F2000 - AFM REV13 Complet - 20100721

FALCON 2000 Airplane Flight Manual

AFMORIGINAL : November 30, 1994 REVISION 13 : July 12, 2010

DTM537

Copyright 1994 by Dassault Aviation. All rights reserved. No part of this work may be reproduced or copied in any form or by any means without written permission of Dassault Aviation.

F2000 Airplane Flight Manual

GENERALINTRODUCTION

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SECTION 0 GENERAL

DTM537 EASA APPROVED

DASSAULT AVIATION Proprietary Data

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GENERALINTRODUCTION



INTENTIONALLY LEFT BLANK



GENERALINTRODUCTION DGAC Approval

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DASSAULT AVIATION

AIRPLANE FLIGHT MANUAL

Approved by DIRECTION GENERALE DE L'AVIATION CIVILE

This document, DTM537, is the FALCON 2000 AIRPLANE FLIGHT MANUAL

Serial No: Registration No: Approved by: C. SOUFFLET (DGAC)

Date of approval of the original issue : November 30, 1994.



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GENERALINTRODUCTION DGAC Approval






GENERALINTRODUCTION FAA Approval

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DASSAULT AVIATION


Approved by DIRECTION GENERALE DE L'AVIATION CIVILE on behalf of the FEDERAL AVIATION ADMINISTRATIONDASSAULT AVIATION Proprietary Data


This Manual is approved in accordance with FAR 21.29 for US registered airplanes.

Serial No: Registration No: Approved by: C. SOUFFLET (I.E.E.A.C)

Date of approval of the original issue : February 2, 1995.

US registered A/C


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GENERALINTRODUCTION FAA Approval





US registered A/C


GENERALINTRODUCTION CTA Approval

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DASSAULT AVIATION


Approved by DIRECTION GENERALE DE L'AVIATION CIVILE on behalf of the CENTRO TECHNICO AEROSPACIAL


This Airplane Flight Manual is approved by DGAC on behalf of Centro Tcnico Aeroespacial for Brazilian registered Airplanes in accordance with the Regulamentos Brasileiros de Homologao Aeronutica (RBHA) Part 21, Section 21.29.

Serial No: Registration No: Approved by: S. MORALES (I.E.E.A.C) on behalf of CTA.

Date of approval of the original issue : September 22, 2000.

Brazilian registered A/C



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GENERALINTRODUCTION CTA Approval





Brazilian registered A/C


GENERALINTRODUCTION CAA Approval

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DASSAULT AVIATION


Approved by DIRECTION GENERALE DE L'AVIATION CIVILE on behalf of the UK CIVIL AVIATION AUTHORITYDASSAULT AVIATION Proprietary Data


This Manual is approved in accordance with the CAA Type Certificate FA 66 for UK registered airplanes.

Serial No: Registration No: Approved by: S. MORALES (I.E.E.A.C).

Date of approval of the original issue : October 21, 1996.

UK registered A/C


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GENERALINTRODUCTION CAA Approval





UK registered A/C


GENERALINTRODUCTION List of sections

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LIST OF SECTIONS

SECTION 0 GENERAL.

SECTION 1 LIMITATIONS.

SECTION 2 EMERGENCY PROCEDURES.

SECTION 4 NORMAL PROCEDURES.

SECTION 5 PERFORMANCE.

ANNEXES.

SUPPLEMENTS.

CONFIGURATION DEVIATION LIST.



SECTION 3 ABNORMAL PROCEDURES.

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GENERALINTRODUCTION List of sections






GENERALINTRODUCTION Table of contents

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TABLE OF CONTENTS INTRODUCTION DGAC Approval ......................................................................................................................0-000-01 FAA Approval....................................................................................................................... 0-000-01A CTA Approval ...................................................................................................................... 0-000-01B CAA Approval ...................................................................................................................... 0-000-01C List of sections ........................................................................................................................0-000-05 Table of contents ....................................................................................................................0-000-10

GENERAL INFORMATION Organization of the manual .....................................................................................................0-050-05 Definition of note, caution and warning ...................................................................................0-050-10 Definition of symbols...............................................................................................................0-050-15 REVISIONSDASSAULT AVIATION Proprietary Data

List of AFM revisions...............................................................................................................0-100-05 Reference cross table between Revision 12 pages and Revision 13 sub-sub-sections...........0-100-10 EFFECTIVE SUB-SUB-SECTIONS Preamble to the list of effective sub-sub-sections ...................................................................0-200-05 List of effective sub-sub-sections ............................................................................................0-200-10 FOREIGN CERTIFICATIONS US Certification.................................................................................................................... 0-250-05A Brazilian Certification ........................................................................................................... 0-250-05B UK Certification.................................................................................................................... 0-250-05C Canadian Certification.......................................................................................................... 0-250-05D

SERVICE BULLETINS AND OPTIONS Summary of the service bulletins and modifications ................................................................0-300-05


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GENERALINTRODUCTION Table of contents






GENERALGENERAL INFORMATION Organization of the manual

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ORGANIZATION OF THE MANUALThis Manual is divided into sections, sub-sections and sub-sub-sections. Each sub-sub-section is composed of an even number of pages. Annexes introduce special operations of the airplane, and are considered as separated sections and possibly with sub-section numbers. Supplements introduce optional equipment, and are considered as independent manuals, and can have sections, sub-sections and sub-sub-sections, specifically when this supplement must be incorporated in basic AFM as a variant of the basic airplane. Numbering of sub-sections and sub-sub-sections is not continuous and numbers are reserved for future use. Sections, sub-sections and sub-sub-sections may include variants. The manual of a specific airplane must only comprise sections, sub-sections and sub-sub-sections which are applicable to it, referring to the list of effective sub-sub-sections. The constitution of the Manuals of new airplanes is ensured by the manufacturer upon airplane delivery. After delivery of the airplane, updating following a revision or incorporation or deletion of an option or service bulletin will be ensured by the operator. Modifications of texts, diagrams or drawings (correction, insertion, withdrawal or skipping of texts) are indicated by a vertical line in the left hand margin opposite to the part modified.



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GENERALGENERAL INFORMATION Organization of the manual






GENERALGENERAL INFORMATION Definition of note, caution and warning

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DEFINITION OF NOTE, CAUTION AND WARNINGNOTE Used with respect to matters not directly related to safety but which are particularly unusual or particularly important.

CAUTION Used with respect to safety matters of a secondary order or not immediately imminent.

WARNING USED WITH RESPECT TO SAFETY MATTERS OF A PRIMARY ORDER OR IMMEDIATELY IMMINENT.DASSAULT AVIATION Proprietary Data


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GENERALGENERAL INFORMATION Definition of note, caution and warning






GENERALGENERAL INFORMATION Definition of symbols

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DEFINITION OF SYMBOLSFollowing symbols are used to identify pushbuttons, lights and messages: - Red lighted pushbuttons ........................................................................................................... FIRE - Green lighted pushbuttons ......................................................................................................... APU - Unlighted pushbuttons ................................................................................................................. OIL - Status lights .............................................................................................................................. ISOL - Annunciations ........................................................................ AP 1, TRANS, IGN, SLATS, DEPLOY

- Red MASTER WARNING light ......................................................................................... MASTER - Amber MASTER CAUTION light....................................................................................... MASTER - Red lights on warning panel...................................................................................................... OIL 1 - Amber lights on warning panel................................................................................................ GEN 1 - GEN .. ".." symbol is used to identify one of the following number : 1, 2 or 3. - - Checked is used to signify the check of status or control. - Actions:1st level of action: 2nd level of action: 3rd level of action: 4th level of action: 5th level of action: 6th level of action:DASSAULT AVIATION Proprietary Data

Xxxxxxxxx Xxxxxxxxx Xxxxxxxxx Xxxxxxxxx Xxxxxxxxx Xxxxxxxxx


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GENERALGENERAL INFORMATION Definition of symbols


- Conditions or events: If Xxxxxxxxx: Xxxxxxxxx If Xxxxxxxxx: Xxxxxxxxx If Xxxxxxxxx: Xxxxxxxxx If Xxxxxxxxx: Xxxxxxxxx If Xxxxxxxxx: Xxxxxxxxx

1st level of condition or event:

2nd level of condition or event:

3rd level of condition or event:

4th level of condition or event:

5th level of condition or event:


- Black symbol " " is used to identify a phase of flight. - Green arrow is used to indicate the referenced procedure has to be followed. - Green symbol or green line are used to inform that the AFM procedure is completed. Crew remains responsible and has to take into account operational consequences if necessary.



GENERALREVISIONS List of AFM revisions

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LIST OF AFM REVISIONS

Revision and Date Original 30-Nov-1994. Revision 1 02-Feb-1995.

Title and Approval reference

Pages changes Added First issue of all pages Revised Cancelled

US certification

0-000A-1, 2; 0-015A-1,2; 1-120-1A, 2A; 1-150-3A, 4A; 4-145-1A, 2A; 5-650-1, 2.

0-003-1, 2; 0-010-1; 0-010-7; 0-010-10 0-020-1; 0-025-1.

Revision 2 28-Apr-1995.

.

31923, 4.

00031, 2; 00101, 2, 3, 4, 5, 6, 7, 8, 9, 10; 0015A1; 00201; 11101,2; 11201, 2; 20501; 21302; 21312; 21402, 4; 31001, 2; 31021; 31041, 2; 31061; 31151; 31411; 31432; 31511, 2; 31921, 2; 33301; 41053; 41101, 2, 3; 41112, 3, 4; 41151; 41161; 41181, 2; 41201, 2, 3, 4, 5, 6; 41402; 41451; 41951; 53004, 5.

00151, 2; 11201A, 2A; 41451A, 2A.DASSAULT AVIATION Proprietary Data

Revision 3 22-Jun-1995.

CAT. II certification

00031, 2; 00101, 10; 00201; 12301, 2; List of supplements 1.

00253, 4; List of annexes 1, 2 ; A11, 2, 3, 4, 5, 6, 7, 8, 9,10.


0-100-05PAGE 2 / 10 Issue 1Revision and Date Revision 4 23-Aug-1995. Title and Approval reference Flaps + Slats 10 operation. Integration of T.C. 15 and 17. Minor corrections.

GENERALREVISIONS List of AFM revisionsPages changes Added 001011, 12; 11001A, 2A; 31161, 2; 50005, 6; 5-450-1A, 2A; 5-460-1A, 2A; 55001, 2, 1A, 2A, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14 ; 55101, 2, 1A, 2A, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14; 55201, 2, 3, 4, 5, 6, 7, 8; 56101, 2; 56201, 2, 3, 4. Annex: A111, 12. Annex: A19. Revised Title page; 00031, 2; 00101, 3, 4, 5, 6, 7, 8, 9, 10; 00202; 00252; 10001; 11002; 11501; 12001; 30001, 2, 3, 4; 40001, 2; 41101; 41112; 41151, 2; 41201, 4, 7; 4-1551; 50001, 2, 3, 4; 51501, 2, 3, 4; 52001, 2.


Cancelled 56003, 4, 5, 6.

Revision 5DASSAULT AVIATION Proprietary Data

07-Mar-1996

Integration of TC 1 (Airspeed and Mach limitations). Integration of TC 14 (Thrust reversers). Annex 2: performance APU door open. MUH 70 ft (see annex 1). Minor corrections.

12311, 2; 12351, 2; 33501, 2, 1A, 2A; 42001, 2. Annex: A21, 2, 3, 4, 5, 6.

Title page; 00031, 2; 00101, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12; 0015A1; 00202; 00251, 2; 00301; 10002; 11201; 11301; 11502; 12301, 2; 30004; 31511; 32101; 32401; 40002; 41053, 4; 41111, 2; 41201, 2, 3, 6, 7; 41451; 4-1551. List of annexes1. Annex: A13, 4, 7. Supplement 12, 4, 5, 6; Supplement 21, 2, 3, 4, 5; Supplement 31, 2, 3, 4, 5; Supplement 41, 2, 3, 4; Supplement 52, 4, 10; Supplement 61, 2, 3, 4, 5.

Supplement 4 pages 5 and 6.


F2000 Airplane Flight ManualRevision and Date Revision 6 22-Jan-1998. Title and Approval reference

GENERALREVISIONS List of AFM revisionsPages changes Added 0000C1, 2; 001013, 14; 0015C1, 2 ; 00203, 4; 11203, 4; 1160B1, 2; 11901A, 2A; 1231A1, 2; 1231B1, 2; 1231C1, 2; 1235A1, 2; 1235B1, 2 ; 12381, 2; 1238A1, 2; 3143A1, 2; 4118A1, 2; 4200A1, 2; 545015, 16; 546015, 16; 550015, 16; 551015, 16. Annex: A31, 2, 3, 4. Revised 00001; 0000A1; 00021; 00031, 2; 00052; 00101, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12; 0015A1; 00251, 2, 3, 4, 5, 6, 7, 8; 00301; 10001, 2; 11101, 2; 11201, 2; 11301; 11601; 12201; 12311, 2; 12351, 2; 20001; 21111; 21302; 21311, 2; 21401, 2, 4; 21501, 2; 21511; 31001, 2; 31021; 40001, 2; 41111, 4; 41151, 2, 3; 41182; 41201, 2, 3, 4, 5, 6, 7, 8; 42001; 50003, 4, 5; 50501, 7; 51502; 52001, 2; 52503; 53502; 54002, 3, 6, 7; 54501, 1A, 12, 13, 14; 54601, 1A, 12, 13, 14; 54703, 4, 5, 6, 7; 55001, 1A, 12, 13, 14; 55101, 1A, 12,13, 14; 55203, 4, 5, 6, 7; 56001, 2; 56101, 2; 56201, 2; 56501. List of annexes1. Annex: A1 10, 11; Annex: A21, 2, 3, 4, 5, 6.

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Cancelled 21405, 6; 41951, 2.

Integration of T.C. No 3, 10, 21, 22, 23, 24, 25, 26, 27, 28, 32, 33, 35, 36, 37, 38. Integration of Annex 3 (T.C. No 42). Performance: Take-off and Landing capability between 10,000 ft and 14,000 ft. Cancellation of Engine failure during take-off procedure in Section 2 (see Section 3). Minor corrections. Approved by DGAC J. ANDRE dated January 22, 1998



0-100-05PAGE 4 / 10 Issue 1Revision and Date Revision 7 12-Oct-1998 Title and Approval reference Issue of Annex 6 : Supplementary performance information for operation on runways contaminated by standing water, slush, loose snow, compacted snow or ice. Integration of temporary change No 50 (Annex 5): Operations with braking system No 2 inoperative. Cancellation of specific US pages 11901A and 2A. Approved by DGAC S. MORALES dated October 12, 1998

GENERALREVISIONS List of AFM revisionsPages changes Added Annex 5 pages 1, 2, 3, 4, 5, 6; Annex 6 pages 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24, 25, 26, 27, 28. Revised Title page; 00031, 2; 00101, 9, 13, 14; 0015A1; 00204; 00259, 10, 11, 12; 00301; 11901; 50001; 50504; List of annexes page 1.


Cancelled 11901A, 2A. Temporary change No 50: List of annexes pages 1, 2; Annex 5 pages 1, 2, 3, 4.



F2000 Airplane Flight ManualRevision and Date Revision 8 24-Dec-1998 Title and Approval reference Integration of Temporary Changes No 20, 29, 31, 41, 45, 46, 47, 48, 52, 54, 59, 61, 62, 63, 64, 68, 69, 70, 71, 75, 77, 78, 79, 80, 81, 82, 83, 84, 86, 87 and 88. Integration of modification M298 (MASTER WARNING system). Integration of modification M1086 (GALLEY MASTER switch). Integration of modification M1141 (EGPWS) in Annex 3. Integration of modification M1614 (MASTER FMS switches). Cancellation of specific US pages 11503A, 4A and Temporary Change No 20 (VFE limitations). Colored reissue of section 5, subsection 400. Miscellaneous corrections. Approved by DGAC

GENERALREVISIONS List of AFM revisionsPages changes Added 001015, 16; 00205, 6; 11601B, 2B; 11603, 4 ; 1231D1, 2; 1235B3, 4; 1235C1, 2, 3, 4; 1235D1, 2, 3, 4; 1238A3, 4; 1238B1, 2, 3, 4; 1238C1, 2, 3, 4; 12401, 2; 2130A1, 2; 3130A1, 2; 32103, 4; 41101A, 2A; 4155A1, 2; 41951, 2; 4200C1, 2; 4200D1, 2, 3, 4; 42101, 2; 4210A1, 2; 4210B1, 2; 42151, 2; Annex 3 pages 1A, 2A. Revised Title page; 00031, 2; 00052, 4; 00101 thru 14; 0015A1; 0015C1; 00251 thru 16; 00301, 2; 10001, 2; 11001A, 2A, 3; 11102; 11601, 2; 12201; 12351, 2; 1235A1, 2; 1235B1, 2; 12381, 2; 1238A1, 2; 21011; 21121; 21131; 21301, 2; 21311; 21403; 30001, 3, 4; 31021; 31051; 31061, 2; 31101; 31151; 31161; 31301, 2; 31311, 3; 31321; 31401; 31411, 2; 31421; 31431, 2; 3143A1, 2; 31441; 31451; 31511, 2; 31601, 2; 31611, 2; 31701; 31711, 3; 31801, 4, 5; 31901, 2; 31911; 31921, 3; 32001, 2; 32101, 2; 32151; 32301, 2; 32401; 33401; 33501, 1A, 2A; 40002; 41102, 4; 41111, 2, 3, 4; 41161; 41181, 2; 4118A1, 2; 41201, 2, 3, 7, 8; 41402; 42001; 4200A1, 2; 54001, 2, 3, 4, 5, 6, 7, 8; 55001, 1A; 55101, 1A.

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Cancelled 11503A, 4A; 1160B1, 2.

S. MORALES dated December 24, 1998



0-100-05PAGE 6 / 10 Issue 1Revision and Date Revision 9 17-OCT-2000. Title and Approval reference Integration of Temporary Changes No 34, 44, 74, 89, 90, 93, 95, 96, 98, 99, 100, 101, 102, 103, 107. Integration of modification M1578 (MEGGITT secondary flight display system). Cancellation of temporary change No 65. Miscellaneous corrections.

GENERALREVISIONS List of AFM revisionsPages changes Added 1120A1, 2, 3, 4; 11501A, 2A; 1230A1, 2; 21313, 4; 31321A, 2A; 3160A1, 2; 33203A, 4A; 41183, 4; 4118A3, 4; 53003A, 4A, 5A, 6A; Approved by DGAC S. MORALES dated October 17, 2000 Supplements 21, 21A, 21B, 21C, 21D. Supplements 22, 22A, 22B, 22C, 22D, 22E. Revised Title page; 00011; 00031, 2; 00101 thru 16; 0015A1; 0015C1; 00206; 00251 thru 20; 00301, 2; 10001, 2; 10502; 11201, 2, 3; 11301; 11504; 12302; 21001; 21101; 21111; 21131; 21301, 2; 2130A1, 2; 21311, 2; 21401, 2, 3, 4; 21501; 21511; 30003; 31101; 31151; 31161; 31311, 2; 31411; 31421; 31431; 3143A1; 31501; 31512; 31601, 2; 31611; 31701; 31713; 32002; 32102; 33001, 2; 33201, 2; 40001, 2; 41001; 41051, 2, 3, 4; 41101, 2; 41101A, 2A; 41111, 2, 4; 41152; 41182; 4118A2; 41201, 3, 5, 8; 41401; 41901, 2; 53003; Annex 3 page 2; Annex 6 page 19. List of supplements pages 1 thru 8; Supplement 3 pages 1, 2; Supplement 12 pages 1, 2; Supplement 15 pages 1, 2; Supplement 16 pages 1, 2.


Cancelled 12311, 2; 1231A1, 2; 1231B1, 2; 1231C1, 2; 1231D1, 2; 12351, 2; 1235A1, 2; 1235B1, 2, 3, 4; 1235C1, 2, 3, 4; 1235D1, 2, 3, 4; 12381, 2; 1238A1, 2, 3, 4; 1238B1, 2, 3, 4; 1238C1, 2, 3, 4; 12401, 2; 41951, 2; 42001, 2; 4200A1, 2; 4200C1, 2; 4200D1, 2, 3, 4; 42101, 2; 4210A1, 2; 4210B1, 2; 42151, 2.


Supplements 23, 23A, 23B, 23C. Supplements 24, 24A, 24B.


F2000 Airplane Flight ManualRevision and Date Revision 10 15-Feb-2008. Title and Approval reference Integration of supplement No 14 (Brazilian registered A/C) in the basic Manual. Issuance of annex No 3A. Issuance of temporary change No 130. Integration of temporary changes No 105, 108, 109, 111, 112, 113, 116, 117, 118, 119, 121, 123, 124, 125, 126, 127 and 129. Miscellaneous corrections. Approved by EASA under EASA approval reference A.A.01357 on February 15, 2008

GENERALREVISIONS List of AFM revisionsPages changes Added 00033, 4; 001017, 18, 19, 20; 00207, 8; 00303, 4. 11003A, 4A; 11603A, 4A; 13001, 2. 31413, 4; 3340A1, 2; 3350A1, 2. 41055, 6; 41209, 10, 11, 12. 50001A, 2A; 56103, 4. Annex 3A : p. 1, 2, 3, 4. Annex 7 : p. 1, 2, 3, 4, 5, 6, 7, 8. Revised Renumbered pages: 0000B1, 2; 0015B1, 2. 50005A, 6A; 5590A1, 2; 5630A1, 2, 3, 4, 5, 6, 7, 8. Revised pages: Cover page; 00011; 00021; 00031, 2; 00052, 3, 4; 00101, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16; 0015A1; 0015C1; 00206; 00251, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24, 25, 26; 00301, 2. 10001, 2; 11101, 2; 11202; 11501, 1A, 4; 11601, 2, 3, 4; 12002; 12301; 1230A1, 2. 21001; 21011; 21021; 21111, 3; 21121, 2; 21131; 21301, 2; 2130A1, 2; 21312, 3; 21401, 2, 3, 4; 21501, 2; 21511; 21521. 30001, 2, 3, 4; 31001; 31011; 31021; 31041, 2; 31061, 2; 31101; 31151, 2; 31311, 2, 3; 31402; 31411, 2; 31421; 31432; 31441; 31451; 31501, 2; 31511; 31601; 3160A1, 2; 31701; 31711, 2, 3; 31902; 31911; 31922, 3; 32001; 32151, 2; 32301; 32401; 32801; 33202; 33402; 33501.

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Cancelled 11601B, 2B. 31161, 2; 3143A1, 2; 33301, 2; 33501A, 2A. 4118A1, 2, 3, 4; 4155A1, 2. 56201, 2, 3, 4. Annex 1: p. 11, 12. Annex 3: p. 1A, 2A. Supplement 14: p. 1, 2; 31061A, 2A; 31501A, 2A; 32101A, 2A; 33501B, 2B; 50505A, 6A (the other pages are renumbered).



0-100-05PAGE 8 / 10 Issue 1Revision and Date Title and Approval reference

GENERALREVISIONS List of AFM revisionsPages changes Added Revised 40001, 2; 40501; 41001; 41053, 4; 41101, 2, 1A, 2A, 3, 4; 41111, 2, 3, 4; 41151, 2, 3; 41181, 2, 3; 41201, 2, 3, 4, 5, 6, 7, 8; 41401, 2; 41451; 41551, 2; 41901. 50002, 6; 50505, 7; 51501, 2, 4; 56001, 2; 56101, 2. List of annexes: p. 1. Annex 1: p. 9, 10. Annex 3: p. 4.


Cancelled


Annex 5: p. 2, 3. Annex 6: p. 10. List of supplements : p. 1/8, 2/8, 3/8, 4/8, 5/8, 6/8, 7/8, 8/8.


F2000 Airplane Flight ManualRevision and Date Revision 11 12-Dec-2008. Title and Approval reference Integration of temporary changes No 122, 130, 131, 132, 133, 135, 136, 137, 138, 139, 140, 144, 145, 146, 147, 148, 150 and 152.

GENERALREVISIONS List of AFM revisionsPages changes Added 0015D1, 2; 00209, 10; 002527, 28. 11605, 6, 5A, 6A, 7, 8; 12501, 2. 21313A, 4A. Revised Cover page; 00021; 00031, 2, 3, 4; 00101, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18; 00251, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24, 25, 26; 00301, 2, 3, 4. 10001, 2 ; 11201; 1120A1; 11601, 2, 3, 4; 12201; 12301, 2; 1230A1, 2. 20001; 20501; 21102; 21313; 21401, 2, 3, 4; 21501; 21511; 21521. 30002; 30501; 31611, 2; 33002. 40501 ; 41451. 5630A1, 2, 3, 4, 5, 6, 7, 8; 56501, 2 ; 5650A1, 2. Annex 3: p. 1. Annex 6: p. 3.

0-100-05PAGE 9 / 10 Issue 1

Cancelled 001019, 20. 11603A, 4A. 31321A, 2A.

For information: Temporary Change No 91 becomes Supplement No 34. Approved by EASA reference M3209 on December 12, 2008 under the Authority of EASA DOA 21J.051.

30003A, 4A; 3100A1, 2; 3132A1, 2; 31411A, 2A; 31613, 4; 3191A1, 2. 41201A, 2A, 3A, 4A; 4140A1, 2, 3, 4. 50005B, 6B.



0-100-05PAGE 10 / 10 Issue 1Revision and Date Revision 12 24-Jul-2009. Title and Approval reference Integration of Temporary Changes No 141, 151, 153, 155, 157, 158, 159 and 160. For information : Temporary Changes No 141, 151, 155, 157, 158, 159 and 160 are approved, but not issued and integrated by revision No 12. EASA reference DGTDTC 338959 on July 24, 2009 under the Authority of EASA DOA 21J.051.

GENERALREVISIONS List of AFM revisionsPages changes Added 11201A, 2A; 1120A1A, 2A. 41471, 2. 55901, 2; 56301, 2, 3, 4, 5, 6, 7, 8. Revised Cover page; 00031, 2, 3, 4; 00101, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18; 0015B1; 0015D1; 002010; 002523, 24, 25, 26, 27, 28; 00304. 21101, 2; 2111 ; 21121; 21211. 30001; 31151, 2; 32102; 32201; 3350A2. 40002. 50006; 56501, 2; 5650A1, 2.


Cancelled 50005A, 6A; 50005B, 6B; 5590A1, 2; 5630A1, 2, 3, 4, 5, 6, 7, 8. Annex 7 : p. 7, 8.


Annex 6: p. 4. Annex 7: p. 2, 3, 4. Revision 13 12-Jul-2010. For information:Temporary Change N 161 is approved, but not issued and integrated by revision N 13. Approved under DOA EASA.21.J.051 authority under change reference M3346. New AFM layout. Issue 1 of all sub-sub-sections. Refer to 0-100-10 for a reference cross table between revision 12 pages and revision 13 sub-sub-sections.



GENERALREVISIONS Reference cross table between Revision 12 pages and Revision 13 sub-sub-sections

0-100-10PAGE 1 / 14 Issue 1

CROSS REFERENCE TABLE BETWEEN REVISION 12 PAGES AND REVISION 13 SUBSUB-SECTIONSRevision 12 Pages SECTION 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 000 1, 2 000A 1, 2 000B 1, 2 000C 1, 2 001 1, 2 002 1, 2 003 1 to 4 005 1 005 2 005 3 005 4 010 1 to 18 015A 1, 2 015B 1, 2 015C 1, 2 015D 1, 2 020 1 to 10 025 1 to 28 030 1 to 4 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 000 01 p1, 2 Revision 13 Sub-sub-sections Issue 1

000 01A p1, 2 000 01B p1, 2 000 01C p1, 2 000 05 000 10 200 10 050 05 050 10 050 15 200 05 200 10 p1, 2 p1, 2 p1 p1 p1 p1, 2 p1 p1 to 8DASSAULT AVIATION Proprietary Data

250 05A p1, 2 250 05B p1, 2 250 05C p1, 2 250 05D p1, 2 100 05 300 05 p1 to 10 p1 to 4

Canceled


0-100-10PAGE 2 / 14 Issue 1



Revision 12 Pages SECTION 1 1 1 1 1 1 000 1, 2 050 1, 2 100 1, 2 100 1A, 2A 100 3, 4

Revision 13 Sub-sub-sections Issue 1

1 1 1 1 and and and and and and 1 1 1 1 1 1 1 1

000 01 000 05 050 05 1 1 1 1 1 1 1 1 050 050 050 050 050 050 050 050

p1, 2 p1, 2 p1, 2 05 05A 05B 10 05 05A 05B 10A p1, 2 p1, 2 p3, 4 p3, 4 p3, 4 p3, 4 p1 p3, 4 p3, 4 p3, 4 p1

050 05A p1, 2

1DASSAULT AVIATION Proprietary Data

100 3A, 4A 110 1, 2 120 1, 2, 1A, 2A 120 3, 4 120A 1, 2, 1A, 2A 120A 3, 4 130 1, 2 150 1, 2 150 1A, 2A 150 3, 4 160 1 to 4 160 5, 6 160 5A, 6A 160 7, 8 190 1, 2 200 1, 2 220 1, 2

1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1

100 05 100 10 100 10

100 10A p1, 2 100 10A p3, 4 100 15 150 05 p1, 2 p1,2

150 05A p1,2 150 05 p2, 3 150 05A p2, 3 p1 to 5 p3, 4 p3, 4 p5, 6 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2

1 and 1 1 1 1

300 05 300 05 300 05

1 and 1 1 1 and 1 and 1 and 1 1

300 05 150 15 p1, 2 05 10 20 25 p1, 2 200 200 200 200

150 20

200 30




0-100-10PAGE 3 / 14 Issue 1

Revision 12 Pages

Revision 13 Sub-sub-sections Issue 1 and and and and and and and and and and 1 1 1 1 1 1 1 1 1 1 1 1 1 200 250 250 250 250 250 200 250 250 250 250 250 35 05 05A 10 15 20 35 05 05A 10A 15 20 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2

1

230 1, 2

1

230A 1, 2

1 1

250 1, 2 300 1, 2

350 05

1 and 1

200 15 200 40



0-100-10PAGE 4 / 14 Issue 1



Revision 12 Pages SECTION 2 2 2 2 2 2 2 2 2 2DASSAULT AVIATION Proprietary Data


000 1, 2 050 1, 2 100 1, 2 101 1, 2 102 1, 2 110 1, 2 111 1 to 4 112 1, 2 113 1, 2 120 1, 2 121 1, 2 130 1, 2 130A 1, 2 131 1 to 4 131 3A, 4A 140 1, 2 140 3, 4 150 1, 2 151 1, 2 152 1, 2

2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2

000 01 000 05 050 05 050 10 050 15 050 20 050 25 050 30 050 35 100 05 150 05 200 05 200 10 250 05 250 10 300 05 300 10 300 15

p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1 to 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2

2 2 2 2 2 2 2 2 2 2 2

200 05A p1, 2 200 10A p1, 2




0-100-10PAGE 5 / 14 Issue 1

Revision 12 Pages SECTION 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 000 1 to 4 000 3A, 4A 050 1, 2 100 1, 2 100A 1, 2 101 1, 2 102 1, 2 103 1, 2 104 1, 2 105 1, 2 106 1 to 4 110 1,2 115 1, 2 130 1, 2 130A 1, 2 131 1, 2 131 3, 4 132 1, 2 132A 1, 2 140 1 140 2 141 1 141 2 141 1A 141 2A 141 3, 4 142 1, 2 143 1, 2 144 1, 2 145 1, 2


3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3

000 01 000 01 000 05 100 05 100 10 100 25 100 25 100 25 100 25 100 20 100 30 100 40 120 05 120 05 120 15 120 120 120 120

p1 to 4 p2 to 4 p1, 2 p1, 2 p1, 2 p1, 2 p2, 3 p3 p1 to 4 p1, 2 p1, 2 p1 and 4 p2, 3 p1, 2 10 15 10 15A p1 p1 p1 p1, 2 p1, 2 p1, 2 p1 p2 to 4 p1, 2 p1, 2 DTM537 EASA APPROVED p1, 2 p1 p1, 2 p1DASSAULT AVIATION Proprietary Data

100 05A p1, 2

p2

120 05A p1 and 4

3 and 3 3 and 3 3 3 3 3 3 3 3 3 3 3 3

130 05 130 15 130 05 130 10 130 05 130 15 130 20 130 20 130 25 130 30

130 10A p1, 2

0-100-10PAGE 6 / 14 Issue 1



Revision 12 Pages 3 3 3 3 3 3 3 3 3 3 3 3 3DASSAULT AVIATION Proprietary Data

Revision 13 Sub-sub-sections Issue 1 3 3 3 3 3 3 3 3 3 140 05 140 10 140 15 150 05 150 15 160 05 160 10 160 10 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p3, 4 p1, 2 p1, 2 p2

150 1, 2 151 1, 2 152 1, 2 160 1, 2 160A 1, 2 161 1 to 4 170 1 170 2 171 1 to 4 180 1 to 3 180 4 to 6 190 1, 2 191 1, 2 191A 1, 2 192 1 to 4 200 1 200 2 210 1, 2 210 3, 4 215 1, 2 220 1, 2 230 1 230 2 240 1, 2 250 1, 2 280 1, 2 300 1, 2 320 1 320 2 320 3 320 3A

150 05A p1, 2

3 and 3 3 3

170 05 170 10 p1, 2 p1 05 10 05 10A p1, 2

170 10 190 05 190 190 190 190

3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3

3 and 3 3 and 3 3 3 and 3 3 3 and 3 3 3 3

p1 p1, 2 p1 p1, 2 p1, 2 p1 p1, 2 p1

190 15

200 10 200 15 p1, 2 210 10 210 05 p1, 2 p1, 2 p1, 2 05 10 10 05 p1, 2 p1, 2 p1, 2 p1, 2 p1

200 25

210 05 220 05 230 05 240 240 240 240

3 and 3 3 and 3 3 3 3 3 3

p1 p1 p1 p1

250 05 260 05 270 05 280 05 290 05

3 and 3 3 3

290 20 290 25 p1, 2

p1, 2 p2

290 25

290 25A p1, 2




0-100-10PAGE 7 / 14 Issue 1

Revision 12 Pages 3 3 3 3 3 3 3 320 4 320 4A 321 1, 2 340 1, 2 340A 1, 2 350 1, 2 350A 1, 2

Revision 13 Sub-sub-sections Issue 1 3 and 3 3 and 3 3 3 3 3 3 290 290 290 290 25 05 25A 05 p1, 2 p1, 2 p1, 2 p1 p2 p1 p2

290 10 290 15 110 05

290 15A p1, 2 110 05A p1, 2



0-100-10PAGE 8 / 14 Issue 1



Revision 12 Pages SECTION 4 4 4 4 4 4 4 4 4 4DASSAULT AVIATION Proprietary Data


000 1, 2 050 1, 2 100 1, 2 105 1 to 6 110 1, 2 110 1A, 2A 110 3, 4 111 1 to 4 115 1 to 4 116 1, 2 118 1 to 4 120 1, 2 120 1A, 2A 120 3 120 3A 120 4 120 4A 120 5 120 6 120 7 120 8 to 12 140 1, 2 140A 1 to 4 145 1, 2 147 1, 2 150 1, 2 150 3

4 4 4 4 4 4

000 01 000 05 050 05 050 05 100 05

p1, 2 p1, 2 p1 p2 to 4 p1 to 4

100 05A p1 to 4 100 05 p2, 3 100 05A p2, 3 p1 to 4 p1, 2 p3 p4 to 6 p1, 2 p1 10 15 10A 15 p1 p1 p1 p1 p2 p1 p2 p1

4 and 4 4 4 4 4 4 4 4 4

100 10 100 15 100 15 100 15 150 05 150 10 150 150 150 150

4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4

150 05A p1, 2 150 10A p1

4 and 4 4 and 4 4 4

150 15 150 20

4 and 4 4 4 4 4 4

150 20 150 25 p1, 2 p1, 2

150 30 200 05 200 05 200 10 200 20

p1 to 4 p1, 2 p1, 2 p1, 2 p1

4 and 4 4

250 10 250 05 p1

250 05




0-100-10PAGE 9 / 14 Issue 1

Revision 12 Pages 4 4 4 4 155 1 155 2 170 1, 2 190 1, 2

Revision 13 Sub-sub-sections Issue 1 4 and 4 4 4 4 250 10 250 05 p2 p1, 2 p1 p2 p1

250 15 200 15 250 15



0-100-10PAGE 10 / 14 Issue 1



Revision 12 Pages SECTION 5 5 5 5 5 5 5 5 5DASSAULT AVIATION Proprietary Data


000 1, 2 000 1A, 2A 000 3 to 6 050 1, 2 050 3 050 4 050 5, 6 050 7, 8 100 1, 2 150 1 150 2 to 4 200 1, 2 200 3, 4 250 1 250 2 250 3 250 4 250 5 250 6 300 1 300 2 300 3, 4 300 3A, 4A 300 5, 6 300 5A, 6A 350 1 350 2 400 1 to 3 400 4

5 5 5 5 5

000 01 000 01 000 01 050 05 050 10

p1, 2 p1, 2 p2 to 4 p1, 2 p1 p2 p1 p3 p1, 2

5 and 5 5 5 and 5 5 5

050 10 050 15 p1, 2 050 15 050 20 p1, 2 p1

050 15

5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5

100 05 150 05

5 and 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5

150 10 150 15 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p3, 4 p1, 2 p1, 2

p1, 2 p1, 2

200 05 200 10 250 05 250 10 250 15 250 20 250 25 250 30 300 05 300 10 300 15 300 15 350 05 350 10 400 05 400 10

300 15A p1, 2 300 15A p3, 4

p1 to 4 p2


F2000 Airplane Flight Manual5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 400 5 to 7 400 8 450 1 450 2 450 1A 450 2A 450 3 to 13 450 14, 15 450 16 460 1 460 2 460 1A 460 2A 460 3 to 13 460 14, 15 460 16 470 1, 2 470 3, 4 470 5 to 8 500 1 500 2 500 1A 500 2A 500 3 to 13 500 14, 15 500 16 510 1 510 2 510 1A 510 2A 510 3 to 13 510 14, 15 510 16 520 1, 2 520 3, 4 520 5 to 8


0-100-10PAGE 11 / 14 Issue 1

Revision 12 Pages

Revision 13 Sub-sub-sections Issue 1 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 450 05 450 10 500 04 500 05 500 05 500 05 500 10 500 15 500 19 500 20 500 20 500 20 500 25 500 30 500 35 500 40 500 45 550 04 550 05 550 05 550 05 550 10 550 15 550 19 550 20 550 20 550 20 550 25 550 30 550 35 550 40 550 45 p1 to 4 p2 p1, 2 p1 p1 p2 to 12 p2, 3 p1 p1, 2 p1 p1 p2 to 12 p1, 2 p1 p1, 2 p1 to 4 p1, 2 p1 p1 p2 to 12 p2, 3 p1 p1, 2 p1 p1 p2 to 12 p2, 3 p1 p1 p1, 2 p1 to 4 DTM537 EASA APPROVEDDASSAULT AVIATION Proprietary Data

500 04A p1, 2

500 19A p1, 2

p2, 3

550 04A p1, 2

550 19A p1, 2

0-100-10PAGE 12 / 14 Issue 1



Revision 12 Pages 5 5 5 5 5 5 5 5 5 5 5 550 1 550 2 590 1, 2 600 1 600 2 610 1 610 2 to 4 630 1 to 3 630 4 to 8 650 1, 2 650A 1, 2

Revision 13 Sub-sub-sections Issue 1 5 5 5 5 5 5 5 5 5 5 5 600 10 600 05 700 04 700 10 700 15 700 20 700 25 800 04 800 04 900 05 p1 p1 p1, 2 p1 p1 p1 p1, 2 p1, 2 p2 to 6 p1, 2

900 05A p1, 2





0-100-10PAGE 13 / 14 Issue 1

Revision 12 Pages ANNEXES List of annexes 1, 2 A1 A2 A3 A5 A6 A6 A6 A6 A6 A6 A6 A6 A6 A6 A7 A7 A7 A7 A7 1 to 10 1 to 6 1 to 4 1 to 4 1 to 6 1, 2 3 4 5 to 10 11 to 13 14 to 17 18 to 20 21 to 25 26 27, 28 1, 2 3 4 5 6


List of annexes p1, 2 A1 A2 A3 A5 A6 A6 A6 p1 to 6 p1 to 4 p1 to 4 p1 to 4 Part 1 Part 2 Part 3 Part 4 Part 5 Part 6 p1, 2 p1, 2 p1, 2DASSAULT AVIATION Proprietary Data

A3A -

A3A p1 to 4

A6 and A6 and A6 A6 A6 A6 A6 A6 A6

p1, 2 p1, 2 p1, 2 p1, 2 p1 to 6 p1, 2

Part 7 Part 8 Part 9 Part 10 Part 11 Part 12 p1, 2 p1, 2

p1 to 6

A7 and A7 A7 A7 A7 A7

Part 0 Part 1

p1, 2 p1, 2 p1, 2 p1, 2 p1, 2 p1, 2

Part 2 Part 3 Part 4 Part 5


0-100-10PAGE 14 / 14 Issue 1







GENERALEFFECTIVE SUB-SUB-SECTIONS Preamble to the list of effective sub-sub-sections

0-200-05PAGE 1 / 2 Issue 1

PREAMBLE TO THE LIST OF EFFECTIVE SUB-SUB-SECTIONSPAGES IDENTIFICATION The identification of the pages of the Manual consists of the following data printed at the top and the bottom of each page: - Name of the Aircraft, - Title of the document: Airplane Flight Manual, - Page numbering system, - Notation: EASA APPROVED, - Sub-sub-section issue number. PAGE NUMBERING SYSTEM The page numbering system consists of 4 elements: - Number of the section, possibly followed by an alphabetical index corresponding to a variant, - Number of the sub-section, possibly followed by an alphabetical index corresponding to a variant, - Number of the sub-sub-section, possibly followed by an alphabetical index corresponding to a variant, - Number of the page in the sub-sub-section always followed by total number of pages of the current sub-sub-section. AMENDMENT SYSTEM When a page is modified, the whole sub-sub-section is revised and its issue number is incremented. Revised parts are indicated with revision marks. This modified sub-sub-section is published through a new AFM revision. The following table of version of sub-sub-sections list all effective sub-sub-sections and give information about issue and applicability. APPLICABILITY SYSTEM - The applicability of a sub-sub-section is clearly indicated at the bottom: - When a specific content (text, diagram...) is not applicable to the basic airplane due to specific national regulation, specific airplane option or installed Service Bulletin, a variant of the sub-subsection is inserted. - The alphabetical index following the section, sub-section or sub-sub-section number identifies a variant material. The airplane must only include in its Manual the variant section, sub-section or sub-sub-section in accordance with its configuration and applicable regulations.

NOTE Throughout the Manual, a reference to a sub-sub-section, sub-section or section does not indicate whether this sub-sub-section, sub-section or section is a variant.



0-200-05PAGE 2 / 2 Issue 1

GENERALEFFECTIVE SUB-SUB-SECTIONS Preamble to the list of effective sub-sub-sections






GENERALEFFECTIVE SUB-SUB-SECTIONS List of effective sub-sub-sections

0-200-10PAGE 1 / 8 Issue 1

AFM - VERSIONS AND APPLICABILITY OF SUB-SUB-SECTIONSReference 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 000 000 000 000 000 000 000 050 050 050 100 100 200 200 250 250 250 250 300 000 000 000 050 050 050 050 050 100 100 100 100 150 150 150 150 150 200 00 01 01A 01B 01C 05 10 05 10 15 05 10 05 10 05A 05B 05C 05D 05 00 01 05 05 05A 05B 10 10A 05 10 10A 15 05 05A 10 15 20 05 Issue Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 A/C with MEGGITT secondary flight display system (M1578), A/C S/N 70 A/C with M1903 or SB F2000-202 A/C with M57 A/C with M1190 or SB F2000-186 A/C S/N 2 A/C S/N 1DASSAULT AVIATION Proprietary Data

Special applicability

US registered A/C Brazilian registered A/C UK registered A/C

Issue 1


0-200-10PAGE 2 / 8 Issue 1 Reference 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1DASSAULT AVIATION Proprietary Data

GENERALEFFECTIVE SUB-SUB-SECTIONS List of effective sub-sub-sections Issue Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 A/C S/N 70 and subsequent (M1578) A/C with M375 A/C with GPIRS and without M2004, or SB F2000-273 A/C S/N 2 to 68 until compliance with SB F2000-145 A/C with GPIRS and without M2004, or SB F2000-273 Special applicability


200 200 200 200 200 200 200 250 250 250 250 250 250 300 350 000 000 000 050 050 050 050 050 050 050 100 150 200 200 200 200 250 250 300 300 300 000 000 000

10 15 20 25 30 35 40 05 05A 10 10A 15 20 05 05 00 01 05 05 10 15 20 25 30 35 05 05 05 05A 10 10A 05 10 05 10 15 00 01 05

2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 3 3 3


F2000 Airplane Flight ManualReference 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 100 100 100 100 100 100 100 110 110 120 120 120 120 120 130 130 130 130 130 130 130 140 140 140 150 150 150 160 160 170 170 190 190 190 190 200 200 200 210 05 05A 10 20 25 30 40 05 05A 05 05A 10 15 15A 05 10 10A 15 20 25 30 05 10 15 05 05A 15 05 10 05 10 05 10 10A 15 10 15 25 05 Issue Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1

GENERALEFFECTIVE SUB-SUB-SECTIONS List of effective sub-sub-sections Special applicability A/C without M3249 or M2500 or SB F2000-376

0-200-10PAGE 3 / 8 Issue 1

US and Brazilian registered A/C A/C with M375

A/C with M1403 or SB F2000-153

Canadian registered A/C


A/C without M2500 or M3249 or SB F2000-376




GENERALEFFECTIVE SUB-SUB-SECTIONS List of effective sub-sub-sections Issue Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 A/C without M3249 or M2500, or SB F2000-376 A/C without M3249 or M2500 or SB F2000-376 A/C without M3249 or M2500 or SB F2000-376 A/C with M650 A/C with M1600 and M1716 (FMS 6100) A/C with M76, M259 and M189 A/C with M45 or M1168 or M1716 or M1891 A/C with M54, M6B and M254 A/C with M45 or M1168 and M189 Special applicability


210 220 230 240 240 250 260 270 280 290 290 290 290 290 290 290 290 290 290 290 000 000 000 050 100 100 100 100 150 150 150 150 150 150 150 150 200 200 200

10 05 05 05 10 05 05 05 05 05 10 15 15A 15B 15C 15D 15E 20 25 25A 00 01 05 05 05 05A 10 15 05 05A 10 10A 15 20 25 30 05 05A 10

3 3 3 3 3 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4

A/C with MEGGITT secondary flight display system, A/C S/N 70 (M1578)


F2000 Airplane Flight ManualReference 4 4 4 4 4 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 200 200 250 250 250 000 000 050 050 050 050 100 150 150 150 200 200 250 250 250 250 250 250 300 300 300 300 350 350 400 400 450 450 500 500 500 500 500 500 15 20 05 10 15 00 01 05 10 15 20 05 05 10 15 05 10 05 10 15 20 25 30 05 10 15 15A 05 10 05 10 05 10 04 04A 05 10 15 19 Issue Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1

GENERALEFFECTIVE SUB-SUB-SECTIONS List of effective sub-sub-sections Special applicability

0-200-10PAGE 5 / 8 Issue 1

A/C with MEGGITT secondary flight display system, A/C S/N 70 with M1578

A/C with M57




GENERALEFFECTIVE SUB-SUB-SECTIONS List of effective sub-sub-sections Issue Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 A/C with M955 and M1500 or SB F2000-314 A/C S/N > 11 or with SB F2000-64 US registered A/C A/C with M57 A/C with M57 Special applicability A/C with M57


500 500 500 500 500 500 500 550 550 550 550 550 550 550 550 550 550 550 550 550 600 600 700 700 700 700 700 800 800 900 900

19A 20 25 30 35 40 45 04 04A 05 10 15 19 19A 20 25 30 35 40 45 05 10 04 10 15 20 25 04 10 05 05A

5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5

List of annexes Annex 1 Annex 2 Annex 3 Annex 3A Annex 5 Annex 6 Annex 6 Part 1 Part 2

Issue 1 Issue 1


F2000 Airplane Flight ManualReference Annex 6 Annex 6 Annex 6 Annex 6 Annex 6 Annex 6 Annex 6 Annex 6 Annex 6 Annex 6 Annex 7 Annex 7 Annex 7 Annex 7 Annex 7 Annex 7 Part 3 Part 4 Part 5 Part 6 Part 7 Part 8 Part 9 Part 10 Part 11 Part 12 Part 0 Part 1 Part 2 Part 3 Part 4 Part 5 Issue Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1 Issue 1

GENERALEFFECTIVE SUB-SUB-SECTIONS List of effective sub-sub-sections Special applicability

0-200-10PAGE 7 / 8 Issue 1



0-200-10PAGE 8 / 8 Issue 1

GENERALEFFECTIVE SUB-SUB-SECTIONS List of effective sub-sub-sections






GENERALFOREIGN CERTIFICATIONS US Certification

0-250-05APAGE 1 / 2 Issue 1

US CERTIFICATIONSub-sub-sections listed herebelow are applicable only to US registered airplanes: Section 0 0-000-01A, 0-250-05A. Section 3 3-110-05A. Section 5 5-900-05A. Supplements See "List of Dassault Aviation supplements" and "Table of contents" of each supplement. Sub-sub-sections listed herebelow are not applicable to US registered airplanes: Annexes Annexes 3A and 6. Supplements See "List of Dassault Aviation supplements" and "Table of contents" of each supplement.



0-250-05APAGE 2 / 2 Issue 1

GENERALFOREIGN CERTIFICATIONS US Certification






GENERALFOREIGN CERTIFICATIONS Brazilian Certification

0-250-05BPAGE 1 / 2 Issue 1

BRAZILIAN CERTIFICATIONSub-sub-sections listed herebelow are applicable only to BRAZILIAN registered airplanes: Section 0 0-000-01B, 0-250-05B Section 3 3-110-05A Supplements See "List of Dassault Aviation supplements" and "Table of contents" of each supplement. Sub-sub-sections listed herebelow are not applicable to BRAZILIAN registered airplanes: Supplements See "List of Dassault Aviation supplements" and "Table of contents" of each supplement.



0-250-05BPAGE 2 / 2 Issue 1

GENERALFOREIGN CERTIFICATIONS Brazilian Certification






GENERALFOREIGN CERTIFICATIONS UK Certification

0-250-05CPAGE 1 / 2 Issue 1

UK CERTIFICATIONSub-sub-sections listed herebelow are applicable only to UK registered airplanes: Section 0 0-000-01C, 0-250-05C. Supplements See "List of Dassault Aviation supplements" and "Table of contents" of each supplement. Sub-sub-sections listed herebelow are not applicable to UK registered airplanes: Supplements See "List of Dassault Aviation supplements" and "Table of contents" of each supplement.



0-250-05CPAGE 2 / 2 Issue 1

GENERALFOREIGN CERTIFICATIONS UK Certification






GENERALFOREIGN CERTIFICATIONS Canadian Certification

0-250-05DPAGE 1 / 2 Issue 1

CANADIAN CERTIFICATIONSub-sub-sections listed herebelow are applicable only to CANADIAN registered airplanes: Section 0 0-250-05D Section 3 3-130-10A Supplements See "List of Dassault Aviation supplements" and "Table of contents" of each supplement. Sub-sub-sections listed herebelow are not applicable to CANADIAN registered airplanes: Supplements See "List of Dassault Aviation supplements" and "Table of contents" of each supplement.



0-250-05DPAGE 2 / 2 Issue 1

GENERALFOREIGN CERTIFICATIONS Canadian Certification






GENERALSERVICE BULLETINS AND OPTIONS Summary of the service bulletins and modifications

0-300-05PAGE 1 / 2 Issue 1

SUMMARY OF THE SERVICE BULLETINS, OPTIONS AND MODIFICATIONS QUOTED IN THE MANUAL (FOR INFORMATION)

M M3A M34 M48 M57 M200 M298 M375 M613 M650 M694 M760 M912 M955 M972 M1077 M1080 M1086 M1199 M1251 M1378 M1403 M1445 M1500 M1578 M1600 M1614 M1667 M1716 M1758

SB DESCRIPTION SB F2000-19 Thrust reversers SB F2000-108 Installation of a brake heating system. Pressurization : LOW RATE command. Increased maximum take-off weights (MRW 36,700 lb and MTOW 36,500 lb). Second radioaltimeter. MASTER warning system. Electrical pitch variable bellcrank. SB F2000-99 Installation of mach hold option. Glareshield mounted avionic control. Stick shaker installation. Braking and steering system separation of electrical SB F2000-64 grounds providing the ground / flight signal. HONEYWELL GPS. Steep approach landing with E-GPWS. Auxiliary power supply for VHF, ATC, ICS and RTU. Digital battery temperature indicator. SB F2000-63 Static Source Error Correction (SSEC). GALLEY MASTER switch. SB F2000-99 Capability of installation of mach hold option. Reduced Vertical Separation Minimum (RVSM) SB F2000-63 capability. Passenger door - Electrical lifting. No 2 system main hydraulic power improved air SB F2000-153 bleeding of hydraulic pump suction line. SB F2000-145 HONEYWELL HG2001GC03 IRS. Full installation of EGPWS with Steep Approach SB F2000-314 function. MEGGITT secondary flight display system. FMS 6100. Installation of two FMS MASTER switches (HONEYWELL). SB F2000-192 Lead acid main battery. Complete installation of AHS-3000 and wiring for 2 IRS. SB F2000-193 New hydraulic accumulators.



0-300-05PAGE 2 / 2 Issue 1

GENERALSERVICE BULLETINS AND OPTIONS Summary of the service bulletins and modifications


M M1776 M1778 M1903 M1960 M2004 M2061 M2062 M2107 M2144 M2325 M2468 M2500 M2624 M2632DASSAULT AVIATION Proprietary Data

SB

SB F2000-202 SB F2000-273 SB F2000-108 SB F2000-253

SB F2000-327 SB F2000-376 SB F2000-312 SB F2000-312

M2974 M3072SB F2000-285

DESCRIPTION Pilots audio isolation from perturbations coming from options (ISOL pushbutton). Stand-by horizon : battery power supply indicator. Reinstatement of fuel types JET B and JP4. IRS. GPS / IRS hybrid data inhibit. Installation of a brake heating system. Full authority digital electronic control (FADEC). Upgrade FADEC software to version V6.5. Mid cabin partition door. IFE load shedding. 115 / 230 VAC light pushbutton. Air Traffic Control reply inhibit on ground. Wing anti-ice valve - Thrust bearing implementation. Air Traffic Control with Enhanced Surveillance. Air Traffic Control with Enhanced Surveillance. Automatic dependant surveillance-broadcast out in non radar areas (ADS-B out in NRA). Wing fuel tank improvement. Safety collar GPS deactivation.



LIMITATIONSGENERAL

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SECTION 1 LIMITATIONS



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LIMITATIONSGENERAL






LIMITATIONSGENERAL Table of contents

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TABLE OF CONTENTS GENERAL Table of contents ....................................................................................................................1-000-01 Introduction; Year 2000 limitations ..........................................................................................1-000-05 WEIGHTS AND LOADING Weights; Center of gravity limits..............................................................................................1-050-05 Weights; Center of gravity limits (A/C with M57) .................................................................. 1-050-05A Weights; Center of gravity limits (A/C with M1190) .............................................................. 1-050-05B Loading...................................................................................................................................1-050-10 Loading (A/C S/N 1)............................................................................................................. 1-050-10A

POWERPLANT CFE738-1-1B engine ..............................................................................................................1-100-05 Fuel system ............................................................................................................................1-100-10 Fuel system (A/C with M1903) ............................................................................................. 1-100-10A Lubrication system ..................................................................................................................1-100-15

SPEED AND OPERATIONAL LIMITS Airspeed and mach.................................................................................................................1-150-05 Airspeed and mach (A/C S/N 70 (M1578))........................................................................ 1-150-05A Limiting maneuvering flight load factors ..................................................................................1-150-10 Minimum flight crew ................................................................................................................1-150-15 Operational limitations; Temperature and altitude limits ..........................................................1-150-20

SYSTEMS Anti-ice....................................................................................................................................1-200-05 Cabin pressurization ...............................................................................................................1-200-10 Instrument color markings.......................................................................................................1-200-15 Hydraulic.................................................................................................................................1-200-20 Electrical .................................................................................................................................1-200-25 Auxiliary power unit (APU) ......................................................................................................1-200-30 Tires and brakes .....................................................................................................................1-200-35 Towbarless towing ..................................................................................................................1-200-40

AVIONICS Automatic pilot (APS 4000) .....................................................................................................1-250-05 Automatic pilot (APS 4000) (A/C with GPIRS and without M2004)....................................... 1-250-05A IRS (HONEYWELL LASEREF III OR IV) ................................................................................1-250-10



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LIMITATIONSGENERAL Table of contents


IRS (HONEYWELL LASEREF III OR IV) (A/C S/N 2 to 68 until compliance with SB F2000-145) .................................................................................................................... 1-250-10A AHRS (COLLINS CCU65).......................................................................................................1-250-15 HEAD UP GUIDANCE SYSTEM (A/C with GPIRS and without M2004) .................................1-250-20 KINDS OF OPERATION Kinds of operation...................................................................................................................1-300-05 FLIGHT MANAGEMENT AND NAVIGATION SYSTEM Flight Management and Navigation System............................................................................1-350-05




LIMITATIONSGENERAL Introduction; Year 2000 limitations

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INTRODUCTION

THE AIRPLANE MUST BE OPERATED IN COMPLIANCE WITH THE LIMITATIONS PRESENTED IN THIS SECTION



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LIMITATIONSGENERAL Introduction; Year 2000 limitations


YEAR 2000 LIMITATIONSAfter issuance of the following French DGAC Airworthiness directives to take into account consequences of Y2K on airborne systems: - French DGAC Airworthiness Directive 1999-514(AB) - French DGAC Airworthiness Directive 1999-450(B) R1 - French DGAC Airworthiness Directive 1999-472(AB) The following limitations are added: In order to avoid known or possible malfunctions which could affect airworthiness the following actions are rendered mandatory: - The use of OMEGA/VLF navigation mode is prohibited definitively after December 31, 1999. The OMEGA/VLF RPU shall be deactivated (Reference AD 1999-472(AB)). - Systems which are definitively prohibited from December 31, 1999 must be deactivated (Reference AD 1999-472(AB) and AD 1999-450(B) paragraph 3-1 Note 1 and paragraph 3-3). - Without an other authorized source of navigation, it is prohibited to use the navigation system referenced in the following Airworthiness directive (see hereafter), or magnetic variation shall be entered manually, in oceanic and remote areas above north latitude N60 and below south latitude S50 according to the AD, from January 1st, 2000 (Reference AD 1999-514(AB)). - Equipment which are prohibited as a precautionary measure from December 31, 1999: use will be authorized again after January 1st, 2000 and after function check of the involved equipment on ground, engines running as per applicable documentation (Reference AD 1999-450(B) paragraph 3-2).




LIMITATIONSWEIGHTS AND LOADING Weights; Center of gravity limits

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WEIGHTSTRUCTURAL LIMITATIONS Maximum ramp weight......................................................................................36,000 lb (16,329 kg) Maximum take-off weight ..................................................................................35,800 lb (16,238 kg) Maximum landing weight ..................................................................................33,000 lb (14,968 kg) Maximum zero fuel weight ................................................................................28,660 lb (13,000 kg) Minimum flight weight .............................................................. Refer to Center of gravity limits chart.

LIMITATIONS DUE TO PERFORMANCE The Maximum Take-Off Weight (MTOW) and the Maximum Landing Weight (MLW) given as structural limitations may have to be reduced to comply with performance and operating requirements.(see Maximum Allowable Weights, 5-150-10)



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CENTER OF GRAVITY LIMITS


NOTE Landing gear position has no effect on the CG location.


F2000 Airplane Flight ManualCG DATUM


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Datum is 25 % of mean aerodynamic chord (MAC) which coincides with fuselage station (FS) 400.43 in (10,171 mm) (fuselage station + 0 is the forward end of the airplane nose cone). MEAN AERODYNAMIC CHORD - Length: 113.69 in (2,887.7 mm). - Zero % MAC is at FS + 372.01 in (9,449 mm).



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LIMITATIONSWEIGHTS AND LOADING Weights; Center of gravity limits (A/C with M57)

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A/C with M57



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NOTE Landing gear position has no effect on the CG location.A/C with M57




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A/C with M57



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A/C with M57



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NOTE Landing gear position has no effect on the CG location.A/C with M1190 or SB F2000-186




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LIMITATIONSWEIGHTS AND LOADING Loading

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LOADINGFOREWORD The airplane must be loaded in compliance with the center of gravity location limits (See 1-050-05). Information for determination of airplanes weight and balance are included in the Loading Manual DTM541. The weights indicated below must not be exceeded when loading the airplane: TOTAL WEIGHT Baggage compartment LH and RH coat compartment Payload lb 1,600 5,990 kg 725 2,717 DISTRIBUTED LOAD lb/sq.ft kg/m 61.4 300 81.9 400 -

A/C S/N 2



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LIMITATIONSWEIGHTS AND LOADING Loading





A/C S/N 2


LIMITATIONSWEIGHTS AND LOADING Loading (A/C S/N 1)

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LOADINGFOREWORD The airplane must be loaded in compliance with the center of gravity location limits (See 1-050-05). Information for determination of airplanes weight and balance are included in the Loading Manual DTM541. The weights indicated below must not be exceeded when loading the airplane: TOTAL WEIGHT Baggage compartment LH and RH coat compartment Payload lb 1,000 5,990 kg 453 2,717 DISTRIBUTED LOAD lb/sq.ft kg/m 61.4 300 81.9 400 -

A/C S/N 1



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LIMITATIONSWEIGHTS AND LOADING Loading (A/C S/N 1)





A/C S/N 1


LIMITATIONSPOWERPLANT CFE738-1-1B engine

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THRUST RATINGSCFE738-1-1B ENGINE (UNINSTALLED, SEA LEVEL, ISA) - Take-off ............................................................................................................. 5,888 lb (2,620 daN) - Maximum continuous ......................................................................................... 5,613 lb (2,497 daN) CAUTION The take-off thrust rating is time limited to 5 minutes.

THRUST SETTINGSThe engine low pressure rotor speed N1 is used as the thrust setting parameter. The take-off and maximum continuous thrust as defined in AFM section 5-050-20 must be based on the N1 values given in AFM sections 5-400 and 5-450.

ROTOR SPEED LIMITSCONDITION OF USE Maximum / Normal take-off (5 minutes max.) Maximum continuous 100 % N1 = 9,725 RPM 100 % N2 = 26,415 RPM N1 96.7 % 96.7 % N2 106 % 104.9 %

ENGINE VIBRATION LIMITS- N1..................................................................................................................................... 1.0 in./sec. - N2..................................................................................................................................... 1.5 in./sec.



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LIMITATIONSPOWERPLANT CFE738-1-1B engine


INTERSTAGE TURBINE TEMPERATURE (ITT) LIMITSCONDITION OF USE Ground start Airstart Restart max. temperature Max. take-off (APR) Normal take-off Max. continuous C 815 C 890 C 150 C 890 C 864 C 861 C 970 C Windmilling max. temperature 1,000 C

5 minutes max. 5 minutes max. 10 seconds max. 2 seconds max.

STARTING TIMEDASSAULT AVIATION Proprietary Data

CONDITION OF USE Ground start: From start to light-off From light-off to idle Airstart (from light-off to idle): Assisted Windmilling 10 seconds max. after reaching 22 % N2 60 seconds max. 90 seconds 180 seconds

STARTER RE-ENGAGEMENT LIMITS- Maximum N2............................................................................................. Starter cutout N2 (53.6 %)

THRUST REVERSER DHC TR 6000 (A/C WITH SB F2000-19)The thrust reverser is approved only when on the ground.



LIMITATIONSPOWERPLANT Fuel system

1-100-10PAGE 1 / 4 Issue 1

FUEL TYPESFuel used must conform to the following specifications.SPECIFICATION DESIGNATION TRADE NAME EQUIVALENCE (FOR INFO.) ASTM D 1655-82 Type A CAN 2-3.23 M.D.2494 Issue 9 AIR 3405 C ASTM D 1655-82 Type A CAN 2-3.23 DEF STAN 91-91 M.D 2494 Issue 9 AIR 3405 C MIL-T-83133 M.D.2453 Issue 4-Amd 1 AIR 3405 C DEF STAN 91-87 NTSB GB6537-94 Issue 2 NTSB GB6537-05 GOST10227-86 GSTU 320.00149943.011-99 GSTU 320.00149943.007-97 AIR 3404 C DEF STAN 91-86 CAN 3GP24 M.D.2452 Issue 2-Amd 1 MIL-T-5624H FREEZING POINT (C) - 40 ADDITIVES ANTIICE * * * * * * W/O * * WITH * WITH WITH * * W/O W/O * * WITH WITH WITH * WITH ANTISTATIC * WITH * * * * WITH WITH * * * * WITH * * W/O W/O * * * W/O * * W/O NATO CODE

JET A

F-35

JET A-1

- 47

F-35

KEROSENE

JET A-1 Type JP-8 No 3 Jet Fuel No 3A Jet Fuel TS-1 (CIS) (**) RT (CIS) (**) TS-1(Ukraine) (**) RT (Ukraine) (**)

- 50 - 47 - 47 - 60 - 60 - 55 - 55

F-34 * *DASSAULT AVIATION Proprietary Data

HIGH FLASH POINT TYPE FUEL

JP-5

- 46

F-44

* Information to be checked with the fuel supplier. ** Refer to engines maintenance manual.


1-100-10PAGE 2 / 4 Issue 1



USABLE QUANTITYThe total usable fuel quantity is distributed as follows: For A/C without M3072 and SB F2000-171:Liter LH wing + half center wing box RH wing + half center wing box Airplane capacity total 3,429 3,437 6,866 Kg * 2,753 2,760 5,513 US gal 906 908 1,814 Lb ** 6,070 6,085 12,155

* d=0.803 kg/l ** d=6.706 lb/US gal For A/C with M3072 or SB F2000-171:DASSAULT AVIATION Proprietary Data

Liter LH wing + half center wing box RH wing + half center wing box Airplane capacity total 3,413 3,421 6,834

Kg * 2,740 2,747 5,487

US gal 902 904 1,806

Lb ** 6,042 6,057 12,099

* d=0.803 kg/l ** d=6.706 lb/US gal NOTE The amount of fuel left in the tanks when the fuel quantity indicators reach zero is not safely usable in all flight conditions.

WARNING USE OF JP-4 OR JET B OR THEIR EQUIVALENT IS PROHIBITED.




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FUEL TEMPERATUREIn flight, tank fuel temperature must be maintained at least 3 C above the freezing point of fuel being used.

MAXIMUM FUEL UNBALANCED FOR FLIGHT- Maximum fuel dissymmetry....................................................................................................2,200 lb

PRESSURE FUELING SYSTEM- Maximum feed pressure ........................................................................... 50 psi / 3.5 bars / 350 kPa

FUEL ADDITIVESThe following additives are authorized for use in the fuel: - Anti-icing, conforming to AIR 3652 or MIL-I-27686 D specifications (JP8) or MIL-I-85470 (JP5) or equivalent at a concentration not in excess of 0.15 % by volume. - SOHIO Biobor JF biocide, or equivalent, at a concentration not to exceed 270 ppm. - Anti-static additive provided the quantity added does not exceed: - 1 ppm for SHELL ASA3, - 3 ppm for STADIS 450, - 5 ppm for SIGBOL TU 38-101741-78.

FUEL CONTROL COMPUTERThe Fuel Quantity Management Computer (FQMC) must be operative for take-off.



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LIMITATIONSPOWERPLANT Fuel system (A/C with M1903)

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FUEL TYPESFuel used must conform to the following specifications.SPECIFICATION DESIGNATION TRADE NAME EQUIVALENCE (FOR INFO.) ASTM D 1655-82 Type A CAN 2-3.23 M.D.2494 Issue 9 AIR 3405 C ASTM D 1655-82 Type A CAN 2-3.23 DEF STAN 91-91 M.D 2494 Issue 9 AIR 3405 C MIL-T-83133 M.D.2453 Issue 4-Amd 1 AIR 3405 C DEF STAN 91-87 NTSB GB6537-94 Issue 2 NTSB GB6537-05 GOST10227-86 GSTU 320.00149943.011-99 GSTU 320.00149943.007-97 ASTM D 1655-85 Type B CAN 2-3.22 M.D.2486 Issue 9-Amd 1 AIR 3407 B Rus. T2 MIL-T-5624L AIR 3407 B DEF STAN 91-88 CAN 2-3.22 M.D.2454 Issue 4-Amd 1 AIR 3404 C DEF STAN 91-86 CAN 3GP24 M.D.2452 Issue 2-Amd 1 MIL-T-5624H FREEZING POINT (C) - 40 ADDITIVES ANTIICE * * * * * * W/O * * WITH * WITH WITH * * W/O W/O * * * * * * * WITH WITH WITH WITH * WITH WITH WITH * WITH ANTISTATIC * WITH * * * * WITH WITH * * * * WITH * * W/O W/O * * * * WITH * * WITH * W/O WITH * * W/O * * W/O NATO CODE

JET A

F-35

JET A-1

- 47

F-35

KEROSENE

JET A-1 Type JP-8 No 3 Jet Fuel No 3A Jet Fuel TS-1 (CIS) (**) RT (CIS) (**) TS-1(Ukraine) (**) RT (Ukraine) (**)

- 50

F-34DASSAULT AVIATION Proprietary Data

- 47 - 47 - 60 - 60 - 55 - 55 - 51

* *

JET B WIDE CUT TYPE FUEL JP-4

- 60

- 58

F-40

HIGH FLASH POINT TYPE FUEL

JP-5

- 46

F-44

* Information to be checked with the fuel supplier. ** Refer to engines maintenance manual.



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USABLE QUANTITYThe total usable fuel quantity is distributed as follows: For A/C without M3072 and SB F2000-171:Liter LH wing + half center wing box RH wing + half center wing box Airplane capacity total 3,429 3,437 6,866 Kg * 2,753 2,760 5,513 US gal 906 908 1,814 Lb ** 6,070 6,085 12,155

* d=0.803 kg/l ** d=6.706 lb/US gal For A/C with M3072 or SB F2000-171:DASSAULT AVIATION Proprietary Data

Liter LH wing + half center wing box RH wing + half center wing box Airplane capacity total 3,413 3,421 6,834

Kg * 2,740 2,747 5,487

US gal 902 904 1,806

Lb ** 6,042 6,057 12,099

* d=0.803 kg/l ** d=6.706 lb/US gal NOTE The amount of fuel left in the tanks when the fuel quantity indicators reach zero is not safely usable in all flight conditions.





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FUEL TEMPERATUREIn flight, tank fuel temperature must be maintained at least 3 C above the freezing point of fuel being used.

USE OF JP-4 OR JET BFlight altitude is limited to 23,000 ft after low booster pump failure.

MAXIMUM FUEL UNBALANCED FOR FLIGHT- Maximum fuel dissymmetry....................................................................................................2,200 lb

PRESSURE FUELING SYSTEM- Maximum feed pressure ........................................................................... 50 psi / 3.5 bars / 350 kPa

FUEL ADDITIVESThe following additives are authorized for use in the fuel: - Anti-icing, conforming to AIR 3652 or MIL-I-27686 D specifications (JP4/JP8) or MIL-I-85470 (JP5) or equivalent at a concentration not in excess of 0.15 % by volume. - SOHIO Biobor JF biocide, or equivalent, at a concentration not to exceed 270 ppm. - Anti-static additive provided the quantity added does not exceed: - 1 ppm for SHELL ASA3, - 3 ppm for STADIS 450, - 5 ppm for SIGBOL TU 38-101741-78.

FUEL CONTROL COMPUTERThe Fuel Quantity Management Computer (FQMC) must be operative for take-off.




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LIMITATIONSPOWERPLANT Lubrication system

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APPROVED OILSApproved oil conforming to General Electric Specifications D50TF1, or AlliedSignal oil specifications EMS 53110.

OIL PRESSURE LIMITSOperating range Transient (3 min. max.) Minimum (at IDLE) Cold start: oil T < 0 C (2.5 min. max.) 60 to 85 psi 85 to 100 psi 30 psi 135 psi

NOTE The OIL 1 and OIL 2 lights in the warning panel illuminate for an oil pressure below 25 psi.DASSAULT AVIATION Proprietary Data

OIL TEMPERATURE LIMITS

Maximum Minimum for take-off Transient: for 3 min. Cold start

138 C 30 C 138 to 155 C - 40 C

NOTE In case of take-off at very low temperature, TEMP OIL indication may drop in the lower yellow range during take-off run.


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LIMITATIONSPOWERPLANT Lubrication system






LIMITATIONSSPEED AND OPERATIONAL LIMITS Airspeed and mach

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Unless otherwise specified, limits are expressed in terms of indicated values. Instrument error is assumed to be zero.

MAXIMUM OPERATING LIMIT SPEEDVMO / MMO ENVELOPE

CAUTION The maximum operating limit speed VMO / MMO must not be deliberately exceeded in any regime of flight (climb, cruise, descent) unless a higher speed is authorized for flight test or pilot training.



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DESIGN MAXIMUM MANEUVERING SPEED- VA....................................................................................................................................... 198 KIAS CAUTION Full application of rudder or aileron controls, as well as maneuvers that involve angles-ofattack near the stall must be confined to speeds below VA. Rapidly alternating large rudder applications in combination with large sideslip angles may result in structural failure at any speed.

HIGH LIFT DEVICES OPERATING OR EXTENDED LIMIT SPEEDS : VFE- VFE Slats extended + flaps 10 .......................................................................................... 200 KIAS - VFE Slats extended + flaps 20 .......................................................................................... 160 KIAS - VFE Slats extended + flaps 40 .......................................................................................... 160 KIASDASSAULT AVIATION Proprietary Data

CAUTION Above 20,000 ft do not establish or maintain a configuration with the flaps or the slats extended.

MAXIMUM LANDING GEAR OPERATING SPEED: VLO / MLO- VLO .................................................................................................................................... 190 KIAS - MLO....................................................................................................................................... MI 0.70 VLO / MLO is the maximum speed at which it is safe to extend or retract the landing gear.

MAXIMUM LANDING GEAR EXTENDED SPEED: VLE / MLE- VLE..................................................................................................................................... 245 KIAS - MLE ....................................................................................................................................... MI 0.75 VLE / MLE is the maximum speed at which the airplane can be safely flown with the landing gear extended and locked and main doors closed.

MINIMUM CONTROL SPEED IN THE AIR: VMCA- VMCA ................................................................................................................................... 90 KIAS




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MINIMUM CONTROL SPEED DURING APPROACH AND LANDING: VMCL- VMCL ................................................................................................................................... 90 KIAS

MINIMUM CONTROL SPEED ON THE GROUND: VMCG- VMCG................................................................................................................................... 98 KIAS

MISCELLANEOUS LIMIT SPEEDSWINDSHIELD WIPER OPERATING SPEED - V WWO............................................................................................................................... 215 KIAS PILOT WINDOW OPENING SPEED - V Window ........................................................................................................................... 215 KIAS TIRE MAXIMUM OPERATING SPEED - V Tire...............................................................................................................195 kt (ground speed) STALL SPEED CAUTION Do not intentionally fly the airplane slower than initial stall warning onset.DASSAULT AVIATION Proprietary Data


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LIMITATIONSSPEED AND OPERATIONAL LIMITS Airspeed and mach (A/C S/N 70 (M1578))

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Unless otherwise specified, limits are expressed in terms of indicated values. Instrument error is assumed to be zero.

MAXIMUM OPERATING LIMIT SPEEDVMO / MMO ENVELOPE

CAUTION The maximum operating limit speed VMO / MMO must not be deliberately exceeded in any regime of flight (climb, cruise, descent) unless a higher speed is authorized for flight test or pilot training.

A/C with MEGGITT secondary flight display system (M1578) A/C S/N 70



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LIMITATIONSSPEED AND OPERATIONAL LIMITS Airspeed and mach (A/C S/N 70 (M1578))


NOTE The red warnings occur simultaneously on the standby instrument and on the pilot / copilot EFIS (or HUD if any). However the VMO / MMO STAND-BY indicated value may be different from the pilot and the copilot values on the EFIS (or HUD if any) (see correction curves 5-300-15A pages 4 and 5).

DESIGN MAXIMUM MANEUVERING SPEED- V

F2000 - AFM REV13 Complet - 20100721

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