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“DASSAULT AVIATION Proprietary Data” 

# FALCON 900



# MAINTENANCE MANUAL CHAPTER 5- 40

AIRWORTHINESS LIMITATIONS

ORIGINAL

– March1986 REVISION 20 - October 2012

DGT 113873-PUB 471 or 476090040008057f995 - VALIDATED - Certification Repository

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Rev. Date : October 2012 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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Rev. Date : October 2012 

### 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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Rev. Date : October 2012 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: Th is 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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Rev. Date : October 2012 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

## FALCON 900 CHAPTER 5-40

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Rev. Date : October 2012 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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Rev. Date : October 2012 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 mandator il y 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.

## FALCON 900 CHAPTER 5-40

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Rev. Date : October 2012 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 u se d in this document a re 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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Rev. Date : October 2012 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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Rev. Date : October 2012 D. NOTES

The following notes are the notes u se d in this document:

NOTE (1) : For actuator 5318-1 and 5318-1 Amdt A u se d 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.

## FALCON 900 CHAPTER 5-40

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Rev. Date : October 2012 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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27 : FLIGHT CONTROLS

Scheduled maintenance task number Title / Operation Limited service life Component Functional Index Remark P/N

P/N 105045-10 523CW - pitch AAFU 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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# FALCON 900 CHAPTER 5-40

32 : LANDING GEAR

Scheduled maintenance task number Title / Operation Limited service life Component Functional Index Remark P/N

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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## FALCON 900 CHAPTER 5-40

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Rev. Date : October 2012 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: T he task must have been performed no later than this maximum limit. Column 5: Interval: The task must be repeated no later than this maximum int erval thereafter. Column 6: Remark: Note, comment or effectivity related to the procedure/operation or its interval. The numbered notes are listed in § Notes

# FALCON 900 CHAPTER 5-40

21 : AIR CONDITIONING

Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks

21-308 1640 FH 21-32-06-200-801-03 INSPECTION / CHECK OF THE ELECTROPNEUMATIC AND PNEUMATIC VALVES - CHECK OF OVERPRESSURE TIGHTNESS OF ELECTROPNEUMATIC VALVE (4HP) 1640 FH CMR

21-308 1640 FH 21-32-06-200-801-04 INSPECTION / CHECK OF THE ELECTROPNEUMATIC AND PNEUMATIC VALVES - CHECK OF OVERPRESSURE TIGHTNESS OF PNEUMATIC VALVE (5HP) 1640 FH CMR

21-308 7500 FH 21-32-06-200-801-05 INSPECTION / CHECK OF THE ELECTROPNEUMATIC AND PNEUMATIC VALVES - CHECK OF OVERPRESSURE RELIEF VALVE VACUUM SUPPLY LINES (975HP) AND (976HP) 7500 FH CMR

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

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# FALCON 900 CHAPTER 5-40

25 : EQUIPMENT / FURNISHINGS

Scheduled maintenance task number Title / Operation First Inspection Origin 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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27 : FLIGHT CONTROLS

Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks

27-003 4000 FH 27-00-00-220-801 INTEGRITY CHECK AND VISUAL INSPECTION FOR CORROSION AND EXTERNAL LEAKS ON FLIGHT CONTROL HYDRAULIC COMPONENTS 4000 FH CMR See note (3)

27-002 10000 FH 27-00-00-720-803 FUNCTIONAL TEST OF THE AUXILIARY AFU (AAFU CONNECTION AND VISUAL INSPECTION) 10000 FH CMR

27-108 20000 FH 27-14-05-720-801 FUNCTIONAL TEST OF THE ROLL TRIM CONTROL SAFETY RELAYS 20000 FH CMR

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

27-211 20000 FH 27-24-05-720-802 FUNCTIONAL TEST OF THE YAW TRIM CONTROL SAFETY RELAYS 20000 FH CMR

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

27-412 16000 FH 27-40-15-710-801 OPERATIONAL TEST OF THE HS EMERGENCY TRIM CONTROL RELAY 16000 FH CMR

27-405 5000 FH 27-40-17-720-801 FUNCTIONAL TEST OF THE HORIZONTAL STABILIZER RELAY BOX 5000 FH CMR

27-502 1800 FH 27-50-00-720-802 FUNCTIONAL TEST OF THE FLAP ASYMMETRY DETECTION SYSTEM 1800 FH CMR A/C with DED flap control system

27-502 450 FH 27-50-00-720-802 FUNCTIONAL TEST OF THE FLAP ASYMMETRY DETECTION SYSTEM 450 FH CMR A/C with AVIAC flap control system
4500 LDG 27-53-01-350-801-01 RESTORATION OF THE FLAP SCREW JACKS (OVERHAUL) - LH OUTBOARD FLAP SCREW JACK (L502CG) 4500 LDG RetEx See note (5) P/N 1-5319-3
3500 LDG 27-53-01-350-801-02 RESTORATION OF THE FLAP SCREW JACKS (OVERHAUL) - LH INBOARD FLAP LATERAL SCREW JACK (L501CG) 3500 LDG RetEx See note (5) P/N 5318-3
3500 LDG 27-53-01-350-801-03 RESTORATION OF THE FLAP SCREW JACKS (OVERHAUL) - LH INBOARD FLAP CENTER SCREW JACK (L500CG) 3500 LDG RetEx See note (5) P/N 5318-3
3500 LDG 27-53-01-350-801-04 RESTORATION OF THE FLAP SCREW JACKS (OVERHAUL) - RH INBOARD FLAP CENTER SCREW JACK (R500CG) 3500 LDG RetEx See note (5) P/N 5318-3
3500 LDG 27-53-01-350-801-05 RESTORATION OF THE FLAP SCREW JACKS (OVERHAUL) - RH INBOARD FLAP LATERAL SCREW JACK (R501CG) 3500 LDG RetEx See note (5) P/N 5318-3

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27 : FLIGHT CONTROLS

Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks

4500 LDG 27-53-01-350-801-06 RESTORATION OF THE FLAP SCREW JACKS (OVERHAUL) - RH OUTBOARD FLAP SCREW JACK (R502CG) 4500 LDG RetEx 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) 2500 LDG RetEx 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) 750 LDG RetEx 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) 2000 LDG RetEx P/N 5318-2

27-53-01-350-802-03 UPGRADE OF THE FLAP SCREW JACKS (AVIAC) - LH INBOARD FLAP CENTER SCREW JACK (L500CG) 750 LDG RetEx 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) 2000 LDG RetEx P/N 5318-2

27-53-01-350-802-04 UPGRADE OF THE FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP CENTER SCREW JACK (R500CG) 750 LDG RetEx 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) 2000 LDG RetEx P/N 5318-2

27-53-01-350-802-05 UPGRADE OF THE FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP LATERAL SCREW JACK (R501CG) 750 LDG RetEx 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) 2000 LDG RetEx P/N 5318-2

27-53-01-350-802-06 UPGRADE OF THE FLAP SCREW JACKS (AVIAC) - RH OUTBOARD FLAP SCREW JACK (R502CG) 2500 LDG RetEx See note (2) P/N 2-5319-1 or P/N 2-5319-2

27-514 330 FH 27-53-01-720-803-01 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH OUTBOARD FLAP SCREW JACK (L502CG) 1000 LDG RetEx 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 Title / Operation First Inspection Origin Interval Remarks

27-514 330 FH 27-53-01-720-803-01 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH OUTBOARD FLAP SCREW JACK (L502CG) 2000 LDG RetEx P/N 1-5319-2

27-514 450 FH 27-53-01-720-803-01 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH OUTBOARD FLAP SCREW JACK (L502CG) 3000 LDG RetEx P/N 1-5319-3

27-514 600 LDG 27-53-01-720-803-02 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH INBOARD FLAP LATERAL SCREW JACK (L501CG) 600 LDG RetEx P/N 5318-1 or P/N 5318-1 Amdt A

27-514 630 FH 27-53-01-720-803-02 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH INBOARD FLAP LATERAL SCREW JACK (L501CG) 630 FH RetEx P/N 5318-2

27-514 450 FH 27-53-01-720-803-02 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH INBOARD FLAP LATERAL SCREW JACK (L501CG) 3000 LDG RetEx P/N 5318-3

27-514 600 LDG 27-53-01-720-803-03 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH INBOARD FLAP CENTER SCREW JACK (L500CG) 600 LDG RetEx P/N 5318-1 or P/N 5318-1 Amdt A

27-514 630 FH 27-53-01-720-803-03 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH INBOARD FLAP CENTER SCREW JACK (L500CG) 630 FH RetEx P/N 5318-2

27-514 450 FH 27-53-01-720-803-03 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH INBOARD FLAP CENTER SCREW JACK (L500CG) 3000 LDG RetEx P/N 5318-3

27-514 600 LDG 27-53-01-720-803-04 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP CENTER SCREW JACK (R500CG) 600 LDG RetEx P/N 5318-1 or P/N 5318-1 Amdt A

27-514 630 FH 27-53-01-720-803-04 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP CENTER SCREW JACK (R500CG) 630 FH RetEx P/N 5318-2

27-514 450 FH 27-53-01-720-803-04 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP CENTER SCREW JACK (R500CG) 3000 LDG RetEx P/N 5318-3

27-514 600 LDG 27-53-01-720-803-05 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP LATERAL SCREW JACK (R501CG) 600 LDG RetEx P/N 5318-1 or P/N 5318-1 Amdt A

27-514 630 FH 27-53-01-720-803-05 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP LATERAL SCREW JACK (R501CG) 630 FH RetEx P/N 5318-2

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# FALCON 900 CHAPTER 5-40

27 : FLIGHT CONTROLS

Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks

27-514 450 FH 27-53-01-720-803-05 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP LATERAL SCREW JACK (R501CG) 3000 LDG RetEx P/N 5318-3

27-514 330 FH 27-53-01-720-803-06 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH OUTBOARD FLAP SCREW JACK (R502CG) 1000 LDG RetEx P/N 2-5319-1 or P/N 2-5319-1 Amdt A

27-514 330 27-53-01-720-803-06 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH OUTBOARD FLAP SCREW JACK (R502CG) 2000 LDG RetEx P/N 2-5319-2

27-514 450 FH 27-53-01-720-803-06 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH OUTBOARD FLAP SCREW JACK (R502CG) 3000 LDG RetEx 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 Title / Operation First Inspection Origin Interval Remarks

76-200 11600 FH 28-21-13-710-801 OPERATIONAL TEST OF THE FUEL SHUT-OFF VALVES 11600 FH CMR

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 Title / Operation First Inspection Origin Interval Remarks

52-200 24 M 52-20-00-610-801-01 SERVICING OF THE EMERGENCY EXIT DOOR - TEST OF THE EMERGENCY EXIT DOOR UNLOCKING FROM INSIDE THE CABIN 24 M RetEx

52-301 8000 FH 52-30-00-710-801-02 OPERATIONAL TEST OF THE BAGGAGE COMPARTMENT DOOR - TEST OF DOOR SLIDING BOLTS 8000 FH CMR

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 Title / Operation First Inspection Origin Interval Remarks

53-053 3750 FC 53-00-00-200-803-01 INSPECTION OF THE FUSELAGE SKIN - FRAME 4 TO FRAME 30 - GENERAL VISUAL INSPECTION 11250 FC FD

53-053 3750 FC 53-00-00-200-803-02 INSPECTION OF THE FUSELAGE SKIN - FRAME 4 TO FRAME 30 - DETAILED INSPECTION IN SPECIFIC AREAS 11250 FC FD See note (6)

53-051 3750 FC 53-10-00-200-810-01 INSPECTION OF THE FUSELAGE SKIN - FRAME 0 TO FRAME 4 - GENERAL VISUAL INSPECTION 7500 FC FD See note (4)

53-051 3750 FC 53-10-00-200-810-02 INSPECTION OF THE FUSELAGE SKIN - FRAME 0 TO FRAME 4 - DETAILED INSPECTION IN SPECIFIC AREAS 11250 FC FD See note (6)

53-052 3750 FC 53-10-03-250-801 SPECIAL DETAILED INSPECTION OF THE UPPER PASSENGER DOOR FRAME EDGING 11250 FC FD

53-039 3750 FC 53-10-41-220-801 DETAILED INSPECTION OF THE ATTACHMENT FITTING OF THE NLG ACTUATOR 3750 FC FD A/C without SB F900-197

53-040 3750 FC 53-10-43-220-801 DETAILED INSPECTION OF THE STIFFENERS AT THE BOTTOM OF THE NLG WELL LH WALL 11250 FC FD A/C S/N < 189

53-055 3750 FC 53-30-00-250-801 EDDY CURRENT INSPECTION OF THE PASSENGER CABIN SKIN PANEL AROUND EMERGENCY EXIT DOOR ROUNDED ANGLES 7500 FC FD

53-054 3750 FC 53-30-00-250-802 EDDY CURRENT INSPECTION OF THE SKIN PANELS AROUND CABIN WINDOW CUT-OUTS 7500 FC FD

53-050 7500 FC 53-41-00-220-802 DETAILED INSPECTION OF THE LOWER WING ROOT BOLT RECESSES 11250 FC FD

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 Title / Operation First Inspection Origin Interval Remarks

55-050 3750 FC 55-10-00-270-801 ULTRASONIC INSPECTION OF THE HORIZONTAL STABILIZER HINGE FITTINGS 11250 FC FD

55-501 3750 FC 55-10-31-220-801 DIMENSIONAL CHECK OF HORIZONTAL STABILIZER REAR HINGE BUSHINGS 3750 FC FD A.D. N° 97-370-020

55-051 3750 FC 55-10-39-220-801 DETAILED INSPECTION OF THE HORIZONTAL STABILIZER ACTUATOR ATTACHMENT FITTINGS AND PINS 11250 FC FD

55-052 3750 FC 55-30-00-270-801 ULTRASONIC INSPECTION OF THE VERTICAL STABILIZER / STUB ATTACHMENTS 11250 FC FD

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 Title / Operation First Inspection Origin Interval Remarks

57-008 3750 FC 57-10-01-210-801 GENERAL VISUAL INSPECTION OF THE WING LOWER PANELS 11250 FC FD See note (6)

57-060 7500 FC 57-10-14-220-801 DETAILED INSPECTION OF THE WING FRONT SPAR FROM ROOT TO RIB 17 EXCEPT RIB 6 TO RIB 9 11250 FC FD See note (6)

57-070 3750 FC 57-10-14-220-802 DETAILED INSPECTION OF THE WING FRONT SPAR FROM RIB 6 TO RIB 9 11250 FC FD See note (6)

57-090 3750 FC 57-10-15-220-801 DETAILED INSPECTION OF THE WING REAR SPAR 1 FROM ROOT TO RIB 3 11250 FC FD See note (6)

57-080 7500 FC 57-10-15-220-802 DETAILED INSPECTION OF THE WING REAR SPAR 2 FROM RIB 3 TO RIB 17 11250 FC FD See note (6)

57-050 3750 FC 57-10-15-250-801 EDDY-CURRENT INSPECTION OF THE RIB 8 REAR WING SPAR SPLICE PLATE 11250 FC FD

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 Title / Operation First Inspection Origin Interval Remarks

54-050 2500 FC 71-20-02-250-801 SPECIAL DETAILED INSPECTION OF THE ENGINE 1 AND 3 FRONT MOUNTS 10000 FC FD

54-051 2500 FC 71-20-07-250-801 SPECIAL DETAILED INSPECTION OF THE ENGINE 1 AND 3 REAR MOUNTS 10000 FC FD

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 Title / Operation First Inspection Origin Interval Remarks

73-201 1640 FH 73-20-01-710-802 OPERATIONAL TEST OF THE ENGINE 1 COMPUTER STAND-BY POWER SUPPLY 1640 FH CMR

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