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FALCON 2000

MAINTENANCE MANUAL

CHAPTER 5-40

AIRWORTHINESS LIMITATIONS

ORIGINAL - JANUARY 1995

REVISION 18 - JULY 2012

DGT 113876 - PUB 653

090040008057f981 - VALIDATED - Certification Repository 
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INFORMATION TO OPERATORS

Please find enclosed Revision No. 18 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 011.
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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 EASA

Date of approval:

- Original edition: January 18, 1995

- Revision 4 DTM 544 § 5-40: November 27, 1997

- Revision 5 DTM 544 § 5-40: September 28, 1998

- Revision 6 DTM 544 § 5-40: December 20, 1999

- Revision 7 DTM 544 § 5-40: October 20, 2000

- Revision 8 DTM 544 § 5-40: July 10, 2001

- Revision 9 DTM 544 § 5-40: May 2002

- Revision 10 DTM 544 § 5-40: EASA approved under EASA.A.C.02409 on November 28, 

2005

- Revision 11 DTM 544 § 5-40: EASA approved under EASA.A.C.04543 on October 25, 

2006

- Revision 12 DGT 113876 supersedes DTM 544 § 5-40: EASA approved under 

EASA.A.C.09643 on July, 1, 2008

- Revision 13 DGT 113876 is cancelled and superseded by Revision 14

- Revision 14 DGT 113876 approved under EASA.A.C.12550 on July, 1, 2009

- Revision 15 DGT 113876

This revision 15 is the integration of the following EASA change proposal, with no further 

technical changes:

CP 003, EASA approved under EASA 10029544 on March 31, 2010

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

reference R5017. 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: October 13, 2010.

- Revision 16 DGT 113876

This revision 16 is the integration of the following EASA change proposal, with no further 

technical changes:

CP 004, EASA approved under change reference M3391

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: November 07, 2011.

- Revision 17 DGT 113876

This revision 17 is the integration of the following EASA changes proposal, with no further 

technical changes:

CP 005, EASA approved under change reference M3337

CP 008, EASA approved under change reference M3399

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

reference R5032. 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: March 28, 2012.
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- Revision 18 DGT 113876

This complete revision 18 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 011, EASA approved under change reference M3469

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

reference R5037. 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: September 21, 2012.
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B. GENERAL

This document is applicable to FALCON 2000.

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

Appendix H, paragraph H25-4 and at change 13). 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 type 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.

- Others types of operation than normal passengers 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.
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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 othervise 

specified.

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

will be which ever is reached the first.

4. List of units

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 to 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 A/C having exceeded the maximum number of landings limit at the date of

Revision 14 (Sep 16, 2009), overhaul to be done within 50 LDG.

NOTE (2): 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 750 LDG then every 330 FH or 7M.

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

outboard position.

NOTE (3): For screwjack having exceeded 2100 LDG at the effective date of the revision 16, 

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 16, upgrade to 

be done within 50 LDG.

NOTE (4): After revision 15, 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 53-024".

NOTE (5): Operations covered by zonal inspection 55-00-00-210-802- TSK and 57-00-00-

210-801- TSK scheduled every 2 Y

NOTE (6): Reserved.
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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.
FALCON 2000 

CHAPTER 5-40

21 : AIR CONDITIONING

Scheduled

maintenance

task number

Limited Title / Operation

service life

Component

Functional

Index

P/N Remark

P/N F2MA721512100 21-52-75-960-801 DISCARD OF THE DOWNSTREAM TURBOCOOLER 

CONDITIONING PIPE

3750 FC or 6 Y A/C 002-017

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FALCON 2000 

CHAPTER 5-40

27 : FLIGHT CONTROLS

Scheduled

maintenance

task number

Limited Title / Operation

service life

Component

Functional

Index

P/N Remark

20CP - pitch AAFU P/N 105045-10 27-35-07-350-801 RESTORATION OF THE PITCH AUXILIARY AFU (DISCARD OF 

BUSHINGS 1050450002)

2000 LDG

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FALCON 2000 

CHAPTER 5-40

32 : LANDING GEAR

Scheduled

maintenance

task number

Limited Title / Operation

service life

Component

Functional

Index

P/N Remark

5GA - LH MLG leg P/N D23345000-X 32-11-00-960-801-01 REPLACEMENT OF THE MLG LEGS (DISCARD OF LIFE LIMITED 

PARTS) - LH MLG LEG (5GA)

20000 LDG

10GA - RH MLG leg P/N D23346000-X 32-11-00-960-801-02 REPLACEMENT OF THE MLG LEGS (DISCARD OF LIFE LIMITED 

PARTS) - RH MLG LEG (10GA)

20000 LDG

5GB - NLG leg P/N D23332000-X 32-21-00-960-801-01 REPLACEMENT OF THE NLG LEG (DISCARD OF LIFE LIMITED 

PARTS) - NLG LEG (5GB)

20000 LDG

32-433

L220GC - LH MLG inboard P/N A34807-1

wheel

L225GC - LH MLG outboard 

wheel

R220GC - RH MLG inboard 

wheel

R225GC - RH MLG outboard 

wheel

300 LDG 32-44-15-960-801 REPLACEMENT OF THE MLG WHEEL FLANGES

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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.
FALCON 2000 

CHAPTER 5-40

05 : TIME LIMITS / MAINTENANCE CHECKS

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

05-102

05-60-00-200-801-04 CMR BASIC INSPECTION - CHECK OF MAGNETIC INDICATORS 350 FH 350 FH

05-102

05-60-00-200-801-05 BASIC INSPECTION - CHECK THE PRESSURE OF PARK BRAKE 200 FH

ACCUMULATOR

CMR 200 FH

A/C 001-141 without SB F2000-193-3

05-102

05-60-00-200-801-06 BASIC INSPECTION - OPERATIONAL TEST OF THE FEEDER 400 FH

ISOLATION VALVE

CMR 400 FH

05-102

05-60-00-200-801-07 CMR BASIC INSPECTION - CABIN WARNING TEST 200 FH 200 FH

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FALCON 2000 

CHAPTER 5-40

21 : AIR CONDITIONING

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

21-314

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

VALVES - CHECK OF OVERPRESSURE TIGHTNESS OF 

ELECTROPNEUMATIC VALVE (70HP)

CMR 1640 FH

21-314

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

VALVES - CHECK OF OVERPRESSURE TIGHTNESS OF PNEUMATIC 

VALVE (80HP)

CMR 1640 FH

21-314

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

21-32-06-720-801-01 FUNCTIONAL TEST OF THE ELECTROPNEUMATIC AND PNEUMATIC 7500 FH

VALVES - ELECTROPNEUMATIC VALVE (70HP)

CMR 7500 FH

21-32-06-720-801-02 FUNCTIONAL TEST OF THE ELECTROPNEUMATIC AND PNEUMATIC 7500 FH

VALVES - PNEUMATIC VALVE (80HP)

CMR 7500 FH

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FALCON 2000 

CHAPTER 5-40

22 : AUTO FLIGHT

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

22-106

22-13-01-350-801 CMR RESTORATION OF THE YAW DAMPER ACTUATOR (OVERHAUL) 3000 FH 3000 FH

P/N 822-1794-001

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FALCON 2000 

CHAPTER 5-40

24 : ELECTRICAL POWER

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

24-304

24-30-00-710-801 CMR OPERATIONAL TEST OF THE VOLTAGE MONITORING CIRCUITS 1800 FH 1800 FH

24-313

24-32-00-710-802 CMR CHECK OF THE BATTERY REVERSE CURRENT PROTECTION 7500 FH 7500 FH

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FALCON 2000 

CHAPTER 5-40

26 : FIRE PROTECTION

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

26-104

26-10-17-720-801 CMR FUNCTIONAL TEST OF THE PINPOINT FIRE DETECTORS 20000 FH 20000 FH

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FALCON 2000 

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 (5)

27-000

27-00-00-710-801 CMR OPERATIONAL TEST OF THE FLIGHT CONTROLS 1650 FH 1650 FH A/C not CIS aviation registered

27-000

27-00-00-710-801 CMR OPERATIONAL TEST OF THE FLIGHT CONTROLS 800 FH 800 FH A/C CIS aviation registered

27-009

27-00-00-720-804-01 CHECK OF THE AUXILIARY AFU NON-DISCONNECTION - INSPECTION 10000 FH

OF LH ROLL AAFU (L66CR)

CMR 10000 FH

27-009

27-00-00-720-804-03 CHECK OF THE AUXILIARY AFU NON-DISCONNECTION - INSPECTION 10000 FH

OF RH ROLL AAFU (R66CR)

CMR 10000 FH

27-009

27-00-00-720-804-05 CHECK OF THE AUXILIARY AFU NON-DISCONNECTION - INSPECTION 10000 FH

OF YAW AAFU (20CL)

CMR 10000 FH

27-009

27-00-00-720-804-07 CHECK OF THE AUXILIARY AFU NON-DISCONNECTION - INSPECTION 10000 FH

OF PITCH AAFU (20CP)

CMR 10000 FH

27-007

27-00-00-790-803 CMR CHECK OF THE SERVO-ACTUATOR INTERNAL DAMPING 1800 FH 1800 FH

27-104

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

27-206

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

27-409

27-40-01-350-801 RESTORATION OF THE HORIZONTAL STABILIZER ACTUATOR (FULL 7725 FC

DISASSEMBLY, INSPECTION/CHECK AND NDT)

CMR 7725 FC

27-411

27-40-15-710-801 OPERATIONAL TEST OF THE RELAY IN THE HORIZONTAL STABILIZER 16000 FH

EMERGENCY CONTROL BOX

CMR 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 450 FH 450 FH

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

OUTBOARD FLAP SCREW JACK (40CF)

RetEx 4500 LDG See note (1)

P/N 1-5319-3

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FALCON 2000 

CHAPTER 5-40

27 : FLIGHT CONTROLS

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

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

INBOARD FLAP LATERAL SCREW JACK (L25CF)

RetEx 3500 LDG See note (1)

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 (L20CF)

RetEx 3500 LDG See note (1)

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 (R20CF)

RetEx 3500 LDG See note (1)

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 (R25CF)

RetEx 3500 LDG See note (1)

P/N 5318-3

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

OUTBOARD FLAP SCREW JACK (30CF)

RetEx 4500 LDG See note (1)

P/N 2-5319-3

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

SCREW JACK (40CF)

RetEx 2500 LDG See note (3)

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 (L25CF)

RetEx 1000 LDG See note (2)

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 (L25CF)

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 (L20CF)

RetEx 1000 LDG See note (2)

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 (L20CF)

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 (R20CF)

RetEx 1000 LDG See note (2)

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 (R20CF)

RetEx 2000 LDG

P/N 5318-2

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FALCON 2000 

CHAPTER 5-40

27 : FLIGHT CONTROLS

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

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

LATERAL SCREW JACK (R25CF)

RetEx 1000 LDG See note (2)

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 (R25CF)

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 (30CF)

RetEx 2500 LDG See note (3)

P/N 2-5319-1 or

P/N 2-5319-2

27-504

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

LH OUTBOARD FLAP SCREW JACK (40CF)

RetEx 1000 LDG

P/N 1-5319-1 or

P/N 1-5319-1 Amdt A

27-504

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

LH OUTBOARD FLAP SCREW JACK (40CF)

RetEx 2000 LDG

P/N 1-5319-2

27-504

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

LH OUTBOARD FLAP SCREW JACK (40CF)

RetEx 3000 LDG

P/N 1-5319-3

27-504

27-53-01-720-803-02 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 750 LDG

LH INBOARD FLAP LATERAL SCREW JACK (L25CF)

RetEx 750 LDG

P/N 5318-1 or

P/N 5318-1 Amdt A

27-504

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 (L25CF)

RetEx 630 FH

P/N 5318-2

27-504

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 (L25CF)

RetEx 3000 LDG

P/N 5318-3

27-504

27-53-01-720-803-03 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 750 LDG

LH INBOARD FLAP CENTER SCREW JACK (L20CF)

RetEx 750 LDG

P/N 5318-1 or

P/N 5318-1 Amdt A

27-504

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 (L20CF)

RetEx 630 FH

P/N 5318-2

27-504

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 (L20CF)

RetEx 3000 LDG

P/N 5318-3

Page 23 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

CHAPTER 5-40

27 : FLIGHT CONTROLS

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

27-504

27-53-01-720-803-04 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 750 LDG

RH INBOARD FLAP CENTER SCREW JACK (R20CF)

RetEx 750 LDG

P/N 5318-1 or

P/N 5318-1 Amdt A

27-504

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 (R20CF)

RetEx 630 FH

P/N 5318-2

27-504

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 (R20CF)

RetEx 3000 LDG

P/N 5318-3

27-504

27-53-01-720-803-05 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - 750 LDG

RH INBOARD FLAP LATERAL SCREW JACK (R25CF)

RetEx 750 LDG

P/N 5318-1 or

P/N 5318-1 Amdt A

27-504

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 (R25CF)

RetEx 630 FH

P/N 5318-2

27-504

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 (R25CF)

RetEx 3000 LDG

P/N 5318-3

27-504

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

RH OUTBOARD FLAP SCREW JACK (30CF)

RetEx 1000 LDG

P/N 2-5319-1 or

P/N 2-5319-1 Amdt A

27-504

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

RH OUTBOARD FLAP SCREW JACK (30CF)

RetEx 2000 LDG

P/N 2-5319-2

27-504

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

RH OUTBOARD FLAP SCREW JACK (30CF)

RetEx 3000 LDG

P/N 2-5319-3

27-801

27-80-00-710-806 OPERATIONAL TEST OF THE GROUND / FLIGHT RELAYS AND ANGLE- 1800 FH

OF-ATTACK SENSOR CONTACTS

CMR 1800 FH

Page 24 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

CHAPTER 5-40

29 : HYDRAULIC POWER

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

29-114

29-12-05-710-801 CMR OPERATIONAL TEST OF THE HYDRAULIC SHUT-OFF VALVES 450 FH 450 FH

A/C with hydraulic shut-off valves (M0749)

Page 25 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

CHAPTER 5-40

30 : ICE AND RAIN PROTECTION

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

30-103

30-11-09-350-801 RESTORATION OF THE OUTBOARD SLAT TELESCOPIC DUCTS 2400 FH or 2000 FC

(OVERHAUL)

RetEx 2400 FH or 2000 FC

P/N 5035-400 or

P/N 5035-500

Page 26 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

CHAPTER 5-40

31 : INDICATING - RECORDING SYSTEMS

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

31-300

31-54-00-720-801 CMR FUNCTIONAL TEST OF THE TAKE-OFF SAFETIES: ALARM TEST 700 FH 700 FH

Page 27 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

CHAPTER 5-40

32 : LANDING GEAR

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

32-408

32-42-05-720-801 CMR FUNCTIONAL TEST OF THE PARK BRAKE ACCUMULATOR CAPACITY 1240 FH 1240 FH

A/C 142 and above or with SB F2000-193-

3

Page 28 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

CHAPTER 5-40

34 : NAVIGATION

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

34-324

34-31-00-720-801 CMR FUNCTIONAL TEST OF THE HGS DUAL POWER SUPPLY 1400 FH 1400 FH

Page 29 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

CHAPTER 5-40

35 : OXYGEN

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

35-920

35-20-00-720-801 CMR FUNCTIONAL TEST OF THE PASSENGER OXYGEN SYSTEM 1740 FH 1740 FH

A/C with (M1112 or M1707)

35-200

35-20-00-720-801 CMR FUNCTIONAL TEST OF THE PASSENGER OXYGEN SYSTEM 1740 FH 1740 FH

A/C without (M1112 and M1707)

Page 30 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

CHAPTER 5-40

36 : PNEUMATIC

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

36-107

36-10-05-200-801-03 INSPECTION OF THE BLEED AIR CHECK VALVES - APU CHECK VALVE 7500 FH

(130KH)

CMR 7500 FH

Page 31 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

CHAPTER 5-40

49 : AUXILIARY POWER UNIT

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

36-104

49-52-01-710-801 OPERATIONAL TEST OF THE APU BLEED AIR VALVE CLOSURE WHEN 7500 FH

ENGINE BLEED AIR VALVES ARE FAILED OPEN

CMR 7500 FH

Page 32 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

CHAPTER 5-40

52 : DOORS

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

52-205

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

Page 33 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

CHAPTER 5-40

53 : FUSELAGE

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

53-025

53-00-00-200-803-01 INSPECTION OF THE FUSELAGE SKIN - FRAME 4 TO FRAME 26 - 3750 FC

GENERAL VISUAL INSPECTION

FD 11250 FC

53-025

53-00-00-200-803-02 INSPECTION OF THE FUSELAGE SKIN - FRAME 4 TO FRAME 26 - 3750 FC

DETAILED INSPECTION IN SPECIFIC AREAS

FD 11250 FC

53-024

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

GENERAL VISUAL INSPECTION OF SKIN

FD 7500 FC See note (5)

53-024

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

53-031

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

FRAME EDGING

FD 11250 FC

53-037

53-10-39-220-802 DETAILED INSPECTION OF THE COCKPIT WINDSHIELD / WINDOW 3750 FC

FRAMES

FD 11250 FC

53-039

53-10-41-220-801-01 DETAILED INSPECTION OF THE ATTACHMENT FITTING OF THE NLG 3750 FC

ACTUATOR - FITTING

FD 3750 FC

A/C without M1647 and without M1207

53-039

53-10-41-220-801-02 DETAILED INSPECTION OF THE ATTACHMENT FITTING OF THE NLG 3750 FC

ACTUATOR - VERTICAL PANEL SUPPORTING THE FITTING

FD 11250 FC

A/C without M1647 and with SB F2000-147

53-028

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

53-027

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

WINDOW CUT-OUTS

FD 7500 FC

53-043

53-30-26-220-801 FD DETAILED INSPECTION AT FRAME 26 11250 FC 3750 FC

53-042

53-30-26-250-801-01 FD EDDY CURRENT INSPECTION AT FRAME 26 - VERTICAL BEAMS 3750 FC 3750 FC

53-042

53-30-26-250-801-02 FD EDDY CURRENT INSPECTION AT FRAME 26 - STIFFENER 17 7500 FC 3750 FC

53-042

53-30-26-250-801-03 EDDY CURRENT INSPECTION AT FRAME 26 - KEEL BEAM FLANGE 3750 FC

CONNECTION

FD 11250 FC

53-034

53-41-00-220-802 FD DETAILED INSPECTION OF THE LOWER WING ROOT BOLT RECESSES 11250 FC 3750 FC

Page 34 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

CHAPTER 5-40

53 : FUSELAGE

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

53-030

53-50-23-250-802 EDDY CURRENT INSPECTION OF THE BAGGAGE COMPARTMENT 3750 FC

SKIN PANELS AROUND DOOR LOWER ROUNDED ANGLE AT FRAME 23

FD 11250 FC

53-044

53-50-30-250-801 FD EDDY-CURRENT INSPECTION AT FRAME 30 11250 FC 3750 FC

53-045

53-50-33-250-801 FD EDDY-CURRENT INSPECTION AT FRAME 33 11250 FC 3750 FC

53-047

53-50-43-250-801 EDDY-CURRENT INSPECTION OF THE LOWER FIN FRONT SPAR 3750 FC

FLANGES

FD 11250 FC

Page 35 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

CHAPTER 5-40

54 : NACELLES AND PYLONS

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

78-321

54-14-01-210-802-01 GENERAL VISUAL INSPECTION OF THE THRUST REVERSER POD 350 FH

FAIRINGS - ENGINE 1 THRUST REVERSER

CMR 350 FH

A/C 003-028 Before SB F2000-022 

(M0808)

54-006

54-50-00-210-801 GENERAL VISUAL INSPECTION OF THE ENGINE PYLON UPPER SKIN 3750 FC

PANEL

FD 7500 FC

A/C 002-013 without M0134

Page 36 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

CHAPTER 5-40

55 : STABILIZERS

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

55-002

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 Refer to French D.G.A.C A.D. N°. 97-369-

004 (B) R1 and F.A.A. A.D. N° 99-25-09

55-003

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

ATTACHMENT FITTINGS AND PINS

FD 11250 FC

55-004

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

ATTACHMENTS

FD 11250 FC

Page 37 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

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

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

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

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

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

57-005

57-10-15-250-801 EDDY-CURRENT INSPECTION OF THE RIB 8 REAR WING SPAR SPLICE 7500 FC

PLATE

FD 11250 FC

Page 38 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

CHAPTER 5-40

71 : POWER PLANT

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

54-002

71-20-02-250-801 SPECIAL DETAILED INSPECTION OF THE ENGINE FRONT MOUNTS 3750 FC

AND FITTINGS

FD 3750 FC

54-003

71-20-07-250-801 FD SPECIAL DETAILED INSPECTION OF THE ENGINE REAR MOUNTS 11250 FC 3750 FC

Page 39 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

CHAPTER 5-40

73 : ENGINE FUEL AND CONTROL

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

71-008

73-20-05-710-801 CMR OPERATIONAL TEST OF THE HMU 1800 FH 1800 FH

71-005

73-40-00-700-801 CMR INDICATION TEST OF APR 450 FH 450 FH

71-004

73-40-00-710-801 CMR OPERATIONAL TEST OF APR 1800 FH 1800 FH

Page 40 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
FALCON 2000 

CHAPTER 5-40

78 : EXHAUST

Scheduled

maintenance

task number

Origin Title / Operation First Inspection Interval Remarks

78-316

78-32-00-760-801-01 TEST OF THE GROUND / FLIGHT RELAY AND TRCU INPUT CIRCUIT - 10000 FH

RELAY PCB (413JE)

CMR 10000 FH JAA registered A/C

78-316

78-32-00-760-801-01 TEST OF THE GROUND / FLIGHT RELAY AND TRCU INPUT CIRCUIT - 1800 FH

RELAY PCB (413JE)

CMR 1800 FH FAA registered A/C

78-316

78-32-00-760-801-02 TEST OF THE GROUND / FLIGHT RELAY AND TRCU INPUT CIRCUIT - 10000 FH

PCB (414JE)

CMR 10000 FH JAA registered A/C

78-316

78-32-00-760-801-02 TEST OF THE GROUND / FLIGHT RELAY AND TRCU INPUT CIRCUIT - 1800 FH

PCB (414JE)

CMR 1800 FH FAA registered A/C

78-316

78-32-00-760-801-03 TEST OF THE GROUND / FLIGHT RELAY AND TRCU INPUT CIRCUIT - 2670 FH

LH TRCU (L40ER)

CMR 2670 FH

P/N DS232-67

78-316

78-32-00-760-801-04 TEST OF THE GROUND / FLIGHT RELAY AND TRCU INPUT CIRCUIT - 2670 FH

RH TRCU (R40ER)

CMR 2670 FH

P/N DS232-67

Page 41 / 42

“DASSAULT AVIATION Proprietary Data”

Effectivity : ALL – Reference DGT 113876

Rev. Date : 07/2012
F2000

CHAPTER 5-40

Effectivity : ALL-Reference DGT 113876

Rev. Date : 07/2012

Page 42 / 42

“DASSAULT AVIATION Proprietary Data”

 END OF DOCUMENT