “ACCELERATION”; after checking airspeed consistent with the flap maneuver speed, the PF asks for “CLIMB SEQUENCE”, which will lead the PNF to crosscheck the speed, retract flaps to 0°, set the CLB mode on the Thrust Rating panel and select speed 210 Kt or FLC on the FGS according to the SID. The standard FD mode for takeoff should be T/O with the HDG BUG set to either the runway heading or an ATC/SID request after takeoff heading. Any changes on this heading after airborne should be requested by the PF as “SET HEADING. . . . ”.
Once the autopilot is engaged the FD mode selections are done by the PF. Upon passing the transition altitude the PNF calls out “TRANSITION ALTITUDE“ and the PF responds “STANDARD AND AFTER TAKEOFF“. Both pilots press the STD buttons on their PFD's. The PNF verifies that both altimeters are set to QNE with consistent indications and calls out “CROSS CHECKED“. In case of operation other than ICAO, an altitude reference should be established for the check list call instead of the transition altitude. Normally all the actions of the After Takeoff Checklist are to be done before the check list is called for by the PF. The After Takeoff Check list should be read by the PNF and responded by himself. If he is interrupted by a call from the ATC he should halt the reading and when he restarts it he must be sure of where he stopped. If not, the Check List must be read from start again. Upon completing the After Takeoff Check List he must call out “AFTER TAKEOFF CHECK LIST COMPLETED TO THE LINE“.
Page
Code
2 01 1-02-41 (Pages 03 to 04 deleted)
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
AFTER TAKEOFF NOTE: Keep the airplane trimmed to avoid excessive loads on the Horizontal Stabilizer Actuator (HSA). The airplane should be trimmed before 160 KIAS. Failure to accomplish the above procedure may lead to an inoperative trim condition not associated with any EICAS message. Windshield Heating ....................................................... AS REQUIRED Turn on windshield heating if entering icing conditions or if fog begins to form on windshield. Air Conditioning Panel................................................... SET Once CLB thrust is set the PNF should set the air conditioning as follows: - If the takeoff was performed on APU BLEED then both engine BLEEDS must be selected to OPEN, the CROSS BLEED must be set to AUTO and the APU bleed must be CLOSED. - If the takeoff was performed on ENGINE BLEED and T/O, depending on the temperature, both PACKS must be reset, preferably one at a time, one shortly after the other for the sake of passenger comfort. Altimeters ...................................................................... SET & XCHECKED Upon passing the transition altitude, the altimeters are set to QNE by the respective pilots if it is an operation in ICAO airspace. Thrust Rating................................................................. CLIMB The PNF selects CLB mode on the THRUST RATING panel and confirms on the EICAS the CLB indication.
Page
JANUARY 17, 2003
1-02-45
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Landing Gear.................................................................UP The PNF commands gear up on request by the PF, after confirming that the rate of climb is positive. The PNF must confirm the three white UP indications on the EICAS. Flaps..............................................................................0° The PNF commands flaps up as requested by the PF and according to the FLAP RETRACTION SPEED below: o
Flaps 9 Takeoff − Select flaps 0° at V2 + 15 KIAS or higher. Pressurization................................................................CHECKED Once the air conditioning system is set the PNF must verify that the pressurization is functioning properly. He must verify the cabin altitude, the differential pressure and the cabin rate of climb on the EICAS. APU ...............................................................................SET Shut the APU down in case this has not yet been done. If the expected flight time to destination is less than 30 minutes it is recommended that the APU be left running throughout the flight because the wear caused by the start is more significant than the wear caused by 30 minutes of continuous operation. Shut down the APU IMMEDIATELY after the engine bleed valves are open, that is, without any cool down period. This practice extends APU life. Upon completing the After Takeoff Check List, the PNF must call out “AFTER TAKEOFF CHECK LIST COMPLETED TO THE LINE”. ABOVE 10000 FT Upon passing 10000 ft the PNF switches the external lights OFF except strobe and red beacon. The logo light should be switched OFF as well as the FSTN BELTS sign, if conditions allow.
PC Power System .........................................................AS REQUIRED If PC Power supply is desired press the PC Power button on IFE overhead panel to turn on the system for passengers use. Once the check list is finished the PNF must call out “AFTER TAKEOFF COMPLETED”.
Page
Code
2 01 1-02-45 (Pages 3 and 4 deleted)
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
CLIMB TECHNIQUE The climb to cruise altitude should be preferably be done by using the AP FLC mode. However, if the flight is short and the cruise altitude is low (25000 ft or less), or if the aircraft is heavy (weight above 20000 kg or 44000 lb), proceed as follows: Climb up to 10000 ft on the FLC mode; then select 260 KIAS until M=0.60 when the SPD selector knob must be pressed so that the autopilot maintains constant Mach number until the cruise level is reached. The cabin differential pressure may reach its maximum on lengthy climbs to FL270 or higher, and this may result in high cabin rates with the consequent passenger discomfort. To avoid this, the following technique can be used: When the cabin differential pressure reaches 8.1 psi on the EICAS, select the autopilot VS mode and use a rate of climb of 1500 ft or less until reaching cruise level. If during a climb the Air Traffic Control stops the climb momentarily, maintain a speed of 240 KIAS maximum if at FL 100 or lower and 300 KIAS if above. To restart the climb reselect the new target altitude with the ASEL button and use the VS mode with a rate of 2000 to 3000 ft/min until the FLC speed is reached (240 KIAS below FL 100, 290 KIAS or Mach number 0.65 above); then select FLC. During climbs through moderate to heavy turbulence where the SPD or FLC modes are ON, changing to the VS mode may prevent the aircraft from chasing the speed, which causes wide variations in rate of climb. CAUTION: THE USE OF THE VS MODE CALLS FOR EXTRA ATTENTION REGARDING THE SPEED OF THE AIRCRAFT, SINCE AS THE AIRCRAFT CLIMBS ON A CONSTANT RATE OF CLIMB THE AIRSPEED TENDS TO DECREASE. Once the aircraft levels at the cruise level, the PNF must wait until the aircraft reaches Mach 0.70 (or 300 KIAS at lower levels) to select CRZ THRUST RATING.
Page
NOVEMBER 30, 2001
1-02-47
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-02-47
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
FUEL TRANSFER TECHNIQUE Fuel transfer starts automatically when the fuel quantity in at least one wing tank achieves the starting level – 1900 kg (4189 lb) and the FUS TK XFER knob is set to either FUS 1 or FUS 2. If the FUS TK XFER knob is set to OFF and fuel level has reached 1850 kg (4079 lb) in at least one wing tank, the EICAS message FUEL XFER CHECK is displayed. NOTE: Fuel transfer operations during takeoff and landing is prohibited, therefore, during those flight phases, the FUS TK XFER knob must be set to OFF. The transfer occurs until the selected auxiliary fuel tank is empty, closing automatically the transfer shutoff valve and turning off the pump. The transfer is not finished unless there is an OFF indication displayed in the associated fuel pump MFD Fuel Page. If the pilot sets the FUS TK XFER knob to OFF before OFF indication, the EICAS message FUEL XFER CHECK may be displayed under certain circumstances. NOTE: Do not switch OFF the FUS TK XFER knob until the MFD Fuel Page displays the associated fuel pump OFF.
Page
REVISION 6
1-02-48
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-02-48
Code
2 01
REVISION 6
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
DESCENT Windshield Heating ....................................................... ON The system must be switched ON to prevent fog and ice formation on the windshield. Speed Bugs................................................................... SET Check on the FMS the expected landing weight and set VREF, VAPP, VAPP CLB, VFS on the MFD: VAPP = VREF + wind correction. Wind correction = ½ headwind + full gust For Flaps 45° landing, the minimum wind correction is 5 KIAS and the maximum is 15 KIAS. For Flaps 22° landing, the minimum wind correction is 0 KIAS and the maximum is 20 KIAS. EXAMPLE: - VREF = 118 kt - Reported wind = 16 kt, gusting to 25 kt - The wind correction would be ½ (16) + (25 - 16) = 17 kt However the maximum wind correction is 15 kt (Flaps 45°), thus: - VAPP = 118 kt + 15 kt = 133 kt This policy is for normal flight only. Refer to the Abnormal and Emergency procedures to obtain the approach speeds for specific non-standard configurations. WHITE BUG CYAN BUG MAGENTA BUG
= VAPP CLB (the same bug used for takeoff V2) = VREF (the same bug used for takeoff VR) = VFS (the same bug used for V1)
Pressurization ............................................................... CHECKED Verify that the digital controller was set to the destination airport elevation. If landing in an airport above 8000 ft, set the destination airport altitude. NOTE: When landing in airports with pressure altitude between 8000 and 8500 ft, the cabin altitude displayed in EICAS will become amber during approach.
Page
REVISION 5
1-02-49
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Curtains .........................................................................STOWED Any curtain used during flight must be stowed for landing. Approach Briefing..........................................................COMPLETED The approach briefing must be carried out by the PF and he must address at least the following items: - Meteorological conditions and runway conditions at destination (LDA, contamination, prevailing winds, lighting, etc.); - Detailed discussion about the STAR and APPROACH PROCEDURE based on the applicable charts; - The setting of the radios, the selection of radio aids, when and how to identify them, how to set courses, altitudes and heights. The approach must be planned to allow a stabilized approach for the last 3 miles before touchdown. It must be kept in mind that this is possibly the last opportunity to do major reprogramming of the FMS. Once below 10000 ft entries into the FMS must be limited to basic data such as direct to. The missed approach procedure must be discussed in detail and both pilots must be totally aware of what to do should the need for a missed approach procedure ever arise. Discuss the best alternative from the company perspective that satisfies the operational constraints. Reserve time available before proceeding to the alternative; conditions at the alternative airport. Radio aids and arrival at the alternative. NOTE: It is highly recommended that the briefing be performed with the active participation of both pilots. Techniques such as reading back or posing questions to each other enhance this participation. Briefings consisting of mechanical repetition of a memorized speech without having the mind set on the subject are useless. Once all items to be performed at the top of descent are complete, the PNF must call out “DESCENT CHECK LIST COMPLETED TO THE LINE”.
Page
1-02-49
Code
2 01
REVISION 5
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
BELOW 10000 FT The following lights must be turned ON upon crossing 10000 ft: - LDG1, NOSE, LDG2 AND TAXI. During night time, the LOGO light must also be turned ON. PC Power ...................................................................... OFF Below 10000 ft the PC Power System must be turned off by pressing the PC Power button on IFE overhead panel. Pax Signs ...................................................................... ON Switch the FSTN BELTS and NO SMKG signs ON upon crossing 10000 ft, if it is not ON yet.
Pocket Door .................................................................. OPEN AND LOCKED Assure that the Pocket Door is in open and locked position. Curtains......................................................................... STOWED Passenger Announcement............................................ PERFORM This announcement is performed by the CREW in order to inform the passengers that the cabin must be in landing configuration according to Pax Briefing. Once all the items above are performed, the PNF must call out “DESCENT CHECK LIST COMPLETED”.
Page
REVISION 4
1-02-49
Code
3 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-02-49
Code
4 01
ORIGINAL
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
DESCENT TECHNIQUE The descent check list must be called for by the PF, challenged and responded by the PNF, when departing the cruise level for lower and after the approach briefing is complete. The PNF must obtain the necessary meteorological information about the destination and the alternate prior to the descent. The Top of Descent can be estimated by taking the difference between the cruise altitude and the initial approach altitude (in hundreds of feet), and dividing it by three. Ex. Cruise altitude: 35000 ft Initial Approach Altitude = 2000 ft TOD = 350-20 = 110 nm 3 The descent can be initiated by selecting FLC after having set the desired target altitude on the ASEL. Use power as necessary to maintain the cruise Mach number that was in use when in cruise flight until reaching 310 KIAS. From this point on the speed of 310 KIAS should be maintained until passing 11000 ft when the engines should be reduced to IDLE. This procedure (the speed/power schedule and the FLC mode) will produce an indicated speed in the vicinity of 240 KIAS when passing 8000 ft. If turbulence is expected during descent, speed must be reduced to the turbulent air penetration speed. In some cases, depending on the weight of the airplane, the use of SPEED BRAKE and/or of the autopilot VS mode may be necessary to decelerate the airplane to 240 KIAS at 8000 ft. Alternatively, an economic descent technique can be used. In this case, the altitude difference is divided by four instead of three. The economic descent is initiated by selecting FLC to ensure a smooth transition. Once the airplane is descending at 2000 ft/min, VS mode is selected and the rate of descent is increased to 3000 ft/min. That rate of descent is maintained down to 10000 ft, where it is reduced to 1000 ft/min.
Page
JANUARY 17, 2003
1-02-53
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-02-53
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
APPROACH Altimeters ...................................................................... SET & XCHECKED When the altimeters are set to QNH (passing the Transition Level) the PF should call for the Approach Checklist, if it is a flight in ICAO airspace. If the flight is in other than ICAO airspace, checklist must be called for at an altitude established as operational standard. The standby altimeter is set to QNH by the PNF. The PNF must verify that both altimeters and the standby altimeter are set to QNH. Approach Aids............................................................... SET & XCHECKED NOTE: The VAPP mode should be selected only on final approach segment, below 2500 ft AGL. Therefore, the outbound segment should be flown using any other mode. Both pilots must verify that the frequencies and courses that were selected are correct for the intended approach. Ensure that both PFD’s are displaying appropriate information. They must also verify that the radio altimeter alert (DH) and the FMS are properly selected for the type of approach in mind. CAUTION: RADIO ALTIMETER-BASED DECISION HEIGHTS ARE NOT RECOMMENDED ON CAT I APPROACHES. THE DECISION ON A CAT I APPROACH HAS TO BE BASED ON THE ALTIMETER RATHER THAN ON THE RADIO ALTIMETER. THE DH ALERT IN THESE CASES IS A REFERENCE ONLY THAT MUST BE USED WITH CARE AND ITS VALIDITY DEPENDS ON THE PILOTS' KNOWLEDGE OF THE TERRAIN BEFORE THE RUNWAY. ALTIMETER-BASED DECISIONS ARE NOT ALLOWED ON CAT II APPROACHES. THE DECISION ON THESE APPROACHES HAS TO BE BASED ON THE RADIO ALTIMETER.
Page
REVISION 3
1-02-57
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
The table below shows the flap maneuvering speeds during a visual approach or during an instrument approach:
Flap
Flap Maneuvering Speed
0 9 22 45
180 kt (200 kt in icing conditions) 160 kt 140 kt 140 kt
These speeds allow an inadvertent 15° overshoot beyond the normal 30° bank. If an overweight land is anavoidable, the speeds above are maintained except for DN/22° configurations, which must be 150 KIAS. If fuel consumption is a consideration, consult the In-flight performance software for maximum endurance speeds. NOTE: The maximum flap 45° extended speed (VFE) of 145 KIAS must not be exceeded in any condition. However, if momentary deviations happen to speeds up to 155 KIAS during flight with flaps 45° or during flap retraction, no maintenance action is required.
Page
Code
2 01 1-02-57 (Pages 3 and 4 deleted)
REVISION 4
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
BEFORE LANDING Landing Gear ................................................................ DOWN The PNF commands gear down when requested by the PF and checks whether the speed is within limits for landing gear extension. Both pilots must check the three green lights before this item is confirmed. Flaps ............................................................................. ___°SET Both pilots must check that the flap position is the intended one for landing. Fuel Transfer................................................................. OFF The PNF must set the fuselage tanks transfer system knob on the Fuel Panel to OFF. Auto Pilot & Yaw Damper.............................................. OFF If this item is challenged when the Autopilot is still coupled, the PF must respond "STANDBY" later in the approach, when the Autopilot and the Yaw Damper are no longer coupled, the PNF responds: "CHECKLIST COMPLETED". CAUTION: YAW DAMPER ON DURING LANDING MAKES THE DIRECTIONAL CONTROLLABILITY OF THE AIRPLANE ON THE RUNWAY MORE DIFFICULT ESPECIALLY WITH GUSTS AND CROSS WINDS.
Page
JANUARY 17, 2003
1-02-61
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-02-61
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
LANDING TECHNIQUE The landing configuration (gear down and landing flaps) should be established early on final approach or at the outer marker on an ILS approach. Airspeed, power and descent rate should be stabilized early. Avoid power off approaches. Fly the aircraft on a stable glide path towards the touch down point. Great changes in airspeed require great changes in thrust and attitude. Speed must be kept within +10 kt, -0 kt relative to the target approach speed. Unnecessary N1 changes of more than 5% will destabilize the approach. Avoid excessive rates of descent during final approach. Descent rates in excess of 1000 ft/min on short final should be avoided. If an excessive rate of descent develops, a missed approach must be performed immediately. Make sure that the aircraft is properly trimmed during the approach. This maximizes elevator authority for the flare or in the event of a missed approach. As the airplane approaches the touch down point, reduce the rate of descent and slowly reduce thrust levers to idle so that they are at idle when the airplane touches down. Normally a 2 to 3 degrees pitch change will be enough for the flare. Plan to touch down as close as possible to the 1000-foot point. Do not allow the aircraft to float in ground effect, which unnecessarily increases the landing distance. Apply back pressure on the control wheel after the main gear touches down to smoothly ease the nosewheel onto the runway. Apply forward pressure on the control wheel after the nosewheel touches down to maximize directional controllability.
Page
NOVEMBER 30, 2001
1-02-65
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-02-65
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
AFTER LANDING After landing and if the F/O is not the PF, he takes over the aircraft controls and calls out “MY CONTROLS”. The copilot in this case hands the control to the CPT and responds “YOUR CONTROLS”. Normal landing is accomplished by using idle and braking as necessary. Braking is most effective at low speeds. If maximum braking is necessary, apply maximum and steady force on the brake pedals. The anti-skid will modulate the pressure applied to each wheel to ensure maximum braking for the runway condition. Do not pump the pedals. Carbon brakes wear more quickly when they are cold, thus avoid heavy brakes application with the brakes cold. Use pedal steering to maintain runway centerline. Avoid using the steering handle at high speeds, which may result in losing the runway centerline and causing passenger discomfort due to its sensitivity. Reverse thrust can be used whenever required to reduce the runway rollout. Reverse thrust is available when the main wheels are rolling at a speed in excess of 25 kt. Use reverse thrust judiciously: it is most effective when the airplane is moving at high speed. After the nosewheel contacts the ground, lift idle gates, smoothly retard thrust levers into Reverse range, then set the proper amount of thrust according to the runway length. Avoid making the first turnoff and use maximum reverse whenever it is operationally essential, but within safety limits. Applying reverse at low ground speeds may cause ingestion of fine sand and debris, which can damage the engine. Therefore, select IDLE below 60 KIAS and use brakes for deceleration. Windshield Heating ....................................................... AS REQUIRED Turn windshield heating off if not required to defog or deice the windshield. The strobe lights must be turned OFF by the copilot as soon as the airplane leaves the runway. However, LDG1, NOSE and LDG2 are switched OFF at the captain’s discretion. The taxi light must remain ON throughout the taxi regardless the time of the day.
Page
JUNE 20, 2002
1-02-69
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Flaps..............................................................................0° The copilot must retract the flaps to 0°. NOTE: Flap retraction from 22° to 0° following landing on a contaminated runway or after operation in icing condition should be delayed until maintenance can visually inspect flap gaps and actuators for freedom of contamination or ice. APU ...............................................................................SET If the intention is to start the APU, do it now. Do not use the APU BLEED until the aircraft is parked and with blocks on (wait at least 3 minutes for use APU bleed). This will maximize the APU life. Transponder ..................................................................STANDBY The copilot must set the TCAS to STBY and press the button by the transponder code for 3 seconds to recall the discrete number that was stored in memory (ex.: 0000). Gust Lock ......................................................................LOCKED The GUST LOCK must be applied immediately after the aircraft leaves the runway by the copilot.
Page
1-02-69
Code
2 01
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
SHUTDOWN GPU/APU ...................................................................... SET If the APU is not running yet, then start it up before the engines are shut down. If the APU (or the APU generator) is unserviceable and there is a GPU available, select the GPU before shutting down the engine. Check the GPU voltage on the MFD ELEC page before selecting it. Shed Buses................................................................... SET When the electrical system is being powered by the APU after the shutdown of both engines. The shed buses must be switched to OVRD if the galley and the IFE power is necessary. If the electrical system is being powered by a GPU after shutdown, the shed buses can be left in AUTO. PUMP PWR .................................................................. SET If the APU is running, keep the right fuel pump ON (or the left pump ON and CROSSFEED open). If the APU is not running, turn both fuel pumps OFF. Red Beacon .................................................................. OFF The red beacon should be switched OFF after the engines are shut down. The use of the Red Beacon should be associated with engine(s) running or aircraft in movement. Start/Stop Selectors ...................................................... STOP Once the Emergency/Parking Brake is applied, shut down the engines by selecting the engine start knobs to STOP. CAUTION: THE ENGINES WILL NOT SHUT DOWN WITH START/STOP SELECTORS UNLESS THRUST LEVERS ARE FIRST MOVED TO IDLE. IF STOP IS SELECTED BEFORE THRUST LEVER IS RETARDED TO IDLE, MOMENTARILY CYCLE START/STOP SELECTOR TO RUN AND BACK TO STOP. NOTE: The engines must run for at least 1 minute at idle thrust before shutdown.
Page
REVISION 3
1-02-73
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
Elec. Hydraulic Pumps ..................................................OFF Once the airplane is parked and the parking brake is applied, the copilot must switch both electric hydraulic pumps to OFF. Air Conditioning Panel ...................................................SET The copilot must switch APU BLEED to OPEN, CROSSBLEED to OPEN, both engine BLEEDs to CLOSED and switch PACK 1 to OFF, thus reducing the external noise in the vicinity of the main passenger door, for better passenger comfort. If better cooling is required after disembarkation is finished, PACK 1 can be switched ON again. Pax Signs ......................................................................OFF The FSTN BELTS lights should be switched OFF by CPT as soon as the airplane is static and the engines are shut down. Parking Brake................................................................ON Typically when approaching the parking position and turning towards the marshal, turn OFF the taxi light. This is especially important during nighttime. Pull the Emergency/Parking Brake and twist it to the set position after airplane has stopped. Make sure that the airplane is static before pulling the Emergency/Parking Brake. The CPT should verify the brake temperatures. If the brakes are in yellow band, release the Emergency/Parking Brake as soon as the chocks are ON. NOTE: To avoid hydraulic fluid transference from system 1 to system 2 first apply brakes using the pedals and after pull the emergency/parking brake handle. To release the emergency/parking brake, do the same procedure.
Page
1-02-73
Code
2 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
NORMAL PROCEDURES
LEAVING THE AIRPLANE Leaving the Airplane phase actions can be carried out by any of the pilots. However it is recommended that both pilots perform them. IRS 1 & 2....................................................................... OFF The manual switching of the IRS ensures proper finalization of the IRS software. Wait a minimum of ten seconds before removing the input power. Avionics Master 1 & 2 ................................................... OFF Select the AVIONICS MASTER 1 & 2 OFF prior to switching GPU or APU OFF. If the airplane is equipped with UNIVERSAL FMS installation, switch the FMS's OFF prior to switching OFF AVIONICS MASTER 1 & 2. Emergency Lights ........................................................ OFF The emergency lights must be switched from ARM to OFF before the batteries are switched OFF. Otherwise the emergency lights will illuminate and drain their batteries. External & Internal Lights .............................................. OFF Pilots should make sure that all internal and external lights are switched OFF (with the exception of the cockpit dome light at night) before switching OFF GPU or APU. Radar ............................................................................ OFF Switch the radar from SBY to OFF. GPU/APU ...................................................................... OFF Shut APU down by pressing the STOP button on its panel. Verify the shutdown on the EICAS. Wait until APU rotation drops to 20% before switching APU MASTER OFF. NOTE: Do not turn the air conditioning packs off before shutting down the APU. Shutting down the APU while bleed air is coming out of it helps extending APU life. If a GPU is the source of electrical power, switch it OFF through the GPU button on the Electrical System panel. Pilots should never leave the airplane unattended and energized. A member of the maintenance team, familiar with the airplane, should always be left in charge before they leave. Page
REVISION 7
1-02-77
Code
1 01
NORMAL PROCEDURES
AIRPLANE OPERATIONS MANUAL
PUMP PWR...................................................................OFF Fuel pumps are needed only as long as the APU is in use. Once the APU is shut down the fuel pumps are not needed any more. So if the airplane is being powered by the GPU or solely by the batteries the pumps are not needed. Air Conditioning Panel ...................................................OFF Set the PACK buttons to OFF and the BLEED buttons to CLOSED on the Air Conditioning/Pneumatic panel, if they are not in this position already. The XBLEED valve should be left in AUTO. The RECIRC and GASPER buttons should be left pressed (this is their normal state). Batteries 1 & 2 ...............................................................OFF Switch both batteries OFF.
Page
1-02-77
Code
2 01
REVISION 7
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AIRPLANE OPERATIONS MANUAL
OPERATION IN ICING CONDITIONS This Section contains amplified procedures to Operation in Icing Conditions, Cold Weather Operation and Cold Soak Operation that supplement those procedures published in the AFM. In case of disagree, the AFM shall prevail. EXTERNAL SAFETY INSPECTION Operating regulations clearly state that no takeoff is allowed when snow, ice or frost is adhering to the airplane. The responsibility for ensuring a clean airplane rests with the flight crew. The primary method for the flight crew to ensure a clean airplane is through close visual or physical inspection of the critical surfaces prior to takeoff. Even at intermediate stops, an external walk around is necessary due to the possibility of ice forming after landing from either cold soaking frost, conventional frost, clear ice on wing upper surface or precipitation freezing on the airplane. During the pre-flight walk-around, ensure that the pitot tubes, static ports, TAT probe, AOA vanes, all inlets, outlets and vents are clear of ice and unobstructed. A 3 mm (1/8 in) frost layer is permitted on the underwing surfaces. Frost is not permitted on the lower surface of the horizontal stabilizer or the upper surface of the wing. If the airplane has become cold soaked as a result of flight at very cold temperatures, fuel might be at a subfreezing temperature. This can cause ice accretion if the airplane is subjected to high humidity, fog, drizzle or rain even when the outside air temperature is substantially above freezing. At the completion of the walk-around, if ice, snow or frost is discovered, de-icing, and possibly anti-icing will be required. The check for ice accumulation should be done in a well-lit area.
Page
NOVEMBER 30, 2001
1-02-79
Code
1 01
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AIRPLANE OPERATIONS MANUAL
All Protective Covers .....................................................REMOVE Remove covers from engine air inlet/outlet, APU air outlet, pitot tubes, TAT probes and wheels. Fuselage, Wing, Tail and Control Surfaces .................................................FREE OF FROST, ICE OR SNOW Check that the fuselage, wing upper and lower surfaces, tail and control surfaces are free of frost, ice or snow. Inspect control surfaces, gaps and hinges for signs of residual fluid or gel. A thin layer of hoarfrost is permitted on the fuselage provided the layer is thin enough to distinguish surface features underneath, such as painting and markings. Frost is not permitted on the lower surface of the horizontal stabilizer or the upper surface of the wing. Pitot Tubes, TAT, Static Ports and AOA Vanes ...............................CLEAR OF ICE Engine/APU Air Inlet......................................................CLEAR OF ICE OR SNOW Check that the engine inlet is clear of ice or snow, and that the fan is free to rotate. Ensure that all ice deposits are removed prior to engine starting. Check the APU air inlet to ensure that it is clear of ice or snow. Landing Gear ................................................................CLEAR OF ICE, UNOBSTRUCTED Check that doors, gear locks and mechanisms are unobstructed and clear of ice and snow. Check that no leakage exists. Air Conditioning Inlets and Outlets ................................CLEAR OF ICE Fuel Tank Vents ............................................................CLEAR OF ICE OR SNOW Batteries ........................................................................INSTALLED Certain temperatures require batteries removal to prevent cold soaking. Verify that batteries have been re-installed.
Page
1-02-79
Code
2 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
INTERNAL SAFETY INSPECTION APU............................................................................... START Observe fuel and oil limitations before APU starting. Minimum fuel temperature is -40°C (-40°F). Minimum MIL-L-23699 oil temperature is -43°C (-45°F). Minimum MIL-L-7808 oil temperature is -54°C (-65°F). Minimum battery temperature to start the APU is -20°C (- 4°F). Minimum temperature to start APU using external electrical power is -54°C (- 65°F). If APU cannot be started, apply heat from a ground cart directly into the APU compartment. Do not allow the hot air from the ground heating cart to exceed 100°C (212°F), as it may damage the components inside the compartment. Air Conditioning ............................................................ SET Turn both air conditioning packs on, bleeding air from the APU (or from a ground conditioned air cart, with packs off) to warm up the interior of the airplane. The warm-up should be accomplished with all doors closed, if possible. Turn recirculation fans on. In very cold days, Embraer recommends a gradual warming of the cabin, as follows: - Set air conditioning control to manual mode; - Put the cockpit temperature selection knob in the 9 o’clock position; - Wait approximately 3 minutes; - Change control to automatic mode; - Wait another 2 minutes before controlling temperature as required. CAUTION: • MANTAIN CABIN AT THE FIELD ELEVATION. DO NOT PRESSURIZE THE AIRPLANE. • WITH PACKS OPERATING AND DOORS CLOSED, DO NOT LEAVE THE AIRPLANE UNATTENDED. Electric Hydraulic Pumps .............................................. ON Check hydraulic pressure. If pressure does not rise to normal values, warm up the hydraulic reservoir compartment with hot air and keep the electric hydraulic pumps running for 15 minutes. Do not allow the hot air from the ground cart to exceed 100°C (212°F), as it may damage the components inside the compartment. Page
REVISION 7
1-02-79
Code
3 01
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AIRPLANE OPERATIONS MANUAL
Flight Controls ...............................................................CHECK Check control wheel, control column and rudder pedals for freedom of movement and full travel. Control forces can be increased at low temperatures. Operate all trim systems, including back up pitch trim system, checking for freedom of movement and full travel. If any flight control is suspected of restricted movement or jamming, report to maintenance personnel. Flaps..............................................................................CHECK Extend and retract the flaps. Make sure the flaps are free from snow or ice before moving them. Leave flaps UP if application of anti-icing/deicing fluids is expected. ENGINE START SPS/ICE SPEEDS message will remain displayed after icing encounter. Before takeoff the message must be removed by testing the Stall Protection System. Do not start the engine until it has been checked that all ice deposits have been removed from the air inlet. Fuel and oil temperature limits are the same as those prescribed for APU start. Proceed with normal engine start. In cold weather conditions, the usage of dual ignition (ignition switch rotated to the ON position) is highly recommended for the first engine start of the day or if the engine has not been run in the previous 90 minutes. This procedure may reduce the time from fuel introduction to light-up. As a reference, this procedure can be used for temperatures below 5°C (41°F), or at operator's discretion. After a successful start the Ignition Switch must be switched to the AUTO position. If the engine does not start, ground heating may be necessary to warm the nacelle, Air Turbine Starter (ATS) and Starting Control Valve (SCV). Do not allow the hot air from the ground cart to exceed 100°C (212°F), as it may damage the components inside the nacelle.
Page
1-02-79
Code
4 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AFTER START
Ice Detection Override Knob ......................................... ENG The Ice Detection Override Knob must be at ENG during all ground operations (in icing conditions) except during ice protection system test. Wing and stabilizer anti-icing must be kept off. Crossbleed .................................................................... AUTO CAUTION: • BOTH ENGINE BLEEDS MUST BE OPEN, IN ORDER TO ASSURE BLEED AIR FLOW THROUGH THE LEADING EDGES. APU BLEED MUST NOT BE USED. • DELAYING THE USE OF THE ENGINE ANTI-ICING SYSTEM UNTIL ICE BUILD-UP IS VISIBLE FROM THE COCKPIT MAY RESULT IN ICE INGESTION AND POSSIBLE ENGINE DAMAGE OR FLAME-OUT. Engine Instruments ....................................................... MONITOR Continue to monitor engine instruments, mainly oil pressure and temperature. Apply associated abnormal procedure if any failure arises. Main Panel .................................................................... CHECK Check proper operation of all instruments and systems.
Page
REVISION 4
1-02-79
Code
5 01
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AIRPLANE OPERATIONS MANUAL
AIRPLANE ANTI-ICING/DEICING ENGINES/APU RUNNING
FLUID
APPLICATION
WITH
WARNING: APU OPERATION IS NOT RECOMMENDED DURING THE AIRPLANE DEICING/ANTI-ICING PROCEDURE. IF THE APU IS KEPT IN OPERATION DURING THE DEICING/ANTI-ICING PROCEDURE, DAMAGE CAN OCCUR TO IT. IF APU OPERATION IS ABSOLUTELY NECESSARY, MAKE SURE THAT THE APU BLEED AIR VALVE IS CLOSED, PACKS ARE SET TO OFF, AND THE DEICING/ANTI-ICING FLUID IS NOT APPLIED DIRECTLY TO OR NEAR THE APU AIR INLET. Parking Brake................................................................ON Thrust Levers ................................................................IDLE Gust Lock ......................................................................ENGAGE Doors.............................................................................CLSD o Flaps..............................................................................0 o Pitch Trim ......................................................................4 NOSE UP Engine Bleed .................................................................CLOSED APU Bleed .....................................................................CLOSED Air Conditioning Packs ..................................................OFF Packs should be off to avoid contamination of cabin air with fumes generated from ingestion of fluids in engine/APU. Ice Detection Override Knob .........................................ENG After Deicing/Anti-icing Procedure is complete: ENG Bleeds...................................................................OPEN AFTER 1 MIN Packs.............................................................................ON AFTER NEXT 3 MIN APU Bleed .....................................................................REMAIN CLOSED DURING T/O AND INITIAL CLIMB Wait at least one minute to open engine bleed, and three minutes to turn air conditioning packs on, thereby avoiding contaminating the airframe air conditioning system with deicing/anti-icing fluid gases. The deicing/anti-icing fluid shall drop out after initial climb then allowing the APU bleed valve opening. Page
1-02-79
Code
6 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
Ice Detection Override Knob ......................................... ENG The Ice Detection Override Knob must be at ENG during all ground operations in icing conditions. Pitch Trim ...................................................................... SET Pitch Trim must be set as per CG position stated in the Weight and Balance sheet. TAXI The maximum recommended wind speeds for airplane towing, pivoting, turning and taxi are: - Dry Runways .............................................................. 50 kts - Wet Runways ............................................................. 45 kts - Snow Covered Runways............................................. 30 kts - Ice Covered Runways ................................................. 10 kts Power backs are not allowed. Use minimum thrust to avoid blowing snow or slush on personnel or airplanes nearby. During taxi, “cold set” (the condition where the tire retains the flat shape it had while parked) may induce vibration in the airplane. Vibration should disappear as the tires recover their elasticity during taxi. Do not initiate your takeoff run before the cold set disappears. Maintain a greater than normal distance behind other airplanes while taxiing in snow-covered runways, to avoid contamination by snow blown by jet blasts. Do not apply reverse thrust during taxi, unless it is strictly necessary. Flaps ............................................................................. AS REQUIRED When taxiing through slush or standing water, flaps should be retracted to avoid snow and slush contamination from the main gear wheels. CAUTION: • IF FLAPS WERE LEFT UP DURING TAXI, COMPLETE AFTER START CHECKLIST BEFORE TAKEOFF. • TAXI AT REDUCED SPEED IN ICE-COVERED RUNWAYS TO AVOID SKIDDING THE AIRPLANE.
Page
REVISION 7
1-02-79
Code
7 01
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AIRPLANE OPERATIONS MANUAL
BEFORE TAKEOFF Ice Protection Test: NOTE: - The ice protection test must be carried out once a day (not necessarily at the first flight of the day) when icing conditions are forecast. - The test may be carried out completely on the ground, or in 2 separate phases (first phase on the ground and second phase in flight), depending on weather conditions and crew discretion. For takeoffs when icing conditions exist or are anticipated for takeoff or climb, the tests in paragraph A must be performed. On the ground, if engine vibration increases, advance thrust levers, one at a time, to obtain at least 60% N1 for 5 seconds and then return to the former setting. A - When actual icing conditions exist or are anticipated for takeoff and climb, proceed: Ice Detection Override Knob ....................................ALL Thrust Levers ...........................................................83% N2 Ice Detection Test Knob...........................................1, THEN 2 Test knob must be held at least 10 seconds in each test position but no more than 15 seconds. For each side separately, check that OPEN inscriptions in the buttons are illuminated and that, ICE DET 1 (or 2) FAIL and BLD 1 (or 2) LOW TEMP caution messages and ICE CONDITION and CROSS BLD OPEN advisory messages are displayed on EICAS. NOTE: - When the Ice Detection Test Knob is selected to 1, the CLR ICE 1, CLR ICE 2, CLR/I INOP 1 and CLR/I INOP 2 caution messages are displayed on the EICAS and the lights CLR ICE 1 and CLR ICE 2 illuminate; when the Ice Detection Override Knob is selected to 2, none of those caution messages are displayed on the EICAS. - Wait for the messages go out of view after each release of the Test knob. Thrust Levers ...........................................................IDLE Ice Detection Override Knob ....................................ENG CAUTION: ICE DETECTION OVERRIDE KNOB MUST NOT BE SET TO "ALL" ON GROUND, EXCEPT DURING TEST.
Page
1-02-79
Code
8 01
REVISION 6
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
B - For flight when no actual icing conditions exist or are anticipated for takeoff and climb, proceed: Before engines start, perform the on ground test: APU Bleed ..................................................... CLOSE Engine Bleed ................................................. CLOSE Anti-Icing Buttons (Engine, Wing and Stabilizer) ........................... PRESSED Ice Detection Override Knob.......................... AUTO Ice Detection Test Knob ................................ 1, THEN 2 Test knob must be held at least 10 seconds in each test position. For each side separately, check that ICE DET 1 (or 2) FAIL and BLD 1 (or 2) LOW TEMP caution messages and ICE CONDITION advisory message are displayed on EICAS. NOTE: When the Ice Detection Test Knob is selected to 1, the CLR ICE 1, CLR ICE 2, CLR/I INOP 1 and CLR/I INOP 2 caution messages are displayed on the EICAS and the lights CLR ICE 1 and CLR ICE 2 illuminate; when the Ice Detection Override Knob is selected to 2, none of those caution messages are displayed on the EICAS. During climb, perform the inflight test: Engine Bleeds................................................ OPEN Thrust Lever .................................................. THRUST SET Altitude........................................................... FROM 2000 TO 23000 FT TAT ................................................................ LESS THAN 10°C Ice Detection Override Knob.......................... ALL FOR 20 SECONDS Check that OPEN inscriptions in the buttons are illuminated and NO ICE-A/ICE ON caution message is displayed on EICAS. The CROSS BLD OPEN advisory message may be also displayed. Ice Detection Override Knob.......................... AUTO (AFTER 20 SECONDS) NOTE: The ice protection test must be fully accomplished before entering icing conditions and before reaching 23000 ft.
Page
REVISION 6
1-02-79
Code
9 01
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AIRPLANE OPERATIONS MANUAL
After completion of the test, set the Ice Detection Override Knob to ENG. Check that engine REF A/ICE on MFD takeoff page is set to ON. Ignition ...........................................................................ON Turn ignition on when standing water, ice, or snow is present on the takeoff runway. Takeoff Briefing .............................................................COMPLETE Confirm V1/VR/V2 and VFS speeds for the associated runway or takeoff condition. Flight Controls ...............................................................CHECK Check freedom of movement and full travel of all flight controls (including trims). Flaps..............................................................................TAKEOFF SETTING Set flaps to takeoff setting (if flaps were left up after starting). Takeoff Configuration....................................................CHECK Ice Accumulation ...........................................................CHECK Continuously monitor ice accumulation, by checking windshield and windshield wiper. High winds and jet blast may cause anti-icing fluid to flow off and many other factors contribute to reduce fluid effectiveness. TAKEOFF
Takeoff in a normal manner. Check thrust rating mode. T/O-1 mode gives the maximum weight and thrust for the associated runway. Do not apply static takeoff technique on an icy or slippery runway, as the airplane may begin to slide when thrust lever is advanced with brakes applied. In this case, release brakes and advance thrust levers simultaneously. However, takeoff distance for slippery runways is calculated in the AFM using the static takeoff technique only. For rolling takeoffs, performance data is valid from the point where takeoff thrust is achieved. Check N1 indication consistent with takeoff thrust setting tables (check AFM performance tables which have dedicated thrust setting tables for takeoff in icing conditions). Check N1 pointer reaching N1 target.
Page
1-02-79
Code
10 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
Apply light forward pressure on control column to increase nose wheel steering effectiveness. Check engine stable operation during takeoff run. Rotate the airplane at VR smoothly to takeoff attitude. After lift-off, smooth flight control inputs should be applied if any tendency in pitch and roll are felt. Use of flight director takeoff sub-mode is recommended (on those certifications which allow the use of flight director during takeoff). Flight controls forces may be heavier than normal, without causing any difficult in controllability. Increased V2 procedures (if available in the approved AFM) may be used if runway length is not a limiting factor. AFTER TAKEOFF Ice Protection Test (if applicable).................................. COMPLETE Ice Detection Override Knob ......................................... AUTO Monitor weather conditions for an encounter with ice for the remainder of the flight. Closely monitor the static air temperature indication so that when moisture is present, a look at the windshield and windshield wiper will indicate if ice is accumulating. Notwithstanding installation of the ice detector, the crew remains responsible for monitoring icing conditions and for manual activation of the ice protection system whenever necessary. Ignition........................................................................... AS REQUIRED CLIMB/CRUISE If engine vibration increases, advance thrust levers, one at a time, to obtain 60% N1 minimum for 5 seconds, and then return to the former setting. If ITT increases beyond limits, reduce Thrust Levers as required to maintain ITT within limits. When flying in icing conditions or after flying in icing conditions, ice accretion on unprotected areas may cause vibration at high speeds. If vibration and/or buffeting occurs, a change in the current airspeed will eliminate these effects. At high speeds reduce the airspeed as required, limited to a minimum of 200 KIAS. Observe normal (including operation in icing conditions) procedures contained in the approved AFM.
Page
REVISION 7
1-02-79
Code
11 01
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AIRPLANE OPERATIONS MANUAL
No special technique is required to fly with the autopilot on or off. Climb using FLC mode provides enough speed margin to stall. SPD and VS modes may also be used, provided that the airspeed is not allowed to decrease below 200 KIAS (when flying IAS) or 0.56 M (when flying Mach). During autopilot operation, monitor pitch attitude and speed continuously. If BLD 1 (2) LOW TEMP message appears, advance Thrust Lever until the message disappears and check bleed temperature pointer (MFD ECS and Pneumatic page) in the green range. During cruise, observe minimum fuel tank temperature (-40°C). If fuel temperature is reaching the limit, apply the FUEL LOW TEMPERATURE procedure in the AFM. HOLDING Landing Gear.................................................................UP Flaps..............................................................................UP Minimum Airspeed.........................................................200 KIAS CAUTION: MAINTAIN A MINIMUM AIRSPEED OF 200 KIAS SINCE EVEN SMALL ACCUMULATIONS OF ICE ON THE WING LEADING EDGE MAY CHANGE THE STALL CHARACTERISTICS OR THE STALL PROTECTION SYSTEM WARNING MARGIN.
DESCENT Observe normal (including operation in icing conditions) procedures contained in the approved AFM. When using the autopilot, monitor pitch attitude and speed continuously. If approaching the terminal area in icing conditions, an increased rate of descent may be necessary. In this case, a combination of flaps set o at 9 and speed brakes open may be used.
Page
1-02-79
Code
12 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
APPROACH AND LANDING Observe normal (including operation in icing conditions) approach/landing procedures contained in the approved AFM. When landing below -40°C (-40°F), ensure that rate of descent before touchdown is less than 300 ft/min. After landing, report to the maintenance personnel. NOTE: During approach and landing with engines and anti-icing system on, the FADEC logic automatically reduces the Flight Idle thrust when landing gear is lowered. LANDING ON WET OR SLIPPERY RUNWAYS Wet runways can cause airplane hydroplaning, the technical term used to express slipperiness. The factors that influence the occurrence of this phenomenon are high speed, standing water and poor runway macrotexture. When hydroplaning occurs, it causes a substantial loss of tire friction and wheel spin-up may not occur. Icy runways can be very slippery at all speeds depending on temperature. Stopping the airplane with the least landing run must be emphasized when landing on wet or slippery runways. − Anticipate the approach procedures and speeds: a well-planned and executed approach, flare and touchdown minimize the landing distance. − Immediately after touchdown, check the ground spoiler automatic deployment when thrust levers are reduced to IDLE. − Lower nose wheel immediately to the runway. It will decrease lift and will increase main gear loading. − Apply thrust reversers judiciously to observe how the airplane responds before full reverse is used. Normal procedure is to move the thrust levers out of reverse when ground speed is reduced to 50 knots. In a emergency, reverse thrust may be used to bring the airplane to a full stop. − Do not use asymmetric reverse thrust on slippery and icy runways. − Apply brakes with moderate-to-firm pressure, smoothly and symmetrically, and let the anti-skid do its job. − If no braking action is felt, hydroplanning is probably occurring. Do not apply Emergency/Parking Brake, as it will cut anti-skid protection and may cause the spoilers to close. Maintain runway centerline and keep braking until airplane is decelerated. Page
ORIGINAL
1-02-79
Code
13 01
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AIRPLANE OPERATIONS MANUAL
TAXI-IN AND PARKING Ice Detection Override Knob .........................................ENG Flaps..............................................................................AS REQUIRED NOTE: Make sure the flaps are free from snow, ice or slush before moving them to the up position. CAUTION: TAXI AT REDUCED SPEED IN ICE-COVERED RUNWAYS TO AVOID SKIDDING THE AIRPLANE.
THROUGH-FLIGHTS Doors and Windows ......................................................CLOSED Whenever possible, to maintain the cabin warm, keep the passenger, baggage and service doors closed at intermediate stops. APU ...............................................................................ON APU should be on to provide bleed air to maintain cabin warm. Air Conditioning Packs ..................................................ON Recirculation Fans.........................................................ON Walk around the airplane and check the following items: Wing, Tail and Control Surfaces ...................................FREE OF FROST, ICE OR SNOW Pitot Tubes, TAT, Static Ports and AOA Vanes...............................................................CLEAR OF ICE Engine/APU Air Inlet......................................................CLEAR OF ICE OR SNOW Landing Gear ................................................................CLEAR OF ICE, UNOBSTRUCTED Air Conditioning Inlets and Outlets ................................CLEAR OF ICE Fuel Tank Vents ............................................................CLEAR OF ICE OR SNOW Ask for deice/anti-ice fluid application, if necessary.
Page
1-02-79
Code
14 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
LEAVING THE AIRPLANE - SECURING FOR COLD SOAK OR AN EXTENDED PERIOD Anti-icing fluid can be applied to the airplane surfaces at the time of arrival, on short turnarounds during freezing precipitation, and on overnight stops. This will minimize ice accumulation before departure and usually makes subsequent deicing easier. The procedures below should be performed in the event of extended airplane exposure at low temperatures. In the event that the airplane is off the maintenance base, the crew should ensure that all actions have been accomplished. Wheel Chocks............................................................... IN PLACE Emergency/Parking Brakes .......................................... AS REQUIRED For an icy ramp, leave Emergency/Parking Brakes applied. Otherwise, Emergency/Parking Brakes must not be applied to avoid freezing of the brakes. Flight Controls ............................................................... LOCKED Set pitch trim to at least 4 degrees nose UP after landing in icing conditions to prevent melting snow from accumulating and freezing between control surfaces. Protective Covers.......................................................... INSTALLED Install protective covers at engines and APU inlets/outlets, pitot, TAT probes, and wheels. Water and Waste System ............................................. DRAINED Drain water and waste from all water tanks, if cold soak temperature is expected to be below 0°C (32°F). Fuel System .................................................................. DRAINED Drain water from all fuel tanks, if cold soak temperature is expected to be below 0°C (32°F). Batteries ........................................................................ REMOVED Remove the batteries if temperatures are expected to be below -20°C (-4°F). This protects the batteries and ensures starting capability of the APU upon installation. Doors and Windows...................................................... CLOSED All doors and windows must be closed to prevent snow and humidity from entering into the airplane.
Page
REVISION 6
1-02-79
Code
15 01
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AIRPLANE OPERATIONS MANUAL
GENERAL REMARKS WHEN FLYING IN ICING CONDITIONS − Continuously monitor engine parameters, airplane pitch attitude and airspeed; − Be careful for any mistrimed condition that may be masked by the autopilot - keep the airplane trimmed all the time. Consider turning autopilot off if you suspect you are flying in severe icing conditions; − Monitor anti-ice systems for proper operation. Apply the associated AFM abnormal procedure in case of system failure. If the failure persists, exit and avoid icing conditions. Make the air traffic controller know you are requesting a change due to icing conditions and keep him informed about it; − Strictly follow AFM Operation In Icing Condition normal procedures; − Avoid landing in an airport where icing conditions exist or are anticipated if anti-ice system, brakes, thrust reverse, ground spoilers, nosewheel steering or flight controls have failed; − Do not hesitate to leave icing conditions when icing cannot be handled, even with anti-ice system operating properly. FREEZING RAIN AND FREEZING DRIZZLE Atmospheric conditions involving freezing rain or freezing drizzle associated to supercooled large droplets (SLD), may present a condition that is beyond those for which the airplane was certified. Both freezing rain and freezing drizzle can exist down to ground level and cause ice to form quite rapidly on all surfaces even during short exposures and on areas not normally known to be subjected to ice accretion. This means that the aircraft is not designed to fly under freezing rain/drizzle (SLD) conditions. If the crew notices abnormal ice formation on areas not usually affected by this phenomenon, or ice formation on the previously treated upper surface of the wings, they must consider to be flying under severe icing conditions. In this case, the anti-ice system is failing to reduce or control ice formation. The crew must then exit freezing rain/drizzle conditions as soon as possible since continuous flight under such conditions is, indeed, quite hazardous.
Page
1-02-79
Code
16 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
FLAP OPERATION UNDER ICING CONDITIONS Ice accretion on an airplane depends mainly on the cloud type encountered, the cloud liquid water content and droplet size, and weather conditions. Icing should be expected when flying in visible precipitation, such as rain or cloud droplets, with a temperature between +2°C and -10°C (between 35.6°F and 14°F). Regardless of the airplane type, the wing, horizontal stabilizer, and engine inlets are typically critical airplane parts for ice accretion and are protected with anti-icing or de-icing systems. The wing flaps are not equipped with a anti-icing or de-icing system and, therefore, if they remain extended for a long period of time in icing conditions, ice may build up on the flaps leading edge. This ice may cause difficulties in retracting the flaps. For a certain flight time in different weather conditions, the ice accretion intensity may vary, being either trace, light, moderate, or severe. Because of the varying conditions, it is not possible to state a reliable time figure that would cover all situations. Therefore, as a general policy, the use of flaps in icing conditions should be avoided or minimized whenever possible.
Page
REVISION 7
1-02-79
Code
16A 01
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
Code
1-02-79 16B 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
TURBULENT AIR PENETRATION Flight through severe turbulence must be avoided, if possible. If not possible, reduce altitude to increase buffet margin. The recommended procedures for turbulent air penetration are: 1. AIRSPEED At or below 10000 ft ................................................. 200 KIAS Above 10000 ft......................................................... 250 KIAS/ 0.63 M, WHICHEVER IS LOWER Severe turbulence will cause large and often rapid variations in indicated airspeed. Do not chase the airspeed. 2. ATTITUDE Maintain wings level and proper pitch attitude. Use attitude indicator as the primary instrument. In extreme drafts, large attitude changes may occur. Do not use sudden large control inputs. 3. PITCH TRIM Maintain control of the airplane with the elevators. After establishing the trim setting for penetration speed, do not change pitch trim. 4. ALTITUDE Large altitude variations are possible in severe turbulence. Sacrifice altitude in order to maintain the desired attitude. Do not chase altitude. 5. THRUST SETTING Make an initial thrust setting for the target airspeed. Change thrust setting only in case of extreme airspeed variation. In case of inadvertent negative-g condition, reduce thrust levers. NOTE: Do not extend flaps except for approach and landing.
Page
ORIGINAL
1-02-79
Code
17 01
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AIRPLANE OPERATIONS MANUAL
VOLCANIC ASH Flight in areas of known volcanic activity must be avoided. This is particularly important during hours of darkness or daytime instrument meteorological conditions when volcanic dust may not be visible. When a flight is planned into an area with a known potential for volcanic activity, it is recommended that all NOTAMs and air traffic control directives be reviewed for current status of volcanic activity. If volcanic activity is reported, the planned flight should remain well clear of the area and, if possible, stay on the upwind side of the volcanic dust. The airplane’s weather radar is not capable of detecting volcanic ash/dust clouds and is therefore not reliable under these circumstances. The presence of volcanic ash/dust may be indicated by: − Smoke of dust appearing inside the airplane; − An acrid odor similar to electrical smoke or burnt dust or sulfur; − Engine malfunctions such as power loss, engine stalls, increasing ITT, fluctuating engine RPM, etc; − At night, Saint Elmo’s fire/static discharges may be observed around the windshield or windows; − Orange glow from engine inlets. Flight into volcanic ash/dust clouds can result in the degradation of airplane and engine performance. The adverse effects cause by volcanic ash/dust encounters may be: − Rapid erosion and damage to the internal engine components; − Ash/dust buil-up and blockage of the guide vanes and cooling holes, which may cause surge, loss of thrust and/or high ITT; − Ash/dust blockage of the pitot system, resulting in unreliable airspeed indications; − The abrasive properties of volcanic material may cause serious damage to the engines, wing and tail leading edge surfaces, windshields, landing lights, etc. − Windshield and windows may become opaque, reducing the visibility.
Page
1-02-79
Code
18 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
ON GROUND OPERATIONS The following recommendations apply to starting and operating engines on airports where volcanic ash has fallen and ground contamination is present: − During preflight, check that the engine inlet and exhaust areas have been cleared of volcanic ash; − Check that all volcanic ash has been cleaned away from the area within 25 ft of the engine inlets; − Prior to starting, dry motor the engine for one minute in order to blow out any ash that may have entered the engine bypass duct area; − Use minimum required thrust for breakaway and taxi; − Be aware of loose ash being blown by the exhaust wake of other aircraft. Maintain adequate ground separation; − Use a rolling takeoff technique. Avoid setting high thrust at low airspeeds; − After landing at an airport contaminated with volcanic ash, minimize the use of reverse thrust to prevent any recirculation ingestion; − Avoid static engine operation above idle; − Use APU for engine starting only, not for air conditioning.
Page
ORIGINAL
1-02-79
Code
19 01
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AIRPLANE OPERATIONS MANUAL
IN FLIGHT OPERATIONS Flight operations in volcanic ash are extremely hazardous and must be avoided. However, volcanic ash/dust clouds may sometimes extend for hundreds of miles, reaching altitudes above 60000 ft and an encounter may be unavoidable. In case of an inadvertent encounter, proceed as follows: APU (if available)...........................................................START Thrust Lever (if altitude permits) ...................................IDLE Anti-Icing Buttons (Engine, Wing and Stabilizer)...........PRESSED Ice Detection Override Knob .........................................ALL This action will increase bleed air extraction from the engines and further improve the engine stall margin. ITT .................................................................................MONITOR If the ITT is still increasing even with the thrust levers in idle: Affected Engine ........................................................SHUTDOWN If it becomes necessary to shutdown an engine to prevent exceeding ITT limits, restart the engine once it has cooled down. If the engine fails to start, repeated attempts should be made immediately. NOTE: A successful start may not be possible until the airplane is clear of the volcanic ash/dust, and the airspeed and altitude is within the airstart envelope. Take note that engines can be very slow to accelerate to idle at high altitudes and this could be interpreted as a failure to start or as an engine malfuntion. After exiting the area of volcanic ash/dust cloud and the engine(s) restarted, restore systems to normal operation. Inform ATC of the encounter.
Page
1-02-79
Code
20 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
LIGHTNING STRIKE Even though the airplane is adequately protected against lightning strikes effects, operating procedures should be established in an attempt to avoid such phenomenon. Avoid penetration of thunderstorms. In-flight lightning avoidance is closely associated with thunderstorm avoidance. Maintain visual contact with thunderstorms during the daytime and lightning at night. Check the radar for precipitation, review all available types of weather information, examine other pilot reports and follow ATC instructions. Even with a good weather report received and understood, pay close attention to those storms that develop rapidly along the route in a given area and that cannot be predicted. While enroute, constantly update the previous weather briefing through radio contact and airborne equipment for actual storm avoidance. Remember that radar detects only liquid droplets, not the cloud itself. Only rain suspended in the cloud will produce a radar echo, which may lead to occasional encounters with hail and lightning. Circumnavigate the detected thundercloud or area, if possible by more than 25 miles when traffic conditions permit. Flying over the top of the thunderclouds is preferable. Be aware that lightning can strike an airplane miles away from the extreme side of a developed thunderstorm. Reports of airplane receiving strikes in clear air at 25 or more miles from the nearest storm are common. The following paragraphs summarize the conditions in which strikes are most common: − Meteorological conditions: incident reports show that an airplane must be within or beneath a cloud to receive a strike, or in or near regions of precipitation. Incident reports show that in over 80% of the strikes, the airplane was within a cloud and experiencing some precipitation and turbulence. But other strikes may occur in a cloud where there is no precipitation nearby, in clear air reasonably distant from a thundercloud, during snowstorms and in clouds over erupting volcanoes. Flight through or in the vicinity of cold front, warm front, stationary front, unstable air or squall line are indicators of imminent lightning strikes. Incident reports also show that lightning strikes occur most commonly under light or heavy turbulence conditions. − Flight regime: Takeoff, climb, level flight, descent or approach.
Page
ORIGINAL
1-02-79
Code
21 01
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AIRPLANE OPERATIONS MANUAL
− Altitude: strikes are more intercepted between 5000 and 15000 ft, but may occur at virtually all flight altitudes. Lightning strike incidents at lower altitudes are far more frequent since at higher altitudes airplanes can divert around thunderclouds with greater ease. − Outside air temperature: most strike incidents have occurred when the airplane is flying in temperatures near or at freezing level. Strikes may also occur at temperatures as high as 25°C, or as low as -45°C. Metal airplanes produce a phenomenon called Faraday Cage effect, which distributes electrical charges along the airframe in such a manner that occupants and internal components will not receive the high current that causes injury and damage. There seems to be no record of any case of crew incapacitation due to lightning, although flash blindness can occur for a few seconds. Direct effects which result from lightning current attachment to and flow through the airplane may be: − Pit marks are often seen along the fuselage or holes in the trailing edge of wing and tail tips. − Melting of rivets. − Puncturing of nonmetallic structures. − Puncturing and de-lamination of composites. − Slight deformation of metal skins and structure. − Welding or roughening of moveable hinges and bearings. − Damage to other parts that may conduct lightning current other than the airframe, such as bonding or diverted straps and pitot tubes. Effects caused by the flash-induced electromagnetic field and the increase of the voltage due to the current at the airplane structure are defined as indirect effects and may be: − Interruption of instruments and navigation equipment. − Damage to electronic and electrical equipment. − Popping of circuit breakers. − Loss of electrical power. − Engine flame-out. In case of lightning strike, report the incident to the maintenance personnel, by filling out the LIGHTNING STRIKE REPORT (Abnormal Procedures - Section 1-03-30 - Doors and Miscellaneous).
Page
1-02-79
Code
22 01
REVISION 7
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AIRPLANE OPERATIONS MANUAL
IN FLIGHT OPERATIONS IF LIGHTNING STRIKE IS SUSPECTED TO OCCUR An imminent lightning strike event may be indicated to flight crews by the buildup of static discharge which causes interference on ADF indicators or noise in communication receivers. Another indication is St. Elmo’s Fire, which is visible at night as small electrical discharges running across the windshields and sparking on the wings. Consider wearing sunglasses to protect your eyes from the flash or have one pilot keep eyes downward. All Cockpit Lights........................................................... ON/FULL BRIGHTNESS IF THE AIRPLANE HAS BEEN HIT BY LIGHTNING If situation is under control after a lightning strike, apply the following procedure to ascertain whether the flight may be proceed. Circuit Breakers ............................................................ CHECK Compass/Heading System ........................................... CHECK Check magnetic compass and heading system for normal indication. Engine Indication........................................................... CHECK Check engine for normal indication and apply associated procedure if any failure arises after strike attachment. In case of engine shutdown, the flight crew shall analyze the circumstances of the event and consider an engine airstart. Pressurization ............................................................... CHECK Check pressurization system for normal indication. Flight Controls ............................................................... CHECK Check all flight controls for freedom of movement. Verify that flaps and speed brakes are working properly (refer to flaps and speed brakes operating limits). Fuel System .................................................................. CHECK Check fuel system for normal operation. Monitor fuel remaining and fuel consumption to ascertain that no fuel leak exists. Altitude .......................................................................... MAINTAIN Never climb the airplane after a lightning strike, unless required by performance (climb or obstacle clearance) or operation contingencies. If any structural damage is suspected, apply EMERGENCY DESCENT procedure. Page
REVISION 7
1-02-79
Code
23 01
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AIRPLANE OPERATIONS MANUAL
All Other Airplane Systems............................................CHECK Check all airplane instruments following a panel scan sequence to ascertain that flight safety prevails. The display colors may be changed, however the display information remains valid. Apply the associated emergency/abnormal procedure if any failure arises after a lightning strike. Consider discontinuing the flight and land at the nearest suitable airport if any unsafe condition is revealed after checking systems operation.
ON GROUND OPERATIONS ON THE GROUND Approaching and landing an airplane during a thunderstorm is strongly not recommended. The human body may provide the grounding that is otherwise lacking. If you are in the cockpit, do not attempt to communicate with ground through a wire handset, and stay inside the airplane until the storm has passed. IF THE AIRPLANE HAS BEEN HIT BY LIGHTNING External safety inspection Check for holes, punctures, discoloration and de-lamination throughout the whole airframe. Verify for loose, melted or missing rivets. Check that all static dischargers are in place or in accordance with the CDL. Verify the integrity of the lights installed on tail, wing, fuselage and landing gear. Verify all antennas, ice detectors, pitot tubes, angle-of-attack vanes, TAT probes and static ports for condition. Report to maintenance personnel any detected damage or failure. Perform SECTION 05-50-01 (AMM) for detailed procedures to carry out a general inspection after a lightning strikes the airplane. Make sure that these procedures are carried out before flying the airplane again.
Page
1-02-79
Code
24 01
REVISION 7
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
PRESSURIZATION IN MANUAL MODE This section contains additional information to assist pressurization operation in manual mode. If necessary, consult AOM Section 2-14-15 - Pressurization System. Procedures are intented to supplement the procedures published in the QRH. Procedures herein are valid for dispatch with the pressurization system automatic mode inoperative (MEL item 21-30-00) or in case of loss of automatic mode in flight. For rapid loss of pressurization, refer to the RAPID CABIN DEPRESSURIZATION procedure in the QRH. GENERAL It has been observed that cabin altitude indication may vary under manual mode operation. Therefore, it is recommended to wait until cabin altitude indication stabilizes, when the manual controller should be operated as required to control cabin altitude. In manual mode, crew selection of the cabin rate and proper monitoring of cabin differential pressure is required to maintain appropriate cabin pressurization. With relation to the 12 o’clock position, clockwise rotation of the controller will induce a positive cabin rate of climb, and a counter-clockwise rotation will induce a negative cabin rate of climb. The manual controller gain is very sensitive and the response time to the command may take few seconds. Avoid fast and large displacement of the controller. After making cabin rate changes, wait a few seconds for the system to stabilize and then verify if the result is the desired one. If necessary repeat the procedure until the desired result is achieved.
Page
JUNE 20, 2002
1-02-79
Code
25 01
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AIRPLANE OPERATIONS MANUAL
RECEIVING/BEFORE DOOR CLOSING Pressurization manual controller ..................................FULL UP Pressurization mode selector button .............................MANUAL Check that MAN inscription illuminates inside the button. Pack .............................................................................ONLY ONE PACK ON This setting allows one outflow valve to be fully open and reduces cabin airflow, thus avoiding uncomfortable pressure changes when the doors are closed or during engine starts. TAXI OUT/BEFORE TAKEOFF Pressurization manual controller ..................................FULL UP This setting will make the cabin altitude remain stable during taxi, independent of any variation in bleed. Just before take-off: Manual controller ..........................................................11 O’CLOCK POSITION This position will guarantee an acceptable pressurization during climb out. AFTER TAKEOFF/CLIMB Just after the initial climb: Pressurization manual controller ...................................BETWEEN 11 AND 12 O’CLOCK Keeping the manual controller within the green mark allows a null or slightly positive rate for the cabin altitude. Passing 10000 ft pressure altitude: Manual controller ..........................................................TURN CLOCKWISE Identify the resulting cabin rate. Usually a 400 to 500 ft/min will be sufficient for this situation.
Page
1-02-79
Code
26 01
JUNE 20, 2002
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
Above 10000 ft: QRH table ..................................................................... CHECK Search for the LOSS OF PRESSURIZATION INDICATION procedure in the QRH and use the table contained therein. Maintain the cabin altitude consistent with the airplane altitude specified on the table by close monitoring differential pressure and intermittent setting of the manual controller. CRUISE Once cruise level is established, or a step in the climb is desired: QRH table ..................................................................... CHECK Manual Controller.......................................................... NULL RATE Allow the cabin to climb (or descend) to the value specified on the QRH table, then set null rate. Cabin altitude and ∆P must be consistent with the table. Keeping the manual controller close to the 12 o’clock position to keep a null rate is a good position for the rest of the cruise. However, minor adjustments might be required. DESCENT Just after initiating descent: Manual controller........................................................... SLOWLY TURN COUNTER CLOCKWISE Initially, set - 400 ft/min rate, which corresponds to a position between 12 and 11 o’clock in the manual controller. During descent: Set a cabin rate that will meet the required landing altitude upon landing. Allow the cabin to descend slowly towards the desired landing altitude so that upon landing ∆P reads zero. During holding at any flight altitude: Manual controller .......................................................... SET AROUND 12 O’CLOCK POSITION Keep the manual controller close to the 12 o’clock position to keep a null rate. However, minor adjustments might be required.
Page
JUNE 20, 2002
1-02-79
Code
27 01
SUPPLEMENTARY PROCEDURES ENVIRONMENTAL
AIRPLANE OPERATIONS MANUAL
TAXI-IN On the ground: Differential pressure ......................................................ZERO Once ∆P reads zero: Manual controller ...........................................................FULL UP In this position, the outflow valve will be kept fully open, which will equalize outside and inside cabin pressure. After that, cockpit side windows and aircraft doors can be opened.
Page
1-02-79
Code
28 01
JUNE 20, 2002
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES NAVIGATION
FMZ 2000 FLIGHT MANAGEMENT SYSTEM The information contained herein supplements the information of the basic AOM Normal Procedures.
HOLDING If a Holding Pattern entering is necessary: FMS ......................................................................... AS REQUIRED The pilot must check the entry type and turn direction of holding pattern before entering it. For entry types other than the direct one, the pilot must activate the procedure holding pattern as soon as the approach procedure is retrieved from the Navigation Data Base. NOTE: The FMS normal operating procedures are contained in the Honeywell Flight Management System (FMS) Pilot's Operating Manual, Honeywell Publication Number A281146-133-00, February 1999 edition (or later revision of the manual) for the software version NZ5.2.
Page
NOVEMBER 30, 2001
1-02-80
Code
1 01
SUPPLEMENTARY PROCEDURES NAVIGATION
AIRPLANE OPERATIONS MANUAL
FMS SOURCE SELECTION Flight Plan......................................................................SELECT OR CREATE FMS Source ..................................................................SELECT The FMS can be selected as the navigation source through the FMS Selector Button located on the Display Control Panel. FMS Label .....................................................................CHECK The FMS label appears on the associated PFD and MFD. On PFD: If the FMS is the navigation source for only one side the color will be magenta, otherwise it will be amber. On MFD the label will be always magenta. For FMS coupling to the Autopilot/Flight Director: NAV Mode (Flight Guidance Controller)...................SELECT The FMS will be coupled to the Autopilot/Flight Director when is selected and valid at the on side EHSI and crew selects the NAV mode on the associated Flight Guidance Controller. Once coupled the autopilot will follow the preselected flight plan on the FMS.
APPROACH
The FMS GPS, NDB, RNAV, VOR, VOR/DME and VFR approaches may be linked into the flight plan and laterally coupled to the autopilot/Flight Director.
ILS approaches can be retrieved from the navigation data base and linked to the flight plan, but cannot be armed or activated as FMS approaches. The FMS can be used to provide navigation up to the final approach course at the point that the PFD must be changed to display raw ILS data.
Page
1-02-80
Code
2 01
JUNE 20, 2002
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES NAVIGATION
TRANSITION FROM FMS TO AUTOPILOT ILS APPROACH ILS Frequency............................................................... SELECT AS REQUIRED Radio Altitude................................................................ SELECT AS REQUIRED HDG Mode (Flight Guidance Controller) ....................... SELECT Before selection, set the desired interception course on heading bug. Navigation Source......................................................... SELECT Select the NAV source on the Display Control Panel (LOC course selected on the PFD). Autopilot/Flight Director................................................. AS REQUIRED When cleared for Approach: APR Mode (Flight Guidance Controller) .................. SELECT ARC DME APPROACH USING FMS Pilot Not-flying ............................................................... CHECK DME During Arc DME approach using FMS the pilot not-flying must check DME Raw Data. MISSED APPROACH Thrust Levers ................................................................ MAX Go-Around Button ......................................................... PRESS Verify that airplane rotates to 10° nose up wings level (Pitch Mode) and changes to Speed Hold Mode after 20 seconds. Flaps ............................................................................. 9° NAV Mode (Flight Guidance Controller)........................ SELECT Reselecting the NAV mode the airplane will regain the lateral guidance from the FMS to fly the missed approach legs to the missed holding point and to enter holding, as required. With positive rate of climb: Landing Gear ........................................................... UP Airspeed................................................................... APPROACH CLIMB SPEED OR ABOVE
Page
REVISION 6
1-02-80
Code
3 01
SUPPLEMENTARY PROCEDURES NAVIGATION
AIRPLANE OPERATIONS MANUAL
RVSM OPERATION The RVSM operation reduces the EMB-135BJ minimum vertical separation from 2000 ft to 1000 ft between FL 290 and FL 390. Airworthiness approval alone does not authorize flight into airspace for which an RVSM operational approval is required by an ICAO Regional Navigation Agreement.
LIMITATIONS MINIMUM EQUIPMENT REQUIRED During RVSM operation it is necessary that the following equipment and instruments be in proper operating condition: − 2 Primary Altitude Measurement Systems; − 1 Autopilot with Altitude Hold Mode operative; − 1 Altitude Alerter; − 1 Transponder. NOTE: - An operating transponder may not be required for entry into all designated RVSM airspace. The operator should determine the requirement for an operational transponder in each RVSM area where operations are intended. The operator should also determine the transponder requirements for transition areas next to RVSM airspace. - Should any of the required equipment fail prior to the aircraft entering RVSM airspace, the pilot should request a new clearance to avoid entering this airspace.
Page
1-02-80
Code
4 01
ORIGINAL
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES NAVIGATION
EMERGENCY AND ABNORMAL PROCEDURES The procedures presented in the basic AOM Emergency/Abnormal Procedures remain unchanged, except as amended herein. − In case of emergency or abnormal situation or contingencies (equipment failures, weather, etc.) which affect the ability to maintain the cleared flight level, notify ATC and co-ordinate an action plan that is appropriate to the airspace concerned; − Notify ATC when encountering greater than moderate turbulence; − If unable to notify ATC and obtain an ATC clearance prior to deviating from the cleared flight level, follow any established contingency procedures and obtain ATC clearance as soon as possible.
NORMAL PROCEDURES The procedures presented in the basic AOM Normal Procedures remain unchanged, except as amended herein. EXTERNAL SAFETY INSPECTION - NOSE SECTION Sensors, Pitot Tubes and Static Ports ........................CONDITION, NO OBSTRUCTION Particular attention should be paid to the condition of static sources and to the marked area on the fuselage skin near each primary static source. BEFORE TAKEOFF Altimeters ....................................................................SET TO THE AIRFIELD QNH Altitude Indications ......................................................CHECK NOTE: - An alternative procedure using QFE may also be used. - The maximum difference between altimeters indication should not exceed 23 m (75 ft).
Page
NOVEMBER 30, 2001
1-02-80
Code
5 01
SUPPLEMENTARY PROCEDURES NAVIGATION
AIRPLANE OPERATIONS MANUAL
CRUISE Be sure that all required equipment are in proper operating condition. Ensure that the aircraft is flown at the cleared flight level and that ATC clearances are fully understood and followed. Do not depart from cleared flight level without a positive clearance from ATC except for a contingency or emergency situation. While changing flight levels, do not overshoot or undershoot the cleared flight level by more than 45 m (150 ft). The autopilot should be operative and engaged during level cruise, except for circumstances such as the need to re-trim the aircraft or when it must be disengaged due to turbulence. AFTER LANDING In case of failure or malfunction, the following information should be recorded when appropriate: a) Primary and standby altimeter readings; b) Altitude selector setting; c) Subscale setting on altimeter; d) Flight Director used with the Autopilot to control the airplane and any differences when the other Flight Director was coupled; e) Use of air data computer selector for fault diagnosis procedure; f) The transponder selected to provide altitude information to ATC and any difference noted when an alternative transponder was selected.
Page
1-02-80
Code
6 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES ENGINE
ENGINE START WITH AIRPLANE BATTERIES AND LOW PRESSURE UNIT (LPU) This procedure may be used when operating without APU or GPU but with the batteries and a Low Pressure Unit (LPU) available for engine start. NOTE: - Before attempting to start the engines using the batteries ensure that minimum batteries voltage is 24.0 VDC. - Accomplish a BEFORE START - FIRST FLIGHT procedure as soon as the electrical source is established. - The Captain may elect to start the remaining engine using the LPU or to perform a crossbleed start. - The engines pneumatic start does not affect the electrical system or the individual loads connected to it. The voltage of the buses fed by the batteries remain steady during engine starts, with no power transients. After the first engine start and with generators on line, the normal electrical system voltage will be between 24 V and 28.5 V. - It is recommended that audio communication with the ground crew be used instead of signaling.
BEFORE START Internal and External Safety Inspections ................................................... ACCOMPLISH Parking Brake ............................................................... ON Batteries 1 & 2............................................................... AUTO Avionics Masters ........................................................... ON Batteries Voltage........................................................... CHECK Avionics Masters ........................................................... OFF Emergency Lights ......................................................... ARM Fire Detection System................................................... CHECK Crossbleed .................................................................... OPEN Packs ............................................................................ OFF Engine Bleeds ............................................................... CLOSE
Page
ORIGINAL
1-02-81
Code
1 01
SUPPLEMENTARY PROCEDURES ENGINE
AIRPLANE OPERATIONS MANUAL
CLEARED TO START Windows........................................................................CLOSED Red Beacon...................................................................ON Fuel Pump (associated engine).....................................ON Start Pressure ...............................................................AVAILABLE
START Start/Stop Selector (associated engine)........................START, THEN RUN Engine Indication ...........................................................MONITOR
Page
1-02-81
Code
2 01
REVISION 4
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES ENGINE
ENGINE START ASSISTED BY THE OPPOSITE ENGINE (CROSS START) This procedure may be used to start the second engine using the operating engine bleed as the pneumatic source. Crossbleed .................................................................... AUTO or OPEN Engine Bleed (non-operating engine) ........................... CLOSE Engine Bleed (operating engine)................................... OPEN N2 of the operating engine must be accelerated to above 80%. Start/Stop Selector ........................................................ START,THEN RUN Engine Indication........................................................... MONITOR NOTE: After the start is completed, reduce operating engine power to idle.
ENGINE START ASSISTED BY THE APU This procedure may be used to start the engine using the APU bleed as the pneumatic source. APU bleed ..................................................................... OPEN Crossbleed ................................................................... OPEN or AUTO Engine Bleeds ............................................................... CLOSED Start/Stop Selector ........................................................ START,THEN RUN Engine Indication........................................................... MONITOR NOTE: With the APU Bleed Valve open and the Crossbleed Valve in AUTO position, the Engine 1 will always be started assisted by the APU, even when the Engine 2 is running with associated Engine Bleed Valve open.
Page
NOVEMBER 30, 2001
1-02-81
Code
3 01
SUPPLEMENTARY PROCEDURES ENGINE
AIRPLANE OPERATIONS MANUAL
SINGLE ENGINE TAXI The procedures below are provided to allow operators to perform a single engine taxi. This procedure can be adopted at crowded airports, where the taxi time may be too long, leading to unnecessary fuel waste and air pollution. For single engine taxi, change or complement the normal procedures according to the following.
BEFORE START Evaluate which engine will be started based on fuel distribution on tanks, passenger boarding and baggage loading. If the airplane is operating under MEL with one engine driven generator inoperative, choose the engine which has both generators operating. NOTE: Batteries charge may be preserved by using all available generators.
AFTER START FADEC Control Knob ....................................................RESET, THEN ALTN Electric Hydraulic Pumps ..............................................AUTO Check on MFD Hydraulic Page that both hydraulic systems pressure are within green range. Air Conditioning and Pneumatic System .......................AS REQUIRED If both air conditioning packs are required, select Crossbleed to OPEN. Shed Buses ...................................................................OVRD Check all DC Buses energized and operating generators load. If required, turn off equipment not essential (galley, coffee maker, etc.). In such case, inform flight attendant that those equipment shall be off until second engine start.
TAXI Monitor wings fuel quantities to avoid excessive fuel imbalance.
Page
1-02-81
Code
4 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES ENGINE
BEFORE TAKEOFF Non Operating Engine................................................... START Crossfeed...................................................................... OFF Shed Buses................................................................... AUTO Electric Hydraulic Pumps .............................................. AUTO Air Conditioning and Pneumatic System....................... AS REQUIRED
AFTER LANDING Shed Buses................................................................... OVRD Electric Hydraulic Pumps .............................................. AUTO Air Conditioning and Pneumatic System....................... AS REQUIRED Selected Engine ............................................................ SHUTDOWN
ABNORMAL PROCEDURES If the operating engine fails, stop the airplane as soon as possible, apply Parking Brakes and turn off both hydraulic pumps and any unnecessary equipment. APU may be used to start remaining engine and return to gate. NOTE: Batteries will be discharging until APU or remaining generators are turned on.
Page
NOVEMBER 30, 2001
1-02-81
Code
5 01
SUPPLEMENTARY PROCEDURES ENGINE
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-02-81
Code
6 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY NORMAL PROCEDURES CAT II OPERATION
CAT II OPERATION The information contained herein supplements the information of the the basic AOM Normal Procedures.
AUTOPILOT COUPLED CAT II APPROACH BEFORE INTERCEPTING LOCALIZER COURSE − Perform the Descent/Approach/Before Landing checklists, as appropriate. − Perform the Radio Altimeter test. − Set the CAT II Decision Height on both Display Control Panels. − Check radio altimeter information on both PFD. − Select the same ILS frequency on both RMU. NOTE: - After test, if Radio Altimeter is checked not functioning properly the CAT ll approach must discontinued. - A minimum distance of 4 NM to the Outer Marker is recommended for interception and stabilization along the approach course. BEFORE INTERCEPTING THE GLIDE SLOPE − Monitor radio altimeter information. − Lower landing gear (one dot below GS interception) and set flaps to 22°. − Set the Landing Reference Speed (VREF 22) on AP bug (green bug). − Stabilize and maintain the Landing Reference Speed (VREF 22). − Set approach climb speed on SPD reference speed bug (cyan bug). − Be sure that Marker Beacon audio is on.
Page
SEPTEMBER 30, 2002
1-02-83
Code
1 01
SUPPLEMENTARY NORMAL PROCEDURES CAT II OPERATION
AIRPLANE OPERATIONS MANUAL
AFTER PASSING THE OUTER MARKER INBOUND − The pilot flying should maintain the Landing Reference Speed (VREF 22). − Both pilots must monitor the progress of the approach on their displays down to approximately 200 ft above the decision height. At this point the pilot not flying looks out for external visual references while the pilot flying continues to monitor his displays down to the decision height. − At 80 ft above the decision height setting the EGPWS will call out "APPROACHING MINIMUM". − At the decision height setting the EGPWS will call out "MINIMUM", and the pilot not flying will call out "LANDING" or "GO AROUND", as appropriate. − If visual contact is not made upon reaching the decision height or if any malfunction could not be promptly identified during approach, a missed approach must be immediately initiated. NOTE: The Landing Reference Speed used for ILS CAT ll approaches is the VREF 22 speed presented in the Landing Climb and Reference Speeds (Flaps 22°) chart of the applicable engine Supplement.
MISSED APPROACH GO-AROUND Procedure ..............................................ACCOMPLISH
LANDING Reaching the Decision Height with runway in sight: Autopilot ...................................................................DISENGAGE Landing.....................................................................PERFORM
Page
1-02-83
Code
2 01
SEPTEMBER 30, 2002
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES MAINTENANCE INSP BY THE FLIGHT CREW
MAINTENANCE INSPECTIONS PERFORMED BY THE FLIGHT CREW This Section contains procedures to be accomplished by the flight crew when the airplane is not at the maintenance base. In case of conflicting information between these procedures and the AFM, the AFM must prevail. For further instructions pertaining to the subjects covered herein refer to the Aircraft Maintenance Manual. NOTE: The procedures presented herein must be accomplished by the flight crew properly trained.
CMC MESSAGES CHECK ON THE MFD The purpose of this procedure is to check the MDF 1 for no maintenance messages. − − − − −
Make sure that the airplane is safe for maintenance; Energize the airplane; Make sure that the CMC system is operational and on; On the MFD select the maintenance page; Make sure that the CMC FADEC ( ) INPUT FAIL message is not shown on the MFD maintenance page; − Check if any message is displayed and report to the maintenance personnel. CAUTION: IF THE CMC MESSAGE ENG 1(2) OIL DEBRIS IS DISPLAYED, DO NOT TAKEOFF.
− Return the MFD to its normal condition.
Page
REVISION 5
1-02-86
Code
1 01
SUPPLEMENTARY PROCEDURES MAINTENANCE INSP BY THE FLIGHT CREW
AIRPLANE OPERATIONS MANUAL
ENGINE TREND DOWNLOAD To accomplish the engine trend download/analysis procedures, follow the instructions below: − Install the Personal Computer to download the engine trend data; − On the Menu bar of the DAS program, choose the option TREND & EXCEED and download Engine Trend Data; − Save the data and send it to the maintenance base.
ENGINE TREND DOWNLOAD
Page
1-02-86
Code
2 01
REVISION 5
AIRPLANE OPERATIONS MANUAL
SUPPLEMENTARY PROCEDURES MAINTENANCE INSP BY THE FLIGHT CREW
TOILET AND GALLEY OUTLET At least once a month, perform the outlet test as shown below: − With the airplane energized and the outlet green light on, press the TEST button; − The RESET button will pop out and the green light will extinguish; − Press the RESET button again. The green light will illuminate to show that the equipment is energized again.
OUTLET POWER
Page
REVISION 5
1-02-86
Code
3 01
SUPPLEMENTARY PROCEDURES MAINTENANCE INSP BY THE FLIGHT CREW
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-02-86
Code
4 01
REVISION 5
PROFILES
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
Code
1 01
Page
NORMAL PROCEDURES
1-02-95
Code
2 01
Page
NORMAL PROCEDURES
1-02-95
AIRPLANE OPERATIONS MANUAL
NOVEMBER 30, 2001
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
Code
3 01
Page
NORMAL PROCEDURES
1-02-95
Code
4 01
Page
NORMAL PROCEDURES
1-02-95
AIRPLANE OPERATIONS MANUAL
NOVEMBER 30, 2001
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
Code
5 01
Page
NORMAL PROCEDURES
1-02-95
Code
6 01
Page
NORMAL PROCEDURES
1-02-95
AIRPLANE OPERATIONS MANUAL
SEPTEMBER 30, 2002
AIRPLANE OPERATIONS MANUAL
PERFORMANCE
SECTION 1-04 PERFORMANCE TABLE OF CONTENTS Block Page Introduction .........................................................................1-04-00 .. 03 Wind and Altitude Conversion ............................................1-04-05 .. 01 Altimeter Setting to Station Pressure ..............................1-04-05 .. 03 QNH to Pressure Altitude ............................................1-04-05 .. 03 QFE to Station Pressure .............................................1-04-05 .. 04 Geometric Height to Pressure Height..........................1-04-05 .. 05 Thrust Setting Tables..........................................................1-04-10 .. 01 Takeoff (*) ...........................................................................1-04-15 .. 01 Weight and Speeds Determination Method ....................1-04-15 .. 01 Simplified Takeoff Analysis Table ...................................1-04-15 .. 03 Takeoff Speeds ...............................................................1-04-15 106 Takeoff Speeds for Balanced Performance....................1-04-15 106 Flaps Retraction Schedule ..............................................1-04-15 110 Final Segment Speed......................................................1-04-15 110 Pitch Trim Setting for Takeoff .........................................1-04-15 110 Supplementary Takeoff Information ...................................1-04-20 .. 01 Turn Analysis...................................................................1-04-20 .. 01 Operational Limitations................................................1-04-20 .. 01 Equivalent Straight Flight Path Determination.............1-04-20 .. 01 Performance Charts Presentation ...............................1-04-20 .. 04 Aircraft Classification Number.........................................1-04-20 .. 11 Takeoff Performance .....................................................1-04-20 .. 15 EMBRAER Runway Analysis Software .......................1-04-20 .. 15 The Takeoff Output Data.............................................1-04-20 .. 15 Approach (*)........................................................................1-04-25 .. 01 o Approach Climb Speed - Flaps 9 ...................................1-04-25 .. 01 Landing Climb and Reference Speeds ...........................1-04-25 .. 02 Flap Maneuvering Speed ................................................1-04-25 .. 03 Final Approach Speed.....................................................1-04-25 .. 03 Approach Climb Weight Tables ......................................1-04-25 .. 04 Landing (*) ..........................................................................1-04-30 .. 01 Unfactored Landing Distances ........................................1-04-30 .. 01 Landing Distance Correction Factor................................1-04-30 .. 05 Maximum Landing Weight - Field Length Limited...........1-04-30 .. 07 Page
REVISION 6
1-04-00
Code
1 04
PERFORMANCE
AIRPLANE OPERATIONS MANUAL
Quick Turn Around Weight ............................................. 1-04-30 ..11 Landing Performance .................................................... 1-04-30 ..31 EMBRAER Runway Analysis Software....................... 1-04-30 ..31 The Landing Output Data ........................................... 1-04-30 ..31
NOTE: Items marked with an asterisk (∗) may not be present in this manual.
Page
1-04-00
Code
2 04
REVISION 6
AIRPLANE OPERATIONS MANUAL
PERFORMANCE
INTRODUCTION This section presents takeoff, approach and landing performance information. For determination of the takeoff and landing limiting weights, the performance data as presented in the approved Airplane Flight Manual (AFM) or Runway Analysis Software must be used.
Page
JANUARY 17, 2003
1-04-00
Code
3 04
PERFORMANCE
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-04-00
Code
4 04
JANUARY 17, 2003
PERFORMANCE
AIRPLANE OPERATIONS MANUAL
WIND AND ALTITUDE CONVERSION WIND COMPONENT
EFFECTIVE HEADWIND COMPONENT - KTS
80
WIND DIRECTION RELATIVE TO RUNWAY (STRAIGHT LINES)
70 60 0°
50
10°
20° 30° 40°
40
50°
30
60°
20
70°
10
80°
0
90°
145CTA50 - OUT 01, 1996
EFFECTIVE TAILWIND COMPONENT - KTS
0
10
20
30
40
50
-10
CROSSWIND COMPONENT 60 70- KTS80 90
100°
-20
110° 120°
-30 130°
-40
140° 150°
-50 180°
170°
160°
REPORTED WIND SPEED (CURVED LINES)
-60 -70 -80
Page
NOVEMBER 30, 2001
1-04-05
Code
1 01
PERFORMANCE
AIRPLANE OPERATIONS MANUAL
USE Enter the chart with the reported wind velocity and the relative angle to the runway, to read the wind component parallel to the runway and the crosswind. EXAMPLE Given: Wind velocity ............................................................20 kt Wind direction ..........................................................60° Determine: Wind component parallel to the runway ...................10 kt Crosswind.................................................................17.5 kt
Page
1-04-05
Code
2 01
NOVEMBER 30, 2001
PERFORMANCE
AIRPLANE OPERATIONS MANUAL
ALTIMETER SETTING TO STATION PRESSURE QNH TO PRESSURE ALTITUDE QNH in Hg
hPa
28.81 to 28.91 28.92 to 29.02 29.03 to 29.12 29.13 to 29.23 29.24 to 29.34 29.35 to 29.44 29.45 to 29.55 29.56 to 29.66 29.67 to 29.76 29.77 to 29.87 29.88 to 29.97 29.98 to 30.08 30.09 to 30.19 30.20 to 30.30 30.31 to 30.41 30.42 to 30.52 30.53 to 30.63 30.64 to 30.74 30.75 to 30.85 30.86 to 30.96 30.97 to 31.07
976 to 979 980 to 983 984 to 986 987 to 990 991 to 994 995 to 997 998 to 1001 1002 to 1004 1005 to 1008 1009 to 1012 1013 to 1015 1016 to 1019 1020 to 1022 1023 to 1026 1027 to 1030 1031 to 1034 1035 to 1037 1038 to 1041 1042 to 1045 1046 to 1048 1049 to 1052
CORRECTION TO ELEVATION FOR PRES. ALT. (FT) 1000 900 800 700 600 500 400 300 200 100 0 -100 -200 -300 -400 -500 -600 -700 -800 -900 -1000
Example: Elevation = 2000 ft QNH = 29.60 in Hg Correction = 300 ft Pressure Altitude = 2300 ft
Page
NOVEMBER 30, 2001
1-04-05
Code
3 01
PERFORMANCE
AIRPLANE OPERATIONS MANUAL
QFE TO STATION PRESSURE QFE in Hg hPa 31.01 30.86 30.71 30.57 30.42 30.27 30.12 29.98 29.83 29.68 29.53 29.38 29.23 29.09 28.94 28.79 28.64 28.50 28.35 28.20 28.05 27.91 27.76 27.61 27.46 27.32 27.17 27.02 26.87 26.73 26.58 26.43 26.28 26.14 25.99 25.84 25.69
1050 1045 1040 1035 1030 1025 1020 1015 1010 1005 1000 995 990 985 980 975 970 965 960 955 950 945 940 935 930 925 920 915 910 905 900 895 890 885 880 875 870 Page
1-04-05
PRESSURE ALTITUDE (ft) -989 -856 -723 -589 -454 -319 -184 -48 89 227 364 503 641 781 921 1062 1202 1344 1486 1630 1773 1918 2062 2208 2353 2500 2647 2796 2944 3094 3243 3394 3545 3698 3850 4004 4157
QFE in Hg hPa 25.55 25.40 25.25 25.10 24.96 24.81 24.66 24.51 24.36 24.21 24.07 23.92 23.77 23.62 23.48 23.33 23.18 23.03 22.89 22.74 22.59 22.44 22.30 22.15 22.00 21.85 21.71 21.56 21.41 21.26 21.12 20.97 20.82 20.67 20.53 20.38 20.19
865 860 855 850 845 840 835 830 825 820 815 810 805 800 795 790 785 780 775 770 765 760 755 750 745 740 735 730 725 720 715 710 705 700 695 690 685
PRESSURE ALTITUDE (ft) 4313 4468 4625 4781 4939 5097 5257 5417 5579 5740 5903 6065 6230 6394 6561 6727 6895 7063 7233 7402 7574 7745 7920 8095 8269 8442 8619 8796 8975 9154 9335 9516 9699 9882 10068 10253 10439
Code
4 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
PERFORMANCE
GEOMETRIC HEIGHT TO PRESSURE HEIGHT Pressure altimeters are calibrated to indicate true altitude under International Standard Atmosphere (ISA) conditions. Any deviation from ISA will therefore result in an erroneous reading on the altimeter. In the case when the temperature is higher than ISA the true altitude will be higher than the figure indicated by the altimeter, and the true altitude will be lower when the temperature is lower than ISA. The altimeter error may be significant under conditions of extremely cold temperature (ICAO PANS-OPS Vol I 3.5.4.5.2). AERODROME TEMP. o ( C)
0 -10 -20 -30 -40 -50
AERODROME TEMP. o ( C)
0 -10 -20 -30 -40 -50
HEIGHT ABOVE THE ELEVATION OF THE ALTIMETER SETTING SOURCE (feet) 200 300 400 500 600 700 800 0 20 20 20 20 20 40 20 20 40 40 40 60 60 20 40 40 60 80 80 100 40 60 60 80 100 120 140 40 60 80 100 140 160 180 60 80 100 140 160 200 220
HEIGHT ABOVE THE ELEVATION OF THE ALTIMETER SETTING SOURCE (feet) 900 1000 1500 2000 3000 4000 5000 40 40 60 80 120 160 200 80 80 120 160 240 320 400 100 120 180 240 360 500 620 160 160 260 340 500 680 860 200 220 320 440 660 880 1100 240 280 400 540 820 110 1380
NOTE: The tables above are based on aerodrome elevation of 2000 ft; however, they can be used operationally at any aerodrome.
Page
REVISION 4
1-04-05
Code
5 01
PERFORMANCE
AIRPLANE OPERATIONS MANUAL
Example: Airport elevation.................................................................. 1500 ft Airport Temperature ........................................................... -20°C Obstacle Height above airport elevation............................. 800 ft Altimeter adjusted to airport QNH (on ground altimeter reads 1500 ft) Enter table with 800 ft and -20°C and read 100 ft. So, when the airplane reaches the obstacle geometric height, the altimeter will read 1500 + 800 + 100 = 2400 ft. Altimeters reads 2400 ft
800 ft
Elevation = 1500 ft T = -20°C Altimeters reads 1500 ft
Page
1-04-05
Code
6 01
ORIGINAL
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E
THRUST SETTING TABLES Thrust setting tables are presented for various Pressure Altitudes and Static Air Temperatures, with engine bleed closed or open, and antiicing on or off. The tables present the following data: • N1 for Takeoff (ALT T/O-1 mode). • N1 for Takeoff (T/O mode). • N1 for Takeoff (E T/O mode). • N1 for Go-Around (E T/O mode). • N1 for Maximum Continuous Thrust (CON mode). ALT T/O-1: It is an engine rating lower than the takeoff thrust, intended for engine life extension (due to lower turbine temperatures). It is also time-limited to 5 minutes. In the case of an engine failure, the FADEC will command the operating engine to T/O-1 mode. T/O: It is the normal thrust at takeoff for existing conditions of temperature and pressure altitude. This rating is time-limited to 5 minutes. In the case of an engine failure, the FADEC will command the operating engine to T/O RSV mode. E T/O: It is the maximum permissible thrust at takeoff for existing conditions of temperature and pressure altitude. This rating is timelimited to 5 minutes. In the case of an engine failure, the FADEC will command the operating engine to E T/O RSV mode. GO AROUND (E T/O): It is the maximum permissible thrust during go around. The amount of thrust is the same as for takeoff at E T/O mode, but the N1s are different because the effect of the airplane’s airspeed during go around is taken into consideration. Go-around thrust is also time-limited to 5 minutes. MAXIMUM CONTINUOUS THRUST (CON): It is the maximum permissible thrust for continuous use. Maximum Continuous Thrust is to be used whenever in the pilot’s judgment it is deemed necessary for safety reasons (1 engine inoperative, severe icing, etc).
Page
REVISION 4
1-04-10
Code
1 02
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL N1 FOR TAKEOFF (ALT T/O-1 MODE) FADEC REF A/ICE OFF AIRSPEED: 0 KCAS ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000
Static Air Temperature - °C -40
-30
-20
-10
0
10
20
30
40
50
74.6 75.1 76.1 77.0 77.9 79.0 80.0 80.5 81.0 81.4 81.8 82.2
76.1 76.7 77.7 78.6 79.6 80.6 81.7 82.2 82.7 83.1 83.6 84.0
77.7 78.3 79.2 80.2 81.2 82.3 83.4 83.9 84.4 84.8 85.3 85.7
79.2 79.8 80.8 81.8 82.8 83.9 85.0 85.5 86.0 86.5 86.9 87.4
80.7 81.3 82.3 83.3 84.3 85.5 86.6 87.1 87.6 88.1 88.6 89.0
82.2 82.8 83.8 84.8 85.9 87.0 88.2 88.7 89.2 89.7 90.2 90.6
83.6 84.3 85.3 86.3 87.4 88.5 89.7 90.2 90.8 91.0 91.2 91.3
85 85.7 86.7 87.8 88.9 89.8 90.2 89.7 89.7 89.6 89.5 89.4
86.4 87.1 88.1 88.6 88.4 88.5 88.5 88.5 88.3 88.3 88.5 -
87.3 87.5 86.9 87.1 87.3 87.6 -
Page
1-04-10
Code
2 02
REVISION 3
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL N1 FOR TAKEOFF (ALT T/O-1 MODE) FADEC REF A/ICE ON AIRSPEED: 0 KCAS
ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000
Static Air Temperature - °C -40
-35
-30
-25
-20
-15
-10
-5
0
5
10
75.7 76.3 77.2 78.1 79.1 80.1 81.1 81.6 82.1 82.5 83.0 83.4
76.5 77.1 78.0 78.9 79.9 80.9 82.0 82.5 83.0 83.4 83.8 84.3
77.3 77.9 78.8 79.7 80.7 81.8 82.9 83.3 83.8 84.3 84.7 85.2
78.1 78.7 79.6 80.6 81.6 82.6 83.7 84.2 84.7 85.2 85.6 86.0
78.9 79.5 80.4 81.4 82.4 83.5 84.5 85.0 85.5 86.0 86.5 86.9
79.6 80.3 81.2 82.2 83.2 84.3 85.4 85.9 86.4 86.9 87.3 87.7
80.4 81.0 82.0 83.0 84.0 85.1 86.2 86.7 87.2 87.7 88.1 88.6
81.2 81.8 82.8 83.8 84.8 85.9 87.0 87.5 88.0 88.5 89.0 89.4
80.7 81.3 82.3 83.3 84.3 85.5 86.6 87.1 87.6 88.1 88.6 89.0
81.4 82.1 83.1 84.1 85.1 86.2 87.4 87.9 88.4 88.9 89.4 89.8
82.2 82.8 83.8 84.8 85.9 87.0 88.1 88.7 89.2 89.4 89.3 89.2
Page
JANUARY 17, 2003
1-04-10
Code
3 02
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL N1 FOR TAKEOFF (T/O MODE) FADEC REF A/ICE OFF AIRSPEED: 0 KCAS ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000
Static Air Temperature - °C -54
-50
-45
-40
-35
-30
-25
-20
-15
-10
-5
74.8 75.5 76.5 77.5 78.5 79.5 80.4 80.9 81.4 82.0
75.5 76.1 77.2 78.2 79.2 80.2 81.1 81.7 82.2 82.7
76.4 77.0 78.0 79.1 80.1 81.1 82.0 82.6 83.1 83.6
77.2 77.8 78.9 80.0 81.0 82.0 82.9 83.5 84.0 84.6
78.0 78.7 79.7 80.8 81.8 82.8 83.8 84.4 84.9 85.5
78.8 79.5 80.6 81.7 82.7 83.7 84.7 85.2 85.8 86.3
79.6 80.3 81.4 82.5 83.5 84.6 85.6 86.1 86.7 87.2
80.4 81.1 82.2 83.3 84.4 85.4 86.4 87.0 87.5 88.1
81.2 81.9 83.0 84.1 85.2 86.2 87.3 87.8 88.4 89.0
82.0 82.7 83.8 84.9 86.0 87.1 88.1 88.7 89.2 89.8
82.8 83.5 84.6 85.7 86.8 87.9 88.9 89.5 90.1 90.7
Pressure Altitude
Static Air Temperature - °C
(ft)
-1000 0 1000 2000 3000 4000 5000 6000 7000 8000
0
5
10
15
20
25
30
35
40
45
50
83.6 84.2 85.4 86.5 87.6 88.7 89.8 90.3 90.9 91.5
84.3 85.0 86.2 87.3 88.4 89.5 90.6 91.2 91.7 92.4
85.1 85.8 86.9 88.1 89.2 90.3 91.4 92.0 92.6 93.2
85.8 86.5 87.7 88.9 90.0 91.1 92.2 92.8 93.4 94.0
86.6 87.3 88.4 89.7 90.8 91.9 93.0 93.6 94.2 94.5
87.3 88.0 89.2 90.4 91.6 92.7 93.8 94.0 94.2 94.4
88.0 88.8 90.0 91.2 92.3 93.2 93.7 93.2 93.2 93.1
88.8 89.5 90.7 91.9 92.7 93.1 92.7 92.6 92.4 92.3
89.5 90.2 91.4 92.0 91.8 91.8 91.9 91.7 91.6 91.6
90.2 90.9 91.4 91.0 91.0 91.0 91.0 91.2 91.4 -
90.3 90.8 90.1 90.1 90.4 90.7 -
Page
1-04-10
Code
4 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL N1 FOR TAKEOFF (T/O MODE) FADEC REF A/ICE ON AIRSPEED: 0 KCAS
ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000
Static Air Temperature - °C -54
-50
-45
-40
-35
-30
-25
-20
-15
-10
-5
75.9 76.6 77.6 78.6 79.6 80.6 81.5 82.0 82.5 83.1
76.6 77.3 78.3 79.3 80.3 81.3 82.3 82.8 83.3 83.8
77.5 78.1 79.2 80.2 81.2 82.2 83.2 83.7 84.2 84.8
78.3 79.0 80.0 81.1 82.1 83.1 84.1 84.6 85.1 85.7
79.2 79.8 80.9 82.0 83.0 84.0 85.0 85.5 86.0 86.6
80.0 80.6 81.7 82.8 83.9 84.9 85.9 86.4 86.9 87.5
80.8 81.5 82.6 83.7 84.7 85.7 86.7 87.3 87.8 88.4
81.6 82.3 83.4 84.5 85.6 86.6 87.6 88.2 88.7 89.3
82.4 83.1 84.2 85.3 86.4 87.4 88.5 89.0 89.6 90.2
83.2 83.9 85.0 86.2 87.2 88.3 89.3 89.9 90.4 91.0
84.0 84.7 85.8 87.0 88.1 89.1 90.2 90.7 91.3 91.8
Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000
Static Air Temperature - °C 0
5
10
15
20
25
30
35
40
45
50
83.6 84.2 85.4 86.5 87.6 88.7 89.8 90.3 90.6 90.0
84.3 85.0 86.2 87.3 88.4 89.5 90.5 90.1 89.8 89.3
85.1 85.8 86.9 88.1 89.2 89.5 89.5 89.1 88.8 88.4
85.8 86.5 87.7 88.9 90.0 91.1 92.2 92.8 93.4 94.0
86.6 87.3 88.4 89.7 90.8 91.9 93.0 93.6 94.2 94.5
87.3 88.0 89.2 90.4 91.6 92.7 93.8 94.0 94.2 94.4
88.0 88.8 90.0 91.2 92.3 93.2 93.7 93.2 93.2 93.1
88.8 89.5 90.7 91.9 92.7 93.1 92.7 92.6 92.4 92.3
89.5 90.2 91.4 92.0 91.8 91.8 91.9 91.7 91.6 91.6
90.2 90.9 91.4 91.0 91.0 91.0 91.0 91.2 91.4 -
90.3 90.8 90.1 90.1 90.4 90.7 -
Page
JANUARY 17, 2003
1-04-10
Code
5 02
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL N1 FOR TAKEOFF (E T/O MODE) FADEC REF A/ICE OFF AIRSPEED: 0 KCAS ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000
Static Air Temperature - °C -40
-30
-20
-10
0
10
20
30
40
50
79.2 79.9 80.9 81.9 83.0 84.2 85.3 86.0 86.6 87.2 87.8 88.4
80.9 81.6 82.6 83.7 84.8 86.0 87.2 87.8 88.5 89.1 89.7 90.3
82.5 83.2 84.3 85.4 86.5 87.7 88.9 89.6 90.3 90.9 91.5 92.1
84.1 84.9 86.0 87.0 88.2 89.4 90.7 91.3 92.0 92.7 93.3 93.9
85.7 86.5 87.6 88.7 89.8 91.1 92.4 93.1 93.8 94.4 95.0 95.7
87.3 88.0 89.2 90.3 91.5 92.8 94.0 94.8 95.4 95.6 95.8 95.0
88.8 89.6 90.7 91.9 93.1 94.0 94.7 93.7 93.5 93.5 93.4 93.2
90.3 91.1 92.3 92.8 92.3 92.3 92.3 92.2 92.1 92.0 91.7 91.5
91.3 91.6 90.9 90.9 90.8 90.9 90.9 90.7 90.5 90.5 90.7 -
89.1 89.2 89.2 89.3 89.4 89.7 -
Page
1-04-10
Code
6 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL N1 FOR TAKEOFF (E T/O MODE) FADEC REF A/ICE ON AIRSPEED: 0 KCAS
ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000
Static Air Temperature - °C -40
-35
-30
-25
-20
-15
-10
-5
0
5
10
80.3 81.0 82.0 83.1 84.1 85.3 86.5 87.1 87.8 88.4 88.9 89.5
81.2 81.9 82.9 83.9 85.0 86.2 87.4 88.0 88.7 89.3 89.9 90.5
82.0 82.7 83.8 84.8 85.9 87.1 88.3 89.0 89.6 90.2 90.8 91.4
82.9 83.6 84.6 85.7 86.8 88.0 89.2 89.9 90.5 91.2 91.8 92.4
83.7 84.4 85.5 86.5 87.7 88.9 90.1 90.8 91.4 92.1 92.7 93.3
84.5 85.3 86.3 87.4 88.5 89.8 91.0 91.7 92.3 93.0 93.6 94.2
85.3 86.1 87.2 88.2 89.4 90.6 91.9 92.6 93.2 93.9 94.5 94.7
86.1 86.9 88.0 89.1 90.2 91.5 92.7 93.4 94.1 94.8 95.0 94.7
85.7 86.5 87.6 88.9 89.8 91.1 92.4 93.1 93.8 94.4 92.3 92.0
86.5 87.3 88.4 89.5 90.7 91.9 93.2 92.8 92.8 92.1 91.8 91.5
87.3 88.0 89.2 90.3 91.5 92.5 92.7 92.0 91.8 91.5 91.2 90.9
Page
JANUARY 17, 2003
1-04-10
Code
7 02
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL N1 FOR GO-AROUND (E T/O MODE) FADEC REF A/ICE OFF AIRSPEED: 100 KCAS ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000
Static Air Temperature - °C -55
-50
-45
-40
-35
-30
-25
-20
-15
-10
-5
76.5 77.2 78.1 79.1 80.1 81.1 82.2 82.8 83.3 83.9
77.3 78.0 79.0 80.0 81.0 82.1 83.1 83.7 84.3 84.9
78.2 78.9 79.9 80.9 81.9 83.0 84.0 84.6 85.2 85.8
79.1 79.8 80.8 81.7 82.8 83.9 85.0 85.6 86.2 86.8
79.9 80.6 81.6 82.6 83.7 84.8 85.9 86.5 87.1 87.7
80.7 81.5 82.5 83.5 84.5 85.7 86.8 87.4 88.0 88.6
81.6 82.3 83.3 84.3 85.4 86.5 87.6 88.3 88.9 89.5
82.4 83.1 84.2 85.2 86.3 87.4 88.5 89.2 89.8 90.4
83.2 83.9 85.0 86.0 87.1 88.3 89.4 90.0 90.7 91.3
84.0 84.7 85.8 86.8 88.0 89.1 90.3 90.9 91.5 92.2
84.8 85.5 86.6 87.7 88.8 89.9 91.1 91.8 92.4 93.1
Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000
Static Air Temperature - °C 0
5
10
15
20
25
30
35
40
45
50
85.6 86.3 87.4 88.5 89.6 90.8 92.0 92.6 93.3 93.9
86.3 87.1 88.2 89.3 90.4 91.6 92.8 93.5 94.1 94.8
87.1 87.9 89.0 90.1 91.2 92.4 93.6 94.3 95.0 95.3
87.9 88.7 89.8 90.9 92.0 93.2 94.4 94.8 95.0 94.2
88.6 89.4 90.6 91.7 92.8 94.0 94.5 93.6 93.4 93.3
89.4 90.2 91.3 92.4 93.3 93.8 92.8 92.7 92.7 92.6
90.1 91.0 92.1 92.7 92.3 92.2 92.2 92.2 92.1 92.0
90.9 91.7 92.1 91.6 91.5 91.5 91.6 91.5 91.3 91.1
91.1 91.5 90.8 90.8 90.8 90.8 90.8 90.7 90.5 90.4
90.0 90.1 90.0 90.0 90.0 90.0 90.0 90.1 90.3 -
89.1 89.1 89.1 89.2 89.4 89.7 -
Page
1-04-10
Code
8 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL N1 FOR GO-AROUND (E T/O MODE) FADEC REF A/ICE ON AIRSPEED: 100 KCAS
ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000
Static Air Temperature - °C -50
-45
-40
-35
-30
-25
-20
-15
-10
-5
0
5
10
78.5 79.2 80.1 81.1 82.1 83.2 84.2 84.8 85.4 86.0
79.3 80.0 81.0 82.0 83.0 84.1 85.2 85.8 86.4 87.0
80.2 80.9 81.9 82.9 83.9 85.0 86.1 86.7 87.3 87.9
81.0 81.8 82.8 83.8 84.8 85.9 87.0 87.6 88.2 88.9
81.9 82.6 83.6 84.6 85.7 86.8 87.9 88.5 89.2 89.8
82.7 83.5 84.5 85.5 86.6 87.7 88.8 89.4 90.1 90.7
83.6 84.3 85.3 86.4 87.5 88.6 89.7 90.3 91.0 91.6
84.4 85.1 86.2 87.2 88.3 89.5 90.6 91.2 91.9 92.5
85.2 86.0 87.0 88.1 89.2 90.3 91.5 92.1 92.7 93.4
86.0 86.8 87.8 88.9 90.0 91.2 92.3 93.0 93.6 94.3
85.6 86.3 87.4 88.7 89.6 90.8 92.0 92.6 93.3 93.3
86.3 87.1 88.2 89.3 90.4 91.6 92.8 92.9 93.0 92.3
87.1 87.9 89.0 90.1 91.2 92.4 92.8 92.1 91.9 91.6
Page
JANUARY 17, 2003
1-04-10
Code
9 02
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL N1 FOR GO-AROUND (E T/O MODE) FADEC REF A/ICE OFF AIRSPEED: 150 KCAS ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000
Static Air Temperature - °C -55
-50
-45
-40
-35
-30
-25
-20
-15
-10
-5
76.3 77.0 78.0 79.0 80.0 81.0 82.0 82.5 83.0 83.6
77.2 77.9 78.9 79.9 80.9 81.9 82.9 83.4 84.0 84.5
78.0 78.7 79.7 80.8 81.8 82.8 83.8 84.4 84.9 85.5
78.9 79.6 80.6 81.6 82.7 83.7 84.7 85.3 85.8 86.4
79.7 80.4 81.5 82.5 83.6 84.6 85.6 86.2 86.7 87.3
80.6 81.3 82.3 83.4 84.4 85.5 86.5 87.1 87.6 88.2
81.4 82.1 83.2 84.2 85.3 86.4 87.4 88.0 88.5 89.1
82.2 82.9 84.0 85.1 86.1 87.2 88.3 88.9 89.4 90.0
83.0 83.8 84.8 85.9 87.0 88.1 89.2 89.7 90.3 90.9
83.8 84.6 85.6 86.7 87.8 88.9 90.0 90.6 91.2 91.8
84.6 85.4 86.4 87.5 88.7 89.8 90.9 91.5 92.0 92.7
Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000
Static Air Temperature - °C 0
5
10
15
20
25
30
35
40
45
50
85.4 86.2 87.2 88.4 89.5 90.6 91.7 92.3 92.9 93.5
86.2 86.9 88.0 89.2 90.3 91.4 92.5 93.1 93.7 94.4
86.9 87.7 88.8 90.0 91.1 92.2 93.4 94.0 94.6 95.0
87.7 88.5 89.6 90.8 91.9 93.0 94.2 94.6 94.7 94.8
88.5 89.3 90.4 91.5 92.7 93.9 94.4 94.4 93.2 93.1
89.2 90.0 91.2 92.3 93.2 93.7 92.7 92.6 92.6 92.5
90.0 90.8 91.9 92.6 92.2 92.1 92.1 92.0 92.0 91.9
90.7 91.5 92.0 91.5 91.5 91.5 91.5 91.4 91.2 91.1
91.0 91.5 90.8 90.7 90.7 90.7 90.7 90.5 90.4 90.4
89.9 90.0 89.9 89.8 89.8 89.8 89.9 90.1 90.2 -
88.9 88.9 88.8 88.9 89.1 89.5 -
Page
1-04-10
Code
10 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL N1 FOR GO-AROUND (E T/O MODE) FADEC REF A/ICE ON AIRSPEED: 150 KCAS
ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000
Static Air Temperature - °C -50
-45
-40
-35
-30
-25
-20
-15
-10
-5
0
5
10
78.3 79.0 80.0 81.0 82.0 83.0 84.0 84.5 85.1 85.7
79.2 79.9 80.9 81.9 82.9 83.9 84.9 85.5 86.0 86.6
80.0 80.7 81.8 82.8 83.8 84.8 85.9 86.4 87.0 87.5
80.9 81.6 82.6 83.7 84.7 85.7 86.8 87.3 87.9 88.5
81.7 82.5 83.5 84.5 85.6 86.6 87.7 88.3 88.8 89.4
82.6 83.3 84.3 85.4 86.5 87.5 88.6 89.2 89.7 90.3
83.4 84.1 85.2 86.3 87.3 88.4 89.5 90.0 90.6 91.2
84.2 85.0 86.0 87.1 88.2 89.3 90.4 90.9 91.5 92.1
85.0 85.8 86.9 87.9 89.0 90.1 91.2 91.8 92.4 93.0
85.8 86.6 87.7 88.8 89.9 91.0 92.1 92.7 93.3 93.9
85.4 86.2 87.2 88.4 89.7 90.6 91.7 92.3 92.9 93.0
86.2 86.9 88.0 89.2 90.3 91.4 92.5 92.9 93.1 92.8
86.9 87.7 88.8 90.0 91.1 92.2 92.8 92.7 91.9 91.6
Page
JANUARY 17, 2003
1-04-10
Code
11 02
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL N1 FOR GO-AROUND (E T/O MODE) FADEC REF A/ICE OFF AIRSPEED: 200 KCAS ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000
Static Air Temperature - °C -55
-50
-45
-40
-35
-30
-25
-20
-15
-10
-5
75.9 76.6 77.7 78.8 79.9 80.8 81.8 82.2 82.7 83.2
76.8 77.5 78.6 79.7 80.8 81.7 82.7 83.2 83.7 84.2
77.7 78.3 79.5 80.6 81.7 82.6 83.6 84.1 84.6 85.1
78.5 79.2 80.3 81.5 82.6 83.5 84.5 85.0 85.5 86.1
79.3 80.0 81.2 82.3 83.4 84.4 85.4 85.9 86.4 87.0
80.2 80.9 82.0 83.2 84.3 85.3 86.3 86.8 87.3 87.9
81.0 81.7 82.9 84.1 85.2 86.2 87.2 87.7 88.2 88.8
81.8 82.5 83.7 84.9 86.0 87.1 88.1 88.6 89.1 89.7
82.6 83.3 84.5 85.7 86.9 87.9 88.9 89.5 90.0 90.5
83.4 84.1 85.3 86.6 87.7 88.8 89.8 90.3 90.8 91.4
84.2 84.9 86.1 87.4 88.5 89.6 90.6 91.2 91.7 92.3
Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000
Static Air Temperature - °C 0
5
10
15
20
25
30
35
40
45
50
85.0 85.7 86.9 88.2 89.4 90.4 91.5 92.0 92.6 93.1
85.7 86.5 87.7 89.0 90.2 91.2 92.3 92.9 93.4 94.0
86.5 87.2 88.5 89.8 91.0 92.1 93.1 93.7 94.2 94.8
87.3 88.0 89.3 90.6 91.8 92.9 94.0 94.5 94.7 94.7
88.0 88.8 90.1 91.4 92.6 93.7 94.1 94.3 93.2 93.0
88.8 89.5 90.8 92.1 93.1 93.6 92.8 92.6 92.5 92.4
89.5 90.3 91.6 92.5 92.1 92.1 92.1 92.0 91.9 91.8
90.2 91.0 91.8 91.4 91.4 91.4 91.4 91.3 91.2 91.0
90.7 91.2 90.6 90.6 90.6 90.6 90.6 90.5 90.4 90.4
89.7 89.8 89.6 89.6 89.6 89.6 89.7 89.9 90.2 -
88.5 88.5 88.4 88.5 88.8 89.2 -
Page
1-04-10
Code
12 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL N1 FOR GO-AROUND (E T/O MODE) FADEC REF A/ICE ON AIRSPEED: 200 KCAS
ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000
Static Air Temperature - °C -50
-45
-40
-35
-30
-25
-20
-15
-10
-5
0
5
10
77.9 78.6 79.7 80.8 81.9 82.9 83.8 84.3 84.8 85.3
78.8 79.5 80.6 81.7 82.8 83.8 84.8 85.2 85.7 86.3
79.6 80.3 81.5 82.6 83.7 84.7 85.7 86.2 86.7 87.2
80.5 81.2 82.3 83.5 84.6 85.6 86.6 87.1 87.6 88.1
81.3 82.0 83.2 84.4 85.5 86.5 87.5 88.0 88.5 89.1
82.2 82.9 84.0 85.2 86.4 87.4 88.4 88.9 89.4 90.0
83.0 83.7 84.9 86.1 87.2 88.2 89.3 89.8 90.3 90.9
83.8 84.5 85.7 86.9 88.1 89.1 90.2 90.7 91.2 91.8
84.6 85.3 86.6 87.8 88.9 90.0 91.0 91.6 92.1 92.6
85.4 86.1 87.4 88.6 89.8 90.8 91.9 92.4 92.9 93.5
85.0 85.7 86.9 88.2 89.7 90.7 91.5 92.0 92.6 93.1
85.7 86.5 87.7 89.0 90.2 91.2 92.3 92.9 92.9 92.9
86.5 87.2 88.5 89.8 91.0 92.1 92.7 92.8 92.0 91.7
Page
JANUARY 17, 2003
1-04-10
Code
13 02
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL
N1 FOR MAXIMUM CONTINUOUS MODE (CON MODE) FADEC REF A/ICE OFF AIRSPEED: 100 KCAS ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 2000 4000 6000 8000 10000 12000 14000 16000 18000 20000 22000 24000 26000 28000 30000 32000 34000 36000 37000
Static Air Temperature - °C -55
-50
-45
-40
-35
-30
-25
-20
-15
-10
-5
74.0 74.5 76.4 78.4 79.8 80.7 81.7 82.7 83.9 85.0 86.1 87.9 88.0 88.2 88.5 88.7 89.6 90.5 91.4 92.3 92.3
74.8 75.3 77.3 79.3 80.7 81.6 82.6 83.7 84.8 85.9 87.1 88.9 89.0 89.2 89.5 89.8 90.6 91.6 92.4 93.3 93.3
75.6 76.2 78.2 80.2 81.6 82.5 83.5 84.6 85.8 86.9 88.1 89.9 90.0 90.2 90.5 90.8 91.7 92.6 93.5 94.0 94.2
76.5 77.0 79.0 81.1 82.5 83.4 84.4 85.5 86.7 87.8 89.1 90.9 91.0 91.2 91.5 91.7 92.7 93.6 94.1 93.7 94.0
77.3 77.8 79.9 81.9 83.4 84.3 85.3 86.4 87.6 88.8 90.0 91.8 92.0 92.2 92.4 92.7 93.6 94.2 94.0 93.7 94.0
78.1 78.6 80.7 82.8 84.3 85.2 86.2 87.3 88.5 89.7 91.0 92.8 92.9 93.1 93.4 93.7 94.4 94.1 93.3 92.8 93.2
78.9 79.4 81.5 83.6 85.1 86.1 87.1 88.2 89.4 90.6 91.9 93.7 93.9 94.1 94.4 94.4 93.8 93.2 92.7 92.2 92.5
79.7 80.2 82.3 84.5 86.0 86.9 88.0 89.1 90.3 91.5 92.8 94.7 94.8 95.0 94.9 93.7 93.1 92.6 92.0 91.3 91.5
80.5 81.0 83.2 85.3 86.8 87.8 88.8 90.0 91.2 92.4 93.7 95.6 95.8 95.5 94.3 93.0 92.4 91.8 91.1 90.6 90.8
81.2 81.8 84.0 86.1 87.7 88.6 89.7 90.8 92.1 93.3 94.6 96.1 95.7 94.7 93.2 92.2 91.7 91.0 90.7 -
82.0 82.6 84.7 86.9 88.5 89.5 90.5 91.7 93.0 94.2 95.5 95.3 94.4 93.4 92.3 91.5 90.9 90.7 -
Page
1-04-10
Code
14 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL
N1 FOR MAXIMUM CONTINUOUS MODE (CON MODE) FADEC REF A/ICE OFF AIRSPEED: 100 KCAS ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 2000 4000 6000 8000 10000 12000 14000 16000 18000 20000 22000 24000 26000 28000 30000 32000 34000 36000 37000
Static Air Temperature - °C 0
5
10
15
20
25
30
35
40
45
50
82.8 83.3 85.5 87.8 89.3 90.3 91.4 92.6 93.8 95.0 95.4 94.0 93.0 92.2 91.4 90.8 -
83.5 84.1 86.3 88.6 90.1 91.1 92.2 93.4 94.3 94.8 93.3 92.6 92.0 91.2 90.8 -
84.3 84.9 87.1 89.3 90.9 91.9 93.0 93.9 93.2 92.7 92.1 91.8 91.1 90.7 -
85.0 85.6 87.9 90.1 91.7 92.7 93.4 92.7 92.3 91.8 91.4 91.1 90.8 -
85.7 86.3 88.6 90.9 92.5 92.8 92.2 91.9 91.4 91.0 90.7 -
86.5 87.1 89.4 91.7 92.6 91.7 91.5 91.0 90.6 90.5 -
87.2 87.8 90.1 92.0 91.3 91.0 90.5 90.1 90.2 -
87.9 88.5 90.8 90.7 90.4 90.1 89.6 89.8 -
88.6 89.2 90.9 89.9 89.6 89.3 -
89.3 89.6 89.4 89.1 89.1 -
89.4 88.8 88.6 88.8 -
Page
JANUARY 17, 2003
1-04-10
Code
15 02
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL
N1 FOR MAXIMUM CONTINUOUS MODE (CON MODE) FADEC REF A/ICE ON AIRSPEED: 100 KCAS ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 2000 4000 6000 8000 10000 12000 14000 16000 18000 20000 22000 24000 26000 28000 30000 32000 34000 36000 37000
Static Air Temperature - °C -50
-45
-40
-35
-30
-25
-20
-15
-10
-5
0
5
10
75.9 76.4 78.4 80.4 81.9 82.7 83.7 84.8 85.9 87.1 88.2 90.0 90.1 90.0 90.6 90.9 89.2 86.5 87.1 87.4 87.0
76.8 77.3 79.3 81.3 82.8 83.6 84.6 85.7 86.9 88.0 89.2 90.8 90.4 88.9 90.7 90.9 87.3 85.5 85.8 85.5 85.4
77.6 78.1 80.2 82.2 83.7 84.6 85.6 86.7 87.8 89.0 90.2 90.3 89.4 87.8 88.4 88.5 86.5 85.0 85.0 84.4 84.5
78.4 79.0 81.0 83.1 84.6 85.5 86.5 87.6 88.8 89.9 91.2 89.8 88.6 86.8 87.3 87.3 85.6 84.5 84.1 83.4 83.6
79.3 79.8 81.9 84.0 85.4 86.3 87.4 88.5 89.7 90.9 91.2 89.3 87.7 86.0 86.4 86.0 84.7 84.0 83.4 82.7 83.0
80.1 80.6 82.7 84.8 86.3 87.2 88.3 89.4 90.6 91.5 89.4 88.7 87.1 85.6 85.6 84.7 83.8 83.4 82.7 82.1 82.3
80.9 81.4 83.5 85.7 87.2 88.1 89.2 90.3 91.5 91.2 88.4 88.0 86.5 85.1 84.6 83.5 83.2 82.7 82.1 81.4 81.4
81.7 82.2 84.4 86.5 88.0 89.0 90.0 91.2 91.5 89.1 88.0 87.2 85.8 84.6 83.8 83.1 82.7 82.1 81.5 80.9 80.7
82.4 83.0 85.2 87.3 88.9 89.8 90.9 91.3 89.5 88.6 87.6 86.4 85.1 84.2 83.4 82.7 82.2 81.7 81.2 -
83.2 83.8 86.0 88.2 89.7 90.7 90.9 89.4 88.9 88.0 87.1 85.5 84.6 83.7 82.9 82.3 81.8 81.5 -
82.8 83.3 85.5 88.1 89.7 90.4 88.2 87.5 86.9 86.2 85.3 83.8 82.9 81.9 81.1 80.8 -
83.5 84.1 86.3 88.6 89.0 88.7 87.4 86.8 86.2 85.4 84.1 83.2 82.1 81.1 80.7 -
84.3 84.9 87.1 88.3 88.1 87.7 86.7 86.0 85.2 84.1 83.0 82.4 81.3 80.7 -
Page
1-04-10
Code
16 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL
N1 FOR MAXIMUM CONTINUOUS MODE (CON MODE) FADEC REF A/ICE OFF AIRSPEED: 150 KCAS ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 2000 4000 6000 8000 10000 12000 14000 16000 18000 20000 22000 24000 26000 28000 30000 32000 34000 36000 37000
Static Air Temperature - °C -55
-50
-45
-40
-35
-30
-25
-20
-15
-10
-5
73.9 74.5 76.4 78.5 79.9 80.6 81.5 82.5 83.6 84.6 85.9 87.6 88.2 88.9 88.9 88.9 90.0 91.2 92.2 93.3 93.1
74.7 75.3 77.3 79.3 80.8 81.6 82.5 83.5 84.6 85.6 86.8 88.6 89.2 89.9 89.9 89.9 91.0 92.2 93.3 94.4 94.2
75.6 76.2 78.2 80.2 81.7 82.5 83.4 84.4 85.5 86.5 87.8 89.6 90.2 90.9 91.0 90.9 92.0 93.2 94.3 94.7 94.8
76.4 77.0 79.0 81.1 82.6 83.4 84.3 85.3 86.4 87.5 88.8 90.6 91.2 91.9 91.9 91.9 93.0 94.2 94.5 94.5 94.6
77.2 77.8 79.9 82.0 83.4 84.3 85.2 86.2 87.3 88.4 89.7 91.6 92.2 92.9 92.9 92.9 94.0 94.3 93.8 93.4 93.7
78.0 78.6 80.7 82.8 84.3 85.1 86.1 87.1 88.3 89.3 90.6 92.5 93.1 93.9 93.9 93.9 94.4 93.7 93.3 92.8 93.2
78.8 79.4 81.5 83.7 85.2 86.0 87.0 88.0 89.2 90.3 91.6 93.5 94.1 94.9 94.9 94.3 93.7 93.2 92.7 92.1 92.4
79.6 80.2 82.3 84.5 86.0 86.9 87.8 88.9 90.1 91.2 92.5 94.4 95.0 95.8 95.2 93.7 93.1 92.6 91.9 91.1 91.3
80.4 81.0 83.1 85.3 86.9 87.7 88.7 89.8 90.9 92.1 93.4 95.3 96.0 95.9 94.3 93.0 92.4 91.7 90.9 90.4 90.5
81.2 81.8 84.0 86.2 87.7 88.6 89.5 90.6 91.8 92.9 94.3 96.0 95.9 94.8 93.2 92.2 91.6 90.7 90.4 -
81.9 82.6 84.7 87.0 88.5 89.4 90.4 91.5 92.7 93.8 95.2 95.8 94.3 93.4 92.3 91.4 90.7 90.4 -
Page
JANUARY 17, 2003
1-04-10
Code
17 02
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL
N1 FOR MAXIMUM CONTINUOUS MODE (CON MODE) FADEC REF A/ICE OFF AIRSPEED: 150 KCAS ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 2000 4000 6000 8000 10000 12000 14000 16000 18000 20000 22000 24000 26000 28000 30000 32000 34000 36000 37000
Static Air Temperature - °C 0
5
10
15
20
25
30
35
40
45
50
82.7 83.3 85.5 87.8 89.4 90.2 91.2 92.3 93.5 94.7 95.2 93.7 92.9 92.3 91.4 90.7 -
83.5 84.1 86.3 88.6 90.2 91.1 92.1 93.2 94.0 94.5 93.1 92.4 92.0 91.4 90.8 -
84.2 84.9 87.1 89.4 91.0 91.9 92.9 93.6 93.0 92.6 92.1 91.7 91.2 91.0 -
84.9 85.6 87.8 90.2 91.8 92.7 93.3 92.5 92.2 91.7 91.3 91.0 91.0 -
85.7 86.3 88.6 90.9 92.6 92.8 92.1 91.8 91.4 90.9 90.6 -
86.4 87.1 89.4 91.7 92.5 91.7 91.4 91.0 90.5 90.4 -
87.1 87.8 90.1 91.9 91.2 90.9 90.5 90.3 90.1 -
87.8 88.5 90.8 90.7 90.4 90.1 89.6 89.8 -
88.5 89.2 90.8 89.9 89.6 89.4 -
89.3 89.6 89.4 89.2 89.1 -
89.4 88.7 88.5 88.8 -
Page
1-04-10
Code
18 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL
N1 FOR MAXIMUM CONTINUOUS MODE (CON MODE) FADEC REF A/ICE ON AIRSPEED: 150 KCAS ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 2000 4000 6000 8000 10000 12000 14000 16000 18000 20000 22000 24000 26000 28000 30000 32000 34000 36000 37000
Static Air Temperature - °C -50
-45
-40
-35
-30
-25
-20
-15
-10
-5
0
5
10
75.9 76.4 78.4 80.5 81.9 82.7 83.6 84.6 85.7 86.7 88.0 89.7 90.3 90.5 90.7 90.5 88.8 87.6 87.6 86.7 86.7
76.7 77.3 79.3 81.4 82.8 83.6 84.5 85.5 86.6 87.7 88.9 90.7 91.4 89.4 89.5 88.8 87.2 86.3 85.8 84.3 84.6
77.5 78.1 80.2 82.3 83.7 84.5 85.4 86.5 87.6 88.6 89.9 91.7 91.3 88.6 88.4 87.6 86.4 85.6 84.7 82.9 83.4
78.4 79.0 81.0 83.1 84.6 85.4 86.3 87.4 88.5 89.6 90.9 92.1 89.7 87.6 87.4 86.7 85.6 84.8 83.5 81.9 82.5
79.2 79.8 81.9 84.0 85.5 86.3 87.2 88.3 89.4 90.5 91.5 90.9 88.8 86.9 86.6 85.7 84.7 84.0 82.9 81.9 82.4
80.0 80.6 82.7 84.9 86.4 87.2 88.1 89.2 90.3 91.4 91.3 90.0 88.0 86.3 85.7 84.6 83.8 83.5 82.7 81.7 82.1
80.8 81.4 83.5 85.7 87.2 88.1 89.0 90.1 91.2 91.6 88.7 89.0 87.2 85.7 84.8 83.6 83.5 83.2 82.3 81.1 81.3
81.6 82.2 84.4 86.5 88.1 88.9 89.9 91.0 91.3 89.0 88.3 88.0 86.3 85.0 84.1 83.5 83.2 82.6 81.6 80.6 80.8
82.4 83.0 85.2 87.4 88.9 89.8 90.8 90.9 89.3 88.5 87.8 86.9 85.5 84.5 83.8 83.3 82.7 82.0 81.2 -
83.2 83.8 86.0 88.2 89.8 90.6 90.8 89.2 88.7 88.1 87.3 85.8 84.9 84.2 83.4 82.7 82.0 81.7 -
82.7 83.3 85.5 87.8 89.7 90.5 88.1 87.4 86.9 86.3 85.5 84.0 83.2 82.4 81.6 81.0 -
83.5 84.1 86.3 88.6 88.9 88.5 87.5 86.8 86.3 85.6 84.4 83.4 82.5 81.7 81.1 -
84.2 84.9 87.1 88.8 88.1 87.6 86.8 86.2 85.4 84.4 83.3 82.5 81.7 81.3 -
Page
JANUARY 17, 2003
1-04-10
Code
19 02
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL
N1 FOR MAXIMUM CONTINUOUS MODE (CON MODE) FADEC REF A/ICE OFF AIRSPEED: 200 KCAS ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 2000 4000 6000 8000 10000 12000 14000 16000 18000 20000 22000 24000 26000 28000 30000 32000 34000 36000 37000
Static Air Temperature - °C -55
-50
-45
-40
-35
-30
-25
-20
-15
-10
-5
73.7 74.3 76.4 78.5 79.9 80.7 81.5 82.4 83.3 84.3 85.3 86.8 88.0 89.4 89.4 89.1 90.3 91.8 92.1 92.3 92.3
74.5 75.2 77.3 79.4 80.8 81.6 82.4 83.3 84.3 85.2 86.3 87.8 89.0 90.4 90.4 90.1 91.4 92.9 93.1 93.3 93.3
75.4 76.0 78.1 80.3 81.7 82.5 83.3 84.2 85.2 86.2 87.2 88.8 90.0 91.4 91.4 91.1 92.4 93.9 94.2 93.9 94.1
76.2 76.9 79.0 81.2 82.6 83.4 84.2 85.2 86.1 87.1 88.2 89.7 91.0 92.4 92.4 92.1 93.4 94.5 94.3 93.4 93.7
77.0 77.7 79.8 82.0 83.5 84.3 85.1 86.1 87.1 88.0 89.1 90.7 91.9 93.4 93.4 93.1 94.4 94.0 93.5 92.9 93.1
77.8 78.5 80.7 82.9 84.4 85.2 86.0 87.0 88.0 89.0 90.0 91.7 92.9 94.4 94.4 94.1 94.4 93.5 93.0 92.2 92.4
78.6 79.3 81.5 83.7 85.3 86.1 86.9 87.9 88.9 89.9 91.0 92.6 93.1 95.4 95.3 94.3 93.4 92.9 92.3 91.4 91.6
79.4 80.1 82.3 84.6 86.1 86.9 87.8 88.7 89.8 90.8 91.9 93.5 94.8 96.3 95.3 93.4 92.9 92.3 91.5 90.4 90.6
80.2 80.9 83.1 85.4 87.0 87.8 88.6 89.6 90.6 91.7 92.8 94.4 95.7 96.1 94.0 92.8 92.3 91.4 90.5 89.7 89.9
80.9 81.7 83.9 86.2 87.8 88.6 89.5 90.5 91.5 92.5 93.7 95.3 94.9 94.4 93.1 92.2 91.4 90.4 89.9 -
81.7 82.4 84.7 87.0 88.6 89.5 90.3 91.3 92.4 93.4 94.5 95.3 93.8 93.1 92.2 91.3 90.4 90.1 -
Page
1-04-10
Code
20 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL
N1 FOR MAXIMUM CONTINUOUS MODE (CON MODE) FADEC REF A/ICE OFF AIRSPEED: 200 KCAS ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 2000 4000 6000 8000 10000 12000 14000 16000 18000 20000 22000 24000 26000 28000 30000 32000 34000 36000 37000
Static Air Temperature - °C 0
5
10
15
20
25
30
35
40
45
50
82.5 83.2 85.5 87.8 89.4 90.3 91.2 92.2 93.2 94.3 94.4 93.3 92.7 92.2 91.4 90.4 -
83.2 84.0 86.3 88.6 90.3 91.1 92.0 93.0 93.8 94.1 92.9 92.3 91.9 91.5 90.8 -
84.0 84.7 87.0 89.4 91.1 91.9 92.8 93.5 93.5 92.5 92.0 91.5 91.1 91.1 -
84.7 85.4 87.8 90.2 91.9 92.7 93.2 92.5 92.1 91.7 91.2 90.8 90.9 -
85.4 86.2 88.6 91.0 92.7 93.0 92.1 91.7 91.3 90.9 90.5 -
86.2 86.9 89.3 91.8 92.7 91.7 91.3 90.9 90.5 90.3 -
86.9 87.6 90.1 92.0 91.2 90.9 90.5 90.1 90.1 -
87.6 88.4 90.8 90.7 90.4 90.1 89.7 89.9 -
88.3 89.1 90.8 89.9 89.7 89.5 -
89.0 89.6 89.3 89.2 89.2 -
89.2 89.4 88.4 88.9 -
Page
JANUARY 17, 2003
1-04-10
Code
21 02
PERFORMANCE EMB-135BJ A1E
AIRPLANE OPERATIONS MANUAL
N1 FOR MAXIMUM CONTINUOUS MODE (CON MODE) FADEC REF A/ICE ON AIRSPEED: 200 KCAS ROLLS ROYCE AE3007A1E ENGINES
Pressure Altitude (ft) -1000 0 2000 4000 6000 8000 10000 12000 14000 16000 18000 20000 22000 24000 26000 28000 30000 32000 34000 36000 37000
Static Air Temperature - °C -50
-45
-40
-35
-30
-25
-20
-15
-10
-5
0
5
10
75.7 76.3 78.4 80.5 82.0 82.7 83.5 84.4 85.4 86.3 87.4 88.9 90.1 91.6 91.1 89.7 88.9 88.1 86.5 85.6 85.9
76.5 77.2 79.3 81.4 82.9 83.7 84.5 85.4 86.3 87.3 88.4 89.9 91.1 91.8 90.0 87.9 87.2 86.4 85.3 84.6 84.9
77.3 78.0 80.1 82.3 83.8 84.6 85.4 86.3 87.3 88.3 89.3 90.9 92.1 90.6 89.1 86.9 86.4 85.7 84.6 84.0 84.3
78.2 78.8 81.0 83.2 84.7 85.5 86.3 87.2 88.2 89.2 90.3 91.9 91.9 89.8 88.1 86.2 85.7 84.9 83.9 83.5 83.8
79.0 79.7 81.8 84.0 85.6 86.4 87.2 88.1 89.1 90.1 91.2 92.1 89.9 88.8 87.2 85.5 84.9 84.0 83.6 83.4 83.5
79.8 80.5 82.7 84.9 86.4 87.3 88.1 89.0 90.1 91.1 91.1 90.2 88.9 87.8 86.3 84.8 84.0 83.8 83.5 83.0 83.1
80.6 81.3 83.5 85.8 87.3 88.1 89.0 89.9 91.0 91.0 88.5 89.2 87.9 86.8 85.3 84.0 83.9 83.7 83.1 82.2 82.3
81.4 82.1 84.3 86.6 88.2 89.0 89.8 90.8 91.0 88.8 88.2 88.2 86.9 85.7 84.5 84.0 83.8 83.1 82.2 81.6 81.7
82.2 82.9 85.1 87.4 89.0 89.9 90.7 90.8 89.2 88.5 87.8 87.2 85.9 84.9 84.3 83.9 83.0 82.3 81.7 -
82.9 83.7 85.9 88.3 89.8 90.7 90.5 89.2 88.7 88.1 87.5 86.1 85.2 84.4 83.8 82.9 82.0 82.0 -
82.5 83.2 85.5 87.8 89.8 90.4 88.1 87.5 87.0 86.5 85.7 84.2 83.3 82.5 81.8 80.9 -
83.2 84.0 86.3 88.6 88.8 88.4 87.6 87.0 86.5 85.8 84.6 83.5 82.4 81.9 81.2 -
84.0 84.7 87.0 88.8 88.1 87.7 87.0 86.5 85.6 84.6 83.4 82.3 81.4 81.5 -
Page
1-04-10
Code
22 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E FAA
TAKEOFF TAKEOFF ANALYSIS WEIGHTS AND SPEEDS DETERMINATION METHOD 1) Using the Simplified Takeoff Analysis Tables (AOM 1-04-15 pages 04 to 105) enter Airport Pressure Altitude, Runway Length and Temperature, according to aircraft configuration (Thrust Setting and Anti-Ice On or Off), and obtain the Maximum Takeoff Weight and associated V1; 2) Determine Actual Takeoff Weight. - If Actual Takeoff Weight is equal to the Maximum Takeoff Weight, use VR and V2 from Simplified Takeoff Analysis Tables. - If Actual Takeoff Weight is lower than the Maximum Takeoff Weight, get VR and V2 associated to Actual Weight and Thrust Setting from VR / V2 Speeds Tables (AOM 1-04-15 pages 107 and 108): - If V1 is lower than VR, use this V1. - If V1 is greater than VR, set V1 = VR. NOTE: The Simplified Takeoff Analysis Tables do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
1 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-04-15
Code
2 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E FAA
SIMPLIFIED TAKEOFF ANALYSIS TABLES Simplified Takeoff Analysis tables are presented for a set of pressure altitudes, temperatures and runway lengths for the conditions below: • Dry runway; • Zero wind; • Zero slope; • No clearway; • No stopway; • Obstacles are not considered; • Anti ice-off and Anti ice-on. Following limitation factors were considered in the calculation of these tables: • Field length; • Climb; • Brake energy. Limitation codes: • R - Runway Length; • W - WAT (Climb); • B - Brake; • S - Structural.
Page
JANUARY 17, 2003
1-04-15
Code
3 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: Sea Level Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
41240 R
43772 R
47169 R
49604 S
49604 S
49604 S
49604 S
113/119/128 117/123/131 123/128/136 127/132/139 127/132/139 127/132/139 127/132/139
4
41003 R
43532 R
46874 R
49424 R
49604 S
49604 S
49604 S
112/119/128 117/123/131 123/128/135 127/132/139 127/132/139 127/132/139 127/132/139
8
40770 R
43291 R
46579 R
49115 R
49604 S
49604 S
49604 S
112/119/127 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139 127/132/139
12
40545 R
43055 R
46287 R
48815 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 122/127/135 126/131/138 127/132/139 127/132/139 127/132/139
16
40329 R
42824 R
45865 R
48528 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/127/134 125/130/138 127/132/139 127/132/139 127/132/139
20
40125 R
42603 R
45469 R
48238 R
49604 S
49604 S
49604 S
111/118/126 115/122/130 120/126/134 125/130/137 127/132/139 127/132/139 127/132/139
24
39921 R
42379 R
45077 R
47943 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 120/125/133 124/130/137 127/132/139 127/132/139 127/132/139
28
39722 R
42156 R
44695 R
47651 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 119/125/133 124/129/136 127/132/139 127/132/139 127/132/139
32
39263 R
41937 R
44327 R
47363 R
49604 S
49604 S
49604 S
109/116/125 114/121/129 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139
36
38739 R
41717 R
44014 R
47084 R
49400 R
49604 S
49604 S
108/115/124 114/120/129 118/124/132 123/128/136 127/132/139 127/132/139 127/132/139
40
38200 R
41498 R
43782 R
46805 R
49123 R
49604 S
49604 S
107/114/124 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
44
37556 R
41247 R
43511 R
46481 R
48805 R
49604 S
49604 S
105/113/123 113/119/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
4 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
40953 R
43480 R
46811 R
49357 R
49604 S
49604 S
49604 S
112/119/127 117/123/131 122/128/135 126/131/139 127/132/139 127/132/139 127/132/139
4
40721 R
43240 R
46517 R
49049 R
49604 S
49604 S
49604 S
112/118/127 116/123/131 122/128/135 126/131/138 127/132/139 127/132/139 127/132/139
8
40492 R
42998 R
46183 R
48744 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/127/135 125/131/138 127/132/139 127/132/139 127/132/139
12
40273 R
42764 R
45756 R
48450 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/126/134 125/130/137 127/132/139 127/132/139 127/132/139
16
40070 R
42543 R
45363 R
48159 R
49604 S
49604 S
49604 S
110/117/126 115/121/130 120/126/133 125/130/137 127/132/139 127/132/139 127/132/139
20
39866 R
42318 R
44971 R
47863 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 119/125/133 124/129/137 127/132/139 127/132/139 127/132/139
24
39643 R
42096 R
44592 R
47571 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 119/125/132 124/129/136 127/132/139 127/132/139 127/132/139
28
39105 R
41872 R
44219 R
47279 R
49596 R
49604 S
49604 S
108/116/125 114/120/129 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139
32
38564 R
41645 R
43938 R
46993 R
49309 R
49604 S
49604 S
107/115/124 114/120/128 118/124/132 123/128/136 126/131/139 127/132/139 127/132/139
36
38025 R
41429 R
43707 R
46716 R
49035 R
49604 S
49604 S
106/114/123 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
40
37463 R
41207 R
43468 R
46429 R
48755 R
49604 S
49604 S
105/113/122 113/119/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
44
36909 R
40798 R
43018 R
45735 R
48194 R
49604 S
49604 S
104/112/122 112/119/127 116/122/130 121/127/134 125/130/137 127/132/139 127/132/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
5 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 1000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
40676 R
43193 R
46459 R
48989 R
49604 S
49604 S
49604 S
112/118/127 116/122/131 122/128/135 126/131/138 127/132/139 127/132/139 127/132/139
4
40448 R
42952 R
46097 R
48686 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/127/134 125/131/138 127/132/139 127/132/139 127/132/139
8
40222 R
42709 R
45658 R
48378 R
49604 S
49604 S
49604 S
111/118/126 116/122/130 121/126/134 125/130/137 127/132/139 127/132/139 127/132/139
12
40014 R
42482 R
45256 R
48078 R
49604 S
49604 S
49604 S
110/117/126 115/121/130 120/126/133 124/130/137 127/132/139 127/132/139 127/132/139
16
39817 R
42263 R
44877 R
47791 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 119/125/133 124/129/137 127/132/139 127/132/139 127/132/139
20
39500 R
42036 R
44491 R
47492 R
49604 S
49604 S
49604 S
109/116/125 114/121/129 119/124/132 124/129/136 127/132/139 127/132/139 127/132/139
24
38963 R
41811 R
44123 R
47202 R
49519 R
49604 S
49604 S
108/116/125 114/120/129 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139
28
38410 R
41583 R
43872 R
46913 R
49230 R
49604 S
49604 S
107/115/124 114/120/128 118/124/132 123/128/135 126/131/138 127/132/139 127/132/139
32
37851 R
41361 R
43634 R
46628 R
48949 R
49604 S
49604 S
106/114/123 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
36
37374 R
41145 R
43401 R
46349 R
48676 R
49604 S
49604 S
105/113/122 113/119/128 117/123/131 122/127/135 125/131/138 127/132/139 127/132/139
40
37045 R
40911 R
43142 R
45941 R
48364 R
49604 S
49604 S
104/112/122 112/119/127 116/122/131 121/127/134 125/130/137 127/132/139 127/132/139
44
36226 R
40227 R
42385 R
44734 R
47353 R
49455 R
49604 S
103/111/121 111/118/126 115/122/129 119/125/133 124/129/136 127/132/139 127/132/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
6 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 1500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
40388 R
42888 R
45981 R
48607 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/127/134 125/130/138 127/132/139 127/132/139 127/132/139
4
40167 R
42649 R
45551 R
48299 R
49604 S
49604 S
49604 S
111/118/126 115/122/130 120/126/134 125/130/137 127/132/139 127/132/139 127/132/139
8
39951 R
42412 R
45134 R
47986 R
49604 S
49604 S
49604 S
110/117/126 115/121/130 120/126/133 124/130/137 127/132/139 127/132/139 127/132/139
12
39750 R
42188 R
44749 R
47692 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 119/125/133 124/129/136 127/132/139 127/132/139 127/132/139
16
39340 R
41969 R
44380 R
47405 R
49604 S
49604 S
49604 S
109/116/125 114/121/129 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139
20
38787 R
41737 R
44035 R
47109 R
49426 R
49604 S
49604 S
108/115/124 114/120/129 118/124/132 123/128/136 127/132/139 127/132/139 127/132/139
24
38227 R
41509 R
43793 R
46818 R
49137 R
49604 S
49604 S
107/114/124 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
28
37659 R
41287 R
43554 R
46532 R
48855 R
49604 S
49604 S
106/113/123 113/119/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
32
37266 R
41069 R
43317 R
46230 R
48580 R
49604 S
49604 S
105/113/122 113/119/128 117/123/131 122/127/135 125/130/138 127/132/139 127/132/139
36
36982 R
40860 R
43086 R
45848 R
48288 R
49604 S
49604 S
104/112/122 112/119/127 116/122/130 121/127/134 125/130/137 127/132/139 127/132/139
40
36543 R
40490 R
42679 R
45189 R
47738 R
49604 S
49604 S
103/112/121 112/118/127 116/122/130 120/126/133 124/129/137 127/132/139 127/132/139
44
35549 R
39673 R
41763 R
43887 R
46566 R
48650 R
49604 S
102/110/120 110/117/126 114/121/129 118/124/132 122/128/135 126/131/138 127/132/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
7 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 2000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
40110 R
42587 R
45441 R
48217 R
49604 S
49604 S
49604 S
111/118/126 115/122/130 120/126/134 125/130/137 127/132/139 127/132/139 127/132/139
4
39896 R
42351 R
45028 R
47906 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 120/125/133 124/129/137 127/132/139 127/132/139 127/132/139
8
39691 R
42121 R
44636 R
47605 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 119/125/133 124/129/136 127/132/139 127/132/139 127/132/139
12
39170 R
41899 R
44263 R
47313 R
49604 S
49604 S
49604 S
109/116/125 114/120/129 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139
16
38629 R
41672 R
43967 R
47027 R
49343 R
49604 S
49604 S
108/115/124 114/120/128 118/124/132 123/128/136 126/131/139 127/132/139 127/132/139
20
38058 R
41442 R
43721 R
46733 R
49052 R
49604 S
49604 S
106/114/123 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
24
37479 R
41218 R
43480 R
46443 R
48768 R
49604 S
49604 S
105/113/122 113/119/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
28
37168 R
41000 R
43241 R
46103 R
48491 R
49604 S
49604 S
104/113/122 112/119/128 117/123/131 121/127/134 125/130/137 127/132/139 127/132/139
32
36901 R
40791 R
43010 R
45723 R
48184 R
49604 S
49604 S
104/112/122 112/119/127 116/122/130 121/126/134 125/130/137 127/132/139 127/132/139
36
36663 R
40590 R
42790 R
45365 R
47886 R
49604 S
49604 S
103/112/121 112/118/127 116/122/130 120/126/133 124/129/137 127/132/139 127/132/139
40
35892 R
39955 R
42077 R
44273 R
46959 R
49055 R
49604 S
102/111/120 111/118/126 115/121/129 119/125/132 123/129/136 126/131/138 127/132/139
44
34716 R
38425 R
41152 R
43210 R
45642 R
47809 R
49220 W
101/109/119 108/116/124 114/120/128 117/123/131 121/127/134 125/130/137 127/132/138
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
8 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 2500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
39831 R
42278 R
44903 R
47810 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 119/125/133 124/129/137 127/132/139 127/132/139 127/132/139
4
39518 R
42043 R
44504 R
47503 R
49604 S
49604 S
49604 S
109/117/125 114/121/129 119/125/132 124/129/136 127/132/139 127/132/139 127/132/139
8
38972 R
41815 R
44129 R
47207 R
49524 R
49604 S
49604 S
108/116/125 114/120/129 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139
12
38432 R
41592 R
43881 R
46924 R
49241 R
49604 S
49604 S
107/115/124 114/120/128 118/124/132 123/128/136 126/131/138 127/132/139 127/132/139
16
37861 R
41364 R
43638 R
46633 R
48954 R
49604 S
49604 S
106/114/123 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
20
37366 R
41140 R
43395 R
46342 R
48669 R
49604 S
49604 S
105/113/122 113/119/128 117/123/131 122/127/135 125/131/138 127/132/139 127/132/139
24
37060 R
40922 R
43155 R
45961 R
48380 R
49604 S
49604 S
104/112/122 112/119/127 116/122/131 121/127/134 125/130/137 127/132/139 127/132/139
28
36808 R
40713 R
42925 R
45583 R
48068 R
49604 S
49604 S
104/112/122 112/119/127 116/122/130 120/126/134 124/130/137 127/132/139 127/132/139
32
36565 R
40508 R
42699 R
45221 R
47765 R
49604 S
49604 S
103/112/121 111/118/127 116/122/130 120/126/133 124/129/137 127/132/139 127/132/139
36
36165 R
40177 R
42329 R
44649 R
47280 R
49382 R
49604 S
103/111/121 111/118/126 115/121/129 119/125/133 123/129/136 127/132/139 127/132/139
40
35184 R
39037 R
41463 R
43557 R
46155 R
48240 R
49604 S
101/110/119 109/116/125 114/120/128 117/124/131 122/128/135 125/130/137 127/132/139
44
34010 R
37397 R
40560 R
42537 R
44696 R
47003 R
48299 W
100/108/117 107/114/122 113/119/127 117/122/130 120/126/133 124/129/136 126/131/137
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
9 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 3000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
39354 R
41975 R
44389 R
47413 R
49604 S
49604 S
49604 S
109/116/125 114/121/129 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139
4
38781 R
41735 R
44033 R
47106 R
49423 R
49604 S
49604 S
108/115/124 114/120/129 118/124/132 123/128/136 127/132/139 127/132/139 127/132/139
8
38235 R
41512 R
43796 R
46822 R
49141 R
49604 S
49604 S
107/114/124 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
12
37672 R
41291 R
43559 R
46539 R
48861 R
49604 S
49604 S
106/113/123 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
16
37263 R
41068 R
43315 R
46227 R
48578 R
49604 S
49604 S
105/113/122 113/119/128 117/123/131 122/127/135 125/130/138 127/132/139 127/132/139
20
36971 R
40850 R
43075 R
45830 R
48273 R
49604 S
49604 S
104/112/122 112/119/127 116/122/130 121/127/134 125/130/137 127/132/139 127/132/139
24
36723 R
40641 R
42845 R
45454 R
47960 R
49604 S
49604 S
104/112/121 112/118/127 116/122/130 120/126/134 124/130/137 127/132/139 127/132/139
28
36477 R
40434 R
42617 R
45092 R
47656 R
49604 S
49604 S
103/111/121 111/118/127 115/122/130 120/126/133 124/129/136 127/132/139 127/132/139
32
36233 R
40233 R
42391 R
44743 R
47361 R
49462 R
49604 S
103/111/121 111/118/126 115/121/129 119/125/133 123/129/136 127/132/139 127/132/139
36
35502 R
39579 R
41720 R
43841 R
46513 R
48594 R
49604 S
101/110/120 110/117/126 114/121/129 118/124/131 122/128/135 125/131/138 127/132/139
40
34346 R
37893 R
40863 R
42884 R
45175 R
47413 R
49324 R
100/109/118 107/115/123 113/120/127 117/123/130 121/126/133 124/130/136 127/132/139
44
33508 R
36678 R
40009 R
41894 R
43893 R
46264 R
47377 W
100/107/117 106/113/121 113/119/126 116/122/129 119/125/132 124/128/135 125/130/136
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
10 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 3500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
38582 R
41653 R
43946 R
47002 R
49319 R
49604 S
49604 S
107/115/124 114/120/128 118/124/132 123/128/136 126/132/139 127/132/139 127/132/139
4
38002 R
41420 R
43698 R
46704 R
49024 R
49604 S
49604 S
106/114/123 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
8
37454 R
41201 R
43461 R
46421 R
48746 R
49604 S
49604 S
105/113/122 113/119/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
12
37148 R
40986 R
43225 R
46076 R
48470 R
49604 S
49604 S
104/113/122 112/119/128 117/123/131 121/127/134 125/130/137 127/132/139 127/132/139
16
36876 R
40770 R
42988 R
45686 R
48154 R
49604 S
49604 S
104/112/122 112/119/127 116/122/130 121/126/134 125/130/137 127/132/139 127/132/139
20
36622 R
40556 R
42752 R
45304 R
47835 R
49604 S
49604 S
103/112/121 112/118/127 116/122/130 120/126/133 124/129/137 127/132/139 127/132/139
24
36374 R
40349 R
42522 R
44944 R
47531 R
49604 S
49604 S
103/111/121 111/118/127 115/122/130 119/125/133 124/129/136 127/132/139 127/132/139
28
36100 R
40124 R
42269 R
44558 R
47203 R
49304 R
49604 S
102/111/120 111/118/126 115/121/129 119/125/132 123/129/136 126/132/139 127/132/139
32
35719 R
39815 R
41917 R
44055 R
46759 R
48850 R
49604 S
102/110/120 110/117/126 114/121/129 118/124/132 122/128/135 126/131/138 127/132/139
36
34681 R
38377 R
41127 R
43182 R
45601 R
47774 R
49604 S
100/109/119 108/115/124 113/120/128 117/123/131 121/127/134 124/130/137 127/132/139
40
33732 R
37023 R
40271 R
42202 R
44249 R
46618 R
48454 W
99/108/117 106/113/122 113/119/127 116/122/129 120/125/132 123/129/135 126/131/137
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
11 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 4000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
37799 R
41340 R
43612 R
46602 R
48923 R
49604 S
49604 S
106/114/123 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
4
37335 R
41118 R
43371 R
46313 R
48641 R
49604 S
49604 S
105/113/122 113/119/128 117/123/131 122/127/135 125/131/138 127/132/139 127/132/139
8
37034 R
40903 R
43133 R
45926 R
48352 R
49604 S
49604 S
104/112/122 112/119/127 116/122/130 121/127/134 125/130/137 127/132/139 127/132/139
12
36789 R
40696 R
42906 R
45553 R
48043 R
49604 S
49604 S
104/112/121 112/119/127 116/122/130 120/126/134 124/130/137 127/132/139 127/132/139
16
36539 R
40486 R
42675 R
45183 R
47732 R
49604 S
49604 S
103/112/121 111/118/127 116/122/130 120/126/133 124/129/137 127/132/139 127/132/139
20
36280 R
40271 R
42434 R
44810 R
47417 R
49519 R
49604 S
103/111/121 111/118/127 115/121/130 119/125/133 123/129/136 127/132/139 127/132/139
24
36031 R
40068 R
42205 R
44463 R
47122 R
49221 R
49604 S
102/111/120 111/118/126 115/121/129 119/125/132 123/129/136 126/131/138 127/132/139
28
35721 R
39816 R
41918 R
44056 R
46761 R
48852 R
49604 S
102/110/120 110/117/126 114/121/129 118/124/132 122/128/135 126/131/138 127/132/139
32
34968 R
38762 R
41326 R
43405 R
45928 R
48050 R
49604 S
100/109/119 108/116/124 113/120/128 117/123/131 121/127/134 125/130/137 127/132/139
36
33991 R
37373 R
40541 R
42515 R
44667 R
46978 R
48867 R
99/108/118 106/114/122 112/119/127 116/122/130 120/126/133 124/129/136 126/132/138
40
33276 R
36272 R
39705 R
41554 R
43507 R
45741 R
47493 W
99/107/116 105/112/121 112/118/126 116/121/128 119/124/131 123/128/134 125/130/136
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
12 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 4500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
37231 R
41045 R
43290 R
46185 R
48549 R
49604 S
49604 S
105/113/122 113/119/128 117/123/131 122/127/135 125/130/138 127/132/139 127/132/139
4
36950 R
40832 R
43056 R
45798 R
48247 R
49604 S
49604 S
104/112/122 112/119/127 116/122/130 121/127/134 125/130/137 127/132/139 127/132/139
8
36701 R
40622 R
42825 R
45422 R
47933 R
49604 S
49604 S
104/112/121 112/118/127 116/122/130 120/126/134 124/130/137 127/132/139 127/132/139
12
36451 R
40414 R
42594 R
45056 R
47625 R
49604 S
49604 S
103/111/121 111/118/127 115/122/130 120/125/133 124/129/136 127/132/139 127/132/139
16
36200 R
40206 R
42361 R
44697 R
47322 R
49423 R
49604 S
103/111/121 111/118/126 115/121/129 119/125/133 123/129/136 127/132/139 127/132/139
20
35942 R
39995 R
42123 R
44341 R
47017 R
49115 R
49604 S
102/111/120 110/117/126 115/121/129 118/124/132 123/128/136 126/131/138 127/132/139
24
35679 R
39783 R
41880 R
44015 R
46714 R
48803 R
49604 S
102/110/120 110/117/126 114/121/129 118/124/132 122/128/135 126/131/138 127/132/139
28
35185 R
39038 R
41463 R
43558 R
46156 R
48241 R
49604 S
101/109/119 109/116/125 114/120/128 117/123/131 122/127/135 125/130/137 127/132/139
32
34201 R
37674 R
40738 R
42741 R
44976 R
47243 R
49147 R
99/108/118 106/114/123 112/119/127 116/122/130 120/126/133 123/129/136 126/132/138
36
33464 R
36606 R
39955 R
41833 R
43825 R
46170 R
48018 R
99/107/116 105/113/121 112/118/126 116/121/129 119/124/131 123/128/135 126/131/137
40
32709 R
35512 R
38683 R
40935 R
42790 R
44816 R
46515 W
98/106/115 104/111/120 111/117/124 115/120/127 118/123/130 121/126/133 124/129/135
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
13 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 5000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
36869 R
40764 R
42981 R
45675 R
48144 R
49604 S
49604 S
104/112/122 112/119/127 116/122/130 121/126/134 125/130/137 127/132/139 127/132/139
4
36628 R
40561 R
42757 R
45314 R
47842 R
49604 S
49604 S
103/112/121 112/118/127 116/122/130 120/126/133 124/129/137 127/132/139 127/132/139
8
36375 R
40350 R
42523 R
44946 R
47532 R
49604 S
49604 S
103/111/121 111/118/127 115/122/130 119/125/133 124/129/136 127/132/139 127/132/139
12
36120 R
40140 R
42287 R
44586 R
47226 R
49327 R
49604 S
102/111/120 111/118/126 115/121/129 119/125/132 123/129/136 126/132/139 127/132/139
16
35867 R
39934 R
42053 R
44239 R
46929 R
49025 R
49604 S
102/110/120 110/117/126 115/121/129 118/124/132 123/128/136 126/131/138 127/132/139
20
35611 R
39728 R
41818 R
43948 R
46636 R
48722 R
49604 S
101/110/120 110/117/126 114/120/129 118/124/132 122/128/135 125/131/138 127/132/139
24
35329 R
39249 R
41565 R
43670 R
46319 R
48383 R
49604 S
101/110/119 109/116/125 114/120/128 117/123/131 122/127/135 125/130/137 127/132/139
28
34414 R
37994 R
40920 R
42948 R
45266 R
47490 R
49404 R
99/109/118 107/114/123 113/119/127 116/123/130 120/126/133 124/129/136 127/132/139
32
33635 R
36879 R
40161 R
42073 R
44083 R
46472 R
48320 R
99/107/117 105/113/122 112/118/126 116/122/129 119/125/132 123/128/135 126/131/137
36
33062 R
35852 R
39132 R
41210 R
43110 R
45221 R
47211 R
98/106/116 104/112/120 111/117/125 115/121/128 118/124/130 122/127/133 125/130/136
40
32078 R
34893 R
37785 R
40345 R
42088 R
43978 R
45555 W
98/105/114 103/110/119 109/115/123 114/120/127 117/122/129 120/125/132 123/128/134
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
14 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 5500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
36337 R
40319 R
42488 R
44891 R
47486 R
49588 R
49604 S
103/111/121 111/118/127 115/122/130 119/125/133 124/129/136 127/132/139 127/132/139
4
36090 R
40116 R
42259 R
44545 R
47191 R
49292 R
49604 S
102/111/120 111/118/126 115/121/129 119/125/132 123/129/136 126/132/139 127/132/139
8
35836 R
39909 R
42025 R
44198 R
46894 R
48989 R
49604 S
102/110/120 110/117/126 115/121/129 118/124/132 123/128/135 126/131/138 127/132/139
12
35580 R
39704 R
41791 R
43918 R
46601 R
48686 R
49604 S
101/110/120 110/117/126 114/121/129 118/124/132 122/128/135 126/131/138 127/132/139
16
35326 R
39245 R
41563 R
43668 R
46317 R
48380 R
49604 S
101/110/119 109/116/125 114/120/128 117/123/131 122/128/135 125/130/137 127/132/139
20
34986 R
38785 R
41338 R
43418 R
45947 R
48066 R
49604 S
100/109/119 108/116/124 113/120/128 117/123/131 121/127/134 125/130/137 127/132/139
24
34606 R
38271 R
41071 R
43119 R
45510 R
47697 R
49604 S
100/109/119 107/115/124 113/119/128 116/123/130 120/126/134 124/129/136 127/132/139
28
33783 R
37096 R
40327 R
42267 R
44335 R
46692 R
48562 R
98/108/117 105/113/122 112/119/127 115/122/129 119/125/132 123/128/135 126/131/138
32
33180 R
36087 R
39459 R
41402 R
43332 R
45510 R
47458 R
98/106/116 104/112/120 111/118/125 115/121/128 118/124/131 122/127/134 125/130/136
36
32301 R
35102 R
38118 R
40570 R
42358 R
44286 R
46396 W
98/105/115 103/111/119 110/116/123 114/120/127 117/123/129 121/126/132 124/129/135
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
15 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 6000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
35819 R
39895 R
42009 R
44174 R
46874 R
48968 R
49604 S
102/111/120 110/118/126 115/121/129 118/124/132 123/128/135 126/131/138 127/132/139
4
35567 R
39693 R
41779 R
43905 R
46586 R
48671 R
49604 S
101/110/120 110/117/126 114/121/129 118/124/132 122/128/135 126/131/138 127/132/139
8
35312 R
39218 R
41551 R
43654 R
46301 R
48363 R
49604 S
101/110/119 109/116/125 114/120/128 117/124/131 122/128/135 125/130/137 127/132/139
12
34964 R
38757 R
41324 R
43402 R
45924 R
48046 R
49604 S
100/109/119 108/116/124 113/120/128 117/123/131 121/127/134 125/130/137 127/132/139
16
34646 R
38328 R
41101 R
43153 R
45559 R
47738 R
49604 S
100/109/119 107/115/124 113/120/128 117/123/131 121/126/134 124/130/137 127/132/139
20
34368 R
37927 R
40882 R
42905 R
45205 R
47439 R
49350 R
99/108/118 106/114/123 112/119/127 116/122/130 120/126/133 124/129/136 127/132/139
24
33933 R
37298 R
40483 R
42448 R
44576 R
46900 R
48785 R
99/108/118 105/113/122 112/119/127 115/122/130 119/125/132 123/129/135 126/131/138
28
33308 R
36331 R
39749 R
41603 R
43563 R
45816 R
47719 R
98/107/116 104/112/121 111/118/126 115/121/128 118/124/131 122/127/134 125/130/137
32
32515 R
35304 R
38421 R
40769 R
42594 R
44573 R
46652 R
98/105/115 103/111/119 110/116/124 114/120/127 117/123/130 121/126/132 124/129/135
36
31684 R
34554 R
37225 R
39957 R
41644 R
43476 R
45373 W
97/104/114 103/110/118 108/114/122 114/119/126 117/122/128 120/125/131 123/127/134
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
16 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 6500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
35272 R
39145 R
41515 R
43615 R
46243 R
48313 R
49604 S
101/110/119 109/116/125 114/120/128 117/124/131 122/128/135 125/130/137 127/132/139
4
34910 R
38685 R
41287 R
43362 R
45864 R
47996 R
49604 S
100/109/119 108/116/124 113/120/128 117/123/131 121/127/134 125/130/137 127/132/139
8
34594 R
38254 R
41062 R
43108 R
45495 R
47684 R
49604 S
100/109/119 107/115/124 113/120/128 117/123/130 121/127/134 124/130/136 127/132/139
12
34318 R
37853 R
40840 R
42858 R
45139 R
47382 R
49291 R
99/108/118 106/114/123 112/119/127 116/122/130 120/126/133 124/129/136 127/132/139
16
34076 R
37478 R
40623 R
42609 R
44795 R
47088 R
48984 R
99/108/118 106/114/122 112/119/127 116/122/130 119/125/133 123/129/136 126/131/138
20
33852 R
37190 R
40400 R
42352 R
44447 R
46789 R
48666 R
98/108/118 105/113/122 112/119/127 115/122/129 119/125/132 123/128/135 126/131/138
24
33415 R
36522 R
39892 R
41762 R
43744 R
46060 R
47926 R
98/107/117 104/112/121 111/118/126 115/121/129 118/124/131 122/128/134 125/130/137
28
32730 R
35533 R
38710 R
40952 R
42809 R
44840 R
46883 R
98/106/115 103/111/120 110/116/124 114/120/127 117/123/130 121/126/133 124/129/135
32
31897 R
34719 R
37503 R
40146 R
41852 R
43724 R
45754 R
97/104/114 103/110/118 109/115/123 114/119/126 117/122/129 120/125/131 123/128/134
36
30744 R
33948 R
36300 R
39095 R
40976 R
42669 R
44363 W
95/103/112 102/109/117 107/113/121 113/118/125 116/121/128 119/123/130 122/126/132
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
17 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 7000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
34578 R
38232 R
41049 R
43095 R
45475 R
47668 R
49587 R
100/109/118 107/115/124 113/120/128 117/123/130 121/127/134 124/130/136 127/132/139
4
34296 R
37820 R
40821 R
42836 R
45108 R
47356 R
49265 R
99/109/118 107/114/123 113/119/127 116/123/130 120/126/133 124/129/136 127/132/139
8
34050 R
37446 R
40598 R
42581 R
44756 R
47055 R
48948 R
99/108/118 106/114/122 112/119/127 116/122/130 119/126/133 123/129/136 126/132/138
12
33835 R
37167 R
40382 R
42331 R
44420 R
46765 R
48641 R
98/108/118 105/113/122 112/119/127 115/122/129 119/125/132 123/128/135 126/131/138
16
33643 R
36891 R
40171 R
42084 R
44095 R
46484 R
48333 R
98/107/117 105/113/122 111/118/126 115/121/129 118/124/132 122/128/135 125/131/137
20
33442 R
36569 R
39927 R
41802 R
43789 R
46122 R
47977 R
98/107/117 104/112/121 111/118/126 115/121/129 118/124/131 122/128/134 125/130/137
24
32959 R
35757 R
39004 R
41133 R
43021 R
45107 R
47113 R
97/106/116 103/111/120 110/117/125 114/120/128 117/123/130 121/126/133 124/129/136
28
32067 R
34882 R
37768 R
40333 R
42074 R
43963 R
46052 R
97/105/114 103/110/119 109/115/123 113/119/127 117/122/129 120/125/132 123/128/134
32
31064 R
34151 R
36592 R
39443 R
41194 R
42930 R
44791 R
96/103/113 102/109/118 107/113/121 113/118/125 116/121/128 119/124/130 122/127/133
36
29709 R
33311 R
35477 R
38049 R
40327 R
41902 R
43351 W
93/101/111 102/108/116 106/112/120 111/116/123 116/120/127 118/122/129 121/125/131
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
18 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 7500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
34006 R
37392 R
40556 R
42532 R
44690 R
46998 R
48889 R
99/108/118 106/114/122 112/119/127 116/122/130 120/126/133 123/129/136 126/132/138
4
33792 R
37108 R
40336 R
42277 R
44349 R
46704 R
48575 R
99/108/117 106/113/122 112/119/127 116/122/129 119/125/132 123/129/135 126/131/138
8
33601 R
36826 R
40122 R
42026 R
44034 R
46420 R
48261 R
98/107/117 105/113/122 111/118/126 115/121/129 119/125/132 122/128/135 125/131/137
12
33431 R
36549 R
39912 R
41785 R
43770 R
46096 R
47955 R
98/107/117 104/112/121 111/118/126 115/121/129 118/124/131 122/128/134 125/130/137
16
33275 R
36270 R
39704 R
41553 R
43506 R
45740 R
47654 R
98/107/117 104/112/121 111/118/126 114/121/128 118/124/131 121/127/134 124/130/136
20
33075 R
35869 R
39155 R
41224 R
43127 R
45243 R
47230 R
97/106/116 103/111/120 110/117/125 114/120/128 117/123/130 121/126/133 124/129/136
24
32226 R
35032 R
38008 R
40497 R
42270 R
44181 R
46311 R
97/105/115 102/110/119 108/115/123 113/119/127 117/122/129 120/125/132 123/128/135
28
31297 R
34315 R
36841 R
39710 R
41374 R
43148 R
45055 R
96/104/113 102/109/118 107/114/122 113/118/126 116/121/128 119/124/131 122/127/133
32
29962 R
33517 R
35729 R
38380 R
40531 R
42142 R
43860 R
94/101/112 102/108/117 106/112/120 111/117/124 115/120/127 118/123/129 121/125/132
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
19 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 8000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
33574 R
36785 R
40090 R
41989 R
43994 R
46378 R
48215 R
99/107/117 105/113/121 112/118/126 115/121/129 119/125/132 123/128/135 126/131/137
4
33404 R
36503 R
39878 R
41747 R
43727 R
46037 R
47905 R
98/107/117 105/112/121 111/118/126 115/121/129 118/124/131 122/128/134 125/130/137
8
33251 R
36226 R
39659 R
41516 R
43464 R
45683 R
47606 R
98/107/116 104/112/121 111/118/126 115/121/128 118/124/131 122/127/134 125/130/136
12
33113 R
35950 R
39267 R
41290 R
43203 R
45342 R
47314 R
98/106/116 104/111/120 110/117/125 114/120/128 118/123/131 121/127/133 124/129/136
16
32863 R
35666 R
38883 R
41059 R
42935 R
44998 R
47019 R
97/106/116 103/111/120 109/116/125 114/120/128 117/123/130 121/126/133 124/129/136
20
32367 R
35163 R
38213 R
40633 R
42433 R
44377 R
46482 R
97/105/115 102/110/119 108/115/124 113/119/127 117/122/130 120/125/132 123/128/135
24
31558 R
34480 R
37103 R
39880 R
41559 R
43373 R
45328 R
96/104/114 102/109/118 107/114/122 113/119/126 116/121/128 119/124/131 122/127/133
28
30248 R
33703 R
35967 R
38684 R
40721 R
42365 R
44108 R
94/102/112 101/108/117 106/112/120 112/117/124 115/120/127 118/123/129 121/126/132
32
29301 R
32774 R
34997 R
37358 R
39893 R
41429 R
43039 R
92/100/111 101/107/115 105/111/119 110/115/122 115/119/126 118/122/128 120/124/130
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
20 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: Sea Level Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
43007 R
46663 R
49494 R
49604 S
49604 S
49604 S
49604 S
116/122/130 122/128/135 127/132/139 127/132/139 127/132/139 127/132/139 127/132/139
-30
42768 R
46363 R
49156 R
49604 S
49604 S
49604 S
49604 S
116/122/130 122/127/135 126/131/138 127/132/139 127/132/139 127/132/139 127/132/139
-26
42530 R
45911 R
48827 R
49604 S
49604 S
49604 S
49604 S
115/121/130 121/127/134 126/131/138 127/132/139 127/132/139 127/132/139 127/132/139
-22
42303 R
45450 R
48518 R
49604 S
49604 S
49604 S
49604 S
115/121/129 120/126/134 125/130/138 127/132/139 127/132/139 127/132/139 127/132/139
-18
42078 R
45002 R
48211 R
49604 S
49604 S
49604 S
49604 S
114/121/129 119/125/133 125/130/137 127/132/139 127/132/139 127/132/139 127/132/139
-14
41840 R
44555 R
47897 R
49604 S
49604 S
49604 S
49604 S
114/120/129 119/125/132 124/129/137 127/132/139 127/132/139 127/132/139 127/132/139
-10
41585 R
44129 R
47590 R
49604 S
49604 S
49604 S
49604 S
114/120/128 118/124/132 124/129/136 127/132/139 127/132/139 127/132/139 127/132/139
-6
41349 R
43881 R
47303 R
49604 S
49604 S
49604 S
49604 S
113/120/128 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139 127/132/139
-2
41130 R
43661 R
47033 R
49592 R
49604 S
49604 S
49604 S
113/119/128 117/123/131 123/128/136 127/132/139 127/132/139 127/132/139 127/132/139
2
40906 R
43432 R
46752 R
49295 R
49604 S
49604 S
49604 S
112/119/127 117/123/131 122/128/135 126/131/139 127/132/139 127/132/139 127/132/139
6
40678 R
43195 R
46462 R
48993 R
49604 S
49604 S
49604 S
112/118/127 116/122/131 122/128/135 126/131/138 127/132/139 127/132/139 127/132/139
10
40450 R
42954 R
46102 R
48689 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/127/134 125/131/138 127/132/139 127/132/139 127/132/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
21 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
42751 R
46342 R
49133 R
49604 S
49604 S
49604 S
49604 S
116/122/130 122/127/135 126/131/138 127/132/139 127/132/139 127/132/139 127/132/139
-30
42513 R
45875 R
48803 R
49604 S
49604 S
49604 S
49604 S
115/121/130 121/127/134 126/131/138 127/132/139 127/132/139 127/132/139 127/132/139
-26
42277 R
45397 R
48482 R
49604 S
49604 S
49604 S
49604 S
115/121/129 120/126/134 125/130/137 127/132/139 127/132/139 127/132/139 127/132/139
-22
42047 R
44943 R
48170 R
49604 S
49604 S
49604 S
49604 S
114/121/129 119/125/133 125/130/137 127/132/139 127/132/139 127/132/139 127/132/139
-18
41811 R
44508 R
47863 R
49604 S
49604 S
49604 S
49604 S
114/120/129 119/124/132 124/129/137 127/132/139 127/132/139 127/132/139 127/132/139
-14
41556 R
44086 R
47556 R
49604 S
49604 S
49604 S
49604 S
113/120/128 118/124/132 124/129/136 127/132/139 127/132/139 127/132/139 127/132/139
-10
41312 R
43844 R
47258 R
49604 S
49604 S
49604 S
49604 S
113/119/128 118/123/131 123/129/136 127/132/139 127/132/139 127/132/139 127/132/139
-6
41077 R
43607 R
46966 R
49522 R
49604 S
49604 S
49604 S
112/119/128 117/123/131 123/128/136 127/132/139 127/132/139 127/132/139 127/132/139
-2
40851 R
43375 R
46682 R
49222 R
49604 S
49604 S
49604 S
112/119/127 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139 127/132/139
2
40623 R
43137 R
46390 R
48918 R
49604 S
49604 S
49604 S
112/118/127 116/122/131 122/127/135 126/131/138 127/132/139 127/132/139 127/132/139
6
40398 R
42898 R
45999 R
48619 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/127/134 125/130/138 127/132/139 127/132/139 127/132/139
10
40171 R
42654 R
45560 R
48305 R
49604 S
49604 S
49604 S
111/118/126 115/122/130 120/126/134 125/130/137 127/132/139 127/132/139 127/132/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
22 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 1000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
42500 R
45848 R
48785 R
49604 S
49604 S
49604 S
49604 S
115/121/130 121/127/134 126/131/138 127/132/139 127/132/139 127/132/139 127/132/139
-30
42262 R
45367 R
48462 R
49604 S
49604 S
49604 S
49604 S
115/121/129 120/126/133 125/130/137 127/132/139 127/132/139 127/132/139 127/132/139
-26
42028 R
44906 R
48144 R
49604 S
49604 S
49604 S
49604 S
114/121/129 119/125/133 124/130/137 127/132/139 127/132/139 127/132/139 127/132/139
-22
41783 R
44461 R
47829 R
49604 S
49604 S
49604 S
49604 S
114/120/129 119/124/132 124/129/137 127/132/139 127/132/139 127/132/139 127/132/139
-18
41529 R
44059 R
47523 R
49604 S
49604 S
49604 S
49604 S
113/120/128 118/124/132 124/129/136 127/132/139 127/132/139 127/132/139 127/132/139
-14
41283 R
43815 R
47222 R
49604 S
49604 S
49604 S
49604 S
113/119/128 117/123/131 123/129/136 127/132/139 127/132/139 127/132/139 127/132/139
-10
41050 R
43579 R
46932 R
49485 R
49604 S
49604 S
49604 S
112/119/128 117/123/131 123/128/136 127/132/139 127/132/139 127/132/139 127/132/139
-6
40816 R
43339 R
46637 R
49175 R
49604 S
49604 S
49604 S
112/119/127 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139 127/132/139
-2
40583 R
43095 R
46340 R
48866 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 122/127/135 126/131/138 127/132/139 127/132/139 127/132/139
2
40351 R
42848 R
45907 R
48557 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/127/134 125/130/138 127/132/139 127/132/139 127/132/139
6
40128 R
42607 R
45476 R
48243 R
49604 S
49604 S
49604 S
111/118/126 115/122/130 120/126/134 125/130/137 127/132/139 127/132/139 127/132/139
10
39904 R
42360 R
45044 R
47918 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 120/125/133 124/129/137 127/132/139 127/132/139 127/132/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
23 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 1500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
42227 R
45297 R
48414 R
49604 S
49604 S
49604 S
49604 S
115/121/129 120/126/133 125/130/137 127/132/139 127/132/139 127/132/139 127/132/139
-30
41990 R
44832 R
48092 R
49604 S
49604 S
49604 S
49604 S
114/121/129 119/125/133 124/130/137 127/132/139 127/132/139 127/132/139 127/132/139
-26
41741 R
44389 R
47778 R
49604 S
49604 S
49604 S
49604 S
114/120/129 118/124/132 124/129/137 127/132/139 127/132/139 127/132/139 127/132/139
-22
41484 R
44015 R
47468 R
49604 S
49604 S
49604 S
49604 S
113/120/128 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139 127/132/139
-18
41235 R
43767 R
47163 R
49604 S
49604 S
49604 S
49604 S
113/119/128 117/123/131 123/128/136 127/132/139 127/132/139 127/132/139 127/132/139
-14
40995 R
43523 R
46863 R
49413 R
49604 S
49604 S
49604 S
112/119/128 117/123/131 123/128/135 127/132/139 127/132/139 127/132/139 127/132/139
-10
40764 R
43285 R
46572 R
49107 R
49604 S
49604 S
49604 S
112/119/127 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139 127/132/139
-6
40535 R
43044 R
46267 R
48802 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 122/127/135 126/131/138 127/132/139 127/132/139 127/132/139
-2
40297 R
42790 R
45804 R
48485 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/127/134 125/130/137 127/132/139 127/132/139 127/132/139
2
40066 R
42538 R
45355 R
48152 R
49604 S
49604 S
49604 S
110/117/126 115/121/130 120/126/133 125/130/137 127/132/139 127/132/139 127/132/139
6
39853 R
42303 R
44945 R
47843 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 119/125/133 124/129/137 127/132/139 127/132/139 127/132/139
10
39584 R
42071 R
44551 R
47539 R
49604 S
49604 S
49604 S
109/117/126 114/121/129 119/125/132 124/129/136 127/132/139 127/132/139 127/132/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
24 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 2000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
41960 R
44774 R
48051 R
49604 S
49604 S
49604 S
49604 S
114/121/129 119/125/133 124/130/137 127/132/139 127/132/139 127/132/139 127/132/139
-30
41701 R
44323 R
47731 R
49604 S
49604 S
49604 S
49604 S
114/120/129 118/124/132 124/129/137 127/132/139 127/132/139 127/132/139 127/132/139
-26
41445 R
43976 R
47420 R
49604 S
49604 S
49604 S
49604 S
113/120/128 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139 127/132/139
-22
41196 R
43728 R
47114 R
49604 S
49604 S
49604 S
49604 S
113/119/128 117/123/131 123/128/136 127/132/139 127/132/139 127/132/139 127/132/139
-18
40953 R
43480 R
46811 R
49357 R
49604 S
49604 S
49604 S
112/119/127 117/123/131 122/128/135 126/132/139 127/132/139 127/132/139 127/132/139
-14
40718 R
43237 R
46513 R
49046 R
49604 S
49604 S
49604 S
112/119/127 116/123/131 122/128/135 126/131/138 127/132/139 127/132/139 127/132/139
-10
40490 R
42997 R
46180 R
48743 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/127/135 125/131/138 127/132/139 127/132/139 127/132/139
-6
40265 R
42755 R
45741 R
48438 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/126/134 125/130/137 127/132/139 127/132/139 127/132/139
-2
40024 R
42492 R
45274 R
48092 R
49604 S
49604 S
49604 S
110/117/126 115/121/130 120/126/133 124/130/137 127/132/139 127/132/139 127/132/139
2
39793 R
42236 R
44830 R
47755 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 119/125/133 124/129/137 127/132/139 127/132/139 127/132/139
6
39428 R
42006 R
44441 R
47453 R
49604 S
49604 S
49604 S
109/116/125 114/121/129 119/124/132 123/129/136 127/132/139 127/132/139 127/132/139
10
38899 R
41784 R
44085 R
47169 R
49485 R
49604 S
49604 S
108/115/125 114/120/129 118/124/132 123/128/136 127/132/139 127/132/139 127/132/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
25 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 2500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
41666 R
44265 R
47689 R
49604 S
49604 S
49604 S
49604 S
114/120/128 118/124/132 124/129/136 127/132/139 127/132/139 127/132/139 127/132/139
-30
41403 R
43934 R
47369 R
49604 S
49604 S
49604 S
49604 S
113/120/128 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139 127/132/139
-26
41152 R
43683 R
47059 R
49604 S
49604 S
49604 S
49604 S
113/119/128 117/123/131 123/128/136 127/132/139 127/132/139 127/132/139 127/132/139
-22
40908 R
43434 R
46754 R
49298 R
49604 S
49604 S
49604 S
112/119/127 117/123/131 122/128/135 126/131/139 127/132/139 127/132/139 127/132/139
-18
40672 R
43188 R
46453 R
48984 R
49604 S
49604 S
49604 S
112/118/127 116/122/131 122/128/135 126/131/138 127/132/139 127/132/139 127/132/139
-14
40442 R
42945 R
46086 R
48678 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/127/134 125/131/138 127/132/139 127/132/139 127/132/139
-10
40215 R
42701 R
45644 R
48367 R
49604 S
49604 S
49604 S
111/118/126 116/122/130 121/126/134 125/130/137 127/132/139 127/132/139 127/132/139
-6
39993 R
42458 R
45215 R
48047 R
49604 S
49604 S
49604 S
110/117/126 115/121/130 120/126/133 124/130/137 127/132/139 127/132/139 127/132/139
-2
39749 R
42187 R
44747 R
47691 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 119/125/133 124/129/136 127/132/139 127/132/139 127/132/139
2
39237 R
41926 R
44309 R
47349 R
49604 S
49604 S
49604 S
109/116/125 114/121/129 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139
6
38681 R
41693 R
43989 R
47054 R
49370 R
49604 S
49604 S
108/115/124 114/120/129 118/124/132 123/128/136 127/132/139 127/132/139 127/132/139
10
38181 R
41491 R
43774 R
46795 R
49114 R
49604 S
49604 S
107/114/124 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
26 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 3000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
41375 R
43907 R
47335 R
49604 S
49604 S
49604 S
49604 S
113/120/128 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139 127/132/139
-30
41116 R
43647 R
47015 R
49573 R
49604 S
49604 S
49604 S
113/119/128 117/123/131 123/128/136 127/132/139 127/132/139 127/132/139 127/132/139
-26
40870 R
43395 R
46706 R
49247 R
49604 S
49604 S
49604 S
112/119/127 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139 127/132/139
-22
40632 R
43146 R
46402 R
48931 R
49604 S
49604 S
49604 S
112/118/127 116/122/131 122/128/135 126/131/138 127/132/139 127/132/139 127/132/139
-18
40402 R
42902 R
46007 R
48625 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/127/134 125/130/138 127/132/139 127/132/139 127/132/139
-14
40176 R
42659 R
45569 R
48312 R
49604 S
49604 S
49604 S
111/118/126 116/122/130 120/126/134 125/130/137 127/132/139 127/132/139 127/132/139
-10
39951 R
42412 R
45133 R
47986 R
49604 S
49604 S
49604 S
110/117/126 115/121/130 120/126/133 124/130/137 127/132/139 127/132/139 127/132/139
-6
39732 R
42168 R
44715 R
47666 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 119/125/133 124/129/136 127/132/139 127/132/139 127/132/139
-2
39144 R
41888 R
44245 R
47299 R
49604 S
49604 S
49604 S
109/116/125 114/121/129 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139
2
38490 R
41615 R
43906 R
46954 R
49271 R
49604 S
49604 S
107/115/124 114/120/128 118/124/132 123/128/136 126/131/139 127/132/139 127/132/139
6
37924 R
41389 R
43665 R
46665 R
48985 R
49604 S
49604 S
106/114/123 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
10
37465 R
41208 R
43469 R
46431 R
48756 R
49604 S
49604 S
105/113/122 113/119/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
27 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 3500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
41101 R
43632 R
46996 R
49554 R
49604 S
49604 S
49604 S
113/119/128 117/123/131 123/128/136 127/132/139 127/132/139 127/132/139 127/132/139
-30
40847 R
43371 R
46677 R
49217 R
49604 S
49604 S
49604 S
112/119/127 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139 127/132/139
-26
40609 R
43122 R
46373 R
48900 R
49604 S
49604 S
49604 S
112/118/127 116/122/130 122/128/135 126/131/138 127/132/139 127/132/139 127/132/139
-22
40376 R
42875 R
45957 R
48591 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/127/134 125/130/138 127/132/139 127/132/139 127/132/139
-18
40146 R
42626 R
45511 R
48269 R
49604 S
49604 S
49604 S
111/118/126 115/122/130 120/126/134 125/130/137 127/132/139 127/132/139 127/132/139
-14
39921 R
42379 R
45076 R
47942 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 120/125/133 124/130/137 127/132/139 127/132/139 127/132/139
-10
39698 R
42130 R
44650 R
47616 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 119/125/133 124/129/136 127/132/139 127/132/139 127/132/139
-6
39135 R
41884 R
44239 R
47294 R
49604 S
49604 S
49604 S
109/116/125 114/121/129 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139
-2
38388 R
41574 R
43862 R
46902 R
49219 R
49604 S
49604 S
107/115/124 114/120/128 118/124/132 123/128/135 126/131/138 127/132/139 127/132/139
2
37689 R
41298 R
43567 R
46547 R
48870 R
49604 S
49604 S
106/114/123 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
6
37275 R
41076 R
43324 R
46242 R
48588 R
49604 S
49604 S
105/113/122 113/119/128 117/123/131 122/127/135 125/130/138 127/132/139 127/132/139
10
36976 R
40855 R
43080 R
45838 R
48280 R
49604 S
49604 S
104/112/122 112/119/127 116/122/130 121/127/134 125/130/137 127/132/139 127/132/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
28 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 4000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
40838 R
43361 R
46665 R
49204 R
49604 S
49604 S
49604 S
112/119/127 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139 127/132/139
-30
40588 R
43101 R
46346 R
48873 R
49604 S
49604 S
49604 S
112/118/127 116/122/130 122/127/135 126/131/138 127/132/139 127/132/139 127/132/139
-26
40357 R
42854 R
45920 R
48565 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/127/134 125/130/138 127/132/139 127/132/139 127/132/139
-22
40130 R
42608 R
45479 R
48245 R
49604 S
49604 S
49604 S
111/118/126 115/122/130 120/126/134 125/130/137 127/132/139 127/132/139 127/132/139
-18
39901 R
42356 R
45037 R
47913 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 120/125/133 124/130/137 127/132/139 127/132/139 127/132/139
-14
39661 R
42103 R
44605 R
47581 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 119/125/132 124/129/136 127/132/139 127/132/139 127/132/139
-10
39060 R
41852 R
44189 R
47255 R
49571 R
49604 S
49604 S
108/116/125 114/120/129 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139
-6
38446 R
41597 R
43887 R
46932 R
49249 R
49604 S
49604 S
107/115/124 114/120/128 118/124/132 123/128/136 126/131/138 127/132/139 127/132/139
-2
37623 R
41273 R
43539 R
46514 R
48837 R
49604 S
49604 S
106/113/123 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
2
37161 R
40995 R
43235 R
46093 R
48483 R
49604 S
49604 S
105/113/122 112/119/128 117/123/131 121/127/134 125/130/137 127/132/139 127/132/139
6
36886 R
40779 R
42997 R
45701 R
48166 R
49604 S
49604 S
104/112/122 112/119/127 116/122/130 121/126/134 125/130/137 127/132/139 127/132/139
10
36582 R
40522 R
42714 R
45245 R
47785 R
49604 S
49604 S
103/112/121 111/118/127 116/122/130 120/126/133 124/129/137 127/132/139 127/132/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
29 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 4500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
40553 R
43063 R
46301 R
48826 R
49604 S
49604 S
49604 S
112/118/127 116/122/130 122/127/135 126/131/138 127/132/139 127/132/139 127/132/139
-30
40310 R
42804 R
45829 R
48503 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/127/134 125/130/138 127/132/139 127/132/139 127/132/139
-26
40078 R
42552 R
45378 R
48170 R
49604 S
49604 S
49604 S
111/118/126 115/122/130 120/126/134 125/130/137 127/132/139 127/132/139 127/132/139
-22
39852 R
42302 R
44943 R
47841 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 119/125/133 124/129/137 127/132/139 127/132/139 127/132/139
-18
39535 R
42050 R
44516 R
47512 R
49604 S
49604 S
49604 S
109/117/125 115/121/129 119/125/132 124/129/136 127/132/139 127/132/139 127/132/139
-14
38927 R
41796 R
44099 R
47183 R
49500 R
49604 S
49604 S
108/116/125 114/120/129 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139
-10
38302 R
41539 R
43825 R
46857 R
49175 R
49604 S
49604 S
107/115/124 114/120/128 118/124/131 123/128/135 126/131/138 127/132/139 127/132/139
-6
37694 R
41300 R
43569 R
46550 R
48872 R
49604 S
49604 S
106/114/123 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
-2
37136 R
40977 R
43215 R
46060 R
48457 R
49604 S
49604 S
104/113/122 112/119/128 117/123/131 121/127/134 125/130/137 127/132/139 127/132/139
2
36809 R
40713 R
42925 R
45584 R
48068 R
49604 S
49604 S
104/112/122 112/119/127 116/122/130 121/126/134 124/130/137 127/132/139 127/132/139
6
36536 R
40484 R
42672 R
45178 R
47728 R
49604 S
49604 S
103/112/121 111/118/127 116/122/130 120/126/133 124/129/137 127/132/139 127/132/139
10
36080 R
40108 R
42250 R
44531 R
47179 R
49280 R
49604 S
102/111/120 111/118/126 115/121/129 119/125/132 123/129/136 126/131/139 127/132/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
30 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 5000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
40280 R
42771 R
45770 R
48460 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/127/134 125/130/137 127/132/139 127/132/139 127/132/139
-30
40043 R
42514 R
45312 R
48120 R
49604 S
49604 S
49604 S
111/118/126 115/122/130 120/126/133 125/130/137 127/132/139 127/132/139 127/132/139
-26
39810 R
42255 R
44863 R
47780 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 119/125/133 124/129/137 127/132/139 127/132/139 127/132/139
-22
39418 R
42002 R
44434 R
47448 R
49604 S
49604 S
49604 S
109/116/125 114/121/129 119/124/132 123/129/136 127/132/139 127/132/139 127/132/139
-18
38809 R
41746 R
44045 R
47121 R
49437 R
49604 S
49604 S
108/115/124 114/120/129 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139
-14
38183 R
41491 R
43774 R
46796 R
49114 R
49604 S
49604 S
107/114/124 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
-10
37534 R
41239 R
43502 R
46470 R
48794 R
49604 S
49604 S
105/113/123 113/119/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
-6
37189 R
41015 R
43257 R
46130 R
48510 R
49604 S
49604 S
105/113/122 112/119/128 117/123/131 121/127/134 125/130/138 127/132/139 127/132/139
-2
36789 R
40697 R
42907 R
45554 R
48044 R
49604 S
49604 S
104/112/121 112/119/127 116/122/130 120/126/134 124/130/137 127/132/139 127/132/139
2
36486 R
40442 R
42626 R
45106 R
47668 R
49604 S
49604 S
103/111/121 111/118/127 116/122/130 120/126/133 124/129/136 127/132/139 127/132/139
6
36191 R
40199 R
42353 R
44685 R
47311 R
49413 R
49604 S
103/111/121 111/118/126 115/121/129 119/125/133 123/129/136 127/132/139 127/132/139
10
35592 R
39713 R
41801 R
43929 R
46614 R
48700 R
49216 W
101/110/120 110/117/126 114/120/129 118/124/132 122/128/135 125/131/138 126/131/138
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
31 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 5500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
39808 R
42253 R
44860 R
47778 R
49604 S
49604 S
49604 S
110/117/126 115/121/129 119/125/133 124/130/137 127/132/139 127/132/139 127/132/139
-30
39406 R
41997 R
44426 R
47441 R
49604 S
49604 S
49604 S
109/117/125 115/121/129 119/125/132 124/129/136 127/132/139 127/132/139 127/132/139
-26
38784 R
41736 R
44034 R
47108 R
49424 R
49604 S
49604 S
108/116/124 114/120/129 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139
-22
38164 R
41484 R
43766 R
46786 R
49105 R
49604 S
49604 S
107/114/123 114/120/128 118/124/131 123/128/135 126/131/138 127/132/139 127/132/139
-18
37530 R
41237 R
43501 R
46468 R
48793 R
49604 S
49604 S
105/113/123 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
-14
37163 R
40996 R
43236 R
46096 R
48485 R
49604 S
49604 S
105/113/122 113/119/128 117/123/131 121/127/134 125/130/137 127/132/139 127/132/139
-10
36866 R
40761 R
42978 R
45670 R
48140 R
49604 S
49604 S
104/112/122 112/119/127 116/122/130 121/127/134 125/130/137 127/132/139 127/132/139
-6
36604 R
40541 R
42735 R
45278 R
47813 R
49604 S
49604 S
103/112/121 112/118/127 116/122/130 120/126/133 124/130/137 127/132/139 127/132/139
-2
36251 R
40248 R
42408 R
44769 R
47383 R
49485 R
49604 S
103/111/121 111/118/126 115/121/130 119/125/133 123/129/136 127/132/139 127/132/139
2
35928 R
39984 R
42109 R
44322 R
47001 R
49098 R
49604 S
102/111/120 111/118/126 115/121/129 118/124/132 123/128/136 126/131/138 127/132/139
6
35568 R
39694 R
41780 R
43906 R
46588 R
48672 R
49604 S
101/110/120 110/117/126 114/120/129 118/124/132 122/128/135 125/131/138 127/132/139
10
34829 R
38578 R
41232 R
43300 R
45773 R
47920 R
48034 W
100/109/119 108/115/124 113/120/128 117/123/131 121/127/134 124/130/137 124/130/137
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
32 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 6000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
38815 R
41749 R
44048 R
47124 R
49441 R
49604 S
49604 S
108/116/124 114/121/129 118/124/132 123/129/136 127/132/139 127/132/139 127/132/139
-30
38173 R
41487 R
43770 R
46791 R
49110 R
49604 S
49604 S
107/115/124 114/120/128 118/124/131 123/128/135 126/131/138 127/132/139 127/132/139
-26
37521 R
41234 R
43497 R
46464 R
48788 R
49604 S
49604 S
106/114/123 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
-22
37163 R
40996 R
43236 R
46096 R
48485 R
49604 S
49604 S
105/113/122 113/119/128 117/123/131 122/127/134 125/131/137 127/132/139 127/132/139
-18
36871 R
40765 R
42982 R
45677 R
48146 R
49604 S
49604 S
104/112/122 112/119/127 116/122/130 121/127/134 125/130/137 127/132/139 127/132/139
-14
36602 R
40539 R
42733 R
45275 R
47810 R
49604 S
49604 S
104/112/121 112/119/127 116/122/130 120/126/133 124/130/137 127/132/139 127/132/139
-10
36335 R
40317 R
42486 R
44888 R
47484 R
49586 R
49604 S
103/111/121 111/118/127 115/122/130 120/125/133 124/129/136 127/132/139 127/132/139
-6
36064 R
40094 R
42235 R
44508 R
47160 R
49260 R
49604 S
102/111/120 111/118/126 115/121/129 119/125/132 123/129/136 126/132/138 127/132/139
-2
35727 R
39822 R
41924 R
44063 R
46769 R
48860 R
49604 S
102/110/120 110/117/126 114/121/129 118/124/132 123/128/135 126/131/138 127/132/139
2
35385 R
39356 R
41616 R
43726 R
46382 R
48454 R
49604 S
101/110/119 109/117/125 114/120/128 118/124/131 122/128/135 125/131/137 127/132/139
6
34846 R
38601 R
41244 R
43314 R
45793 R
47936 R
49320 W
100/109/119 108/115/124 113/120/128 117/123/131 121/127/134 124/130/137 127/132/139
10
34157 R
37605 R
40698 R
42695 R
44912 R
46853 W 46853 W
99/108/118 106/114/123 112/119/127 116/122/130 120/125/133 123/128/135 123/128/135
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
33 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 6500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
37542 R
41242 R
43505 R
46474 R
48798 R
49604 S
49604 S
106/114/123 113/120/128 117/123/131 122/128/135 126/131/138 127/132/139 127/132/139
-30
37154 R
40990 R
43230 R
46085 R
48476 R
49604 S
49604 S
105/113/122 113/119/128 117/123/131 122/127/134 125/131/137 127/132/139 127/132/139
-26
36852 R
40750 R
42965 R
45649 R
48123 R
49604 S
49604 S
104/113/122 112/119/127 116/123/130 121/127/134 125/130/137 127/132/139 127/132/139
-22
36577 R
40518 R
42710 R
45238 R
47779 R
49604 S
49604 S
104/112/121 112/119/127 116/122/130 120/126/133 124/130/137 127/132/139 127/132/139
-18
36307 R
40294 R
42460 R
44848 R
47450 R
49552 R
49604 S
103/112/121 111/118/127 116/122/130 120/126/133 124/129/136 127/132/139 127/132/139
-14
36040 R
40075 R
42213 R
44475 R
47132 R
49231 R
49604 S
103/111/120 111/118/126 115/121/129 119/125/132 123/129/136 126/132/138 127/132/139
-10
35766 R
39853 R
41960 R
44104 R
46813 R
48906 R
49604 S
102/111/120 111/118/126 115/121/129 118/124/132 123/128/135 126/131/138 127/132/139
-6
35500 R
39576 R
41718 R
43839 R
46511 R
48592 R
49604 S
102/110/120 110/117/126 114/121/129 118/124/131 122/128/135 125/131/138 127/132/139
-2
35132 R
38972 R
41431 R
43522 R
46102 R
48195 R
49604 S
101/110/119 109/116/125 114/120/128 117/123/131 122/127/134 125/130/137 127/132/139
2
34630 R
38306 R
41089 R
43139 R
45539 R
47722 R
49467 W
100/109/119 107/115/124 113/120/128 117/123/131 121/127/134 124/130/137 127/132/139
6
34134 R
37569 R
40677 R
42671 R
44879 R
47161 R
47983 W
99/108/118 106/114/123 112/119/127 116/122/130 120/126/133 123/129/136 125/130/137
10
33631 R
36873 R
40157 R
42068 R
44078 R
45626 W 45626 W
98/107/117 104/113/122 111/118/126 115/121/129 118/124/132 121/127/134 121/127/134
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
34 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 7000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
36877 R
40771 R
42989 R
45687 R
48154 R
49322 W 49322 W
105/113/122 112/119/127 117/123/130 121/127/134 125/130/137 127/132/139 127/132/139
-30
36593 R
40532 R
42725 R
45262 R
47799 R
49322 W 49322 W
104/112/121 112/119/127 116/122/130 120/126/133 124/130/137 127/132/139 127/132/139
-26
36313 R
40299 R
42466 R
44858 R
47458 R
49320 W 49320 W
104/112/121 112/118/127 116/122/130 120/126/133 124/129/136 127/132/139 127/132/139
-22
36031 R
40068 R
42205 R
44463 R
47122 R
49221 R
49313 W
103/111/120 111/118/126 115/122/129 119/125/132 123/129/136 127/132/138 127/132/139
-18
35759 R
39847 R
41954 R
44095 R
46805 R
48898 R
49302 W
102/111/120 111/118/126 115/121/129 118/124/132 123/129/135 126/131/138 127/132/139
-14
35494 R
39564 R
41713 R
43833 R
46504 R
48585 R
49287 W
102/110/120 110/117/126 114/121/129 118/124/131 122/128/135 126/131/138 127/132/139
-10
35185 R
39038 R
41463 R
43558 R
46156 R
48241 R
49256 W
101/110/119 109/116/125 114/120/128 118/124/131 122/128/135 125/131/137 127/132/138
-6
34830 R
38579 R
41233 R
43301 R
45774 R
47920 R
49328 W
101/109/119 108/116/124 113/120/128 117/123/131 121/127/134 125/130/137 127/132/139
-2
34468 R
38074 R
40964 R
42998 R
45337 R
47550 R
49309 W
100/109/118 107/115/123 113/120/128 117/123/130 120/126/133 124/130/136 127/132/139
2
34043 R
37438 R
40592 R
42573 R
44746 R
47046 R
48660 W
99/108/118 106/114/122 112/119/127 116/122/130 119/125/133 123/129/136 126/131/138
6
33620 R
36856 R
40144 R
42053 R
44062 R
46450 R
46645 W
98/107/117 105/113/122 111/118/126 115/121/129 118/124/132 122/128/135 123/128/135
10
33237 R
36197 R
39617 R
41493 R
43437 R
44399 W 44399 W
97/107/117 103/112/121 110/117/126 114/120/128 117/123/131 119/125/132 119/125/132
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
35 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 7500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
36313 R
40299 R
42466 R
44858 R
47458 R
48656 W 48656 W
104/112/121 112/119/127 116/122/130 120/126/133 124/130/136 126/131/138 126/131/138
-30
36030 R
40067 R
42204 R
44461 R
47120 R
48658 W 48658 W
103/111/120 111/118/126 116/122/129 119/125/132 124/129/136 126/131/138 126/131/138
-26
35746 R
39837 R
41942 R
44081 R
46791 R
48651 W 48651 W
103/111/120 111/118/126 115/121/129 119/125/132 123/129/135 126/131/138 126/131/138
-22
35461 R
39501 R
41684 R
43801 R
46467 R
48547 R
48639 W
102/110/119 110/117/125 115/121/129 118/124/131 123/128/135 126/131/138 126/131/138
-18
35146 R
38989 R
41439 R
43531 R
46116 R
48207 R
48628 W
102/110/119 109/116/125 114/120/128 118/124/131 122/128/134 125/131/137 126/131/138
-14
34788 R
38523 R
41204 R
43268 R
45727 R
47880 R
48616 W
101/109/119 108/116/124 114/120/128 117/123/131 121/127/134 125/130/137 126/131/138
-10
34468 R
38074 R
40964 R
42998 R
45337 R
47550 R
48582 W
100/109/118 107/115/123 113/120/128 117/123/130 121/127/133 124/130/136 126/131/138
-6
34207 R
37683 R
40743 R
42747 R
44985 R
47251 R
48699 W
100/108/118 107/114/123 113/119/127 116/123/130 120/126/133 124/129/136 126/131/138
-2
33888 R
37239 R
40437 R
42395 R
44505 R
46839 R
48423 W
99/108/117 106/113/122 112/119/127 116/122/130 119/125/132 123/129/135 126/131/137
2
33532 R
36717 R
40039 R
41929 R
43930 R
46311 R
47355 W
98/107/117 105/113/121 111/118/126 115/121/129 118/124/132 122/128/135 124/129/136
6
33184 R
36094 R
39469 R
41408 R
43339 R
45215 W 45215 W
97/106/116 103/111/120 110/117/125 114/120/128 117/123/131 120/126/133 120/126/133
10
32614 R
35412 R
38557 R
40856 R
42696 R
43153 W 43153 W
96/106/116 102/110/119 108/116/124 113/120/127 116/122/130 117/123/131 117/123/131
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
36 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 8000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
35765 R
39852 R
41960 R
44103 R
46813 R
47990 W 47990 W
103/111/120 111/118/126 115/121/129 119/125/132 123/129/135 125/130/137 125/130/137
-30
35483 R
39543 R
41703 R
43822 R
46491 R
47995 W 47995 W
103/111/120 111/118/125 115/121/129 119/124/131 123/128/135 125/130/137 125/130/137
-26
35159 R
39005 R
41447 R
43540 R
46129 R
47981 W 47981 W
102/110/119 110/117/125 114/121/128 118/124/131 122/128/134 125/130/137 125/130/137
-22
34775 R
38505 R
41195 R
43258 R
45711 R
47867 R
47966 W
101/109/119 109/116/124 114/120/128 118/123/131 122/127/134 125/130/137 125/130/137
-18
34456 R
38056 R
40954 R
42987 R
45320 R
47537 R
47955 W
100/109/118 108/115/123 113/120/127 117/123/130 121/127/133 125/130/136 125/130/137
-14
34184 R
37647 R
40722 R
42723 R
44951 R
47222 R
47946 W
100/108/118 107/114/123 113/119/127 117/123/130 120/126/133 124/129/136 125/130/137
-10
33941 R
37308 R
40491 R
42457 R
44588 R
46911 R
47909 W
99/108/117 106/114/122 113/119/127 116/122/130 120/126/132 124/129/135 125/130/137
-6
33740 R
37034 R
40280 R
42212 R
44263 R
46629 R
48070 W
99/108/117 106/113/122 112/119/127 116/122/129 119/125/132 123/129/135 125/131/137
-2
33454 R
36589 R
39942 R
41818 R
43808 R
46147 R
47538 W
98/107/117 105/112/121 111/118/126 115/121/129 118/124/131 122/128/134 125/130/136
2
33148 R
36022 R
39367 R
41349 R
43271 R
45430 R
46050 W
98/106/116 104/112/120 110/117/125 114/120/128 118/123/131 121/127/134 122/128/134
6
32566 R
35360 R
38491 R
40814 R
42647 R
43784 W 43784 W
97/106/116 102/110/119 109/116/124 113/120/127 117/122/130 118/124/131 118/124/131
10
32001 R
34819 R
37666 R
40262 R
41908 W 41908 W 41908 W
96/105/115 101/110/119 107/114/123 112/119/127 115/121/129 115/121/129 115/121/129
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
37 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: Sea Level Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
42851 R
46174 R
49439 R
49604 S
49604 S
49604 S
49604 S
113/121/130 119/126/135 124/130/139 125/130/139 125/130/139 125/130/139 125/130/139
4
42564 R
45879 R
49064 R
49604 S
49604 S
49604 S
49604 S
112/120/130 119/125/134 124/130/138 125/130/139 125/130/139 125/130/139 125/130/139
8
42275 R
45581 R
48685 R
49604 S
49604 S
49604 S
49604 S
112/120/129 118/125/134 123/129/138 125/130/139 125/130/139 125/130/139 125/130/139
12
41995 R
45292 R
48342 R
49604 S
49604 S
49604 S
49604 S
111/119/129 118/125/133 123/129/137 125/131/139 125/131/139 125/131/139 125/131/139
16
41759 R
45013 R
48037 R
49604 S
49604 S
49604 S
49604 S
111/119/129 117/124/133 122/128/137 125/131/139 125/131/139 125/131/139 125/131/139
20
41558 R
44749 R
47752 R
49604 S
49604 S
49604 S
49604 S
111/119/128 117/124/133 122/128/137 125/130/139 125/130/139 125/130/139 125/130/139
24
41354 R
44476 R
47463 R
49604 S
49604 S
49604 S
49604 S
110/118/128 116/123/132 121/128/136 125/130/139 125/130/139 125/130/139 125/130/139
28
41148 R
44201 R
47174 R
49604 S
49604 S
49604 S
49604 S
110/118/128 116/123/132 121/127/136 125/131/139 125/131/139 125/131/139 125/131/139
32
40948 R
43917 R
46894 R
49604 S
49604 S
49604 S
49604 S
109/118/128 115/122/132 120/127/136 125/131/139 125/131/139 125/131/139 125/131/139
36
40688 R
43534 R
46530 R
49423 R
49604 S
49604 S
49604 S
109/117/127 115/122/131 120/126/135 125/130/139 125/131/139 125/131/139 125/131/139
40
40242 R
42869 R
45872 R
48558 R
49604 S
49604 S
49604 S
109/117/126 114/121/130 119/126/134 124/129/138 126/131/139 126/131/139 126/131/139
44
39611 R
41982 R
44963 R
47628 R
49604 S
49604 S
49604 S
109/117/126 113/120/129 119/125/133 123/129/136 126/131/139 126/131/139 126/131/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
38 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
42400 R
45710 R
48849 R
49604 S
49604 S
49604 S
49604 S
112/120/130 118/125/134 124/129/138 125/131/139 125/131/139 125/131/139 125/131/139
4
42113 R
45414 R
48476 R
49604 S
49604 S
49604 S
49604 S
112/120/129 118/125/134 123/129/137 125/131/139 125/131/139 125/131/139 125/131/139
8
41838 R
45116 R
48149 R
49604 S
49604 S
49604 S
49604 S
111/119/129 117/124/133 123/128/137 125/131/139 125/131/139 125/131/139 125/131/139
12
41623 R
44835 R
47845 R
49604 S
49604 S
49604 S
49604 S
111/119/128 117/124/133 122/128/137 125/131/139 125/131/139 125/131/139 125/131/139
16
41419 R
44564 R
47555 R
49604 S
49604 S
49604 S
49604 S
110/119/128 116/124/132 122/128/136 125/131/139 125/131/139 125/131/139 125/131/139
20
41217 R
44293 R
47271 R
49604 S
49604 S
49604 S
49604 S
110/118/128 116/123/132 121/127/136 125/131/139 125/131/139 125/131/139 125/131/139
24
41016 R
44017 R
46989 R
49604 S
49604 S
49604 S
49604 S
110/118/128 115/123/132 121/127/136 125/131/139 125/131/139 125/131/139 125/131/139
28
40816 R
43724 R
46709 R
49604 S
49604 S
49604 S
49604 S
109/118/127 115/122/131 120/127/135 125/131/139 125/131/139 125/131/139 125/131/139
32
40621 R
43436 R
46438 R
49295 R
49604 S
49604 S
49604 S
109/117/127 114/122/131 120/126/135 125/130/139 125/131/139 125/131/139 125/131/139
36
40304 R
42962 R
45967 R
48679 R
49604 S
49604 S
49604 S
109/117/127 114/121/130 119/126/134 124/129/138 125/131/139 125/131/139 125/131/139
40
39839 R
42257 R
45245 R
47910 R
49604 S
49604 S
49604 S
109/117/126 113/121/129 119/125/133 123/129/137 126/131/139 126/131/139 126/131/139
44
38147 R
41374 R
44161 R
46845 R
49475 R
49604 S
49604 S
106/114/123 113/120/128 118/124/132 122/128/135 126/131/139 127/132/139 127/132/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
39 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 1000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
41962 R
45258 R
48304 R
49604 S
49604 S
49604 S
49604 S
112/120/129 118/125/133 123/129/137 125/131/139 125/131/139 125/131/139 125/131/139
4
41720 R
44962 R
47982 R
49604 S
49604 S
49604 S
49604 S
111/119/129 117/124/133 123/128/137 125/131/139 125/131/139 125/131/139 125/131/139
8
41495 R
44664 R
47662 R
49604 S
49604 S
49604 S
49604 S
111/119/128 117/124/133 122/128/136 125/131/139 125/131/139 125/131/139 125/131/139
12
41289 R
44390 R
47372 R
49604 S
49604 S
49604 S
49604 S
110/119/128 116/123/132 122/128/136 125/131/139 125/131/139 125/131/139 125/131/139
16
41094 R
44127 R
47097 R
49604 S
49604 S
49604 S
49604 S
110/118/128 116/123/132 121/127/136 125/131/139 125/131/139 125/131/139 125/131/139
20
40890 R
43833 R
46813 R
49604 S
49604 S
49604 S
49604 S
110/118/127 115/123/131 121/127/135 125/131/139 125/131/139 125/131/139 125/131/139
24
40693 R
43542 R
46537 R
49433 R
49604 S
49604 S
49604 S
109/118/127 115/122/131 120/127/135 125/130/139 125/131/139 125/131/139 125/131/139
28
40497 R
43250 R
46262 R
49055 R
49604 S
49604 S
49604 S
109/117/127 114/122/131 120/126/135 124/130/138 125/131/139 125/131/139 125/131/139
32
40305 R
42964 R
45969 R
48683 R
49604 S
49604 S
49604 S
108/117/127 114/121/130 119/126/134 124/129/138 125/131/139 125/131/139 125/131/139
36
39937 R
42406 R
45398 R
48064 R
49604 S
49604 S
49604 S
108/117/126 113/121/130 119/125/134 123/129/137 126/131/139 126/131/139 126/131/139
40
38813 R
41651 R
44543 R
47215 R
49604 S
49604 S
49604 S
107/115/124 113/120/129 118/124/132 123/128/136 126/131/139 126/131/139 126/131/139
44
36899 R
40828 R
43344 R
46090 R
48433 R
49604 S
49604 S
104/112/122 112/119/127 117/123/131 121/127/135 125/130/137 127/132/139 127/132/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
40 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 1500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
41588 R
44788 R
47794 R
49604 S
49604 S
49604 S
49604 S
111/119/128 117/124/133 122/128/137 125/131/139 125/131/139 125/131/139 125/131/139
4
41367 R
44494 R
47481 R
49604 S
49604 S
49604 S
49604 S
111/119/128 117/124/132 122/128/136 125/131/139 125/131/139 125/131/139 125/131/139
8
41151 R
44204 R
47178 R
49604 S
49604 S
49604 S
49604 S
110/118/128 116/123/132 121/128/136 125/131/139 125/131/139 125/131/139 125/131/139
12
40954 R
43925 R
46901 R
49604 S
49604 S
49604 S
49604 S
110/118/128 116/123/132 121/127/136 125/131/139 125/131/139 125/131/139 125/131/139
16
40758 R
43638 R
46628 R
49558 R
49604 S
49604 S
49604 S
110/118/127 115/122/131 120/127/135 125/131/139 125/131/139 125/131/139 125/131/139
20
40559 R
43344 R
46352 R
49176 R
49604 S
49604 S
49604 S
109/117/127 115/122/131 120/126/135 125/130/138 125/131/139 125/131/139 125/131/139
24
40364 R
43053 R
46060 R
48798 R
49604 S
49604 S
49604 S
109/117/127 114/121/130 119/126/134 124/129/138 125/131/139 125/131/139 125/131/139
28
40172 R
42763 R
45764 R
48436 R
49604 S
49604 S
49604 S
108/117/126 114/121/130 119/126/134 124/129/137 125/131/139 125/131/139 125/131/139
32
39948 R
42424 R
45416 R
48082 R
49604 S
49604 S
49604 S
108/117/126 113/121/130 118/125/134 123/129/137 125/131/139 125/131/139 125/131/139
36
39183 R
41797 R
44743 R
47411 R
49604 S
49604 S
49604 S
107/116/125 113/120/129 118/125/133 123/128/136 126/131/139 126/131/139 126/131/139
40
37484 R
41078 R
43723 R
46452 R
48904 R
49604 S
49604 S
105/113/122 112/119/128 117/123/131 122/127/135 126/130/138 127/132/139 127/132/139
44
35777 R
40301 R
42569 R
45237 R
47603 R
49604 S
49604 S
102/111/120 111/118/127 116/122/130 120/126/133 124/129/136 127/132/139 127/132/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
41 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 2000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
41242 R
44327 R
47306 R
49604 S
49604 S
49604 S
49604 S
111/119/128 117/124/132 122/128/136 125/131/139 125/131/139 125/131/139 125/131/139
4
41027 R
44033 R
47004 R
49604 S
49604 S
49604 S
49604 S
110/118/128 116/123/132 121/127/136 125/131/139 125/131/139 125/131/139 125/131/139
8
40822 R
43732 R
46717 R
49604 S
49604 S
49604 S
49604 S
110/118/127 116/123/131 121/127/135 125/131/139 125/131/139 125/131/139 125/131/139
12
40632 R
43452 R
46453 R
49317 R
49604 S
49604 S
49604 S
110/118/127 115/122/131 120/127/135 125/130/139 125/131/139 125/131/139 125/131/139
16
40436 R
43161 R
46170 R
48938 R
49604 S
49604 S
49604 S
109/117/127 114/122/131 120/126/135 124/130/138 125/131/139 125/131/139 125/131/139
20
40240 R
42866 R
45868 R
48554 R
49604 S
49604 S
49604 S
109/117/126 114/121/130 119/126/134 124/129/138 125/131/139 125/131/139 125/131/139
24
40047 R
42574 R
45570 R
48239 R
49604 S
49604 S
49604 S
108/117/126 113/121/130 119/125/134 123/129/137 125/131/139 125/131/139 125/131/139
28
39859 R
42287 R
45276 R
47941 R
49604 S
49604 S
49604 S
108/116/126 113/120/129 118/125/133 123/129/137 126/131/139 126/131/139 126/131/139
32
39401 R
41880 R
44856 R
47523 R
49604 S
49604 S
49604 S
107/116/125 112/120/129 118/124/133 122/128/136 126/131/139 126/131/139 126/131/139
36
37959 R
41292 R
44044 R
46737 R
49318 R
49604 S
49604 S
105/114/123 112/119/128 117/124/132 122/128/135 126/131/139 126/131/139 126/131/139
40
36288 R
40560 R
42944 R
45649 R
48007 R
49604 S
49604 S
102/111/121 111/119/127 116/122/130 121/127/134 125/130/137 127/132/139 127/132/139
44
34689 R
39786 R
41869 R
44461 R
46832 R
49100 R
49245 W
100/109/119 111/118/126 115/121/129 119/125/132 123/129/135 127/131/138 127/132/138
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
42 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 2500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
40893 R
43837 R
46817 R
49604 S
49604 S
49604 S
49604 S
110/118/127 116/123/131 121/127/135 126/131/139 126/131/139 126/131/139 126/131/139
4
40682 R
43526 R
46523 R
49413 R
49604 S
49604 S
49604 S
110/118/127 115/122/131 121/127/135 125/131/139 126/131/139 126/131/139 126/131/139
8
40483 R
43231 R
46241 R
49029 R
49604 S
49604 S
49604 S
110/118/127 115/122/131 120/127/135 125/130/138 126/131/139 126/131/139 126/131/139
12
40296 R
42951 R
45955 R
48665 R
49604 S
49604 S
49604 S
109/117/127 114/122/130 120/126/134 124/130/138 126/131/139 126/131/139 126/131/139
16
40102 R
42658 R
45655 R
48325 R
49604 S
49604 S
49604 S
109/117/126 114/121/130 119/126/134 124/129/137 126/131/139 126/131/139 126/131/139
20
39909 R
42364 R
45355 R
48020 R
49604 S
49604 S
49604 S
108/117/126 113/121/130 119/125/134 123/129/137 126/131/139 126/131/139 126/131/139
24
39720 R
42074 R
45058 R
47723 R
49604 S
49604 S
49604 S
108/116/126 113/120/129 118/125/133 123/128/137 126/131/139 126/131/139 126/131/139
28
39214 R
41809 R
44759 R
47427 R
49604 S
49604 S
49604 S
107/115/125 112/120/129 118/124/133 122/128/136 126/131/139 126/131/139 126/131/139
32
38245 R
41416 R
44219 R
46901 R
49556 R
49604 S
49604 S
105/114/124 112/119/128 117/124/132 122/128/136 126/131/139 126/131/139 126/131/139
36
36693 R
40742 R
43214 R
45947 R
48295 R
49604 S
49604 S
103/112/121 111/119/127 116/123/131 121/127/134 125/130/137 127/132/139 127/132/139
40
35309 R
40027 R
42188 R
44818 R
47189 R
49604 S
49604 S
101/110/119 111/118/126 115/121/129 120/126/133 124/129/136 127/132/139 127/132/139
44
33524 R
38645 R
41302 R
43675 R
46034 R
48129 R
48300 W
98/107/117 109/116/124 114/121/128 118/124/131 122/128/134 126/130/137 126/131/137
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
43 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 3000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
40557 R
43341 R
46349 R
49172 R
49604 S
49604 S
49604 S
110/118/127 115/122/131 121/127/135 125/130/138 126/131/139 126/131/139 126/131/139
4
40348 R
43028 R
46035 R
48766 R
49604 S
49604 S
49604 S
110/118/127 115/122/130 120/126/134 125/130/138 126/131/139 126/131/139 126/131/139
8
40160 R
42745 R
45744 R
48417 R
49604 S
49604 S
49604 S
109/117/126 114/121/130 119/126/134 124/129/137 126/131/139 126/131/139 126/131/139
12
39973 R
42461 R
45454 R
48121 R
49604 S
49604 S
49604 S
109/117/126 114/121/130 119/125/134 124/129/137 126/131/139 126/131/139 126/131/139
16
39781 R
42167 R
45153 R
47818 R
49604 S
49604 S
49604 S
108/117/126 113/120/129 118/125/133 123/129/137 126/131/139 126/131/139 126/131/139
20
39394 R
41877 R
44853 R
47519 R
49604 S
49604 S
49604 S
108/116/125 113/120/129 118/125/133 123/128/136 126/131/139 126/131/139 126/131/139
24
38837 R
41660 R
44557 R
47228 R
49604 S
49604 S
49604 S
106/115/124 112/120/129 117/124/132 122/128/136 126/131/139 126/131/139 126/131/139
28
38296 R
41438 R
44249 R
46930 R
49597 R
49604 S
49604 S
105/114/124 112/119/128 117/124/132 122/128/136 126/131/139 126/131/139 126/131/139
32
37117 R
40922 R
43487 R
46237 R
48599 R
49604 S
49604 S
103/112/122 111/119/127 116/123/131 121/127/135 125/130/138 126/131/139 126/131/139
36
35649 R
40229 R
42469 R
45126 R
47494 R
49604 S
49604 S
101/110/120 111/118/126 115/122/130 120/126/133 124/129/136 127/132/139 127/132/139
40
34049 R
39264 R
41579 R
44065 R
46435 R
48548 R
49392 W
99/108/118 110/117/125 114/121/128 119/125/132 123/128/135 126/131/138 127/132/139
44
32704 R
37491 R
40750 R
42935 R
45239 R
47340 R
47364 W
97/106/116 108/114/122 113/120/127 117/123/130 121/127/133 125/130/136 125/130/136
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
44 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 3500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
40221 R
42837 R
45839 R
48516 R
49604 S
49604 S
49604 S
109/117/126 114/122/130 120/126/134 124/130/137 126/131/139 126/131/139 126/131/139
4
40021 R
42535 R
45530 R
48197 R
49604 S
49604 S
49604 S
109/117/126 114/121/130 119/126/134 124/129/137 126/131/139 126/131/139 126/131/139
8
39835 R
42251 R
45239 R
47904 R
49604 S
49604 S
49604 S
109/117/126 113/121/129 119/125/133 123/129/137 126/131/139 126/131/139 126/131/139
12
39575 R
41964 R
44945 R
47611 R
49604 S
49604 S
49604 S
108/116/126 113/120/129 118/125/133 123/128/136 126/131/139 126/131/139 126/131/139
16
39002 R
41726 R
44646 R
47316 R
49604 S
49604 S
49604 S
107/115/125 112/120/129 118/124/133 122/128/136 126/131/139 126/131/139 126/131/139
20
38461 R
41507 R
44345 R
47023 R
49604 S
49604 S
49604 S
106/114/124 112/120/128 117/124/132 122/128/136 126/131/139 126/131/139 126/131/139
24
37961 R
41293 R
44045 R
46738 R
49320 R
49604 S
49604 S
105/114/123 112/119/128 117/124/132 121/127/135 126/131/139 126/131/139 126/131/139
28
37338 R
41016 R
43630 R
46370 R
48784 R
49604 S
49604 S
103/113/122 111/119/128 116/123/131 121/127/135 125/130/138 126/131/139 126/131/139
32
35940 R
40387 R
42693 R
45373 R
47737 R
49604 S
49604 S
101/110/120 111/118/127 115/122/130 120/126/134 124/129/137 127/132/139 127/132/139
36
34481 R
39701 R
41779 R
44338 R
46708 R
48927 R
49604 S
99/109/119 110/117/126 114/121/129 119/125/132 123/128/135 126/131/138 127/132/139
40
33047 R
38010 R
41004 R
43269 R
45598 R
47698 R
48448 W
98/106/116 108/115/123 113/120/128 117/124/131 122/127/134 125/130/136 126/131/137
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
45 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 4000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
39898 R
42346 R
45337 R
48002 R
49604 S
49604 S
49604 S
109/117/126 114/121/129 119/126/134 124/129/137 126/131/139 126/131/139 126/131/139
4
39706 R
42052 R
45035 R
47700 R
49604 S
49604 S
49604 S
109/117/126 113/121/129 119/125/133 123/129/136 126/131/139 126/131/139 126/131/139
8
39181 R
41796 R
44742 R
47410 R
49604 S
49604 S
49604 S
108/116/125 113/120/129 118/125/133 123/128/136 126/131/139 126/131/139 126/131/139
12
38643 R
41582 R
44449 R
47124 R
49604 S
49604 S
49604 S
106/115/124 112/120/128 118/124/132 122/128/136 126/131/139 126/131/139 126/131/139
16
38132 R
41367 R
44152 R
46837 R
49463 R
49604 S
49604 S
105/114/123 112/119/128 117/124/132 122/128/135 126/131/139 126/131/139 126/131/139
20
37640 R
41149 R
43830 R
46547 R
49042 R
49604 S
49604 S
104/113/123 112/119/128 117/123/131 121/127/135 125/130/138 126/131/139 126/131/139
24
37161 R
40941 R
43516 R
46266 R
48635 R
49604 S
49604 S
103/112/122 111/119/128 116/123/131 121/127/135 125/130/138 126/131/139 126/131/139
28
36273 R
40553 R
42934 R
45638 R
47996 R
49604 S
49604 S
101/111/121 111/118/127 115/122/130 120/126/134 124/129/137 126/132/139 126/132/139
32
34903 R
39869 R
41975 R
44583 R
46955 R
49273 R
49604 S
99/109/119 110/118/126 114/121/129 119/125/132 123/128/136 127/131/138 127/132/139
36
33411 R
38501 R
41236 R
43584 R
45935 R
48032 R
49386 W
98/107/117 108/116/124 113/120/128 118/124/131 122/127/134 125/130/137 127/132/139
40
32364 R
37020 R
40446 R
42547 R
44822 R
46922 R
47510 W
97/105/115 106/113/122 113/119/127 117/123/130 121/126/133 124/129/136 125/130/136
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
46 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 4500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
39379 R
41872 R
44845 R
47512 R
49604 S
49604 S
49604 S
108/116/125 113/120/129 119/125/133 123/129/136 126/132/139 126/132/139 126/132/139
4
38832 R
41659 R
44554 R
47226 R
49604 S
49604 S
49604 S
107/115/124 113/120/129 118/124/132 123/128/136 126/132/139 126/132/139 126/132/139
8
38312 R
41445 R
44259 R
46940 R
49604 S
49604 S
49604 S
106/114/124 112/120/128 117/124/132 122/128/136 126/131/139 126/131/139 126/131/139
12
37825 R
41233 R
43956 R
46658 R
49204 R
49604 S
49604 S
105/114/123 112/119/128 117/124/132 122/128/135 126/131/138 126/132/139 126/132/139
16
37351 R
41022 R
43638 R
46378 R
48795 R
49604 S
49604 S
104/113/122 111/119/128 116/123/131 121/127/135 125/130/138 126/132/139 126/132/139
20
36861 R
40812 R
43321 R
46064 R
48408 R
49604 S
49604 S
103/112/122 111/119/127 116/123/131 121/127/134 125/130/137 126/132/139 126/132/139
24
36235 R
40535 R
42907 R
45608 R
47967 R
49604 S
49604 S
101/111/121 111/118/127 115/122/130 120/126/134 124/129/137 126/132/139 126/132/139
28
35292 R
40017 R
42174 R
44802 R
47173 R
49584 R
49604 S
100/109/119 110/118/126 114/121/129 119/125/133 123/128/136 127/132/139 127/132/139
32
33680 R
38836 R
41389 R
43796 R
46164 R
48256 R
49604 S
98/108/118 109/116/124 113/120/128 118/124/131 122/128/135 125/130/137 127/132/139
36
32591 R
37339 R
40656 R
42814 R
45108 R
47210 R
48413 W
97/106/116 107/114/122 113/119/127 117/123/130 121/126/133 124/129/136 126/131/137
40
32149 R
36227 R
39851 R
41833 R
44045 R
46116 R
46525 W
97/105/115 105/112/121 112/119/126 116/122/129 120/125/132 123/128/135 124/129/135
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
47 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 5000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
38501 R
41524 R
44369 R
47046 R
49604 S
49604 S
49604 S
107/115/124 113/120/128 118/124/132 123/128/136 127/132/139 127/132/139 127/132/139
4
38025 R
41321 R
44087 R
46775 R
49374 R
49604 S
49604 S
106/114/123 112/120/128 117/124/132 122/128/135 126/131/139 127/132/139 127/132/139
8
37551 R
41109 R
43769 R
46493 R
48963 R
49604 S
49604 S
105/113/123 112/119/128 117/123/131 122/127/135 126/130/138 127/132/139 127/132/139
12
37064 R
40899 R
43452 R
46201 R
48554 R
49604 S
49604 S
103/112/122 111/119/127 116/123/131 121/127/135 125/130/138 127/132/139 127/132/139
16
36591 R
40698 R
43148 R
45874 R
48225 R
49604 S
49604 S
102/112/121 111/119/127 116/122/131 121/127/134 124/130/137 127/132/139 127/132/139
20
36162 R
40499 R
42855 R
45551 R
47911 R
49604 S
49604 S
101/111/121 111/118/127 115/122/130 120/126/134 124/129/137 127/132/139 127/132/139
24
35499 R
40143 R
42347 R
44993 R
47362 R
49604 S
49604 S
100/110/120 110/118/126 114/121/129 119/125/133 123/129/136 127/132/139 127/132/139
28
34004 R
39213 R
41557 R
44034 R
46405 R
48506 R
49604 S
98/108/118 109/116/125 113/120/128 118/124/132 122/128/135 125/130/137 127/132/139
32
32809 R
37657 R
40832 R
43042 R
45354 R
47455 R
49179 W
97/106/116 107/114/123 113/120/127 117/123/130 121/127/134 124/129/136 127/132/138
36
32112 R
36529 R
40092 R
42112 R
44355 R
46447 R
47454 W
96/105/115 105/113/121 112/119/126 116/122/129 120/125/132 123/129/135 125/130/136
40
32072 R
35579 R
38834 R
41222 R
43284 R
45313 R
45567 W
97/105/114 104/111/120 111/117/124 115/121/128 119/124/131 122/127/133 122/128/134
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
48 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 5500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
37514 R
41092 R
43744 R
46470 R
48931 R
49604 S
49604 S
105/113/123 112/119/128 117/124/131 122/128/135 126/131/138 127/132/139 127/132/139
4
37045 R
40891 R
43440 R
46189 R
48537 R
49604 S
49604 S
104/112/122 112/119/127 116/123/131 121/127/135 125/130/138 127/132/139 127/132/139
8
36574 R
40691 R
43137 R
45862 R
48213 R
49604 S
49604 S
103/112/121 111/119/127 116/123/131 121/127/134 125/130/137 127/132/139 127/132/139
12
36146 R
40492 R
42844 R
45539 R
47899 R
49604 S
49604 S
102/111/121 111/118/127 115/122/130 120/126/134 124/129/137 127/132/139 127/132/139
16
35762 R
40293 R
42558 R
45224 R
47591 R
49604 S
49604 S
101/110/120 111/118/127 115/122/130 120/126/133 124/129/136 127/132/139 127/132/139
20
35417 R
40094 R
42280 R
44918 R
47289 R
49604 S
49604 S
100/110/119 110/118/126 114/121/129 119/125/133 123/129/136 127/132/139 127/132/139
24
34311 R
39550 R
41703 R
44234 R
46604 R
48781 R
49604 S
98/108/119 109/117/125 113/120/129 118/124/132 122/128/135 126/130/138 127/132/139
28
33004 R
37948 R
40974 R
43230 R
45555 R
47656 R
49604 S
97/106/117 107/114/123 113/120/128 117/123/131 121/127/134 124/129/136 127/132/139
32
32166 R
36717 R
40232 R
42283 R
44538 R
46633 R
48183 W
96/105/115 105/113/121 112/119/126 116/122/129 120/126/132 123/129/135 126/130/137
36
32119 R
35781 R
39221 R
41423 R
43530 R
45571 R
46408 W
97/105/115 104/112/120 111/118/125 115/121/128 119/124/131 122/127/134 124/129/135
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
49 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 6000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
36573 R
40690 R
43136 R
45861 R
48212 R
49604 S
49604 S
103/112/121 112/119/127 116/123/131 121/127/134 125/130/137 127/132/139 127/132/139
4
36156 R
40496 R
42850 R
45546 R
47907 R
49604 S
49604 S
102/111/121 111/118/127 116/122/130 120/126/134 124/129/137 127/132/139 127/132/139
8
35770 R
40297 R
42563 R
45230 R
47597 R
49604 S
49604 S
101/110/120 111/118/127 115/122/130 120/126/133 124/129/136 127/132/139 127/132/139
12
35420 R
40096 R
42282 R
44921 R
47292 R
49604 S
49604 S
100/110/119 110/118/126 115/121/129 119/125/133 123/129/136 127/132/139 127/132/139
16
34971 R
39895 R
42009 R
44621 R
46992 R
49326 R
49604 S
99/109/119 110/118/126 114/121/129 119/125/133 123/128/136 127/131/139 127/132/139
20
34469 R
39696 R
41774 R
44331 R
46701 R
48917 R
49604 S
99/109/119 110/117/126 114/121/129 118/125/132 122/128/135 126/131/138 127/132/139
24
33294 R
38349 R
41165 R
43487 R
45831 R
47929 R
49604 S
97/107/118 107/115/124 113/120/128 117/123/131 121/127/134 125/130/137 127/132/139
28
32315 R
36947 R
40396 R
42485 R
44755 R
46854 R
48855 R
96/106/116 105/113/122 112/119/127 116/122/130 120/126/133 123/129/135 127/131/138
32
32144 R
35969 R
39574 R
41602 R
43752 R
45806 R
47155 W
96/105/115 104/112/120 111/118/126 115/121/128 119/125/131 122/128/134 125/129/136
36
31907 R
35131 R
38005 R
40773 R
42754 R
44753 R
45393 W
97/104/114 103/111/119 110/116/123 114/120/127 118/123/130 121/126/133 122/127/134
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
50 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 6500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
35732 R
40276 R
42534 R
45198 R
47565 R
49604 S
49604 S
101/110/120 111/118/127 115/122/130 120/126/133 124/129/136 127/132/139 127/132/139
4
35386 R
40075 R
42254 R
44890 R
47260 R
49604 S
49604 S
101/110/119 111/118/126 115/121/129 119/125/133 123/129/136 127/132/139 127/132/139
8
34911 R
39872 R
41979 R
44587 R
46959 R
49279 R
49604 S
100/109/119 110/118/126 114/121/129 119/125/132 123/128/136 127/131/138 127/132/139
12
34407 R
39650 R
41747 R
44293 R
46663 R
48864 R
49604 S
99/109/119 110/117/126 114/121/129 118/125/132 122/128/135 126/131/138 127/132/139
16
33956 R
39159 R
41533 R
44000 R
46372 R
48470 R
49604 S
98/108/118 109/116/125 113/120/128 118/124/132 122/128/135 125/130/137 127/132/139
20
33424 R
38518 R
41244 R
43594 R
45947 R
48044 R
49604 S
97/107/118 108/115/124 113/120/128 117/124/131 121/127/134 125/130/137 127/132/139
24
32494 R
37206 R
40571 R
42705 R
44991 R
47092 R
49170 R
96/106/116 105/113/122 112/119/127 116/122/130 120/126/133 124/129/136 127/131/138
28
32151 R
36151 R
39788 R
41767 R
43961 R
46026 R
47918 R
96/105/115 104/112/120 111/118/126 115/121/129 119/125/132 122/128/134 126/130/137
32
31980 R
35322 R
38323 R
40948 R
42958 R
44969 R
46149 W
96/105/115 103/111/119 110/116/124 114/120/128 118/124/130 121/127/133 123/128/135
36
31528 R
34503 R
37039 R
40083 R
41984 R
43930 R
44374 W
96/104/113 103/110/118 108/114/122 114/119/126 117/122/129 120/125/132 121/126/132
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
51 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 7000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
34906 R
39870 R
41976 R
44584 R
46956 R
49275 R
49604 S
100/109/119 110/118/126 114/121/129 119/125/132 123/129/136 127/131/138 127/132/139
4
34388 R
39631 R
41738 R
44282 R
46652 R
48848 R
49604 S
99/109/119 110/117/126 114/121/129 119/125/132 123/128/135 126/131/138 127/132/139
8
33935 R
39135 R
41522 R
43984 R
46358 R
48454 R
49604 S
98/108/118 109/116/125 114/120/128 118/124/132 122/128/135 126/130/137 127/132/139
12
33535 R
38658 R
41308 R
43683 R
46042 R
48137 R
49604 S
98/107/118 108/116/124 113/120/128 118/124/131 122/127/134 125/130/137 127/132/139
16
33180 R
38195 R
41092 R
43388 R
45726 R
47825 R
49604 S
97/107/117 107/115/124 113/120/128 117/123/131 121/127/134 125/130/137 127/132/139
20
32673 R
37448 R
40725 R
42902 R
45203 R
47305 R
49455 R
97/106/117 106/114/122 112/119/127 116/123/130 120/126/133 124/129/136 127/132/139
24
32135 R
36382 R
39977 R
41975 R
44208 R
46296 R
48186 R
96/105/116 104/112/121 111/118/126 115/121/129 119/125/132 123/128/135 126/130/137
28
32046 R
35496 R
38671 R
41136 R
43180 R
45203 R
46954 W
96/105/115 103/111/120 110/116/124 114/121/128 118/124/131 121/127/133 124/129/136
32
31658 R
34665 R
37271 R
40294 R
42214 R
44184 R
45133 W
96/104/114 102/110/118 108/114/122 114/120/127 117/123/129 120/126/132 122/127/133
36
30928 R
33830 R
36363 R
39192 R
41239 R
43092 R
43374 W
95/103/113 102/109/117 107/113/121 113/118/125 116/121/128 119/124/130 120/125/131
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
52 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 7500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
33897 R
39091 R
41503 R
43957 R
46332 R
48425 R
49550 W
98/108/118 109/117/125 114/121/128 118/124/132 122/128/135 126/130/137 127/132/139
4
33490 R
38602 R
41282 R
43648 R
46004 R
48100 R
49542 W
98/107/117 108/116/124 113/120/128 118/124/131 122/127/134 125/130/137 127/132/139
8
33137 R
38137 R
41065 R
43351 R
45685 R
47785 R
49525 W
97/107/117 107/115/123 113/120/128 117/123/131 121/127/134 125/130/137 127/132/139
12
32830 R
37689 R
40848 R
43063 R
45376 R
47477 R
49506 W
97/106/117 107/114/123 113/119/127 117/123/130 121/126/134 124/129/136 127/132/139
16
32559 R
37295 R
40628 R
42778 R
45070 R
47171 R
49275 R
96/106/116 106/113/122 112/119/127 116/123/130 120/126/133 124/129/136 127/132/138
20
32099 R
36590 R
40138 R
42168 R
44415 R
46508 R
48419 R
96/105/116 104/112/121 111/118/126 115/122/129 119/125/132 123/128/135 126/130/137
24
32096 R
35671 R
39013 R
41316 R
43397 R
45432 R
47322 R
96/105/115 103/111/120 110/117/125 114/121/128 118/124/131 121/127/134 125/129/136
28
31753 R
34814 R
37467 R
40463 R
42402 R
44382 R
45926 W
96/104/114 102/110/119 108/115/122 113/120/127 117/123/130 120/126/132 123/128/134
32
31092 R
34016 R
36548 R
39520 R
41443 R
43321 R
44110 W
95/103/113 102/109/117 107/113/121 113/119/125 116/122/128 119/125/131 120/126/132
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
53 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 8000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
33128 R
38124 R
41059 R
43343 R
45677 R
47776 R
49009 W
97/107/117 108/115/123 113/120/128 117/124/131 121/127/134 125/130/137 127/131/138
4
32814 R
37665 R
40836 R
43047 R
45359 R
47461 R
48996 W
97/106/116 107/114/123 113/120/127 117/123/130 121/127/134 124/129/136 127/131/138
8
32546 R
37277 R
40617 R
42763 R
45054 R
47156 R
48978 W
96/106/116 106/114/122 112/119/127 116/123/130 120/126/133 124/129/136 127/131/138
12
32317 R
36950 R
40398 R
42487 R
44758 R
46857 R
48858 R
96/106/116 105/113/122 112/119/127 116/122/130 120/126/133 123/129/135 127/131/138
16
32116 R
36634 R
40171 R
42208 R
44458 R
46552 R
48467 R
96/105/116 105/112/121 112/119/126 115/122/129 119/125/132 123/128/135 126/131/137
20
32137 R
35904 R
39453 R
41541 R
43676 R
45726 R
47618 R
96/105/116 103/111/120 110/117/125 114/121/128 118/124/131 122/127/134 125/130/136
24
31856 R
35013 R
37812 R
40664 R
42629 R
44622 R
46497 R
96/105/115 102/110/119 108/115/123 113/120/127 117/123/130 120/126/133 124/129/135
28
31270 R
34216 R
36746 R
39792 R
41661 R
43567 R
44895 W
95/104/113 102/109/118 107/114/121 113/119/126 116/122/129 119/125/131 122/127/133
32
30215 R
33345 R
35878 R
38384 R
40706 R
42495 R
43087 W
94/106/112 101/108/116 106/113/120 112/117/124 116/121/127 119/123/130 119/124/130
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
54 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: Sea Level Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
45346 R
48975 R
49604 S
49604 S
49604 S
49604 S
49604 S
118/125/134 124/129/138 125/130/139 125/130/139 125/130/139 125/130/139 125/130/139
-30
45042 R
48586 R
49604 S
49604 S
49604 S
49604 S
49604 S
117/124/133 123/129/138 125/130/139 125/130/139 125/130/139 125/130/139 125/130/139
-26
44741 R
48219 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/124/133 123/128/137 125/130/139 125/130/139 125/130/139 125/130/139 125/130/139
-22
44447 R
47872 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/123/132 122/128/137 125/130/139 125/130/139 125/130/139 125/130/139 125/130/139
-18
44159 R
47536 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/123/132 121/128/136 125/130/139 125/130/139 125/130/139 125/130/139 125/130/139
-14
43853 R
47206 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/122/132 121/127/136 125/130/139 125/130/139 125/130/139 125/130/139 125/130/139
-10
43541 R
46880 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/122/131 120/127/136 125/130/139 125/130/139 125/130/139 125/130/139 125/130/139
-6
43252 R
46582 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/121/131 120/126/135 125/130/139 125/130/139 125/130/139 125/130/139 125/130/139
-2
42983 R
46309 R
49604 S
49604 S
49604 S
49604 S
49604 S
113/121/130 119/126/135 125/130/139 125/130/139 125/130/139 125/130/139 125/130/139
2
42703 R
46022 R
49246 R
49604 S
49604 S
49604 S
49604 S
113/121/130 119/126/134 124/130/138 125/130/139 125/130/139 125/130/139 125/130/139
6
42412 R
45721 R
48864 R
49604 S
49604 S
49604 S
49604 S
112/120/130 118/125/134 124/129/138 125/130/139 125/130/139 125/130/139 125/130/139
10
42125 R
45426 R
48490 R
49604 S
49604 S
49604 S
49604 S
112/120/129 118/125/134 123/129/137 125/131/139 125/131/139 125/131/139 125/131/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
55 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
44953 R
48475 R
49604 S
49604 S
49604 S
49604 S
49604 S
117/124/133 123/129/137 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-30
44649 R
48110 R
49604 S
49604 S
49604 S
49604 S
49604 S
117/124/133 123/128/137 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-26
44347 R
47755 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/123/132 122/128/137 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-22
44053 R
47418 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/123/132 121/128/136 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-18
43742 R
47089 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/122/131 121/127/136 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-14
43432 R
46767 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/122/131 120/127/135 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-10
43130 R
46458 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/121/131 120/126/135 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-6
42837 R
46159 R
49420 R
49604 S
49604 S
49604 S
49604 S
113/121/130 119/126/135 125/130/139 125/131/139 125/131/139 125/131/139 125/131/139
-2
42548 R
45862 R
49043 R
49604 S
49604 S
49604 S
49604 S
113/120/130 119/125/134 124/130/138 125/131/139 125/131/139 125/131/139 125/131/139
2
42258 R
45564 R
48663 R
49604 S
49604 S
49604 S
49604 S
112/120/129 118/125/134 124/129/138 125/131/139 125/131/139 125/131/139 125/131/139
6
41969 R
45265 R
48312 R
49604 S
49604 S
49604 S
49604 S
112/120/129 118/125/133 123/129/137 125/131/139 125/131/139 125/131/139 125/131/139
10
41723 R
44966 R
47986 R
49604 S
49604 S
49604 S
49604 S
111/119/129 117/124/133 122/128/137 125/131/139 125/131/139 125/131/139 125/131/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
56 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 1000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
44570 R
48016 R
49604 S
49604 S
49604 S
49604 S
49604 S
117/124/132 123/128/137 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-30
44266 R
47660 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/123/132 122/128/136 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-26
43953 R
47312 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/123/132 121/128/136 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-22
43642 R
46984 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/122/131 121/127/136 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-18
43330 R
46662 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/122/131 120/127/135 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-14
43022 R
46349 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/121/130 120/126/135 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-10
42729 R
46048 R
49279 R
49604 S
49604 S
49604 S
49604 S
113/121/130 119/126/134 125/130/138 125/131/139 125/131/139 125/131/139 125/131/139
-6
42433 R
45743 R
48891 R
49604 S
49604 S
49604 S
49604 S
113/120/130 119/125/134 124/129/138 125/131/139 125/131/139 125/131/139 125/131/139
-2
42125 R
45426 R
48490 R
49604 S
49604 S
49604 S
49604 S
112/120/129 118/125/134 123/129/137 125/131/139 125/131/139 125/131/139 125/131/139
2
41839 R
45118 R
48151 R
49604 S
49604 S
49604 S
49604 S
112/119/129 118/124/133 123/129/137 125/131/139 125/131/139 125/131/139 125/131/139
6
41613 R
44821 R
47830 R
49604 S
49604 S
49604 S
49604 S
111/119/128 117/124/133 122/128/137 125/131/139 125/131/139 125/131/139 125/131/139
10
41385 R
44518 R
47507 R
49604 S
49604 S
49604 S
49604 S
111/119/128 117/124/132 122/128/136 125/131/139 125/131/139 125/131/139 125/131/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
57 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 1500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
44173 R
47552 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/123/132 122/128/136 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-30
43853 R
47206 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/123/132 121/128/136 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-26
43532 R
46870 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/122/131 121/127/135 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-22
43220 R
46549 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/122/131 120/127/135 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-18
42910 R
46235 R
49516 R
49604 S
49604 S
49604 S
49604 S
114/121/130 120/126/135 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-14
42606 R
45921 R
49118 R
49604 S
49604 S
49604 S
49604 S
113/121/130 119/126/134 125/130/138 125/131/139 125/131/139 125/131/139 125/131/139
-10
42309 R
45616 R
48730 R
49604 S
49604 S
49604 S
49604 S
113/120/129 119/125/134 124/129/138 125/131/139 125/131/139 125/131/139 125/131/139
-6
42013 R
45311 R
48362 R
49604 S
49604 S
49604 S
49604 S
112/120/129 118/125/133 123/129/137 125/131/139 125/131/139 125/131/139 125/131/139
-2
41723 R
44966 R
47986 R
49604 S
49604 S
49604 S
49604 S
112/119/129 118/124/133 123/128/137 125/131/139 125/131/139 125/131/139 125/131/139
2
41477 R
44640 R
47637 R
49604 S
49604 S
49604 S
49604 S
111/119/128 117/124/133 122/128/136 125/131/139 125/131/139 125/131/139 125/131/139
6
41253 R
44341 R
47321 R
49604 S
49604 S
49604 S
49604 S
111/119/128 116/123/132 122/128/136 125/131/139 125/131/139 125/131/139 125/131/139
10
41019 R
44021 R
46993 R
49604 S
49604 S
49604 S
49604 S
110/118/128 116/123/132 121/127/136 125/131/139 125/131/139 125/131/139 125/131/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
58 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 2000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
43762 R
47110 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/123/131 121/128/136 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-30
43437 R
46773 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/122/131 121/127/135 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-26
43122 R
46450 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/122/131 120/127/135 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-22
42808 R
46130 R
49383 R
49604 S
49604 S
49604 S
49604 S
114/121/130 120/126/135 125/131/139 125/131/139 125/131/139 125/131/139 125/131/139
-18
42501 R
45814 R
48981 R
49604 S
49604 S
49604 S
49604 S
113/121/130 119/126/134 125/130/138 125/131/139 125/131/139 125/131/139 125/131/139
-14
42200 R
45504 R
48586 R
49604 S
49604 S
49604 S
49604 S
113/120/129 119/125/134 124/129/138 125/131/139 125/131/139 125/131/139 125/131/139
-10
41901 R
45195 R
48236 R
49604 S
49604 S
49604 S
49604 S
112/120/129 118/125/133 123/129/137 125/131/139 125/131/139 125/131/139 125/131/139
-6
41665 R
44889 R
47904 R
49604 S
49604 S
49604 S
49604 S
112/119/129 118/124/133 123/128/137 125/131/139 125/131/139 125/131/139 125/131/139
-2
41385 R
44518 R
47507 R
49604 S
49604 S
49604 S
49604 S
111/119/128 117/124/132 122/128/136 125/131/139 125/131/139 125/131/139 125/131/139
2
41130 R
44177 R
47149 R
49604 S
49604 S
49604 S
49604 S
111/119/128 116/123/132 122/128/136 125/131/139 125/131/139 125/131/139 125/131/139
6
40908 R
43859 R
46838 R
49604 S
49604 S
49604 S
49604 S
110/118/127 116/123/132 121/127/135 125/131/139 125/131/139 125/131/139 125/131/139
10
40670 R
43509 R
46506 R
49390 R
49604 S
49604 S
49604 S
110/118/127 115/122/131 120/127/135 125/131/139 125/131/139 125/131/139 125/131/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
59 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 2500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
43324 R
46656 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/122/131 121/127/135 126/131/139 126/131/139 126/131/139 126/131/139 126/131/139
-30
43003 R
46329 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/122/130 120/127/135 126/131/139 126/131/139 126/131/139 126/131/139 126/131/139
-26
42686 R
46004 R
49223 R
49604 S
49604 S
49604 S
49604 S
114/121/130 120/126/134 125/130/138 126/131/139 126/131/139 126/131/139 126/131/139
-22
42375 R
45683 R
48815 R
49604 S
49604 S
49604 S
49604 S
113/121/130 119/126/134 124/130/138 126/131/139 126/131/139 126/131/139 126/131/139
-18
42069 R
45369 R
48426 R
49604 S
49604 S
49604 S
49604 S
113/120/129 119/125/134 124/129/137 126/131/139 126/131/139 126/131/139 126/131/139
-14
41796 R
45061 R
48090 R
49604 S
49604 S
49604 S
49604 S
112/120/129 118/125/133 123/129/137 126/131/139 126/131/139 126/131/139 126/131/139
-10
41562 R
44753 R
47757 R
49604 S
49604 S
49604 S
49604 S
112/119/128 118/124/133 123/128/137 126/131/139 126/131/139 126/131/139 126/131/139
-6
41333 R
44448 R
47434 R
49604 S
49604 S
49604 S
49604 S
111/119/128 117/124/132 122/128/136 126/131/139 126/131/139 126/131/139 126/131/139
-2
41039 R
44051 R
47021 R
49604 S
49604 S
49604 S
49604 S
111/118/128 116/123/132 121/128/136 126/131/139 126/131/139 126/131/139 126/131/139
2
40778 R
43667 R
46656 R
49595 R
49604 S
49604 S
49604 S
110/118/127 116/123/131 121/127/135 126/131/139 126/131/139 126/131/139 126/131/139
6
40557 R
43340 R
46348 R
49171 R
49604 S
49604 S
49604 S
110/118/127 115/122/131 120/127/135 125/130/138 126/131/139 126/131/139 126/131/139
10
40312 R
42974 R
45979 R
48695 R
49604 S
49604 S
49604 S
109/117/127 114/122/130 120/126/134 124/130/138 126/131/139 126/131/139 126/131/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
60 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 3000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
42898 R
46223 R
49501 R
49604 S
49604 S
49604 S
49604 S
114/122/130 120/127/135 126/131/139 126/131/139 126/131/139 126/131/139 126/131/139
-30
42580 R
45895 R
49084 R
49604 S
49604 S
49604 S
49604 S
114/121/130 120/126/134 125/130/138 126/131/139 126/131/139 126/131/139 126/131/139
-26
42262 R
45567 R
48668 R
49604 S
49604 S
49604 S
49604 S
113/121/129 119/126/134 124/130/138 126/131/139 126/131/139 126/131/139 126/131/139
-22
41953 R
45249 R
48294 R
49604 S
49604 S
49604 S
49604 S
113/120/129 119/125/133 124/129/137 126/131/139 126/131/139 126/131/139 126/131/139
-18
41700 R
44936 R
47954 R
49604 S
49604 S
49604 S
49604 S
112/120/129 118/125/133 123/129/137 126/131/139 126/131/139 126/131/139 126/131/139
-14
41470 R
44631 R
47627 R
49604 S
49604 S
49604 S
49604 S
112/119/128 118/124/133 123/128/136 126/131/139 126/131/139 126/131/139 126/131/139
-10
41239 R
44323 R
47302 R
49604 S
49604 S
49604 S
49604 S
111/119/128 117/124/132 122/128/136 126/131/139 126/131/139 126/131/139 126/131/139
-6
41014 R
44014 R
46986 R
49604 S
49604 S
49604 S
49604 S
111/119/128 116/123/132 122/128/136 126/131/139 126/131/139 126/131/139 126/131/139
-2
40709 R
43566 R
46560 R
49464 R
49604 S
49604 S
49604 S
110/118/127 116/123/131 121/127/135 126/131/139 126/131/139 126/131/139 126/131/139
2
40441 R
43168 R
46177 R
48947 R
49604 S
49604 S
49604 S
110/118/127 115/122/131 120/127/135 125/130/138 126/131/139 126/131/139 126/131/139
6
40221 R
42837 R
45839 R
48517 R
49604 S
49604 S
49604 S
109/117/126 114/121/130 120/126/134 124/129/137 126/131/139 126/131/139 126/131/139
10
39970 R
42457 R
45451 R
48117 R
49604 S
49604 S
49604 S
109/117/126 114/121/130 119/125/134 124/129/137 126/131/139 126/131/139 126/131/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
61 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 3500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
42447 R
45758 R
48910 R
49604 S
49604 S
49604 S
49604 S
114/121/130 120/126/134 125/130/138 126/131/139 126/131/139 126/131/139 126/131/139
-30
42126 R
45427 R
48491 R
49604 S
49604 S
49604 S
49604 S
113/120/129 119/126/134 124/130/137 126/131/139 126/131/139 126/131/139 126/131/139
-26
41831 R
45108 R
48140 R
49604 S
49604 S
49604 S
49604 S
113/120/129 119/125/133 124/129/137 126/131/139 126/131/139 126/131/139 126/131/139
-22
41593 R
44794 R
47801 R
49604 S
49604 S
49604 S
49604 S
112/120/128 118/125/133 123/129/137 126/131/139 126/131/139 126/131/139 126/131/139
-18
41358 R
44483 R
47470 R
49604 S
49604 S
49604 S
49604 S
112/119/128 117/124/132 123/128/136 126/131/139 126/131/139 126/131/139 126/131/139
-14
41127 R
44172 R
47144 R
49604 S
49604 S
49604 S
49604 S
111/119/128 117/124/132 122/128/136 126/131/139 126/131/139 126/131/139 126/131/139
-10
40903 R
43851 R
46830 R
49604 S
49604 S
49604 S
49604 S
111/118/127 116/123/132 122/128/135 126/131/139 126/131/139 126/131/139 126/131/139
-6
40682 R
43525 R
46522 R
49411 R
49604 S
49604 S
49604 S
110/118/127 116/123/131 121/127/135 126/131/139 126/131/139 126/131/139 126/131/139
-2
40371 R
43063 R
46070 R
48811 R
49604 S
49604 S
49604 S
110/118/127 115/122/130 120/127/134 125/130/138 126/131/139 126/131/139 126/131/139
2
40107 R
42664 R
45662 R
48333 R
49604 S
49604 S
49604 S
109/117/126 114/121/130 120/126/134 124/129/137 126/131/139 126/131/139 126/131/139
6
39887 R
42330 R
45320 R
47986 R
49604 S
49604 S
49604 S
109/117/126 114/121/129 119/125/133 124/129/137 126/131/139 126/131/139 126/131/139
10
39401 R
41880 R
44856 R
47523 R
49604 S
49604 S
49604 S
108/116/125 113/120/129 118/125/133 123/128/136 126/131/139 126/131/139 126/131/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
62 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 4000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
42008 R
45306 R
48357 R
49604 S
49604 S
49604 S
49604 S
113/120/129 119/126/133 124/130/137 126/131/139 126/131/139 126/131/139 126/131/139
-30
41729 R
44973 R
47994 R
49604 S
49604 S
49604 S
49604 S
113/120/129 119/125/133 124/129/137 126/131/139 126/131/139 126/131/139 126/131/139
-26
41492 R
44660 R
47658 R
49604 S
49604 S
49604 S
49604 S
112/120/128 118/125/133 123/129/136 126/131/139 126/131/139 126/131/139 126/131/139
-22
41261 R
44352 R
47332 R
49604 S
49604 S
49604 S
49604 S
112/119/128 117/124/132 123/128/136 126/131/139 126/131/139 126/131/139 126/131/139
-18
41031 R
44038 R
47010 R
49604 S
49604 S
49604 S
49604 S
111/119/128 117/124/132 122/128/136 126/131/139 126/131/139 126/131/139 126/131/139
-14
40799 R
43699 R
46686 R
49604 S
49604 S
49604 S
49604 S
111/118/127 116/123/131 121/127/135 126/131/139 126/131/139 126/131/139 126/131/139
-10
40580 R
43375 R
46381 R
49217 R
49604 S
49604 S
49604 S
110/118/127 116/123/131 121/127/135 126/131/138 126/131/139 126/131/139 126/131/139
-6
40363 R
43052 R
46058 R
48796 R
49604 S
49604 S
49604 S
110/118/127 115/122/130 120/127/134 125/130/138 126/131/139 126/131/139 126/131/139
-2
40048 R
42576 R
45572 R
48240 R
49604 S
49604 S
49604 S
109/117/126 114/121/130 120/126/134 124/129/137 126/131/139 126/131/139 126/131/139
2
39787 R
42177 R
45164 R
47828 R
49604 S
49604 S
49604 S
109/117/126 113/121/129 119/125/133 123/129/137 126/131/139 126/131/139 126/131/139
6
39325 R
41851 R
44817 R
47484 R
49604 S
49604 S
49604 S
108/116/125 113/120/129 118/125/133 123/128/136 126/131/139 126/131/139 126/131/139
10
38354 R
41462 R
44284 R
46963 R
49604 S
49604 S
49604 S
106/114/124 112/120/128 117/124/132 122/128/136 126/131/139 126/131/139 126/131/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
63 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 4500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
41608 R
44814 R
47823 R
49604 S
49604 S
49604 S
49604 S
113/120/128 118/125/133 124/129/137 126/132/139 126/132/139 126/132/139 126/132/139
-30
41362 R
44487 R
47475 R
49604 S
49604 S
49604 S
49604 S
112/120/128 118/124/132 123/129/136 126/132/139 126/132/139 126/132/139 126/132/139
-26
41126 R
44171 R
47144 R
49604 S
49604 S
49604 S
49604 S
112/119/128 117/124/132 122/128/136 126/132/139 126/132/139 126/132/139 126/132/139
-22
40898 R
43844 R
46824 R
49604 S
49604 S
49604 S
49604 S
111/119/127 117/123/131 122/128/135 126/131/139 126/131/139 126/131/139 126/131/139
-18
40674 R
43514 R
46512 R
49397 R
49604 S
49604 S
49604 S
111/118/127 116/123/131 121/127/135 126/131/139 126/131/139 126/131/139 126/131/139
-14
40451 R
43182 R
46192 R
48966 R
49604 S
49604 S
49604 S
110/118/127 116/122/131 121/127/135 125/130/138 126/131/139 126/131/139 126/131/139
-10
40233 R
42856 R
45858 R
48541 R
49604 S
49604 S
49604 S
110/118/126 115/122/130 120/126/134 125/130/138 126/132/139 126/132/139 126/132/139
-6
40029 R
42547 R
45542 R
48210 R
49604 S
49604 S
49604 S
110/117/126 114/121/130 120/126/134 124/129/137 126/132/139 126/132/139 126/132/139
-2
39730 R
42089 R
45073 R
47738 R
49604 S
49604 S
49604 S
109/117/126 114/121/129 119/125/133 123/129/137 126/132/139 126/132/139 126/132/139
2
39073 R
41754 R
44685 R
47354 R
49604 S
49604 S
49604 S
108/116/125 113/120/129 118/125/133 123/128/136 126/132/139 126/132/139 126/132/139
6
38444 R
41500 R
44336 R
47014 R
49604 S
49604 S
49604 S
106/115/124 112/120/128 118/124/132 122/128/136 126/131/139 126/131/139 126/131/139
10
37439 R
41059 R
43694 R
46427 R
48866 R
49604 S
49604 S
104/113/122 112/119/128 116/123/131 121/127/135 125/130/138 126/131/139 126/131/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
64 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 5000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
41250 R
44337 R
47317 R
49604 S
49604 S
49604 S
49604 S
112/119/128 118/124/132 123/128/136 127/132/139 127/132/139 127/132/139 127/132/139
-30
41011 R
44010 R
46982 R
49604 S
49604 S
49604 S
49604 S
112/119/128 117/124/132 122/128/136 127/132/139 127/132/139 127/132/139 127/132/139
-26
40778 R
43667 R
46656 R
49595 R
49604 S
49604 S
49604 S
111/119/127 117/123/131 122/128/135 127/132/139 127/132/139 127/132/139 127/132/139
-22
40552 R
43334 R
46342 R
49163 R
49604 S
49604 S
49604 S
111/118/127 116/123/131 121/127/135 126/131/138 127/132/139 127/132/139 127/132/139
-18
40334 R
43007 R
46013 R
48738 R
49604 S
49604 S
49604 S
110/118/127 115/122/130 121/127/134 125/130/138 127/132/139 127/132/139 127/132/139
-14
40118 R
42682 R
45680 R
48351 R
49604 S
49604 S
49604 S
110/118/126 115/122/130 120/126/134 125/130/137 127/132/139 127/132/139 127/132/139
-10
39902 R
42353 R
45344 R
48009 R
49604 S
49604 S
49604 S
110/117/126 114/121/129 120/126/134 124/129/137 127/132/139 127/132/139 127/132/139
-6
39710 R
42058 R
45042 R
47706 R
49604 S
49604 S
49604 S
109/117/126 114/121/129 119/125/133 124/129/136 127/132/139 127/132/139 127/132/139
-2
38897 R
41685 R
44590 R
47261 R
49604 S
49604 S
49604 S
107/116/125 113/120/129 118/125/132 123/128/136 127/132/139 127/132/139 127/132/139
2
38246 R
41417 R
44220 R
46902 R
49557 R
49604 S
49604 S
106/114/124 112/120/128 118/124/132 122/128/136 126/132/139 127/132/139 127/132/139
6
37672 R
41164 R
43852 R
46566 R
49071 R
49604 S
49604 S
105/113/123 112/119/128 117/124/132 122/128/135 126/131/138 127/132/139 127/132/139
10
36556 R
40683 R
43125 R
45849 R
48201 R
49145 W 49145 W
102/112/121 111/119/127 116/122/131 120/127/134 124/130/137 126/131/138 126/131/138
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
65 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 5500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
40795 R
43692 R
46679 R
49604 S
49604 S
49604 S
49604 S
112/119/127 117/123/131 122/128/135 127/132/139 127/132/139 127/132/139 127/132/139
-30
40563 R
43349 R
46357 R
49183 R
49604 S
49604 S
49604 S
111/118/127 116/123/131 122/127/135 126/131/138 127/132/139 127/132/139 127/132/139
-26
40336 R
43010 R
46016 R
48742 R
49604 S
49604 S
49604 S
111/118/127 116/122/130 121/127/134 125/130/138 127/132/139 127/132/139 127/132/139
-22
40118 R
42682 R
45680 R
48351 R
49604 S
49604 S
49604 S
110/118/126 115/122/130 120/126/134 125/130/137 127/132/139 127/132/139 127/132/139
-18
39907 R
42360 R
45351 R
48016 R
49604 S
49604 S
49604 S
110/117/126 114/121/129 120/126/134 124/129/137 127/132/139 127/132/139 127/132/139
-14
39698 R
42039 R
45022 R
47687 R
49604 S
49604 S
49604 S
109/117/126 114/121/129 119/125/133 124/129/136 127/132/139 127/132/139 127/132/139
-10
39095 R
41763 R
44697 R
47365 R
49604 S
49604 S
49604 S
108/116/125 113/120/129 119/125/133 123/129/136 127/132/139 127/132/139 127/132/139
-6
38534 R
41538 R
44387 R
47064 R
49604 S
49604 S
49604 S
107/115/124 113/120/128 118/124/132 123/128/136 127/132/139 127/132/139 127/132/139
-2
37839 R
41239 R
43965 R
46666 R
49216 R
49604 S
49604 S
106/114/123 112/120/128 117/124/132 122/128/135 126/131/138 127/132/139 127/132/139
2
37224 R
40968 R
43556 R
46306 R
48688 R
49604 S
49604 S
104/113/122 112/119/128 117/123/131 121/127/135 125/130/138 127/132/139 127/132/139
6
36560 R
40684 R
43128 R
45852 R
48203 R
49604 S
49604 S
103/112/121 111/119/127 116/123/131 121/127/134 125/130/137 127/132/139 127/132/139
10
35594 R
40198 R
42425 R
45078 R
47447 R
47949 W 47949 W
100/110/120 110/118/126 115/121/130 119/126/133 123/129/136 124/129/137 124/129/137
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
66 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 6000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
40366 R
43055 R
46062 R
48801 R
49604 S
49604 S
49604 S
111/118/127 116/123/130 121/127/134 126/131/138 127/132/139 127/132/139 127/132/139
-30
40140 R
42715 R
45714 R
48385 R
49604 S
49604 S
49604 S
111/118/126 115/122/130 121/127/134 125/130/137 127/132/139 127/132/139 127/132/139
-26
39919 R
42379 R
45370 R
48036 R
49604 S
49604 S
49604 S
110/118/126 115/122/130 120/126/134 125/130/137 127/132/139 127/132/139 127/132/139
-22
39709 R
42057 R
45040 R
47705 R
49604 S
49604 S
49604 S
110/117/126 114/121/129 119/126/133 124/129/136 127/132/139 127/132/139 127/132/139
-18
39130 R
41776 R
44715 R
47383 R
49604 S
49604 S
49604 S
108/116/125 114/121/129 119/125/133 123/129/136 127/132/139 127/132/139 127/132/139
-14
38539 R
41539 R
44390 R
47066 R
49604 S
49604 S
49604 S
107/115/124 113/120/128 118/125/132 123/128/136 127/132/139 127/132/139 127/132/139
-10
38004 R
41312 R
44073 R
46763 R
49356 R
49604 S
49604 S
106/114/123 113/120/128 118/124/132 122/128/135 127/131/139 127/132/139 127/132/139
-6
37502 R
41086 R
43735 R
46463 R
48920 R
49604 S
49604 S
105/113/122 112/119/128 117/124/131 122/128/135 126/131/138 127/132/139 127/132/139
-2
36879 R
40819 R
43332 R
46076 R
48420 R
49604 S
49604 S
104/112/122 112/119/127 116/123/131 121/127/135 125/130/137 127/132/139 127/132/139
2
36278 R
40555 R
42937 R
45641 R
47999 R
49604 S
49604 S
102/111/121 111/119/127 116/122/130 121/126/134 124/130/137 127/132/139 127/132/139
6
35659 R
40235 R
42477 R
45135 R
47503 R
49260 W 49260 W
101/110/120 111/118/126 115/122/130 120/126/133 124/129/136 126/131/138 126/131/138
10
34539 R
39726 R
41805 R
44373 R
46744 R
46753 W 46753 W
99/109/119 110/117/126 114/121/129 118/125/132 122/128/135 122/128/135 122/128/135
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
67 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 6500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
39925 R
42388 R
45380 R
48045 R
49604 S
49604 S
49604 S
110/118/126 115/122/130 120/126/134 125/130/137 127/132/139 127/132/139 127/132/139
-30
39707 R
42053 R
45037 R
47701 R
49604 S
49604 S
49604 S
110/117/126 114/121/129 120/126/133 124/129/136 127/132/139 127/132/139 127/132/139
-26
39100 R
41765 R
44699 R
47368 R
49604 S
49604 S
49604 S
109/116/125 114/121/129 119/125/133 124/129/136 127/132/139 127/132/139 127/132/139
-22
38501 R
41524 R
44369 R
47046 R
49604 S
49604 S
49604 S
108/115/124 113/120/128 119/125/132 123/129/136 127/132/139 127/132/139 127/132/139
-18
37954 R
41290 R
44041 R
46733 R
49314 R
49604 S
49604 S
106/114/123 113/120/128 118/124/132 123/128/135 127/131/139 127/132/139 127/132/139
-14
37448 R
41063 R
43700 R
46432 R
48874 R
49604 S
49604 S
105/113/122 112/120/128 117/124/131 122/128/135 126/131/138 127/132/139 127/132/139
-10
36926 R
40838 R
43361 R
46108 R
48451 R
49604 S
49604 S
104/112/122 112/119/127 117/123/131 122/127/135 125/130/137 127/132/139 127/132/139
-6
36439 R
40630 R
43047 R
45763 R
48117 R
49604 S
49604 S
103/112/121 112/119/127 116/123/130 121/127/134 125/130/137 127/132/139 127/132/139
-2
35965 R
40400 R
42711 R
45393 R
47757 R
49604 S
49604 S
102/111/120 111/118/127 116/122/130 120/126/134 124/129/137 127/132/139 127/132/139
2
35450 R
40114 R
42307 R
44949 R
47319 R
49400 W 49400 W
101/110/119 111/118/126 115/122/129 120/126/133 124/129/136 127/132/139 127/132/139
6
34551 R
39730 R
41810 R
44380 R
46751 R
47912 W 47912 W
99/109/119 110/117/126 114/121/129 119/125/132 123/128/135 125/130/137 125/130/137
10
33488 R
38600 R
41281 R
43646 R
45519 W 45519 W 45519 W
97/107/118 108/115/124 113/120/128 117/124/131 121/126/134 121/126/134 121/126/134
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
68 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 7000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
39149 R
41784 R
44725 R
47393 R
49245 W 49245 W 49245 W
109/117/125 114/121/129 119/125/133 124/129/136 127/131/138 127/131/138 127/131/138
-30
38533 R
41537 R
44387 R
47063 R
49245 W 49245 W 49245 W
108/115/124 114/120/128 119/125/132 123/129/136 127/131/138 127/131/138 127/131/138
-26
37972 R
41298 R
44053 R
46744 R
49245 W 49245 W 49245 W
107/114/123 113/120/128 118/124/132 123/128/135 127/131/138 127/131/138 127/131/138
-22
37446 R
41062 R
43698 R
46430 R
48872 R
49242 W 49242 W
106/114/122 113/120/128 118/124/131 122/128/135 126/131/138 127/131/138 127/131/138
-18
36912 R
40833 R
43352 R
46098 R
48441 R
49231 W 49231 W
104/113/122 112/119/127 117/123/131 122/127/135 126/130/137 127/131/138 127/131/138
-14
36424 R
40624 R
43037 R
45752 R
48107 R
49214 W 49214 W
103/112/121 112/119/127 116/123/130 121/127/134 125/130/137 127/131/138 127/131/138
-10
35978 R
40407 R
42721 R
45404 R
47768 R
49174 W 49174 W
102/111/120 112/119/127 116/122/130 121/126/134 125/130/137 127/131/138 127/131/138
-6
35594 R
40198 R
42425 R
45078 R
47447 R
49247 W 49247 W
101/110/120 111/118/126 115/122/130 120/126/133 124/129/136 127/131/138 127/131/138
-2
35230 R
39990 R
42137 R
44761 R
47133 R
49231 W 49231 W
101/110/119 111/118/126 115/121/129 119/125/133 123/129/136 127/131/138 127/131/138
2
34434 R
39679 R
41759 R
44310 R
46680 R
48583 W 48583 W
99/109/119 110/117/126 114/121/129 119/125/132 123/128/135 126/130/138 126/130/138
6
33507 R
38623 R
41292 R
43661 R
46018 R
46564 W 46564 W
97/107/118 108/116/124 113/120/128 117/124/131 122/127/134 123/128/135 123/128/135
10
32730 R
37532 R
40770 R
42962 R
44284 W 44284 W 44284 W
97/106/117 106/114/123 112/119/127 116/123/130 119/125/132 119/125/132 119/125/132
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
69 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 7500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
37976 R
41300 R
44055 R
46746 R
48570 W 48570 W 48570 W
107/115/123 113/120/128 118/125/132 123/128/135 126/131/138 126/131/138 126/131/138
-30
37444 R
41061 R
43697 R
46430 R
48572 W 48572 W 48572 W
106/114/122 113/120/128 118/124/131 123/128/135 126/131/138 126/131/138 126/131/138
-26
36902 R
40829 R
43346 R
46092 R
48435 R
48565 W 48565 W
105/113/122 113/119/127 117/123/131 122/128/135 126/130/137 126/131/138 126/131/138
-22
36386 R
40606 R
43012 R
45724 R
48079 R
48554 W 48554 W
104/112/121 112/119/127 117/123/130 121/127/134 125/130/137 126/131/138 126/131/138
-18
35942 R
40389 R
42695 R
45375 R
47739 R
48541 W 48541 W
103/111/120 112/119/127 116/122/130 121/126/134 125/130/137 126/131/138 126/131/138
-14
35558 R
40177 R
42396 R
45046 R
47415 R
48530 W 48530 W
102/110/120 111/118/126 115/122/130 120/126/133 124/129/136 126/131/138 126/131/138
-10
35149 R
39961 R
42098 R
44718 R
47089 R
48490 W 48490 W
101/110/119 111/118/126 115/121/129 120/126/133 124/129/136 126/131/137 126/131/137
-6
34617 R
39757 R
41838 R
44419 R
46790 R
48608 W 48608 W
100/109/119 111/118/126 114/121/129 119/125/132 123/128/135 126/131/138 126/131/138
-2
34067 R
39283 R
41588 R
44078 R
46447 R
48334 W 48334 W
99/108/118 110/117/125 114/121/128 118/125/132 123/128/135 126/130/137 126/130/137
2
33382 R
38465 R
41219 R
43560 R
45910 R
47266 W 47266 W
98/107/117 108/115/124 113/120/128 118/124/131 122/127/134 124/129/136 124/129/136
6
32645 R
37411 R
40702 R
42873 R
45122 W 45122 W 45122 W
96/106/116 106/114/122 112/119/127 116/123/130 120/126/133 120/126/133 120/126/133
10
32111 R
36532 R
40093 R
42114 R
43034 W 43034 W 43034 W
96/105/116 104/112/121 111/118/126 115/122/129 117/123/130 117/123/130 117/123/130
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
70 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 8000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
36940 R
40844 R
43370 R
46117 R
47895 W 47895 W 47895 W
105/113/122 113/120/127 117/124/131 122/128/135 125/130/137 125/130/137 125/130/137
-30
36422 R
40623 R
43036 R
45750 R
47900 W 47900 W 47900 W
104/112/121 112/119/127 117/123/130 122/127/134 125/130/137 125/130/137 125/130/137
-26
35965 R
40400 R
42711 R
45393 R
47757 R
47884 W 47884 W
103/111/120 112/119/127 116/123/130 121/127/134 125/130/137 125/130/137 125/130/137
-22
35551 R
40173 R
42390 R
45040 R
47409 R
47865 W 47865 W
102/111/120 112/119/126 116/122/130 120/126/133 124/129/136 125/130/137 125/130/137
-18
35131 R
39954 R
42089 R
44708 R
47080 R
47851 W 47851 W
101/110/119 111/118/126 115/122/129 120/126/133 124/129/136 125/130/137 125/130/137
-14
34578 R
39741 R
41821 R
44396 R
46766 R
47847 W 47847 W
100/109/119 111/118/126 115/121/129 119/125/132 123/129/135 125/130/137 125/130/137
-10
34076 R
39294 R
41592 R
44084 R
46453 R
47805 W 47805 W
99/108/118 110/117/125 114/121/128 119/125/132 123/128/135 125/130/137 125/130/137
-6
33671 R
38825 R
41384 R
43789 R
46157 R
47968 W 47968 W
98/108/117 109/116/124 114/120/128 118/124/131 122/128/135 125/130/137 125/130/137
-2
33198 R
38220 R
41104 R
43404 R
45743 R
47437 W 47437 W
98/107/117 108/115/124 113/120/128 117/124/131 122/127/134 124/129/136 124/129/136
2
32634 R
37396 R
40693 R
42861 R
45159 R
45949 W 45949 W
96/106/116 106/114/122 113/119/127 116/123/130 121/126/133 122/127/134 122/127/134
6
32102 R
36578 R
40128 R
42157 R
43680 W 43680 W 43680 W
96/105/116 104/112/121 112/118/126 115/122/129 118/124/131 118/124/131 118/124/131
10
32114 R
35757 R
39176 R
41400 R
41784 W 41784 W 41784 W
96/105/116 103/111/120 110/117/125 114/120/128 115/121/129 115/121/129 115/121/129
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
71 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: Sea Level Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
45123 R
48602 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/124/133 121/129/138 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
4
44877 R
48224 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/133 120/128/137 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
8
44639 R
47856 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/133 120/128/137 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
12
44408 R
47502 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/122/132 119/127/136 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
16
44178 R
47155 R
49604 S
49604 S
49604 S
49604 S
49604 S
113/122/132 118/127/136 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
20
43655 R
46837 R
49604 S
49604 S
49604 S
49604 S
49604 S
112/121/131 118/126/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
24
42955 R
46518 R
49604 S
49604 S
49604 S
49604 S
49604 S
111/120/130 117/126/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
28
42306 R
46227 R
49580 R
49604 S
49604 S
49604 S
49604 S
110/119/129 117/125/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
32
41717 R
45984 R
49242 R
49604 S
49604 S
49604 S
49604 S
109/118/129 117/125/134 122/130/138 123/130/139 123/130/139 123/130/139 123/130/139
36
40935 R
45577 R
48694 R
49604 S
49604 S
49604 S
49604 S
109/117/127 116/124/134 121/129/138 123/130/139 123/130/139 123/130/139 123/130/139
40
39635 R
44695 R
47479 R
49604 S
49604 S
49604 S
49604 S
105/115/126 115/124/133 120/128/136 124/131/139 124/131/139 124/131/139 124/131/139
44
38456 R
43334 R
46267 R
49132 R
49604 S
49604 S
49604 S
104/114/124 113/122/131 119/126/135 123/130/138 124/131/139 124/131/139 124/131/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
72 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
44754 R
48034 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/133 120/128/137 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
4
44511 R
47659 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/132 120/127/136 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
8
44272 R
47296 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/122/132 119/127/136 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
12
43919 R
46953 R
49604 S
49604 S
49604 S
49604 S
49604 S
113/122/132 118/126/136 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
16
43218 R
46640 R
49604 S
49604 S
49604 S
49604 S
49604 S
112/121/131 118/126/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
20
42552 R
46327 R
49604 S
49604 S
49604 S
49604 S
49604 S
110/120/130 117/125/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
24
41923 R
46077 R
49371 R
49604 S
49604 S
49604 S
49604 S
109/119/129 117/125/134 122/130/139 123/130/139 123/130/139 123/130/139 123/130/139
28
41411 R
45834 R
49038 R
49604 S
49604 S
49604 S
49604 S
109/118/128 116/125/134 122/129/138 123/130/139 123/130/139 123/130/139 123/130/139
32
40920 R
45569 R
48683 R
49604 S
49604 S
49604 S
49604 S
108/117/127 116/124/134 121/129/138 123/130/139 123/130/139 123/130/139 123/130/139
36
39936 R
44921 R
47787 R
49604 S
49604 S
49604 S
49604 S
106/116/126 115/124/133 120/128/137 123/131/139 123/131/139 123/131/139 123/131/139
40
38712 R
43956 R
46605 R
49494 R
49604 S
49604 S
49604 S
103/114/124 114/123/132 119/127/135 124/131/139 124/131/139 124/131/139 124/131/139
44
37975 R
41895 R
45531 R
48219 R
49604 S
49604 S
49604 S
103/113/123 111/120/129 118/125/134 122/129/137 124/131/139 124/131/139 124/131/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
73 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 1000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
44398 R
47487 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/132 119/127/136 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
4
44151 R
47114 R
49604 S
49604 S
49604 S
49604 S
49604 S
113/122/132 119/127/136 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
8
43498 R
46767 R
49604 S
49604 S
49604 S
49604 S
49604 S
112/121/131 118/126/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
12
42803 R
46447 R
49604 S
49604 S
49604 S
49604 S
49604 S
111/120/130 118/126/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
16
42190 R
46182 R
49517 R
49604 S
49604 S
49604 S
49604 S
110/119/129 117/125/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
20
41616 R
45935 R
49176 R
49604 S
49604 S
49604 S
49604 S
109/118/128 117/125/134 122/130/138 123/130/139 123/130/139 123/130/139 123/130/139
24
41139 R
45691 R
48846 R
49604 S
49604 S
49604 S
49604 S
109/118/128 116/125/134 122/129/138 123/130/139 123/130/139 123/130/139 123/130/139
28
40716 R
45448 R
48524 R
49604 S
49604 S
49604 S
49604 S
108/117/127 116/124/134 121/129/138 123/130/139 123/130/139 123/130/139 123/130/139
32
40211 R
45120 R
48063 R
49604 S
49604 S
49604 S
49604 S
107/116/126 115/124/133 120/128/137 123/130/139 123/130/139 123/130/139 123/130/139
36
38994 R
44279 R
46923 R
49604 S
49604 S
49604 S
49604 S
104/115/125 115/123/132 119/127/136 124/131/139 124/131/139 124/131/139 124/131/139
40
38171 R
42531 R
45869 R
48647 R
49604 S
49604 S
49604 S
103/113/124 112/121/130 118/126/134 123/130/138 124/131/139 124/131/139 124/131/139
44
37654 R
41062 R
44820 R
47317 R
49604 S
49604 S
49604 S
103/113/123 110/119/128 117/125/133 121/128/136 125/132/139 125/132/139 125/132/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
74 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 1500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
43844 R
46920 R
49604 S
49604 S
49604 S
49604 S
49604 S
113/122/131 119/127/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
4
43075 R
46574 R
49604 S
49604 S
49604 S
49604 S
49604 S
112/121/130 118/126/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
8
42381 R
46256 R
49604 S
49604 S
49604 S
49604 S
49604 S
110/120/129 117/126/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
12
41784 R
46015 R
49286 R
49604 S
49604 S
49604 S
49604 S
109/119/129 117/125/134 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
16
41301 R
45777 R
48962 R
49604 S
49604 S
49604 S
49604 S
109/118/128 117/125/134 122/130/138 123/130/139 123/130/139 123/130/139 123/130/139
20
40857 R
45532 R
48635 R
49604 S
49604 S
49604 S
49604 S
108/117/127 116/124/134 122/129/138 123/130/139 123/130/139 123/130/139 123/130/139
24
40460 R
45288 R
48299 R
49604 S
49604 S
49604 S
49604 S
108/116/127 116/124/133 121/129/137 123/130/139 123/130/139 123/130/139 123/130/139
28
40078 R
45026 R
47932 R
49604 S
49604 S
49604 S
49604 S
107/116/126 115/124/133 120/128/137 123/130/139 123/130/139 123/130/139 123/130/139
32
39300 R
44487 R
47199 R
49604 S
49604 S
49604 S
49604 S
105/115/125 115/123/132 119/127/136 123/131/139 123/131/139 123/131/139 123/131/139
36
38333 R
43003 R
46107 R
48934 R
49604 S
49604 S
49604 S
103/114/124 112/121/130 118/126/134 123/130/138 124/131/139 124/131/139 124/131/139
40
37788 R
41426 R
45148 R
47728 R
49604 S
49604 S
49604 S
103/113/123 110/119/128 117/125/133 121/129/137 124/131/139 124/131/139 124/131/139
44
36998 R
40291 R
44081 R
46408 R
48940 R
49604 S
49604 S
103/112/122 109/118/127 117/124/132 120/127/135 124/131/138 125/132/139 125/132/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
75 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 2000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
42687 R
46392 R
49604 S
49604 S
49604 S
49604 S
49604 S
111/120/130 118/126/135 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
4
42007 R
46110 R
49417 R
49604 S
49604 S
49604 S
49604 S
110/119/129 117/126/134 123/130/139 123/131/139 123/131/139 123/131/139 123/131/139
8
41469 R
45863 R
49078 R
49604 S
49604 S
49604 S
49604 S
109/118/128 117/125/134 122/130/138 123/131/139 123/131/139 123/131/139 123/131/139
12
41013 R
45622 R
48753 R
49604 S
49604 S
49604 S
49604 S
108/118/128 117/125/134 122/129/138 123/131/139 123/131/139 123/131/139 123/131/139
16
40606 R
45381 R
48431 R
49604 S
49604 S
49604 S
49604 S
108/117/127 116/124/134 121/129/137 123/131/139 123/131/139 123/131/139 123/131/139
20
40234 R
45137 R
48086 R
49604 S
49604 S
49604 S
49604 S
107/116/126 116/124/133 121/128/137 123/131/139 123/131/139 123/131/139 123/131/139
24
39898 R
44892 R
47748 R
49604 S
49604 S
49604 S
49604 S
106/116/126 115/124/133 120/128/137 123/131/139 123/131/139 123/131/139 123/131/139
28
39432 R
44571 R
47311 R
49604 S
49604 S
49604 S
49604 S
105/115/126 115/123/132 119/127/136 123/131/139 123/131/139 123/131/139 123/131/139
32
38531 R
43525 R
46369 R
49244 R
49604 S
49604 S
49604 S
104/114/124 113/122/131 118/126/135 123/130/138 124/131/139 124/131/139 124/131/139
36
37912 R
41741 R
45411 R
48064 R
49604 S
49604 S
49604 S
103/113/123 111/120/129 117/125/134 122/129/137 124/131/139 124/131/139 124/131/139
40
37527 R
40699 R
44466 R
46881 R
49404 R
49604 S
49604 S
103/113/123 110/118/127 117/124/132 121/128/135 124/131/139 125/132/139 125/132/139
44
36090 R
39534 R
42786 R
45623 R
48047 R
49604 S
49604 S
101/111/120 109/117/125 115/122/130 120/126/134 123/130/137 126/132/139 126/132/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
76 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 2500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
41740 R
45994 R
49257 R
49604 S
49604 S
49604 S
49604 S
110/119/129 117/125/134 123/130/138 123/131/139 123/131/139 123/131/139 123/131/139
4
41225 R
45737 R
48908 R
49604 S
49604 S
49604 S
49604 S
109/118/128 117/125/134 122/130/138 123/131/139 123/131/139 123/131/139 123/131/139
8
40790 R
45493 R
48583 R
49604 S
49604 S
49604 S
49604 S
108/117/127 117/125/134 122/129/138 123/131/139 123/131/139 123/131/139 123/131/139
12
40412 R
45257 R
48255 R
49604 S
49604 S
49604 S
49604 S
107/117/127 116/124/133 121/129/137 123/131/139 123/131/139 123/131/139 123/131/139
16
40058 R
45011 R
47912 R
49604 S
49604 S
49604 S
49604 S
106/116/126 116/124/133 121/128/137 123/131/139 123/131/139 123/131/139 123/131/139
20
39736 R
44766 R
47575 R
49604 S
49604 S
49604 S
49604 S
105/115/126 115/124/133 120/128/136 123/131/139 123/131/139 123/131/139 123/131/139
24
39324 R
44502 R
47220 R
49604 S
49604 S
49604 S
49604 S
105/115/125 115/123/132 120/127/136 123/131/139 123/131/139 123/131/139 123/131/139
28
38692 R
43909 R
46580 R
49467 R
49604 S
49604 S
49604 S
105/114/125 114/122/132 118/126/135 123/130/139 123/131/139 123/131/139 123/131/139
32
38041 R
42117 R
45651 R
48376 R
49604 S
49604 S
49604 S
103/113/123 111/120/129 117/125/134 122/129/137 124/131/139 124/131/139 124/131/139
36
37608 R
40935 R
44699 R
47167 R
49604 S
49604 S
49604 S
103/113/123 110/118/127 116/124/133 121/128/136 125/131/139 125/131/139 125/131/139
40
36491 R
39897 R
43393 R
45992 R
48500 R
49604 S
49604 S
102/111/121 109/117/126 115/123/131 120/127/134 124/130/138 125/132/139 125/132/139
44
35406 R
38773 R
41669 R
44857 R
47090 R
49419 R
49604 S
101/110/119 108/116/124 113/120/128 119/125/133 123/129/136 126/132/139 126/132/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
77 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 3000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
41020 R
45626 R
48758 R
49604 S
49604 S
49604 S
49604 S
108/118/128 117/125/134 122/130/138 124/131/139 124/131/139 124/131/139 124/131/139
4
40586 R
45368 R
48412 R
49604 S
49604 S
49604 S
49604 S
107/117/127 116/125/133 122/129/137 124/131/139 124/131/139 124/131/139 124/131/139
8
40229 R
45133 R
48081 R
49604 S
49604 S
49604 S
49604 S
106/116/126 116/124/133 121/129/137 124/131/139 124/131/139 124/131/139 124/131/139
12
39901 R
44895 R
47751 R
49604 S
49604 S
49604 S
49604 S
106/116/126 116/124/133 121/128/137 124/131/139 124/131/139 124/131/139 124/131/139
16
39557 R
44648 R
47416 R
49604 S
49604 S
49604 S
49604 S
105/115/126 115/124/133 120/128/136 124/131/139 124/131/139 124/131/139 124/131/139
20
39172 R
44402 R
47086 R
49604 S
49604 S
49604 S
49604 S
104/115/125 115/123/132 119/127/136 124/131/139 124/131/139 124/131/139 124/131/139
24
38759 R
44059 R
46661 R
49553 R
49604 S
49604 S
49604 S
104/114/124 114/123/132 119/127/135 124/131/139 124/131/139 124/131/139 124/131/139
28
38208 R
42642 R
45925 R
48715 R
49604 S
49604 S
49604 S
104/113/124 111/120/130 117/125/134 122/130/138 124/131/139 124/131/139 124/131/139
32
37709 R
41216 R
44961 R
47494 R
49604 S
49604 S
49604 S
102/113/123 110/119/128 117/124/133 121/128/136 124/131/139 124/131/139 124/131/139
36
36874 R
40200 R
43920 R
46304 R
48839 R
49604 S
49604 S
102/112/122 109/117/126 116/123/132 120/127/135 124/131/138 125/132/139 125/132/139
40
35718 R
39146 R
42165 R
45230 R
47560 R
49604 S
49604 S
101/110/120 108/116/125 114/121/129 119/126/133 123/129/136 126/132/139 126/132/139
44
34471 R
38057 R
40861 R
44147 R
46196 R
48552 R
49137 W
100/108/118 107/115/123 112/119/127 118/125/132 122/128/135 125/131/138 126/132/138
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
78 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 3500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
40369 R
45228 R
48215 R
49604 S
49604 S
49604 S
49604 S
107/117/127 116/125/133 121/129/137 124/131/139 124/131/139 124/131/139 124/131/139
4
40013 R
44979 R
47867 R
49604 S
49604 S
49604 S
49604 S
106/116/126 116/124/133 121/128/137 124/131/139 124/131/139 124/131/139 124/131/139
8
39707 R
44742 R
47543 R
49604 S
49604 S
49604 S
49604 S
106/116/126 116/124/133 120/128/136 124/131/139 124/131/139 124/131/139 124/131/139
12
39321 R
44501 R
47217 R
49604 S
49604 S
49604 S
49604 S
105/115/125 115/123/132 120/127/136 124/131/139 124/131/139 124/131/139 124/131/139
16
38962 R
44253 R
46890 R
49604 S
49604 S
49604 S
49604 S
104/115/125 115/123/132 119/127/135 124/131/139 124/131/139 124/131/139 124/131/139
20
38674 R
43867 R
46557 R
49443 R
49604 S
49604 S
49604 S
104/114/124 114/122/131 119/127/135 124/131/139 124/131/139 124/131/139 124/131/139
24
38243 R
42746 R
45978 R
48779 R
49604 S
49604 S
49604 S
104/113/124 112/121/130 118/126/134 122/130/138 124/131/139 124/131/139 124/131/139
28
37814 R
41492 R
45204 R
47800 R
49604 S
49604 S
49604 S
103/113/123 110/119/128 117/125/133 121/128/137 124/131/139 124/131/139 124/131/139
32
37246 R
40462 R
44242 R
46603 R
49130 R
49604 S
49604 S
102/112/122 109/118/127 116/124/132 120/127/135 124/131/138 125/131/139 125/131/139
36
35976 R
39421 R
42603 R
45508 R
47906 R
49604 S
49604 S
101/110/120 108/116/125 114/122/130 119/126/134 123/129/137 125/132/139 125/132/139
40
34897 R
38382 R
41228 R
44468 R
46594 R
48945 R
49604 S
100/109/119 107/115/124 113/120/128 118/125/132 122/128/135 125/131/138 126/132/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
79 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 4000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
39830 R
44840 R
47676 R
49604 S
49604 S
49604 S
49604 S
106/116/126 116/124/133 121/128/136 124/131/139 124/131/139 124/131/139 124/131/139
4
39471 R
44595 R
47344 R
49604 S
49604 S
49604 S
49604 S
105/115/125 116/124/132 120/128/136 124/131/139 124/131/139 124/131/139 124/131/139
8
39104 R
44356 R
47025 R
49604 S
49604 S
49604 S
49604 S
105/115/125 115/123/132 120/127/136 124/131/139 124/131/139 124/131/139 124/131/139
12
38799 R
44115 R
46709 R
49603 R
49604 S
49604 S
49604 S
104/114/124 115/123/132 119/127/135 124/131/139 124/131/139 124/131/139 124/131/139
16
38542 R
43552 R
46384 R
49260 R
49604 S
49604 S
49604 S
103/114/124 114/122/131 119/126/135 123/131/138 124/131/139 124/131/139 124/131/139
20
38315 R
42952 R
46081 R
48903 R
49604 S
49604 S
49604 S
103/114/124 112/121/130 118/126/134 123/130/138 124/131/139 124/131/139 124/131/139
24
37879 R
41658 R
45343 R
47977 R
49604 S
49604 S
49604 S
103/113/123 110/119/128 117/125/133 121/129/137 124/131/139 124/131/139 124/131/139
28
37541 R
40740 R
44507 R
46932 R
49455 R
49604 S
49604 S
102/112/123 109/118/127 116/124/132 120/127/136 124/131/139 124/131/139 124/131/139
32
36275 R
39708 R
43074 R
45799 R
48265 R
49604 S
49604 S
101/111/121 108/117/126 114/122/130 119/126/134 123/130/137 125/132/139 125/132/139
36
35330 R
38674 R
41558 R
44759 R
46965 R
49300 R
49604 S
100/109/119 107/115/124 113/120/128 118/125/133 122/128/136 126/132/139 126/132/139
40
34101 R
37667 R
40422 R
43522 R
45770 R
48024 R
49406 W
99/108/117 106/114/123 112/119/127 117/124/131 121/127/134 125/130/137 127/132/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
80 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 4500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
39184 R
44410 R
47097 R
49604 S
49604 S
49604 S
49604 S
105/115/125 115/124/132 120/128/136 124/131/139 124/131/139 124/131/139 124/131/139
4
38861 R
44170 R
46780 R
49604 S
49604 S
49604 S
49604 S
104/115/125 115/123/132 120/127/135 124/131/139 124/131/139 124/131/139 124/131/139
8
38608 R
43711 R
46472 R
49353 R
49604 S
49604 S
49604 S
104/114/124 114/122/131 119/127/135 124/131/139 124/131/139 124/131/139 124/131/139
12
38389 R
43157 R
46182 R
49026 R
49604 S
49604 S
49604 S
103/114/124 113/122/131 119/126/135 123/130/138 124/131/139 124/131/139 124/131/139
16
38192 R
42595 R
45901 R
48686 R
49604 S
49604 S
49604 S
103/113/124 112/121/130 118/126/134 123/130/138 124/131/139 124/131/139 124/131/139
20
37916 R
41751 R
45419 R
48074 R
49604 S
49604 S
49604 S
102/113/123 110/120/129 117/125/134 122/129/137 124/131/139 124/131/139 124/131/139
24
37596 R
40900 R
44665 R
47126 R
49604 S
49604 S
49604 S
102/112/123 109/118/127 116/124/133 120/128/136 124/131/139 124/131/139 124/131/139
28
36544 R
39942 R
43470 R
46038 R
48551 R
49604 S
49604 S
101/111/122 108/117/126 114/122/131 119/126/134 123/130/138 125/131/139 125/131/139
32
35536 R
38934 R
41851 R
45018 R
47293 R
49604 S
49604 S
100/110/120 107/116/125 113/120/129 118/125/133 122/129/136 125/132/139 125/132/139
36
34337 R
37930 R
40718 R
43968 R
46057 R
48384 R
49604 S
99/108/118 106/114/123 112/119/127 118/124/132 121/127/134 125/131/137 127/132/139
40
33643 R
36947 R
39604 R
42350 R
44986 R
47022 R
48408 W
99/107/117 105/113/122 111/118/126 116/122/129 120/126/133 124/129/136 126/131/137
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
81 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 5000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
38662 R
43839 R
46542 R
49427 R
49604 S
49604 S
49604 S
105/114/124 115/123/131 119/127/135 124/131/139 124/131/139 124/131/139 124/131/139
4
38445 R
43305 R
46254 R
49115 R
49604 S
49604 S
49604 S
104/114/124 114/122/131 119/126/135 123/131/138 124/131/139 124/131/139 124/131/139
8
38253 R
42776 R
45993 R
48797 R
49604 S
49604 S
49604 S
103/114/124 113/121/130 118/126/134 123/130/138 124/131/139 124/131/139 124/131/139
12
38086 R
42265 R
45730 R
48478 R
49604 S
49604 S
49604 S
103/113/123 112/120/129 118/126/134 122/130/137 124/131/139 124/131/139 124/131/139
16
37923 R
41767 R
45431 R
48090 R
49604 S
49604 S
49604 S
103/113/123 111/120/129 117/125/134 122/129/137 124/131/139 124/131/139 124/131/139
20
37642 R
41030 R
44790 R
47280 R
49604 S
49604 S
49604 S
102/113/123 109/118/128 116/124/133 121/128/136 124/131/139 124/131/139 124/131/139
24
36840 R
40176 R
43876 R
46277 R
48811 R
49604 S
49604 S
102/112/122 108/117/126 115/123/132 119/127/135 123/130/138 124/131/139 124/131/139
28
35756 R
39188 R
42231 R
45273 R
47613 R
49604 S
49604 S
100/110/120 107/116/125 113/121/129 118/125/133 122/129/136 125/132/139 125/132/139
32
34637 R
38195 R
41018 R
44284 R
46357 R
48720 R
49604 S
99/108/118 106/115/124 112/119/128 118/124/132 121/127/135 125/131/138 126/132/139
36
33794 R
37215 R
39920 R
42792 R
45287 R
47410 R
49527 W
98/107/117 105/113/122 111/118/126 116/123/130 121/126/133 124/129/136 127/132/139
40
33099 R
36336 R
38863 R
41417 R
44261 R
46109 R
47424 W
98/106/116 105/112/121 110/117/125 115/121/128 120/125/132 123/128/134 125/130/136
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
82 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 5500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
38232 R
42713 R
45962 R
48758 R
49604 S
49604 S
49604 S
104/114/124 113/121/130 119/126/134 123/130/138 125/131/139 125/131/139 125/131/139
4
38072 R
42219 R
45706 R
48447 R
49604 S
49604 S
49604 S
104/114/123 112/120/129 118/126/134 123/130/137 124/131/139 124/131/139 124/131/139
8
37930 R
41784 R
45445 R
48108 R
49604 S
49604 S
49604 S
103/113/123 111/120/129 118/125/134 122/129/137 124/131/139 124/131/139 124/131/139
12
37804 R
41466 R
45182 R
47771 R
49604 S
49604 S
49604 S
103/113/123 111/119/128 117/125/133 122/129/137 124/131/139 124/131/139 124/131/139
16
37637 R
41015 R
44776 R
47263 R
49604 S
49604 S
49604 S
103/113/123 110/119/128 117/124/133 121/128/136 124/131/139 124/131/139 124/131/139
20
37021 R
40307 R
44101 R
46426 R
48957 R
49604 S
49604 S
101/112/122 108/117/127 115/123/132 120/127/135 123/131/138 125/131/139 125/131/139
24
35975 R
39420 R
42601 R
45507 R
47904 R
49604 S
49604 S
101/110/121 107/116/125 113/121/130 118/126/134 122/129/137 125/132/139 125/132/139
28
34953 R
38417 R
41268 R
44503 R
46639 R
48989 R
49604 S
99/109/119 106/115/124 112/119/128 117/124/132 121/128/135 125/131/138 125/132/139
32
33931 R
37436 R
40163 R
43142 R
45521 R
47708 R
49604 S
98/107/117 105/114/122 111/118/126 116/123/131 120/126/134 124/130/136 127/132/139
36
33366 R
36535 R
39088 R
41684 R
44490 R
46374 R
48434 W
98/107/116 105/112/121 110/117/125 115/121/129 120/125/132 123/128/135 126/131/137
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
83 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 6000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
37922 R
41765 R
45430 R
48089 R
49604 S
49604 S
49604 S
104/113/123 112/120/129 118/126/134 122/129/137 125/132/139 125/132/139 125/132/139
4
37799 R
41455 R
45172 R
47759 R
49604 S
49604 S
49604 S
103/113/123 111/119/128 118/125/133 122/129/137 125/132/139 125/132/139 125/132/139
8
37689 R
41160 R
44911 R
47430 R
49604 S
49604 S
49604 S
103/113/123 110/119/128 117/125/133 121/128/136 125/132/139 125/132/139 125/132/139
12
37590 R
40883 R
44649 R
47106 R
49604 S
49604 S
49604 S
103/113/123 110/118/127 117/124/133 121/128/136 125/132/139 125/132/139 125/132/139
16
37087 R
40354 R
44144 R
46480 R
49009 R
49604 S
49604 S
102/112/122 109/118/127 116/124/132 120/127/135 124/131/138 125/132/139 125/132/139
20
36167 R
39608 R
42907 R
45697 R
48139 R
49604 S
49604 S
101/111/121 107/116/126 114/122/130 118/126/134 122/129/137 125/132/139 125/132/139
24
35333 R
38678 R
41561 R
44762 R
46969 R
49304 R
49604 S
100/109/119 106/115/124 112/120/128 117/125/133 121/128/136 124/131/139 125/132/139
28
34108 R
37676 R
40431 R
43536 R
45779 R
48036 R
49604 S
98/108/118 105/114/123 111/118/127 116/123/131 120/127/134 124/130/137 126/132/139
32
33536 R
36739 R
39344 R
41994 R
44738 R
46700 R
48897 R
98/107/117 104/113/121 110/117/125 115/121/129 120/126/133 123/128/135 126/132/138
36
31963 R
35861 R
38359 R
40824 R
43528 R
45538 R
47351 W
96/105/115 104/111/120 109/116/124 114/120/127 119/124/131 122/127/134 125/130/136
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
84 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 6500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
37674 R
41120 R
44874 R
47384 R
49604 S
49604 S
49604 S
103/113/123 111/119/128 117/125/133 121/128/136 125/132/139 125/132/139 125/132/139
4
37578 R
40848 R
44614 R
47063 R
49590 R
49604 S
49604 S
103/113/123 110/118/127 117/124/132 121/128/136 125/132/139 125/132/139 125/132/139
8
37432 R
40581 R
44351 R
46740 R
49263 R
49604 S
49604 S
103/113/122 110/118/127 117/124/132 120/128/135 124/131/138 125/132/139 125/132/139
12
36934 R
40245 R
43998 R
46354 R
48888 R
49604 S
49604 S
102/112/122 109/117/126 116/123/132 120/127/135 124/131/138 125/132/139 125/132/139
16
36178 R
39618 R
42925 R
45708 R
48152 R
49604 S
49604 S
100/111/121 108/116/126 114/122/130 119/126/134 123/130/137 125/132/139 125/132/139
20
35487 R
38874 R
41783 R
44958 R
47217 R
49541 R
49604 S
100/109/120 106/115/125 112/120/129 118/125/133 121/128/136 125/132/139 125/132/139
24
34316 R
37908 R
40693 R
43931 R
46033 R
48355 R
49604 S
99/108/118 105/114/123 111/119/127 117/124/132 120/127/134 124/130/137 126/132/139
28
33634 R
36930 R
39584 R
42321 R
44966 R
46996 R
49175 R
98/107/117 104/113/122 110/117/126 115/122/129 119/126/133 123/129/136 126/132/138
32
32397 R
36068 R
38574 R
41075 R
43883 R
45782 R
47813 R
96/106/115 104/112/120 109/116/124 114/120/128 119/124/132 122/127/134 125/130/137
36
30960 R
35065 R
37642 R
39997 R
42377 R
44721 R
46251 W
94/103/113 103/110/119 108/115/123 113/119/126 117/123/129 121/126/133 124/128/135
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
85 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 7000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
37406 R
40564 R
44336 R
46721 R
49244 R
49604 S
49604 S
103/113/122 110/118/127 117/124/132 121/128/135 125/131/138 125/132/139 125/132/139
4
36974 R
40274 R
44050 R
46388 R
48920 R
49604 S
49604 S
102/112/122 109/118/127 116/124/132 120/127/135 124/131/138 125/132/139 125/132/139
8
36601 R
39989 R
43550 R
46086 R
48603 R
49604 S
49604 S
102/112/121 109/117/126 115/123/131 120/127/134 124/130/138 125/132/139 125/132/139
12
36144 R
39586 R
42872 R
45676 R
48113 R
49604 S
49604 S
101/111/121 108/116/126 114/122/130 119/126/134 123/130/137 125/132/139 125/132/139
16
35527 R
38922 R
41838 R
45006 R
47279 R
49600 R
49604 S
100/109/120 107/115/125 112/120/129 118/125/133 122/128/136 125/132/139 125/132/139
20
34616 R
38179 R
40999 R
44267 R
46335 R
48700 R
49604 S
100/108/119 105/114/124 111/119/128 117/124/132 120/127/135 124/130/138 125/132/139
24
33762 R
37161 R
39858 R
42704 R
45228 R
47333 R
49493 R
98/107/118 104/113/122 110/117/126 115/122/130 119/126/133 123/129/136 126/132/139
28
32979 R
36284 R
38806 R
41349 R
44202 R
46044 R
48163 R
97/106/116 104/112/121 109/116/124 114/120/128 119/125/132 122/128/134 125/131/137
32
31223 R
35361 R
37869 R
40257 R
42736 R
44981 R
46780 R
94/104/114 103/111/119 108/115/123 113/119/127 117/123/130 121/126/133 124/129/135
36
30892 R
34270 R
36905 R
39230 R
41425 R
43881 R
45182 W
94/103/113 102/109/118 107/114/122 112/118/125 116/121/128 120/125/132 123/127/133
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
86 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 7500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
36547 R
39944 R
43473 R
46040 R
48553 R
49604 S
49604 S
102/112/121 109/117/126 116/123/131 120/127/134 124/130/138 126/132/139 126/132/139
4
36222 R
39659 R
42993 R
45750 R
48204 R
49604 S
49604 S
101/111/121 109/117/126 115/122/130 120/126/134 123/130/137 126/132/139 126/132/139
8
35934 R
39378 R
42534 R
45465 R
47852 R
49604 S
49604 S
101/110/120 108/116/125 114/122/130 119/126/134 123/129/137 126/132/139 126/132/139
12
35494 R
38883 R
41793 R
44967 R
47229 R
49552 R
49604 S
100/109/120 107/116/125 113/120/129 118/125/133 122/129/136 125/132/139 126/132/139
16
34658 R
38212 R
41036 R
44300 R
46378 R
48740 R
49604 S
99/108/118 106/114/124 111/119/128 117/124/132 121/127/135 124/131/138 126/132/139
20
33914 R
37410 R
40135 R
43102 R
45494 R
47674 R
49604 S
99/108/118 104/113/122 110/118/126 115/122/130 119/126/134 123/129/136 126/132/139
24
33298 R
36485 R
39031 R
41616 R
44432 R
46298 R
48507 R
97/107/117 103/112/121 109/116/125 114/121/128 119/125/132 122/128/135 125/131/138
28
31481 R
35563 R
38062 R
40480 R
43046 R
45201 R
47059 R
95/104/115 103/111/120 108/115/123 113/119/127 117/123/130 121/126/133 124/129/136
32
30892 R
34467 R
37124 R
39447 R
41669 R
44170 R
45836 R
94/103/113 102/109/118 107/114/122 112/118/125 116/122/128 121/125/132 123/128/134
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
87 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE OFF Airport Pressure Altitude: 8000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) 0
35910 R
39352 R
42492 R
45439 R
47820 R
49604 S
49604 S
101/110/120 108/116/125 114/122/130 120/126/134 123/130/137 126/132/139 126/132/139
4
35652 R
39070 R
42048 R
45155 R
47465 R
49604 S
49604 S
101/110/120 108/116/125 114/121/129 119/126/133 123/129/136 126/132/139 126/132/139
8
35421 R
38791 R
41689 R
44875 R
47113 R
49441 R
49604 S
100/110/119 107/116/124 113/120/129 119/125/133 122/129/136 126/132/139 126/132/139
12
34649 R
38205 R
41029 R
44293 R
46369 R
48732 R
49604 S
99/108/118 106/115/124 112/119/128 118/124/132 121/127/135 125/131/138 126/132/139
16
34005 R
37542 R
40281 R
43314 R
45634 R
47852 R
49604 S
98/108/118 105/113/123 110/118/127 116/123/131 120/126/134 123/130/137 126/132/139
20
33528 R
36722 R
39322 R
41965 R
44718 R
46673 R
48873 R
98/107/117 103/112/121 109/117/125 114/121/129 119/125/133 122/128/135 125/131/138
24
31853 R
35801 R
38297 R
40752 R
43428 R
45468 R
47402 R
96/105/115 103/111/120 108/115/124 113/119/127 118/124/131 121/127/134 124/129/136
28
30891 R
34703 R
37356 R
39685 R
41948 R
44406 R
46094 R
94/103/114 102/109/118 107/114/122 112/118/126 116/122/129 120/126/132 123/128/134
32
30893 R
33845 R
36324 R
38689 R
40820 R
43069 R
44950 W
95/103/113 101/108/117 107/113/121 111/117/124 115/120/127 119/124/130 122/127/133
NOTE: The values above do not take into account obstacles
Page
1-04-15
Code
88 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: Sea Level Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
47540 R
49604 S
49604 S
49604 S
49604 S
49604 S
49604 S
119/127/136 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-30
47135 R
49604 S
49604 S
49604 S
49604 S
49604 S
49604 S
118/127/136 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-26
46745 R
49604 S
49604 S
49604 S
49604 S
49604 S
49604 S
118/126/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-22
46364 R
49604 S
49604 S
49604 S
49604 S
49604 S
49604 S
117/125/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-18
46082 R
49604 S
49604 S
49604 S
49604 S
49604 S
49604 S
117/125/134 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-14
45827 R
49604 S
49604 S
49604 S
49604 S
49604 S
49604 S
116/125/134 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-10
45575 R
49272 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/124/134 122/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-6
45324 R
48899 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/124/133 121/129/138 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-2
45053 R
48501 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/123/133 121/129/138 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
2
44792 R
48093 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/133 120/128/137 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
6
44551 R
47720 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/132 119/127/137 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
10
44311 R
47355 R
49604 S
49604 S
49604 S
49604 S
49604 S
113/122/132 119/127/136 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
89 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
47000 R
49604 S
49604 S
49604 S
49604 S
49604 S
49604 S
118/126/136 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-30
46609 R
49604 S
49604 S
49604 S
49604 S
49604 S
49604 S
118/126/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-26
46242 R
49604 S
49604 S
49604 S
49604 S
49604 S
49604 S
117/125/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-22
45981 R
49604 S
49604 S
49604 S
49604 S
49604 S
49604 S
117/125/134 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-18
45722 R
49491 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/125/134 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-14
45465 R
49108 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/124/134 122/130/138 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-10
45214 R
48737 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/124/133 121/129/138 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-6
44965 R
48362 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/123/133 121/128/137 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-2
44685 R
47926 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/133 120/128/137 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
2
44417 R
47517 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/132 119/127/136 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
6
44175 R
47150 R
49604 S
49604 S
49604 S
49604 S
49604 S
113/122/132 119/127/136 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
10
43566 R
46797 R
49604 S
49604 S
49604 S
49604 S
49604 S
112/121/131 118/126/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
90 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 1000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
46488 R
49604 S
49604 S
49604 S
49604 S
49604 S
49604 S
118/126/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-30
46162 R
49604 S
49604 S
49604 S
49604 S
49604 S
49604 S
117/125/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-26
45880 R
49604 S
49604 S
49604 S
49604 S
49604 S
49604 S
117/125/134 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-22
45627 R
49349 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/125/134 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-18
45372 R
48969 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/124/133 122/129/138 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-14
45114 R
48590 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/124/133 121/129/138 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-10
44864 R
48205 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/123/133 121/128/137 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-6
44616 R
47820 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/132 120/128/137 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-2
44328 R
47381 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/132 119/127/136 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
2
43965 R
46973 R
49604 S
49604 S
49604 S
49604 S
49604 S
113/122/132 119/127/136 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
6
43177 R
46621 R
49604 S
49604 S
49604 S
49604 S
49604 S
112/121/131 118/126/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
10
42445 R
46280 R
49604 S
49604 S
49604 S
49604 S
49604 S
110/120/130 117/126/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
91 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 1500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
46062 R
49604 S
49604 S
49604 S
49604 S
49604 S
49604 S
117/125/134 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-30
45793 R
49598 R
49604 S
49604 S
49604 S
49604 S
49604 S
117/125/134 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-26
45519 R
49187 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/124/134 122/130/138 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-22
45262 R
48808 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/124/133 122/129/138 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-18
45009 R
48431 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/124/133 121/129/137 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-14
44756 R
48036 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/123/133 121/128/137 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-10
44509 R
47656 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/132 120/128/136 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-6
44259 R
47276 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/132 119/127/136 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
-2
43653 R
46836 R
49604 S
49604 S
49604 S
49604 S
49604 S
113/122/131 118/126/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
2
42763 R
46428 R
49604 S
49604 S
49604 S
49604 S
49604 S
111/120/130 118/126/135 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
6
42074 R
46137 R
49453 R
49604 S
49604 S
49604 S
49604 S
110/119/129 117/125/134 123/130/139 123/130/139 123/130/139 123/130/139 123/130/139
10
41527 R
45892 R
49117 R
49604 S
49604 S
49604 S
49604 S
109/118/128 117/125/134 122/130/138 123/130/139 123/130/139 123/130/139 123/130/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
92 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 2000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
45702 R
49461 R
49604 S
49604 S
49604 S
49604 S
49604 S
117/125/134 123/130/139 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
-30
45435 R
49062 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/124/134 122/130/138 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
-26
45168 R
48669 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/124/133 122/129/138 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
-22
44909 R
48274 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/124/133 121/129/137 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
-18
44657 R
47883 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/123/133 120/128/137 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
-14
44409 R
47504 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/132 120/128/136 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
-10
44164 R
47134 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/132 119/127/136 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
-6
43498 R
46767 R
49604 S
49604 S
49604 S
49604 S
49604 S
113/122/131 119/126/135 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
-2
42551 R
46326 R
49604 S
49604 S
49604 S
49604 S
49604 S
111/120/130 118/126/135 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
2
41737 R
45993 R
49255 R
49604 S
49604 S
49604 S
49604 S
109/119/129 117/125/134 123/130/138 123/131/139 123/131/139 123/131/139 123/131/139
6
41223 R
45736 R
48906 R
49604 S
49604 S
49604 S
49604 S
109/118/128 117/125/134 122/130/138 123/131/139 123/131/139 123/131/139 123/131/139
10
40824 R
45513 R
48610 R
49604 S
49604 S
49604 S
49604 S
108/117/127 116/125/134 122/129/138 123/131/139 123/131/139 123/131/139 123/131/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
93 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 2500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
45320 R
48892 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/124/133 122/130/138 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
-30
45053 R
48500 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/124/133 122/129/138 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
-26
44795 R
48097 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/124/133 121/128/137 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
-22
44542 R
47706 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/123/132 120/128/136 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
-18
44288 R
47321 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/132 120/127/136 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
-14
43907 R
46948 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/122/132 119/127/136 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
-10
43137 R
46603 R
49604 S
49604 S
49604 S
49604 S
49604 S
112/121/130 118/126/135 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
-6
42397 R
46262 R
49604 S
49604 S
49604 S
49604 S
49604 S
111/120/129 118/126/135 123/131/139 123/131/139 123/131/139 123/131/139 123/131/139
-2
41608 R
45931 R
49171 R
49604 S
49604 S
49604 S
49604 S
109/119/128 117/125/134 123/130/138 123/131/139 123/131/139 123/131/139 123/131/139
2
41007 R
45618 R
48749 R
49604 S
49604 S
49604 S
49604 S
108/118/128 117/125/134 122/129/138 123/131/139 123/131/139 123/131/139 123/131/139
6
40586 R
45368 R
48412 R
49604 S
49604 S
49604 S
49604 S
107/117/127 116/124/133 121/129/137 123/131/139 123/131/139 123/131/139 123/131/139
10
40264 R
45157 R
48115 R
49604 S
49604 S
49604 S
49604 S
107/116/127 116/124/133 121/129/137 123/131/139 123/131/139 123/131/139 123/131/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
94 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 3000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
44951 R
48340 R
49604 S
49604 S
49604 S
49604 S
49604 S
116/124/133 122/129/137 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-30
44683 R
47923 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/124/133 121/128/137 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-26
44434 R
47542 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/123/132 120/128/136 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-22
44186 R
47167 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/132 120/127/136 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-18
43560 R
46795 R
49604 S
49604 S
49604 S
49604 S
49604 S
113/122/131 119/127/135 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-14
42769 R
46431 R
49604 S
49604 S
49604 S
49604 S
49604 S
112/121/130 118/126/135 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-10
42089 R
46143 R
49462 R
49604 S
49604 S
49604 S
49604 S
110/120/129 118/126/134 123/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-6
41491 R
45874 R
49093 R
49604 S
49604 S
49604 S
49604 S
109/119/128 117/125/134 123/130/138 124/131/139 124/131/139 124/131/139 124/131/139
-2
40891 R
45552 R
48661 R
49604 S
49604 S
49604 S
49604 S
108/118/127 117/125/134 122/129/138 124/131/139 124/131/139 124/131/139 124/131/139
2
40406 R
45253 R
48249 R
49604 S
49604 S
49604 S
49604 S
107/117/127 116/124/133 121/129/137 124/131/139 124/131/139 124/131/139 124/131/139
6
40054 R
45009 R
47909 R
49604 S
49604 S
49604 S
49604 S
106/116/126 116/124/133 121/128/137 124/131/139 124/131/139 124/131/139 124/131/139
10
39790 R
44809 R
47634 R
49604 S
49604 S
49604 S
49604 S
105/116/126 115/124/133 120/128/136 124/131/139 124/131/139 124/131/139 124/131/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
95 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 3500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
44558 R
47731 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/123/132 121/128/137 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-30
44295 R
47331 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/123/132 120/128/136 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-26
43926 R
46956 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/123/132 119/127/136 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-22
43132 R
46600 R
49604 S
49604 S
49604 S
49604 S
49604 S
113/121/130 119/127/135 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-18
42388 R
46258 R
49604 S
49604 S
49604 S
49604 S
49604 S
111/120/129 118/126/135 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-14
41718 R
45984 R
49243 R
49604 S
49604 S
49604 S
49604 S
110/119/129 118/126/134 123/130/138 124/131/139 124/131/139 124/131/139 124/131/139
-10
41194 R
45721 R
48886 R
49604 S
49604 S
49604 S
49604 S
109/118/128 117/125/134 123/130/138 124/131/139 124/131/139 124/131/139 124/131/139
-6
40731 R
45457 R
48536 R
49604 S
49604 S
49604 S
49604 S
108/117/127 117/125/134 122/129/138 124/131/139 124/131/139 124/131/139 124/131/139
-2
40248 R
45146 R
48100 R
49604 S
49604 S
49604 S
49604 S
107/117/126 116/124/133 121/129/137 124/131/139 124/131/139 124/131/139 124/131/139
2
39855 R
44859 R
47703 R
49604 S
49604 S
49604 S
49604 S
106/116/126 116/124/133 121/128/136 124/131/139 124/131/139 124/131/139 124/131/139
6
39505 R
44617 R
47374 R
49604 S
49604 S
49604 S
49604 S
105/115/125 115/124/132 120/128/136 124/131/139 124/131/139 124/131/139 124/131/139
10
39109 R
44364 R
47036 R
49604 S
49604 S
49604 S
49604 S
104/115/125 115/123/132 120/127/136 124/131/139 124/131/139 124/131/139 124/131/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
96 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 4000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
44178 R
47155 R
49604 S
49604 S
49604 S
49604 S
49604 S
115/123/132 120/127/136 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-30
43523 R
46778 R
49604 S
49604 S
49604 S
49604 S
49604 S
114/122/131 119/127/135 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-26
42732 R
46413 R
49604 S
49604 S
49604 S
49604 S
49604 S
112/121/130 119/126/135 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-22
42021 R
46116 R
49424 R
49604 S
49604 S
49604 S
49604 S
111/120/129 118/126/134 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-18
41438 R
45847 R
49056 R
49604 S
49604 S
49604 S
49604 S
109/119/128 118/126/134 123/130/138 124/131/139 124/131/139 124/131/139 124/131/139
-14
40937 R
45578 R
48696 R
49604 S
49604 S
49604 S
49604 S
108/118/127 117/125/134 122/130/138 124/131/139 124/131/139 124/131/139 124/131/139
-10
40495 R
45310 R
48330 R
49604 S
49604 S
49604 S
49604 S
107/117/127 117/125/133 122/129/137 124/131/139 124/131/139 124/131/139 124/131/139
-6
40114 R
45052 R
47968 R
49604 S
49604 S
49604 S
49604 S
107/117/126 116/124/133 121/129/137 124/131/139 124/131/139 124/131/139 124/131/139
-2
39717 R
44750 R
47554 R
49604 S
49604 S
49604 S
49604 S
106/116/126 116/124/133 121/128/136 124/131/139 124/131/139 124/131/139 124/131/139
2
39278 R
44476 R
47184 R
49604 S
49604 S
49604 S
49604 S
105/115/125 115/123/132 120/128/136 124/131/139 124/131/139 124/131/139 124/131/139
6
38930 R
44236 R
46867 R
49604 S
49604 S
49604 S
49604 S
104/115/125 115/123/132 119/127/135 124/131/139 124/131/139 124/131/139 124/131/139
10
38597 R
43712 R
46473 R
49353 R
49604 S
49604 S
49604 S
103/114/124 114/122/131 119/127/135 124/131/139 124/131/139 124/131/139 124/131/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
97 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 4500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
43055 R
46565 R
49604 S
49604 S
49604 S
49604 S
49604 S
113/122/130 119/127/135 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-30
42294 R
46222 R
49573 R
49604 S
49604 S
49604 S
49604 S
111/120/129 119/126/135 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-26
41628 R
45941 R
49184 R
49604 S
49604 S
49604 S
49604 S
110/119/128 118/126/134 123/131/138 124/131/139 124/131/139 124/131/139 124/131/139
-22
41104 R
45672 R
48821 R
49604 S
49604 S
49604 S
49604 S
109/118/128 118/125/134 123/130/138 124/131/139 124/131/139 124/131/139 124/131/139
-18
40643 R
45404 R
48463 R
49604 S
49604 S
49604 S
49604 S
108/118/127 117/125/134 122/129/137 124/131/139 124/131/139 124/131/139 124/131/139
-14
40232 R
45135 R
48085 R
49604 S
49604 S
49604 S
49604 S
107/117/126 117/125/133 122/129/137 124/131/139 124/131/139 124/131/139 124/131/139
-10
39875 R
44875 R
47724 R
49604 S
49604 S
49604 S
49604 S
107/116/126 116/124/133 121/128/137 124/131/139 124/131/139 124/131/139 124/131/139
-6
39498 R
44614 R
47369 R
49604 S
49604 S
49604 S
49604 S
106/116/125 116/124/132 121/128/136 124/131/139 124/131/139 124/131/139 124/131/139
-2
39038 R
44316 R
46972 R
49604 S
49604 S
49604 S
49604 S
105/115/125 115/123/132 120/127/136 124/131/139 124/131/139 124/131/139 124/131/139
2
38720 R
43998 R
46628 R
49518 R
49604 S
49604 S
49604 S
104/114/124 115/123/132 119/127/135 124/131/139 124/131/139 124/131/139 124/131/139
6
38503 R
43481 R
46344 R
49218 R
49604 S
49604 S
49604 S
104/114/124 114/122/131 119/126/135 123/131/138 124/131/139 124/131/139 124/131/139
10
38070 R
42239 R
45716 R
48461 R
49604 S
49604 S
49604 S
103/113/123 111/120/129 118/125/134 122/129/137 124/131/139 124/131/139 124/131/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
98 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 5000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
41909 R
46071 R
49363 R
49604 S
49604 S
49604 S
49604 S
111/120/129 119/126/134 124/131/139 124/131/139 124/131/139 124/131/139 124/131/139
-30
41323 R
45789 R
48977 R
49604 S
49604 S
49604 S
49604 S
110/119/128 118/126/134 123/130/138 124/131/139 124/131/139 124/131/139 124/131/139
-26
40816 R
45508 R
48603 R
49604 S
49604 S
49604 S
49604 S
109/118/127 118/125/134 123/130/138 124/131/139 124/131/139 124/131/139 124/131/139
-22
40389 R
45241 R
48233 R
49604 S
49604 S
49604 S
49604 S
108/117/127 117/125/133 122/129/137 124/131/139 124/131/139 124/131/139 124/131/139
-18
40005 R
44972 R
47858 R
49604 S
49604 S
49604 S
49604 S
107/117/126 117/124/133 121/129/137 124/131/139 124/131/139 124/131/139 124/131/139
-14
39652 R
44705 R
47492 R
49604 S
49604 S
49604 S
49604 S
107/116/126 116/124/133 121/128/136 124/131/139 124/131/139 124/131/139 124/131/139
-10
39240 R
44451 R
47152 R
49604 S
49604 S
49604 S
49604 S
106/115/125 116/124/132 120/128/136 124/131/139 124/131/139 124/131/139 124/131/139
-6
38872 R
44188 R
46804 R
49604 S
49604 S
49604 S
49604 S
105/115/125 115/123/132 120/127/135 124/131/139 124/131/139 124/131/139 124/131/139
-2
38560 R
43622 R
46423 R
49301 R
49604 S
49604 S
49604 S
104/114/124 114/123/131 119/127/135 124/131/139 124/131/139 124/131/139 124/131/139
2
38341 R
43053 R
46131 R
48964 R
49604 S
49604 S
49604 S
104/114/124 113/122/130 119/126/134 123/130/138 124/131/139 124/131/139 124/131/139
6
38189 R
42615 R
45912 R
48698 R
49604 S
49604 S
49604 S
103/114/124 112/121/130 118/126/134 123/130/138 124/131/139 124/131/139 124/131/139
10
37729 R
41280 R
45019 R
47566 R
49604 S
49604 S
49604 S
102/113/123 110/119/128 117/125/133 121/128/136 124/131/139 124/131/139 124/131/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
99 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 5500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
40833 R
45518 R
48617 R
49604 S
49604 S
49604 S
49604 S
109/118/127 118/126/134 123/130/138 125/131/139 125/131/139 125/131/139 125/131/139
-30
40374 R
45231 R
48219 R
49604 S
49604 S
49604 S
49604 S
108/117/127 117/125/133 122/129/137 125/131/139 125/131/139 125/131/139 125/131/139
-26
39982 R
44955 R
47835 R
49604 S
49604 S
49604 S
49604 S
108/117/126 117/125/133 122/129/137 125/131/139 125/131/139 125/131/139 125/131/139
-22
39620 R
44686 R
47467 R
49604 S
49604 S
49604 S
49604 S
107/116/126 116/124/133 121/128/136 124/131/139 124/131/139 124/131/139 124/131/139
-18
39189 R
44418 R
47107 R
49604 S
49604 S
49604 S
49604 S
106/115/125 116/124/132 121/128/136 124/131/139 124/131/139 124/131/139 124/131/139
-14
38835 R
44156 R
46762 R
49604 S
49604 S
49604 S
49604 S
105/115/124 116/123/132 120/127/135 125/131/139 125/131/139 125/131/139 125/131/139
-10
38565 R
43634 R
46430 R
49308 R
49604 S
49604 S
49604 S
105/114/124 115/123/131 120/127/135 124/131/139 125/131/139 125/131/139 125/131/139
-6
38341 R
43053 R
46131 R
48964 R
49604 S
49604 S
49604 S
104/114/124 114/122/130 119/126/134 123/131/138 125/131/139 125/131/139 125/131/139
-2
38148 R
42489 R
45847 R
48620 R
49604 S
49604 S
49604 S
104/114/123 113/121/130 118/126/134 123/130/138 125/131/139 125/131/139 125/131/139
2
37998 R
42000 R
45588 R
48293 R
49604 S
49604 S
49604 S
103/113/123 112/120/129 118/126/134 122/130/137 124/131/139 124/131/139 124/131/139
6
37792 R
41448 R
45167 R
47753 R
49604 S
49604 S
49604 S
103/113/123 111/119/128 117/125/133 122/129/137 124/131/139 124/131/139 124/131/139
10
37296 R
40497 R
44274 R
46644 R
49169 R
49604 S
49604 S
102/112/122 109/118/127 116/124/132 120/127/135 124/131/138 124/131/139 124/131/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
100 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 6000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
40022 R
44985 R
47876 R
49604 S
49604 S
49604 S
49604 S
108/117/126 117/125/133 122/129/137 125/132/139 125/132/139 125/132/139 125/132/139
-30
39633 R
44694 R
47477 R
49604 S
49604 S
49604 S
49604 S
107/116/126 117/124/133 121/128/136 125/132/139 125/132/139 125/132/139 125/132/139
-26
39196 R
44422 R
47113 R
49604 S
49604 S
49604 S
49604 S
106/116/125 116/124/132 121/128/136 125/132/139 125/132/139 125/132/139 125/132/139
-22
38829 R
44151 R
46756 R
49604 S
49604 S
49604 S
49604 S
106/115/124 116/124/132 120/127/135 125/132/139 125/132/139 125/132/139 125/132/139
-18
38550 R
43598 R
46409 R
49287 R
49604 S
49604 S
49604 S
105/115/124 115/123/131 120/127/135 124/131/139 125/132/139 125/132/139 125/132/139
-14
38328 R
43017 R
46113 R
48943 R
49604 S
49604 S
49604 S
105/114/124 114/122/130 119/127/134 124/131/138 125/132/139 125/132/139 125/132/139
-10
38139 R
42460 R
45832 R
48603 R
49604 S
49604 S
49604 S
104/114/123 113/121/130 119/126/134 123/130/138 125/132/139 125/132/139 125/132/139
-6
37983 R
41949 R
45560 R
48258 R
49604 S
49604 S
49604 S
104/114/123 112/120/129 118/126/134 123/130/137 125/132/139 125/132/139 125/132/139
-2
37857 R
41617 R
45309 R
47933 R
49604 S
49604 S
49604 S
104/113/123 111/120/128 118/125/133 122/129/137 125/132/139 125/132/139 125/132/139
2
37748 R
41330 R
45064 R
47622 R
49604 S
49604 S
49604 S
103/113/123 111/119/128 117/125/133 122/129/136 125/132/139 125/132/139 125/132/139
6
37524 R
40691 R
44457 R
46870 R
49393 R
49604 S
49604 S
103/113/123 109/118/127 116/124/132 120/128/135 124/131/139 125/132/139 125/132/139
10
36169 R
39726 R
43104 R
45818 R
48287 R
49604 S
49604 S
101/111/121 108/116/126 114/122/130 119/126/134 123/130/137 125/132/139 125/132/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
101 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 6500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
39193 R
44420 R
47111 R
49604 S
49604 S
49604 S
49604 S
107/116/125 117/124/132 121/128/136 125/132/139 125/132/139 125/132/139 125/132/139
-30
38812 R
44136 R
46736 R
49604 S
49604 S
49604 S
49604 S
106/115/124 116/124/132 120/128/135 125/132/139 125/132/139 125/132/139 125/132/139
-26
38536 R
43563 R
46390 R
49266 R
49604 S
49604 S
49604 S
105/115/124 115/123/131 120/127/135 124/131/138 125/132/139 125/132/139 125/132/139
-22
38305 R
42952 R
46081 R
48903 R
49604 S
49604 S
49604 S
105/114/124 114/122/130 119/127/134 124/131/138 125/132/139 125/132/139 125/132/139
-18
38114 R
42383 R
45792 R
48554 R
49604 S
49604 S
49604 S
104/114/123 113/121/129 119/126/134 123/130/138 125/132/139 125/132/139 125/132/139
-14
37956 R
41865 R
45509 R
48191 R
49604 S
49604 S
49604 S
104/114/123 112/120/129 118/126/134 123/130/137 125/132/139 125/132/139 125/132/139
-10
37820 R
41521 R
45229 R
47832 R
49604 S
49604 S
49604 S
104/113/123 111/120/128 118/125/133 122/129/137 125/132/139 125/132/139 125/132/139
-6
37703 R
41207 R
44954 R
47484 R
49604 S
49604 S
49604 S
104/113/123 111/119/128 118/125/133 122/129/136 125/132/139 125/132/139 125/132/139
-2
37614 R
40958 R
44721 R
47195 R
49604 S
49604 S
49604 S
103/113/123 110/119/127 117/125/133 121/128/136 125/132/139 125/132/139 125/132/139
2
37521 R
40680 R
44446 R
46857 R
49379 R
49604 S
49604 S
103/113/123 110/118/127 117/124/132 121/128/135 124/131/139 125/132/139 125/132/139
6
36387 R
39885 R
43373 R
45980 R
48486 R
49604 S
49604 S
101/111/121 108/117/126 115/123/131 119/126/134 123/130/137 125/132/139 125/132/139
10
35031 R
38923 R
41838 R
45007 R
47279 R
49601 R
49604 S
100/109/119 106/115/125 112/120/129 118/125/133 121/128/136 125/132/139 125/132/139
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
102 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 7000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
38543 R
43582 R
46400 R
49277 R
49604 S
49604 S
49604 S
106/115/124 116/123/131 120/127/135 125/131/139 125/132/139 125/132/139 125/132/139
-30
38306 R
42957 R
46084 R
48906 R
49604 S
49604 S
49604 S
105/114/124 114/122/130 120/127/134 124/131/138 125/132/139 125/132/139 125/132/139
-26
38117 R
42392 R
45797 R
48560 R
49604 S
49604 S
49604 S
105/114/123 113/121/129 119/126/134 124/130/138 125/132/139 125/132/139 125/132/139
-22
37952 R
41855 R
45502 R
48181 R
49604 S
49604 S
49604 S
104/114/123 112/120/129 119/126/134 123/130/137 125/132/139 125/132/139 125/132/139
-18
37813 R
41503 R
45213 R
47812 R
49604 S
49604 S
49604 S
104/114/123 112/120/128 118/125/133 122/129/137 125/132/139 125/132/139 125/132/139
-14
37692 R
41179 R
44928 R
47452 R
49604 S
49604 S
49604 S
104/113/123 111/119/128 118/125/133 122/129/136 125/132/139 125/132/139 125/132/139
-10
37589 R
40883 R
44649 R
47106 R
49604 S
49604 S
49604 S
104/113/123 111/119/127 117/125/133 121/128/136 125/132/139 125/132/139 125/132/139
-6
37466 R
40602 R
44371 R
46765 R
49286 R
49604 S
49604 S
103/113/122 110/118/127 117/124/132 121/128/135 125/131/139 125/132/139 125/132/139
-2
37093 R
40367 R
44155 R
46495 R
49024 R
49604 S
49604 S
103/112/122 110/118/127 117/124/132 120/127/135 124/131/138 125/132/139 125/132/139
2
36601 R
40036 R
43632 R
46135 R
48656 R
49604 S
49604 S
102/112/121 109/117/126 116/123/131 120/127/134 124/130/138 125/132/139 125/132/139
6
35407 R
39126 R
42134 R
45211 R
47535 R
49604 S
49604 S
100/109/119 107/116/125 113/121/129 118/125/133 122/129/136 125/132/139 125/132/139
10
33861 R
38173 R
40992 R
44261 R
46328 R
48692 R
49604 S
100/108/119 105/114/124 111/119/128 117/124/132 120/127/135 124/130/138 125/132/139
NOTE: The values above do not take into account obstacles.
Page
JANUARY 17, 2003
1-04-15
Code
103 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 7500 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
38106 R
42355 R
45777 R
48537 R
49604 S
49604 S
49604 S
105/114/123 114/121/129 120/126/134 124/130/138 126/132/139 126/132/139 126/132/139
-30
37938 R
41822 R
45475 R
48147 R
49604 S
49604 S
49604 S
105/114/123 113/120/129 119/126/134 123/130/137 126/132/139 126/132/139 126/132/139
-26
37797 R
41462 R
45179 R
47768 R
49604 S
49604 S
49604 S
105/114/123 112/120/128 119/126/133 123/129/137 126/132/139 126/132/139 126/132/139
-22
37678 R
41137 R
44890 R
47404 R
49604 S
49604 S
49604 S
104/114/123 111/119/128 118/125/133 122/129/136 126/132/139 126/132/139 126/132/139
-18
37575 R
40841 R
44608 R
47055 R
49582 R
49604 S
49604 S
104/113/123 111/119/127 118/125/132 122/128/136 126/132/139 126/132/139 126/132/139
-14
37385 R
40552 R
44325 R
46707 R
49231 R
49604 S
49604 S
104/113/122 110/118/127 117/124/132 121/128/135 125/131/138 126/132/139 126/132/139
-10
36911 R
40247 R
44002 R
46357 R
48891 R
49604 S
49604 S
103/112/122 110/118/126 117/124/132 121/127/135 124/131/138 126/132/139 126/132/139
-6
36512 R
39974 R
43525 R
46071 R
48586 R
49604 S
49604 S
102/112/121 109/117/126 116/123/131 120/127/134 124/130/138 126/132/139 126/132/139
-2
36192 R
39743 R
43133 R
45835 R
48308 R
49604 S
49604 S
101/111/121 109/117/126 115/122/130 120/127/134 124/130/137 126/132/139 126/132/139
2
35479 R
39186 R
42228 R
45271 R
47611 R
49604 S
49604 S
100/109/120 108/116/125 114/121/129 119/126/133 123/129/136 126/132/139 126/132/139
6
33920 R
38305 R
41141 R
44391 R
46496 R
48852 R
49604 S
99/108/118 106/115/124 111/119/128 117/124/132 121/127/135 124/131/138 126/132/139
10
33615 R
37349 R
40079 R
43020 R
45440 R
47605 R
48615 W
99/108/118 104/113/122 109/117/126 115/122/130 119/126/134 123/129/136 124/131/138
NOTE: The values above do not take into account obstacles.
Page
1-04-15
Code
104 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° - DRY RUNWAY - ANTI-ICE ON Airport Pressure Altitude: 8000 ft Temp RUNWAY LENGTH (ft) o ( C) 4600 5300 6000 6700 7400
8100
8800
MAXIMUM TAKEOFF WEIGHT (lb) - LIMITATION CODE V1/VR/V2 (KIAS) -34
37803 R
41478 R
45192 R
47785 R
49604 S
49604 S
49604 S
105/114/123 113/120/128 119/126/133 123/129/137 126/132/139 126/132/139 126/132/139
-30
37678 R
41137 R
44890 R
47404 R
49604 S
49604 S
49604 S
105/114/123 112/119/128 119/125/133 123/129/136 126/132/139 126/132/139 126/132/139
-26
37567 R
40818 R
44585 R
47027 R
49553 R
49604 S
49604 S
105/114/123 111/119/127 118/125/132 122/128/136 126/132/139 126/132/139 126/132/139
-22
37345 R
40527 R
44302 R
46678 R
49202 R
49604 S
49604 S
104/113/122 111/118/127 118/124/132 122/128/135 125/132/138 126/132/139 126/132/139
-18
36878 R
40225 R
43964 R
46332 R
48866 R
49604 S
49604 S
103/112/122 110/118/126 117/124/132 121/127/135 125/131/138 126/132/139 126/132/139
-14
36438 R
39922 R
43435 R
46017 R
48528 R
49604 S
49604 S
102/111/121 110/117/126 116/123/131 120/127/134 124/131/138 126/132/139 126/132/139
-10
36028 R
39620 R
42928 R
45710 R
48155 R
49604 S
49604 S
102/111/120 109/117/126 115/122/130 120/126/134 124/130/137 126/132/139 126/132/139
-6
35715 R
39378 R
42533 R
45464 R
47851 R
49604 S
49604 S
101/110/120 108/116/125 115/122/130 120/126/134 123/130/137 126/132/139 126/132/139
-2
35436 R
39151 R
42173 R
45236 R
47567 R
49604 S
49604 S
100/110/119 108/116/125 114/121/129 119/126/133 123/129/136 126/132/139 126/132/139
2
33965 R
38394 R
41242 R
44481 R
46610 R
48961 R
49604 S
98/108/118 106/115/124 112/120/128 118/125/132 121/128/135 125/131/138 126/132/139
6
33656 R
37540 R
40278 R
43309 R
45631 R
47848 R
49324 W
98/107/118 105/113/123 110/118/127 116/123/131 120/126/134 123/130/137 126/132/139
10
33481 R
36649 R
39230 R
41850 R
44631 R
46560 R
47507 W
98/107/118 103/112/121 108/116/125 113/121/129 118/125/133 121/128/135 123/129/136
NOTE: The values above do not take into account obstacles.
Page
REVISION 3
1-04-15
Code
105 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
TAKEOFF SPEEDS Takeoff performance in the FAA approved EMB-135BJ AFM is presented in the following format: a) Balanced Field Length (fixed V1/VR ratio): - Flaps 9°, ALT T/O-1 thrust - AFM. - Flaps 9°, T/O thrust - AFM. - Flaps 9°, E T/O thrust - AFM.
TAKEOFF SPEEDS FOR BALANCED PERFORMANCE Takeoff speeds VR and V2 for Balanced Performance are read from the tables using the procedure below: a) Enter the appropriate table with Airport Pressure Altitude and move right as far as the appropriate Static Air Temperature Range. b) Enter the table with Airplane Brake Release Gross Weight and move right as far as the appropriate temperature column. Read VR and V2. If necessary, interpolate between two weights to obtain the associated speed.
Page
1-04-15
Code
106 02
REVISION 4
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
VR/V2 SPEEDS EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION ALT T/O-1 MODE - FLAPS 9° ANTI-ICE ON OR OFF PRESSURE ALTITUDE (ft) SL 1000 2000 3000 4000 5000 6000 7000 8000
è è è è è è è è è
STATIC AIR TEMPERATURE (°°C) -40 -40 -40 -40 -40 -40
to to to to to to
43 43 42 38 34 29
44 44 43 39 35 30 -40 -40
ê WEIGHT (lb)
V1
VR
30000 31000 32000 33000 34000 35000 36000 37000 38000 39000 40000 41000 42000 43000 44000 45000 46000 47000 48000 48900 49800
100 100 100 100 100 101 102 104 106 108 110 112 114 116 118 119 121 123 124 126 127
105 105 106 107 108 109 111 112 114 116 117 119 121 122 124 125 127 128 130 131 132
to to to to to to to to
47 46 44 40 36 31 26 22
48 47 45 41 37 32 27 23 -40
ê V2 V1 117 117 117 118 118 119 120 122 123 125 126 128 129 130 132 133 134 136 137 138 139
100 99 99 99 100 101 102 104 106 108 110 112 114 116 118 120 121 123 124 126 127
VR 104 105 105 107 108 109 111 112 114 116 117 119 121 122 124 125 127 128 130 131 132
to to to to to to to to to
50 48 46 44 41 37 32 28 23
42 38 33 29 24
ê V2 V1 117 117 117 117 118 119 120 122 123 125 126 128 129 130 132 133 134 136 137 138 139
96 96 96 98 99 101 103 105 107 109 111 113 115 117 119 120 122 123 125 126 127
VR 102 104 105 106 108 110 111 113 115 116 118 120 121 123 124 126 128 129 130 131 133
to to to to to
42 40 38 35 30
36 31
ê V2 V1 115 115 116 117 118 119 120 122 123 125 126 128 129 130 132 133 134 136 137 138 139
93 95 97 99 101 103 105 107 109 111 113 115 117 118 120 122 124 124 124 124 124
VR 102 103 105 106 108 110 112 114 116 117 119 120 122 124 125 127 128 129 129 129 129
to to
36 34
ê V2 V1 112 113 114 116 117 119 120 122 123 125 126 128 129 130 132 133 134 135 135 135 135
94 96 99 101 103 105 107 109 111 113 115 117 119 120 121 121 121 121 121 121 121
VR
V2
101 103 105 107 109 111 113 115 116 118 120 121 123 124 125 125 125 125 125 125 125
112 113 114 116 117 119 120 122 123 125 126 128 129 130 131 131 131 131 131 131 131
Page
JANUARY 17, 2003
1-04-15
Code
107 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
VR/V2 SPEEDS EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION T/O MODE - FLAPS 9° ANTI-ICE ON OR OFF PRESSURE ALTITUDE (ft) SL 1000 2000 3000 4000 5000 6000 7000 8000
STATIC AIR TEMPERATURE (°°C)
è -40 è -40 è è è è è è è
to to
38 35
39 36 -40 -40
ê WEIGHT (lb) 30000 31000 32000 33000 34000 35000 36000 37000 38000 39000 40000 41000 42000 43000 44000 45000 46000 47000 48000 48900 49800
to to to to
43 42 38 34
44 43 39 35 -40 -40 -40
ê
to to to to to to to
48 47 43 40 36 31 27
49 48 44 41 37 32 28 -40 -40
ê
to to to to to to to to to ê
50 48 46 44 42 39 34 30 25
40 35 31 26
to to to to ê
40 38 36 32
33
to ê
34
V1
VR
V2
V1
VR
V2
V1
VR
V2
V1
VR
V2
V1
VR
V2
V1
VR
V2
105 104 104 104 104 104 104 104 105 106 108 110 112 114 115 117 119 121 122 124 125
112 111 109 110 110 110 110 112 113 115 116 118 120 121 123 124 126 127 128 130 131
123 122 122 122 121 121 121 122 123 125 126 128 129 130 132 133 134 136 137 138 139
102 102 102 101 101 101 101 103 104 107 109 111 113 115 116 118 120 122 123 125 126
110 108 106 107 108 109 110 112 113 115 117 119 120 122 123 125 126 128 129 130 132
119 119 118 119 119 120 121 122 123 125 126 128 129 130 132 133 134 136 137 138 139
99 99 99 98 98 100 101 104 106 108 110 112 114 116 117 119 121 123 124 126 127
109 107 106 107 108 109 111 112 114 116 118 119 121 122 124 125 127 128 129 131 132
117 117 117 118 119 119 120 122 123 125 126 128 129 130 132 133 134 136 137 138 139
96 96 96 97 99 101 103 105 107 109 111 113 115 117 118 120 122 124 125 126 127
108 107 105 107 108 110 111 113 115 116 118 120 121 123 124 126 127 129 130 131 132
115 115 116 117 118 119 120 122 123 125 126 128 129 130 132 133 134 136 137 138 139
94 96 97 99 101 103 105 107 109 111 113 115 116 118 120 121 122 122 122 122 122
107 106 105 107 108 110 112 114 116 117 119 121 122 124 125 126 128 128 128 128 128
113 113 114 116 117 119 120 122 123 125 126 128 129 130 132 133 134 134 134 134 134
94 96 98 101 103 105 107 109 111 113 115 117 118 119 119 119 119 119 119 119 119
107 106 105 107 109 111 113 115 116 118 120 121 123 123 123 123 123 123 123 123 123
112 113 114 116 117 119 120 122 123 125 126 128 129 129 129 129 129 129 129 129 129
Page
1-04-15
Code
108 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
VR/V2 SPEEDS EMB-135BJ - AE3007A1E ENGINES - FAA CERTIFICATION E T/O MODE - FLAPS 9° ANTI-ICE ON OR OFF PRESSURE ALTITUDE (ft) SL 1000 2000 3000 4000 5000 6000 7000 8000
STATIC AIR TEMPERATURE (°°C)
è -40 è -40 è è è è è è è
to to
37 33
38 34 -40 -40
ê WEIGHT (lb) 30000 31000 32000 33000 34000 35000 36000 37000 38000 39000 40000 41000 42000 43000 44000 45000 46000 47000 48000 48900 49800
to to to to
42 39 34 30
43 40 35 31 -40 -40
ê
to to to to to to
47 44 40 36 32 27
48 45 41 37 33 28 -40 -40
ê
to to to to to to to to
50 48 46 43 39 35 31 26
44 40 36 32 27 -40
ê
to to to to to to ê
44 42 40 36 32 28
37 33 29
to to to ê
38 36 34
V1
VR
V2
V1
VR
V2
V1
VR
V2
V1
VR
V2
V1
VR
V2
V1
VR
V2
109 109 109 109 109 108 108 108 108 108 108 109 109 111 113 115 117 118 120 122 123
116 115 115 114 114 113 113 113 113 114 115 117 119 120 122 123 125 126 128 129 130
129 129 128 127 126 125 125 125 125 125 126 128 129 130 132 133 134 136 137 138 139
107 106 106 106 106 105 105 105 105 105 106 108 110 112 114 116 117 119 121 122 124
112 112 111 111 110 110 110 111 113 114 116 118 119 121 122 124 125 127 128 130 131
125 125 124 123 122 122 122 123 123 125 126 128 129 130 132 133 134 136 137 138 139
103 103 103 103 103 102 102 103 103 105 107 109 111 113 115 117 119 120 122 123 125
109 108 107 108 108 109 110 112 113 115 117 118 120 122 123 125 126 128 129 130 132
121 121 120 120 120 120 121 122 123 125 126 128 129 130 132 133 134 136 137 138 139
100 100 100 100 99 100 101 103 105 107 109 111 113 115 117 118 120 121 123 124 126
105 106 106 107 108 109 110 112 114 116 117 119 121 122 124 125 127 128 130 131 132
118 117 117 118 118 119 120 122 123 125 126 128 129 130 132 133 134 136 137 138 139
97 97 97 98 99 101 103 105 107 109 111 113 115 116 118 120 122 123 125 125 126
104 105 105 106 107 109 111 113 115 116 118 120 121 123 124 126 127 129 130 131 132
115 116 116 117 117 119 120 122 123 125 126 128 129 130 132 133 134 136 137 138 138
93 95 96 99 101 103 105 107 109 111 113 115 117 118 120 122 123 124 124 124 124
102 103 105 106 108 110 112 114 115 117 119 120 122 124 125 127 128 128 128 128 128
113 113 114 116 117 119 120 122 123 125 126 128 129 130 132 133 134 135 135 135 135
Page
JANUARY 17, 2003
1-04-15
Code
109 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
FLAPS RETRACTION SCHEDULE Takeoff with flaps 9°: Flaps 9° to UP ...............................................................V2 + 15 KIAS
FINAL SEGMENT SPEED WEIGHT (lb) 29000 30000 31000 32000 33000 34000 35000 36000 37000 38000 39000 40000 41000 42000 43000 44000 45000 46000 47000 48000 49000 50000
VFS (KIAS) 136 138 140 142 144 146 148 150 152 154 156 157 159 161 162 164 166 167 169 170 172 173
PITCH TRIM SETTING FOR TAKEOFF LESS CG THAN POSITION 25% PITCH TRIM 8 UNITS
Page
1-04-15
27%
30%
32%
35%
7
6
5
4
Code
110 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E FAA
CLIMB GRADIENT The climb gradient tables show the climb gradients for several weights, temperatures and altitudes. These tables are published in the following configurations: GRADIENTS FOR TAKEOFF THRUST AND FLAPS 9° The gradients were obtained for a speed equal to V2 + 10 KIAS and V2/VS ratio equal to 1.20. The thrust rating was E T/O with Anti-Ice OFF. Correction in the climb gradient for Anti-Ice ON is also provided below each table. GRADIENTS FOR TAKEOFF THRUST AND FLAPS UP The gradients were obtained for a speed equal to 200 KIAS. The thrust rating was E T/O with Anti-Ice OFF. Below each table are provided corrections in the climb gradients for Anti-Ice ON and corrections for climb speed equal to VFS. GRADIENTS FOR CLIMB THRUST AND FLAPS UP The gradients were obtained for the following climb schedule: − 240 KIAS up to 10000 ft, increasing linearly to 300 KIAS at 12000 ft, maintaining this speed up to 20000 ft. − The thrust rating was CLB with Anti-Ice OFF. Corrections in the climb gradient for Anti-Ice ON are provided after the tables.
Page
REVISION 7
1-04-15
Code
111 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
CLIMB GRADIENT - ALL ENGINES OPERATING TAKEOFF RATING - FLAPS 9° AE3007A1E ENGINES ANTI ICE: OFF LANDING GEAR UP E T/O MODE AIRSPEED: V2 + 10 KIAS WINGS LEVELED
ALTITUDE: 0 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
36.76 36.76 36.87 36.76 36.64 36.53 32.76
33.96 33.96 34.05 33.94 33.83 33.73 30.12
31.46 31.45 31.52 31.41 31.31 31.20 27.73
29.21 29.20 29.24 29.14 29.04 28.94 25.54
27.16 27.15 27.16 27.07 26.97 26.87 23.55
25.27 25.26 25.23 25.14 25.04 24.94 21.74
23.48 23.48 23.42 23.33 23.24 23.15 20.12
21.86 21.86 21.80 21.72 21.63 21.54 18.67
20.41 20.40 20.35 20.27 20.19 20.10 17.37
19.09 19.08 19.03 18.96 18.88 18.80 16.19
17.88 17.88 17.83 17.76 17.68 17.61 15.12
ALTITUDE: 2000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
36.71 36.68 36.76 36.66 36.55 35.04 31.38
33.88 33.85 33.91 33.81 33.71 32.28 28.78
31.34 31.32 31.35 31.26 31.16 29.81 26.39
29.06 29.04 29.05 28.96 28.87 27.58 24.25
26.97 26.95 26.92 26.84 26.74 25.51 22.32
25.02 25.00 24.96 24.87 24.79 23.61 20.58
23.23 23.21 23.17 23.09 23.01 21.90 19.02
21.63 21.61 21.57 21.49 21.42 20.37 17.63
20.19 20.17 20.13 20.06 19.99 18.99 16.38
18.88 18.86 18.83 18.76 18.69 17.74 15.25
17.69 17.67 17.64 17.57 17.51 16.60 14.22
ALTITUDE: 4000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
37.02 37.02 37.01 36.99 36.87 33.34 29.97
34.14 34.13 34.12 34.09 33.98 30.66 27.40
31.54 31.54 31.52 31.48 31.38 28.24 25.02
29.21 29.20 29.17 29.09 28.99 26.02 22.95
27.02 27.02 26.99 26.91 26.82 24.01 21.08
25.04 25.04 25.01 24.94 24.85 22.18 19.42
23.25 23.25 23.21 23.15 23.07 20.54 17.92
21.64 21.64 21.61 21.55 21.47 19.08 16.59
20.20 20.20 20.17 20.11 20.04 17.76 15.40
18.90 18.89 18.86 18.81 18.74 16.57 14.31
17.70 17.70 17.67 17.62 17.56 15.48 13.33
FOR ANTI-ICE ON, REDUCE THE CLIMB GRADIENT BY 4.38%.
Page
1-04-15
Code
112 02
REVISION 7
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
CLIMB GRADIENT - ALL ENGINES OPERATING TAKEOFF RATING - FLAPS 9° AE3007A1E ENGINES ANTI ICE: OFF LANDING GEAR UP E T/O MODE AIRSPEED: V2 + 10 KIAS WINGS LEVELED
ALTITUDE: 6000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
35.91 35.92 35.90 35.89 35.68 31.63 28.35
33.05 33.06 33.05 33.02 32.82 29.02 25.78
30.45 30.46 30.45 30.38 30.20 26.61 23.50
28.07 28.08 28.07 28.00 27.83 24.45 21.51
25.94 25.95 25.95 25.88 25.72 22.52 19.72
24.01 24.02 24.01 23.95 23.79 20.77 18.14
22.27 22.28 22.27 22.21 22.05 19.21 16.71
20.72 20.72 20.72 20.66 20.51 17.81 15.44
19.32 19.33 19.32 19.27 19.12 16.56 14.31
18.06 18.06 18.06 18.01 17.86 15.43 13.28
16.90 16.91 16.91 16.86 16.71 14.39 12.34
ALTITUDE: 8000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
33.98 34.00 33.97 33.92 33.63 29.89 26.51
31.18 31.20 31.18 31.11 30.83 27.32 24.03
28.56 28.58 28.56 28.49 28.24 24.94 21.85
26.29 26.31 26.29 26.23 25.98 22.87 19.95
24.25 24.26 24.25 24.19 23.96 21.01 18.26
22.40 22.42 22.40 22.35 22.14 19.34 16.75
20.75 20.77 20.75 20.70 20.50 17.85 15.41
19.28 19.29 19.28 19.23 19.04 16.52 14.21
17.96 17.97 17.96 17.91 17.73 15.33 13.13
16.76 16.77 16.76 16.71 16.55 14.25 12.16
15.66 15.67 15.66 15.62 15.46 13.26 11.27
ALTITUDE: 10000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
31.97 32.03 31.97 31.90 31.27 28.21 24.50
29.16 29.22 29.17 29.10 28.49 25.63 22.16
26.67 26.72 26.67 26.61 26.04 23.35 20.09
24.50 24.55 24.50 24.44 23.91 21.36 18.30
22.54 22.59 22.55 22.49 21.99 19.58 16.71
20.79 20.84 20.80 20.74 20.28 17.99 15.30
19.23 19.27 19.23 19.18 18.74 16.57 14.03
17.83 17.87 17.83 17.79 17.37 15.31 12.91
16.57 16.62 16.58 16.54 16.15 14.18 11.90
15.44 15.48 15.44 15.40 15.03 13.15 10.99
14.40 14.44 14.41 14.37 14.02 12.22 10.16
FOR ANTI-ICE ON, REDUCE THE CLIMB GRADIENT BY 4.38%.
Page
REVISION 7
1-04-15
Code
113 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
CLIMB GRADIENT - ALL ENGINES OPERATING TAKEOFF RATING - FLAPS 9° AE3007A1E ENGINES ANTI ICE: OFF LANDING GEAR UP E T/O MODE AIRSPEED: V2 + 10 KIAS WINGS LEVELED
ALTITUDE: 12000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
29.03 29.07 29.05 28.98 28.86 26.34 22.75
26.38 26.41 26.39 26.33 26.21 23.87 20.50
24.05 24.08 24.06 24.01 23.89 21.70 18.54
22.01 22.05 22.03 21.97 21.86 19.80 16.83
20.20 20.23 20.21 20.16 20.06 18.11 15.33
18.58 18.61 18.59 18.54 18.45 16.62 13.98
17.14 17.17 17.15 17.10 17.01 15.27 12.78
15.85 15.88 15.85 15.81 15.72 14.08 11.72
14.69 14.72 14.70 14.65 14.57 13.01 10.76
13.64 13.67 13.65 13.61 13.53 12.04 9.90
12.69 12.71 12.69 12.65 12.57 11.16 9.11
ALTITUDE: 13500 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
27.26 27.29 27.29 27.21 27.02 24.88 21.52
24.73 24.75 24.76 24.68 24.49 22.51 19.35
22.50 22.53 22.53 22.46 22.27 20.42 17.46
20.55 20.58 20.58 20.51 20.33 18.60 15.82
18.83 18.85 18.85 18.79 18.61 16.99 14.37
17.30 17.31 17.32 17.25 17.07 15.56 13.09
15.92 15.94 15.94 15.88 15.70 14.28 11.93
14.70 14.71 14.71 14.66 14.48 13.14 10.91
13.60 13.62 13.62 13.56 13.39 12.12 9.99
12.60 12.62 12.62 12.57 12.40 11.20 9.17
11.70 11.71 11.71 11.66 11.49 10.35 8.41
FOR ANTI-ICE ON, REDUCE THE CLIMB GRADIENT BY 4.38%.
Page
1-04-15
Code
114 02
REVISION 7
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
CLIMB GRADIENT - ALL ENGINES OPERATING TAKEOFF RATING - FLAPS UP AE3007A1E ENGINES ANTI ICE: OFF LANDING GEAR UP E T/O MODE AIRSPEED: 200 KIAS WINGS LEVELED
ALTITUDE: 0 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
31.72 31.65 31.54 31.38 31.21 31.06 27.31
29.40 29.33 29.23 29.08 28.92 28.78 25.28
27.35 27.29 27.20 27.05 26.90 26.77 23.49
25.53 25.48 25.39 25.25 25.11 24.99 21.90
23.90 23.85 23.77 23.64 23.50 23.39 20.47
22.43 22.39 22.30 22.18 22.06 21.95 19.18
21.10 21.06 20.98 20.86 20.74 20.64 18.01
19.88 19.84 19.77 19.66 19.54 19.45 16.95
18.77 18.73 18.66 18.55 18.44 18.35 15.96
17.74 17.70 17.64 17.54 17.43 17.34 15.06
16.79 16.75 16.69 16.59 16.49 16.41 14.22
ALTITUDE: 2000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
31.82 31.75 31.67 31.52 31.38 29.97 25.98
29.49 29.43 29.35 29.21 29.08 27.76 24.04
27.44 27.38 27.30 27.17 27.05 25.82 22.33
25.62 25.56 25.49 25.36 25.25 24.09 20.80
23.98 23.93 23.86 23.75 23.64 22.54 19.44
22.51 22.46 22.40 22.29 22.18 21.15 18.20
21.18 21.13 21.07 20.96 20.87 19.88 17.08
19.96 19.91 19.85 19.75 19.66 18.72 16.06
18.84 18.79 18.74 18.64 18.56 17.66 15.12
17.81 17.77 17.71 17.62 17.54 16.68 14.25
16.86 16.81 16.76 16.68 16.60 15.77 13.45
ALTITUDE: 4000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
31.81 31.78 31.68 31.53 31.37 28.25 24.61
29.48 29.45 29.36 29.22 29.07 26.16 22.76
27.43 27.40 27.32 27.19 27.04 24.31 21.13
25.61 25.58 25.50 25.38 25.24 22.67 19.68
23.97 23.95 23.88 23.76 23.63 21.20 18.38
22.50 22.48 22.41 22.30 22.18 19.88 17.20
21.17 21.15 21.08 20.97 20.86 18.68 16.13
19.95 19.93 19.87 19.77 19.66 17.58 15.15
18.83 18.81 18.75 18.66 18.55 16.57 14.25
17.80 17.78 17.73 17.63 17.54 15.64 13.42
16.85 16.83 16.78 16.69 16.59 14.77 12.65
FOR ANTI-ICE ON, REDUCE THE CLIMB GRADIENT BY 4.29%. CLIMBING IN VFS, INCREASE THE CLIMB GRADIENT BY 0.81%.
Page
REVISION 7
1-04-15
Code
115 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
CLIMB GRADIENT - ALL ENGINES OPERATING TAKEOFF RATING - FLAPS UP AE3007A1E ENGINES ANTI ICE: OFF LANDING GEAR UP E T/O MODE AIRSPEED: 200 KIAS WINGS LEVELED
ALTITUDE: 6000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
30.64 30.60 30.54 30.41 30.26 26.47 23.09
28.39 28.35 28.29 28.17 28.03 24.49 21.34
26.41 26.37 26.32 26.20 26.07 22.76 19.80
24.64 24.61 24.56 24.45 24.33 21.21 18.43
23.07 23.04 22.99 22.89 22.77 19.82 17.19
21.64 21.62 21.57 21.47 21.36 18.57 16.08
20.35 20.33 20.28 20.19 20.08 17.43 15.07
19.17 19.15 19.11 19.02 18.92 16.39 14.14
18.09 18.07 18.03 17.95 17.85 15.44 13.29
17.09 17.07 17.03 16.96 16.86 14.56 12.50
16.17 16.15 16.11 16.04 15.95 13.74 11.77
ALTITUDE: 8000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
28.62 28.61 28.54 28.42 28.29 24.47 21.43
26.50 26.50 26.43 26.32 26.20 22.63 19.79
24.64 24.63 24.57 24.47 24.35 21.01 18.35
22.98 22.98 22.92 22.82 22.71 19.57 17.06
21.50 21.49 21.44 21.34 21.24 18.27 15.91
20.16 20.15 20.10 20.01 19.92 17.10 14.86
18.94 18.94 18.89 18.80 18.71 16.04 13.91
17.83 17.83 17.78 17.70 17.61 15.06 13.04
16.81 16.81 16.76 16.69 16.60 14.17 12.24
15.87 15.87 15.82 15.75 15.67 13.34 11.50
15.00 14.99 14.95 14.88 14.81 12.58 10.81
ALTITUDE: 10000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
26.68 26.68 26.58 26.49 25.95 22.74 19.74
24.70 24.70 24.60 24.52 24.01 21.02 18.21
22.95 22.95 22.86 22.78 22.31 19.50 16.87
21.39 21.39 21.31 21.23 20.79 18.15 15.67
19.99 19.99 19.92 19.85 19.42 16.93 14.59
18.73 18.73 18.66 18.59 18.19 15.83 13.62
17.59 17.59 17.52 17.46 17.08 14.83 12.73
16.54 16.54 16.48 16.42 16.06 13.92 11.91
15.58 15.58 15.52 15.46 15.12 13.08 11.16
14.70 14.70 14.63 14.58 14.25 12.30 10.47
13.87 13.87 13.82 13.76 13.45 11.58 9.82
FOR ANTI-ICE ON, REDUCE THE CLIMB GRADIENT BY 4.29%. CLIMBING IN VFS, INCREASE THE CLIMB GRADIENT BY 0.81%.
Page
1-04-15
Code
116 02
REVISION 7
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
CLIMB GRADIENT - ALL ENGINES OPERATING TAKEOFF RATING - FLAPS UP AE3007A1E ENGINES ANTI ICE: OFF LANDING GEAR UP E T/O MODE AIRSPEED: 200 KIAS WINGS LEVELED
ALTITUDE: 12000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
23.84 23.82 23.76 23.64 23.50 21.09 17.92
22.04 22.02 21.97 21.86 21.73 19.48 16.52
20.46 20.44 20.39 20.29 20.17 18.06 15.28
19.05 19.03 18.99 18.89 18.77 16.79 14.17
17.78 17.77 17.72 17.63 17.52 15.65 13.18
16.64 16.63 16.58 16.50 16.39 14.62 12.28
15.60 15.59 15.55 15.46 15.37 13.68 11.46
14.65 14.64 14.60 14.52 14.43 12.82 10.70
13.77 13.76 13.73 13.65 13.56 12.03 10.01
12.97 12.96 12.92 12.85 12.77 11.30 9.37
12.22 12.21 12.18 12.11 12.03 10.62 8.77
ALTITUDE: 13500 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
22.22 22.19 22.15 22.03 21.82 19.86 16.75
20.53 20.51 20.47 20.36 20.16 18.33 15.43
19.04 19.02 18.98 18.88 18.70 16.98 14.26
17.71 17.69 17.66 17.56 17.39 15.77 13.22
16.52 16.50 16.47 16.38 16.22 14.69 12.27
15.45 15.43 15.40 15.31 15.16 13.71 11.42
14.47 14.45 14.42 14.34 14.19 12.82 10.64
13.57 13.56 13.53 13.45 13.31 12.00 9.93
12.75 12.73 12.70 12.63 12.50 11.25 9.27
11.99 11.97 11.94 11.87 11.75 10.55 8.66
11.28 11.26 11.24 11.17 11.05 9.90 8.09
FOR ANTI-ICE ON, REDUCE THE CLIMB GRADIENT BY 4.29%. CLIMBING IN VFS, INCREASE THE CLIMB GRADIENT BY 0.81%.
Page
REVISION 7
1-04-15
Code
117 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
CLIMB GRADIENT - ALL ENGINES OPERATING CLIMB RATING - FLAPS UP AE3007A1E ENGINES ANTI ICE: OFF LANDING GEAR UP CLB MODE WINGS LEVELED SPEED SCHEDULE: 240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 300 KIAS AT 12000 FT. MAINTAINING THIS SPEED UP TO 20000 FT.
ALTITUDE: 0 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
20.61 20.56 20.46 20.31 19.96 16.62 13.59
19.10 19.05 18.96 18.81 18.48 15.37 12.55
17.76 17.72 17.63 17.50 17.19 14.27 11.62
16.57 16.53 16.45 16.33 16.03 13.29 10.80
15.51 15.47 15.39 15.28 15.00 12.41 10.05
14.55 14.51 14.44 14.33 14.07 11.61 9.38
13.68 13.65 13.58 13.47 13.22 10.89 8.77
12.89 12.85 12.79 12.69 12.45 10.23 8.21
12.16 12.13 12.06 11.97 11.74 9.62 7.69
11.49 11.46 11.40 11.30 11.09 9.06 7.22
10.86 10.84 10.78 10.69 10.48 8.54 6.77
ALTITUDE: 2000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
19.24 19.19 19.11 18.97 18.52 15.45 12.57
17.81 17.77 17.69 17.56 17.15 14.28 11.59
16.56 16.52 16.44 16.32 15.93 13.25 10.72
15.44 15.40 15.34 15.22 14.86 12.33 9.95
14.44 14.40 14.34 14.23 13.89 11.50 9.25
13.54 13.50 13.44 13.34 13.02 10.75 8.63
12.72 12.69 12.63 12.53 12.22 10.07 8.05
11.97 11.94 11.89 11.79 11.50 9.45 7.53
11.29 11.25 11.20 11.12 10.83 8.88 7.04
10.65 10.62 10.57 10.49 10.22 8.35 6.59
10.07 10.04 9.99 9.91 9.65 7.86 6.18
ALTITUDE: 4000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
17.88 17.84 17.76 17.64 17.20 14.26 11.51
16.55 16.51 16.44 16.32 15.92 13.17 10.60
15.37 15.34 15.27 15.16 14.78 12.21 9.80
14.33 14.29 14.23 14.13 13.77 11.35 9.08
13.39 13.36 13.30 13.20 12.86 10.58 8.43
12.54 12.51 12.46 12.37 12.04 9.88 7.85
11.78 11.75 11.69 11.61 11.30 9.24 7.31
11.07 11.05 10.99 10.91 10.62 8.66 6.82
10.43 10.40 10.35 10.27 10.00 8.12 6.37
9.83 9.81 9.76 9.68 9.42 7.63 5.95
9.28 9.26 9.21 9.14 8.88 7.17 5.56
FOR ANTI-ICE ON, REDUCE THE CLIMB GRADIENT BY 3.33%.
Page
1-04-15
Code
118 02
REVISION 7
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
CLIMB GRADIENT - ALL ENGINES OPERATING CLIMB RATING - FLAPS UP AE3007A1E ENGINES ANTI ICE: OFF LANDING GEAR UP CLB MODE WINGS LEVELED SPEED SCHEDULE: 240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 300 KIAS AT 12000 FT. MAINTAINING THIS SPEED UP TO 20000 FT.
ALTITUDE: 6000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
16.60 16.56 16.49 16.37 15.94 13.08 10.47
15.35 15.31 15.25 15.14 14.74 12.07 9.63
14.25 14.21 14.16 14.05 13.68 11.18 8.89
13.27 13.24 13.18 13.08 12.73 10.38 8.23
12.39 12.36 12.31 12.22 11.88 9.66 7.63
11.60 11.57 11.52 11.43 11.12 9.01 7.09
10.88 10.85 10.80 10.72 10.42 8.42 6.59
10.22 10.19 10.15 10.07 9.78 7.88 6.14
9.61 9.59 9.54 9.47 9.20 7.38 5.72
9.05 9.03 8.99 8.91 8.65 6.92 5.33
8.53 8.51 8.47 8.40 8.15 6.49 4.96
ALTITUDE: 8000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
15.39 15.37 15.32 15.20 14.81 11.98 9.50
14.23 14.21 14.16 14.05 13.68 11.04 8.72
13.20 13.18 13.13 13.03 12.69 10.21 8.04
12.28 12.27 12.22 12.12 11.80 9.47 7.43
11.46 11.44 11.40 11.31 11.00 8.80 6.87
10.71 10.70 10.66 10.57 10.28 8.20 6.37
10.04 10.02 9.98 9.90 9.63 7.65 5.91
9.42 9.41 9.37 9.29 9.03 7.14 5.49
8.85 8.84 8.80 8.73 8.48 6.68 5.10
8.32 8.31 8.28 8.21 7.97 6.25 4.73
7.83 7.82 7.79 7.72 7.49 5.84 4.40
ALTITUDE: 10000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
14.23 14.20 14.13 14.05 13.73 10.88 8.52
13.14 13.11 13.05 12.98 12.68 10.01 7.81
12.18 12.15 12.10 12.02 11.75 9.25 7.18
11.32 11.30 11.25 11.18 10.91 8.57 6.62
10.55 10.53 10.48 10.42 10.17 7.95 6.11
9.86 9.83 9.79 9.73 9.49 7.39 5.65
9.22 9.20 9.16 9.10 8.88 6.88 5.23
8.65 8.62 8.58 8.53 8.31 6.41 4.84
8.11 8.09 8.05 8.00 7.80 5.98 4.48
7.62 7.60 7.56 7.51 7.32 5.58 4.14
7.16 7.14 7.11 7.06 6.87 5.21 3.83
FOR ANTI-ICE ON, REDUCE THE CLIMB GRADIENT BY 3.33%.
Page
REVISION 7
1-04-15
Code
119 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
CLIMB GRADIENT - ALL ENGINES OPERATING CLIMB RATING - FLAPS UP AE3007A1E ENGINES ANTI ICE: OFF LANDING GEAR UP CLB MODE WINGS LEVELED SPEED SCHEDULE: 240 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 300 KIAS AT 12000 FT. MAINTAINING THIS SPEED UP TO 20000 FT.
ALTITUDE: 12000 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
7.42 7.36 7.29 7.15 6.73 4.34 2.24
6.84 6.78 6.72 6.59 6.20 3.97 2.00
6.32 6.27 6.21 6.09 5.73 3.63 1.79
5.87 5.82 5.76 5.65 5.30 3.34 1.60
5.46 5.41 5.36 5.25 4.92 3.06 1.43
5.08 5.04 4.99 4.89 4.58 2.82 1.27
4.74 4.70 4.65 4.56 4.26 2.59 1.12
4.43 4.39 4.35 4.26 3.98 2.38 0.98
4.14 4.11 4.06 3.98 3.71 2.19 0.85
3.88 3.84 3.80 3.72 3.46 2.01 0.73
3.63 3.60 3.56 3.48 3.23 1.84 0.61
ALTITUDE: 13500 FT ISA+ ºC
WEIGHT (lb) 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000
-30 -20 -10 0 10 20 30
6.69 6.63 6.56 6.44 5.93 3.72 1.68
6.16 6.11 6.04 5.93 5.45 3.38 1.49
5.69 5.64 5.58 5.47 5.03 3.09 1.31
5.27 5.22 5.16 5.06 4.65 2.82 1.15
4.89 4.85 4.79 4.70 4.30 2.58 1.00
4.55 4.51 4.45 4.36 3.99 2.36 0.86
4.24 4.20 4.15 4.06 3.71 2.16 0.73
3.95 3.91 3.86 3.78 3.45 1.97 0.61
3.69 3.65 3.60 3.53 3.20 1.79 0.50
3.44 3.40 3.36 3.29 2.98 1.63 0.39
3.21 3.18 3.13 3.06 2.77 1.48 0.29
FOR ANTI-ICE ON, REDUCE THE CLIMB GRADIENT BY 3.33%.
Page
1-04-15
Code
120 02
REVISION 7
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E FAA
SUPPLEMENTARY TAKEOFF INFORMATION TURN ANALYSIS The method below presents the criteria for transforming a takeoff flight path with turns in an equivalent straight one to allow the use of the AFM charts or runway analysis software to determine obstacle clearance. The method to be used herein converts an actual flight path with turns and wind effects to an equivalent straight flight path with still air. The equivalent straight flight path with still air will be determined in terms of increments on the existing obstacles' height that should be taken into account to ensure obstacle clearance. With the equivalent straight flight path, the performance calculation must be done, as usual, as presented in the AFM. OPERATIONAL LIMITATIONS Maximum bank angle:
All Engines Operative: 25° at V2 + 10 One Engine Inoperative: 15° at V2 One Engine Inoperative: 20° at V2 + 5 (*) One Engine Inoperative: 25° at V2 + 10 (*)
(*) According FAR 121.189 (f), the maximum bank angle with one engine inoperative is 15°. According JAR OPS 1.495 (c), if the airplane is banked by more than 15° the net path must clear all obstacles after the banked turn by 50 ft instead of 35 ft. EQUIVALENT STRAIGHT FLIGHT PATH DETERMINATION The equivalent straight flight path (zero wind) to be used in the performance calculation should be determined as follows: 1. OBSTACLE INCREMENT IN A STEADY TURN During a steady turn the climb gradient deteriorates. To compensate, an increment of the actual obstacle height must be obtained as a function of the gradient loss due to a steady turn and the turning distance flown to the obstacle by the following relation: ∆H = DT x GL
Page
JANUARY 17, 2003
1-04-20
Code
1 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
Where: ∆H = height increment. DT = distance flown along the turning flight. GL = gradient loss (obtained from the gradient loss due to a steady turn chart). The equivalent obstacle height to be used in a obstacle clearance calculation is: HE = HA + ∆H1 + ∆H2 + ......+ ∆Hn Where: HE = equivalent obstacle height. HA = actual obstacle height. ∆H1, 2, n = height increments for each distance portion flown in turn to the obstacle. 2) WIND EFFECT ON THE FLIGHT PATH a) STRAIGHT FLIGHT PORTIONS Considering the drift compensation, the straight portions of the flight path may be corrected to still air equivalent distance as follows:
SAD =
GD × TAS GS
Where: SAD = still air equivalent distance. GD = actual ground distance. TAS = airplane true airspeed (obtained from the radius of turns and speed conversion chart). GS = airplane ground speed. For straight flight: GS = TAS + (VW x cosα). Where: VW = wind speed. α = angle between flight direction and wind direction. Remarks: VW x cosα is negative for a head wind component. VW x cosα is positive for a tailwind component. b) TURNING FLIGHT PORTIONS Two effects must be taken into account: b1) Trajectory Displacement: The trajectory is displaced in the wind component direction proportionally to the time. The displacement may be calculated by: Page
1-04-20
Code
2 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E FAA
∆D = ∆t x VW ∆D = trajectory displacement in the wind component direction. ∆t = elapsed time in turning flight (obtained from the Horizontal Distance and Time to Complete chart). VW = wind speed.
b2) Distance Flown Compensation: The wind takes the same effect as mentioned in item 2a.
SAD =
GD × TAS GS
Page
JANUARY 17, 2003
1-04-20
Code
3 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
For turning flight:
GS =
Dm ∆t
Where: Dm = distance flown along the actual trajectory. ∆t = elapsed time in turning flight. PERFORMANCE CHARTS PRESENTATION GRADIENT LOSS DUE TO A STEADY TURN This chart shows the gradient loss due to a steady turn as a function of the bank angle. For bank angle greater than 15° use the following corrections: Bank 20° 25°
Speed V2 + 5 V2 + 10
Gradient Correction 15° gradient loss multiplied by 2 15° gradient loss multiplied by 3
NOTE: For bank angle greater than 15°, add an extra 15 ft to the corrected obstacle height, due to net path margin increased from 35 ft to 50 ft. RADIUS OF TURN AND SPEED CONVERSION This chart shows the radius of turn and the true airspeed to be used on the turning flight path calculation as a function of the indicated airspeed (V2), airport pressure altitude, outside air temperature and the bank angle. HORIZONTAL DISTANCE AND TIME TO COMPLETE This chart shows the horizontal distance and the elapsed time during a turning flight as a function of the radius of turn, heading change and the bank angle. NOTE: If necessary, the heading change may be divided in segments and the elapsed time of each segment should be added.
Page
1-04-20
Code
4 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
GRADIENT LOSS DUE TO A STEADY TURN ONE ENGINE INOPERATIVE FLAPS 9° 2.4
2.2
Φ 0 15 20 25 30
2.0
∆V (KIAS)
0 0 5 10 15
1.8
GRADIENT LOSS - %
1.6
1.4
1.2
1.0
0.8
0.6
0.4
135BJAOMCTA003 - 07APR2002
0.2
0.0 0
2
4
6
8
10
12
14
16
18
20
22
24
26
28
Page
JANUARY 17, 2003
30
BANK ANGLE - deg
1-04-20
Code
5 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-04-20
Code
6 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E FAA
Page Code
JANUARY 17, 2003
1-04-20
7 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-04-20
Code
8 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E FAA
Page Code
JANUARY 17, 2003
1-04-20
9 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-04-20
Code
10 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E FAA
AIRCRAFT CLASSIFICATION NUMBER - ACN The Pavement Classification Number (PCN) reported shall indicate that an airplane with ACN equal to or less than the reported PCN can operate on that pavement. PCN - PAVEMENT CLASSIFICATION NUMBER Example: PCN 50 / F / A / X / T
1 2 3 4 1 - Type of pavement: R = Rigid (concrete) F = Flexible (asphalt) 2 - Pavement sub-grade strength category: A = High, B = Medium, C = Low, D = Ultra-low. 3 - Maximum tire pressure authorized for the pavement: W = High, no limit; X = Medium (up to 217 psi) Y = Low (up to 145 psi); Z = Very low (up to 73 psi) 4 - Pavement evaluation method: T = Technical evaluation; U = By experience of airplane actually using the pavement. OVERLOAD OPERATIONS Individual airport authorities are free to decide on their own criteria for permitting overload operations as long as pavements remain safe for use by airplane. However, a 10% difference in ACN over PCN for flexible pavement and 5% for rigid pavements is generally accepted, provided that overload operations do not exceed 5% of the annual departures and are spread throughout the year.
Page
JANUARY 17, 2003
1-04-20
Code
11 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
EMB-135BJ - ACN FLEXIBLE PAVEMENT 16
D (CBR = 3%)
14
AIRCRAFT CLASSIFICATION NUMBER - ACN...
C (CBR = 6%)
B (CBR = 10%)
12 A (CBR = 15%)
10
8
135BJAOMFAA001 - 27AUG2002
6
4 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 50000 52000 54000
WEIGHT - lb
Page
1-04-20
Code
12 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E FAA
EMB-135BJ - ACN RIGID PAVEMENT 16 D (K = 20 MN/m3) C (K = 40 MN/m 3)
B (K = 80 MN/m3)
14
AIRCRAFT CLASSIFICATION NUMBER - ACN...
A (K = 150 MN/m3)
12
10
8
135BJAOMFAA002 - 29JUL2002
6
4 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 50000 52000 54000
WEIGHT - lb
Page
JANUARY 17, 2003
1-04-20
Code
13 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-04-20
Code
14 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E FAA
TAKEOFF PERFORMANCE Refer to the Airplane Flight Manual for a complete set of charts for determination of the limiting takeoff weights. EMBRAER RUNWAY ANALYSIS SOFTWARE Although the AFM presents all the required performance data for takeoff, the amount of options and charts presented, makes their use very difficult. In order to help operators, EMBRAER developed a runway analysis software for determination of the limiting weights. THE TAKEOFF OUTPUT DATA The program outputs the N1, weight, V1/VR/V2, the level-off altitude and height, and the code assigned to the limitation detected during the calculation process. These data are valid for the wind and temperature associated. The data are calculated for up to seven reference winds for a range of temperatures. The level-off output depends upon the Minimum Level-off Height entered in the data input. If obstacle clearance is required, a value higher than the one entered will be automatically be provided. NOTE: Level-off height must be corrected for temperatures below standard. Limitation codes assigned are a number (1, 2 etc.) for Obstacle limited weight, R for Runway limited weight, W for WAT limited weight (same as Climb or Second Segment), S for Structural limited weight, V for V1min, L for Level Off limited weight and B for a Brake Energy limited weight. If the operation for a specific condition is considered unfeasible or outside the performance tables, the relevant data will be provided with asterisks .
Page
JANUARY 17, 2003
1-04-20
Code
15 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
Wind (in knots) EMB-135 BJ RUNWAY ANALYSIS, ALLISON 3007A1P ENGINES, FAA CERTIFICATION ------------------------------------------------------------------------------------------------------Airport: AIRPORT NAME Runway: 01 Elevation: 101 RUNWAY LENGTH: 6500 ft Slope: 1 % --------------------------------------------------------------------------------------------------------Anti Ice: OFF Normal V2 Thrust schedule : T/O 1 NO REVERSE Alignment allowance: 0ft --------------------------------------------------------------------------------------------------------LIMIT WEIGHTS (lb), V1, VR, V2 (Kt) as function of Temperature and Wind: ----------------------------------------------------------------------------------------------------------Temp(C)/N1(%) -10 Kt 0 Kt 10 Kt 20 Kt --------------------------------------------------------------------------------------------------------4 / 84.9 41137/ 123/ 123/ 134 R 43503/ 129/ 129/ 139 R 43600/ 129/ 129/ 139 S 43600/ 129/ 129/ 139 S 6 / 85.2 41086/ 123/ 123/ 134 R 43450/ 128/ 128/ 139 R 43600/ 129/ 129/ 139 S 43600/ 129/ 129/ 139 S 8 / 85.5 41035/ 123/ 123/ 134 R 43397/ 128/ 128/ 138 R 43600/ 129/ 129/ 139 S 43600/ 129/ 129/ 139 S 10 / 85.9 40983/ 122/ 123/ 134 R 43346/ 128/ 128/ 138 R 43600/ 129/ 129/ 139 S 43600/ 129/ 129/ 139 S 12 / 86.1 40928/ 122/ 122/ 134 R 43292/ 128/ 128/ 138 R 43600/ 129/ 129/ 139 S 43600/ 129/ 129/ 139 S 14 / 86.4 40872/ 122/ 122/ 133 R 43238/ 128/ 128/ 138 R 43600/ 129/ 129/ 139 S 43600/ 129/ 129/ 139 S 16 / 86.7 40817/ 122/ 122/ 133 R 43186/ 127/ 127/ 138 R 43300/ 129/ 129/ 139 R 43600/ 129/ 129/ 139 S 18 / 87.1 40764/ 121/ 122/ 133 R 43135/ 127/ 127/ 138 R 42600/ 129/ 129/ 139 R 43600/ 129/ 129/ 139 S 20 / 87.4 40710/ 121/ 121/ 133 R 43084/ 127/ 127/ 137 R 42479/ 129/ 129/ 139 R 43600/ 129/ 129/ 139 S 22 / 87.7 40656/ 121/ 121/ 133 R 43033/ 127/ 127/ 137 R 42425/ 128/ 128/ 139 R 43600/ 129/ 129/ 139 S 24 / 87.9 40602/ 121/ 121/ 132 R 42981/ 127/ 127/ 137 R 42372/ 128/ 128/ 138 R 43600/ 129/ 129/ 139 S 26 / 88.2 40549/ 120/ 121/ 132 R 42923/ 126/ 126/ 137 R 42320/ 128/ 128/ 138 R 43600/ 129/ 129/ 139 S 28 / 88.6 40496/ 120/ 120/ 132 R 42865/ 126/ 126/ 137 R 42268/ 128/ 128/ 138 R 43600/ 129/ 129/ 139 S 30 / 88.9 40444/ 120/ 120/ 132 R 42809/ 126/ 126/ 137 R 42217/ 128/ 128/ 138 R 43600/ 129/ 129/ 139 S 32 / 89.2 40393/ 120/ 120/ 132 R 42753/ 126/ 126/ 136 R 42167/ 127/ 127/ 138 R 42560/ 129/ 129/ 139 R 34 / 89.4 40343/ 119/ 120/ 132 R 42699/ 126/ 126/ 136 R 41119/ 127/ 127/ 138 R 42509/ 129/ 129/ 139 R 36 / 89.7 40293/ 119/ 120/ 131 R 42645/ 125/ 125/ 136 R 41071/ 127/ 127/ 137 R 42458/ 129/ 129/ 139 R 38 / 90 40244/ 119/ 119/ 131 R 42593/ 125/ 125/ 136 R 41024/ 127/ 127/ 137 R 42409/ 128/ 128/ 138 R 40 / 90.3 40188/ 119/ 119/ 131 R 42533/ 125/ 125/ 136 R 41966/ 127/ 127/ 137 R 42352/ 128/ 128/ 138 R 42 / 90.5 40107/ 118/ 119/ 131 R 42445/ 125/ 125/ 135 R 40874/ 126/ 126/ 137 R 42270/ 128/ 128/ 138 R --------------------------------------------------------------------------------------------------------Limitation codes: 1,2,.. - Obstacle No.; L = Level off; R - Runway; S - Structural; B - Brake Energy; W - WAT
Temperature (in degrees Celsius) and N1 (in percentage)
Weight/V1/VR/V2 and limitation code (weight in pounds, and speeds in knots) EXAMPLE
Page
1-04-20
Code
16 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E FAA
APPROACH APPROACH CLIMB SPEED - FLAPS 9° WEIGHT (lb) 29000 30000 31000 32000 33000 34000 35000 36000 37000 38000 39000 40000 41000 42000 43000 44000 45000 46000 47000 48000 49000 50000
APPROACH CLIMB SPEED (KIAS) 127 129 132 134 136 137 139 141 143 145 146 148 150 152 153 155 157 158 160 161 163 164
Page
JANUARY 17, 2003
1-04-25
Code
1 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
LANDING CLIMB AND REFERENCE SPEEDS WEIGHT (lb) 29000 30000 31000 32000 33000 34000 35000 36000 37000 38000 39000 40000 41000 42000 43000 44000 45000 46000 47000 48000 49000 50000
Page
1-04-25
VREF - KIAS FLAPS 45° FLAPS 22° 110 110 110 111 110 113 112 114 113 116 115 118 117 119 118 121 120 122 121 124 123 125 124 127 126 128 127 130 129 131 130 133 132 134 133 135 135 137 136 138 137 139 139 141
Code
2 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E FAA
FLAP MANEUVERING SPEED GEAR / FLAP
SPEED (KIAS)
UP / 0°
180
UP / 9°
160
(DN/ 22° / 45°)
140
For icing conditions, the speeds above are maintained except for o UP/0 configuration, which must be 200 KIAS. These speeds allow an inadvertent 15 degrees overshoot beyond the normal 30 degrees bank and are valid for weights up to the Maximum Structural Landing Weight. If an overweight land is anavoidable, the speeds above are maintained except for DN/22° configurations, wich must be 150 KIAS. These speeds are also valid for icing conditions. If fuel consumption is a consideration, consult the Inflight Performance Software for maximum endurance speeds.
FINAL APPROACH SPEED VAPP = VREF + wind correction. Wind correction = ½ steady headwind component + gust increment above steady wind. For Flaps 45° landing, the minimum wind correction is 5 KIAS and the maximum is 15 KIAS. For Flaps 22° landing, the minimum wind correction is 0 KIAS and the maximum is 20 KIAS. For Emergency and Abnormal procedures using Flaps 0° and 9°, the minimum wind correction is 0 KIAS and the maximum is 20 KIAS. When there is wind and abnormal operation speed additives, use the sum of both corrections.
Page
REVISION 5
1-04-25
Code
3 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
APPROACH CLIMB WEIGHT TABLES The one engine inoperative Approach Climb Weight tables show the weights as function of airport pressure altitude (ft) and temperature (°C) for different Approach Climb Gradients. The associated conditions are: Flaps ........................................................................9° Gear ........................................................................UP Anti-Ice ....................................................................ON or OFF Temperature Anti-Ice OFF........................................................UP to ISA + 30°C Anti-Ice ON..........................................................UP to 10°C
Page
1-04-25
Code
4 02
REVISION 3
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
APPROACH CLIMB WEIGHTS - ONE ENGINE INOPERATIVE ANTI-ICE OFF - NO ICE ACCRETION Altitude (ft) 0
Gradient (%) 2.1
2.5
3.0
3.5
4.0
4.5
5.0
5.5
6.0
52910 52758 50517 48490 46623 44983 43374 41766 40418
500
52910 51750 49571 47576 45756 44125 42452 40973 39600
1000
52910 51826 49642 47646 45818 44190 42522 41033 39657
1500
52740 50855 48734 46760 45025 43339 41675 40267 38922
2000
52854 50974 48844 46869 45122 43444 41765 40360 39012
2500
51907 50065 47962 46013 44313 42573 41016 39588 38260
3000
51927 50083 47980 46029 44330 42591 41031 39603 38276
3500
50961 49188 47099 45240 43484 41732 40266 38864 37503
4000
50961 49188 47099 45240 43484 41732 40266 38864 37503
4500
50075 48309 46227 44448 42629 40997 39513 38119 36831
5000
50037 48272 46193 44413 42591 40965 39481 38085 36801
5500
49086 47334 45351 43510 41679 40146 38682 37282 36056
6000
48907 47157 45192 43337 41531 39991 38531 37147 35915
6500
47955 46198 44318 42389 40720 39176 37697 36404 35160
7000
47875 46127 44243 42308 40650 39108 37625 36341 35102
7500
46868 45233 43275 41397 39778 38247 36837 35543 34372
8000
46635 45026 43050 41204 39582 38047 36659 35359 34202
The data above is valid to temperature up to ISA + 30°C. NOTE: - Decrease weight by 613 lb per 1°C above ISA + 30°C conditions. - In case of ICE ACCRETION increase required approach climb gradient by 2.13%.
Page
JANUARY 17, 2003
1-04-25
Code
5 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
APPROACH CLIMB WEIGHTS - ONE ENGINE INOPERATIVE ANTI-ICE ON - NO ICE ACCRETION Altitude
Gradient (%)
(ft) 0
2.1
2.5
3.0
3.5
4.0
4.5
5.0
5.5
6.0
52910 52910 52910 52379 50340 48472 46780 45264 43811
500
52910 52910 52910 52302 50268 48404 46710 45201 43743
1000
52910 52910 52910 52226 50196 48337 46639 45137 43676
1500
52910 52910 52910 52123 50100 48246 46544 45053 43585
2000
52910 52910 52910 52020 50004 48155 46449 44967 43494
2500
52910 52910 52910 52020 50004 48155 46449 44967 43494
3000
52910 52910 52910 52020 50004 48155 46449 44967 43494
3500
52910 52910 52910 52020 50004 48155 46449 44967 43494
4000
52910 52910 52910 52020 50004 48155 46449 44967 43494
4500
52910 52910 52910 51163 49199 47393 45745 44256 42735
5000
52910 52910 52446 50317 48378 46598 45034 43500 41942
5500
52910 52910 51324 49265 47372 45653 44092 42491 41063
6000
52910 52427 50206 48191 46308 44702 43071 41506 40147
6500
52910 51307 49156 47173 45394 43737 42045 40623 39265
7000
52045 50193 48087 46125 44431 42700 41125 39694 38370
7500
50796 49036 46948 45105 43339 41606 40135 38737 37385
8000
49615 47857 45820 44018 42167 40602 39128 37715 36471
The data above is valid to temperatures up to 10°C. NOTE: Decrease weight by 2.13 % in ICE ACCRETION conditions.
Page
1-04-25
Code
6 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E FAA
LANDING UNFACTORED LANDING DISTANCES Unfactored landing distance is the actual distance to land the airplane on a zero slope, ISA temperature, dry runway from a point 50 ft above runway threshold at VREF, using only the brakes and spoilers as deceleration device (i.e., no engine reverse thrust is used). The required landing distance for dispatch is the unfactored landing distance increased by the 66.7% for dry runway or 91.7% for wet runway. For obtaining the DRY runway factored distance, multiply unfactored landing distance by 1.667. For obtaining the WET runway factored distance, multiply unfactored landing distance by 1.917. NOTE: The landing distance correction factors mentioned in some emergency or abnormal procedures must be applied to the flap o 45 unfactored landing distance.
Page
JANUARY 17, 2003
1-04-30
Code
1 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
UNFACTORED LANDING DISTANCE TABLE FAA - FLAPS 22° - NO ICE ENCOUNTER ISA CONDITIONS - SLOPE 0% ALTITUDE 0 ft
Weight (lb)
1000 ft WIND
-10 kt
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
3107 3112 3215 3361 3504 3647 3791 3936 4082
2642 2646 2739 2871 3001 3130 3261 3392 3524
2494 2498 2588 2716 2841 2967 3093 3220 3348
2350 2354 2441 2565 2686 2807 2929 3052 3176
3169 3175 3281 3431 3578 3726 3874 4024 4175
2698 2703 2799 2934 3068 3202 3336 3472 3608
2548 2553 2646 2777 2906 3036 3166 3297 3429
2403 2407 2497 2624 2749 2874 3000 3127 3255
27000 29000 31000 33000 35000 37000 39000 41000 43000
ALTITUDE 2000 ft
Weight (lb)
3000 ft WIND
-10 kt
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
3234 3239 3349 3503 3655 3807 3961 4115 4272
2756 2761 2860 3000 3138 3275 3414 3554 3696
2605 2610 2705 2841 2974 3107 3242 3377 3514
2457 2462 2555 2686 2814 2943 3073 3204 3337
3301 3306 3419 3578 3735 3892 4050 4210 4372
2817 2822 2924 3068 3210 3352 3495 3640 3786
2664 2668 2767 2907 3044 3181 3320 3460 3602
2514 2519 2614 2749 2882 3015 3149 3285 3422
27000 29000 31000 33000 35000 37000 39000 41000 43000
ALTITUDE 4000 ft
Weight (lb)
5000 ft WIND
-10 kt
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
3372 3378 3494 3658 3820 3982 4146 4311 4478
2882 2887 2992 3141 3287 3434 3582 3731 3883
2726 2731 2833 2977 3118 3260 3403 3548 3695
2575 2580 2678 2817 2954 3091 3230 3370 3512
3445 3451 3571 3740 3907 4075 4244 4415 4588
2948 2953 3062 3215 3366 3517 3671 3825 3982
2790 2795 2900 3049 3195 3341 3490 3639 3791
2637 2642 2743 2887 3028 3170 3313 3458 3605
27000 29000 31000 33000 35000 37000 39000 41000 43000
NOTE: Landing distance in feet.
Page
1-04-30
Code
2 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL UNFACTORED LANDING DISTANCE TABLE FAA - FLAPS 22° - AFTER ICE ENCOUNTER ISA CONDITIONS - SLOPE 0% ALTITUDE 0 ft
Weight (lb) 27000 29000 31000 33000 35000 37000 39000 41000 43000
1000 ft WIND
-10 kt
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
3225 3384 3543 3701 3854 4003 4156 4313 4473
2755 2899 3042 3186 3324 3459 3598 3740 3885
2605 2745 2883 3022 3156 3287 3421 3558 3699
2459 2594 2728 2863 2992 3119 3249 3381 3517
3290 3454 3617 3781 3938 4092 4250 4412 4578
2813 2962 3109 3258 3400 3539 3682 3829 3979
2662 2806 2948 3092 3229 3364 3503 3645 3790
2514 2653 2791 2930 3063 3194 3328 3465 3606
ALTITUDE 2000 ft
Weight (lb) 27000 29000 31000 33000 35000 37000 39000 41000 43000
3000 ft WIND
-10 kt
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
3357 3526 3694 3863 4024 4183 4347 4514 4686
2874 3027 3179 3332 3478 3622 3770 3922 4077
2721 2869 3016 3164 3305 3445 3588 3734 3885
2571 2714 2857 3000 3137 3272 3410 3552 3697
3426 3600 3774 3948 4115 4279 4448 4621 4799
2937 3095 3251 3409 3560 3709 3862 4018 4179
2782 2934 3086 3238 3384 3528 3676 3828 3983
2630 2777 2924 3072 3213 3353 3496 3643 3793
ALTITUDE 4000 ft
Weight (lb) 27000 29000 31000 33000 35000 37000 39000 41000 43000
5000 ft WIND
-10 kt
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
3500 3679 3858 4038 4210 4380 4554 4734 4918
3004 3166 3328 3490 3646 3800 3958 4120 4287
2846 3003 3160 3317 3468 3617 3769 3927 4088
2693 2844 2996 3148 3294 3438 3586 3738 3894
3578 3762 3946 4131 4310 4485 4666 4852 5043
3074 3241 3408 3575 3736 3896 4059 4228 4400
2914 3076 3237 3399 3555 3709 3867 4030 4197
2758 2915 3071 3228 3378 3527 3681 3838 4000
NOTE: Landing distance in feet.
Page
JANUARY 17, 2003
1-04-30
Code
3 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
UNFACTORED LANDING DISTANCE TABLE FAA - FLAPS 45° - NO ICE ENCOUNTER ISA CONDITIONS - SLOPE 0% ALTITUDE 0 ft
Weight (lb)
1000 ft WIND
-10 kt
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
2598 2598 2606 2715 2822 2929 3034 3142 3254
2202 2202 2208 2307 2404 2500 2596 2694 2795
2077 2077 2083 2179 2273 2366 2458 2553 2651
1956 1956 1962 2055 2146 2236 2325 2416 2511
2649 2649 2656 2769 2879 2988 3095 3208 3325
2247 2247 2254 2356 2455 2554 2651 2754 2860
2121 2121 2128 2226 2322 2418 2512 2611 2713
1999 1999 2005 2100 2193 2286 2377 2473 2572
27000 29000 31000 33000 35000 37000 39000 41000 43000
ALTITUDE 2000 ft
Weight (lb)
3000 ft WIND
-10 kt
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
2701 2701 2709 2824 2937 3048 3160 3278 3399
2294 2294 2301 2406 2508 2609 2710 2817 2926
2167 2167 2173 2275 2373 2471 2569 2672 2778
2043 2043 2049 2147 2242 2337 2432 2531 2634
2755 2755 2763 2881 2997 3111 3228 3350 3475
2343 2343 2350 2457 2562 2666 2772 2882 2995
2214 2214 2221 2324 2426 2526 2628 2735 2844
2088 2088 2095 2195 2293 2390 2489 2593 2698
27000 29000 31000 33000 35000 37000 39000 41000 43000
ALTITUDE 4000 ft
Weight (lb)
5000 ft WIND
-10 kt
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
2812 2812 2820 2941 3060 3178 3300 3427 3556
2395 2395 2403 2512 2620 2726 2837 2952 3068
2264 2264 2271 2377 2481 2584 2691 2802 2915
2137 2137 2144 2246 2347 2446 2550 2657 2766
2870 2870 2879 3003 3125 3246 3374 3506 3639
2448 2448 2455 2568 2678 2787 2904 3023 3143
2315 2315 2323 2432 2538 2644 2756 2871 2988
2186 2186 2193 2299 2402 2504 2613 2724 2837
27000 29000 31000 33000 35000 37000 39000 41000 43000
NOTE: Landing distance in feet.
Page
1-04-30
Code
4 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E FAA
LANDING DISTANCE CORRECTION FACTOR - FAA Emerg./Abnormal Procedure
Flaps - Speed
Factor
Advanced Stall Protection - Icing conditions
Flaps 22° - VREF 45 + 15 kt
1.55
Advanced Stall Protection - No icing conditions
Flaps 45° - VREF 45 + 5 kt
1.13
Aileron System Inoperative
Flaps 22° - VREF 45 + 10 kt
1.45
Both Hydraulic Systems Failure
Flaps 22° - VREF 45 + 10 kt
2.67
Brakes Degraded - Icing conditions
Flaps 22° - VREF 45 + 10 kt
1.71
Brakes Degraded - No icing conditions
Flaps 45° - VREF 45
1.20
Brakes Inoperative - Icing conditions
Flaps 22° - VREF 45 + 10 kt
2.18
Brakes Inoperative - No icing conditions
Flaps 45° - VREF 45
1.49
Flap System Failure (1)
Flaps 0° to 8° - VREF 45 + 30 kt
1.70
Flap System Failure (2)
Flaps 9° to 21° - VREF 45 + 10 kt
1.40
Flap System Failure (3)
Flaps 22° to 44° - VREF 45 + 5 kt
1.20
Hydraulic System 1 Failure - Icing Flaps 22° - VREF 45 + 10 kt conditions
2.38
Hydraulic System 1 Failure - No icing conditions
1.64
Flaps 45° - VREF 45
Hydraulic System 2 Failure - Icing Flaps 22° - VREF 45 + 10 kt conditions
2.27
Hydraulic System 2 Failure - No icing conditions
1.56
Flaps 45° - VREF 45
Inadvertent Spoiler Opening in Flaps 22° - VREF 45 + 10 kt Flight (spoilers closed or floating)
1.50
Page
JANUARY 17, 2003
1-04-30
Code
5 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
Emerg./Abnormal Procedure
Flaps - Speed
Factor
Flaps 22° - VREF 45 + 10 kt
1.45
Erroneous Stall Protect. Actuation Flaps 22° - VREF 45 + 15 kt - Icing conditions
1.55
Erroneous Stall Protect. Actuation Flaps 45° - VREF 45 + 5 kt - No icing conditions
1.13
Jammed Aileron - Icing conditions Flaps 22° - VREF 45 + 15 kt
1.55
Jammed Aileron - No icing conditions
Flaps 45° - VREF 45 + 5 kt
1.13
Jammed Elevator
Flaps 22° - VREF 45 + 10 kt
1.45
Jammed Rudder - Icing conditions Flaps 22° - VREF 45 + 15 kt
1.55
Jammed Rudder - No icing conditions
1.13
Inadvertent Spoiler Opening in Flight (spoilers open)
Flaps 45° - VREF 45 + 5 kt
Landing Gear Air/Ground Failure - Flaps 22° - VREF 45 + 10 kt Icing conditions
1.73
Landing Gear Air/Ground Failure - Flaps 45° - VREF 45 No icing conditions
1.34
Pitch Trim Inoperative (Pitch up tendency)
Flaps 22° - VREF 45 + 10 kt
1.45
Pitch Trim Inoperative (Pitch down tendency)
Flaps 22° - VREF 45 + 25 kt
1.75
Stabilizer Anti-Icing Failure
Flaps 22° - VREF 45 + 15 kt
1.55
Stabilizer + Wing Anti-Icing Failure Flaps 22° - VREF 45 + 30 kt
1.85
Stall Protection Inoperative - Icing Flaps 22° - VREF 45 + 15 kt conditions
1.55
Stall Protection Inoperative - No icing conditions
Flaps 45° - VREF 45 + 5 kt
1.13
Wing Anti-Icing Asymmetry
Flaps 22° - VREF 45 + 30 kt
1.85
One Engine Inoperative Approach and Landing
Flaps 22° - VREF 45 + 10 kt
1.44
Wing Anti-Icing Failure
Flaps 22° - VREF 45 + 30 kt
1.85
Page
1-04-30
Code
6 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E FAA
MAXIMUM LANDING WEIGHT - FIELD LENGTH LIMITED Maximum Landing Weights - Field Length Limited are read from the tables based on the runway length, surface condition, pressure altitude and Flaps (22° or 45°) configuration. The associated conditions are: - Anti-Ice System...................................................... ON or OFF - Wind ...................................................................... Zero NOTE: - The Maximum Landing Weight - Field Length Limited tables incorporate runway factoring. Refer to the Unfactored Landing Distances tables for obtaining the actual landing distance. - Check the Maximum Landing Weight (MLW) according to the information provided in the AOM Limitations section before using the table.
Page
JANUARY 17, 2003
1-04-30
Code
7 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
MAXIMUM LANDING WEIGHT TABLES - FIELD LENGHT LIMITED FAA - FLAPS 22° - NO ICE ENCOUNTER DRY Runway Length (ft)
ALTITUDE (ft) 0
500
1000
1500
2000
2500
3000
3500
4000
4500
4200 4400 4600 4800 5000 5200 5400 5600 5800 6000 6200 6400 6600 6800
MAXIMUM LANDING WEIGHT - FIELD LENGTH LIMITED (lb) 31317 30868 30439 30009 28908 33137 32660 32198 31734 31282 30830 30399 29951 34991 34479 33982 33482 32999 32519 32054 31574 31108 30649 36842 36303 35781 35256 34745 34230 33730 33216 32723 32235 38685 38120 37572 37021 36486 35948 35426 34885 34360 33838 40517 39928 39355 38778 38219 37657 37110 36546 35999 35454 40785 40785 40785 40523 39942 39355 38785 38198 37630 37060 40785 40785 40785 40785 40785 40785 40447 39840 39248 38654 40785 40785 40785 40785 40785 40785 40785 40785 40785 40237 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785
Runway
ALTITUDE (ft)
WET Length (ft) 4200 4400 4600 4800 5000 5200 5400 5600 5800 6000 6200 6400 6600 6800
0
500
1000
1500
2000
2500
3000
3500
4000
4500
MAXIMUM LANDING WEIGHT - FIELD LENGTH LIMITED (lb) 30611 30180 29752 32187 31725 31277 30826 30397 29966 28691 33782 33288 32812 32339 31879 31417 30969 30511 30068 29106 35394 34877 34374 33868 33377 32886 32416 31930 31459 30991 37003 36461 35937 35410 34897 34380 33878 33361 32864 32373 38605 38041 37495 36945 36411 35873 35353 34813 34289 33767 40200 39615 39045 38473 37919 37361 36817 36258 35715 35174 40785 40785 40586 39995 39419 38838 38276 37698 37135 36571 40785 40785 40785 40785 40785 40309 39729 39127 38545 37963
Page
1-04-30
Code
8 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
MAXIMUM LANDING WEIGHT TABLES - FIELD LENGHT LIMITED FAA - FLAPS 22° - AFTER ICE ENCOUNTER DRY Runway Length (ft)
ALTITUDE (ft) 0
500
1000
1500
2000
2500
3000
3500
4000
4500
4200 4400 4600 4800 5000 5200 5400 5600 5800 6000 6200 6400 6600 6800
MAXIMUM LANDING WEIGHT - FIELD LENGTH LIMITED (lb) 27075 26674 28735 28310 27898 27481 27077 26669 30411 29958 29518 29076 28647 28216 27797 27368 26951 26526 32082 31604 31142 30676 30222 29767 29324 28870 28431 27983 33781 33255 32759 32271 31796 31318 30855 30378 29915 29444 35527 34972 34437 33901 33381 32865 32379 31880 31397 30907 37307 36718 36146 35573 35022 34472 33939 33393 32874 32361 39032 38436 37858 37271 36688 36102 35534 34958 34405 33846 40725 40116 39523 38915 38327 37736 37151 36544 35956 35362 40785 40785 40785 40529 39930 39318 38720 38110 37521 36901 40785 40785 40785 40785 40785 40785 40261 39641 39026 38402 40785 40785 40785 40785 40785 40785 40785 40785 40507 39875
Runway
ALTITUDE (ft)
WET Length (ft) 4200 4400 4600 4800 5000 5200 5400 5600 5800 6000 6200 6400 6600 6800
0
500
1000
1500
2000
2500
3000
3500
4000
4500
MAXIMUM LANDING WEIGHT - FIELD LENGTH LIMITED (lb) 27869 27456 27055 26651 29318 28882 28460 28035 27623 27207 26804 30775 30316 29871 29424 28989 28552 28129 27694 27272 26843 32227 31747 31283 30815 30359 29902 29457 29001 28559 28110 33705 33181 32689 32201 31727 31251 30788 30312 29850 29380 35219 34673 34143 33611 33095 32596 32114 31619 31140 30653 36765 36184 35621 35060 34522 33980 33455 32924 32424 31918 38284 37700 37121 36532 35962 35387 34838 34278 33736 33187
Page
JANUARY 17, 2003
1-04-30
Code
9 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
MAXIMUM LANDING WEIGHT TABLES - FIELD LENGHT LIMITED FAA - FLAPS 45° - NO ICE ENCOUNTER DRY Runway Length (ft)
ALTITUDE (ft) 0
500
1000
1500
2000
2500
3000
3500
4000
4500
4200
MAXIMUM LANDING WEIGHT - FIELD LENGTH LIMITED (lb) 37407 36851 36310 35767 35237 34709 34194 33663 33145 32637
4400
39921 39341 38764 38177 37615 37051 36500 35934 35382 34834
4600
40785 40785 40785 40528 39960 39364 38779 38192 37635 37063
4800
40785 40785 40785 40785 40785 40785 40785 40353 39766 39170
5000
40785 40785 40785 40785 40785 40785 40785 40785 40785 40785
5200
40785 40785 40785 40785 40785 40785 40785 40785 40785 40785
5400
40785 40785 40785 40785 40785 40785 40785 40785 40785 40785
5600
40785 40785 40785 40785 40785 40785 40785 40785 40785 40785
5800
40785 40785 40785 40785 40785 40785 40785 40785 40785 40785
6000
40785 40785 40785 40785 40785 40785 40785 40785 40785 40785
6200
40785 40785 40785 40785 40785 40785 40785 40785 40785 40785
6400
40785 40785 40785 40785 40785 40785 40785 40785 40785 40785
6600
40785 40785 40785 40785 40785 40785 40785 40785 40785 40785
6800
40785 40785 40785 40785 40785 40785 40785 40785 40785 40785
Runway
ALTITUDE (ft)
WET Length
0
(ft) 4200 4400 4600 4800 5000 5200 5400 5600 5800 6000 6200 6400 6600 6800
32763 34908 37080 39273 40785 40785 40785 40785 40785 40785 40785 40785 40785
500
1500
2000
2500
3000
3500
4000
4500
MAXIMUM LANDING WEIGHT - FIELD LENGTH LIMITED (lb) 32283 31816 31347 30890 34391 33886 33378 32888 32402 31928 31435 30954 36529 35993 35454 34930 34406 33896 33368 32857 32356 38690 38119 37546 36995 36438 35895 35336 34797 34259 40785 40224 39648 39055 38462 37899 37329 36759 36189 40785 40785 40785 40785 40420 39845 39239 38655 38086 40785 40785 40785 40785 40785 40785 40785 40486 39888 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785 40785
Page
1-04-30
1000
Code
10 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E FAA
QUICK TURN AROUND WEIGHT For normal operation, the brake temperature can be monitored through the brake temperature indication in the MFD. The Quick Turn Around Weight Table must be used only when the brake temperature indication is not working properly (according to the MMEL). In this case, if the landing weight exceeds the Quick Turn Around Weight, a subsequent takeoff must not be performed before 33 minutes for ER Brakes (P/N 2-1582) or 36 minutes for LR Brakes (P/N 2-1624) after chocks on. At the end of this time interval, check that the wheel thermal plugs have not melted. The identification of which brakes equip a given airplane can be done through the tire size stamped in its side: - ER brakes: 30 X 9.5-14 tires. - LR brakes: H30 X 9.5-16 tires. NOTE: - If the tires are not flat after 33 minutes for ER Brakes (P/N 2-1582) or 36 minutes for LR Brakes (P/N 2-1624), this is a positive indication that the wheel thermal plugs have not melted. - The tables presented in this section refer to ER Brakes (P/N 2-1582), but can also be used to LR Brakes (P/N 2-1624). If the airplane is equipped with LR Brakes and restrictive weights are found, refer to AFM Quick Turn Around Weight charts.
Page
JANUARY 17, 2003
1-04-30
Code
11 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 22° - NO ICE ENCOUNTER - SEA LEVEL WIND -10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40 44 48
-2% 33470 33201 32938 32679 32422 32177 31935 31700 31471 31244 31021 30811 30602 30393 30187 29989 29793 29604
-1% 33949 33677 33412 33150 32891 32643 32399 32162 31930 31701 31476 31263 31052 30841 30633 30433 30235 30044
0 34423 34145 33875 33608 33345 33092 32843 32602 32366 32133 31903 31687 31472 31257 31045 30841 30640 30445
0 Kt 1% 34950 34668 34394 34123 33856 33599 33347 33102 32862 32625 32392 32172 31954 31736 31521 31314 31110 30912
SLOPE 2% -2% 35411 36632 35126 36324 34849 36024 34574 35728 34303 35435 34043 35155 33787 34879 33539 34611 33296 34349 33056 34091 32820 33836 32597 33595 32376 33357 32155 33118 31937 32883 31728 32657 31521 32434 31321 32218
-1% 37143 36832 36529 36230 35934 35651 35372 35102 34837 34576 34319 34076 33834 33594 33356 33128 32902 32684
0 37675 37358 37050 36745 36444 36156 35872 35596 35326 35061 34799 34551 34306 34061 33819 33586 33356 33134
1% 38251 37930 37617 37307 37002 36709 36421 36141 35867 35597 35331 35080 34831 34582 34337 34100 33867 33642
2% 38756 38431 38114 37800 37491 37194 36902 36619 36341 36068 35798 35544 35291 35039 34790 34551 34315 34086
1% 40761 40407 40063 39723 39387 39065 38748 38441 38139 37843 37550 37274 37000 36726 36456 36196 35940 35692
2% 41299 40941 40592 40247 39907 39581 39260 38948 38643 38342 38046 37766 37488 37211 36937 36674 36415 36163
WIND 10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40 44 48
-2% 37803 37480 37166 36855 36548 36254 35965 35684 35408 35138 34870 34618 34368 34118 33871 33634 33400 33173
-1% 38326 38000 37682 37368 37058 36761 36469 36185 35907 35633 35364 35109 34856 34603 34354 34115 33878 33649
0 38879 38547 38224 37904 37589 37286 36988 36699 36416 36138 35863 35603 35346 35089 34835 34591 34350 34117
20 Kt 1% 39474 39137 38809 38484 38164 37857 37555 37261 36974 36691 36412 36148 35887 35626 35368 35121 34876 34639
SLOPE 2% -2% 39995 39035 39654 38696 39321 38367 38992 38041 38668 37719 38357 37411 38050 37108 37753 36813 37462 36524 37175 36240 36893 35960 36626 35696 36361 35433 36097 35171 35835 34913 35585 34664 35337 34419 35097 34181
-1% 39570 39228 38895 38566 38241 37930 37623 37326 37034 36747 36464 36197 35932 35668 35406 35155 34907 34667
0 40147 39798 39460 39124 38793 38476 38164 37861 37564 37272 36984 36712 36442 36172 35906 35650 35398 35154
NOTE: Quick Turn Around Weight in lb. Page
1-04-30
Code
12 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 22° - NO ICE ENCOUNTER - 1000 FEET WIND -10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40 44 48
-2% 32890 32623 32363 32109 31860 31619 31380 31151 30927 30704 30486 30274 30068 29868 29670 29472 29282 29094
-1% 33363 33093 32831 32574 32323 32079 31838 31607 31380 31155 30935 30721 30513 30311 30110 29910 29719 29529
0 33825 33551 33283 33022 32766 32518 32272 32037 31806 31577 31353 31135 30923 30717 30513 30309 30115 29921
0 Kt 1% 34343 34065 33793 33528 33268 33016 32767 32528 32294 32061 31833 31612 31397 31188 30981 30774 30576 30379
SLOPE 2% -2% 34797 35969 34515 35664 34240 35367 33971 35077 33708 34794 33452 34518 33200 34245 32958 33984 32721 33728 32484 33473 32254 33225 32030 32982 31812 32748 31600 32519 31390 32293 31181 32066 30981 31851 30781 31635
-1% 36473 36165 35865 35573 35286 35007 34732 34468 34210 33952 33701 33457 33219 32988 32760 32531 32313 32096
0 36993 36679 36374 36076 35784 35500 35220 34951 34688 34426 34170 33921 33679 33444 33211 32979 32757 32535
1% 37559 37241 36931 36628 36332 36044 35759 35486 35219 34953 34693 34440 34195 33956 33720 33484 33258 33034
2% 38055 37733 37418 37112 36812 36520 36231 35955 35684 35415 35152 34895 34647 34405 34166 33926 33698 33470
1% 40000 39650 39309 38976 38650 38333 38020 37721 37426 37134 36848 36570 36300 36038 35778 35518 35270 35023
2% 40528 40173 39828 39490 39160 38839 38522 38219 37921 37624 37335 37053 36780 36514 36251 35987 35736 35486
WIND 10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40 44 48
-2% 37108 36788 36477 36173 35875 35586 35300 35026 34757 34490 34229 33975 33729 33489 33252 33015 32788 32562
-1% 37623 37301 36986 36679 36378 36086 35797 35521 35249 34980 34716 34460 34211 33968 33729 33489 33260 33032
0 38164 37836 37515 37202 36896 36598 36304 36023 35747 35472 35203 34942 34689 34442 34198 33954 33721 33489
20 Kt 1% 38748 38415 38089 37772 37461 37159 36860 36574 36294 36015 35742 35477 35220 34970 34722 34474 34237 34002
SLOPE 2% -2% 39260 38306 38922 37971 38592 37644 38271 37326 37956 37014 37649 36710 37347 36410 37057 36123 36773 35842 36490 35562 36215 35288 35946 35022 35685 34764 35431 34512 35180 34264 34929 34015 34690 33777 34451 33540
-1% 38834 38496 38165 37844 37528 37222 36919 36629 36345 36062 35786 35517 35256 35002 34751 34499 34259 34020
0 39397 39052 38716 38388 38067 37755 37447 37152 36862 36574 36293 36019 35753 35494 35239 34983 34738 34495
NOTE: Quick Turn Around Weight in lb. Page
JANUARY 17, 2003
1-04-30
Code
13 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 22° - NO ICE ENCOUNTER - 2000 FEET WIND -10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40 44
-2% 32311 32050 31798 31551 31308 31073 30836 30608 30387 30170 29956 29747 29545 29349 29156 28961 28777
-1% 32778 32515 32260 32010 31765 31528 31288 31058 30835 30616 30399 30188 29984 29786 29591 29395 29209
0 33230 32962 32702 32448 32199 31957 31713 31479 31251 31028 30807 30592 30384 30183 29984 29784 29595
0 Kt 1% 33739 33467 33203 32945 32692 32446 32199 31961 31730 31504 31280 31061 30850 30646 30444 30241 30049
SLOPE 2% -2% 34185 35308 33909 35011 33642 34722 33381 34440 33124 34163 32875 33895 32624 33624 32383 33364 32149 33112 31920 32864 31693 32619 31472 32381 31258 32150 31051 31926 30847 31706 30641 31484 30446 31274
-1% 35806 35505 35214 34929 34649 34378 34105 33842 33587 33337 33090 32849 32616 32390 32167 31943 31731
0 36313 36007 35710 35420 35136 34859 34581 34313 34054 33799 33547 33302 33064 32834 32608 32379 32163
1% 36869 36558 36257 35963 35674 35393 35111 34839 34575 34317 34061 33812 33571 33337 33107 32875 32656
2% 37356 37041 36736 36438 36145 35861 35574 35299 35032 34770 34511 34258 34014 33778 33545 33310 33088
1% 39241 38899 38568 38244 37926 37618 37307 37009 36719 36434 36153 35879 35614 35357 35104 34849 34608
2% 39759 39413 39077 38749 38427 38115 37800 37497 37204 36915 36631 36353 36084 35824 35568 35309 35065
WIND 10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40 44
-2% 36414 36103 35800 35504 35214 34932 34649 34376 34111 33851 33594 33344 33102 32867 32636 32403 32183
-1% 36923 36608 36303 36004 35711 35426 35139 34864 34596 34334 34075 33822 33577 33340 33107 32872 32649
0 37451 37130 36819 36515 36216 35926 35635 35354 35082 34814 34550 34293 34044 33802 33565 33325 33099
20 Kt 1% 38024 37699 37383 37074 36771 36476 36180 35895 35619 35348 35079 34818 34565 34320 34079 33836 33606
SLOPE 2% -2% 38526 37579 38197 37252 37877 36935 37563 36625 37256 36321 36958 36025 36658 35728 36369 35442 36089 35164 35814 34892 35543 34623 35278 34360 35022 34106 34774 33860 34529 33618 34283 33374 34050 33143
-1% 38100 37770 37449 37136 36828 36530 36230 35941 35660 35385 35113 34848 34592 34343 34099 33852 33619
0 38649 38313 37987 37668 37354 37051 36745 36450 36165 35885 35608 35338 35077 34824 34575 34323 34086
NOTE: Quick Turn Around Weight in lb.
Page
1-04-30
Code
14 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 22° - NO ICE ENCOUNTER - 3000 FEET WIND -10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40 44
-2% 31737 31480 31234 30996 30759 30522 30296 30072 29852 29640 29432 29228 29030 28835 28643 28460 28282
-1% 32198 31939 31691 31450 31210 30971 30743 30516 30295 30080 29870 29664 29464 29267 29074 28889 28709
0 32639 32375 32123 31877 31633 31390 31157 30926 30701 30482 30268 30059 29855 29655 29457 29269 29086
0 Kt 1% 33139 32871 32615 32366 32118 31871 31635 31401 31172 30950 30732 30519 30313 30109 29909 29718 29532
SLOPE 2% -2% 33577 34652 33305 34359 33046 34079 32793 33807 32543 33536 32292 33266 32053 33007 31816 32751 31584 32501 31359 32259 31139 32021 30923 31788 30714 31562 30507 31340 30305 31121 30111 30912 29922 30709
-1% 35143 34847 34564 34289 34016 33743 33482 33223 32971 32725 32485 32250 32022 31797 31576 31365 31160
0 35639 35337 35049 34769 34490 34212 33946 33683 33426 33176 32932 32692 32460 32231 32006 31791 31582
1% 36184 35878 35585 35301 35018 34736 34466 34199 33938 33684 33436 33193 32957 32725 32497 32278 32066
2% 36662 36352 36055 35767 35481 35195 34922 34651 34386 34129 33878 33632 33393 33157 32926 32705 32490
1% 38488 38151 37829 37517 37206 36895 36599 36305 36018 35739 35466 35199 34939 34684 34433 34192 33959
2% 38996 38655 38329 38012 37697 37383 37082 36784 36493 36211 35934 35664 35401 35142 34887 34644 34408
WIND 10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40 44
-2% 35727 35419 35125 34840 34556 34272 34001 33733 33471 33216 32967 32723 32486 32253 32023 31804 31591
-1% 36229 35918 35621 35333 35046 34760 34486 34215 33950 33693 33441 33194 32955 32719 32488 32266 32051
0 36744 36427 36125 35831 35539 35248 34969 34693 34423 34161 33905 33654 33410 33170 32934 32708 32489
20 Kt 1% 37306 36985 36678 36380 36084 35787 35504 35224 34950 34684 34424 34169 33922 33678 33438 33209 32987
SLOPE 2% -2% 37799 36858 37473 36536 37163 36228 36860 35928 36560 35631 36260 35333 35973 35049 35689 34768 35412 34493 35142 34226 34879 33965 34620 33709 34370 33460 34123 33216 33880 32975 33648 32745 33423 32522
-1% 37372 37046 36735 36432 36132 35831 35544 35260 34982 34713 34449 34190 33939 33692 33449 33217 32991
0 37908 37576 37259 36951 36645 36339 36047 35757 35474 35200 34931 34668 34412 34161 33913 33677 33447
NOTE: Quick Turn Around Weight in lb.
Page
JANUARY 17, 2003
1-04-30
Code
15 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 22° - NO ICE ENCOUNTER - 4000 FEET WIND -10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40
-2% 31158 30910 30667 30429 30196 29970 29744 29527 29312 29101 28899 28701 28509 28323 28141 27965
-1% 31613 31364 31118 30877 30642 30413 30186 29967 29749 29536 29332 29132 28938 28750 28567 28389
0 32044 31789 31539 31294 31055 30822 30590 30367 30146 29928 29720 29517 29320 29128 28941 28760
0 Kt 1% 32535 32276 32023 31774 31531 31294 31059 30832 30608 30387 30176 29969 29769 29575 29385 29201
SLOPE 2% -2% 32965 33991 32703 33709 32446 33432 32194 33160 31948 32894 31708 32635 31469 32378 31240 32130 31012 31885 30788 31643 30575 31413 30365 31187 30163 30968 29966 30756 29773 30548 29587 30347
-1% 34476 34191 33910 33636 33367 33106 32846 32596 32348 32104 31871 31643 31422 31207 30998 30794
0 34959 34668 34383 34103 33830 33564 33299 33044 32792 32543 32306 32074 31849 31630 31417 31209
1% 35494 35199 34910 34625 34348 34078 33809 33550 33294 33042 32801 32565 32337 32115 31898 31688
2% 35963 35664 35371 35083 34802 34528 34256 33994 33734 33478 33235 32995 32764 32539 32320 32107
1% 37729 37405 37086 36774 36468 36171 35876 35591 35310 35032 34768 34508 34257 34013 33774 33543
2% 38227 37899 37576 37259 36950 36649 36350 36061 35776 35495 35227 34964 34710 34462 34221 33986
WIND 10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40
-2% 35033 34738 34447 34161 33882 33611 33341 33081 32824 32571 32329 32092 31863 31640 31422 31211
-1% 35528 35229 34936 34647 34366 34092 33819 33557 33297 33041 32797 32557 32325 32100 31880 31667
0 36031 35726 35427 35133 34847 34567 34290 34023 33758 33497 33249 33005 32769 32539 32316 32098
20 Kt 1% 36582 36273 35969 35671 35380 35097 34815 34544 34275 34010 33758 33510 33271 33038 32811 32590
SLOPE 2% -2% 37065 36131 36752 35821 36444 35516 36142 35217 35848 34925 35560 34640 35275 34357 35000 34085 34728 33815 34459 33549 34204 33296 33953 33047 33711 32807 33475 32573 33244 32345 33021 32123
-1% 36637 36324 36016 35713 35418 35131 34845 34570 34297 34029 33773 33522 33279 33043 32813 32589
0 37160 36841 36527 36219 35919 35626 35335 35055 34777 34504 34243 33987 33740 33500 33265 33037
NOTE: Quick Turn Around Weight in lb.
Page
1-04-30
Code
16 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 22° - NO ICE ENCOUNTER - 5000 FEET WIND -10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40
-2% 30586 30343 30107 29873 29641 29419 29198 28985 28779 28577 28382 28190 28004 27820 27636 27455
-1% 31036 30790 30552 30316 30081 29857 29634 29419 29210 29006 28809 28615 28428 28242 28056 27874
0 31456 31205 30963 30722 30484 30256 30028 29809 29596 29389 29188 28991 28799 28611 28421 28235
0 Kt 1% 31938 31683 31438 31193 30951 30719 30488 30266 30050 29840 29636 29435 29241 29049 28857 28668
SLOPE 2% -2% 32360 33339 32102 33061 31853 32792 31605 32525 31360 32260 31125 32007 30891 31754 30666 31511 30448 31275 30234 31045 30027 30822 29824 30603 29628 30391 29434 30183 29239 29977 29048 29776
-1% 33817 33536 33264 32994 32727 32471 32216 31971 31732 31500 31274 31053 30839 30628 30421 30218
0 34288 34001 33725 33450 33178 32917 32657 32407 32165 31928 31699 31473 31255 31041 30830 30623
1% 34813 34522 34242 33962 33686 33422 33158 32904 32658 32417 32184 31956 31734 31517 31302 31092
2% 35273 34978 34694 34411 34131 33863 33596 33339 33089 32845 32610 32378 32153 31933 31716 31503
1% 36980 36660 36352 36044 35740 35450 35159 34881 34610 34345 34089 33838 33594 33355 33119 32888
2% 37468 37144 36832 36520 36212 35918 35624 35341 35067 34799 34540 34285 34038 33796 33557 33323
WIND 10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40
-2% 34349 34058 33776 33495 33217 32952 32687 32432 32185 31943 31709 31480 31257 31039 30824 30613
-1% 34837 34543 34258 33974 33694 33426 33158 32901 32651 32407 32171 31939 31714 31493 31276 31063
0 35327 35027 34737 34448 34163 33890 33617 33355 33100 32852 32611 32375 32146 31921 31700 31483
20 Kt 1% 35868 35563 35269 34976 34686 34409 34132 33866 33607 33355 33111 32871 32639 32411 32186 31966
SLOPE 2% -2% 36341 35414 36033 35108 35735 34813 35438 34518 35144 34227 34863 33949 34583 33671 34313 33404 34051 33145 33796 32891 33548 32646 33305 32405 33070 32172 32839 31943 32611 31717 32388 31496
-1% 35913 35604 35305 35008 34714 34433 34152 33883 33621 33365 33117 32874 32638 32407 32179 31955
0 36422 36107 35803 35501 35201 34915 34629 34355 34088 33827 33575 33327 33087 32852 32620 32392
NOTE: Quick Turn Around Weight in lb.
Page
JANUARY 17, 2003
1-04-30
Code
17 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 22° - AFTER ICE ENCOUNTER - SEA LEVEL WIND -10 Kt Temp. (oC) -26 -24 -22 -20 -18 -16 -14 -12 -10 -8 -6 -4 -2 0 2 4 6 8
-2% 32049 31912 31776 31641 31510 31379 31251 31124 30999 30871 30746 30622 30503 30385 30267 30151 30036 29925
-1% 32543 32405 32267 32131 31999 31866 31737 31609 31482 31354 31227 31102 30982 30863 30744 30626 30511 30398
0 33008 32868 32728 32589 32455 32320 32188 32058 31930 31799 31670 31543 31421 31300 31179 31059 30941 30827
0 Kt 1% 33498 33354 33212 33072 32935 32798 32664 32532 32401 32268 32137 32008 31884 31761 31638 31516 31397 31281
SLOPE 2% -2% 33967 34971 33822 34814 33678 34657 33536 34502 33397 34351 33258 34200 33122 34053 32988 33907 32856 33763 32721 33617 32588 33472 32458 33331 32332 33194 32207 33058 32082 32923 31959 32788 31838 32657 31720 32529
-1% 35493 35334 35176 35020 34867 34715 34566 34419 34274 34126 33980 33837 33699 33562 33425 33289 33156 33028
0 36008 35846 35686 35527 35372 35217 35066 34916 34768 34618 34469 34324 34183 34044 33905 33767 33632 33501
1% 36547 36382 36219 36057 35900 35742 35588 35436 35286 35133 34982 34835 34692 34550 34409 34269 34131 33998
2% 37058 36891 36725 36561 36402 36242 36086 35932 35780 35625 35472 35322 35178 35034 34891 34749 34610 34475
1% 38880 38700 38521 38344 38171 37999 37830 37663 37499 37331 37166 37004 36848 36692 36537 36384 36233 36087
2% 39423 39240 39058 38879 38704 38529 38358 38189 38023 37852 37685 37521 37362 37205 37048 36892 36740 36592
WIND 10 Kt Temp. (oC) -26 -24 -22 -20 -18 -16 -14 -12 -10 -8 -6 -4 -2 0 2 4 6 8
-2% 36098 35933 35769 35607 35449 35291 35137 34984 34834 34680 34529 34381 34238 34096 33954 33813 33675 33542
-1% 36631 36464 36299 36135 35976 35816 35661 35506 35355 35200 35047 34897 34753 34609 34466 34324 34185 34050
0 37165 36996 36828 36661 36499 36337 36178 36022 35867 35710 35554 35402 35255 35109 34964 34819 34678 34541
20 Kt 1% 37723 37551 37379 37210 37045 36881 36720 36560 36403 36243 36085 35931 35781 35633 35485 35338 35195 35055
SLOPE 2% -2% 38249 37207 38075 37035 37901 36863 37730 36693 37563 36528 37396 36363 37233 36201 37071 36041 36912 35884 36750 35723 36590 35565 36433 35409 36282 35260 36131 35111 35981 34962 35833 34815 35687 34671 35546 34531
-1% 37751 37577 37403 37232 37065 36898 36735 36574 36415 36252 36092 35936 35784 35634 35484 35336 35190 35049
0 38304 38127 37951 37777 37606 37437 37271 37107 36945 36780 36618 36458 36304 36152 35999 35848 35700 35556
NOTE: Quick Turn Around Weight in lb. Page
1-04-30
Code
18 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 22° - AFTER ICE ENCOUNTER - 1000 FEET WIND -10 Kt Temp. (oC) -26 -24 -22 -20 -18 -16 -14 -12 -10 -8 -6 -4 -2 0 2 4 6 8
-2% 31476 31342 31211 31081 30951 30822 30695 30570 30446 30324 30202 30083 29966 29851 29737 29624 29514 29407
-1% 31964 31829 31697 31566 31434 31304 31176 31049 30924 30801 30678 30557 30440 30324 30208 30094 29983 29875
0 32419 32282 32148 32014 31881 31748 31618 31489 31362 31237 31112 30989 30869 30751 30634 30518 30405 30295
0 Kt 1% 32899 32760 32623 32487 32351 32216 32084 31954 31824 31697 31570 31445 31323 31204 31084 30967 30851 30739
SLOPE 2% -2% 33360 34312 33219 34158 33080 34008 32943 33858 32805 33709 32669 33560 32535 33414 32402 33270 32271 33128 32142 32988 32013 32847 31887 32710 31764 32576 31642 32444 31521 32313 31402 32183 31285 32056 31172 31933
-1% 34827 34673 34520 34370 34219 34068 33922 33776 33632 33491 33349 33211 33075 32942 32809 32678 32550 32426
0 35331 35174 35019 34866 34712 34559 34410 34262 34116 33972 33828 33687 33549 33414 33279 33146 33015 32889
1% 35858 35699 35541 35385 35229 35074 34922 34772 34623 34477 34330 34187 34047 33910 33772 33637 33505 33376
2% 36360 36198 36038 35880 35722 35565 35411 35259 35108 34959 34811 34666 34524 34385 34246 34108 33974 33844
1% 38126 37951 37778 37608 37436 37266 37100 36935 36772 36612 36451 36295 36141 35990 35840 35692 35546 35405
2% 38658 38480 38305 38133 37959 37787 37618 37451 37286 37123 36961 36802 36646 36493 36341 36191 36044 35901
WIND 10 Kt Temp. (oC) -26 -24 -22 -20 -18 -16 -14 -12 -10 -8 -6 -4 -2 0 2 4 6 8
-2% 35408 35247 35089 34933 34776 34621 34469 34318 34169 34022 33875 33731 33591 33453 33315 33180 33047 32918
-1% 35934 35772 35613 35455 35297 35140 34986 34834 34683 34535 34387 34242 34100 33960 33822 33684 33550 33420
0 36456 36292 36130 35969 35808 35649 35492 35337 35184 35033 34883 34735 34591 34449 34308 34169 34032 33900
20 Kt 1% 37002 36835 36670 36507 36344 36181 36022 35865 35709 35556 35403 35253 35107 34962 34819 34677 34539 34404
SLOPE 2% -2% 37519 36484 37350 36317 37182 36151 37017 35988 36851 35824 36687 35661 36526 35501 36366 35343 36209 35187 36053 35033 35898 34880 35746 34729 35598 34583 35452 34438 35306 34294 35163 34152 35022 34013 34886 33878
-1% 37021 36852 36685 36520 36354 36189 36028 35869 35711 35556 35401 35249 35101 34955 34809 34666 34526 34389
0 37562 37390 37220 37052 36884 36716 36553 36390 36230 36072 35914 35760 35609 35461 35313 35167 35024 34885
NOTE: Quick Turn Around Weight in lb. Page
JANUARY 17, 2003
1-04-30
Code
19 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 22° - AFTER ICE ENCOUNTER - 2000 FEET WIND -10 Kt Temp. (oC) -26 -24 -22 -20 -18 -16 -14 -12 -10 -8 -6 -4 -2 0 2 4 6 8
-2% 30910 30779 30651 30524 30398 30272 30148 30027 29910 29792 29676 29561 29448 29336 29223 29110 29000 28893
-1% 31393 31260 31131 31003 30875 30749 30624 30501 30383 30263 30146 30030 29916 29803 29689 29575 29464 29356
0 31838 31704 31572 31443 31312 31183 31056 30932 30811 30690 30571 30453 30337 30222 30106 29990 29877 29767
0 Kt 1% 32308 32172 32038 31906 31774 31643 31514 31387 31264 31141 31020 30900 30782 30665 30547 30430 30315 30203
SLOPE 2% -2% 32762 33661 32623 33511 32488 33363 32354 33218 32220 33072 32087 32928 31956 32786 31828 32646 31704 32511 31579 32375 31456 32242 31335 32110 31215 31980 31097 31851 30977 31721 30858 31592 30742 31465 30628 31342
-1% 34171 34019 33870 33723 33576 33430 33287 33146 33009 32872 32738 32604 32473 32343 32212 32081 31954 31829
0 34663 34509 34357 34208 34058 33910 33764 33621 33482 33343 33206 33071 32937 32805 32671 32539 32409 32282
1% 35180 35022 34869 34717 34565 34414 34266 34120 33979 33838 33699 33561 33425 33291 33155 33020 32888 32759
2% 35672 35513 35357 35203 35049 34896 34746 34598 34455 34312 34171 34031 33894 33758 33620 33483 33349 33219
1% 37382 37210 37041 36875 36708 36543 36381 36221 36067 35912 35759 35608 35459 35312 35163 35016 34871 34730
2% 37904 37729 37559 37390 37221 37054 36889 36728 36571 36414 36259 36106 35956 35806 35655 35506 35359 35216
WIND 10 Kt Temp. (oC) -26 -24 -22 -20 -18 -16 -14 -12 -10 -8 -6 -4 -2 0 2 4 6 8
-2% 34727 34569 34415 34263 34110 33959 33810 33664 33523 33381 33242 33103 32967 32832 32696 32561 32429 32300
-1% 35247 35087 34932 34778 34624 34471 34321 34174 34031 33888 33747 33607 33470 33334 33196 33060 32926 32796
0 35757 35596 35437 35281 35124 34969 34817 34667 34521 34376 34232 34090 33951 33812 33673 33534 33398 33265
20 Kt 1% 36292 36127 35966 35808 35648 35491 35335 35183 35035 34887 34742 34597 34455 34315 34173 34031 33893 33759
SLOPE 2% -2% 36799 35772 36632 35607 36469 35445 36308 35286 36147 35126 35987 34968 35830 34812 35675 34659 35526 34511 35376 34363 35228 34217 35082 34072 34938 33929 34795 33788 34651 33646 34508 33504 34368 33365 34232 33230
-1% 36302 36135 35972 35811 35650 35490 35333 35178 35029 34879 34731 34585 34441 34299 34155 34012 33872 33735
0 36830 36661 36495 36332 36167 36005 35845 35688 35536 35383 35233 35085 34939 34794 34647 34502 34359 34221
NOTE: Quick Turn Around Weight in lb. Page
1-04-30
Code
20 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 22° - AFTER ICE ENCOUNTER - 3000 FEET WIND -10 Kt Temp. (oC) -26 -24 -22 -20 -18 -16 -14 -12 -10 -8 -6 -4 -2 0 2 4 6 8
-2% 30355 30225 30098 29973 29850 29728 29610 29495 29381 29267 29154 29041 28927 28816 28707 28601 28496 28391
-1% 30832 30701 30573 30447 30322 30200 30080 29964 29849 29734 29620 29506 29391 29278 29169 29061 28956 28849
0 31268 31135 31005 30876 30750 30625 30504 30386 30268 30151 30035 29919 29803 29688 29577 29467 29360 29252
0 Kt 1% 31729 31594 31461 31331 31202 31075 30952 30832 30712 30593 30476 30358 30239 30123 30010 29899 29789 29679
SLOPE 2% -2% 32175 33023 32038 32874 31903 32728 31771 32584 31640 32442 31512 32303 31387 32167 31265 32035 31144 31903 31024 31772 30905 31643 30785 31513 30665 31382 30547 31253 30432 31129 30320 31007 30209 30886 30098 30765
-1% 33526 33376 33228 33083 32940 32799 32662 32528 32396 32263 32132 32001 31869 31740 31614 31490 31369 31247
0 34008 33855 33705 33557 33412 33268 33129 32993 32858 32724 32591 32457 32323 32191 32063 31938 31814 31690
1% 34514 34358 34206 34056 33907 33762 33620 33482 33345 33208 33073 32937 32801 32667 32537 32409 32284 32157
2% 34997 34839 34685 34533 34383 34235 34091 33951 33812 33674 33537 33399 33261 33125 32994 32864 32737 32609
1% 36652 36482 36315 36150 35988 35828 35673 35522 35371 35222 35073 34925 34775 34628 34486 34346 34208 34070
2% 37164 36991 36822 36656 36491 36329 36172 36019 35866 35714 35564 35414 35262 35113 34969 34827 34688 34547
WIND 10 Kt Temp. (oC) -26 -24 -22 -20 -18 -16 -14 -12 -10 -8 -6 -4 -2 0 2 4 6 8
-2% 34059 33903 33750 33599 33451 33305 33163 33024 32887 32750 32614 32478 32341 32207 32076 31948 31822 31696
-1% 34572 34414 34260 34108 33958 33811 33667 33528 33389 33250 33113 32976 32838 32702 32570 32441 32314 32186
0 35072 34911 34755 34600 34447 34298 34152 34009 33868 33727 33588 33448 33308 33170 33036 32904 32775 32645
20 Kt 1% 35595 35432 35272 35115 34960 34808 34659 34515 34371 34228 34087 33945 33802 33662 33526 33392 33261 33128
SLOPE 2% -2% 36092 35072 35927 34909 35766 34749 35607 34591 35449 34436 35295 34283 35145 34134 34998 33989 34853 33845 34708 33701 34564 33559 34420 33417 34276 33274 34133 33133 33996 32997 33860 32862 33727 32731 33593 32598
-1% 35595 35430 35269 35110 34953 34798 34648 34502 34356 34211 34068 33924 33780 33637 33500 33364 33231 33097
0 36112 35944 35780 35618 35458 35302 35149 35000 34852 34704 34559 34412 34266 34121 33981 33843 33708 33572
NOTE: Quick Turn Around Weight in lb. Page
JANUARY 17, 2003
1-04-30
Code
21 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 22° - AFTER ICE ENCOUNTER - 4000 FEET WIND -10 Kt Temp. (oC) -26 -24 -22 -20 -18 -16 -14 -12 -10 -8 -6 -4 -2 0 2 4 6 8
-2% 29796 29670 29547 29424 29305 29188 29073 28957 28844 28731 28619 28511 28404 28298 28192 28086 27983 27882
-1% 30268 30141 30016 29892 29773 29654 29537 29421 29306 29192 29079 28970 28863 28756 28648 28541 28438 28335
0 30694 30565 30438 30313 30191 30071 29952 29833 29717 29601 29486 29375 29265 29157 29048 28939 28833 28729
0 Kt 1% 31145 31014 30885 30758 30634 30512 30391 30270 30152 30034 29917 29805 29693 29583 29472 29361 29254 29148
SLOPE 2% -2% 31583 32380 31450 32236 31320 32094 31190 31953 31065 31817 30941 31682 30819 31549 30696 31416 30576 31286 30457 31156 30339 31027 30224 30903 30111 30780 30000 30659 29887 30536 29775 30415 29667 30297 29559 30180
-1% 32877 32731 32588 32446 32308 32172 32038 31903 31772 31641 31511 31386 31262 31139 31016 30893 30773 30656
0 33348 33200 33054 32909 32769 32631 32494 32358 32224 32091 31959 31831 31705 31581 31455 31330 31209 31089
1% 33843 33692 33544 33397 33255 33114 32975 32836 32700 32565 32431 32301 32173 32046 31919 31791 31668 31547
2% 34317 34164 34014 33865 33721 33578 33438 33297 33159 33022 32886 32755 32625 32496 32367 32238 32113 31990
1% 35917 35752 35589 35428 35272 35118 34966 34814 34665 34517 34370 34228 34087 33948 33808 33669 33534 33401
2% 36419 36252 36087 35924 35766 35610 35456 35301 35150 35000 34851 34707 34565 34424 34282 34141 34004 33869
WIND 10 Kt Temp. (oC) -26 -24 -22 -20 -18 -16 -14 -12 -10 -8 -6 -4 -2 0 2 4 6 8
-2% 33386 33235 33086 32939 32796 32655 32516 32377 32240 32105 31970 31840 31711 31584 31456 31329 31205 31083
-1% 33893 33740 33590 33441 33297 33155 33014 32874 32736 32599 32463 32332 32202 32074 31944 31815 31691 31568
0 34381 34225 34073 33922 33775 33630 33487 33344 33204 33065 32927 32793 32661 32531 32399 32268 32141 32016
20 Kt 1% 34892 34735 34580 34426 34277 34130 33984 33839 33697 33555 33415 33279 33145 33012 32878 32745 32616 32489
SLOPE 2% -2% 35381 34368 35221 34209 35064 34054 34908 33900 34757 33750 34608 33602 34460 33457 34313 33311 34169 33168 34025 33026 33883 32885 33746 32749 33610 32614 33475 32481 33340 32347 33205 32214 33074 32084 32945 31957
-1% 34884 34724 34567 34411 34260 34111 33964 33817 33673 33529 33387 33250 33114 32979 32844 32709 32579 32450
0 35389 35226 35066 34908 34755 34603 34453 34304 34157 34011 33866 33727 33588 33452 33314 33177 33044 32913
NOTE: Quick Turn Around Weight in lb. Page
1-04-30
Code
22 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 22° - AFTER ICE ENCOUNTER - 5000 FEET WIND -10 Kt Temp. (oC) -26 -24 -22 -20 -18 -16 -14 -12 -10 -8 -6 -4 -2 0 2 4 6 8
-2% 29248 29125 29003 28883 28767 28652 28540 28431 28323 28211 28100 27992 27888 27784 27679 27575 27473 27373
-1% 29714 29590 29467 29346 29229 29112 29000 28890 28781 28667 28555 28447 28341 28236 28130 28025 27922 27822
0 30132 30006 29880 29757 29638 29520 29405 29293 29182 29067 28953 28843 28735 28628 28521 28414 28309 28207
0 Kt 1% 30574 30445 30318 30193 30072 29951 29835 29721 29609 29492 29376 29264 29154 29046 28936 28828 28721 28617
SLOPE 2% -2% 31004 31750 30874 31609 30745 31469 30618 31331 30495 31198 30373 31065 30256 30937 30140 30811 30026 30687 29907 30558 29790 30431 29676 30307 29565 30187 29455 30067 29344 29946 29234 29827 29126 29709 29021 29595
-1% 32241 32099 31957 31818 31683 31549 31420 31293 31168 31038 30909 30784 30663 30542 30420 30299 30181 30065
0 32701 32556 32412 32271 32134 31997 31866 31737 31610 31477 31346 31219 31096 30973 30849 30726 30606 30488
1% 33185 33038 32892 32748 32608 32470 32337 32205 32076 31941 31808 31679 31554 31429 31303 31178 31056 30936
2% 33651 33501 33353 33208 33066 32926 32791 32658 32526 32390 32255 32124 31997 31870 31743 31616 31492 31371
1% 35196 35035 34875 34717 34564 34413 34266 34123 33981 33833 33687 33546 33408 33272 33133 32997 32863 32732
2% 35689 35525 35363 35203 35048 34895 34746 34601 34457 34307 34159 34016 33877 33738 33598 33460 33324 33191
WIND 10 Kt Temp. (oC) -26 -24 -22 -20 -18 -16 -14 -12 -10 -8 -6 -4 -2 0 2 4 6 8
-2% 32727 32579 32432 32288 32148 32009 31875 31744 31614 31479 31345 31216 31090 30965 30838 30713 30591 30471
-1% 33227 33078 32930 32784 32643 32503 32368 32235 32104 31967 31832 31702 31575 31448 31321 31194 31070 30949
0 33704 33552 33401 33253 33110 32967 32830 32695 32561 32423 32285 32153 32023 31895 31765 31637 31510 31387
20 Kt 1% 34204 34050 33897 33747 33601 33456 33316 33179 33043 32902 32763 32628 32496 32366 32234 32103 31975 31850
SLOPE 2% -2% 34683 33677 34527 33523 34372 33369 34220 33218 34071 33072 33925 32926 33783 32786 33644 32648 33507 32512 33364 32371 33222 32231 33086 32096 32953 31964 32820 31833 32686 31701 32554 31570 32424 31441 32297 31316
-1% 34187 34031 33876 33723 33575 33429 33287 33148 33011 32868 32727 32590 32457 32325 32191 32059 31929 31802
0 34680 34521 34363 34208 34058 33909 33765 33623 33484 33339 33195 33056 32921 32786 32650 32516 32384 32255
NOTE: Quick Turn Around Weight in lb. Page
JANUARY 17, 2003
1-04-30
Code
23 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 45° - NO ICE ENCOUNTER - SEA LEVEL WIND -10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40 44 48
-2% 35671 35390 35115 34844 34577 34320 34068 33822 33581 33344 33111 32890 32670 32452 32236 32028 31824 31625
-1% 36089 35805 35528 35255 34986 34727 34473 34225 33982 33744 33509 33286 33064 32844 32627 32417 32211 32010
0 36564 36277 35998 35722 35450 35188 34931 34680 34435 34194 33957 33731 33508 33285 33066 32854 32645 32443
0 Kt 1% 37027 36735 36452 36171 35895 35629 35369 35114 34866 34621 34380 34151 33924 33698 33475 33260 33048 32843
SLOPE 2% -2% 37486 38725 37193 38408 36907 38098 36624 37793 36346 37492 36078 37202 35815 36918 35559 36641 35308 36370 35061 36103 34818 35840 34588 35591 34359 35344 34131 35097 33906 34854 33690 34620 33476 34389 33269 34165
-1% 39167 38847 38536 38228 37924 37632 37346 37067 36793 36524 36259 36008 35759 35511 35266 35029 34797 34571
0 39675 39352 39036 38725 38419 38124 37834 37552 37276 37004 36736 36482 36230 35980 35732 35494 35259 35030
1% 40184 39856 39536 39221 38909 38610 38316 38029 37749 37473 37201 36944 36688 36433 36182 35940 35701 35469
2% 40669 40338 40016 39697 39384 39082 38786 38497 38214 37936 37662 37403 37145 36888 36635 36391 36150 35916
1% 42668 42310 41962 41617 41278 40951 40631 40318 40012 39711 39415 39134 38855 38578 38303 38039 37779 37526
2% 43173 42812 42460 42113 41771 41442 41119 40804 40495 40192 39894 39610 39329 39049 38773 38507 38245 37990
WIND 10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40 44 48
-2% 39884 39554 39232 38913 38600 38298 38002 37713 37431 37153 36879 36620 36362 36105 35852 35608 35368 35134
-1% 40336 40002 39678 39357 39041 38737 38438 38147 37863 37583 37307 37045 36785 36527 36271 36026 35783 35548
0 40855 40519 40191 39866 39547 39240 38938 38644 38357 38073 37795 37530 37268 37007 36749 36500 36255 36017
20 Kt 1% 41383 41041 40708 40379 40055 39743 39437 39138 38846 38559 38276 38007 37741 37476 37214 36962 36713 36472
SLOPE 2% -2% 41877 41127 41533 40781 41197 40444 40865 40111 40538 39782 40224 39467 39915 39157 39615 38854 39320 38559 39030 38268 38745 37981 38475 37709 38206 37440 37939 37171 37675 36906 37421 36651 37170 36399 36927 36154
-1% 41588 41240 40900 40564 40233 39915 39602 39298 38999 38706 38417 38143 37871 37601 37334 37076 36822 36576
0 42121 41769 41425 41086 40752 40430 40114 39806 39505 39209 38917 38640 38365 38092 37822 37562 37305 37056
NOTE: Quick Turn Around Weight in lb. Page
1-04-30
Code
24 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 45° - NO ICE ENCOUNTER - 1000 FEET WIND -10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40 44 48
-2% 35058 34779 34507 34242 33982 33729 33480 33240 33005 32772 32544 32321 32105 31895 31687 31480 31281 31083
-1% 35470 35190 34916 34648 34387 34132 33880 33639 33402 33167 32937 32713 32495 32283 32073 31864 31664 31464
0 35939 35655 35378 35109 34844 34586 34332 34088 33849 33611 33379 33152 32932 32718 32506 32295 32093 31891
0 Kt 1% 36392 36104 35823 35549 35281 35019 34761 34513 34270 34029 33793 33563 33340 33122 32907 32693 32487 32282
SLOPE 2% -2% 36847 38034 36556 37720 36273 37413 35997 37115 35726 36822 35462 36537 35202 36256 34953 35986 34708 35721 34465 35458 34227 35201 33995 34950 33770 34707 33551 34470 33334 34236 33118 34002 32911 33778 32704 33555
-1% 38470 38154 37845 37544 37249 36962 36678 36406 36139 35874 35615 35362 35117 34878 34642 34406 34181 33956
0 38970 38651 38339 38034 37736 37446 37160 36884 36615 36347 36085 35830 35582 35341 35102 34864 34636 34408
1% 39469 39145 38828 38519 38217 37922 37631 37352 37078 36806 36541 36281 36030 35785 35542 35300 35069 34838
2% 39948 39621 39302 38991 38686 38388 38095 37814 37538 37264 36996 36735 36481 36234 35990 35746 35513 35280
1% 41889 41535 41189 40852 40522 40201 39884 39579 39281 38984 38694 38412 38137 37870 37606 37342 37090 36838
2% 42387 42030 41681 41342 41010 40685 40366 40059 39758 39459 39167 38882 38606 38336 38070 37804 37550 37296
WIND 10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40 44 48
-2% 39164 38837 38518 38207 37902 37605 37312 37031 36755 36481 36214 35952 35699 35452 35208 34964 34731 34499
-1% 39610 39280 38958 38645 38338 38038 37743 37459 37181 36905 36636 36372 36117 35868 35622 35376 35141 34907
0 40122 39789 39464 39147 38836 38534 38235 37949 37668 37389 37117 36850 36592 36341 36092 35844 35607 35370
20 Kt 1% 40638 40300 39970 39648 39333 39026 38723 38432 38147 37864 37587 37317 37055 36800 36547 36296 36054 35814
SLOPE 2% -2% 41126 40373 40786 40031 40453 39697 40129 39371 39811 39052 39501 38741 39196 38434 38903 38140 38616 37851 38330 37564 38051 37284 37779 37011 37515 36745 37258 36487 37003 36231 36749 35976 36506 35732 36264 35489
-1% 40828 40483 40146 39818 39497 39183 38874 38577 38286 37997 37715 37439 37172 36911 36653 36396 36150 35905
0 41353 41005 40664 40333 40008 39691 39378 39078 38784 38492 38207 37928 37658 37395 37135 36875 36626 36378
NOTE: Quick Turn Around Weight in lb. Page
JANUARY 17, 2003
1-04-30
Code
25 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 45° - NO ICE ENCOUNTER - 2000 FEET WIND -10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40 44
-2% 34446 34174 33910 33651 33397 33151 32904 32665 32433 32206 31982 31763 31550 31344 31141 30938 30744
-1% 34854 34580 34314 34053 33797 33549 33299 33059 32826 32596 32370 32149 31936 31728 31523 31318 31123
0 35317 35040 34770 34507 34248 33997 33745 33503 33266 33035 32806 32583 32367 32157 31950 31743 31546
0 Kt 1% 35760 35479 35206 34938 34675 34421 34165 33919 33679 33444 33212 32985 32766 32553 32343 32133 31932
SLOPE 2% -2% 36210 37345 35926 37038 35651 36740 35381 36449 35116 36163 34860 35885 34602 35606 34353 35338 34112 35077 33875 34820 33641 34568 33413 34321 33192 34081 32977 33849 32765 33620 32553 33391 32351 33173
-1% 37776 37467 37167 36873 36584 36305 36024 35753 35490 35231 34977 34728 34487 34252 34022 33791 33571
0 38269 37957 37653 37356 37065 36782 36498 36225 35959 35698 35440 35188 34945 34708 34475 34242 34019
1% 38757 38440 38132 37831 37535 37248 36960 36682 36412 36147 35885 35630 35383 35142 34906 34669 34443
2% 39230 38911 38601 38296 37998 37709 37419 37139 36866 36599 36336 36079 35829 35587 35349 35110 34882
1% 41112 40766 40430 40101 39779 39466 39151 38849 38554 38265 37980 37702 37432 37170 36912 36654 36407
2% 41604 41255 40917 40585 40260 39945 39628 39323 39026 38734 38447 38166 37895 37630 37371 37110 36862
WIND 10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40 44
-2% 38447 38127 37817 37513 37215 36926 36636 36356 36084 35817 35554 35296 35047 34805 34567 34328 34101
-1% 38886 38565 38252 37945 37645 37354 37061 36779 36505 36236 35970 35711 35460 35216 34976 34735 34506
0 39391 39066 38750 38440 38137 37842 37546 37262 36984 36713 36444 36182 35929 35682 35440 35196 34964
20 Kt 1% 39896 39566 39245 38931 38623 38324 38024 37735 37453 37177 36905 36639 36381 36131 35885 35638 35403
SLOPE 2% -2% 40379 39622 40046 39288 39722 38963 39406 38645 39095 38333 38794 38030 38491 37726 38200 37433 37916 37148 37638 36869 37364 36593 37095 36324 36836 36063 36584 35810 36335 35560 36087 35310 35849 35072
-1% 40071 39734 39407 39086 38772 38467 38160 37865 37578 37296 37018 36747 36484 36229 35977 35725 35485
0 40588 40248 39917 39593 39275 38967 38657 38359 38069 37784 37503 37229 36963 36705 36451 36197 35954
NOTE: Quick Turn Around Weight in lb.
Page
1-04-30
Code
26 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 45° - NO ICE ENCOUNTER - 3000 FEET WIND -10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40 44
-2% 33841 33572 33314 33064 32816 32568 32331 32097 31867 31644 31426 31212 31004 30800 30598 30402 30211
-1% 34244 33973 33713 33461 33211 32961 32722 32486 32255 32030 31810 31594 31385 31179 30976 30778 30585
0 34700 34426 34164 33909 33656 33404 33162 32923 32690 32462 32240 32022 31811 31602 31397 31198 31003
0 Kt 1% 35134 34856 34590 34331 34074 33818 33573 33330 33093 32863 32637 32416 32201 31989 31781 31579 31381
SLOPE 2% -2% 35578 36662 35298 36359 35030 36069 34769 35787 34510 35507 34252 35228 34005 34961 33761 34697 33521 34438 33289 34187 33062 33941 32839 33700 32622 33466 32409 33235 32199 33008 31995 32787 31796 32572
-1% 37088 36783 36490 36206 35924 35643 35373 35107 34846 34593 34345 34102 33866 33634 33405 33182 32965
0 37574 37265 36970 36682 36397 36113 35841 35572 35308 35052 34802 34556 34318 34083 33852 33627 33407
1% 38051 37738 37438 37146 36857 36569 36292 36019 35752 35492 35238 34988 34746 34508 34273 34045 33822
2% 38519 38203 37901 37607 37315 37025 36746 36471 36201 35939 35683 35431 35188 34947 34711 34481 34256
1% 40342 40000 39673 39355 39040 38725 38424 38126 37834 37551 37274 37002 36738 36478 36222 35973 35730
2% 40828 40484 40154 39833 39515 39198 38894 38594 38300 38015 37735 37461 37195 36933 36675 36424 36179
WIND 10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40 44
-2% 37736 37420 37118 36824 36532 36242 35964 35688 35419 35157 34901 34650 34406 34166 33929 33699 33475
-1% 38170 37852 37547 37251 36957 36664 36384 36106 35835 35571 35313 35059 34814 34572 34333 34101 33875
0 38667 38345 38038 37738 37441 37146 36862 36582 36307 36041 35780 35524 35276 35031 34790 34556 34327
20 Kt 1% 39161 38835 38522 38219 37917 37617 37329 37044 36766 36495 36230 35970 35719 35470 35226 34988 34756
SLOPE 2% -2% 39638 38878 39309 38547 38994 38231 38687 37923 38384 37618 38081 37314 37791 37022 37504 36734 37223 36452 36950 36178 36683 35910 36421 35647 36168 35392 35917 35140 35671 34893 35431 34652 35197 34417
-1% 39321 38988 38669 38359 38051 37745 37451 37161 36876 36600 36330 36064 35808 35554 35304 35062 34825
0 39830 39494 39171 38858 38547 38237 37940 37647 37360 37081 36807 36539 36280 36023 35771 35526 35287
NOTE: Quick Turn Around Weight in lb.
Page
JANUARY 17, 2003
1-04-30
Code
27 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 45° - NO ICE ENCOUNTER - 4000 FEET WIND -10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40
-2% 33231 32972 32717 32467 32224 31986 31750 31522 31297 31075 30864 30655 30451 30252 30057 29867
-1% 33630 33368 33111 32860 32614 32374 32137 31907 31680 31457 31243 31033 30828 30626 30430 30238
0 34079 33815 33555 33301 33053 32810 32570 32338 32109 31883 31667 31455 31248 31044 30845 30652
0 Kt 1% 34504 34235 33972 33714 33462 33216 32972 32736 32504 32275 32056 31840 31629 31423 31221 31025
SLOPE 2% -2% 34943 35975 34673 35683 34407 35396 34147 35114 33893 34840 33645 34572 33399 34306 33162 34049 32927 33796 32696 33546 32476 33307 32259 33073 32046 32843 31838 32618 31635 32398 31437 32184
-1% 36396 36101 35812 35528 35251 34981 34713 34454 34198 33947 33706 33470 33238 33011 32790 32574
0 36874 36576 36284 35997 35718 35445 35174 34912 34654 34400 34157 33917 33683 33454 33230 33012
1% 37341 37039 36742 36451 36167 35890 35615 35350 35087 34829 34582 34340 34102 33869 33642 33421
2% 37803 37499 37199 36906 36620 36340 36064 35796 35531 35271 35023 34778 34539 34304 34075 33852
1% 39568 39238 38914 38597 38287 37985 37685 37396 37110 36828 36559 36294 36035 35781 35533 35292
2% 40047 39715 39389 39069 38757 38452 38150 37858 37570 37286 37015 36748 36487 36231 35981 35738
WIND 10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40
-2% 37020 36716 36417 36123 35837 35558 35281 35014 34749 34490 34241 33996 33757 33522 33294 33071
-1% 37449 37142 36840 36545 36257 35975 35696 35426 35160 34898 34647 34401 34160 33923 33692 33468
0 37938 37628 37323 37025 36734 36449 36167 35895 35625 35361 35107 34858 34615 34376 34142 33916
20 Kt 1% 38421 38107 37797 37494 37199 36910 36624 36347 36074 35805 35548 35295 35048 34805 34568 34338
SLOPE 2% -2% 38892 38129 38575 37810 38263 37497 37957 37190 37659 36890 37368 36598 37080 36308 36801 36028 36526 35751 36255 35479 35996 35219 35741 34963 35491 34713 35247 34467 35008 34227 34776 33994
-1% 38566 38245 37929 37620 37318 37023 36731 36449 36170 35896 35633 35375 35123 34875 34633 34398
0 39067 38742 38424 38111 37806 37508 37213 36928 36646 36369 36104 35843 35588 35337 35093 34856
NOTE: Quick Turn Around Weight in lb.
Page
1-04-30
Code
28 02
JANUARY 17, 2003
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
QUICK TURN AROUND WEIGHT TABLE FAA - FLAPS 45° - NO ICE ENCOUNTER - 5000 FEET WIND -10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40
-2% 32629 32374 32127 31881 31638 31405 31174 30951 30733 30520 30311 30105 29906 29710 29517 29328
-1% 33023 32765 32516 32269 32024 31789 31556 31331 31112 30897 30686 30479 30278 30080 29886 29696
0 33466 33206 32954 32704 32456 32219 31983 31756 31535 31318 31104 30895 30692 30492 30296 30104
0 Kt 1% 33881 33617 33362 33108 32856 32616 32376 32146 31921 31701 31484 31272 31065 30863 30663 30468
SLOPE 2% -2% 34316 35297 34050 35009 33792 34731 33536 34454 33283 34180 33040 33918 32799 33657 32566 33405 32340 33161 32118 32920 31900 32684 31685 32453 31477 32228 31273 32007 31073 31790 30876 31577
-1% 35712 35422 35141 34862 34586 34322 34059 33805 33558 33316 33079 32845 32618 32396 32177 31963
0 36183 35890 35606 35324 35046 34778 34513 34256 34007 33762 33522 33286 33057 32832 32611 32394
1% 36640 36342 36054 35768 35485 35214 34944 34684 34431 34182 33938 33699 33466 33238 33014 32794
2% 37096 36796 36506 36217 35932 35659 35387 35125 34870 34619 34373 34132 33898 33668 33441 33220
1% 38803 38478 38164 37852 37543 37248 36953 36670 36394 36123 35857 35596 35342 35093 34848 34608
2% 39276 38949 38633 38318 38007 37709 37412 37126 36848 36575 36307 36044 35788 35537 35290 35049
WIND 10 Kt Temp. (oC) -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 36 40
-2% 36314 36014 35724 35435 35150 34877 34605 34343 34088 33838 33592 33351 33117 32887 32661 32439
-1% 36736 36434 36142 35851 35564 35288 35014 34750 34493 34241 33993 33750 33514 33283 33054 32831
0 37218 36913 36617 36324 36034 35755 35478 35212 34952 34697 34447 34201 33962 33728 33498 33272
20 Kt 1% 37691 37381 37081 36783 36488 36205 35924 35653 35390 35131 34877 34627 34385 34148 33914 33684
SLOPE 2% -2% 38156 37389 37843 37075 37541 36771 37240 36469 36943 36171 36658 35885 36375 35600 36102 35326 35836 35059 35576 34797 35319 34540 35068 34287 34824 34042 34584 33801 34348 33564 34117 33332
-1% 37820 37504 37198 36893 36593 36304 36017 35741 35472 35208 34948 34694 34447 34204 33965 33732
0 38314 37994 37685 37377 37073 36782 36492 36213 35941 35674 35412 35155 34905 34660 34418 34182
NOTE: Quick Turn Around Weight in lb.
Page
JANUARY 17, 2003
1-04-30
Code
29 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-04-30
Code
30 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
PERFORMANCE EMB-135BJ A1E FAA
LANDING PERFORMANCE Refer to the Airplane Flight Manual for a complete set of charts for determination of the landing limiting weights. EMBRAER RUNWAYS ANALYSIS SOFTWARE Although the AFM presents all the required performance data for takeoff, the amount of options and charts presented, makes its use very difficult. In order to help operators, EMBRAER developed a runway analysis software for determination of the limiting weights. THE LANDING OUTPUT DATA The program outputs the limit weight, the code for the limitation detected, the approach climb speed, the reference speed and the quick turn around weight. This data is provided for several combinations of wind and temperature. The data is calculated for four reference winds and for a range of temperatures. Limitation codes assigned are an A for approach climb limited weight, R for runway limited weight, L for landing climb limited weight, and S for structural limited weight. If the operation for a specific condition is considered unfeasible or outside the performance tables, the relevant data will be provided with asterisks.
Page
JANUARY 17, 2003
1-04-30
Code
31 02
PERFORMANCE EMB-135BJ A1E FAA
AIRPLANE OPERATIONS MANUAL
Wind (in knots) EMB-135 BJ LANDING ANALYSIS, ALLISON 3007A1P ENGINES, FAA CERTIFICATION ---------------------------------------------------------------------Airport: AIRPORT NAME Runway: 20 Elevation: 110 LANDING DISTANCE AVAILABLE: 2000 m Slope: 0 % --------------------------------------------------------------------------------------------------------Anti Ice: OFF Runway: WET --------------------------------------------------------------------------------------------------------LIMIT WEIGHT (Lb)/ Code/ V.Approach Climb(Kt)/ V.Ref(Kt)/ Quick T.Around Wt(Lb) versus Temperature and Wind: --------------------------------------------------------------------------------------------------------Temp(C) -10 Kt 0 Kt 10 Kt 20 Kt --------------------------------------------------------------------------------------------------------2 18700/S/153/127/15530 18700/S/153/127/17347 18700/S/153/127/17990 18700/S/153/127/18676 4 18700/S/153/127/15475 18700/S/153/127/17282 18700/S/153/127/17920 18700/S/153/127/18603 6 18700/S/153/127/15420 18700/S/153/127/17216 18700/S/153/127/17851 18700/S/153/127/18530 8 18700/S/153/127/15366 18700/S/153/127/17153 18700/S/153/127/17784 18700/S/153/127/18459 10 18700/S/153/127/15313 18700/S/153/127/17089 18700/S/153/127/17716 18700/S/153/127/18388 12 18700/S/153/127/15260 18700/S/153/127/17027 18700/S/153/127/17650 18700/S/153/127/18318 14 18700/S/153/127/15208 18700/S/153/127/16964 18700/S/153/127/17584 18700/S/153/127/18248 16 18700/S/153/127/15157 18700/S/153/127/16903 18700/S/153/127/17520 18700/S/153/127/18181 18 18700/S/153/127/15106 18700/S/153/127/16843 18700/S/153/127/17456 18700/S/153/127/18113 20 18700/S/153/127/15055 18700/S/153/127/16782 18700/S/153/127/17392 18700/S/153/127/18046 22 18700/S/153/127/15005 18700/S/153/127/16722 18700/S/153/127/17329 18700/S/153/127/17979 24 18700/S/153/127/14955 18700/S/153/127/16664 18700/S/153/127/17267 18700/S/153/127/17914 26 18700/S/153/127/14906 18700/S/153/127/16605 18700/S/153/127/17205 18700/S/153/127/17849 28 18700/S/153/127/14858 18700/S/153/127/16548 18700/S/153/127/17144 18700/S/153/127/17785 30 18700/S/153/127/14810 18700/S/153/127/16491 18700/S/153/127/17084 18700/S/153/127/17722 32 18700/S/153/127/14763 18700/S/153/127/16434 18700/S/153/127/17024 18700/S/153/127/17659 34 18700/S/153/127/14715 18700/S/153/127/16378 18700/S/153/127/16964 18700/S/153/127/17596 36 18700/S/153/127/14669 18700/S/153/127/16323 18700/S/153/127/16906 18700/S/153/127/17535 38 18700/S/153/127/14622 18700/S/153/127/16267 18700/S/153/127/16848 18700/S/153/127/17473 ---------------------------------------------------------------------------------------------------------Limitation codes: A - Approach climb; L = Landing Climb; R - Runway; S - Structural
Temperature (in degrees Celsius) EXAMPLE
Page
1-04-30
Limit weight (in pounds), limiting factor, approach climb speed (in knots), reference speed (in knots), and quick turn around weight (in pounds)
Code
32 02
JANUARY 17, 2003
WEIGHT AND BALANCE
AIRPLANE OPERATIONS MANUAL
SECTION 1-06 WEIGHT AND BALANCE TABLE OF CONTENTS Page Block INTRODUCTION ....................................................................... 1-06-00 STANDARD TERMS AND DEFINITIONS ................................. 1-06-10 GENERAL DATA ....................................................................... 1-06-20 INDEX SYSTEM ........................................................................ 1-06-30
Page
NOVEMBER 30, 2001
1-06-00
Code
1 01
WEIGHT AND BALANCE
AIRPLANE OPERATIONS MANUAL
INTRODUCTION This Section contains supplementary information to that already presented in the Weight and Balance manual (CTA: WB-135/1561, FAA: WB-135/1562 and JAA: WB-135/1563). This supplementary information is intended to assist the operator in defining the weight and balance system and constrained CG limits.
Page
1-06-00
Code
2 01
NOVEMBER 30, 2001
WEIGHT AND BALANCE
AIRPLANE OPERATIONS MANUAL
STANDARD TERMS AND DEFINITIONS EQUIPPED EMPTY WEIGHT (EEW) OR MANUFACTURER EMPTY WEIGHT (MEW) It is the weight of structure, power plant, instruments, interior furnishings, systems, optional, portable, and emergency equipment and other items of equipment that are an integral part of the airplane configuration. It is essentially a dry weight, including only those fluids contained in closed systems such as oxygen, fire extinguisher agent, landing gear shock absorber fluid, etc. BASIC EMPTY WEIGHT (BEW) It is the MEW plus the weight of the following items: − APU oil; − Engine oil; − Hydraulic fluid; − Unusable fuel. OPERATIONAL EMPTY WEIGHT (OEW) OR DRY OPERATING WEIGHT (DOW) It is the BEW plus the weight of the operational items. Operational items are those necessary for airplane operation and not included in the BEW. The operational items are: − Crew and crew baggage; − Navigation kit (manuals, charts, etc.); − Catering (beverages and foods) and removable service equipment for galley (such as standard units, etc.); − Lavatory rinse water; − Lavatory chemical fluid. ACTUAL ZERO FUEL WEIGHT (AZFW) This is the OEW plus actual payload.
Page
NOVEMBER 30, 2001
1-06-10
Code
1 01
WEIGHT AND BALANCE
AIRPLANE OPERATIONS MANUAL
PAYLOAD OR TOTAL TRAFFIC LOAD This is the weight of passengers, baggage and cargo. MAXIMUM ALLOWABLE PAYLOAD It is the maximum approved weight that can be loaded into the airplane. Maximum payload is the Maximum Zero Fuel Weight (MZFW) less Operational Empty Weight (OEW). MAXIMUM DESIGN ZERO FUEL WEIGHT (MZFW) This is the maximum authorized weight before usable fuel be loaded. The MZFW is related to airplane structural limitations. MAXIMUM DESIGN RAMP WEIGHT (MRW) This is the maximum authorized ramp weight. MAXIMUM DESIGN TAKEOFF WEIGHT (MTOW) This is the maximum authorized weight for takeoff. MAXIMUM DESIGN LANDING WEIGHT (MLW) This is the maximum authorized weight for landing. MINIMUM OPERATING WEIGHT (MOW) This is the minimum authorized weight to operate the airplane. CENTER OF GRAVITY (CG) This is the position where the mass of the aircraft is considered concentrated for balance purposes. It is normally referred to in terms of %MAC. AIRPLANE DATUM This is a plane perpendicular to the fuselage centerline from where all arm measurements are taken.
Page
1-06-10
Code
2 01
NOVEMBER 30, 2001
WEIGHT AND BALANCE
AIRPLANE OPERATIONS MANUAL MEAN AERODYNAMIC CHORD (MAC)
This is the chord of an imaginary rectangular airfoil with the same area of the actual wing and which produces the same resulting force vectors of the actual wing. The aircraft forward and aft CG limits are referred to in terms of %MAC. INDEX SYSTEM This is a convention for presenting aircraft or body moments. It is the moment of the body converted to a different measuring system.
Page
NOVEMBER 30, 2001
1-06-10
Code
3 01
WEIGHT AND BALANCE
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-06-10
Code
4 01
NOVEMBER 30, 2001
AIRPLANE OPERATIONS MANUAL
WEIGHT AND BALANCE 135BJ LB
GENERAL DATA The general data presented in this section is intended to be used for specific weight and balance calculations and is equivalent to the information contained in the Weight & Balance Manual.
MAXIMUM GROSS GRAVITY LIMITS
WEIGHTS
AND
CENTER
OF
Refer to section 1-01-05.
Page
JANUARY 17, 2003
1-06-20
Code
1 02
WEIGHT AND BALANCE 135BJ LB
AIRPLANE OPERATIONS MANUAL
BALANCE REFERENCE SYSTEM BALANCE ARMS/BODY STATION Longitudinal location of the Centers of Gravity (CG) identified throughout this Manual regarding airplane and components will be referred to as Balance Arms. Balance Arms are the distance in meters from the Airplane Datum which is located at the zero station of the fuselage. Balance Arms (BA) are equivalent to Body Station (BS) on the EMB-135BJ. AIRPLANE DATUM The Airplane Datum is a plane, perpendicular to the fuselage centerline, located at 456.50 in ahead of the wing stub front spar. For external reference, the Datum is located at 570.63 in ahead of the wing jack points. WING MEAN AERODYNAMIC CHORD (MAC) The length of the MAC is 112.80 in. The leading edge of the MAC (LEMAC) is Balance Arm 495.83 in. Percentage of MAC is obtained using the following formula: %MAC = (X − 495.83) × 100 112.80
where X = Balance Arm of airplane CG measured in meters.
Page
1-06-20
Code
2 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
WEIGHT AND BALANCE 135BJ LB
FUEL DATA FUEL DEFINITIONS − USABLE FUEL - Is the fuel to be effectively consumed by the engines. − UNUSABLE FUEL - Is the fuel remaining after total usable fuel has been consumed. − DRAINABLE FUEL - Is that portion of fuel which can be drawn off through fuel drains with the airplane leveled. − UNDRAINABLE FUEL - Is that portion of fuel which can not be drawn off by standard draining procedures.
Page
REVISION 5
1-06-20
Code
3 02
WEIGHT AND BALANCE 135BJ LB
AIRPLANE OPERATIONS MANUAL
FUEL QUANTITIES
FUEL CATEGORY
VOLUME
WEIGHT
(US Gal)
(lb)
CG BALANCE ARM (in)
WING TANKS: • UNUSABLE UNDRAINABLE
2.6
17.6
490.32
• UNUSABLE DRAINABLE
9.0
60.8
490.59
11.6 1689.6
78.3 11406.5
490.59 517.60
• UNUSABLE • USABLE AUXILIARY FUEL SYSTEM 1 or 2 :
Fwd
Aft
Fwd
Aft
• UNUSABLE UNDRAINABLE
1.2
0.4
8.1
2.7
372.52 798.94
• UNUSABLE DRAINABLE
2.4
4.2
16.2
28.4
366.85 798.94
3.6 279.0 294.0
4.6 217.0 217.0
24.3 1764.0 1984.0
31.1 1455.0 1477.0
366.85 798.94 332.28 798.94 332.28 799.49
• UNUSABLE • USABLE
(3) (4)
TOTAL UNUSABLE TOTAL USABLE
(3) (4)
28.0
189.0
2681.9 2711.5
17844.5 18328.5
Fwd
Aft
NOTE: 1) The values above have been determined for an adopted fuel density 6.751 lb/US Gal. 2) Each Auxiliary Fuel System is composed by one forward fuselage tank and one aft fuselage tank. 3) Max usable fuel allowed. Applicable to airplanes S/N up to 591 or Pre-Mod. SB 145LEG-28-0010. 4) Max usable fuel allowed. Applicable to airplanes S/N 625 and on or Post-Mod. SB 145LEG-28-0010.
Page
1-06-20
Code
4 02
REVISION 5
WEIGHT AND BALANCE 135BJ LB
AIRPLANE OPERATIONS MANUAL
MISCELLANEOUS FLUIDS FLUID ENGINE OIL (1) APU OIL (1) HYDRAULIC (2) • WITH THRUST REVERSER LAVATORY CHEMICAL FLUID WATER
(3) (4) (5) (6)
WEIGHT (lb) 53.0 4.4
BALANCE ARM (in) 739.65 930.71
75.0 8.8 110.2 220. 5 77.2 33.1
608.27 667.72 650.00 650.00 651.57 255.91
NOTE: 1) Adopted engine oil density (ref. MIL-L-7808): 8.17 lb/US Gal. 2) Adopted hydraulic fluid density (ref. SAE AS 1241A TYPE IV): 8.26 lb/US Gal. 3) For airplanes with forward lavatory (optional), the forward lavatory chemical fluid weight is 4.2 lb and its balance arm is 251.57 in. 4) For airplanes S/N 528, 549, 625, 637, 642, 644 and 678. 5) For airplanes S/N 412, 462, 484, 495, 505, 516, 540, 555, 586 and 591. 6) For airplanes S/N 686 and on. For airplanes with forward lavatory (optional), the forward water weight is 22.0 lb and its balance arm is 266.14 in.
PITCH TRIM SETTING NOTE: For takeoff when setting pitch trim to 8, first select 7 and stop trimming immediately when the value 8 is displayed. When setting pitch trim to 4, first select 5 and stop trimming immediately when the value 4 is displayed. LESS THAN CG 26.1 OR POSITION UP TO EQUAL (%) 28.5 TO 26.0 PITCH TRIM UNITS
8
7
28.6 UP TO 30.5
6
ABOVE 30.6 OR UP TO EQUAL 33.5 TO 33.6 5
4
Page
REVISION 7
1-06-20
Code
5 02
WEIGHT AND BALANCE 135BJ LB
AIRPLANE OPERATIONS MANUAL
PASSENGERS PASSENGER LOCATION The passenger location and respective balance arm are shown in the applicable Interior Arrangement (Section 1-07-30). PASSENGER WEIGHT Actual or average passenger weights may be used to compute passenger loads. Actual passenger weights should be used in case of flights carrying large groups of passengers whose average weight obviously does not conform with the normal standard weight such as athletic squads or other groups which are smaller or larger than the local average. The actual passenger weight may be either determined by scale weighing of each passenger, or by asking each passenger their weight and adding there to a predetermined constant to compensate the handcarryed articles and clothing. The following standard average weight may be adopted: − Adult passenger ................................180 lb è Summer 185 lb è Winter − Children (age 2-12) ...........................80 lb NOTE: - Adult passenger weight includes 20 lb of carry-on baggage. - Children under age 2 are considered "babies-in-arms" and children over age 12 should be treated as adult passengers for purposes of standard average weights.
Page
1-06-20
Code
6 02
REVISION 3
AIRPLANE OPERATIONS MANUAL
WEIGHT AND BALANCE 135BJ LB
FLIGHT CREW ITEMS ITEM PILOT COPILOT OBSERVER FLIGHT ATTENDANT CREW BAGGAGE NAVIGATION KIT
WEIGHT (lb) 180 180 180
BALANCE ARM (in) 142.91 142.91 166.57
180
187.40
33 22
252.76 169.29
NOTE: - The adopted flight crew items are in accordance with the approved average weight, not including the respective carryon baggage. The crew baggage is supposed to be carried in the forward wardrobe. - The crew members and attendants weights presented herein refer to male. For female crew members and attendants, a weight equal to 130 lb may be adopted (FAA–AC120-27C).
Page
REVISION 5
1-06-20
Code
7 02
WEIGHT AND BALANCE 135BJ LB
AIRPLANE OPERATIONS MANUAL
THIS PAGE IS LEFT BLANK INTENTIONALLY
Page
1-06-20
Code
8 02
REVISION 3
AIRPLANE OPERATIONS MANUAL
WEIGHT AND BALANCE EMB-135BJ lb
INDEX SYSTEM When determining the aircraft center of gravity position it is necessary to make calculations adding and/or subtracting the moment caused by each individual item loaded in the aircraft. Moment, per definition, is weight multiplied by the distance to a reference point. If the moment of the aircraft and of the items loaded on it are computed in reference to the aircraft datum, very long numeric expressions would result. As the operational usage of long numeric expressions may result in safety problems (since personnel may get confused with the long numbers), airlines usually adopt an Index System for weight and balance purposes. The Index System is just a convention for presenting aircraft or body moments on a different measuring system. When using the Index System, short numeric expressions result. The Index System formula is presented below: I=
W × ( Arm − A) +C B
where: I = Index. W = Aircraft or body weight. Arm = Aircraft or body center of gravity. A = Reference arm. Selected arm around which all index values are calculated. On the balance chart CG envelope, the Reference Arm CG% line is the only vertical CG% line. (*) B = Constant used as a denominator to convert moment values into index values. On the balance chart CG envelope, B controls the CG% lines splay (splay decreases with increasing B). (*) C = Constant used as a plus value to avoid negative index figures. It is only used when computing the aircraft Operating Empty Weight Index (OEI), and is not used when computing individual bodies index influence. On the balance chart CG envelope, the Reference Arm CG% vertical line is at C index units. (*) (*)
Values for A, B and C may be chosen at the operator discretion.
Page
JANUARY 17, 2003
1-06-30
Code
1 02
WEIGHT AND BALANCE EMB-135BJ lb
AIRPLANE OPERATIONS MANUAL
The Embraer recommended Index System formula is: EMB-135BJ Model:
I=
W × ( Arm − 515) + 13 17400
INDEX INFLUENCE Index influence is the variation of index when a body is loaded or unloaded from the aircraft. It is usually referred in index units per kilogram for variable weight bodies (cargo, catering, etc.), index units per passenger when computing passenger influence or index units for fixed weight bodies (flight attendant, cockpit observer, etc.).
Page
1-06-30
Code
2 02
JANUARY 17, 2003
WEIGHT AND BALANCE EMB-135BJ lb
AIRPLANE OPERATIONS MANUAL
The following tables show the index influence for various items: INDEX INFLUENCE FOR EMB-135BJ MODEL Item Cargo/Baggage
Arm (in) 731.10
Reference Weight (lb) 1
Index Influence + 0.012 IU/lb
Galley
214.53
1
- 0.017 IU/lb
LH Closet
271.85
1
- 0.015 IU/lb
RH Closet
271.85
1
- 0.014 IU/lb
LH Fwd Closet
251.77
1
- 0.014 IU/lb
Credenza
473.11
1
- 0.024 IU/lb
Cockpit Observer
165.35
180
- 3.62 IU
(*)
The galley, the LH Closet, LH Fwd Closet, RH Closet and Credenza arms are for the standard configuration. Check the aircraft actual configuration arms in the AOM Loading Section.
Example: Computation of cargo index influence for the EMB-135BJ. The EMB-135BJ cargo compartment centroid is located 731.10 inches from the aircraft datum. The index influence per lb is:
I=
1× (731.10 − 515) = 0.012 IU/lb 17400
So, for each lb of cargo loaded in the cargo compartment, the index increases by 0.012 index units.
Page
JANUARY 17, 2003
1-06-30
Code
3 02
WEIGHT AND BALANCE EMB-135BJ lb
AIRPLANE OPERATIONS MANUAL
FUEL INDEX VARIATION EMB-135BJ Wing Tanks Fuel Volume (US Gal)
Weight (lb)
Arm (in)
Index (IU)
50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800 850 900 950 1000 1050 1100 1150 1200 1250 1300 1350 1400 1450 1500 1550 1600 1650 1690
335 670 1005 1340 1675 2010 2345 2680 3015 3350 3685 4020 4355 4690 5025 5360 5695 6030 6365 6700 7035 7370 7705 8040 8375 8710 9045 9380 9715 10050 10385 10720 11055 11323
491.05 491.88 492.73 493.55 494.35 495.07 495.78 496.45 497.10 497.73 498.33 498.91 499.48 500.08 500.67 501.28 501.95 502.58 503.18 503.81 504.45 505.04 505.68 506.28 506.82 507.49 508.38 509.31 510.40 511.57 512.85 514.26 516.12 517.61
-0.5 -0.9 -1.3 -1.7 -2.0 -2.3 -2.6 -2.9 -3.1 -3.3 -3.5 -3.7 -3.9 -4.0 -4.1 -4.2 -4.3 -4.3 -4.3 -4.3 -4.3 -4.2 -4.1 -4.0 -3.9 -3.8 -3.4 -3.1 -2.6 -2.0 -1.3 -0.5 0.7 1.7
Page
1-06-30
Code
4 02
JANUARY 17, 2003
AIRPLANE OPERATIONS MANUAL
WEIGHT AND BALANCE EMB-135BJ lb
Fuel Distribution on the Forward Fuselage Tanks EMB-135BJ S/N up to 591 or Pre-Mod. SB 145LEG-28-0010 Volume (US Gal) 50 75 100 125 150 175 200 225 250 275 300 325 350 375 400 425 450 475 500 525 550 558
Weight (lb) 335 503 670 838 1005 1173 1340 1508 1675 1843 2010 2178 2345 2513 2680 2848 3015 3183 3350 3518 3685 3739
Arm (in) 358.75 355.22 352.12 349.35 346.86 344.63 342.71 341.08 339.68 338.48 337.45 336.58 335.85 335.20 334.64 334.14 333.71 333.32 332.99 332.70 332.46 332.40
Index (IU) -3.01 -4.62 -6.27 -7.98 -9.71 -11.49 -13.27 -15.07 -16.88 -18.70 -20.51 -22.33 -24.14 -25.97 -27.78 -29.60 -31.41 -33.23 -35.04 -36.86 -38.66 -39.24
NOTE: - Max usable fuel allowed on the forward tanks: - Airplanes S/N up to 591 or Pre-Mod. SB 145LEG-28-0010: 3527 lb. - Airplanes S/N 625 and on or Post-Mod. SB 145LEG-28-0010: 3968 lb. - Adopted fuel density of 6.7 lb/US Gal.
Page
REVISION 5
1-06-30
Code
5 02
WEIGHT AND BALANCE EMB-135BJ lb
AIRPLANE OPERATIONS MANUAL
EMB-135BJ S/N 625 and on or Post-Mod. SB 145LEG-28-0010 Volume (US Gal) 50 75 100 125 150 175 200 225 250 275 300 325 350 375 400 425 450 475 500 525 558 586
Weight (lb) 335 503 670 838 1005 1173 1340 1508 1675 1843 2010 2178 2345 2513 2680 2848 3015 3183 3350 3518 3739 3926
Page
1-06-30
Arm (in) 358.65 355.29 352.25 349.56 346.95 344.59 342.58 340.92 339.61 338.33 337.12 336.37 335.63 334.96 334.54 333.82 333.45 333.08 333.07 332.73 332.28 332.28
Index (IU) -3.01 -4.62 -6.27 -7.97 -9.71 -11.49 -13.29 -15.09 -16.88 -18.71 -20.55 -22.36 -24.17 -26.00 -27.79 -29.66 -31.46 -33.28 -35.03 -36.85 -39.26 -41.23
Code
6 02
REVISION 5
AIRPLANE OPERATIONS MANUAL
WEIGHT AND BALANCE EMB-135BJ lb
Fuel Distribution on the Aft Fuselage Tanks The aft fuselage tanks total fuel capacity is 434 US Gal. NOTE: Maximum usable fuel allowed on the aft fuselage tanks: - Airplanes S/N up to 591 or Pre-Mod. SB 145LEG-28-0010: 2910 lb. - Airplanes S/N 625 and on or Post-Mod. SB 145LEG-28-0010: 2954 lb. The cg balance arm is 798.94 in and does not vary relevantly with the mass due to its geometry.
Page
REVISION 5
1-06-30
Code
7 02
WEIGHT AND BALANCE EMB-135BJ lb
AIRPLANE OPERATIONS MANUAL
OEW/OEI DETERMINATION The OEW (Operational Empty Weight) is the BEW plus the weight of the operational items (crew, catering, lavatory fluid, etc.). The OEI (Operational Empty Index) is the index for the OEW. In order to determine the OEW and OEI, it is necessary to add to the BEW all the weight and moment variations referent to the operational items. The BEW is obtained from the aircraft weighting record. Example: Computation of OEW/OEI for the EMB-135BJ. For a BEW equal 30514 lb and BEW moment equal 16282062.44 lb.in: Weight (lb)
Arm (in)
Moment (lb.in)
30514
-
16282062.44
Pilot & Co-Pilot
44.1 110 360
673.62 649.85 142.91
29706.64 71483.50 51447.60
Flight attendant
180
187.40
33732.00
Crew baggage
33
252.76
8341.08
Navigation kit
22
169.29
3724.38
31263.1
-
16480497.64
Item BEW Lavatory fluid
OEW (not catering)
including
Aircraft arm = 16480497.64 31263.1 = 527.15 inches Aircraft Index =
31263.1 × (527.15 − 515 ) 17400
+ 13 = 35 IU
(not including catering)
NOTE: - Catering weight was not considered above because its weight is not constant. In our example we are considering catering as a separate item (see Index Influences). - Unusable fuel, hydraulic fluid, engine and APU oil are considered included in the BEW. - The values above are an example. Use the aircraft actual BEW for determining the OEW.
Page
1-06-30
Code
8 02
REVISION 5