FALCON 7X MAINTENANCE MANUAL

deleted without the concurrence of the responsible Authority With respect to the Airworthiness of the aircraft, this section is subject to approval by the "European Aviation Safety Agency". For U.S. Registered aircraft, this Airworthiness Limitations Section is FAA approved and specifies maintenance required under 14 CFR § 43.16 and 91.403, unless an alternative program has been FAA approved. Section 5-40-00: This Airworthiness Limitation Section is divided into seven paragraphs: - 1. History of revision - 2. General - 3. Instructions - 4. Notes - 5. Airframe components with a limited service life (“SAFE LIFE”). - 6. Fatigue and Damage Tolerance Airworthiness Limitations Section - 7. Certification Maintenance Requirements and Other than Fatigue Airworthiness Limitation Sections EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 7 / 71 « DASSAULT AVIATION Proprietary Data » FALCON 7X MAINTENANCE MANUAL 1. HISTORY OF REVISION Approvals: - Original Issue: EASA approved as part of the original Type Certificate A155 - Original Issue TR01: EASA approved ref A.C.07958 dated 22/October/2007 - Original Issue TR02: EASA approved ref A.C.10965 dated 25/November/2008 - Original Issue CP002: EASA approved ref A.C.12599 dated 29/July/2009 - Revision 1: EASA approved reference 10032466, Rev.1 dated 09/NOV/2010 - Revision 2: This revision is the compilation of the following EASA changes, with no further technical changes:  CP 003, approved by EASA under change reference M650. Impacted task ref: 24-31-01-350-801  CP 004, approved by EASA under change reference M1117. Impacted task ref: 57-40-00-280-804  CP 005, approved by EASA under change reference M1064. Impacted task ref: 32-60-00-710-801  CP 006, approved by EASA under change reference M1225. Impacted task ref: 32-44-17-220-802  CP 009, approved by EASA under change reference M1236. Impacted task ref: 27-40-00-710-801  CP 010, approved by EASA under change reference M1245. Impacted task ref: 27-40-00-710-801, 27-40-00-710-802 and 27-40-01-710-801. The technical content of this revision is approved under DOA EASA.21J.051 authority by reference R5018. This approval means that the revision has been prepared exclusively with already EASA approved data and is released under DOA procedures. - Revision 3: This revision is the compilation of the following EASA changes, with no further technical changes:  CP 011, approved by EASA under change reference M-OPT459. Impacted task ref: 38-16-00-710-801 and 38-16-07-710-801.  CP 014, approved by EASA under change reference M1256. Impacted task ref: 32-44-17-220-802. Task 26-20-01-720-803 inadvertently erased in previous publication and put back in this revision. The technical content of this revision is approved under DOA EASA.21J.051 authority by reference R5025. This approval means that the revision has been prepared exclusively with already EASA approved data and is released under DOA procedures. Effective Date of This Chapter 5-40: 15/OCT/2012 EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 8 / 71 « DASSAULT AVIATION Proprietary Data » FALCON 7X MAINTENANCE MANUAL - Revision 4: This revision is the compilation of the following EASA approved changes, with no further technical changes:  CP 016, approved by EASA under change reference M0854.  CP 012, approved by EASA under change reference M-opt 686  CP 022, approved by EASA under change reference M1566. 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 Chapter 5-40: 11/MAR/2015. - Revision 5: This revision is the compilation of the following EASA approved changes, with no further technical changes:  CP 017, approved by EASA under change reference M1285  CP 019, approved by EASA under change reference M1453  CP 020, approved by EASA under change reference M1454  CP 025, approved by EASA under change reference M1000  CP 026, approved by EASA under change reference M1000  CP 027, approved by EASA under change reference M1254 The technical content of this revision is approved under DOA EASA.21J.051 authority by reference R5089. 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 Chapter 5-40: 31/DEC/2016 - Revision 6: This revision is the compilation of the following EASA approved changes, with no further technical changes:  CH5-40-CP0002: F7X/F8X - Chapter 5-40 data substantiation for M1721 - F8X - steep approach capability  LSA-CP0187: LSA data impact related to 5-40 update : Extension of SDET RIB26 for A/C without M1117 This revision is also the compilation of the following changes approved under DOA EASA.21J.051 authority, with no further technical changes:  LSA-CP0119: LSA data related to PSA 05-00-15: update of scheduled maintenance for emergency lights due to harmonization  LSA-CP0189: LSA data impact related to 5-40 update - Changes introduced in Section 7 of Chap 5-40 Rev 6 The technical content of this revision is approved under DOA EASA.21J.051 authority by reference R5122. 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 Chapter 5-40: 01/SEPT/2018 EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 9 / 71 « DASSAULT AVIATION Proprietary Data » FALCON 7X MAINTENANCE MANUAL - Revision 7: This revision is exclusively a correction of revision 6 for task 27-91-05-710- 801. The technical content of this revision is approved under DOA EASA.21J.051 authority by reference R5123. This approval means that the revision has been prepared exclusively with already EASA approved data and is released under DOA procedures. As this revision is a correction, exceptionally, modifications of both revision 6 and revision 7 are tracked in magenta color. Effective Date of This Chapter 5-40: 01/NOV/2018 - Revision 8: This revision is the compilation of the following EASA approved changes, with no further technical changes:  LSA-CP0212: LSA data impact related to modification 5-40 - NLG fatigue This revision is also the compilation of the following changes approved under DOA EASA.21J.051 authority, with no further technical changes:  LSA-CP0231: LSA data impact related to 5-40 update - Engine mount isolators life limit  LSA-CP0235: LSA data impact related to 5-40 update - extension of operational test of the HSTA TRIM EMERG Control  LSA-CP0239: LSA data impact related to 5-40 update - changes introduced in Chap. 5-40 rev 8 The technical content of this revision is approved under DOA EASA.21J.051 authority by reference R5126. 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 Chapter 5-40: 01/SEPT/2019 - Revision 9: This revision is the compilation of the following EASA approved changes, with no further technical changes:  LSA-CP0041: LSA data impact related to 5-40 update – Change on sections 5 and 6 of Chap 5-40 manual This revision is also the compilation of the following changes approved under DOA EASA.21J.051 authority, with no further technical changes:  LSA-CP0338: LSA data impact related to minor update on 5-40 linked to LSA- CP0041 The technical content of this revision is approved under DOA EASA.21J.051 authority by reference R5141. 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 Chapter 5-40: 01/SEPT/2020 EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 10 / 71 « DASSAULT AVIATION Proprietary Data » FALCON 7X MAINTENANCE MANUAL - Revision 10: This revision is the compilation of the following EASA approved changes, with no further technical changes:  LSA-CP0208 – LSA data impact related to modification Ch 5-40 - F7X M1944 - Fuselage fuel tank draining optimization for Falcon 7X  LSA-CP0280 –LSA data impact related to 5-40 update – Fuel characteristic and pressure sensors on F8X  LSA-CP0342 – LSA data impact related to update on 5-40 linked to Decomatic This revision is also the compilation of the following changes approved under DOA EASA.21J.051 authority, with no further technical changes:  LSA-CP0358 – LSA data impact related to 5-40 update - Minor modification for June 2021 revision The technical content of this revision is approved under DOA EASA.21J.051 authority by reference R5146. 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 Chapter 5-40: 07/SEPT/2021 - Revision 11: This revision is the compilation of the following EASA approved changes, with no further technical changes:  LSA-CP0373 – LSA data impact related to modification Ch 5-40 – LSA data impact related to 5-40 update linked to M2083 – PINTLE PIN LIFE LIMITE EXTENSION  LSA-CP0374 – LSA data impact related to modification Ch 5-40 - LSA data impact related to 5-40 update linked to M1882 - NEW PROTECTION PLAN FOR STRUCTURE PART EXCEPTIONS OF M1662 OAS This revision is also the compilation of the following change approved under DOA EASA.21J.051 authority, with no further technical changes: LSA-CP0386 – LSA data impact related to 5-40 update - Minor modification without technical change on Task 35-10-01-350-801 Restoration (Overhaul) of, the Crew Oxygen Masks Regulators, Goggles and Stowage Boxes. The technical content of this document is approved under the authority of the DOA ref. EASA.21J.051. Reference for Rev 11 is R5153. 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 Chapter 5-40: 07/SEPT/2022 EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 11 / 71 « DASSAULT AVIATION Proprietary Data » FALCON 7X MAINTENANCE MANUAL 2. GENERAL A. DESIGN SERVICE GOAL This document is applicable to: - F7X without M1000 S/N 001 to 400 - F7X with M1000 (F8X) S/N 401 to 999. Falcon 8X is a version of the Falcon 7X model on which modification package M1000 has been applied. The Design Service Goal (DSG) for all Falcon 7X without M1000 is 20,000 flight cycles/50,000 flight hours, whichever occurs first. For F7X with M1000 (F8X), the validity of this chapter 05-40 is temporarily limited to 4000 FC. Fatigue calculations and qualification tests will raise this limit. New limits and associated inspections will be integrated in a future revision of chapter 05-40. B. DEFINITION OF A STANDARD AIRCRAFT a) FATIGUE LOAD SPECTRUM Aircraft operations should be close to the fatigue load spectra defined during type certification. These spectra correspond to public or private transport defined by short, middle and long distance flights. Non standard Aircraft: when types of mission listed hereafter are performed on a regular basis, the aircraft cannot 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 - Unpaved runway Take-off and Landing b) PRIMARY STRUCTURE CHANGES Standard Aircraft Primary structure must be entirely identical to DASSAULT AVIATION type design: Condition of the Principal Structure Elements (P.S.E.) of a standard aircraft has to correspond to definition at aircraft delivery: - which can be supplemented by any DASSAULT AVIATION Service Bulletins (SB) or DASSAULT AVIATION approved repair EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 12 / 71 « DASSAULT AVIATION Proprietary Data » FALCON 7X MAINTENANCE MANUAL - which must have implemented the applicable Airworthiness Directives (AD). Non standard Aircraft: an aircraft cannot be considered as a standard aircraft if its primary structure has been changed by a STC or repaired through a definition not reviewed by DASSAULT AVIATION in the frame of the applicability of these instructions. c) MAINTENANCE The maintenance of a Standard Aircraft must be performed in accordance with: - either Maintenance Manual and Structural Repair Manual - or other approved maintenance procedures. NOTE: For non-standard aircraft, this program needs to be supplemented with Instructions for Continued Airworthiness developed to cover the non-standard features (STC, repairs, operating conditions,…) up to the DSG. C. CDCCL and CPCP Programs a) CDCCL: DEFINITION AND PRINCIPLES Critical Design Configuration Control Limitations (CDCCL): As applied to Fuel Tank safety policy, this term refers to a feature of the fuel system design the integrity of which must be maintained to ensure that unsafe conditions do not develop. Features in an aircraft installation or component that must be retained during modification, change, repair, or scheduled maintenance characterize CDCCL. These features may exist in the fuel system and its related installation or in systems that could, if a failure condition were to develop, interact with the fuel system in such a way that an unsafe condition would develop in the fuel system. Information necessary to maintain those design features that have been defined in the original type design to preclude ignition sources is essential to ensure that maintenance, repairs or modifications do not unintentionally violate the integrity of the original fuel system type design. The CDCCL are listed in the followings as Airworthiness Limitation Items. Some are not inspections or life-limited items, as are most existing Airworthiness Limitation Items. They are features usually controlled by having operators (or, where necessary, holders of type certificates or supplemental type certificates) develop appropriate procedures. b) CORROSION PREVENTION and CONTROL PROGRAM (CPCP) 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). EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 13 / 71 « DASSAULT AVIATION Proprietary Data » FALCON 7X MAINTENANCE MANUAL In order to control the aircraft structure to corrosion level 1 or better on PSE’s, the operator must implement a CPCP into his respective maintenance program. As a guideline to help operator to implement a CPCP, Dassault Aviation provides a Chapter 5-15 (baseline) which compiles all the Dassault Aviation maintenance recommendations (inspections and their thresholds) required for a standard aircraft. All these chapter 5-15 operations are scheduled in Chapter 5.10 and 5.20 (If the operator’s maintenance program is compliant with chapter 5-10 and chapter 5-20 operations and intervals, it is compliant with the chapter 5-15 recommendations). In accordance with the airworthiness mandate for CPCP inclusion in the operator’s maintenance program, it is the operator’s responsibility to take into account ‘non standard‘ features, such as STC’s, repairs,…etc., and add appropriate supplemental CPCP instructions for continued airworthiness to his specific maintenance program. 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. D. IMPORTANT The instructions contained in this document must be imperatively observed by the operators. The mandatory nature of these instructions does not in any way reduce the importance of the other tasks coming from MSG-3 analyses or listed in the Maintenance Planning Document (Chapter 5) which must be carried out in agreement with the National Airworthiness Authorities. The section 5-40 gives mandatory limits. In order to help operators to plan their maintenance program and to reduce grounding due to scheduled maintenance, these mandatory operations are also listed in the MPD (5-10, 5-20) with recommended periodic values lower than or equal to the mandatory limits, corresponding to the aircraft inspections or expressed as a year, month, flight hour or flight cycle. Operations which have two limits (flight/cycles and calendar) are due at the first reached limit. E. UPDATING OF SECTION 5-40-00 When a new maintenance operation is derived from a revision of Chapter 5 section 5- 40-00, this operation must be performed when the time at which it is scheduled falls due. If the limit has been passed, the operation is due immediately unless otherwise specified. F. LIST OF UNITS The units and their equivalent abbreviations used in this document are listed hereafter: - Y: Year - M: Month - FH: Flight Hour - FC: Flight Cycle FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 14 / 71 « DASSAULT AVIATION Proprietary Data » 3. INSTRUCTIONS A. INSTRUCTIONS FOR CDCCL Note: Any changes to CDCCL items may lead to the development of unsafe conditions, so particular attention shall be paid by the operator to all non DASSAULT AVIATION changes concerning these features. Some CDCCL are attached to scheduled maintenance and are mandated by section 7 table (CDCCL in column ‘origin’). The following table indicates the other maintenance procedures that are affected by CDCCL. Only some instructions inside the procedure are mandatory under chapter 5- 40. These instructions are clearly identifiable in the Maintenance Procedures (MPs) text as follows: "Start of Fuel Tank Safety Critical Section …/…. (instructions of CDCCL) …/…. End of Fuel Tank Safety Critical Section" In addition, aircraft applicability is noted in the “Effectivity” column. If a component is applicable to one version only (for example [F7X without M1000]), the applicability is specified between [ ]. If there is no dedicated aircraft identified in this column, the MP is applicable to all F7X aircraft versions. Reference of the MPs that include the Mandated CAUTION Ref Title CDCCL (feature) Effectivity 20-95-00-200-801 INSPECTION OF WIRING ROUTING AND SEGREGATION Respects of : FQIS wiring segregation Feeder versus fuel pipe routing segregation 28-00-00-910-802 ACCEPTANCE CRITERIA FOR FUEL LEAKS Fuel Leakage 28-21-01-900-801 REMOVAL / INSTALLATION OF THE BOOSTER PUMPS Bonding quality Connectors conditions / corrosion Cracks of insulation 28-21-05-900-801 REMOVAL / INSTALLATION OF THE BOOSTER PUMP 1, 2 AND 3 MANIFOLDS Bonding quality Connectors conditions / corrosion Cracks of insulation 28-21-17-900-801 REMOVAL / INSTALLATION OF THE APU FUEL SHUT-OFF VALVE Bonding quality Connectors conditions / corrosion Cracks of insulation [F7X without M1000] 28-21-21-900-801 REMOVAL / INSTALLATION OF THE APU FUEL SHUT-OFF VALVE ACTUATOR Bonding quality Connectors conditions / corrosion Cracks of insulation [F7X without M1000] FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 15 / 71 « DASSAULT AVIATION Proprietary Data » Reference of the MPs that include the Mandated CAUTION Ref Title CDCCL (feature) Effectivity 28-21-25-900-801 REMOVAL / INSTALLATION OF THE LH AND RH CROSSFEED UNITS Bonding quality Connectors conditions / corrosion Cracks of insulation [F7X without M1000] 28-22-01-900-801 REMOVAL / INSTALLATION OF THE WING TANK CROSS VALVE (XTK) Bonding quality Connectors conditions / corrosion Cracks of insulation [F7X without M1000] 28-41-09-900-801 REMOVAL / INSTALLATION OF THE WING FUEL GAUGING PROBES Bonding quality Connectors conditions / corrosion Cracks of insulation 28-50-05-900-801 REMOVAL / INSTALLATION OF THE HIGH- LEVEL SENSORS Bonding quality Connectors conditions / corrosion Cracks of insulation 28-50-17-900-801 REMOVAL / INSTALLATION OF THE GRAVITY REFUELING PLUGS Bonding quality Connectors conditions / corrosion Cracks of insulation 28-70-03-900-801 REMOVAL / INSTALLATION OF THE FUEL TANK PRESSURE SENSOR - FUEL TANK PRESSURE SENSOR (608QJ) Bonding quality Connectors conditions / corrosion Cracks of insulation [F7X with M1000] 53-40-05-900-801 REMOVAL / INSTALLATION OF THE CENTER FUEL TANK RODS Bonding quality Connectors conditions / corrosion Cracks of insulation B. INSTRUCTIONS FOR CPCP Operators are mandated to report any CPCP finding 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 ageing of the fleet and the possible need for escalation or alleviation of maintenance program. FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 16 / 71 « DASSAULT AVIATION Proprietary Data » 4. NOTES The following notes are used in the following tables: Note (1): This task must be performed on components. The value of the interval given for each component considers its cumulated presence on one or several aircraft. Unless specified (APU-H for example), the unit of the interval is expressed in measurable aircraft level figures (aircraft flight hours, aircraft cycles or age) and not in component operating time. Note (2): Grace delay for brakes that have exceeded 400FC at the effective date of revision 4:  If the inspection was performed as per section 5-20 within the preceding 400FC: the next inspection is due at the end of the 400FC interval.  If the inspection was not performed within the preceding 400FC, the inspection is due within 20 FC. Note (3): Part procurable only through an approved repair agent Note (4): The 20000FC limitation is applicable to the indicated P/N and to its sub- components except – if any – for indented component identification shown on the following line(s) which have a specific, lower limitation. Note (5): “Limited service life” is temporarily limited to 4000FC. This limit will be raised as soon as fatigue calculations and qualification tests results will be finished. Note (6): The fatigue damage on the component is 1.3 times higher on F7X with M1000 than on F7X without M1000. If you install the PIN TRUNNION P/N 55-2322008-00 from F7X with M1000 on F7X without M1000, you must multiply the number of FC performed on F7X with M1000 by 1.3 to obtain the equivalent number of FC accumulated by this part on F7X without M1000. If you install the PIN TRUNNION P/N 55-2322008-00 from F7X without M1000 on F7X with M1000, you must divide the number of FC performed on F7X without M1000 by 1.3 to obtain the equivalent number of FC accumulated by this part on F7X with M1000. FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 17 / 71 « DASSAULT AVIATION Proprietary Data » 5. AIRFRAME COMPONENTS WITH LIMITED SERVICE LIFE (“SAFE LIFE”) For Falcon 7X without M1000, fatigue and qualification tests have demonstrated the whole DSG. For Falcon 7X without M1000, this ALS issue lists the aircraft components and structural parts with life limits that are below or equal to 20,000FC/50,000FH. For Falcon 7X with M1000, fatigue and qualification tests have demonstrated 4000 FC. For Falcon 7X with M1000, this ALS issue lists the aircraft components and structural parts with life limits that are below or equal to 4000 FC. Additional fatigue and qualification tests will be performed to demonstrate the whole DSG. This list refers only to installations designed or approved by DASSAULT AVIATION and incorporated in the aircraft type design. Other changes such as STC’s or any major change not approved by the aircraft manufacturer, or change of the type of operation, which may have an impact on the service life of the airframe components, are not included in this document. If an operator installs a secondhand main structural part (example: landing gear or landing gear sub-components), he must note on the aircraft logbook the number of flights or landings accumulated by this part since manufacturing. He must ensure that, during operation, the service life limit of this part, indicated in chapter 5-40, will not be exceeded. In the following charts, some P/N appear with -x (i.e. 10-230201- x) or with the term “and subsequent” (i.e. 10-232101-002 and subsequent). These – x or “and subsequent” are in place of any figures or numbers. This is to avoid a too long list of P/N and numerous updates; and it is sufficient to identify the P/N to be traced. In addition, aircraft applicability is noted in the “Note/Effectivity” column. If a component is applicable to one version only (for example [F7X without M1000]), the applicability is specified between [ ]. If there is no dedicated aircraft identified in this column, the component is applicable to all F7X aircraft versions. FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 18 / 71 « DASSAULT AVIATION Proprietary Data » Aircraft components with limited service life COMPONENT IDENTIFICATION PART NUMBER LIMITED SERVICE LIFE NOTE/ EFFECTIVITY 27 FLIGHT CONTROL Aileron servo actuator 103152-12 20000FC / 50000FH For [F7X with M1000], Refer to Note (5) Rudder servo actuator 103153-05 20000FC / 50000FH For [F7X with M1000], Refer to Note (5) Elevator servo actuator 103154-16 20000FC / 50000FH For [F7X with M1000], Refer to Note (5) HSTA 021173-xx 20000FC / 50000FH For [F7X with M1000], Refer to Note (5) Slat actuator 106136-02 20000FC / 50000FH For [F7X with M1000], Refer to Note (5) Slat actuator 106138-02 106139-02 106140-03 106141-03 20000FC / 50000FH [F7X without M1000] Slat actuator 106150-01 106151-01 106152-01 106153-01 4000 FC [F7X with M1000] Refer to Note (5) Spoiler actuator 106137-01 20000FC / 50000FH For [F7X with M1000], Refer to Note (5) 32 LANDING GEAR NOSE LANDING GEAR  NOSE LANDING GEAR DRESSED 10-230201-xxx 20000 FC Note (4) FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 19 / 71 « DASSAULT AVIATION Proprietary Data » COMPONENT IDENTIFICATION PART NUMBER LIMITED SERVICE LIFE NOTE/ EFFECTIVITY o RACK 55-2303019-00 8000 FC Note (3)  NLG DRAG BRACE 10-232101-xxx 20000 FC Note (4) o UPPER ARM BUSHED 30-2322001-00 8000 FC [F7X without M1000] A/C without M1320 Note (3) o PIN TRUNNION 55-2322008-00 20000 FC [F7X without M1000] Note (3), Note (6) 55-2322008-00 15400 FC [F7X with M1000] Note (3), Note (6)  NLG UPLOCK 10-234101-xxx 20000 FC Note (4) MAIN LANDING GEAR  MAIN LANDING GEAR DRESSED 10-235301- xxx (LH) 10-235302- xxx (LH) 10-235401- xxx (RH) 10-235402- xxx (RH) 20000 FC [F7X without M1000] Note (4) 10-482301-xxx (LH) 10-482401-xxx (RH) 4000 FC [F7X with M1000] Note (4) o TRAILING ARM-AXLE 30-2355002-00 30-2355078-00 11000 FC [F7X without M1000] A/C without M322 o PIN MAIN FTG TO SHOCK STRUT 55-2355013-00 15000 FC [F7X without M1000] A/C without M322 o PINTLE PIN 55-2355007-01 7300 FC [F7X without M1000] 55-4825006-00 55-4825006-01 6000 FC [F7X with M1000]  MLG FOLDING BRACE 10-238101- xxx (LH) 10-238201- xxx (RH) 20000 FC [F7X without M1000] Note (4) 10-485101- xxx (LH) 10-485201- xxx (RH) 4000 FC [F7X with M1000] Note (4)  MLG UPLOCK 10-240101- xxx 20000 FC [F7X without M1000] Note (4) 10-240101- 005 and subsequent 4000 FC [F7X with M1000] Note (4) FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 20 / 71 « DASSAULT AVIATION Proprietary Data » COMPONENT IDENTIFICATION PART NUMBER LIMITED SERVICE LIFE NOTE/ EFFECTIVITY  MLG MAIN DOOR UPLOCK 10-250501- xxx (LH) 10-250601- xxx (RH) 20000 FC [F7X without M1000] Note (4) 10-250501- 004 (LH) and subsequent 10-250601- 004 (RH) and subsequent 4000 FC [F7X with M1000] Note (4)  MLG RETRACT ACTUATOR 10-239701-xxx (LH) 10-239801-xxx (RH) 20000 FC [F7X without M1000] Note (4) 10-239701-002 (LH) and subsequent 10-239801-002 (RH) and subsequent 4000 FC [F7X with M1000] Note (4) o CYLINDER 30-2399001-00 (LH) 30-2400001-00 (RH) 15700 FC [F7X without M1000] A/C without M323 Note (3) 53 FUSELAGE T34: Rear tank upper panel FR 27 to FR 28 F7XC258420B1 4000 FC A/C 002-077 without SB F7X-032 T5 - Frame 37 upper blind fasteners (fasteners as per M625) 4000 FC A/C 004-006 without SB F7X-012 T5 - Frame 37 gusset (as per M626) 4000 FC A/C 004-006 without SB F7X-012 Connection between main landing gear actuator door fitting and the landing gear bay lateral web (as per M571) 12100 FC A/C 005-014 without SB F7X-003 Front lower T34 stringer 15 at finger doubler crossing area (as per M452) 6000 FC A/C 005-010 without SB F7X-002 Fuselage – Fuselage reinforcement at Frame 36 LH side (as per M1182) 4000 FC A/C 006-151 without SB F7X-191 FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 21 / 71 « DASSAULT AVIATION Proprietary Data » 6. FATIGUE AND DAMAGE TOLERANCE AIRWORTHINESS LIMITATIONS A list of inspections has been raised based on calculations and on structural fatigue and damage tolerance tests. For Falcon 7X without M1000 only, the inspections whose calculated threshold is equal to or lower than the Design Service Goal have been retained in this Chapter 5-40 (see note). Note: This list of mandatory inspections will have to be updated when Falcon7X obtains the approval for an Extended Service Goal beyond 20,000FC. For Falcon 7X with M1000, there is no inspections since this aircraft is temporarily limited to 4000FC. Additional calculations and fatigue and damage tolerance tests will be performed to demonstrate the whole DSG. 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. - Column 2: Origin: The origin of these mandatory maintenance operations is ALI/FD (Airworthiness LImitations from Fatigue and Damage tolerances) - Column 3: Title / Operation: 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 section 4. FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 22 / 71 « DASSAULT AVIATION Proprietary Data » 05: TIME LIMITS / MAINTENANCE CHECKS Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 05-32-50-210-801-01 ALI/FD GENERAL VISUAL INSPECTION OF THE T34 AND T5 SECTIONS OUTER SIDE 12100 FC 4000 FC [F7X without M1000] 05-32-72-200-802 ALI/FD INSPECTION OF THE BAGGAGE COMPARTMENT 12100 FC 4000 FC [F7X without M1000] 05-38-00-210-801-01 ALI/FD GENERAL VISUAL INSPECTION OF THE PASSENGER, BAGGAGE COMPARTMENT, EMERGENCY EXIT AND SERVICING COMPARTMENT DOORS 4000 FC 4000 FC [F7X without M1000] FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 23 / 71 « DASSAULT AVIATION Proprietary Data » 52: DOORS Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 52-30-00-200-801-04 ALI/FD VISUAL INSPECTION OF THE BAGGAGE COMPARTMENT DOOR - INSPECTION OF THE BAGGAGE COMPARTEMENT DOOR 8000 FC 4000 FC [F7X without M1000] FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 24 / 71 « DASSAULT AVIATION Proprietary Data » 53: FUSELAGE Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 53-00-00-270-803-01 ALI/FD SPECIAL DETAILED INSPECTION (ULTRASONIC) OF DECOMATIC SCREWS IN FUSELAGE AREA 4000 FC 4000 FC [F7X with M1000] A/C 404-412 and 416-446 53-00-00-270-803-01 ALI/FD SPECIAL DETAILED INSPECTION (ULTRASONIC) OF DECOMATIC SCREWS IN FUSELAGE AREA 4000 FC 4000 FC [F7X without M1000] A/C 272-283 53-00-00-280-801 ALI/FD EDDY-CURRENT INSPECTION OF THE SKIN AT STRINGER 15 LOWER SEAMS 4400 FC 4400 FC [F7X without M1000] A/C 005-010 without SB F7X-002 53-10-00-200-809 ALI/FD DETAILED FATIGUE INSPECTION OF T12 FUSELAGE 12100 FC 4000 FC [F7X without M1000] FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 25 / 71 « DASSAULT AVIATION Proprietary Data » 53: FUSELAGE Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 53-10-00-200-816 ALI/FD FATIGUE INSPECTION OF BRACKETS AND STRINGERS BETWEEN FRAME 9 TO 12 12100 FC 8000 FC [F7X without M1000] 53-10-00-280-801 ALI/FD SPECIAL DETAILED INSPECTION OF FASTENERS ON FRAME 9 OUTBOARD FLANGE 12100 FC 4000 FC [F7X without M1000] 53-10-00-280-802 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION (HFEC) FROM OUTSIDE OF THE TOP AND BOTTOM RADIUSES OF THE WINDSHIELD RETAINERS AT THE LH AND RH REAR ARCHES 12100 FC 4000 FC [F7X without M1000] 53-10-00-280-804 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF FASTENERS ON FRAME 8 OUTBOARD FLANGE 12100 FC 4000 FC [F7X without M1000] FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 26 / 71 « DASSAULT AVIATION Proprietary Data » 53: FUSELAGE Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 53-10-01-220-801 ALI/FD DETAILED FATIGUE INSPECTION OF FRAME 1 AT THE JUNCTION WITH AVIONIC FRONT RACK FITTINGS BEAMS AND STIFFENERS 12100 FC 8000 FC [F7X without M1000] 53-30-00-200-804 ALI/FD FATIGUE INSPECTION OF SECTION T34 INNER SIDE 12100 FC 4000 FC [F7X without M1000] 53-30-00-200-805 ALI/FD FATIGUE INSPECTION OF SECTION T34 OUTER SIDE 12100 FC 4000 FC [F7X without M1000] 53-30-00-200-806 ALI/FD FATIGUE INSPECTION OF THE PANEL OUTER SKIN AT THE FOUR CUT-OUT CORNERS 12100 FC 4000 FC [F7X without M1000] FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 27 / 71 « DASSAULT AVIATION Proprietary Data » 53: FUSELAGE Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 53-30-00-280-801 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION (HFEC) OF THE EMERGENCY EXIT SURROUNDING 12100 FC 4000 FC [F7X without M1000] 53-40-00-200-810-01 ALI/FD INSPECTION OF THE CENTER WING LOWER PANEL FROM FR20 TO FR26 8000 FC 4000 FC [F7X without M1000] A/C with M1944 53-40-00-200-810-01 ALI/FD INSPECTION OF THE CENTER WING LOWER PANEL FROM FR20 TO FR26 12100 FC 4000 FC [F7X without M1000] A/C without M1944 53-40-00-220-803 ALI/FD DETAILED FATIGUE INSPECTION OF THE FUSELAGE LOWER SECTION - SPLICE AREA BETWEEN FRONT CENTER AND REAR LOWER PANELS 8000 FC 4000 FC [F7X without M1000] FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 28 / 71 « DASSAULT AVIATION Proprietary Data » 53: FUSELAGE Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 53-40-00-280-805-01 ALI/FD SPECIAL DETAILED INSPECTION OF UPPER PANEL BETWEEN FR26 AND FR28 - SDI OF THE FUEL BAY AND REAR FUEL TANK UPPER PANEL STIFFENERS TOPS IN FRONT OF AND BEHIND FRAME 27 4000 FC 4000 FC [F7X without M1000] A/C 002-077 and without SB 7X-032 53-40-00-280-805-01 ALI/FD SPECIAL DETAILED INSPECTION OF UPPER PANEL BETWEEN FR26 AND FR28 - SDI OF THE FUEL BAY AND REAR FUEL TANK UPPER PANEL STIFFENERS TOPS IN FRONT OF AND BEHIND FRAME 27 12100 FC 8000 FC [F7X without M1000] A/C 002-077 with SB 7X-032 or A/C 078- 400 53-40-00-280-808 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION (HFEC) OF THE FUEL BAY UPPER PANEL (FR 26) 8000 FC 4000 FC [F7X without M1000] 53-40-00-280-809-01 ALI/FD SPECIAL DETAILED INSPECTION (HFEC) OF GAUGE HOLES ON CENTER WING LOWER PANEL 12100 FC 4000 FC [F7X without M1000] A/C with M1455 or with SB 7X-342 FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 29 / 71 « DASSAULT AVIATION Proprietary Data » 53: FUSELAGE Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 53-40-00-280-810-01 ALI/FD SPECIAL DETAILED INSPECTION (HFEC) OF PUMP HOLES ON CENTER WING LOWER PANEL 12100 FC 8000 FC [F7X without M1000] A/C with M1944 53-41-00-220-802 ALI/FD DETAILED FATIGUE INSPECTION OF THE LOWER WING ROOT BOLT RECESSES 12100 FC 4000 FC [F7X without M1000] 53-50-00-200-802 ALI/FD INSPECTION OF THE JUNCTION BETWEEN INNER SHEET METAL AND BAGGAGE COMPARTMENT SKIN 12100 FC 4000 FC [F7X without M1000] 53-50-00-200-811-01 ALI/FD INSPECTION OF STRUCTURAL PART BETWEEN FR33 AND FR41 12100 FC 4000 FC [F7X without M1000] FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 30 / 71 « DASSAULT AVIATION Proprietary Data » 53: FUSELAGE Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 53-50-00-220-801 ALI/FD DETAILED INSPECTION OF THE RH SKIN DOUBLER OF BAGGAGE COMPARTMENT 12100 FC 8000 FC [F7X without M1000] A/C 002-003 53-50-00-280-803 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION (LFEC) UNDER S-DUCT 12100 FC 4000 FC [F7X without M1000] 53-50-00-280-804 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION AT MANDOLIN-SHAPED STUB JUNCTION AND UNDER THE S-DUCT 12100 FC 4000 FC [F7X without M1000] 53-50-00-280-806-01 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION (HFEC) INSIDE BAGGAGE COMPARTMENT 12100 FC 8000 FC [F7X without M1000] A/C 152-400 FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 31 / 71 « DASSAULT AVIATION Proprietary Data » 53: FUSELAGE Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 53-50-00-280-806-01 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION (HFEC) INSIDE BAGGAGE COMPARTMENT 4000 FC 8000 FC [F7X without M1000] A/C 001-005 or A/C 006-151 with SB 7X- 191 53-50-00-280-808 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF STRUCTURAL PARTS BETWEEN FR33 AND FR41 12100 FC 4000 FC [F7X without M1000] 53-50-00-280-809 ALI/FD SPECIAL DETAILED INSPECTION (HFEC) OF FR36 FREE FLANGE AND FR37 GUSSET 12100 FC 4000 FC [F7X without M1000] FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 32 / 71 « DASSAULT AVIATION Proprietary Data » 54: NACELLES AND PYLONS Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 54-50-00-200-801 ALI/FD INSPECTION OF THE ENGINE PYLONS LOWER AND UPPER SKIN AND FITTINGS 12100 FC 4000 FC [F7X without M1000] FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 33 / 71 « DASSAULT AVIATION Proprietary Data » 55: STABILIZERS Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 55-00-00-270-803-01 ALI/FD SPECIAL DETAILED INSPECTION (ULTRASONIC) OF DECOMATIC SCREWS IN STABILIZER AREA 4000 FC 4000 FC [F7X without M1000] A/C 257 and 259 and 264 and 269-286 55-00-00-270-803-01 ALI/FD SPECIAL DETAILED INSPECTION (ULTRASONIC) OF DECOMATIC SCREWS IN STABILIZER AREA 4000 FC 4000 FC [F7X with M1000] A/C 401-471 55-30-00-200-803 ALI/FD INSPECTION OF THE FIN ATTACHMENT FITTINGS 12100 FC 4000 FC [F7X without M1000] FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 34 / 71 « DASSAULT AVIATION Proprietary Data » 57: WINGS Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 57-00-00-270-803-01 ALI/FD SPECIAL DETAILED INSPECTION (ULTRASONIC) OF DECOMATIC SCREWS IN WING AREA 4000 FC 4000 FC [F7X without M1000] A/C 271-285 57-00-00-270-803-01 ALI/FD SPECIAL DETAILED INSPECTION (ULTRASONIC) OF DECOMATIC SCREWS IN WING AREA 4000 FC 4000 FC [F7X with M1000] A/C 402-455 57-10-00-200-804 ALI/FD INSPECTION OF THE WING LOWER PANELS 12100 FC 4000 FC [F7X without M1000] 57-10-00-220-802 ALI/FD DETAILED INSPECTION OF THE WING LOWER PANELS LONGITUDINAL SPLICES 8000 FC 4000 FC [F7X without M1000] FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 35 / 71 « DASSAULT AVIATION Proprietary Data » 57: WINGS Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 57-10-00-220-804-01 ALI/FD DETAILED INSPECTION OF THE WING REAR SPARS - DETAILED INSPECTION OF THE LH REAR MAIN LANDING GEAR ATTACHMENT 12100 FC 4000 FC [F7X without M1000] A/C without bushing installed in aft MLG bore 57-10-00-220-804-02 ALI/FD DETAILED INSPECTION OF THE WING REAR SPARS - DETAILED INSPECTION OF THE LH WEB CURRENT AREA FLANGE 12100 FC 4000 FC [F7X without M1000] 57-10-00-220-804-03 ALI/FD DETAILED INSPECTION OF THE WING REAR SPARS - DETAILED INSPECTION OF THE LH FLAPS, AIRBRAKES AND SPOILERS ACTUATOR HOLES 12100 FC 4000 FC [F7X without M1000] 57-10-00-220-804-04 ALI/FD DETAILED INSPECTION OF THE WING REAR SPARS - DETAILED INSPECTION OF THE RH REAR MAIN LANDING GEAR ATTACHMENT 12100 FC 4000 FC [F7X without M1000] A/C without bushing installed in aft MLG bore FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 36 / 71 « DASSAULT AVIATION Proprietary Data » 57: WINGS Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 57-10-00-220-804-05 ALI/FD DETAILED INSPECTION OF THE WING REAR SPARS - DETAILED INSPECTION OF THE RH WEB CURRENT AREA FLANGE 12100 FC 4000 FC [F7X without M1000] 57-10-00-220-804-06 ALI/FD DETAILED INSPECTION OF THE WING REAR SPARS - DETAILED INSPECTION OF THE RH FLAPS, AIRBRAKES AND SPOILERS ACTUATOR HOLES 12100 FC 4000 FC [F7X without M1000] 57-10-00-280-802 ALI/FD SPECIAL DETAILED INSPECTION (HFEC) OF THE TENSIBLE SPLICE BETWEEN THE MIDDLE AND THE REAR WING LOWER PANELS 8000 FC 8000 FC [F7X without M1000] A/C without M1117 57-10-00-280-802 ALI/FD SPECIAL DETAILED INSPECTION (HFEC) OF THE TENSIBLE SPLICE BETWEEN THE MIDDLE AND THE REAR WING LOWER PANELS 12100 FC 12000 FC [F7X without M1000] A/C with M1117 FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 37 / 71 « DASSAULT AVIATION Proprietary Data » 57: WINGS Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 57-10-00-280-805-01 ALI/FD SPECIAL DETAILED INSPECTION OF THE REAR BALL- JOINT BORE - LH REAR BALL-JOINT BORE 12100 FC 4000 FC [F7X without M1000] A/C with bushing installed in aft MLG bore 57-10-00-280-805-02 ALI/FD SPECIAL DETAILED INSPECTION OF THE REAR BALL- JOINT BORE - RH REAR BALL-JOINT BORE 12100 FC 4000 FC [F7X without M1000] A/C with bushing installed in aft MLG bore 57-10-05-220-801 ALI/FD DETAILED INSPECTION OF THE AILERON SERVO- ACTUATOR FITTING 12100 FC 3300 FC [F7X without M1000] 57-40-00-220-801 ALI/FD DETAILED INSPECTION OF THE WING FRONT SPARS 8000 FC 4000 FC [F7X without M1000] FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 38 / 71 « DASSAULT AVIATION Proprietary Data » 57: WINGS Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 57-40-00-280-801 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION (HFEC) ON FRONT WING SPAR AT ROLLER SUPPORT FITTINGS 8000 FC 4000 FC [F7X without M1000] 57-40-00-280-802-02 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE FASTENER HOLES AT THE FRONT SPAR / WING LOWER PANEL CONNECTIONS - LH INBOARD SPAR AT TRACK 5 12100 FC 4000 FC [F7X without M1000] A/C 082-400 57-40-00-280-802-03 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE FASTENER HOLES AT THE FRONT SPAR / WING LOWER PANEL CONNECTIONS - LH OUTBOARD SPAR AT SLAT CUT-OUT 12100 FC 4000 FC [F7X without M1000] 57-40-00-280-802-05 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE FASTENER HOLES AT THE FRONT SPAR / WING LOWER PANEL CONNECTIONS - RH INBOARD SPAR AT TRACK 5 12100 FC 4000 FC [F7X without M1000] A/C 082-400 FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 39 / 71 « DASSAULT AVIATION Proprietary Data » 57: WINGS Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 57-40-00-280-802-06 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE FASTENER HOLES AT THE FRONT SPAR / WING LOWER PANEL CONNECTIONS - RH OUTBOARD SPAR AT SLAT CUT-OUT 12100 FC 4000 FC [F7X without M1000] 57-40-00-280-803 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE FASTENER HOLES AT THE FRONT SPAR / WING LOWER PANEL CONNECTIONS AT ROLLER SUPPORTS 5 AND 7 12100 FC 4000 FC [F7X without M1000] A/C 001-081 57-40-00-280-804-01 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE FASTENER HOLES AT THE FRONT SPAR / WING LOWER PANEL CONNECTIONS AT RIB 26 2350 FC 2350 FC [F7X without M1000] A/C without M1117 and with wing S/N 001MA001 57-40-00-280-804-01 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE FASTENER HOLES AT THE FRONT SPAR / WING LOWER PANEL CONNECTIONS AT RIB 26 8000 FC 4000 FC [F7X without M1000] A/C without M1117 and without wing S/N 001MA001 FALCON 7X MAINTENANCE MANUAL EFFECTIVITY : ALL–Reference DGT 107838 Revision 11 Jun/2022 Page 40 / 71 « DASSAULT AVIATION Proprietary Data » 57: WINGS Scheduled maintenance task number Origin Title / Operation First Inspection Interval Remarks 57-40-00-280-804-01 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE FASTENER HOLES AT THE FRONT SPAR / WING LOWER PANEL CONNECTIONS AT RIB 26 12100 FC 12000 FC [F7X without M1000] A/C with M1117 57-40-00-280-805-01 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE FASTENER HOLES WITH SHOULDERED BUSHINGS AT THE FRONT SPAR / WING LOWER PANEL CONNECTIONS - INSPECTION OF THE FASTENER HOLES AT SPAR / WING LOWER PANEL CONNECTIONS 12100 FC 8000 FC [F7X without M1000] A/C with wing S/N 003MA002 (RH) or 011MA010 or 023MA022 or 026MA025 or 033MA032 or 037MA036 or 045MA044 57-40-00-280-805-02 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE FASTENER HOLES WITH SHOULDERED BUSHINGS AT THE FRONT SPAR / WING LOWER PANEL CONNECTIONS - INSPECTION OF THE SPAR FASTENER HOLES AT THE ROLLER SUPPORT FITTING/SPAR/WING LOWER PANEL CONNECTIONS 8000 FC 4000 FC [F7X without M1000] A/C with wing S/N 039MA038 or 070MA069 57-45-00-200-801-02 ALI/FD FATIGUE INSPECTION OF THE SLATS - LH MIDDLE SLAT (L9501CM) 10000 FC 2500 FC [F7X without M1000] Note (1)