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FALCON 900 

MAINTENANCE MANUAL 

CHAPTER 5-40

AIRWORTHINESS LIMITATIONS 

ORIGINAL – March1986 

REVISION 20 - October 2012 

DGT 113873-PUB 471 or 476 

090040008057f995 - VALIDATED - Certification Repository 
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INFORMATION TO OPERATORS 

Please find enclosed Revision No. 20 of Chapter 5-40. 

Modifications and corrections contained in this revision are: 

the renumbering of tasks, 

the presentation of the chapter (The sections 05-40-00, 05-40-10, 05-40-20 and 05-40-

30 are gathered in section 05-40-00), 

the introduction of the Corrosion Prevention Control Program, 

the integration of the CP 006. 
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This document is divided into 5 paragraphs: 

A. History of revision 

B. General 

C. Corrosion Prevention Control Program 

D. Notes 

E. Airframe components with limited service life 

F. Mandatory maintenance operations 
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A. HISTORY OF REVISION

Approved by the E.A.S.A. 

Date of approval: 

- Original edition DMD 35543 § 5-40: March 13, 1986 

- Revision 1 DMD 35543 § 5-40: April 24, 1986 

- Revision 2 DMD 35543 § 5-40: November 21, 1986 

- Revision 3 DMD 35543 § 5-40: October 15, 1987 

- Revision 4 DMD 35543 § 5-40: May 2, 1988 

- Revision 5 DMD 35543 § 5-40: December 5, 1989 

- Revision 6 DMD 35543 § 5-40: April 26, 1991 

- Revision 7 DMD 35543 § 5-40: March 18, 1992 

- Revision 8 DMD 35543 § 5-40: February 4, 1994 

- Revision 9 DMD 35543 § 5-40: October 27, 1997 

- Revision 10 DMD 35543 § 5-40: September 17, 1998 

- Revision 11 DMD 35543 § 5-40: December 23, 1999 

- Revision 12 DMD 35543 § 5-40: October 20, 2000 

- Revision 13 DMD 35543 § 5-40: March 25, 2003 

- Revision 14 DMD 35543 § 5-40: November 28, 2005 

- Revision 15 DMD 35543 § 5-40: October 25, 2006 

- Revision 16 DGT 113873 supersedes DMD 35543 § 5-40: EASA approved under 

EASA.A.C.10057 on July 4, 

- Revision 17 DGT 113873: 

This revision 17 is the compilation of the following EASA changes, with no further technical 

changes: 

· Temporary Revision 01, EASA approved under EASA.A.C.11570 on January 26, 2009 

· Temporary Revision 02, EASA approved under EASA.A.C.11441 revision 1 on February 

02, 2009 

· Change proposal 04, EASA approved under 10028131 on December 03, 2009 

The technical content of this revision is approved under DOA EASA.21J.051 authority by 

reference R5013. This approval means that the revision has been prepared exclusively with 

already EASA approved data and is released under DOA procedures. 

Effective date of this revision: April 19, 2010. 

- Revision 18 DGT 113873: 

This revision 18 is the compilation of the following EASA changes, with no further technical 

changes: 

· Change proposal 03, EASA approved under 10029544 on March 31, 2010 

The technical content of this revision is approved under DOA EASA.21J.051 authority by 

reference R5020. This approval means that the revision has been prepared exclusively with 

already EASA approved data and is released under DOA procedures. 

Effective date of this revision: August 03, 2010. 

- Revision 19 DGT 113873: 

This revision 19 is the compilation of the following EASA changes, with no further technical 

changes: 

· Change proposal 05, EASA approved under change reference M5666 
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The technical content of this revision is approved under DOA EASA.21J.051 authority by 

reference R5025. This approval means that the revision has been prepared exclusively with 

already EASA approved data and is released under DOA procedures. 

Effective date of this revision: August 12, 2011. 

- Revision 20 DGT 113873: 

This complete revision 20 is the renumbering of tasks, the presentation of the chapter, the 

introduction of the Corrosion Prevention Control Program and the integration of the following 

EASA change proposal: 

CP 006, EASA approved under change reference M5739 

The technical content of this revision is approved under DOA EASA.21J.051 authority by 

reference R5041. This approval means that the revision has been prepared exclusively with 

already EASA approved data and is released under DOA procedures. 

Effective date of this revision: December 31, 2012 
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B. GENERAL

This document is applicable to F900. 

This section contains instructions pertaining to Airworthiness (refer to FAR 25 - 1529 

Appendix H, paragraph H25-4 and amendment 25-54). These instructions apply to 

components and systems designed and approved by DASSAULT AVIATION and included in 

the aircraft type design. 

This section contains instructions pertaining to Airworthiness of aircraft and Safe Life 

limitations, until the Design Service Goal (20,000 flights/30,000 flying hours). 

The tasks and intervals specified are mandatory and cannot be changed, escalated, or deleted 

without the concurrence of the responsible Aircraft Certification Office. 

With respect to the Airworthiness of the aircraft, this section is subject to approval by the 

European Aviation Safety Agency (E.A.S.A.). 

For U.S. Registered aircraft, the Airworthiness Limitations section specifies maintenance 

required under part 43 and part 91 of the Federal Aviation Regulations, unless an alternative 

program has been F.A.A. approved. 

Evaluations and reasons for airworthiness limitations do not take into account the influence of 

modifications not approved by DASSAULT AVIATION such as STC, PMA (Part 

Manufacturer Approval), etc. 

1. Definition of a Standard Aircraft

This program is defined for a "STANDARD AIRCRAFT" as defined below. 

For non-standard aircraft, this program needs to be adapted with Instructions for Continued 

Airworthiness developed to cover the non-standard features (STC, repairs, operating 

conditions, ...). 

1.1. Standard Aircraft Primary structure must be entirely identical to DASSAULT 

AVIATION type design: 

Condition of the primary structure of a standard aircraft has to correspond to definition at 

aircraft delivery: 

- which can be supplemented by the DASSAULT AVIATION Service Bulletins 

incorporated on aircraft, 

- which must have incorporated the applicable mandatory Service Bulletins. 

An aircraft cannot be considered as a standard aircraft if its primary structure has been 

changed by an STC or repaired through a definition not reviewed by DASSAULT 

AVIATION in the frame of the applicability of these instructions. 
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1.2. Aircraft operations should be close to the fatigue load spectrum defined during type 

certification. This spectrum corresponds to public or private transport defined by 

short, middle and long distance flights. 

When types of mission listed hereafter are performed on a regular basis, the aircraft can 

not be considered as a Standard Aircraft: 

- Low altitude search and rescue flights. 

- Target towing and transport of under wing stores. 

- Scientific research. 

- Cargo transport. 

- Flight training. 

- Other types of operation than normal passenger transport. 

1.3. Maintenance must have been performed in accordance with either: 

- Maintenance Manual and Structural Repair Manual (formerly Maintenance and Repair 

Instructions) recommended by DASSAULT AVIATION, 

or 

- Approved maintenance procedures. 

2. Important

These instructions must mandatorily be complied with by the operators. 

Failure to comply with these instructions will lead to the immediate suspension of the 

Airworthiness certificate. 

The mandatory nature of these instructions does not in any way reduce the importance of the 

other tasks listed in the Recommended Maintenance Program which must be performed in 

agreement with the national Airworthiness Authorities. 

The mandatory maintenance operations time limits given in section 5-40 correspond to results 

obtained from computations. 

In order to help operators planning maintenance program and to reduce grounding time due to 

scheduled maintenance, these mandatory maintenance operations are also listed in sections 5-

10 or 5-20 but with time limits corresponding to aircraft inspections (A, B, C, etc.). 

The time base to be taken into account for equipment is defined in section 5-20-00 and the 

date of origin to be taken into account for aircraft maintenance operation is defined in section 

5-10-00. 

An operation required in section 5-40 may not necessarily have to be performed, provided it 

was previously performed during an inspection required in sections 5-10 or 5-20. 

3. Updating of 5-40 sections 

When a new maintenance operation is added due to a revision of Chapter 5-40, this operation 

must be performed when the time at which it is scheduled falls due, unless otherwise 

specified. 
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When the aircraft inspection has two limits (i.e. 7500 landings or 12 years), the due time will 

be whichever is reached first. 

4. List of unit

The units and their equivalent abbreviations used in this document are listed hereafter: 

- LDG: landings 

- Y: Years 

- M: Months 

- FH: Flight Hour 

- FC: Flight Cycle 

The definitions of landing, flight hour and flight cycle are in Chapter 5 section 5-00-00 § 

Structural Maintenance. 
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C. CORROSION PREVENTION CONTROL PROGRAM

NOTE: Refer to chapter 05-15 for definitions of Level 1, 2 and 3 corrosion. 

A CPCP is a systematic approach for controlling corrosion in the airplane's primary structure. 

It is a program of maintenance tasks designed to control an aircraft structure to Corrosion 

level 1 or better (Chapter 05-15 and EASA AMC 20-20 provide further details). 

During the whole life of the aircraft, the operator is required to maintain the aircraft structure 

to level 1 of corrosion or better on Principal Structural Element (PSE, Ref. to list in SRM 

number 51-00-02 RPI). 

In order to control the aircraft structure to corrosion level 1 or better on PSEs, the operator 

should implement a CPCP as per Chapter 05-15 (baseline) and comply and conform to the 

aircraft maintenance manual tasks listed in Chapter 5.10 and 5.20. 

This baseline CPCP should be adapted by the operator to take into account "non standard" 

features of his aircraft, if any. In this case, the operator can find some guidelines in 

Chapter 05-15. 

DASSAULT AVIATION is responsible for monitoring the effectiveness of the Baseline 

Program and the pertinence of the inspection threshold and, if necessary, to define changes 

based on analysis of the operators reported findings. Consequently, operators are mandated to 

report any finding affecting a PSE to DASSAULT AVIATION when corrosion level 2 or 3 is 

found. This will allow DASSAULT AVIATION to justify periodicity changes and to publish 

updates of the baseline CPCP. 

NOTE: Reporting of Level 1 corrosion that is recurrent in the same location or nil finding is 

also of interest to DASSAULT AVIATION and should be reported to assist in understanding 

the aging of the fleet and the possible need for escalation or alleviation of maintenance 

program. 
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D. NOTES

The following notes are the notes used in this document: 

NOTE (1): For actuator 5318-1 and 5318-1 Amdt A used solely on the external points of 

inboard flaps this limitation is increased to 2200 LDG, in this case, check of screw/nut play 

(27-53-01-720-803- TSK) is to be performed at 600 LDG then every 330 FH or 7 M. 

It is prohibited to swap actuators between inboard flap inboard position and inboard flap 

outboard position. 

NOTE (2): For screwjack having exceeded 2100 LDG at the effective date of the revision 19, 

upgrade to be done within 400 LDG not to exceed 3500 LDG. 

For screwjack having exceeded 3450 LDG at the effective date of the revision 19, upgrade to 

be done within 50 LDG. 

NOTE (3): Operation covered by structural inspections 53-10-00-210-802- TSK, 53-40-00-

210-802- TSK, 55-00-00-210-801- TSK and 57-00-00-210-801- TSK scheduled every 2 Y. 

NOTE (4): After revision 17, compliance with former "INSPECTION OF THE FUSELAGE 

SKIN - FRAME 0 TO FRAME 4”- MP 53-10-00-200-810- TSK" is equivalent to compliance 

with "Inspection of cockpit skin - Operation: Outside general visual inspection - MP 53-051".

For A/C having exceeded the first repeat inspection frequency limit, inspection to be done 

within 150 FC from effective date of revision 18. 

NOTE (5): For A/C having exceeded the maximum number of landings limit, overhaul to be 

done within 50 LDG from effective date of revision 17. 

NOTE (6): For A/C having exceeded 10750 LDG, inspection to be done within 500 LDG 

from effective date of revision 18. 
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E. AIRFRAME COMPONENTS WITH LIMITED SERVICE LIFE

The components with limited service life are listed in the tabular form as follows: 

Column 1: Component Functional Index (CFI): Index that allows search throughout 

the maintenance documentation, and for electrical components it is also the electrical 

index. 

Column 2: Part Numbers (P/N): The task is applicable only to the listed P/Ns. Note: A 

P/N in the list may not be applicable to your aircraft. Refer to the IPC for this 

information. 

Column 3: Limited service life: threshold at which the task has to be performed. 

Column 4: Remark: Note or comment related to the procedure/operation or its 

interval. The numbered notes are listed in § Notes 

Column 5: Scheduled maintenance task number, may be either: 

o A task number (12 digits), in accordance with the AMM tasks numbering 

system. In this case, the whole task (all operations of the task) must be 

performed at the required interval. 

o An operation number (14 digits), the first 12 digits being the AMM tasks 

number. In this case, only the operation codes listed have to be performed at 

the required interval. 

 Column 6: Task title: Description of the task or the operation in accordance with the 

AMM. 
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CHAPTER 5-40

27 : FLIGHT CONTROLS

Scheduled

maintenance

task number

Limited Title / Operation

service life

Component

Functional

Index

P/N Remark

523CW - pitch AAFU P/N 105045-10 27-35-07-350-801 RESTORATION OF THE PITCH AUXILIARY AFU (DISCARD OF 

BUSHINGS 1050450002)

2000 LDG French D.G.A.C. AD-98-

429-023 (B) and FAA AD

 99-19-24

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CHAPTER 5-40

32 : LANDING GEAR

Scheduled

maintenance

task number

Limited Title / Operation

service life

Component

Functional

Index

P/N Remark

P/N D22801100-X or

P/N D22801400-X

L2GF - LH MLG leg 32-11-00-960-801-01 REPLACEMENT OF THE MLG LEGS (DISCARD OF LIFE LIMITED 

PARTS) - LH MLG LEG (L2GF)

20000 LDG

P/N D22802100-X or

P/N D22802400-X

R2GF - RH MLG leg 32-11-00-960-801-02 REPLACEMENT OF THE MLG LEGS (DISCARD OF LIFE LIMITED 

PARTS) - RH MLG LEG (R2GF)

20000 LDG

P/N D22811200-X or

P/N D22811400-X

3GF - NLG leg 32-21-00-960-801-01 REPLACEMENT OF THE NLG LEG (DISCARD OF LIFE LIMITED 

PARTS) - NLG LEG (3GF)

20000 LDG

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F. MANADATORY MAINTENANCE OPERATIONS

The mandatory maintenance operations to be performed are listed in the tabular form as 

follows: 

Column 1: Scheduled maintenance task number, may be either: 

o A task number (12 digits), in accordance with the AMM tasks numbering 

system. In this case, the whole task (all operations of the task) must be 

performed at the required interval. 

o An operation number (14 digits), the first 12 digits being the AMM tasks 

number. In this case, only the operation codes listed have to be performed at 

the required interval. 

o The previous numbering (5 digits), if existing, is indicated under the new 

AMTOSS number, as it may be called in some old documents. 

 Column 2: Origin : The origin of these mandatory maintenance operations can be 

o Operations resulting from fatigue tests and damage tolerance calculations –

identified by "FD”: Fatigue and Damage.

o Operations resulting from the certification maintenance requirements - 

identified by "CMR". 

o Operations resulting from aircraft utilization identified by "RetEx": Return of 

Experience. 

o Operations resulting from Airworthiness limitation identified by “ALI”.

Column 3: Task title: Description of the task or the operation in accordance with the 

AMM. 

Column 4: First inspection: The task must have been performed no later than this 

maximum limit.

Column 5: Interval: The task must be repeated no later than this maximum interval 

thereafter.

Column 6: Remark: Note, comment or effectivity related to the procedure/operation or 

its interval. The numbered notes are listed in § Notes 

 
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CHAPTER 5-40

21 : AIR CONDITIONING

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

21-308

21-32-06-200-801-03 INSPECTION / CHECK OF THE ELECTROPNEUMATIC AND PNEUMATIC 1640 FH

VALVES - CHECK OF OVERPRESSURE TIGHTNESS OF 

ELECTROPNEUMATIC VALVE (4HP)

CMR 1640 FH

21-308

21-32-06-200-801-04 INSPECTION / CHECK OF THE ELECTROPNEUMATIC AND PNEUMATIC 1640 FH

VALVES - CHECK OF OVERPRESSURE TIGHTNESS OF PNEUMATIC 

VALVE (5HP)

CMR 1640 FH

21-308

21-32-06-200-801-05 INSPECTION / CHECK OF THE ELECTROPNEUMATIC AND PNEUMATIC 7500 FH

VALVES - CHECK OF OVERPRESSURE RELIEF VALVE VACUUM 

SUPPLY LINES (975HP) AND (976HP)

CMR 7500 FH

21-32-06-720-801 FUNCTIONAL TEST OF THE ELECTROPNEUMATIC AND PNEUMATIC 14300 FH

VALVES

CMR 14300 FH

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CHAPTER 5-40

25 : EQUIPMENT / FURNISHINGS

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

25-11-05-200-801 VISUAL INSPECTION OF BUCKLE SPRING OF ANJOU AERONAUTIQUE 

SAFETY BELTS AND RESTRAINT SYSTEM (TYPE 343 AND 343-1)

18 M (*) 

(*) Life limit of 60 M for 

seat safety belt 

assembly

RetEx See CN 2002-105 (AB) and CN 2002-104 

(AB)

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CHAPTER 5-40

27 : FLIGHT CONTROLS

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

27-003

27-00-00-220-801 INTEGRITY CHECK AND VISUAL INSPECTION FOR CORROSION AND 4000 FH

EXTERNAL LEAKS ON FLIGHT CONTROL HYDRAULIC COMPONENTS

CMR 4000 FH See note (3)

27-002

27-00-00-720-803 FUNCTIONAL TEST OF THE AUXILIARY AFU (AAFU CONNECTION AND 10000 FH

VISUAL INSPECTION)

CMR 10000 FH

27-108

27-14-05-720-801 CMR FUNCTIONAL TEST OF THE ROLL TRIM CONTROL SAFETY RELAYS 20000 FH 20000 FH

27-22-01-350-801 RESTORATION OF THE RUDDER SERVO-ACTUATOR (FUNCTIONAL 4000 FH

TEST)

CMR 4000 FH

27-211

27-24-05-720-802 CMR FUNCTIONAL TEST OF THE YAW TRIM CONTROL SAFETY RELAYS 20000 FH 20000 FH

27-32-01-350-801 RESTORATION OF THE ELEVATOR SERVO-ACTUATOR (FUNCTIONAL 14000 FH

TEST)

CMR 14000 FH

27-412

27-40-15-710-801 CMR OPERATIONAL TEST OF THE HS EMERGENCY TRIM CONTROL RELAY 16000 FH 16000 FH

27-405

27-40-17-720-801 CMR FUNCTIONAL TEST OF THE HORIZONTAL STABILIZER RELAY BOX 5000 FH 5000 FH

27-502

27-50-00-720-802 CMR FUNCTIONAL TEST OF THE FLAP ASYMMETRY DETECTION SYSTEM 1800 FH 1800 FH

A/C with DED flap control system

27-502

27-50-00-720-802 CMR FUNCTIONAL TEST OF THE FLAP ASYMMETRY DETECTION SYSTEM 450 FH 450 FH

A/C with AVIAC flap control system

27-53-01-350-801-01 RESTORATION OF THE FLAP SCREW JACKS (OVERHAUL) - LH 4500 LDG

OUTBOARD FLAP SCREW JACK (L502CG)

RetEx 4500 LDG See note (5)

P/N 1-5319-3

27-53-01-350-801-02 RESTORATION OF THE FLAP SCREW JACKS (OVERHAUL) - LH 3500 LDG

INBOARD FLAP LATERAL SCREW JACK (L501CG)

RetEx 3500 LDG See note (5)

P/N 5318-3

27-53-01-350-801-03 RESTORATION OF THE FLAP SCREW JACKS (OVERHAUL) - LH 3500 LDG

INBOARD FLAP CENTER SCREW JACK (L500CG)

RetEx 3500 LDG See note (5)

P/N 5318-3

27-53-01-350-801-04 RESTORATION OF THE FLAP SCREW JACKS (OVERHAUL) - RH 3500 LDG

INBOARD FLAP CENTER SCREW JACK (R500CG)

RetEx 3500 LDG See note (5)

P/N 5318-3

27-53-01-350-801-05 RESTORATION OF THE FLAP SCREW JACKS (OVERHAUL) - RH 3500 LDG

INBOARD FLAP LATERAL SCREW JACK (R501CG)

RetEx 3500 LDG See note (5)

P/N 5318-3

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CHAPTER 5-40

27 : FLIGHT CONTROLS

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

27-53-01-350-801-06 RESTORATION OF THE FLAP SCREW JACKS (OVERHAUL) - RH 4500 LDG

OUTBOARD FLAP SCREW JACK (R502CG)

RetEx 4500 LDG See note (5)

P/N 2-5319-3

27-53-01-350-802-01 UPGRADE OF THE FLAP SCREW JACKS (AVIAC) - LH OUTBOARD 

FLAP SCREW JACK (L502CG)

RetEx 2500 LDG See note (2)

P/N 1-5319-1 or

P/N 1-5319-2

27-53-01-350-802-02 UPGRADE OF THE FLAP SCREW JACKS (AVIAC) - LH INBOARD FLAP 

LATERAL SCREW JACK (L501CG)

RetEx 750 LDG See note (1)

P/N 5318-1 or

P/N 5318-1 Amdt A

27-53-01-350-802-02 UPGRADE OF THE FLAP SCREW JACKS (AVIAC) - LH INBOARD FLAP 

LATERAL SCREW JACK (L501CG)

RetEx 2000 LDG

P/N 5318-2

27-53-01-350-802-03 UPGRADE OF THE FLAP SCREW JACKS (AVIAC) - LH INBOARD FLAP 

CENTER SCREW JACK (L500CG)

RetEx 750 LDG See note (1)

P/N 5318-1 or

P/N 5318-1 Amdt A

27-53-01-350-802-03 UPGRADE OF THE FLAP SCREW JACKS (AVIAC) - LH INBOARD FLAP 

CENTER SCREW JACK (L500CG)

RetEx 2000 LDG

P/N 5318-2

27-53-01-350-802-04 UPGRADE OF THE FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP 

CENTER SCREW JACK (R500CG)

RetEx 750 LDG See note (1)

P/N 5318-1 or

P/N 5318-1 Amdt A

27-53-01-350-802-04 UPGRADE OF THE FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP 

CENTER SCREW JACK (R500CG)

RetEx 2000 LDG

P/N 5318-2

27-53-01-350-802-05 UPGRADE OF THE FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP 

LATERAL SCREW JACK (R501CG)

RetEx 750 LDG See note (1)

P/N 5318-1 or

P/N 5318-1 Amdt A

27-53-01-350-802-05 UPGRADE OF THE FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP 

LATERAL SCREW JACK (R501CG)

RetEx 2000 LDG

P/N 5318-2

27-53-01-350-802-06 UPGRADE OF THE FLAP SCREW JACKS (AVIAC) - RH OUTBOARD 

FLAP SCREW JACK (R502CG)

RetEx 2500 LDG See note (2)

P/N 2-5319-1 or

P/N 2-5319-2

27-514

27-53-01-720-803-01 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 330 FH

LH OUTBOARD FLAP SCREW JACK (L502CG)

RetEx 1000 LDG

P/N 1-5319-1 or

P/N 1-5319-1 Amdt A

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FALCON 900

CHAPTER 5-40

27 : FLIGHT CONTROLS

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

27-514

27-53-01-720-803-01 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 330 FH

LH OUTBOARD FLAP SCREW JACK (L502CG)

RetEx 2000 LDG

P/N 1-5319-2

27-514

27-53-01-720-803-01 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 450 FH

LH OUTBOARD FLAP SCREW JACK (L502CG)

RetEx 3000 LDG

P/N 1-5319-3

27-514

27-53-01-720-803-02 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 600 LDG

LH INBOARD FLAP LATERAL SCREW JACK (L501CG)

RetEx 600 LDG

P/N 5318-1 or

P/N 5318-1 Amdt A

27-514

27-53-01-720-803-02 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 630 FH

LH INBOARD FLAP LATERAL SCREW JACK (L501CG)

RetEx 630 FH

P/N 5318-2

27-514

27-53-01-720-803-02 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 450 FH

LH INBOARD FLAP LATERAL SCREW JACK (L501CG)

RetEx 3000 LDG

P/N 5318-3

27-514

27-53-01-720-803-03 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 600 LDG

LH INBOARD FLAP CENTER SCREW JACK (L500CG)

RetEx 600 LDG

P/N 5318-1 or

P/N 5318-1 Amdt A

27-514

27-53-01-720-803-03 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 630 FH

LH INBOARD FLAP CENTER SCREW JACK (L500CG)

RetEx 630 FH

P/N 5318-2

27-514

27-53-01-720-803-03 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 450 FH

LH INBOARD FLAP CENTER SCREW JACK (L500CG)

RetEx 3000 LDG

P/N 5318-3

27-514

27-53-01-720-803-04 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 600 LDG

RH INBOARD FLAP CENTER SCREW JACK (R500CG)

RetEx 600 LDG

P/N 5318-1 or

P/N 5318-1 Amdt A

27-514

27-53-01-720-803-04 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 630 FH

RH INBOARD FLAP CENTER SCREW JACK (R500CG)

RetEx 630 FH

P/N 5318-2

27-514

27-53-01-720-803-04 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 450 FH

RH INBOARD FLAP CENTER SCREW JACK (R500CG)

RetEx 3000 LDG

P/N 5318-3

27-514

27-53-01-720-803-05 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 600 LDG

RH INBOARD FLAP LATERAL SCREW JACK (R501CG)

RetEx 600 LDG

P/N 5318-1 or

P/N 5318-1 Amdt A

27-514

27-53-01-720-803-05 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 630 FH

RH INBOARD FLAP LATERAL SCREW JACK (R501CG)

RetEx 630 FH

P/N 5318-2

Page 19 / 28

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113873

Rev. Date : October 2012
FALCON 900

CHAPTER 5-40

27 : FLIGHT CONTROLS

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

27-514

27-53-01-720-803-05 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 450 FH

RH INBOARD FLAP LATERAL SCREW JACK (R501CG)

RetEx 3000 LDG

P/N 5318-3

27-514

27-53-01-720-803-06 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 330 FH

RH OUTBOARD FLAP SCREW JACK (R502CG)

RetEx 1000 LDG

P/N 2-5319-1 or

P/N 2-5319-1 Amdt A

27-514

27-53-01-720-803-06 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 330

RH OUTBOARD FLAP SCREW JACK (R502CG)

RetEx 2000 LDG

P/N 2-5319-2

27-514

27-53-01-720-803-06 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 450 FH

RH OUTBOARD FLAP SCREW JACK (R502CG)

RetEx 3000 LDG

P/N 2-5319-3

Page 20 / 28

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113873

Rev. Date : October 2012
FALCON 900

CHAPTER 5-40

28 : FUEL

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

76-200

28-21-13-710-801 CMR OPERATIONAL TEST OF THE FUEL SHUT-OFF VALVES 11600 FH 11600 FH

Page 21 / 28

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113873

Rev. Date : October 2012
FALCON 900

CHAPTER 5-40

52 : DOORS

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

52-200

52-20-00-610-801-01 SERVICING OF THE EMERGENCY EXIT DOOR - TEST OF THE 24 M

EMERGENCY EXIT DOOR UNLOCKING FROM INSIDE THE CABIN

RetEx 24 M

52-301

52-30-00-710-801-02 OPERATIONAL TEST OF THE BAGGAGE COMPARTMENT DOOR - TEST 8000 FH

OF DOOR SLIDING BOLTS

CMR 8000 FH

Page 22 / 28

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113873

Rev. Date : October 2012
FALCON 900

CHAPTER 5-40

53 : FUSELAGE

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

53-053

53-00-00-200-803-01 INSPECTION OF THE FUSELAGE SKIN - FRAME 4 TO FRAME 30 - 3750 FC

GENERAL VISUAL INSPECTION

FD 11250 FC

53-053

53-00-00-200-803-02 INSPECTION OF THE FUSELAGE SKIN - FRAME 4 TO FRAME 30 - 3750 FC

DETAILED INSPECTION IN SPECIFIC AREAS

FD 11250 FC See note (6)

53-051

53-10-00-200-810-01 INSPECTION OF THE FUSELAGE SKIN - FRAME 0 TO FRAME 4 - 3750 FC

GENERAL VISUAL INSPECTION

FD 7500 FC See note (4)

53-051

53-10-00-200-810-02 INSPECTION OF THE FUSELAGE SKIN - FRAME 0 TO FRAME 4 - 3750 FC

DETAILED INSPECTION IN SPECIFIC AREAS

FD 11250 FC See note (6)

53-052

53-10-03-250-801 SPECIAL DETAILED INSPECTION OF THE UPPER PASSENGER DOOR 3750 FC

FRAME EDGING

FD 11250 FC

53-039

53-10-41-220-801 DETAILED INSPECTION OF THE ATTACHMENT FITTING OF THE NLG 3750 FC

ACTUATOR

FD 3750 FC

A/C without SB F900-197

53-040

53-10-43-220-801 DETAILED INSPECTION OF THE STIFFENERS AT THE BOTTOM OF 3750 FC

THE NLG WELL LH WALL

FD 11250 FC

A/C S/N < 189

53-055

53-30-00-250-801 EDDY CURRENT INSPECTION OF THE PASSENGER CABIN SKIN 3750 FC

PANEL AROUND EMERGENCY EXIT DOOR ROUNDED ANGLES

FD 7500 FC

53-054

53-30-00-250-802 EDDY CURRENT INSPECTION OF THE SKIN PANELS AROUND CABIN 3750 FC

WINDOW CUT-OUTS

FD 7500 FC

53-050

53-41-00-220-802 FD DETAILED INSPECTION OF THE LOWER WING ROOT BOLT RECESSES 11250 FC 7500 FC

Page 23 / 28

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113873

Rev. Date : October 2012
FALCON 900

CHAPTER 5-40

55 : STABILIZERS

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

55-050

55-10-00-270-801 ULTRASONIC INSPECTION OF THE HORIZONTAL STABILIZER HINGE 3750 FC

FITTINGS

FD 11250 FC

55-501

55-10-31-220-801 DIMENSIONAL CHECK OF HORIZONTAL STABILIZER REAR HINGE 3750 FC

BUSHINGS

FD 3750 FC A.D. N° 97-370-020

55-051

55-10-39-220-801 DETAILED INSPECTION OF THE HORIZONTAL STABILIZER ACTUATOR 3750 FC

ATTACHMENT FITTINGS AND PINS

FD 11250 FC

55-052

55-30-00-270-801 ULTRASONIC INSPECTION OF THE VERTICAL STABILIZER / STUB 3750 FC

ATTACHMENTS

FD 11250 FC

Page 24 / 28

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113873

Rev. Date : October 2012
FALCON 900

CHAPTER 5-40

57 : WINGS

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

57-008

57-10-01-210-801 FD GENERAL VISUAL INSPECTION OF THE WING LOWER PANELS 11250 FC 3750 FC See note (6)

57-060

57-10-14-220-801 DETAILED INSPECTION OF THE WING FRONT SPAR FROM ROOT TO 7500 FC

RIB 17 EXCEPT RIB 6 TO RIB 9

FD 11250 FC See note (6)

57-070

57-10-14-220-802 DETAILED INSPECTION OF THE WING FRONT SPAR FROM RIB 6 TO 3750 FC

RIB 9

FD 11250 FC See note (6)

57-090

57-10-15-220-801 DETAILED INSPECTION OF THE WING REAR SPAR 1 FROM ROOT TO 3750 FC

RIB 3

FD 11250 FC See note (6)

57-080

57-10-15-220-802 DETAILED INSPECTION OF THE WING REAR SPAR 2 FROM RIB 3 TO 7500 FC

RIB 17

FD 11250 FC See note (6)

57-050

57-10-15-250-801 EDDY-CURRENT INSPECTION OF THE RIB 8 REAR WING SPAR 3750 FC

SPLICE PLATE

FD 11250 FC

Page 25 / 28

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113873

Rev. Date : October 2012
FALCON 900

CHAPTER 5-40

71 : POWER PLANT

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

54-050

71-20-02-250-801 SPECIAL DETAILED INSPECTION OF THE ENGINE 1 AND 3 FRONT 2500 FC

MOUNTS

FD 10000 FC

54-051

71-20-07-250-801 SPECIAL DETAILED INSPECTION OF THE ENGINE 1 AND 3 REAR 2500 FC

MOUNTS

FD 10000 FC

Page 26 / 28

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113873

Rev. Date : October 2012
FALCON 900

CHAPTER 5-40

73 : ENGINE FUEL AND CONTROL

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

73-201

73-20-01-710-802 OPERATIONAL TEST OF THE ENGINE 1 COMPUTER STAND-BY 1640 FH

POWER SUPPLY

CMR 1640 FH

Page 27 / 28

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113873

Rev. Date : October 2012
FALCON 900 

CHAPTER 5-40 

 Page 28/ 28 

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113873

Rev. Date : October, 2012

END OF DOCUMENT