FALCON 50/50EX

MAINTENANCE MANUAL

CHAPTER 5-40

AIRWORTHINESS LIMITATIONS

ORIGINAL - FEBRUARY 1979

REVISION 21 - JUNE 2011

"This document is proprietary to DASSAULT AVIATION. It cannot be used, reproduced,

modified or disclosed without its authorization. DASSAULT AVIATION Proprietary Data."

"© Copyright DASSAULT AVIATION/SOGITEC, 2008"

DGT 113872- PUB 237 or 238

0900400080497332 - VALIDATED - Certification Repository 0900400080464c13 - RELEASED - Certification Repository
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CONTENTS

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CONTENTS

TITLE PAGE

06/2011 ALL - Reference DGT 113872

05-40 : AIRWORTHINESS LIMITATIONS (Reference DGT 113872)

05-40/00 AIRWORTHINESS LIMITATIONS

06/2011 ALL - Reference DGT 113872

05-40/01 NOTE TO USERS

CHAPTER 5

SECTION 5-40

06/2011 ALL - Reference DGT 113872

CHAPTER 5-40

Effectivity: ALL - Reference DGT 113872
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NOTE TO USERS

CHAPTER 5

Section 5-40

Please find enclosed Revision No. 21 of Section 5-40.

Modifications and corrections contained in this revision are listed hereafter:

UP Number Section Modifications and Correction TR/CP 

Number

05-40/00 §1 Wording corrections CP 010

§2 Updated (new CPCP approach) CP 010
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AIRWORTHINESS LIMITATIONS

This section contains instructions pertaining to Airworthiness of aircraft, including SSIP, CPCP and Safe Life 

limitations until the Limit of Validity (refer to paragraph A. 1).

These instructions are rendered mandatory by Airworthiness Directives issued by the country of registration.

For U.S. Registered aircraft, this section is European Aviation Safety Agency approved on behalf of FAA and 

specifies maintenance required under paragraphs 43.16 and 91.409 of the Federal Aviation Regulations, unless an 

alternative program has been FAA approved. Evaluations and reasons for this section do not take into account the 

influence of modifications or repairs not approved by DASSAULT AVIATION such as STC.

Section 05-40/00

This section is divided into four paragraphs:

- 1. General

- 2. Instructions

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

- 4. Mandatory maintenance operations.

SECTION REVISION No. EFFECTIVITY

05-40/00 Revision 21 ALL

Approved by:

Date of approval:

- Original: February 26, 1979

- Revision 1: February 10, 1984

- Revision 2: February 28, 1984

- Revision 3: January 16, 1985

- Revision 4: January 28, 1986

- Revision 5: July 10, 1987

- Revision 6: April 15, 1988

- Revision 7: August 26, 1988

- Revision 8: January 8, 1990

- Revision 9: February 7, 1997

- Revision 10: October 27, 1997

- Revision 11: January 07, 2000

- Revision 12: April 19, 2000

- Revision 13: June 13, 2002

- Revision 14: July 19, 2002
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- Revision 15: EASA approved under EASA 2004-7863 on August 2, 2004

- Revision 16: EASA approved under EASA A.C.04307 Revision 1 on July 13, 2006

- Revision 17: DGT 113872 supersedes DMD 11765 §05-40, EASA approved under EASA.A.C.08114 on 

October 19, 2007 

- Revision 18: This revision 18 is the compilation of the following EASA approved changes, with no further technical 

change:

• TR 001 approved by letter EASA.C.10436 dated August 15, 2008

• TR 002 approved by letter EASA.C.10847 dated April 20, 2009

• TR 003 approved by letter EASA.C.11233 dated January 21, 2009

The technical content of this revision is approved under DOA EASA.21J.051 authority by reference R5001. This 

approval means that the revision has been prepared exclusively with already EASA approved data and is 

released under DOA procedures.

Effective date of revision: October 09, 2009.

- Revision 19: This revision 19 is the compilation of the following EASA approved changes, with no further technical 

change:

• TR 004 approved by letter EASA.A.C.11275 dated March 27, 2009

• CP 006 approved by letter EASA 10028526 dated January 19, 2010

The technical content of this revision is approved under DOA EASA.21J.051 authority by reference R5006. This 

approval means that the revision has been prepared exclusively with already EASA approved data and is 

released under DOA procedures.

Effective date of this revision: March 15, 2010.

- Revision 20: This revision 20 is the compilation of the following EASA approved changes, with no further technical 

change:

• CP 007 approved by letter EASA 10030887 dated July 12, 2010

• CP 009 approved by letter EASA 10032063 dated October 06, 2010

The technical content of this revision is approved under DOA EASA.21J.051 authority by reference R5014. This 

approval means that the revision has been prepared exclusively with already EASA approved data and is 

released under DOA procedures.

Effective date of this revision: November 19, 2010.

- Revision 21: This revision 21 is the compilation of the following EASA approved changes, with no further technical 

change:

• CP 010 approved by EASA under change reference M3195

The technical content of this revision is approved under DOA EASA.21J.051 authority by reference R5019. This 

approval means that the revision has been prepared exclusively with already EASA approved data and is 

released under DOA procedures.

Effective date of this revision: June 10, 2011.
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1. GENERAL

A. DEFINITION OF THE LIMIT OF VALIDITY (L.O.V.)

The Limit Of Validity represents the upper limit expressed in "flights" until which an aircraft can fly in total 

security without appearance of WFD (Widespread Fatigue Damages). The L.O.V. of a standard aircraft 

MYSTERE-FALCON 50 (refer to paragraph B.) is 40,000 flights/60,000 flying hours whichever occurs first.

For a standard aircraft (refer to paragraph B.), to facilitate scheduling of maintenance operations expressed in 

"FLIGHTS", a flight is considered as equivalent to a landing.

For a non-standard aircraft, a flight is not automatically considered as a landing. That is why, "flights" have to 

be recorded regarding a specific definition established by DASSAULT AVIATION. In this case, contact 

DASSAULT AVIATION for appropriate program.

B. DEFINITION OF A STANDARD AIRCRAFT

This program is defined for a "STANDARD AIRCRAFT" as defined below.

For non-standard aircraft, this program needs to be adapted with Instructions for Continued Airworthiness 

developed to cover the non-standard features (STC, repairs, operating conditions,...) up to the L.O.V.

1. Standard Aircraft Primary structure must be entirely identical to DASSAULT AVIATION type design:

- Condition of the primary structure of a standard aircraft has to correspond to definition at aircraft delivery:

• which can be supplemented by the DASSAULT AVIATION Service Bulletins incorporated on aircraft,

• which must have incorporated the applicable mandatory Service Bulletins.

- An aircraft cannot be considered as a standard aircraft if:

• its primary structure has been changed by an STC or repaired through a definition not reviewed by 

DASSAULT AVIATION in the frame of the applicability of these instructions.

2. Aircraft operations should be close to the fatigue load spectrum defined during type certification. This 

spectrum corresponds to public or private transport defined by short, middle and long distance flights.

When types of mission listed hereafter are performed on a regular basis, the aircraft can not be considered 

as a Standard Aircraft:

- Low altitude search and rescue flights.

- Target towing and transport of under wing stores.

- Scientific research.

- Cargo transport.

- Flight training.

- Others types of operation than normal passenger transport.

3. Maintenance must have been performed in accordance with:

- The Maintenance Manual or Structural Repair Manual (formerly Maintenance and Repair Instructions) 

recommended by DASSAULT AVIATION,

- or approved maintenance procedures.
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C. IMPORTANT

The following instructions must be observed by the operators.

The mandatory nature of these instructions does not in any way reduce the importance of the other tasks 

listed in the Recommended Maintenance Manual Program which must be performed in agreement with the 

National Airworthiness Authorities.

In order to help operators in planning their maintenance program and to reduce grounding due to scheduled 

maintenance, these mandatory operations are also listed in section 05-10, 05-15 or 05-20, with time limits 

corresponding to the aircraft inspections (A, B, C, etc.) or expressed as a number of flights. Therefore 

operation codes given in section 05-40 and in sections 05-10, 05-15 or 05-20 can be different.

D. UPDATING OF SECTION 05-40/00

When a new maintenance operation is added, due to a revision of Chapter 5 section 05-40/00, this new 

operation must be performed when the time at which it is scheduled falls due, unless otherwise specified.

2. INSTRUCTIONS

A. SERVICE BULLETIN SB F50-450♦

SB F50-450 is a prerequisite to the application of SSIP program.

♦

NOTE: Dedicated Supplemental Maintenance procedures for SSIP are not included in AMM.

They are delivered attached to corresponding SB.

B. STRUCTURAL SUPPLEMENTAL INSPECTION PROGRAM

NOTE: SB F50-450 shall be embedded before applying the SSIP inspections defined in the 

chapter 05-40/00 section 4.

The Supplemental Structural Inspection Program (SSIP) must be applied to aircraft that have reached the 

"mid life" of its L.O.V. with a continuing structural integrity program in accordance with manufacturer 

Recommended Maintenance Schedule, T.B.O. and Chapter 5. The operator must include in his maintenance 

program the maintenance operations linked with structural inspection for fatigue defects (those operations are 

marked with "SSIP" in the column "Origin" of the Table of mandatory maintenance procedures in 

chapter 05-40/00 section 4 and SB F50-450 Work Card numbers (WC) are given in the column "Maint. Proc.").

Any defect detected during SSIP inspection or zonal inspection as per maintenance procedure 20-010 (or new 

AMTOSS numbering 20-10-00 SDS) must be reported to the manufacturer.
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C. CORROSION PREVENTION CONTROL PROGRAM

♦

NOTE: Refer to chapter 05-15 for definitions of Level 1, 2 and 3 corrosion.

A CPCP is a systematic approach for controlling corrosion in the airplane's primary structure. It is a program 

of maintenance tasks designed to control an aircraft structure to Corrosion level 1 or better (Chapter 05-15 

and EASA AMC 20-20 provide further details).

During the whole life of the aircraft, the operator is required to maintain the aircraft structure to level 1 of 

corrosion or better on Principal Structural Element [PSE, Ref. to list in SRM number 51-00-01 (or new 

SRM AMTOSS numbering 51-00-02 RPI)].

In order to control the aircraft structure to corrosion level 1 or better on PSEs, the operator should implement 

a CPCP as per Chapter 05-15 (baseline) and to comply and conform to the aircraft maintenance manual

tasks listed in Chapter 5.10 and 5.20.

♦

This baseline CPCP should be adapted by the operator to take into account "non standard" features of his 

aircraft, if any. In this case, the operator can find some guidelines in Chapter 05-15.

DASSAULT AVIATION is responsible for monitoring the effectiveness of the Baseline Program and the 

pertinence of the inspection threshold and, if necessary, to define changes based on analysis of the operators 

reported findings. Consequently, operators are mandated to report any finding affecting a PSE to 

DASSAULT AVIATION when corrosion level 2 or 3 is found. This will allow DASSAULT AVIATION to justify 

periodicity changes and to publish updates of the baseline CPCP.

NOTE: Reporting of Level 1 corrosion that is recurrent in the same location or nil finding is also of 

interest to DASSAULT AVIATION and should be reported to assist in understanding the aging 

of the fleet and the possible need for escalation or alleviation of maintenance program.
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3. AIRFRAME COMPONENTS WITH LIMITED SERVICE LIFE ("SAFE LIFE")

The airframe components with limited service life are listed in the table below.

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), 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 05-40/00, will not be 

exceeded.

COMPONENT DENTIFICATION PART NUMBER LIMITED SERVICE LIFE OPERATION 

CODE

32 LANDING GEAR

- Nose gear (See NOTE (1)) C23787-10XX 20,000 landings 322101

- LH main landing gear C23791-10XX 20,000 landings 321101

- RH main landing gear 

except for the following 

components:

C23792-10XX 20,000 landings 321106

• Main landing gear strut 

actuator dash-pot sleeve

D52369

(see NOTE (2))

3550 landings

(A/C 1 to 85 before

SB F50-0124 only)

321104

321109

• Main landing shock absorber 

end-fitting

D50493

(see NOTE (2))

Before SB F50-0123

(A/C 1, 3 to 39)

16,000 landings

321105

321110

After SB F50-0123

20,000 landings

• Rear landing gear shaft D48611

D52554-1

D52554-2

18,670 landings

(A/C after SB F50-0161 only

(MTOW: 18.5 T))

321117

321118
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COMPONENT IDENTIFICATION PART NUMBER LIMITED SERVICE LIFE OPERATION 

CODE

52 DOORS

- Emergency exit F50B296001XX 26,718 flights 522101

522121

53 FUSELAGE

- Central wing section

(for F50 S/N 107 only)

F50B237B5 17,760 flights 570701

54 NACELLES/PYLONS

- No. 1 and No. 3 engines 

rear attachment auxiliary 

fitting bolt introduced by 

SB F50-0113 associated 

with French D.G.A.C.

307336-1-1 1050 hours 540173

540193

 Airworthiness Directive 

 No. 81-226-1(B)

57 WINGS

- Central hinge of RH and LH 

outboard airbrakes

F50B165003001

FGFC165003001

20,000 flights 575186

575181

NOTE (1): Each landing on an unpaved runway shall be multiplied by 2 for the nose gear when 

calculating limited service life.

NOTE (2): Concern shock absorber C23795-10... and C23796-10...
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4. MANDATORY MAINTENANCE OPERATIONS

Operations associated with fatigue are marked with "SSIP" in the column "Origin".

ATA 100 

No. ORIGIN DESCRIPTION MAINT. 

PROC.

OPERATION 

CODE

INSPECTIONS

THRESHOLD INTERVAL

21 AIR CONDITIONING

21-24-01 - Operational test of 

baggage compartment 

supply (154H) and shut 

off (153H) valves

21-010 212167

212179

650 hrs 650 hrs

21-30-01 - Check of cabin sealing in 

flight or ground test

21-080 or 

21-090

213232 7000 flights 

then 

10,000 flights 

then 700 flights

21-31-02 - Operational test of 

pressurization system in 

manual mode only for 

aircraft equipped with 

pressurization controller 

P/N 22201N061000 or 

P/N 22201D131700

21-100 213242 1550 hrs

21-32-02 - Functional test of 

baggage compartment 

pressure relief/vaccum 

pressure relief valves

21-180 213187

213207

3700 hrs

See 

chap. 5-20

- Functional test of 

maximum altitude safety 

limitation of regulating 

valves

213129

213119

5000 hrs

See 

chap. 5-20

- Check of overpressure 

tightness:

• Electropneumatic 

regulating valve

• Pneumatic regulating 

valve

• Check of overpressure 

relief valve vacuum 

supply lines

21-160

21312A

21311A

211602

1640 hrs

1640 hrs

7500 hrs

22 AUTO FLIGHT

See 

chap. 5-20

- Overhaul of Yaw Damper 

only for aircraft equipped 

with P/N 822-1793-001 or 

P/N 822-1795-001

221056 3000 hrs
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ATA 100 

No. ORIGIN DESCRIPTION MAINT. 

PROC.

OPERATION 

CODE

INSPECTIONS

THRESHOLD INTERVAL

25 EQUIPMENT FURNISHING

25-10-00 - Visual inspection of 

buckle spring of Anjou 

Aeronautic safety belts 

and restraint system 

type 343 and type 343-1 

using Anjou Aeronautic 

SB No. 343-1-25-01 and 

343-25-02

(*) Life limit of 60 months on 

Anjou safety belts and 

restraint system

251006 18 months (*)

See 

CN 2002-105 

(AB) and 

CN 2002-104 

(AB)

26 FIRE PROTECTION

26-10-01 - Functional test of 

detectors (operation of 

the pressure warning 

switch)

26-380 261142

261147

261152

261157

261162

261164

261167

5600 hrs

27 FLIGHT CONTROLS

27-40-02 - Operational test of the 

horizontal stabiliser 

control system (check of 

control switches)

27-410 274127 5000 hrs

27-40-06 - Functional test of the 

horizontal stabilizer trim 

control box (all relays)

27-896 274157 5000 hrs

27-60-02 - Functional test of airbrake 

control panel 

(microswitch test)

27-720 276212 10,000 hrs

See 

chap 5-20

- Functional test of the gust 

damping valves and 

non-return valves on 

rudder and pitch power 

servo units

272109

273114

278291

10,000 hrs
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ATA 100 

No. ORIGIN DESCRIPTION MAINT. 

PROC.

OPERATION 

CODE

INSPECTIONS

THRESHOLD INTERVAL

28 FUEL

28-20-01 - Standard servicing and 

maneuvering of shut-off 

valve control

28-180 282242

282267

282292

330 hrs

28-20-02 - Sealing test of shut-off 

valve

28-190 282017

282037

282057

1530 hrs

31 INDICATING -

RECORDING SYSTEM

31-50-07 - Test of EIED 

reconfiguration (A/C with 

engine TFE 731-40)

31-070 315001 1530 hrs

52 DOORS

52-51-03 - Operational test of 

"S Duct" access door 

indicating

52-300 525102 10,000 hrs

52-20-01 - Unlocking test from inside 

of emergency exit LH and 

RH

(AD EASA 

No. 2006-0149)

52-040 522112

522132

24 months

53 FUSELAGE

53-00-05 - Inspection check of 

fuselage structural fuel 

tank

53-250 530102 6 years and 

2 months

53-00-11 - Visual inspection of 

attachment fitting of nose 

landing gear actuator

53-400 530132 10,000 landings 7500 landings

53-00-16 - Internal inspection/check 

of fuselage structural fuel 

tank

NOTE: Inspection to be 

performed at the 

next C inspection 

from effective date 

of revision 20

53-008 530367 6 years and 

2 months
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ATA 100 

No. ORIGIN DESCRIPTION MAINT. 

PROC.

OPERATION 

CODE

INSPECTIONS

THRESHOLD INTERVAL

53-00-21 SSIP - Visual inspection of 

cockpit window lower

53-280 530327 20,000 flights 3750 flights

53-00-27 - Sealing test of feeder 

tanks (for A/C S/N 222 to 

286, 288, 290, 291 and 

without SB F50-328)

53-360 530362 7 months 13 months

53-00-50 - Pilot's and co-pilot's 

window frame with 

frame 0 - Inspection of 

linking screws

53-120 530212

 A/C without M281 6674 flights 3400 flights

 A/C with M281 10,525 flights 3750 flights

53-00-51 - RH bad weather window 

frame inspection

53-040 530227

 A/C without M322 10,050 flights 2719 flights

53-00-53 - LH and RH rear window 

frame inspection

53-070 530237

530239

 A/C S/N < 42 except 

 S/N 31, and without 

 SB F50-198

16,192 flights 2854 flights

 A/C S/N < 42 except 

 S/N 31, and with 

 SB F50-198

12,000 flights 2000 flights

53-00-54 - Baggage compartment 

door forward side fold 

inspection

52-240 530242

 A/C without M142 7034 flights 3028 flights

53-00-55 - Visual inspection of the 

upper stops of the 

passenger door

52-170 530247

 A/C without M141 5995 flights 2000 flights

 A/C with M141 11,435 flights 3750 flights

53-00-56 - Visual inspection of the 

angle between floor and 

beam in T3 section

53-170 530252

 A/C without M313 16,192 flights 4764 flights

SSIP A/C with M313 20,000 flights 7500 flights

53-00-57 SSIP - Baggage compartment - 

Visual inspection of 

frame 35

53-240 530222 20,000 flights 3750 flights
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ATA 100 

No. ORIGIN DESCRIPTION MAINT. 

PROC.

OPERATION 

CODE

INSPECTIONS

THRESHOLD INTERVAL

53-00-58 SSIP - Non-destructive testing of 

windows vertical posts in 

the cockpit area

53-295 530307 20,000 flights 3750 flights

53-00-59 SSIP - Non-destructive testing of 

the cockpit window 

frames, pilot and copilot 

windshield:

 LH/RH front window,

 LR/RH side window,

 LH/RH rear window

(WC 688.0/0) 530059 20,000 flights 3750 flights

53-00-60 SSIP - Visual inspection of skin 

panels in T2, T3 and 

T4 sections (longitudinal 

cracks)

(WC 688.0/1) 530060 20,000 flights 3750 flights

53-00-61 SSIP - Non-destructive testing of 

the corners of the 

passenger/crew door 

frame

(WC 688.0/2) 530061 31,250 flights 3750 flights

53-00-62 SSIP - Non-destructive testing of 

the fuselage framework 

around the windows in T2 

and T3 sections 

(longitudinal crakcs)

(WC 688.0/3) 530062 31,250 flights 7500 flights

53-00-63 SSIP - Non-destructive test of the 

nose landing gear well 

radius

(WC 688.0/4) 530063 31,250 flights 3750 flights

53-00-65 - Visual inspection of the 

angle between frame 27 

foot and floor, and of the 

floor panel in the alleyway 

between frame 26 and 29

53-500 530065 10,000 flights 3750 flights

53-00-66 SSIP - Visual inspection of the 

baggage compartment 

door

(WC 688.0/7) 530066

 A/C with M142 26,299 flights 3750 flights

53-00-67 SSIP - Visual inspection of 

frame 34 in upper and 

lower parts

(WC 688.0/8) 530067 20,000 flights 3750 flights

53-00-68 SSIP - Visual inspection of the 

floor omegas at 

frames 18-19

(WC 688.0/9) 530068 27,500 flights 7500 flights
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ATA 100 

No. ORIGIN DESCRIPTION MAINT. 

PROC.

OPERATION 

CODE

INSPECTIONS

THRESHOLD INTERVAL

53-00-70 SSIP - Visual inspection of the 

cockpit upper skin at the 

windshield and glass 

frame assembly 

attachment

(WC 688.1/1) 530070 20,000 flights 1272 flights

53-00-71 SSIP - Mapping of lower wing 

center section lower panel

53-700 

(WC 688.1/2)

530071 20,000 flights 7500 flights

53-00-73 SSIP - Visual inspection of wing 

center section lower 

panels

(WC 688.1/4) 530073 20,000 flights 7500 flights

53-00-74 SSIP - Non-destructive testing of 

wing center section lower 

panels splice

(WC 688.1/5) 530074 20,000 flights 7500 flights

53-00-75 SSIP - Non-destructive testing of 

emergency exit frame 

edging

(WC 688.1/6) 530075 20,000 flights 7500 flights

53-00-76 SSIP - Non-destructive testing of 

the finger plate of the 

circumferencial splice at 

frame 19 and 26

(WC 688.1/7) 530076 20,000 flights 7500 flights

53-00-78 SSIP - Non-destructive check of 

frame 35 vertical beam

(WC 688.1/9) 530078 20,000 flights 3750 flights

53-00-79 SSIP - Non-destructive check of 

floor between frames 31 

and 35

(WC 688.2/0) 530079 20,000 flights 3750 flights

53-00-80 SSIP - Visual inspection of lower 

fin, front spar

(WC 688.2/1) 530080 20,000 flights 7500 flights

53-00-81 SSIP - Non-destructive check of 

rear passenger door 

frame (FR 12) between 

rib 17 and 18

(WC 688.2/2) 530081 20,000 flights 3750 flights

53-00-90 SSIP - Visual inspection of 

pylons, upper flange rib at 

frame 32

(WC 688.9/0) 530090 20,000 flights 7500 flights

53-00-92 - Visual check of central 

wing section

(for F50 S/N 107 only)

53-380 570706 Oct. 2012 6 years and 

2 months
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ATA 100 

No. ORIGIN DESCRIPTION MAINT. 

PROC.

OPERATION 

CODE

INSPECTIONS

THRESHOLD INTERVAL

54 NACELLES AND PYLONS

54-00-21 SSIP - Visual inspection for 

cracks on lateral engines 

front and rear mounts

(WC 688.9/1) 540021 20,000 flights 3750 flights

54-00-22 SSIP - Visual inspection of 

engine 2 hoisting fitting 

plate and mounts

(WC 688.2/3) 540022 20,000 flights 3750 flights

55 STABILIZERS

55-10-02 SSIP - Visual inspection of front 

and rear upper panels 

between the horizontal 

stabilizer root and Rib 2

(WC 706.0/0) 551002 20,000 flights 7500 flights

55-20-03 SSIP - Visual inspection of the 

elevators skin and the 

elevator hinge fittings

(WC 706.1/0) 552003 20,000 flights 3750 flights

55-40-03 SSIP - Visual inspection of the 

rudder skin and the 

rudder hinge fittings

(WC 706.2/0) 554003 20,000 flights 3750 flights

55-50-01 - Dimensional check of 

horizontal stabilizer rear 

hinge bushes (refer to 

A.D. 

No. 1997-370-020 R2)

55-150 555002 3750 flights 3750 flights

55-50-02 SSIP - Non-destructive testing of 

forward and rear fittings 

of fin and horizontal 

stabilizer

(WC 706.3/0) 555002A 20,000 flights 3750 flights

55-50-03 SSIP - Visual inspection of 

horizontal stabilizer 

actuator attachment 

fittings and pins on 

structure side and on 

stabilizer side

(WC 706.3/1) 555003 20,000 flights 3750 flights
FALCON 50

CHAPTER 5

 Effectivity: ALL - Reference DGT 113872

Rev. Date: 06/2011

05-40/00

Page 15/16

"DASSAULT AVIATION Proprietary Data"

ATA 100 

No. ORIGIN DESCRIPTION MAINT. 

PROC.

OPERATION 

CODE

INSPECTIONS

THRESHOLD INTERVAL

57 WINGS

57-00-07 - Inspection / endoscopic 

check of wing structural 

fuel tanks

57-040 570302 6 years and 

2 months

57-00-12 SSIP - Mapping of lower wing 

panels

57-701 

(WC 728.0/0)

570012 20,000 flights 7500 flights

57-00-14 SSIP - Visual inspection of lower 

wing panels

(WC 728.0/2) 570014 20,000 flights 7500 flights

57-00-15 SSIP - Non-destructive testing of 

wing front spar (except 

between ribs 8 and 9)

(WC 728.0/3) 570015 20,000 flights 7500 flights

57-00-16 SSIP - Non-destructive testing of 

wing front spar between 

ribs 8 and 9

(WC 728.0/4) 570016 20,000 flights 3750 flights

57-00-17 SSIP - Non-destructive testing of 

wing rear spar 2

(WC 728.0/5) 570017 20,000 flights 7500 flights

57-00-18 SSIP - Non-destructive testing of 

wing rear spar 1

(WC 728.0/6) 570018 20,000 flights 3750 flights

57-00-19 SSIP - Non-destructive testing of 

wing rear spar splice 

(between ribs 6 and 8)

(WC 728.0/7) 570019 20,000 flights 3750 flights

57-00-21 - Non-destructive check of 

the wing lower panels 

stiffners between ribs 13 

and 17

57-401 570022 14,200 flights 5350 flights

57-51-03 SSIP - Visual inspection of the 

aileron skin and hinge 

fittings

(WC 728.1/0) 575103 20,000 flights 3750 flights

57-54-05 SSIP - Non-destructive check of 

inboard slat tracks 1 

and 4 and outboard slat 

tracks 5 and 10

NOTE: For A/C having 

exceeded 

20,000 flights, NDT 

check to be 

performed within 

3750 flights from 

effective date of 

revision 20

(WC 728.1/2) 575405 20,000 flights 3750 flights
FALCON 50

CHAPTER 5

 Effectivity: ALL - Reference DGT 113872

Rev. Date: 06/2011

05-40/00

Page 16/16

"DASSAULT AVIATION Proprietary Data"

ATA 100 

No. ORIGIN DESCRIPTION MAINT. 

PROC.

OPERATION 

CODE

INSPECTIONS

THRESHOLD INTERVAL

57-60-02 - Non-destructive check of 

flap tracks 2 and 5

NOTE: For A/C having 

exceeded 

7300 flights, NDT 

check to be done 

within 600 flights 

from effective date 

of revision 19

57-607 576072 7900 flights 6800 flights

76 ENGINE CONTROLS

76-20-01 - Operational test of DEEC 

No. 1 power supply (A/C 

with engine TFE 731-40)

76-120 762002 1530 hours

78 THRUST REVERSER

78-30-10 - Non-destructive test of 

thrust reverser door hinge 

fittings

78-120 783236

783241

28,000 cycles 1155 cycles