# FALCON 7X MAINTENANCE MANUAL

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# AIRWORTHINESS LIMITATIONS

CHAPTER 5 - 40 - 00090040008019acf1 - RELEASED - Certification Repository

# FALCON 7X MAINTENANCE MANUAL

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# AIRWORTHINESS LIMITATION SECTION This Airworthiness Limitation S ection contains instructions pertaining to the Airworthiness of the Falcon 7X aircraft, including CMR, ALI and Safe Life limitations, applicable until D esign Service Goal (refer to § 1. A.). The tasks and intervals specified are ma ndatory and cannot be changed, escalated, or deleted without the concurrence of the responsible A uthority 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 Se ction is divided into five paragraphs:

- 1. General

- 2. Instructions

- 3. Airframe components with a limited service life (“SAFE LIFE”).

- 4. Fatigue and Damage Tolerance Airworthiness Limitations Section

- 5. Certification Maintenance Requirements and Other th a n Fatigue Airworthiness Limitation Sections

# FALCON 7X MAINTENANCE MANUAL

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## List of Revision s PAGES No. REVISION EFFECTIVITY 5

- 40

- 00 (Page 1 to page 12 ) Original I ssue (AMM cross

- references completed) ALL (Only l ife limits below

4000 FC . S ee §3 ) 5

- 40

- 00 Original Issue Temporary Revision N° 01 Dated 06 / July / 2007

- Level 2 and 3 corrosion to be reported

- MAU life limit is cancelled

- HSTA component inspection and restoration added

- ' MAU/ Chassis discard ' added

- all 4800 FH become 4850FH ALL (Only life limits below

4000 FC. See §3) 5

- 40

- 00 Original Issue Temporary Revision N° 02 Dated 19 / Feb / 2008

- HSTA restoration interval depends on p/n

- Fuel Pressurization card: operation s 01 and 02 are mandated

- Park brake cable inspection is cancelled + M715 applicability

- Add Mandatory Flight Cycle monitoring section idem

5

- 40 00 All pages Revision One (Rev 1), managed through M1061, mainly including:

- Already approved changes of Chapter 5

- 40 through miscellaneous CP

- Fatigue tests are taken into account 5 and associated inspections are listed in a new dedicated section §4

- § 5 Some scheduled CDCCL tasks are removed from Chapter 5

- 40

- § 6 MANDATORY FLIGHT PARAMETER MONITORING is cancelled no more useful following fatigue test result s ALL Extension of Service life up to DSG

5

- 40 00 All pages Revision T wo (Rev 2), managed through R501 8 , mainly including:

- Already approved changes of Chapter 5

- 40 thr ough miscellaneous CP. Refer to the under paragraph for the detailed list of CP. ALL

5

- 40 00 All page s Revision Thre e (Rev 3), managed through R50 25 , mainly including:

- Already approved changes of Chapter 5

- 40 through miscellaneous CP. Refer to the under paragraph for the detailed list of CP. U nder of paragraphs 1

- D and 2

- B related to CPCP. ALL



### Approval s :

- Original Issue: EASA approved as part of the original Type Certificate A155

- Original I ssue 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 CP0 02: EASA approved ref A.C.1 2599 dated 29 / July/2009

- Revision 1 : EASA a pproved ref erence 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 tas k 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 R 501 8 . 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 tech nical changes: **•** 

### CP 0 11 , approved by EASA under change reference M - OPT 459 . 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

.

# FALCON 7X MAINTENANCE MANUAL

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- Effective Date of R ev 0 3 : 15 / OCT /2012

# FALCON 7X MAINTENANCE MANUAL

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## 1 GENERAL A. DE SIGN SERVICE GOAL The Falcon 7X Design Service Goal (DSG) is 2 0 ,000 flights/ 5 0,000 flying hours whichever occurs first.

B . DEFINITION OF A STANDARD AIRCRAFT 1

- FATIGUE LOAD SPECTRUM 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. Non standard Aircraft

- Low altitude search and rescu e flights : when types of mission listed hereafter are performed on a regular basis, the aircraft can not be considered as a Standard Aircraft.

- 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

- Rate of Flight Hour per Cycle is significantly higher than 2.5 2

- PRIMARY STRUCTURE CHANGES Standard Aircraft Primary structure must be entirely identical to DASSAULT AVIATION type design: Condition of the pr incipal structure elements (P.S.E.) of a standard aircraft has to correspond to definition at aircraft delivery:

- w hich can be supplemented by any DASSAULT AVIATION service bulletins

- w hich must have i mplemented the applicable Airworthiness Directives

. Non standar d Aircraft:

3

- MAINTENANCE 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.

The m aintenance of a Standard Aircraft must be performed in accordance with:

- e ither Maintenance Manual and Structural Repair Manual

- or other approved maintenance procedures.

# FALCON 7X MAINTENANCE MANUAL

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## 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: DEFINITION AND PRINCIPLES Critical Design Configuration Control Limitations (CDCCL)

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. : 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 su ch a way that an unsafe condition would develop in the fuel system.

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. D . CORROSION PREVENTION and CONTROL PROGRAM NOTE: Refer to chapter 05

- 15 for definition s of Level 1, 2 and 3 corrosion. A CPCP is a systematic approach for controlling corrosion in th e 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 who le 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. (See instructions § 2B CPCP). E . IMPORTANT: The instructions contained in this document must be imperatively observed by the operators.

# FALCON 7X MAINTENANCE MANUAL

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## The mandatory nature of these instructions does not in any way reduce the importance of the other tasks listed in the MRB Report or in the Maintenance Planning Document (Chapter 5) which must be carried out in agreement with the National Airworthiness Authorities. In order to help operators planning their maintenance program and to reduce grounding due to scheduled maintenance, these man datory operations are also listed in the MPD (5

- 10, 5

- 20) with time limits corresponding to the aircraft inspections (A, B, C, etc.) or expressed as a number of flights. F . UPDATING OF SECTION 5 - 40 - 00: When a new maintenance operation is derived from a re vision of Chapter 5 section 5

- 40

- 00, this operation must be carried out when the time at which it is scheduled falls due. If the limit has been passed, the operation is due immediately unless otherwise specified

.

# FALCON 7X MAINTENANCE MANUAL

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## 2. INSTRUCTIONS A . INSTRUCTIONS FOR CDC CL ( Critical Design Configuration Control Limitations)

. Note: Any c hanges 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 the se features

. Some CDCCL are attached to scheduled maintenance and are mandated by section 4 table (CDCCL in column 'CMR ALI CDCCL')

. The following table indicates the other maintenance procedures that are affected by CDCCL. Only some instructions inside the procedure are mandat ory under chapter 5

- 40

. These instructions are clearly identifiable in the Maintenance Procedures (MPs) text as follow s: "Start of Fuel Tank Safety Critical Section .../.... (instructions of CDCCL) .../....

End of Fuel Tank Safety Critical Section" Reference of the MPs that include the Mandated CAUTION Ref Title CDCCL (feature) 28 - 00 - 00 - 910 - 802 ACCEPTANCE CRITERIA FOR FUEL LEAKS - fuel leakage 28 - 21 - 01 - 900 - 801 REMOVAL / INSTALLATION OF THE BOOSTER PUMPS - b onding quality (operation s for measurement: see 28 - 60 - 00 - 3 - 1)

- connectors conditions / corrosion

- cracks of insulation 28 - 21 - 05 - 900 - 801 REMOVAL / INSTALLATION OF THE BOOSTER PUMP 1, 2 AND 3 MANIFOLDS idem 28 - 21 - 17 - 900 - 801 REMOVAL / INSTALLATION OF THE APU FUEL SHUT - OFF VALVE Idem 28 - 21 - 21 - 900 - 801 REMOVAL / INSTALLATION OF THE APU FUEL SHUT - OFF VALVE ACTUATOR Idem 28 - 2 1 - 25 - 900 - 801 REMOVAL / INSTALLATION OF THE LH AND RH CROSSFEED UNITS Idem 28 - 22 - 01 - 900 - 801 REMOVAL / INSTALLATION OF THE WING TANK CROSS VALVE (XTK) Idem 

### 28

- 41

- 09

- 900

- 801 REMOVAL / INSTALLATION OF THE WING FUEL GAUGING PROBES Idem 28 - 50 - 05 - 900 - 801 REMOVAL / INSTALLATION OF THE HIGH - LEVEL SENSORS Idem 28 - 50 - 17 - 900 - 801 REMOVAL / INSTALLATION OF THE GRAVITY REFUELING PLUGS Idem 53 - 40 - 05 - 960 - 801 REPLACEMENT OF THE CENTER FUEL TANK RIB 1 ROD Idem 20 - 95 - 00 - 200 - 801 INSPECTION OF WIRING ROUTING AND SEGREGATION R espects of :

- FQIS wiring segregation

- and Feeder versus fuel pipe routing segregation

# FALCON 7X MAINTENANCE MANUAL

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## B . INSTRUCTIONS FOR CORROSION PREVENTION CONTROL PROGRAM The o perator is mandated to consider the associated tasks that have been identified in the Chapter 05

- 15 as a baseline for his Maintenance Program. Operators are mandated to report to DASSAULT AVIATION the result of inspection when corrosion Level 2 or 3 are found

. 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.

# FALCON 7X MAINTENANCE MANUAL

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## 3. AIRFRAME COMPONENTS WITH LIMITED SERVICE LIFE (“SAFE LIFE”) Fatigue and qualification test s have demonstrated the whole DSG. This ALS issue lists the aircraft components and structural parts which life limits are below 20,000 FC / 50,000FH

. 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 airc raft 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 pa rt, indicated in chapter 5

- 40 , will not be e xceeded. Note 1: These

– * are in place of any figures or numbers. In the following charts, some P/N appear with

- * (i.e. 10

- 230201

- * 

## ). This is to avoid a too long list of P/N and numerous updates ; a nd it is suffici ent to identify the P/N to be traced. Note 2: Some of the followings P/N were not listed in the previous version of Chapter 5

- 40 : u se the current aircraft value s of the ageing parameter (s) of those P/N to initialize the ir life limit management . Aircraft components with limited service life COMPONENT IDENTIFICATION PART NUMBER LIMITED SERVICE LIFE NOTE/ EFFECTIVITY 27 FLIGHT CONTROL Aileron servo actuator 103152

- 12 20,000FC / 50,000FH Rudder servo actuator 103153

- 05 20,000FC / 50,000FH Elevator servo actuator 103154

- 16 20,000FC / 50,000FH HSTA 021173

- xx 20,000FC / 50,000FH

Slat actuator 106136

- 02 106138

- 0 2 106139

- 0 2 20,000FC / 50,000FH

# FALCON 7X MAINTENANCE MANUAL

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## COMPONENT IDENTIFICATION PART NUMBER LIMITED SERVICE LIFE NOTE/ EFFECTIVITY 106140

- 03 106141

- 03 Spoiler actuator 106137

- 01 20,000FC / 50,000FH 

## 32 LANDING GEAR NLG leg 10

- 230201

- * 

## 4000 FC Note: this 4000FC is a temporary limitation, the definitive limitation for landing gear items will be introduced in a next revision of Chapter 5

- 40 NLG Drag Brace 10

- 232101

- * 

## 4000 FC

MLG leg LH & RH 10

- 235301

- * (LH) 10

- 235302

- * (LH) 10

- 235401

- * (RH) 10

- 235402

- * (RH) 

## 4000 FC

MLG Folding brace 10

- 238201

- * (RH) & 10

- 238101

- * (LH) 

## 4000 FC 5 3 FUSELAGE T 34: R ear tank upper panel FR 27 to FR 28 F7XC258420B1 4 1 00 FC All except those with M7 73 or M883 T5

- Frame 37 upper blind fasteners (fasteners as per M625) 4 1 00 FC All without M625 T5

- Frame 37 gusset (as per M626) 4 1 00 FC All without M626 C onnection between main landing gear actuator door fitting and the landing gear bay lateral web (as per M 571 ) 12, 1 00FC All without M571 Front lower T34 stringer 15 at finger doubler crossing area (as per M 452 ) 12,500FC All without M 452 

## FH=Flight Hours FC=Flight Cycles CT= Calendar Time

# FALCON 7X MAINTENANCE MANUAL

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## 4. FATIGUE AND DAMAGE TOLERANCE AIRWORTHINESS LIMITATIONS A list of inspections ha s been raised based on calculations and on structural fatigue and damage tolerance tests and their exploitation. All the determined inspections are taken into account in the MPD with maximum threshold at 12,000FC. Only the inspections which calculated thr eshold is equal to or lower than one Design Service Goals have been retained in this Chapter 5

- 40 (see note). Note this list of mandatory inspections will have to be updated when Falcon7X will get the approval for an Extended Service Goal beyond 20,000FC. This list is presented in the following table. In Max Limit column, the first figure is for threshold ( TH ) and the second if for interval ( IT )

. ALI /FD s (Airworthiness LImita t ions from Fatigue and Damage tolerances) :

MPD task Code Oper Origin Title Max Limit comment effectivity 05 - 31 - 34 - 210 - 801 02 ALI/FD GENERAL VISUAL INSPECTION OF THE ZONES UNDER THE T34 BODY FAIRINGS 12100FC / 4100FC 05 - 31 - 54 - 210 - 801 02 ALI/FD GENERAL VISUAL INSPECTION OF THE MLG WHEEL WELLS 12100FC / 4100FC 05 - 32 - 20 - 210 - 801 02 ALI/FD GENERAL VISUAL INSPECTION OF THE T12 EXTERNAL SIDE 12100FC / 4100FC 05 - 32 - 50 - 210 - 801 02 ALI/FD GENERAL VISUAL INSPECTION OF THE T34 AND T5 OUTER SIDE 12100FC / 4100FC 05 - 32 - 72 - 210 - 801 02 ALI/FD GENERAL VISUAL INSPECTION OF THE BAGGAGE COMPARTMENT 12100FC / 4100FC 05 - 33 - 50 - 210 - 801 02 ALI/FD GENERAL VISUAL INSPECTION OF THE ZONE UNDER S - DUCT FAIRINGS 12100FC / 4100FC 05 - 35 - 00 - 210 - 801 0 3 and 04 ALI/FD GENERAL VISUAL INSPECTION OF THE WINGS 8100FC / 4100FC 05 - 38 - 00 - 210 - 801 02 ALI/FD GENERAL VISUAL INSPECTION OF THE PASSENGER, BAGGAGE COMPARTMENT, EMERGENCY EXIT AND SERVICING COMPARTMENT DOORS 12100FC / 4100FC 05 - 38 - 00 - 210 - 801 03 ALI/FD GENERAL VISUAL INSPECTION OF THE PASSENGER, BAGGAGE COMPARTMENT, EMERGENCY EXIT AND SERVICING COMPARTMENT DOORS 8100FC / 8100FC 05 - 38 - 00 - 210 - 801 04 ALI/FD GENERAL VISUAL INSPECTION OF THE PASSENGER, BAGGAGE COMPARTMENT, EMERGENCY EXIT AND SERVICING COMPARTMENT DOORS 4100FC / 4100FC 52 - 30 - 00 - 200 - 801 03 ALI/FD VISUAL INSPECTION OF THE BAGGAGE COMPARTMENT DOOR 12100FC / 4100FC 53 - 00 - 00 - 280 - 801 - ALI/FD EDDY CURRENT INSPECTION OF THE SKIN AT THE SEAM OF STRINGER 15 4400FC applicable to A/C without M452 and without M454 53 - 10 - 00 - 200 - 806 02 ALI/FD INSPECTION OF THE T12 INNER OVERFLOOR STRUCTURE 12100FC / 8100FC 53 - 10 - 00 - 200 - 80 9 01 ALI/FD DET AILED FATIGUE INSPECTION OF THE PASSENGER DOOR AND OF THE RAT BAY 12100FC / 4100FC 53 - 10 - 00 - 280 - 801 01 ALI/FD SPECIAL DETAILED INSPECTION OF FASTENERS ON FRAME 9 OUTBOARD FLANGE 12100FC / 4100 F C 53 - 10 - 00 - 280 - 802 01 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION FROM OUTSIDE OF THE TOP AND BOTTOM RADIUSES OF THE WINDSHIELD RETAINERS AT THE LH AND RH REAR ARCHES 12100FC / 8100FC

# FALCON 7X MAINTENANCE MANUAL

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CONNECTIONS AT ROLLER SUPPORTS 5 AND 7 12100FC / 4100FC A/C S/N 1 - 81 configuration 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 2350FC / 2350FC A/C with wing S/N 001 MA001 (LH),

071MA069 073MA 071

# FALCON 7X MAINTENANCE MANUAL

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071MA069 073MA071 and

A/C without

M 1117 embodied 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 12000FC / 12000FC A/C with wing S/N 122MA121,

123MA121, 123MA122 and 124MA122 and A/C with M 1117 embodied 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 SPAR FASTENER HOLES AT THE SPAR / WING LOWER PANEL CONNECTIONS 12100FC / 8100FC A/C with wing S/N 003MA002 ( R H),

011MA010, 023MA022, 026MA025, 033MA032, 037MA036, 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 8 100FC / 4 100FC A/C with wing S/N 039MA038

070MA069

57 - 45 - 00 - 280 - 802 01 to 06 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE SLATS 12100FC / 8100FC (see note) 57 - 45 - 00 - 280 - 802 0 7 and 08 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE SLATS 12100FC / 8100FC (see note) Slat P/N F7XC574300000 F7XC574400 0 00 which revision is less or equal to A6 Note : inspection

can only be performed if F7X - SB - 047 is implemented 57 - 45 - 00 - 280 - 803 - ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE SLAT TRACKS 12100FC / 4100FC 57 - 70 - 05 - 200 - 801 - ALI/FD FATIGUE INSPECTION OF THE SPOILERS 8100FC / 4100FC (see note) All with spoiler assembly F7XC577331A6, F7XC577331A7 F7XC577331W8 or F7XC577431A6 F7XC577431A7 F7XC577431 W8 57 - 50 - 00 - 200 - 803 - ALI/FD FATIGUE INSPECTION OF FLAP TRACK RIB 2 AND 4 12100FC / 8100FC 57 - 50 - 00 - 280 - 802 01 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF FLAP TRACK 2 8100FC / 4100FC 57 - 50 - 00 - 280 - 803 01 ALI/FD SPECIAL DETAILED INSPECTION OF FLAPS 12100FC / 12100FC (see note) flap S/N STK1001 up to 1015 57 - 60 - 00 - 200 - 801 02 and 03 ALI/FD INSPECTION OF THE AILERONS AND THE AILERON FITTINGS ON THE WING REAR SPARS 12100FC / 3300FC (see note)

# FALCON 7X MAINTENANCE MANUAL

EFFECTIVITY : ALL Page « DASSAULT AVIATION Proprietary Data » 16/JUL /2012 DGT 107838 Revision 3 15 MPD task Code Oper Origin Title Max Limit comment effectivity 71 - 20 - 00 - 280 - 802 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION (HFEC) OF THE ENGINE YOKE AND ATTACHMENT BOLTS 12100FC / 12100FC (see note) LH and RH engines 

### Note : the F light C ycles accomplished by the concerned removable items must be traced for these inspections.

# FALCON 7X MAINTENANCE MANUAL

EFFECTIVITY : ALL Page « DASSAULT AVIATION Proprietary Data » 16/JUL /2012 DGT 107838 Revision 3 16 

## 5

. CMRs AND OTHER ALI THAN FATIGUE and DAMAGE TOLERANCE's (scheduled ALI CDCCLs and ALI from qualification tests) Operations which have two limits (flight/cycles and calendar) are due at the first reached limit

. All CMRs are only one star CMR as per EASA AMC 25

- 19 and FAA AC 25

- 19

. MPD task Code Oper Origin Title Max Time Limit comment effectivity 21 - 30 - 00 - 720 - 801 - CMR FUNCTIONAL TEST OF THE ALTITUDE LIMIT THRESHOLD 4850 FH 21 - 32 - 01 - 7 2 0 - 802 - CMR FUNCTIONAL TEST OF THE MANUAL MODE OF THE CABIN INTEGRATED PRESSURE CONTROL SYSTEM (IPCS) VALVE 4850 FH 21 - 32 - 01 - 720 - 801 - CMR FUNCTIONAL TEST OF THE ''DUMP'' FUNCTION OF THE CABIN INTEGRATED PRESSURE CONTROL SYSTEM (IPCS) VALVE 4850 FH

21 - 32 - 13 - 720 - 801 - CMR FUNCTIONAL TEST OF THE CABIN POSITIVE PRESSURE RELIEF VALVE 4850 FH 21 - 32 - 17 - 720 - 801 - CMR FUNCTIONAL TEST OF THE BAGGAGE COMPARTMENT POSITIVE PRESSURE RELIEF VALVE 4850 FH 21 - 32 - 25 - 710 - 801 - CMR OPERATIONAL TEST OF THE COCKPIT NEGATIVE PRESSURE RELIEF VALVE 4850 FH 21 - 32 - 29 - 710 - 80 2 - CMR OPERATIONAL TEST OF THE FLAPPER OF THE GROUND MODE VENT AND NEGATIVE PRESSURE RELIEF VALVE 4850 FH 21 - 32 - 33 - 710 - 801 - CMR OPERATIONAL TEST OF THE BAGGAGE COMPARTMENT ISOLATION VALVES 4850 FH 21 - 53 - 00 - 720 - 801 - CMR FUNCTIONAL TEST OF THE EMERGENCY COLD AIR SUPPLY SYSTEM 650FH 21 - 60 - 00 - 720 - 801 - CMR FUNCTIONAL TEST OF THE COCKPIT / CABIN MANUAL TEMPERATURE CONTROL FUNCTION 650FH 21 - 65 - 17 - 710 - 801 - CMR OPERATIONAL TEST OF THE BAGGAGE COMPARTMENT VENTILATION FAN PCB 650 FH A/C without M566 or SB F7X - 100 21 - 65 - 17 - 710 - 801 - CMR OPERATIONAL TEST OF THE BAGGAGE COMPARTMENT VENTILATION FAN PCB 10,000 FH A/C with M566 or SB - F7X - 100 21 - 72 - 03 - 710 - 801 - CMR OPERATIONAL TEST OF THE HUMIDIFIER " HUMID /OFF" SWITCH 10,000FH A/C with an humidifier system installed through Dassault Aviation Mod or SB 24 - 31 - 01 - 350 - 801 - 01, - 03, - 05 ALI RESTORATION OF THE DC GENERATORS (bearing) 650 FH P/N 30089 - 004 or 30089 - 005 24 - 31 - 01 - 350 - 801 - 02, - 04, - 06 ALI RESTORATION OF THE DC GENERATORS (diodes) 3000 FH P/N 30089 - 004 or 30089 - 005 24 - 31 - 01 - 350 - 801 - ALI RESTORATION OF THE DC GENERATORS 3000 FH P/N 30089 - 006 and subsequent 24 - 32 - 01 - 710 - 80 2 - CMR OPERATIONAL TEST OF THE BATTERY THERMOSTAT 1850 FH For A/C having exceeded, operation to be done within next B inspection from effective date of revision 1.

# FALCON 7X MAINTENANCE MANUAL

EFFECTIVITY : ALL Page « DASSAULT AVIATION Proprietary Data » 16/JUL /2012 DGT 107838 Revision 3 17 MPD task Code Oper Origin Title Max Time Limit comment effectivity 24 - 32 - 01 - 710 - 80 1 - CMR OPER A TIONAL T E S T OF BATTERY HEATER RELAY 20,000 FH A/C without M724 24 - 50 - 00 - 720 - 801 - CMR FUNCTIONAL TEST OF THE RAT SYSTEM 1850FH or 28 months 24 - 50 - 00 - 910 - 802 - CMR AUTOMATIC DEPLOYMENT OF THE RAM AIR TURBINE (RAT) 3700FH 24 - 50 - 01 - 710 - 801 - CMR OPERATIONAL TEST OF THE RAT TRANSFORMER RECTIFIER UNIT (TRU) 220FH See 05 - 60 - 00 - 200 - 801 Basic Inspection 24 - 50 - 25 - 720 - 801 - CMR FUNCTIONAL TEST OF THE RAT HEATER 650 FH A/C without M305 or SB F7X - 018 24 - 50 - 25 - 720 - 801 - CMR FUNCTIONAL TEST OF THE RAT HEATER 1900 FH A/C with M305 or SB - F7X - 018 26 - 10 - 00 - 720 - 801 0 8 CMR FUNCTIONAL TEST OF THE PNEUMATIC FIRE DETECTORS LH MLG BAY 20,000FH 26 - 10 - 00 - 720 - 801 0 9 CMR FUNCTIONAL TEST OF THE PNEUMATIC FIRE DETECTORS RH MLG BAY 20,000FH 26 - 20 - 01 - 7 1 0 - 80 1 - CMR OPERATIONAL TEST OF THE APU SOV AUTOMATIC CLOSURE FUNCTION 8100FH 26 - 20 - 01 - 720 - 803 - CMR FUNCTIONAL TEST OF THE FIRE SWITCH/LIGHTS 1150FH 26 - 20 - 09 - 350 - 801 - CMR RESTORATION OF THE FIRE EXTINGUISHERS 10 years 27 - 00 - 00 - 700 - 801 - CMR AUTOMATIC ANTI - FLUTTER TEST 2500 FH 27 - 11 - 01 - 710 - 801 - CMR OPERATIONAL TEST OF THE SPOILER CONTROL BACK - UP CHANNEL 2000 FH 27 - 11 - 05 - 710 - 801 - CMR OPERATIONAL TEST OF THE SPOILER SENSORS 10,000 FH 27 - 11 - 09 - 710 - 801 - CMR TEST OF RESERVOIR FILLING AND LOCAL HYDRAULIC GENERATOR OPERATION 1250 FH 27 - 12 - 00 - 220 - 801 - CMR DETAILED INSPECTION OF THE AILERON CONTROL SYSTEM COMPONENTS 10,000 FH 27 - 20 - 00 - 220 - 801 - CMR DETAILED INSPECTION OF THE RUDDER CONTROL SYSTEM COMPONENTS 10,000 FH 27 - 40 - 00 - 220 - 801 - CMR DETAILED INSPECTION OF THE HORIZONTAL STABILIZER CONTROL SYSTEM COMPONENTS 10,000 FH 27 - 40 - 00 - 710 - 801 - CMR OPERATIONAL TEST OF THE HSTA ELECTRIC MOTORS REVERSION 1850 FH A/C without M 1245 or without SB 214 embodied 27 - 40 - 00 - 710 - 801 - CMR OPERATIONAL TEST OF THE HSTA ELECTRIC MOTORS REVERSION 5050 FH A/C with M 1245 or with SB 214 embodied 27 - 40 - 00 - 710 - 802 - CMR OPERATIONAL TEST OF THE HSTA TRIM EMERG COMMAND 650 FH 27 - 30 - 01 - 710 - 801 - CMR OPERATIONAL TEST OF THE CENTERED MODE 10,000 FH 27

- 40

- 01

- 350

- 801 01 CMR RESTORATION OF THE HORIZONTAL STABILIZER TRIM ACTUATOR 21,000 FH With HSTA P/N 021173 - 03 and subsequent 27

- 40

- 01

- 350

- 801 02 CMR RESTORATION OF THE HORIZONTAL STABILIZER TRIM ACTUATOR 2500 FH With HSTA P/N 021173 - 02

# FALCON 7X MAINTENANCE MANUAL

EFFECTIVITY : ALL Page « DASSAULT AVIATION Proprietary Data » 16/JUL /2012 DGT 107838 Revision 3 18 MPD task Code Oper Origin Title Max Time Limit comment effectivity 27 - 40 - 01 - 640 - 801 - CMR LUBRICATION OF THE HORIZONTAL STABILIZER TRIM ACTUATOR 2000FH 27 - 50 - 00 - 710 - 802 - CMR OPERATIONAL TEST OF THE FLAP BRAKE, AIRBRAKE LOCK AND SFAU POWER MONITOR 700 FH 27 - 50 - 00 - 720 - 802 - CMR FUNCTIONAL TEST OF THE FLAP ASYMMETRY DETECTION CIRCUIT 5000 FH 27 - 53 - 01 - 640 - 801 - CMR LUBRICATION OF THE FLAP ACTUATOR SCREWS 2000 FH CMR is check of flap disconnection 27 - 53 - 01 - 720 - 801 - CMR FUNCTIONAL TEST OF THE FLAP ACTUATOR BACKLASH 4000 FH 27 - 53 - 01 - 720 - 802 - CMR FUNCTIONAL CHECK OF COMPRESSIVE NO - BACK 10,000 FH 27 - 60 - 00 - 710 - 802 - CMR OPERATIONAL TEST OF THE AIRBRAKE AUTO RETRACTION LOGIC 2500 FH 27 - 80 - 00 - 710 - 801 CMR OPERATIONAL TEST OF THE SLATS IN NORMAL MODE 10,000FH A/C with M443 or SB - F7X - 014 27 - 80 - 00 - 710 - 803 - CMR OPERATIONAL TEST OF THE SLAT AUTO - EXTENSION 1000FH 27 - 91 - 05 - 710 - 801 0 2 CMR OPERATIONAL TEST OF THE TRIM UNIT 2000 FH 0 2 = yaw only 27 - 91 - 05 - 710 - 801 01 CMR OPERATIONAL TEST OF THE TRIM UNIT 10,000 FH 01= roll only 27 - 95 - 01 - 710 - 801 - CMR OPERATIONAL TEST OF THE FCS REVERSION MODES 2000 FH 2 8 - 0 0 - 00 - 72 0 - 801 - ALI CDCCL BONDING CHECK OF THE FUEL SYSTEM CRITICAL COMPONENTS 8800FC or 211 months 28 - 10 - 00 - 200 - 802 - ALI CDCCL VISUAL INSPECTION OF THE FUEL PIPE BONDING STRAPS OUTSIDE THE FUEL TANKS 4400 FC or 106 months 28 - 10 - 00 - 200 - 803 - ALI CDCCL VISUAL INSPECTION OF THE BONDING STRAPS IN THE FUEL TANKS 4400 FC or 106 months 28 - 10 - 00 - 720 - 801 - ALI CDCCL FUNCTIONAL CHECK OF THE ELECTRICAL BONDING BETWEEN THE HYDRAULIC COUPLINGS AND THE WING TANKS 8800 FC or 211 months 28 - 21 - 00 - 960 - 801 - ALI CDCCL REPLACEMENT OF THE FUEL UNION SEALS UNDER THE BODY FAIRINGS F14 - F26 AND IN THE FUEL EQUIPMENT BAY 211 Months 28 - 21 - 17 - 710 - 801 - CMR OPERATIONAL TEST OF THE APU FUEL SHUT - OFF VALVE 8000 FH 28 - 50 - 00 - 760 - 801 - ALI CDCCL CHECK OF THE GROUNDING CONNECTOR ELECTRICAL BONDING 40 months 28 - 70 - 00 - 720 - 801 01 CMR FUNCTIONAL TEST OF THE PRESSURIZATION SYSTEM 2700 FH or 53 months 28 - 70 - 00 - 720 - 801 02 ALI CDCCL FUNCTIONAL TEST OF THE PRESSURIZATION SYSTEM 2700 FH or 53 months 28 - 70 - 05 - 350 - 801 - CMR RESTORATION OF THE PRESSURE REDUCER 9600 FH 28 - 70 - 09 - 350 - 801 - CMR RESTORATION OF THE VALVE BOXES (FILTER CLEANING AND CALIBRATION CHECK) 9600 FH 28 - 70 - 13 - 350 - 801 - CMR RESTORATION OF THE WING VACUUM RELIEF VALVES 9600 FH 29 - 12 - 01 - 720 - 801 02 CMR FUNCTIONAL TEST OF THE SYSTEM A AND B PRIORITY VALVES 1300 FH 02= syst B priority valve 29 - 12 - 01 - 720 - 801 01 CMR FUNCTIONAL TEST OF THE SYSTEM A AND B PRIORITY VALVES 2500 FH 01= syst A priority valve

# FALCON 7X MAINTENANCE MANUAL

EFFECTIVITY : ALL Page « DASSAULT AVIATION Proprietary Data » 16/JUL /2012 DGT 107838 Revision 3 19 MPD task Code Oper Origin Title Max Time Limit comment effectivity 29 - 14 - 00 - 720 - 801 - CMR FUNCTIONAL TEST OF THE SYSTEM B BOOTSTRAP SYSTEM 1300 FH 29 - 20 - 01 - 720 - 801 02 CMR CHECK OF THE HYDRAULIC BACKUP PUMP BRUSHE LENGTH AND INDICATION 10,000 FH 02= indication 29 - 20 - 01 - 720 - 801 01 CMR CHECK OF THE HYDRAULIC BACKUP PUMP BRUSHE LENGTH AND INDICATION 7300 FH 01= brush length ; restoration upon result 29 - 11 - 17 - 720 - 801 - CMR FUNCTIONAL TEST OF THE HYDRAULIC RESERVOIR TEMPERATURE SWITCHES 20,000 FH 29 - 3 0 - 01 - 720 - 801 - CMR FUNCTIONAL TEST OF THE HYDRAULIC TEMPERATURE TRANSDUCERS 20,000 FH 30 - 41 - 00 - 710 - 801 - CMR OPERATIONAL TEST OF THE WINDSHIELD DE - ICING SYSTEM 2450 FH 31

- 41

- 00

- 960

- 801 - ALI DISCARD OF THE MAU MODULES 2500 FH A/C without M715 or SB F7X - 020 31

- 41

- 01

- 960

- 801 - ALI DISCARD OF THE MAU CHASSIS 2500 FH A/C without M715 or SB F7X - 020 31 - 60 - 00 - 710 - 801 05 CMR OPERATIONAL TEST OF THE CENTRAL DISPLAY SYSTEM (CDS) - TEST OF THE REVERSION CONTROLLER 10,000 FH 31 - 60 - 00 - 710 - 801 06 CMR OPERATIONAL TEST OF THE CENTRAL DISPLAY SYSTEM (CDS) - TEST OF THE REVERSION/DIMMING SYSTEM 10,000 FH 32 - 41 - 09 - 720 - 801 - CMR FUNCTIONAL TEST OF THE HYDRAULIC F USES 4850FH 32 - 42 - 05 - 720 - 801 - CMR FUNCTIONAL TEST OF THE PARK BRAKE ACCUMULATOR CAPACITY 4850 FH 32 - 44 - 17 - 220 - 802 - CMR DETAILED INSPECTION OF THE INTERFACE BETWEEN WHEEL KEYS AND THE BRAKE INBOARD ROTOR 80 FC brakes P/N 90002744 - 1 , P/N 90002744 - 2 and P/N 90002744 - 4 32 - 50 - 0 5 - 350 - 801 - ALI RESTORATION OF THE STEERING COMMAND 8 000 FC 32 - 60 - 00 - 710 - 801 - 09 CMR OPERATIONAL TEST OF THE WOW PROXIMITY SWITCHES LOGICS - OPERATIONAL TEST OF THE IRS3 POWER SUPPLY WOW LOGIC 6000 FH A/C with M 1064 or with SB 7X - 125 embodied 33 - 50 - 00 - 710 - 801 - CMR OPERATIONAL TEST OF THE EMERGENCY LIGHTS 4850 FH See 05 - 60 - 00 - 200 - 801 Basic Inspection 33 - 50 - 00 - 710 - 803 - CMR OPERATIONAL TEST OF THE EMERGENCY LIGHT BATTERIES 4850 FH 35 - 10 - 00 - 710 - 801 - CMR OPERATIONAL TEST OF THE CREW OXYGEN SYSTEM 700 FH 35 - 10 - 0 1 - 350 - 801 - CMR RESTORATION OF THE CREW OXYGEN MASK - REGULATOR S AND STOWAGE BOXES 4900 FH or 6 years 35 - 20 - 00 - 710 - 801 - CMR OPERATIONAL TEST OF THE PASSENGER OXYGEN MODE SELECTOR INDICATION 700 FH 35 - 20 - 00 - 720 - 801 - CMR FUNCTIONAL TEST OF THE PASSENGER OXYGEN SYSTEM 1300 FH 36 - 10 - 00 - 710 - 80 2 - CMR OPERATIONAL TEST OF THE DISTRIBUTION / BLEED AIR SYSTEM (MANIFOLD PRESSURE REGULATING AND SHUT OFF VALVES) 1850 FH MPRSOV operating 38 - 16 - 00 - 710 - 801 - CMR OPERATIONAL TEST OF THE OPTIONAL SHOWER TEMPERATURE CONTROL SYSTEM 20,000 FH A/C with optional shower system 38 - 16 - 0 7 - 710 - 801 - CMR OPERATIONAL TEST OF THE OPTIONAL SHOWER WATER HEATER CONTACTORS 650 FH A/C with optional shower system

# FALCON 7X MAINTENANCE MANUAL

EFFECTIVITY : ALL Page « DASSAULT AVIATION Proprietary Data » 16/JUL /2012 DGT 107838 Revision 3 20 MPD task Code Oper Origin Title Max Time Limit comment effectivity 52 - 30 - 00 - 200 - 801 02 CMR VISUAL INSPECTION OF THE BAGGAGE COMPARTMENT DOOR LOCKING MECHANISM 20,000 FH 52 - 53 - 00 - 210 - 801 - CMR GENERAL VISUAL INSPECTION OF THE CABIN / BAGGAGE COMPARTMENT DOOR 20,000 FH CMR is seal integrity 52 - 70 - 00 - 710 - 802 01 CMR OPERATIONAL TEST OF THE DOOR INDICATING SYSTEM 20,000 FH 78 - 30 - 00 - 720 - 802 - CMR FUNCTIONAL TEST OF THE TR ACCUMULATOR SYSTEM 2500 FH accumulator and check valve 78 - 31 - 13 - 710 - 801 - CMR OPERATIONAL TEST OF THE THRUST REVERSER DOOR ACTUATOR LOCKS 2500 FH



### END OF DOCUMENT