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AIRWORTHINESS LIMITATIONS

CHAPTER 5-40-00

090040008019acf1 - RELEASED - Certification Repository
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AIRWORTHINESS LIMITATION SECTION

This Airworthiness Limitation Section contains instructions pertaining to the Airworthiness of 

the Falcon 7X aircraft, including CMR, ALI and Safe Life limitations, applicable until Design 

Service Goal (refer to § 1.A.).

The tasks and intervals specified are mandatory and cannot be changed, escalated, or 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 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 than Fatigue Airworthiness 

Limitation Sections
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List of Revisions

PAGES No. REVISION EFFECTIVITY

5-40-00 

(Page 1 to page 12)

Original Issue

(AMM cross-references completed)

ALL 

(Only life limits below 

4000 FC. See §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 4800FH 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: operations 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 5and 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 results

ALL 

Extension of Service life

up to DSG 

5-40 00

All pages

Revision Two (Rev 2), managed through R5018, mainly including:

- Already approved changes of Chapter 5-40 through miscellaneous CP. Refer 

to the under paragraph for the detailed list of CP.

ALL 

5-40 00

All pages

Revision Three (Rev 3), managed through R5025, mainly including:

- Already approved changes of Chapter 5-40 through miscellaneous CP. Refer 

to the under paragraph for the detailed list of CP. Under of paragraphs 1-D and 

2-B related to CPCP.

ALL

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.
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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 :

- Effective Date of Rev 03: 15/OCT/2012
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1 GENERAL 

A. DESIGN SERVICE GOAL

The Falcon 7X Design Service Goal (DSG) is 20,000 flights/50,000 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 rescue 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 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

- which must have implemented the applicable Airworthiness Directives.

Non standard 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 maintenance of a Standard Aircraft must be performed in accordance with:

- either Maintenance Manual and Structural Repair Manual

- or other approved maintenance procedures.
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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 such 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 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. (See instructions § 2B CPCP).

E. IMPORTANT:

The instructions contained in this document must be imperatively observed by the operators.
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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 mandatory 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 revision 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.
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2. INSTRUCTIONS

A. INSTRUCTIONS FOR CDCCL

(Critical Design Configuration Control Limitations). 

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 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 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"

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

- bonding quality (operations 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

28-21-25-900-801 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 

Respects of:

- FQIS wiring segregation 

- and Feeder versus fuel pipe routing 

segregation
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B. INSTRUCTIONS FOR CORROSION PREVENTION CONTROL PROGRAM

The operator 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.
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3. AIRFRAME COMPONENTS WITH LIMITED SERVICE LIFE (“SAFE LIFE”)

Fatigue and qualification tests 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 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.

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; and it is sufficient 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: use 

the current aircraft values of the ageing parameter(s) of those P/N to initialize their 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

106138-02

106139-02

20,000FC / 

50,000FH
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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

53 FUSELAGE

T34: Rear tank upper panel FR 27 to 

FR 28 F7XC258420B1 4100 FC

All except those with 

M773 or M883

T5 - Frame 37 upper blind fasteners (fasteners as per 

M625)

4100 FC All without 

M625

T5 - Frame 37 gusset (as per M626) 4100 FC All without 

M626

Connection between main landing gear 

actuator door fitting and the landing 

gear bay lateral web

(as per M571) 12,100FC All without M571

Front lower T34 stringer 15 at finger 

doubler crossing area (as per M452) 12,500FC All without M452

FH=Flight Hours FC=Flight Cycles CT= Calendar Time
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4. FATIGUE AND DAMAGE TOLERANCE AIRWORTHINESS LIMITATIONS

A list of inspections has 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 threshold 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/FDs (Airworthiness LImitations 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 03 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

53-10-00-200-809 01 ALI/FD DETAILED 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 / 

4100FC

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
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MPD task Code 

Oper Origin Title Max Limit comment effectivity

53-30-00-200-804 01 ALI/FD DETAILED FATIGUE INSPECTION OF SECTION T34 INNER SIDE 12100FC / 

4100FC

53-30-00-200-805 01 ALI/FD DETAILED FATIGUE INSPECTION OF SECTION T34 OUTER SIDE 12100FC / 

4100FC

53-30-00-200-806 01 ALI/FD FATIGUE INSPECTION OF THE PANEL OUTER SKIN AT THE 

FOUR CUT-OUT CORNERS

12100FC / 

4100FC

53-30-00-280-801 01 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION (HFEC) OF 

EMERGENCY EXIT SURROUNDING

12100FC / 

4100FC

53-40-00-200-801 03 ALI/FD INSPECTION OF THE WING-TO-FUSELAGE JUNCTION - DET 

FATIGUE INSPECTION

12100FC / 

4100FC

53-40-00-200-804 02 ALI/FD INSPECTION OF THE MLG BAYS 12100FC / 

4100FC

rear spars 1, 2, 4

53-40-00-200-809 - ALI/FD DETAILED FATIGUE INSPECTION OF REAR FUEL UPPER PANEL 

/ ROOF OF LOWER FR26 TO FR28

8100FC / 

4100FC

53-40-00-280-805 01 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE REAR FUEL 

TANK UPPER PANEL - REAR FUEL TANK UPPER PANEL 

STIFFENER TOPS AT FRAME 27

8100FC / 

4100FC

53-40-00-280-805 02 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE REAR FUEL 

TANK UPPER PANEL - REAR FUEL TANK UPPER PANEL FROM 

FRAME 27 TO FRAME 28

4100FC / 

4100FC

A/C without 

M773 and 

without M883

53-50-00-200-802 02 ALI/FD INSPECTION OF THE JUNCTION BETWEEN INNER SHEET METAL 

AND BAGGAGE COMPARTMENT SKIN

12100FC / 

4100FC

53-50-00-200-805 02 ALI/FD INSPECTION OF THE SERVICING COMPARTMENT INTERNAL 

STRUCTURE OVERFLOOR

12100FC / 

8100FC

53-50-00-200-807 02 ALI/FD INSPECTION OF THE FRAME 33 REAR SIDE AND THE LOWER 

SIDE OF THE BAGGAGE COMPARTMENT FLOOR STRUCTURE

12100FC / 

4100FC

53-50-00-200-811 01 ALI/FD FATIGUE INSPECTION OF THE BAGGAGE COMPARTMENT -

VISUAL FATIGUE INSPECTION

12100FC / 

4100FC

53-50-00-200-811 02 ALI/FD FATIGUE INSPECTION OF THE BAGGAGE COMPARTMENT -

BORESCOPE FATIGUE INSPECTION

12100FC / 

4100FC

53-50-00-220-801 - ALI/FD DETAILED INSPECTION OF THE RH SKIN DOUBLER OF 

BAGGAGE COMPARTMENT

12100FC / 

8100FC

A/C S/N 02 and 

S/N 03

53-50-00-280-803 01 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION (LFEC) UNDER SDUCT12100FC / 

4100FC

53-50-00-280-804 01 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION AT THE MANDOLINSHAPED STUB JUNCTION AND UNDER THE S-DUCT12100FC / 

4100FC

53-50-00-280-806 01 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION (HFEC) INSIDE 

BAGGAGE COMPARTMENT

12100FC / 

4100FC

54-50-00-200-801 01 ALI/FD INSPECTION OF THE ENGINE PYLONS INTERNAL STRUCTURE 12100FC / 

8100FC

54-50-00-200-802 02 ALI/FD INSPECTION OF THE ENGINE PYLONS JUNCTION WITH 

FUSELAGE SKIN

12100FC / 

4100FC

55-30-00-200-802 02 ALI/FD INSPECTION OF THE VERTICAL STABILIZER ATTACHMENT 

FITTINGS

12100FC / 

4100FC

57-40-00-200-802 02 to 

09

ALI/FD INSPECTION OF THE SLATS AND FRONT SPAR 8100FC / 

4100FC

(see note)

57-40-00-280-801 01 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION ON FRONT SPAR OF 

WING AT ROLLER SUPPORT FITTINGS

8100FC / 

4100FC

57-40-00-280-802 02 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE FASTENER 

HOLES AT THE FRONT SPAR / WING LOWER PANEL 

CONNECTIONS - HFEC FATIGUE INSPECTION

12100FC / 

8100FC

57-40-00-280-803 01 ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE FASTENER 

HOLES AT THE FRONT SPAR / WING LOWER PANEL 

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

001MA001 (LH), 

071MA069 

073MA071
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MPD task Code 

Oper Origin Title Max Limit comment effectivity

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

3400FC / 

3400FC

A/C without wing 

S/N 

001MA001(LH), 

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 (RH), 

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

8100FC / 

4100FC

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 07 and 

08

ALI/FD SPECIAL DETAILED FATIGUE INSPECTION OF THE SLATS 12100FC / 

8100FC

(see note)

Slat P/N

F7XC574300000

F7XC574400000

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

F7XC577431W8

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)
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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 Flight Cycles accomplished by the concerned removable items must be traced for these inspections.
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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 4850FH

21-32-01-720-802 - CMR FUNCTIONAL TEST OF THE MANUAL MODE OF THE CABIN 

INTEGRATED PRESSURE CONTROL SYSTEM (IPCS) VALVE

4850FH

21-32-01-720-801 - CMR FUNCTIONAL TEST OF THE ''DUMP'' FUNCTION OF THE 

CABIN INTEGRATED PRESSURE CONTROL SYSTEM (IPCS) 

VALVE

4850FH

21-32-13-720-801 - CMR FUNCTIONAL TEST OF THE CABIN POSITIVE PRESSURE 

RELIEF VALVE

4850FH

21-32-17-720-801 - CMR FUNCTIONAL TEST OF THE BAGGAGE COMPARTMENT 

POSITIVE PRESSURE RELIEF VALVE

4850FH

21-32-25-710-801 - CMR OPERATIONAL TEST OF THE COCKPIT NEGATIVE 

PRESSURE RELIEF VALVE

4850FH

21-32-29-710-802 - CMR OPERATIONAL TEST OF THE FLAPPER OF THE GROUND 

MODE VENT AND NEGATIVE PRESSURE RELIEF VALVE

4850FH

21-32-33-710-801 - CMR OPERATIONAL TEST OF THE BAGGAGE COMPARTMENT 

ISOLATION VALVES

4850FH

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 SBF7X-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

24-32-01-710-802 - 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.
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DGT 107838 Revision 3

17

MPD task Code 

Oper Origin Title Max Time Limit

comment 

effectivity

24-32-01-710-801 - CMR OPERATIONAL TEST OF BATTERYHEATER 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 SBF7X-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 08 CMR FUNCTIONAL TEST OF THE PNEUMATIC FIRE DETECTORS

LH MLG BAY

20,000FH

26-10-00-720-801 09 CMR FUNCTIONAL TEST OF THE PNEUMATIC FIRE DETECTORS

RH MLG BAY

20,000FH

26-20-01-710-801 - 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
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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 02 CMR OPERATIONAL TEST OF THE TRIM UNIT 2000 FH 02= 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

28-00-00-720-801 - 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
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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

29-30-01-720-801 - 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 SBF7X-020

31-41-01-960-801 - ALI DISCARD OF THE MAU CHASSIS 2500 FH A/C without 

M715 or SBF7X-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 FUSES 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

32-50-05-350-801 - ALI RESTORATION OF THE STEERING COMMAND 8000 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

35-10-01-350-801 - CMR RESTORATION OF THE CREW OXYGEN MASK-REGULATORS 

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

36-10-00-710-802 - CMR OPERATIONAL TEST OF THE DISTRIBUTION / BLEED AIR 

SYSTEM (MANIFOLD PRESSURE REGULATING AND SHUTOFF 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

38-16-07-710-801 - CMR OPERATIONAL TEST OF THE OPTIONAL SHOWER WATER 

HEATER CONTACTORS

650 FH A/C with 

optional 

shower system
FALCON 7X

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« 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 checkvalve

78-31-13-710-801 - CMR OPERATIONAL TEST OF THE THRUST REVERSER DOOR 

ACTUATOR LOCKS

2500 FH

END OF DOCUMENT