# FALCON 50/50EX

MAINTENANCE MANUAL CHAPTER 5-40 AIRWORTHINESS LIMITATIONS

ORIGINAL - FEBRUARY 1979 R EV I S I O N 21 - JUNE 201 1

"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"


### D G T 113872 - PUB 237 or 2380900400080497332 - VALIDATED - Certification Repository0900400080464c13 - RELEASED - Certification Repository

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## CONTENTS Page 1/1 "DASSAULT AVIATION Proprietary Data" 

## CONTENTS TITLE PAGE 0 6 /2011 A L L- Reference DGT 113872



## 05- 4 0 : AIRWORTHINESS LIMITATIONS (Reference DGT 113872)

05- 4 0/00 AIRWORTHINESS LIMITATIONS

0 6 /2011 A L L- Reference DGT 113872 05- 4 0/01 NOTE TO USERS

CHAPTER 5 SECTION 5-40 0 6 /2011 ALL - Reference DGT 113872



# CHAPTER 5-40

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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 lis ted 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 ofaircraft, including SSIP, CPCP and Safe Life limitations until the Limit of Validity (refer to paragraph A. 1). These instructions are rendered mandatory by Airworthiness Dir ectives issued by the country of registration. For U.S. Registered aircraft, this section is European Aviation Safe ty 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 reas ons 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, 20 04 - Revision 16: EASA approved under EASA A.C.04307 Revision 1 on J uly 13, 2006 - Revision 17: DGT 113872 supersedes DMD 11765 §05-40, EASA appr oved under EASA.A.C.08114 on October 19, 2007 - Revision 18: This revision 18 is the compilation of the followin g 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 followin g 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 followin g 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 followin g 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. 

### E f f e ct i v e d a t e o ft h i s r e v i s i o n : June 10 , 2 0 1 1

.

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### 1. GENERAL A. DEFINITION OF THE LIMIT OF VALIDITY (L.O.V.) The Limit Of Validity represents the upperlimit expressed in "flights" until which an aircraft can fly in tota l 

### 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/60,000flying hours whichever occurs first. For a standard aircraft (refer to paragraph B.), to facilitate schedu ling 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 consider ed as a landing. That is why, "flights" have to be recorded regarding a specific definition established by DA SSAULT 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 D ASSAULT AVIATION type design: - Condition of the primary structure of a standard aircraft has to cor respond to definition at aircraft delivery:

• 

### which can be supplemented by the DASSAULT AVIATION Service Bulle tins incorporated on aircraft,

• 

### which must have incorporated the applicable mandatory Service B ulletins. - An aircraft cannot be considered as a standard aircraft if:

• 

### its primary structure has been changed by an STC or repaired throu gh 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 d efined during type certification. This spectrum corresponds to public or private transport defined by sh ort, middle and long distance flights. When types of mission listed hereafter are performed on a regula r 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 passengertransport. 

### 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 reduc e 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 theirmaintenance 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 Ch apter 5 section 05-40/00, this new 

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

### 2. INSTRUCTIONS A

. S E R V I C E B U L L E T I N S B F 5 0

- 45 0 ♦ 

### 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 inspect ions defined in the chapter 05-40/00 section 4.
The Supplemental Structural Inspection Program (SSIP) must be appl ied to aircraft that have reached the 

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

### Recommended Maintenance Schedule, T.B.O. and Chapter 5. The operatormust 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 c olumn "Maint. Proc."). 

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

### AMTOSS numbering 20-10-00 SDS) must be reported to the manufacture r.

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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 a irplane's primary structure. It is a program 

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

### a nd E ASA A M C 20

- 2 0 p r o v i d e f u rt he r de t a i l s )

. 

### During the whole life of the aircraft, the operator is required to mai ntain 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 C P C P a s pe r C ha p t e r 05

- 15 ( ba s e li ne ) and to c o m p l y a n d c o n f o r m t ot h e a i r c r a f t m a i n t enan c e m an u a l 

### 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 effectivene ss of the Baseline Program and the pertinence of the inspection threshold and, if necessary, to define changes based o n 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 locatio n or nil finding is also of 

### interest to DASSAULT AVIATION and should be reported to assist in un derstanding the aging 

### of th e f l eet a nd th e po ss i b l e n ee d fo r e s ca l at i o n o r a ll e v i at i o n o f m a i n t e n a n ce p r o g r a m .

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### 3. AIRFRAME COMPONENTS WITH LIMITED SERVICE LIFE ("SAFE LIFE") The airframe components with limited service life are listed in th e table below. This list refers only to installations designed or approved by DA SSAULT AVIATION and incorporated in the aircraft type design. Other changes such as STC's or any major change not approved by th e aircraft manufacturer, or change of the type of operation, which may have an impact on the service life of theairframe 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 pa rt, 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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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 forthe 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 col umn "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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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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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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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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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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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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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

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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 R e v

. D at e : 0 6/20 1 1 

## 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