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Page 1Open in PDF

FALCON 20

MAINTENANCE MANUAL

EFFECTIVITY: AIRCRAFT WITH SB No. 730 (S.S.I.P.) NOTE TO USERS Page 1

“DASSAULT AVIATION Proprietary Data”

AIRWORTHINESS LIMITATIONS CHAPTER 5-40-01, REVISION No. 9

NOTE TO USERS Please find enclosed revision No. 9 of Chapter 5-40-01.

Main modifications and corrections contained in this revision are listed hereafter.

ATA 100 No.

REMARKS Chapter 5–40–01

– New approval date of revision 9

– EASA approval

– Addition of a new mandatory operation and correction of typo error

0900400080af1aea - VALIDATED - Certification Repository

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"DASSAULT AVIATION Proprietary Data"

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FALCON 20

0$,17(1$1&( 0$18$/

TEMPORARY REVISION

EFFECTIVITY : AIRCRAFT WITH SB No. 730 (S.S.I.P)

“DASSAULT AVIATION Proprietary Data”

AIRWORTHINESS LIMITATIONS

LIST OF TEMPORARY REVISIONS DMD 44729

PAGE INTENTIONNALLY LEFT BLANK

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"DASSAULT AVIATION Proprietary Data"

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EFFECTIVITY : AIRCRAFT WITH SB No. 730 (S.S.I.P.)

“DASSAULT AVIATION Proprietary Data” 5-40-01 Page 1 Revision 9 FALCON 20

MAINTENANCE MANUAL

AIRWORTHINESS LIMITATIONS

This section contains instructions pertaining to Airworthiness of aircraft having exceeded 20000 flights/30000 flying hours and within the 40000 flights/60000 flying hours limit, after application of SB 730 (S.S.I.P.).

These instructions must be imperatively observed by operators.

With respect to the airworthiness of the aircraft, this section is subject to approval by the European Aviation Safety (EASA) .

Approved by EASA

Date of approval of the original edition: July 13, 1989 Revision 1: February 23, 1996 Revision 2: October 3, 1996 Revision 3: April 3, 1998 Revision 4: December 23, 1999 Revision 5: September 23, 2002 Revision 6: February 10, 2003 Revision 7: EASA approved under EASA reference 05782 on July 31, 2007.

PAGES No. REVISION EFFECTIVITY 5-40-01 Page 1 5-40-01 Page 2 5-40-01 Page 3 5-40-01 Page 4 5-40-01 Page 5 5-40-01 Page 6 5-40-01 Page 7 5-40-01 Page 8 5-40-01 Page 9 5-40-01 Page 10 Revision 9 Revision 9 Revision 8 Revision 8 Revision 8 Revision 8 Revision 9 Revision 8 Revision 8 Revision 8 AIRCRAFT WITH SB No. 730 (S.S.I.P.)

AIRCRAFT WITH SB No. 730 (S.S.I.P.)

For U.S. Registered aircraft, the Airworthiness Limitations section is EASA approved on behalf of FAA and specifies maintenance required under paragraphs 43.16 and 91.409 of the Federal Aviation Regulations, unless and alternative program has been FAA approved.

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FALCON 20

MAINTENANCE MANUAL EFFECTIVITY : AIRCRAFT WITH SB No. 730 (S.S.I.P.)

“DASSAULT AVIATION Proprietary Data” 5-40-01 Page 2 Revision 9

Revision 8: This revision 8 is the compilation of the following EASA approved changes, with no further technical change:

– TR001 approved by EASA under change reference M2974.

– CP005 approved by EASA under change reference M2980.

The technical content of this rev ision is approved under DOA EASA.21J.05 authority by reference R5038.

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, 2017.

– CP009 approved by EASA under change reference M7022.

Revision 9 : This revision 9 is the integration of the following EASA approved change, with no further technical change:

The technical content of this revision is approved under DOA EASA.21J.05 authority by reference R5041.

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 29, 2017.

– CH5-40-C P0002-CPAS approved by EASA under change reference M7035.

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MAINTENANCE MANUAL EFFECTIVITY : AIRCRAFT WITH SB No. 730 (S.S.I.P.)

“DASSAULT AVIATION Proprietary Data” 5-40-01 Page 3 Revision 8

GENERAL Section 5-40-01: Supersedes the section 5-40-00 of chapter 5 of the FALCON 20 MAINTENANCE MANUAL (DMD DOC No. 11755). lt is divided into two paragraphs:

A- 5-40-01 Airframe components with a limited service life ("SAFE LIFE").

B - 5-40-01 Mandatory maintenance operations.

IMPORTANT: These instructions must be complied with mandatorily by the operators.

Failure to comply with these instructions will lead to the immediate suspension of the Airworthiness Certificate.

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 carried out in agreement with the National Airworthiness Authorities.

The mandatory maintenance operation time limits given in Section 5-40- 01 correspond to results obtained from computations.

In order to reduce down time due to scheduled maintenance, these mandatory operations also appear in section 5 -10, 5-10-01 or 5-20, with time limits corresponding to the aircraft inspections (A, B, Z, C, etc.) or expressed as a number of flights.

An operation required in section 5- 40-01 may not necessarily be carried out, provided it was previously performed during an inspection required in sections 5-10 or 5-10-1.

To facilitate scheduling of maintenance operations expressed in "FLIGHTS", a flight is considered as equivalent to landing except for some specific operation conditions (training aircraft, maritime patrol aircrafts, etc.) see 5- 00-00 paragraph 4E of document DMD No.

11755.

If an operator installs a secondhand main structural part (example: landing gear), he must note on t he 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 5-40-01, will not be exceeded.

Updating of section 5-40-01:

When a new maintenance operation has been introduced during a revision of Chapter 5 Section 5-40-01, this operation must be carried out when the time at which it is scheduled falls due, unless otherwise specified in the "MAXIMUM TIME LIMIT" column.

When the aircraft inspection have two limits (i.e., 12 years or 7500 flights) the due time will be which ever is reached the first.

Responsibilities of the operators (AC 91-56) All additional inspection results, negative or positive, must be reported to the DASSAULT AVIATION manufacturer.

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MAINTENANCE MANUAL EFFECTIVITY : AIRCRAFT WITH SB No. 730 (S.S.I.P.)

“DASSAULT AVIATION Proprietary Data” 5-40-01 Page 4 Revision 8

A - Airframe components with limited service life ("SAFE LIFE")

The airframe components with limited service life having a s ervice life lower than or equal to 40000 flights/60000 flight hours are given 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, PMA (Parts Manufacturer approval) or any major change not approved by the airplane manufacturer, or change of the type of operation, which may have an impact on the airframe components service life, are not included in this document.

COMPONENT

IDENTIFICATION

PART NUMBER LIMITED SERVICE LIFE REMARKS

32 LANDING GEAR/ BRAKES

Nose landing gear leg comprising :

- Magnesium barrel

- Aluminum barrel

- Rocker

- Rotating t ube

Tel escopic bar

Shock absorber

A23659-XX A10-23659-XX A11-23659-XX A23659033-XX A23659023-XX

C48884-9 C48884-10 C1-48884

D49432-1

C1-48723 C2-48723

C48705 C1-48705

A23717 A23717-1 (SB 435) A23717-22

A23660-XXX A23660002-XXX A23660023-XXX

20 000 landings 20 000 landings 20 000 landings

40 000 landings

40 000 landings 40 000 landings

33 000 landings 40 000 landings 20 000 landings

40 000 landings 40 000 landings 40 000 landings

See NOTE (1) (A/C with SB 535)

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MAINTENANCE MANUAL

COMPONENT

IDENTIFICATION

PART NUMBER LIMITED SERVICE LIFE REMARKS

32 LANDING GEAR / BRAKES (cont’d)

Main landing gear leg

Shock absorber

Main landing gear actuator

A23663-XXX (L/H) A23664-XXX (R/H) A10-23663-XXX (L/H) A10-23664-XXX (R/H) A23663023-XXX (L/H) A23664023-XXX (R/H)

A23709-XXX (L/H) A23710-XXX (R/H) A23709023-XXX (L/H) A23710023-XXX (R/H)

A23721-XXX (L/H)

A23722-XXX (R/H)

40 000 landings 40 000 landings 40 000 landings 40 000 landings 36 000 landings 36 000 landings

40 000 landings 40 000 landings 36 000 landings 36 000 landings

40 000 landings 36 000 landings

See NOTE (2) (Aircraft with SB 535)

See NOTE (3)

NOTE (1): O ne landing on an unpaved runway corresponds to:

– 1,5 landings on a paved runway for the barrel, – 4 landings on a paved runway for the rotating tube.

NOTE (2): O ne landing on an unpaved runway corresponds to 2 landings on a paved runway for the main landing gear.

NOTE (3): The limited service life is 40,000 landings if the main landing gear actuator was not previously installed on F200 A/C .

Otherwise, the limited service life is 36,000 landings.

EFFECTIVITY : AIRCRAFT WITH SB N o. 730 (S.S.I.P.)

“DASSAULT AVIATION Proprietary Data” 5-40-01 Page 5 Revision 8

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MAINTENANCE MANUAL EFFECTIVITY : AIRCRAFT WITH SB No. 730 (S.S.I.P.)

“DASSAULT AVIATION Proprietary Data” 5-40-01 Page 6 Revision 8

B – Mandatory maintenance operations Operation associated with fatigue, and marked with an asterisk in the following table, may be carried out within the limit of 3750 flights before the threshold attached to S.S.I.P. operations so that they can be integrated in the scheduled inspections of the maintenance cycle.

DESCRIPTION OF OPERATION MM REFRENCE MAXI

MUM TIME LIMIT

THRESHOLD REPEAT INTERVAL 21 AIR CONDITIONING – Operational test of cabin pressurization in manual mode, A/C with SEMCA pressurization and equipped with pressurization controller P/N 22201E102500 21–31–50

1250 hours

– Check of overpressure tightness

• Main regulating valve

• Emergency regulating valve

21–31–10 21–31–10

1250 hours (**) 1250 hours (**) – Check of overpressure relief valve vacuum supply lines

21–31–10

7500 hours (**) (**) NOTE (8) 25 EQUIPMENT AND FURNISHINGS – V isual inspection of buckle spring of Anjou Aéronautique safety belts, extensions and restraint systems type 343 and 343-1 using Anjou Aéronautique Service Bulletin No. 343-1-25-01 and No. 343-25-02

(*) Life limit of 60 months 18 months (*) See CN 2002-105 (AB) and CN 2002-105 (AB)

27 FLIGHT CONTROLS

– Tail plane relay box – Functional test of resetting relay and contactors 27–40–30 5000 hours – Operational test of tail plane control levers 27–40–40 5000 hours 28 FUEL

– Removal/installation of removable center section panel for corrosion inspection if:

– SB 354 not complied with.

– No inspection performed in the past 12 years.

28–00 M.C.I.

NOTE (1) 12 years – Removal/installation of removable wing panels for corrosion inspection if:

– SB 499 not complied with.

– No inspection performed in the past 12 years.

28–00 M.C.I.

NOTE (1) 12 years – Non–destructive test (eddy curent) crack search of the securing screws between fixed and removable center section panel (with panels removed) 28–00–03* 20000 flights 7500 flights or 12 years – Non–destructive test (eddy current) crack search of the wing lower surface panel rabbet areas located between the wing root and rib 9 28–00–04* 20000 flights 3750 flights or 7500 flights NOTE (2)

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MAINTENANCE MANUAL EFFECTIVITY : AIRCRAFT WITH SB No. 730 (S.S.I.P.)

“DASSAULT AVIATION Proprietary Data” 5-40-01 Page 7 Revision 9

DESCRIPTION OF OPERATION MM REFRENCE

MAXIMUM TIME LIMIT

THRESHOLD REPEAT INTERVAL 28 FUEL (Cont’d)

– Non-destructive test (eddy current) crack search of the rabbet areas on the centerwing lower surface panels 28-00-05* 20000 flights 3750 v ols or 7500 flights NOTE (2) – Detection and checking of reworked or corroded areas on the lower surface skin on the wings and the center wing (removable panel in position) 28-00-06* 20000 flights 3750 flights or 6 years See NOTE (6) 32 LANDING GEAR/BRAKES

– Check for absence of friction points in the door uplock flexible connecting control rods 32-00-6 330 hours – Control and indicating switches. Voltage drop measurement (Before SB 531) 32-30-00 1230 hours 51 STRUCTURE – Detailed anti-corrosion inspection - Renewal of the protection plan by means of preventive and curative anti-corrosion treatment 51-00-00 M.C.I.

NOTE (1) 12 years 52 DOORS – Unlocking test from inside of window emergency exit, RH and LH (EASA Airworthiness Directive No. 2000-0156) 52 -20-1 24 months

52-70-1 800 hours 53 FUSELAGE – Visual inspection of the corners of the nose wheel well opening (frame 7 for A/C S/N 1 to 378) 53-30-0* 20000 flights 3750 flights or 6 years – Non-destructive test (Eddy current) of the joggling between the panels at frame 33 in aircraft center line 53-30-02* 20000 flights NOTE (3) or 30000 flights NOTE (4) 2000 flights

2000 flights – Non-destructive test (Eddy current) of the fuselage frame work around the windows at frames 15-18 and 27 (skin or reinforcements) (longitudinal cracks) 53-30-04* 20000 flights 3750 flights or 7500 flights NOTE (2) – Non-destructive test (Eddy current) of upper fuselage skin between frames 26 and 33 and between stringers 5 LH and 5 RH 53-30-05* 25000 flights 3750 flights or 6 years

– Structural inspection - Frame 33 inspection/check 53-10-0 5000 FC 5000 FC – Functional test of passenger/crew door warning system

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MAINTENANCE MANUAL EFFECTIVITY : AIRCRAFT WITH SB No. 730 (S.S.I.P.)

“DASSAULT AVIATION Proprietary Data” 5-40-01 Page 8 Revision 8

DESCRIPTION OF OPERATION MM REFRENCE

MAXIMUM TIME LIMIT

THRESHOLD REPEAT INTERVAL 53 FUSELAGE (Cont’d)

– Non-destructive test (ultrasonic) of window frame vertical posts on windows secured with screws 53-30-07 M.C.I.

NOTE (1) 6 years – Lower frames of rear and side windows panels in flight compartment 53-30-11 (before SB 701) M.C.I.

NOTE (1) 6 years

• X ray inspection – Endoscopic check of pilot and copilot windshield lower frames 53-30-12 (before SB 701) M.C.I.

NOTE (1) 6 years – Non-destructive test (Eddy current) of windshield frame lower recesses (SB 708 complied with) 53-30-13 (before SB 701) 10 years Every 2 years – Removal/Installation of trim for visual inspection of flight compartment glass panel frames 53-30-14 20000 flights (NOTE 7) 3750 flights or 6 years – Non-destructive test (Eddy current) of windshield frame lower recesses (front, pilot and copilot windshield) 53-30-15 20000 flights (NOTE 7) 3750 flights or 6 years – Stringer and reinforcement/skin interfaces spot welded between frames 33 and 40 53-30-4 M.C.I.

NOTE (1) 12 years

• Check for absence of corrosion using Eddy current inspection method (aircraft S/N 3 to 384 and 392)

– Stringer and reinforcement/skin interfaces spot welded between frames 0 and 33 53-30-40 M.C.I.

NOTE (1) 12 years

• Check for absence of corrosion using Eddy current inspection method (aircraft S/N 3 to 384 and 392)

– Inspection and check of fillets (French D.G.A.C.

Airworthiness Directive No. 96-092-021 (B)) 53-50-0-3D A inspection

– Non-destructive testing (Eddy current) of the cockpit window frames 53-30-06* 20000 flights 3750 fligh ts or 6 years

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