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# FALCON 2000EX



# MAINTENANCE MANUAL CHAPTER 5- 40 AIRWORTHINESS LIMITATIONS REVISION 9 - FEBRUARY 201 3 DGT 113877 - PUB 657/684/45409004000806a01a8 - VALIDATED - Certification Repository

# F2000EX CHAPTER 5-40

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## INFORMATION TO OPERATORS Please find enclosed Revision No. 9 of Chapter 5-40. Modifications and corrections contained in this revision are :

the introduction of the F2000LXS and F2000S Aircraft. the introduction of the CP013 (ATA 27 and 36) the introduction of the CP014 (ATA 3 2 )

# F2000EX CHAPTER 5-40

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# This document is divided into 6 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 EASA Date of approval: - Original edition : June 17, 2004 (for S/N 6 and >= 28) and April 24, 2003 (for S/N 1 to 5 and 7 to 27) - Revision 1 DGT 685: February 20, 2006 - Revision 2 DGT 685: EASA approved under EASA A.A. 01179 on June 8, 2006 (for S/N 6 and >= 28) and EASA approved under EASA A.C. 04543 on October 25, 2006 (for S/N 1 to 5 and 7 to 27) - Revision 3 DGT 113877 supersedes DGT 685 § 5-40: EASA approved under EASA.A.C.09412 on August 15, 2008

- Revision 4 DGT 113877 approved under of the authority of DOA nr. EASA.21J.051 (R5001) which incorporates CP 001 and CP 002: CP 001, EASA approved under EASA.A.C.11570 on January 26, 2009 CP 002, EASA approved under EASA.A.C.04822 on April 23, 2009 - Revision 5 DGT 113877 This revision 5 is the compilation of the following EASA changes proposal, with no further technical changes: CP 003, EASA approved under EASA 10029544 on March 31, 2010 CP 007, EASA approved under EASA 10029959 on May 06, 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: September 29, 2010. - Revision 6 DGT 113877 This revision 6 is the compilation of the following EASA changes proposal, with no further technical changes: CP 004, EASA approved under change reference M3391 CP 009, EASA approved under change reference M3551 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 7 DGT 113877 This revision 7 is the compilation 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 M3339 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.

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## Effective date of this revision: March 28, 2012.
- Revision 8 DGT 113877 This complete revision 8 is the renumbering of tasks, the presentation of the chapter, the introduction of the Corrosion Prevention Control Program. 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
- Revision 9 DGT 113877 This complete revision 9 is the compilation of the following EASA changes proposal: CP 013, EASA approved under change reference M5000 CP 014, EASA approved under change reference M3605 The introduction of the new Aircraft F2000LXS and F2000S. The technical content of this revision is approved under DOA EASA.21J.051 authority by reference R5053. 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: Mai 03, 2013.

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## B. GENERAL This document is applicable to : -FALCON 2000EX S/N 1 to 5 and 7 to 27, -FALCON 2000EX EASy versions S/N 6 and 28 to 604 including : -FALCON 2000EX with M1691 (F2000EX EASy), -FALCON 2000EX with M2846 (F2000LX), -FALCON 2000EX with M5000 (F2000LXS) S/N 263-600, -FALCON 2000EX with M3000 (F2000DX) S/N 601-604, -FALCON 2000EX with M5001 (F2000S) S/N>= 701. For aircraft equipped with Winglets (Modification M2846 (F2000LX, F2000LXS, F2000S) ) the validity of this chapter 05-40 is limited to 5000 flights. Fatigue calculations will raise this limit. New limits and associated inspections will be integrated in a future revision of chapter 05-40. 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, ...).

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## 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. 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 correspondi ng to aircraft inspections (A, B, C, etc.) .

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## 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 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 firs t. 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): Reserved NOTE (2) : Reserved NOTE (3) : Reserved NOTE (4) : Reserved 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): For A/C which exceeded 1400 FH and which did not carry out the inspection yet, inspection to be done within 400 FH from effective date of revision 7.

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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 2000EX CHAPTER 5-40 32 : LANDING GEAR Scheduled maintenance task number Title / Operation Limited service life Component Functional Index Remark P/N P/N D23733000-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 D23734000-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 D23732000 or P/N D23732000-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



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## F . MANDATORY 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 Experien ce. 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: Threshold at which the task has to be performed. Column 5: Interval: Interval at which the task is to be repeated. Column 6: Remark: Note, comment or effectivity related to the procedure/operation or its interval. The numbered notes are listed in § Notes

# FALCON 2000EX CHAPTER 5-40 21 : AIR CONDITIONING Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks
21-315 440 FH 21-32-00-710-803 OPERATIONAL TEST OF THE "CABIN" WARNING LIGHT 440 FH CMR [F2000EX]
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 2000EX CHAPTER 5-40 22 : AUTO FLIGHT Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks
22-112 3000 FH 22-13-01-350-801 RESTORATION OF THE YAW DAMPER ACTUATOR (OVERHAUL) 3000 FH CMR [F2000EX] P/N 822-1794-001



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# FALCON 2000EX CHAPTER 5-40 23 : COMMUNICATIONS Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks
23-110 1640 FH 23-11-17-710-801 OPERATIONAL TEST OF THE "VHF 1 EMERG" RADIO TUNING SWITCH 1640 FH CMR [F2000EX EASy versions and F2000S]
23-503 1640 FH 23-50-00-710-802 OPERATIONAL TEST OF THE "BKUP" AUDIO BUTTON 1640 FH CMR [F2000EX EASy versions and F2000S]
23-503 1640 FH 23-50-00-710-802 OPERATIONAL TEST OF THE "BKUP" AUDIO BUTTON 1640 FH CMR [F2000EX EASy versions and F2000S]



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# FALCON 2000EX 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 See note (6) 24-313 7500 FH 24-30-00-710-803-01 CHECK OF THE CURRENT PROTECTION OF BATTERIES 1 AND 2 AND OF ESS/MD BUSES INTERCONNECTION - CHECK OF CURRENT PROTECTION CIRCUIT BATTERY 1 (150PC) 7500 FH CMR [F2000EX EASy versions and F2000S]
24-313 7500 FH 24-30-00-710-803-02 CHECK OF THE CURRENT PROTECTION OF BATTERIES 1 AND 2 AND OF ESS/MD BUSES INTERCONNECTION - CHECK OF CURRENT PROTECTION CIRCUIT BATTERY 2 (50PC) 7500 FH CMR [F2000EX EASy versions and F2000S]
24-313 7500 FH 24-30-00-710-803-03 CHECK OF THE CURRENT PROTECTION OF BATTERIES 1 AND 2 AND OF ESS/MD BUSES INTERCONNECTION - CHECK OF ESS/MD BUSES INTERCONNECTION CONTACTOR (14PC2) 7500 FH CMR [F2000EX EASy versions and F2000S]
24-313 30000 FH 24-30-00-710-803-04 CHECK OF THE CURRENT PROTECTION OF BATTERIES 1 AND 2 AND OF ESS/MD BUSES INTERCONNECTION - CHECK OF CURRENT PROTECTION CIRCUIT FOR ESS/MD BUSES INTERCONNECTION CONTACTOR (14PC2) 30000 FH CMR [F2000EX EASy versions and F2000S]

24-332 1800 FH 24-30-00-710-804 CHECK OF "LH ISOL" AND "RH ISOL" DISCONNECTION 1800 FH CMR [F2000EX EASy versions and F2000S] See note (6) 24-337 15000 FH 24-30-00-710-805 CHECK OF "LH ISOL" AND "RH ISOL" LOGIC IN FLIGHT CONDITION 15000 FH CMR [F2000EX EASy versions and F2000S]
24-313 7500 FH 24-32-00-710-802 CHECK OF THE BATTERY REVERSE CURRENT PROTECTION 7500 FH CMR [F2000EX]



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# FALCON 2000EX 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 2000EX 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 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 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 (L25CF) 3500 LDG RetEx P/N 5318-3 

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# FALCON 2000EX CHAPTER 5-40 27 : FLIGHT CONTROLS Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks 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 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 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 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 P/N 2-5319-3 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 27-504 450 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 27-504 450 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 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 27-504 450 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 27-504 450 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 27-610 440 FH 27-61-00-720-801 FUNCTIONAL TEST OF THE AUTOMATIC AIRBRAKE EXTENSION CIRCUIT ("BSCU HARDWARE" RELAY) 440 FH CMR [F2000EX EASy versions and F2000S]
27-611 440 FH 27-61-00-720-802 FUNCTIONAL TEST OF THE AUTOMATIC AIRBRAKE EXTENSION CIRCUIT ("LH THROTTLE" and "RH THROTTLE" RELAYS) 440 FH CMR [F2000EX EASy versions and F2000S]
27-612 1240 FH 27-61-00-720-803 FUNCTIONAL TEST OF THE AUTOMATIC AIRBRAKE EXTENSION CIRCUIT ("BSCU SOFTWARE" RELAY) 1240 FH CMR [F2000EX EASy versions and F2000S]



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# FALCON 2000EX CHAPTER 5-40 27 : FLIGHT CONTROLS Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks
27-615 440 FH 27-61-00-720-806 FUNCTIONAL TEST OF THE AUTOMATIC AIRBRAKE EXTENSION CIRCUIT (MONITORING SYSTEM) 440 FH CMR [F2000EX EASy versions and F2000S]
27-616 150 FH 27-61-00-720-807 FUNCTIONAL TEST OF THE AUTOMATIC AIRBRAKE EXTENSION CIRCUIT 150 FH CMR [F2000EX]
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 [F2000EX] 440 FH 27-80-00-710-807 OPERATIONAL TEST OF SLAT EXTENSION THROUGH LH SOLENOID (S1) 440 FH CMR [F2000EX EASy versions and F2000S] A/C 263-600 and >=701 3240 FH 27-80-00-710-808 OPERATIONAL TEST OF THE SLAT MONITORING SYSTEM (INBOARD SLAT EXTENDED POSITION MICROSWITCHES) 3240 FH CMR [F2000EX EASy versions and F2000S] A/C 263-600 and >=701 1840 FH 27-80-00-710-809 OPERATIONAL TEST OF SLAT STALL 1 AND STALL 2 1840 FH CMR [F2000EX EASy versions and F2000S] A/C 263-600 and >=701 27-803 1800 FH 27-80-00-720-801 FUNCTIONAL TEST OF THE SLATS 1800 FH CMR [F2000EX EASy versions and F2000S]



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# FALCON 2000EX 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)



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# FALCON 2000EX CHAPTER 5-40 31 : INDICATING - RECORDING SYSTEMS Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks
31-501 700 FH 31-54-00-720-801 FUNCTIONAL TEST OF THE TAKE-OFF SAFETIES: ALARM TEST 700 FH CMR [F2000EX]
31-600 1640 FH 31-60-00-710-801-08 OPERATIONAL TEST OF THE CENTRAL DISPLAY SYSTEM (CDS) - REVERSION CONTROLLER (364NH) 1640 FH CMR [F2000EX EASy versions and F2000S]



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## Effectivity : ALL – Reference DGT 113877 Rev. Date : 02/2013

# FALCON 2000EX CHAPTER 5-40 32 : LANDING GEAR Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks
32-471 1650 FH 32-41-00-710-803-01 OPERATIONAL TEST OF THE AUTO-BRAKE SYSTEM 1650 FH CMR [F2000EX EASy versions] A/C 6 and 28-262 and 601-604 P/N 5527-4610 or with M3177 32-470 850 FH 32-41-00-720-803-01 FUNCTIONAL TEST OF THE AUTO-BRAKE SYSTEM - TEST OF POSITIVE COIL OF PCB 850 FH CMR [F2000EX EASy versions] A/C 6 and 28-262 and 601-604 P/N 5527-4610 or with M3177 32-470 850 FH 32-41-00-720-803-02 FUNCTIONAL TEST OF THE AUTO-BRAKE SYSTEM - TEST OF NEGATIVE COIL OF PCB 850 FH CMR [F2000EX EASy versions] A/C 6 and 28-262 and 601-604 P/N 5527-4610 or with M3177 32-470 1650 FH 32-41-00-720-803-03 FUNCTIONAL TEST OF THE AUTO-BRAKE SYSTEM - TEST OF INDICATING SYSTEM 1650 FH CMR [F2000EX EASy versions] A/C 6 and 28-262 and 601-604 P/N 5527-4610 or with M3177 32-472 6500 FH 32-41-59-710-801 OPERATIONAL TEST OF THE AUTO-BRAKE PCB'S 6500 FH CMR [F2000EX EASy versions] A/C 6 and 28-262 and 601-604 P/N 5527-4650 or with M3551 32-408 1240 FH 32-42-05-720-801 FUNCTIONAL TEST OF THE PARK BRAKE ACCUMULATOR CAPACITY 1240 FH CMR [F2000EX and F2000EX EASy versions] A/C 001-117



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## Effectivity : ALL – Reference DGT 113877 Rev. Date : 02/2013

# FALCON 2000EX CHAPTER 5-40 34 : NAVIGATION Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks
34-209 5000 FH 34-21-00-700-801-01 CHECK OF THE GENERAL-PURPOSE BUSES TO THE INERTIAL REFERENCE SYSTEM (IRS) - IRU 1 5000 FH CMR [F2000EX EASy versions and F2000S]
34-209 5000 FH 34-21-00-700-801-02 CHECK OF THE GENERAL-PURPOSE BUSES TO THE INERTIAL REFERENCE SYSTEM (IRS) - IRU 2 5000 FH CMR [F2000EX EASy versions and F2000S]
34-324 1400 FH 34-31-00-720-801 FUNCTIONAL TEST OF THE HGS DUAL POWER SUPPLY 1400 FH CMR [F2000EX]



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## Effectivity : ALL – Reference DGT 113877 Rev. Date : 02/2013

# FALCON 2000EX CHAPTER 5-40 35 : OXYGEN Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks
35-200 1740 FH 35-20-00-720-801 FUNCTIONAL TEST OF THE PASSENGER OXYGEN SYSTEM 1740 FH CMR [F2000EX]
35-200 1640 FH 35-20-00-720-801 FUNCTIONAL TEST OF THE PASSENGER OXYGEN SYSTEM 1640 FH CMR [F2000EX EASy versions and F2000S]



## Page 26 / 37 “DASSAULT AVIATION Proprietary Data” 

## Effectivity : ALL – Reference DGT 113877 Rev. Date : 02/2013

# FALCON 2000EX CHAPTER 5-40 36 : PNEUMATIC Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks 9000 FH 36-00-01-710-802 OPERATIONNAL TEST OF ARINC LINK BETWEEN BASC AND MAU 9000 FH CMR [F2000EX EASy versions and F2000S]
36-200 1800 FH 36-21-21-710-801 OPERATIONAL TEST OF THE ENGINE PYLON OVERHEAT PROBES 1800 FH CMR



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## Effectivity : ALL – Reference DGT 113877 Rev. Date : 02/2013

# FALCON 2000EX 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



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## Effectivity : ALL – Reference DGT 113877 Rev. Date : 02/2013

# FALCON 2000EX 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 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 53-052 3750 FC 53-10-11-250-801 SPECIAL DETAILED INSPECTION OF THE SPLICE AT FRAME 11 11250 FC FD 53-037 3750 FC 53-10-39-220-802 DETAILED INSPECTION OF THE COCKPIT WINDSHIELD / WINDOW FRAMES 11250 FC FD 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 53-053 3750 FC 53-50-23-250-801 SPECIAL DETAILED INSPECTION OF FRAME 23 (LH LOWER PART) 11250 FC FD 

## Page 29 / 37 “DASSAULT AVIATION Proprietary Data” 

## Effectivity : ALL – Reference DGT 113877 Rev. Date : 02/2013

# FALCON 2000EX 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 53-054 3750 FC 53-50-29-220-801 DETAILED INSPECTION OF SPLICE AT FRAME 29 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



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## Effectivity : ALL – Reference DGT 113877 Rev. Date : 02/2013

# FALCON 2000EX CHAPTER 5-40 54 : NACELLES AND PYLONS Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks
54-011 3750 FC 54-50-00-220-801 DETAILED VISUAL INSPECTION OF RIBS 29 AND 29-A 11250 FC FD



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## Effectivity : ALL – Reference DGT 113877 Rev. Date : 02/2013

# FALCON 2000EX 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 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



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## Effectivity : ALL – Reference DGT 113877 Rev. Date : 02/2013

# FALCON 2000EX 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



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## Effectivity : ALL – Reference DGT 113877 Rev. Date : 02/2013

# FALCON 2000EX CHAPTER 5-40 71 : POWER PLANT Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks
54-012 3750 FC 71-20-02-250-801 SPECIAL DETAILED INSPECTION OF THE ENGINE FRONT MOUNTS (YOKE ASSEMBLY) 7500 FC FD 11250 FC 71-20-05-350-801 RESTORATION OF THE ENGINE FRONT VIBRATION ISOLATORS (OVERHAUL) 11250 FC FD 11250 FC 71-20-09-350-801 RESTORATION OF THE ENGINE REAR VIBRATION ISOLATORS (OVERHAUL) 11250 FC FD



## Page 34 / 37 “DASSAULT AVIATION Proprietary Data” 

## Effectivity : ALL – Reference DGT 113877 Rev. Date : 02/2013

# FALCON 2000EX CHAPTER 5-40 73 : ENGINE FUEL AND CONTROL Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks
73-302 450 FH 73-40-00-700-801 INDICATION TEST OF APR 450 FH CMR 73-301 1800 FH 73-40-00-710-801 OPERATIONAL TEST OF APR 1800 FH CMR [F2000EX]



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## Effectivity : ALL – Reference DGT 113877 Rev. Date : 02/2013

# FALCON 2000EX CHAPTER 5-40 78 : EXHAUST Scheduled maintenance task number Title / Operation First Inspection Origin Interval Remarks
78-300 1800 FH 78-30-00-210-801 GENERAL VISUAL INSPECTION OF THE THRUST REVERSER 1800 FH CMR 78-350 7500 FH 78-31-03-220-801 DETAILED INSPECTION OF THRUST REVERSER PIVOT LINK ASSEMBLIES 7500 FH CMR 78-351 1800 FH 78-32-00-720-801 FUNCTIONAL TEST OF THE INHIBIT ARM COMMAND CIRCUIT 1800 FH CMR [F2000EX]
78-316 1800 FH 78-32-00-760-802 TEST OF THE TRCU CONTROL INPUT CIRCUITS 1800 FH CMR 78-349 7500 FH 78-32-45-700-801 TEST OF THE THRUST REVERSER CONTROL UNIT 7500 FH CMR



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## Effectivity : ALL – Reference DGT 113877 Rev. Date : 02/2013

# F2000EX CHAPTER 5-40

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# END OF DOCUMENT