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# FALCON 2000



# MAINTENANCE MANUAL CHAPTER 5 - 40 AIRWORTHINESS LIMITATIONS ORIGINAL - J ANUARY 1995 REVISION 1 8 - JULY 201 2

DGT 11387 6 - PUB 653090040008057f981 - VALIDATED - Certification Repository

## F2000 CHAPTER 5 - 40

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Rev. Date : 0 7 /2012 Page 2 / 4 2 “DASSAULT AVIATION Proprietary Data” INFORMATION TO OPERATORS Please find enclosed Revision No. 18 of Chapter 5

- 40. Modifications and corrections contained in this revision are :

t he renumbering of tasks , the presentation of the chapter. ( The section s 05

- 40

- 00, 05

- 40

- 10, 05

- 40

- 20 and 05

- 40

- 30 are g athered in section 05

- 40

- 00 ) , t he i ntroduction of the Corrosion Prevention Control Program , t he integration of the CP 011
.

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Rev. Date : 0 7 /2012 Page 3 / 4 2 “DASSAULT AVIATION Proprietary Data” 

### This document i s 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 : 0 7 /2012 Page 4 / 4 2 “DASSAULT AVIATION Proprietary Data” 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 un der 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- Revision 13 DGT 113876 is cancelled and superseded by Revision 14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 00 8, 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.

## F2000 CHAPTER 5 - 40

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Rev. Date : 0 7 /2012 Page 5 / 4 2 “DASSAULT AVIATION Proprietary Data” - 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 0 11 , EASA approved under change reference M 3469 The technical content of this revision is approved under DOA EASA.21J.051 authority by reference R50 37 . 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 2 1 , 2012
.

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Rev. Date : 0 7 /2012 Page 6 / 4 2 “DASSAULT AVIATION Proprietary Data” 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 pe rtaining 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 s pecifies 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 modificati ons 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 wi th 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.

## F2000 CHAPTER 5 - 40

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Rev. Date : 0 7 /2012 Page 7 / 4 2 “DASSAULT AVIATION Proprietary Data” 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 ba sis, 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 passenger s 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 correspondi ng 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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Rev. Date : 0 7 /2012 Page 8 / 4 2 “DASSAULT AVIATION Proprietary Data” 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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Rev. Date : 0 7 /2012 Page 9 / 4 2 “DASSAULT AVIATION Proprietary Data” 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 wh ole 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 inspect ion 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 D ASSAULT 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 assi st in understanding the aging of the fleet and the possible need for escalation or alleviation of maintenance program.

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Rev. Date : 0 7 /2012 Page 10 / 4 2 “DASSAULT AVIATION Proprietary Data” 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 e ffective 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 for mer " 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

- 80 2

- TSK and 57

- 00

- 00

- 210

- 801

- TSK scheduled every 2 Y NOTE (6) : Reserved
.

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Rev. Date : 0 7 /2012 Page 11 / 4 2 “DASSAULT AVIATION Proprietary Data” 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 Title / Operation Limited service life Component Functional Index Remark P/N P/N F2MA721512100 21-52-75-960-801 DISCARD OF THE DOWNSTREAM TURBOCOOLER CONDITIONING PIPE 3750 FC or 6 Y A/C 002-017

Page 12 / 42

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# FALCON 2000 CHAPTER 5-40
27 : FLIGHT CONTROLS
Scheduled maintenance task number Title / Operation Limited service life Component Functional Index Remark P/N P/N 105045-10 20CP - pitch AAFU 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 Title / Operation Limited service life Component Functional Index Remark P/N P/N D23345000-X 5GA - LH MLG leg 32-11-00-960-801-01 REPLACEMENT OF THE MLG LEGS (DISCARD OF LIFE LIMITED PARTS) - LH MLG LEG (5GA) 20000 LDG

P/N D23346000-X 10GA - RH MLG leg 32-11-00-960-801-02 REPLACEMENT OF THE MLG LEGS (DISCARD OF LIFE LIMITED PARTS) - RH MLG LEG (10GA) 20000 LDG

P/N D23332000-X 5GB - NLG leg 32-21-00-960-801-01 REPLACEMENT OF THE NLG LEG (DISCARD OF LIFE LIMITED PARTS) - NLG LEG (5GB) 20000 LDG

32-433 P/N A34807-1 L220GC - LH MLG inboard wheel L225GC - LH MLG outboard wheel R220GC - RH MLG inboard wheel R225GC - RH MLG outboard wheel 32-44-15-960-801 REPLACEMENT OF THE MLG WHEEL FLANGES 300 LDG

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Rev. Date : 0 7 /2012 Page 15 / 4 2 “DASSAULT AVIATION Proprietary Data” 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 i nterval thereafter. Column 6: Remark: Note, comment or effectivity related to th e 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 Title / Operation First Inspection Origin Interval Remarks

05-102 350 FH 05-60-00-200-801-04 BASIC INSPECTION - CHECK OF MAGNETIC INDICATORS 350 FH CMR

05-102 200 FH 05-60-00-200-801-05 BASIC INSPECTION - CHECK THE PRESSURE OF PARK BRAKE ACCUMULATOR 200 FH CMR A/C 001-141 without SB F2000-193-3 05-102 400 FH 05-60-00-200-801-06 BASIC INSPECTION - OPERATIONAL TEST OF THE FEEDER ISOLATION VALVE 400 FH CMR

05-102 200 FH 05-60-00-200-801-07 BASIC INSPECTION - CABIN WARNING TEST 200 FH CMR

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# FALCON 2000 CHAPTER 5-40
21 : AIR CONDITIONING
Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks

21-314 1640 FH 21-32-06-200-801-03 INSPECTION / CHECK OF THE ELECTROPNEUMATIC AND PNEUMATIC VALVES - CHECK OF OVERPRESSURE TIGHTNESS OF ELECTROPNEUMATIC VALVE (70HP) 1640 FH CMR

21-314 1640 FH 21-32-06-200-801-04 INSPECTION / CHECK OF THE ELECTROPNEUMATIC AND PNEUMATIC VALVES - CHECK OF OVERPRESSURE TIGHTNESS OF PNEUMATIC VALVE (80HP) 1640 FH CMR

21-314 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
7500 FH 21-32-06-720-801-01 FUNCTIONAL TEST OF THE ELECTROPNEUMATIC AND PNEUMATIC VALVES - ELECTROPNEUMATIC VALVE (70HP) 7500 FH CMR 7500 FH 21-32-06-720-801-02 FUNCTIONAL TEST OF THE ELECTROPNEUMATIC AND PNEUMATIC VALVES - PNEUMATIC VALVE (80HP) 7500 FH CMR

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# FALCON 2000 CHAPTER 5-40
22 : AUTO FLIGHT
Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks

22-106 3000 FH 22-13-01-350-801 RESTORATION OF THE YAW DAMPER ACTUATOR (OVERHAUL) 3000 FH CMR P/N 822-1794-001

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# FALCON 2000 CHAPTER 5-40
24 : ELECTRICAL POWER
Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks

24-304 1800 FH 24-30-00-710-801 OPERATIONAL TEST OF THE VOLTAGE MONITORING CIRCUITS 1800 FH CMR
24-313 7500 FH 24-32-00-710-802 CHECK OF THE BATTERY REVERSE CURRENT PROTECTION 7500 FH CMR

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# FALCON 2000 CHAPTER 5-40
26 : FIRE PROTECTION
Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks

26-104 20000 FH 26-10-17-720-801 FUNCTIONAL TEST OF THE PINPOINT FIRE DETECTORS 20000 FH CMR

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# FALCON 2000 CHAPTER 5-40
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 (5)

27-000 1650 FH 27-00-00-710-801 OPERATIONAL TEST OF THE FLIGHT CONTROLS 1650 FH CMR A/C not CIS aviation registered
27-000 800 FH 27-00-00-710-801 OPERATIONAL TEST OF THE FLIGHT CONTROLS 800 FH CMR A/C CIS aviation registered

27-009 10000 FH 27-00-00-720-804-01 CHECK OF THE AUXILIARY AFU NON-DISCONNECTION - INSPECTION OF LH ROLL AAFU (L66CR) 10000 FH CMR

27-009 10000 FH 27-00-00-720-804-03 CHECK OF THE AUXILIARY AFU NON-DISCONNECTION - INSPECTION OF RH ROLL AAFU (R66CR) 10000 FH CMR

27-009 10000 FH 27-00-00-720-804-05 CHECK OF THE AUXILIARY AFU NON-DISCONNECTION - INSPECTION OF YAW AAFU (20CL) 10000 FH CMR

27-009 10000 FH 27-00-00-720-804-07 CHECK OF THE AUXILIARY AFU NON-DISCONNECTION - INSPECTION OF PITCH AAFU (20CP) 10000 FH CMR

27-007 1800 FH 27-00-00-790-803 CHECK OF THE SERVO-ACTUATOR INTERNAL DAMPING 1800 FH CMR
27-104 20000 FH 27-14-05-720-801 FUNCTIONAL TEST OF THE ROLL TRIM CONTROL SAFETY RELAYS 20000 FH CMR

27-206 20000 FH 27-24-05-720-802 FUNCTIONAL TEST OF THE YAW TRIM CONTROL SAFETY RELAYS 20000 FH CMR
27-409 7725 FC 27-40-01-350-801 RESTORATION OF THE HORIZONTAL STABILIZER ACTUATOR (FULL DISASSEMBLY, INSPECTION/CHECK AND NDT) 7725 FC CMR

27-411 16000 FH 27-40-15-710-801 OPERATIONAL TEST OF THE RELAY IN THE HORIZONTAL STABILIZER EMERGENCY CONTROL BOX 16000 FH CMR

27-405 5000 FH 27-40-17-720-801 FUNCTIONAL TEST OF THE HORIZONTAL STABILIZER RELAY BOX 5000 FH CMR
27-502 450 FH 27-50-00-720-802 FUNCTIONAL TEST OF THE FLAP ASYMMETRY DETECTION SYSTEM 450 FH CMR 4500 LDG 27-53-01-350-801-01 RESTORATION OF THE FLAP SCREW JACKS (OVERHAUL) - LH OUTBOARD FLAP SCREW JACK (40CF) 4500 LDG RetEx See note (1) P/N 1-5319-3
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# FALCON 2000 CHAPTER 5-40
27 : FLIGHT CONTROLS
Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks 3500 LDG 27-53-01-350-801-02 RESTORATION OF THE FLAP SCREW JACKS (OVERHAUL) - LH INBOARD FLAP LATERAL SCREW JACK (L25CF) 3500 LDG RetEx See note (1) 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 (L20CF) 3500 LDG RetEx See note (1) 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 (R20CF) 3500 LDG RetEx See note (1) 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 (R25CF) 3500 LDG RetEx See note (1) P/N 5318-3 4500 LDG 27-53-01-350-801-06 RESTORATION OF THE FLAP SCREW JACKS (OVERHAUL) - RH OUTBOARD FLAP SCREW JACK (30CF) 4500 LDG RetEx 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) 2500 LDG RetEx 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) 1000 LDG RetEx 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) 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 (L20CF) 1000 LDG RetEx 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) 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 (R20CF) 1000 LDG RetEx 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) 2000 LDG RetEx P/N 5318-2

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# FALCON 2000 CHAPTER 5-40
27 : FLIGHT CONTROLS
Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks 27-53-01-350-802-05 UPGRADE OF THE FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP LATERAL SCREW JACK (R25CF) 1000 LDG RetEx 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) 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 (30CF) 2500 LDG RetEx See note (3) P/N 2-5319-1 or P/N 2-5319-2 27-504 330 FH 27-53-01-720-803-01 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH OUTBOARD FLAP SCREW JACK (40CF) 1000 LDG RetEx P/N 1-5319-1 or P/N 1-5319-1 Amdt A 27-504 330 FH 27-53-01-720-803-01 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH OUTBOARD FLAP SCREW JACK (40CF) 2000 LDG RetEx P/N 1-5319-2 27-504 450 FH 27-53-01-720-803-01 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH OUTBOARD FLAP SCREW JACK (40CF) 3000 LDG RetEx P/N 1-5319-3 27-504 750 LDG 27-53-01-720-803-02 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH INBOARD FLAP LATERAL SCREW JACK (L25CF) 750 LDG RetEx P/N 5318-1 or P/N 5318-1 Amdt A 27-504 630 FH 27-53-01-720-803-02 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH INBOARD FLAP LATERAL SCREW JACK (L25CF) 630 FH RetEx P/N 5318-2 27-504 450 FH 27-53-01-720-803-02 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH INBOARD FLAP LATERAL SCREW JACK (L25CF) 3000 LDG RetEx P/N 5318-3 27-504 750 LDG 27-53-01-720-803-03 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH INBOARD FLAP CENTER SCREW JACK (L20CF) 750 LDG RetEx P/N 5318-1 or P/N 5318-1 Amdt A 27-504 630 FH 27-53-01-720-803-03 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH INBOARD FLAP CENTER SCREW JACK (L20CF) 630 FH RetEx P/N 5318-2 27-504 450 FH 27-53-01-720-803-03 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - LH INBOARD FLAP CENTER SCREW JACK (L20CF) 3000 LDG RetEx 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 Title / Operation First Inspection Origin Interval Remarks

27-504 750 LDG 27-53-01-720-803-04 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP CENTER SCREW JACK (R20CF) 750 LDG RetEx P/N 5318-1 or P/N 5318-1 Amdt A 27-504 630 FH 27-53-01-720-803-04 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP CENTER SCREW JACK (R20CF) 630 FH RetEx P/N 5318-2 27-504 450 FH 27-53-01-720-803-04 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP CENTER SCREW JACK (R20CF) 3000 LDG RetEx P/N 5318-3 27-504 750 LDG 27-53-01-720-803-05 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP LATERAL SCREW JACK (R25CF) 750 LDG RetEx P/N 5318-1 or P/N 5318-1 Amdt A 27-504 630 FH 27-53-01-720-803-05 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP LATERAL SCREW JACK (R25CF) 630 FH RetEx P/N 5318-2 27-504 450 FH 27-53-01-720-803-05 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH INBOARD FLAP LATERAL SCREW JACK (R25CF) 3000 LDG RetEx P/N 5318-3 27-504 330 FH 27-53-01-720-803-06 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH OUTBOARD FLAP SCREW JACK (30CF) 1000 LDG RetEx P/N 2-5319-1 or P/N 2-5319-1 Amdt A 27-504 330 FH 27-53-01-720-803-06 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH OUTBOARD FLAP SCREW JACK (30CF) 2000 LDG RetEx P/N 2-5319-2 27-504 450 FH 27-53-01-720-803-06 CHECK OF THE SCREW / NUT PLAY ON FLAP SCREW JACKS (AVIAC) - RH OUTBOARD FLAP SCREW JACK (30CF) 3000 LDG RetEx P/N 2-5319-3 27-801 1800 FH 27-80-00-710-806 OPERATIONAL TEST OF THE GROUND / FLIGHT RELAYS AND ANGLE- OF-ATTACK SENSOR CONTACTS 1800 FH CMR

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 Title / Operation First Inspection Origin Interval Remarks

29-114 450 FH 29-12-05-710-801 OPERATIONAL TEST OF THE HYDRAULIC SHUT-OFF VALVES 450 FH CMR 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 Title / Operation First Inspection Origin Interval Remarks

30-103 2400 FH or 2000 FC 30-11-09-350-801 RESTORATION OF THE OUTBOARD SLAT TELESCOPIC DUCTS (OVERHAUL) 2400 FH or 2000 FC RetEx 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 Title / Operation First Inspection Origin Interval Remarks

31-300 700 FH 31-54-00-720-801 FUNCTIONAL TEST OF THE TAKE-OFF SAFETIES: ALARM TEST 700 FH CMR

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 Title / Operation First Inspection Origin Interval Remarks

32-408 1240 FH 32-42-05-720-801 FUNCTIONAL TEST OF THE PARK BRAKE ACCUMULATOR CAPACITY 1240 FH CMR 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 Title / Operation First Inspection Origin Interval Remarks

34-324 1400 FH 34-31-00-720-801 FUNCTIONAL TEST OF THE HGS DUAL POWER SUPPLY 1400 FH CMR

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 Title / Operation First Inspection Origin Interval Remarks

35-920 1740 FH 35-20-00-720-801 FUNCTIONAL TEST OF THE PASSENGER OXYGEN SYSTEM 1740 FH CMR A/C with (M1112 or M1707) 35-200 1740 FH 35-20-00-720-801 FUNCTIONAL TEST OF THE PASSENGER OXYGEN SYSTEM 1740 FH CMR 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 Title / Operation First Inspection Origin Interval Remarks

36-107 7500 FH 36-10-05-200-801-03 INSPECTION OF THE BLEED AIR CHECK VALVES - APU CHECK VALVE (130KH) 7500 FH CMR

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 Title / Operation First Inspection Origin Interval Remarks

36-104 7500 FH 49-52-01-710-801 OPERATIONAL TEST OF THE APU BLEED AIR VALVE CLOSURE WHEN ENGINE BLEED AIR VALVES ARE FAILED OPEN 7500 FH CMR

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 Title / Operation First Inspection Origin Interval Remarks

52-205 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

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 Title / Operation First Inspection Origin Interval Remarks

53-025 3750 FC 53-00-00-200-803-01 INSPECTION OF THE FUSELAGE SKIN - FRAME 4 TO FRAME 26 - GENERAL VISUAL INSPECTION 11250 FC FD

53-025 3750 FC 53-00-00-200-803-02 INSPECTION OF THE FUSELAGE SKIN - FRAME 4 TO FRAME 26 - DETAILED INSPECTION IN SPECIFIC AREAS 11250 FC FD

53-024 3750 FC 53-10-00-200-810-01 INSPECTION OF THE FUSELAGE SKIN - FRAME 0 TO FRAME 4 - GENERAL VISUAL INSPECTION OF SKIN 7500 FC FD See note (5)

53-024 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

53-031 3750 FC 53-10-03-250-801 SPECIAL DETAILED INSPECTION OF THE UPPER PASSENGER DOOR FRAME EDGING 11250 FC FD

53-037 3750 FC 53-10-39-220-802 DETAILED INSPECTION OF THE COCKPIT WINDSHIELD / WINDOW FRAMES 11250 FC FD

53-039 3750 FC 53-10-41-220-801-01 DETAILED INSPECTION OF THE ATTACHMENT FITTING OF THE NLG ACTUATOR - FITTING 3750 FC FD A/C without M1647 and without M1207 53-039 3750 FC 53-10-41-220-801-02 DETAILED INSPECTION OF THE ATTACHMENT FITTING OF THE NLG ACTUATOR - VERTICAL PANEL SUPPORTING THE FITTING 11250 FC FD A/C without M1647 and with SB F2000-147 53-028 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

53-027 3750 FC 53-30-00-250-802 EDDY CURRENT INSPECTION OF THE SKIN PANELS AROUND CABIN WINDOW CUT-OUTS 7500 FC FD

53-043 3750 FC 53-30-26-220-801 DETAILED INSPECTION AT FRAME 26 11250 FC FD
53-042 3750 FC 53-30-26-250-801-01 EDDY CURRENT INSPECTION AT FRAME 26 - VERTICAL BEAMS 3750 FC FD
53-042 3750 FC 53-30-26-250-801-02 EDDY CURRENT INSPECTION AT FRAME 26 - STIFFENER 17 7500 FC FD
53-042 3750 FC 53-30-26-250-801-03 EDDY CURRENT INSPECTION AT FRAME 26 - KEEL BEAM FLANGE CONNECTION 11250 FC FD

53-034 3750 FC 53-41-00-220-802 DETAILED INSPECTION OF THE LOWER WING ROOT BOLT RECESSES 11250 FC FD

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 Title / Operation First Inspection Origin Interval Remarks

53-030 3750 FC 53-50-23-250-802 EDDY CURRENT INSPECTION OF THE BAGGAGE COMPARTMENT SKIN PANELS AROUND DOOR LOWER ROUNDED ANGLE AT FRAME 23 11250 FC FD

53-044 3750 FC 53-50-30-250-801 EDDY-CURRENT INSPECTION AT FRAME 30 11250 FC FD
53-045 3750 FC 53-50-33-250-801 EDDY-CURRENT INSPECTION AT FRAME 33 11250 FC FD
53-047 3750 FC 53-50-43-250-801 EDDY-CURRENT INSPECTION OF THE LOWER FIN FRONT SPAR FLANGES 11250 FC FD

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 Title / Operation First Inspection Origin Interval Remarks

78-321 350 FH 54-14-01-210-802-01 GENERAL VISUAL INSPECTION OF THE THRUST REVERSER POD FAIRINGS - ENGINE 1 THRUST REVERSER 350 FH CMR A/C 003-028 Before SB F2000-022 (M0808) 54-006 3750 FC 54-50-00-210-801 GENERAL VISUAL INSPECTION OF THE ENGINE PYLON UPPER SKIN PANEL 7500 FC FD 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 Title / Operation First Inspection Origin Interval Remarks

55-002 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 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 3750 FC 55-10-39-220-801 DETAILED INSPECTION OF THE HORIZONTAL STABILIZER ACTUATOR ATTACHMENT FITTINGS AND PINS 11250 FC FD

55-004 3750 FC 55-30-00-270-801 ULTRASONIC INSPECTION OF THE VERTICAL STABILIZER / STUB ATTACHMENTS 11250 FC FD

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 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
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

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

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

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

57-005 7500 FC 57-10-15-250-801 EDDY-CURRENT INSPECTION OF THE RIB 8 REAR WING SPAR SPLICE PLATE 11250 FC FD

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 Title / Operation First Inspection Origin Interval Remarks

54-002 3750 FC 71-20-02-250-801 SPECIAL DETAILED INSPECTION OF THE ENGINE FRONT MOUNTS AND FITTINGS 3750 FC FD

54-003 3750 FC 71-20-07-250-801 SPECIAL DETAILED INSPECTION OF THE ENGINE REAR MOUNTS 11250 FC FD

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 Title / Operation First Inspection Origin Interval Remarks

71-008 1800 FH 73-20-05-710-801 OPERATIONAL TEST OF THE HMU 1800 FH CMR
71-005 450 FH 73-40-00-700-801 INDICATION TEST OF APR 450 FH CMR
71-004 1800 FH 73-40-00-710-801 OPERATIONAL TEST OF APR 1800 FH CMR

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 Title / Operation First Inspection Origin Interval Remarks

78-316 10000 FH 78-32-00-760-801-01 TEST OF THE GROUND / FLIGHT RELAY AND TRCU INPUT CIRCUIT - RELAY PCB (413JE) 10000 FH CMR JAA registered A/C

78-316 1800 FH 78-32-00-760-801-01 TEST OF THE GROUND / FLIGHT RELAY AND TRCU INPUT CIRCUIT - RELAY PCB (413JE) 1800 FH CMR FAA registered A/C

78-316 10000 FH 78-32-00-760-801-02 TEST OF THE GROUND / FLIGHT RELAY AND TRCU INPUT CIRCUIT - PCB (414JE) 10000 FH CMR JAA registered A/C

78-316 1800 FH 78-32-00-760-801-02 TEST OF THE GROUND / FLIGHT RELAY AND TRCU INPUT CIRCUIT - PCB (414JE) 1800 FH CMR FAA registered A/C

78-316 2670 FH 78-32-00-760-801-03 TEST OF THE GROUND / FLIGHT RELAY AND TRCU INPUT CIRCUIT - LH TRCU (L40ER) 2670 FH CMR P/N DS232-67 78-316 2670 FH 78-32-00-760-801-04 TEST OF THE GROUND / FLIGHT RELAY AND TRCU INPUT CIRCUIT - RH TRCU (R40ER) 2670 FH CMR P/N DS232-67

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## F2000 CHAPTER 5 - 40

Effectivity : ALL

- Reference DGT 11387 6 Rev. Date : 0 7 /2012 Page 42 / 4 2 “DASSAULT AVIATION Proprietary Data” 

## END OF DOCUMENT