FALCON 20



	




	


ORIGINAL: NOVEMBER 1986

REVISION 15: MARCH 2012

Copyright  1986 by Dassault Aviation.

All rights reserved. No part of this work may be reproduced or copied

in any form or by any means without written permission

of Dassault Aviation.

PUB.: 081Y DGT 131028

09004000805750f7 - RELEASED - Certification Repository 0900400080464ea6 - RELEASED - Certification Repository
FALCON 20

MAINTENANCE MANUAL

Reference DGT 131028

Rev. Date: 03/2012

CONTENTS

Page 1/1

CHAPTER 5-40

CONTENTS

TITLE PAGE

03/2012 Reference DGT 131028

05-40: AIRWORTHINESS LIMITATIONS (Reference DGT 131028)

05-40-00 NOTE TO USERS

CHAPTER 5

SECTION 5-40

03/2012 Reference DGT 131028

05-40-00 AIRWORTHINESS LIMITATIONS

03/2012 Reference DGT 131028

EFFECTIVITY : AIRCRAFT WITHOUT SB No. 730 (S.S.I.P.)
FALCON 20

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Reference DGT 131028

Rev. Date: 03/2012

5–40–00

AIRWORTHINESS LIMITATIONS

CHAPTER 5–40–00

NOTE TO USERS

Please find enclosed revision No. 15 of Chapter 5-40-00.

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

ATA 100 No. Section Modifications and Corrections TR/CP

Number

Chapter 5-40-00 ALL Creation of a new chapter 5-40 manual to make

common the F20 and F20GF chapter 5-40-00:

– with no technical change for the F20,

– 26-10-02: new procedure added for the F20GF S/N 397.

The chapter 5-40 becomes the manual DGT 131028.

Filing instructions:

Remove the section 5-40 from your current chapter 5 manual and replace it by this manual DGT 131028.

EFFECTIVITY: AIRCRAFT WITHOUT SB No. 730 (SSIP)

 “DASSAULT AVIATION Proprietary Data”
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5-40-00

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AIRWORTHINESS LIMITATIONS

This section contains instructions pertaining to Airworthiness.

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 Agency (E.A.S.A.).

For U.S. Registered aircraft, the Airworthiness Limitations section is E.A.S.A. 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.

PAGES No. REVISION EFFECTIVITY

5-40-00 Revision 15 AIRCRAFT WITHOUT SB No. 730 (S.S.I.P.)

Approved by E.A.S.A.

Date of approval

of the original edition: November 21, 1986

Revision 1: March 26, 1987

Revision 2: June 3, 1987

Revision 3: April 15, 1988

Revision 4: July 13, 1989

Revision 5: April 26, 1991

Revision 6: February 23, 1996

Revision 7: October 3, 1996

Revision 8: April 3, 1998

Revision 9: December 23, 1999

Revision 10: September 23, 2002

Revision 11: September 23, 2002

Revision 12: February 10, 2003

Revision 13: EASA approved under EASA reference 05782 on July 31, 2007.

 “DASSAULT AVIATION Proprietary Data”

EFFECTIVITY : AIRCRAFT WITHOUT SB No. 730 (SSIP)
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AIRWORTHINESS LIMITATIONS

Revision 14: This revision 14 is the compilation of the following EASA approved changes, with no further

technical change:

– TR002 approved by EASA under change reference M2974.

– CP003 approved by EASA under change reference M2979.

The technical content of this revision is approved under DOA EASA.21J.05 authority by reference R5010.

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: February 28, 2011.

Revision 15: This revision 15 supersedes:

– the document F20 DMD 11755 section chapter 5-40-00,

– the document F20GF (S/N 397) DMD 33075 section chapter 5-40-00.

This version is approved by EASA under reference M2964.

Effective date of this revision: January 30, 2013.

EFFECTIVITY : AIRCRAFT WITHOUT SB No. 730 (SSIP)
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Reference DGT 131028

Rev. Date: 03/2012

5-40-00

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GENERAL

Section 5-40 is divided into two paragraphs:

A – 5-40-00 Airframe components with limited service life (“SAFE LIFE”).

B – 5-40-00 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 Program, which must be carried

out in agreement with the National Airworthiness Authorities.

The mandatory maintenance operation time limits given in section 5-40 correspond to

results obtained from computations.

In order to reduce down time due to scheduled maintenance, these mandatory

maintenance operations are also listed in section 5-10 or 5-20 but with time limits

corresponding to aircraft inspections (A, B, Z, C) or expressed in number of flights.

An operation required in section 5–40 may not necessarily be carried out, provided it was

previously performed during an inspection required in sections 5–10 or 5-20.

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 4.E.

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 5-40, will not be exceeded.

Airworthiness limitations specific to F20GF are covered by the supplement of the

Maintenance Manual DFS--DE-05-F2-A1, Section 5-40-00 DFS.

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, 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.

EFFECTIVITY : AIRCRAFT WITHOUT SB No. 730 (SSIP)
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A – Airframe components with limited service life (“SAFE LIFE”)

The airframe components with limited service life 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 STCs, PMA 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 SERVICELIFE REMARKS

32 LANDING GEAR/

BRAKES

FALCON 20

Nose landing gear

Magnesium barrel

MESSIER

C48884–9

C48884–10

20 000 landings

NOTE (1)

(Aircraft with SB 535)

– Telescopic bar A23717

A23717–1 (SB 435)

33 000 landings

40 000 landings

– Rocker C1–48723

C2–48723 40 000 landings

– Rotating tube C48705 or

C1–48705 40 000 landings NOTE (2)(Aircraft with SB 535)

– Shock absorber A23660 40 000 landings

Main landing gear

actuator

MESSIER

A23721 and A23722 23 000 landings Aircraft 1 to 470(Without M2437)

FALCON 20GF

(S/N 397)

– Leg MESSIER

A10-23659-12 or

A11-23659-12

20 000 landings

– Telescopic bar A23717-1-2-A 20 000 landings

– Nose landing gear

aluminum barrel

GA58306 20 000 landings NOTE (3)

– Rotating tube GA58112-4

GA58113

20 000 landings

20 000 landings

NOTE (3)

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COMPONENT

IDENTIFICATION PART NUMBER LIMITED SERVICE

LIFE REMARKS

54 STUBS

NACELLES

– Engine front mounts

(S/N 397)

 Fittings, mast side:

fittings

 Attachment

hardware

 Bolt (2 + 2)

AMD-BA

MY202471001G03(G) 

MY202491001G03(D) 

MY2024710510G03(G) 

MY2024910510G03(D) 

NAS1309-17D

 20 000 flights

NOTE (4)

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

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

NOTE (2) : The limited service life of this component is 40 000 landings; However, every 

landing on an unpaved runway corresponds to 4 landings on a paved runway.

NOTE (3) : One landing on an unpaved runway (Aircraft with M3032) corresponds to:

– 1,5 landings on a paved runway for the barrel,

– 8 landings on a paved runway for the rotating tube.

NOTE (4) : M3035 not applied.
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B – Mandatory maintenance operations

DESCRIPTION OF OPERATION MM MAXIMUM TIME LIMIT

REFERENCE THRESHOLD REPEAT

INTERVAL

21 AIR CONDITIONING

– Operational test of cabin pressurization inmanual 

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

– Check of overpressure relief valve static

pressure lines

21-31-10

21-31-10

21-31-10

1250 hours

1250 hours

7500 hours

25 – EQUIPMENT AND FURNISHINGS

– Visual 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

18 months (*)

see

CN 2002-105 (AB)

and

CN 2002-104 (AB)

26 FIRE PROTECTION

– Fire detection box

 189W diode integrity (aircraft No. 397)

26–10–02 5000 hours

NOTE (4)

– Functional test of the fire detectors (operation

of detection pressure switch) (Aircraft No. 397)

167.0 5600 hours

27 FLIGHT CONTROLS

– Tail plane relay box – Functional test of

resetting relay and contactors

27-40-30

234.0 (S/N 397)

5000 hours

– Operational test of tail plane control levers 27-40-40

229.0 (S/N 397)

5000 hours

– Functional test of the non-return valves of the

servo-actuator (Aircraft No. 397)

CMM 27-09-04

CMM 27-35-11

10000 hours

or

10 years

– Functional test of steering anti-gust valve

 (Aircraft No. 397)

CMM 27-24-30 10000 hours

or

10 years

EFFECTIVITY : AIRCRAFT WITHOUT SB No. 730 (SSIP)
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DESCRIPTION OF OPERATION MM MAXIMUM TIME LIMIT

REFERENCE THRESHOLD REPEAT

INTERVAL

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

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 (E.A.S.A. Airworthiness 

Directive No. 2006-0156)

52–20–1 24 months

53 FUSELAGE

– Non–destructive test (ultrasound) 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 glass panels

in flight compartment

 53–30–11

(before SB 701)

M.C.I.

NOTE (1)

12 years

 X ray inspection

– Endoscopic check of pilot and copilot

windshield lower frames

 53–30–12

(before SB 701)

M.C.I.

NOTE (1)

12 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 6 years

NOTE (3)

6 years

EFFECTIVITY : AIRCRAFT WITHOUT SB No. 730 (SSIP)
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DESCRIPTION OF OPERATION MM REFERENCE

MAXIMUM TIME LIMIT

THRESHOLD REPEAT

INTERVAL

53 FUSELAGE (CONT’D)

– Eddy-current check of windshield frame lower

recesses

 53–30–15 M.C.I.

NOTE (1)

NOTE (3)

12 years

– Stringer and reinforcement/skin interfaces

spot welded between frames 33 and 40

 Check for absence of corrosion using

Eddy Current inspection method

(aircraft No. 3 to 384 and 392)

53–30–4 M.C.I.

NOTE (1)

12 years

– Stringer and reinforcement/skin interfaces

spot welded between frames 0 to 33

 Check for absence of corrosion using

Eddy Current inspection method

(aircraft No. 3 to 384 and 392)

53–30–40 M.C.I.

NOTE (1)

12 years

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

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

55 STABILIZER

– Movable tail plane. Inspection for corrosion

and protection

 Endoscope inspection and spraying

 Visual inspection of forward and aft spars

and angle brakets

55–10–40 M.C.I.

NOTE (1)

12 years

– Stiffeners/skin panels interfaces spot welded

 Check for absence of corrosion using 

Eddy Current inspection method

(aircraft No. 3 to 384 and 392)

55–30–10 M.C.I.

NOTE (1)

12 years

– Removal/Installation of horizontal and

vertical stabilizers (M.C.I.) for:

55–50–00 M.C.I.

NOTE (1)

12 years

 Checking fittings and bores

 Detailed corrosion inspection

 Anti–corrosion protection of fittings

 Installing a new fin hinge pin (SB 711)

 Detailed corrosion inspection on:

– the drive tubes of elevators coupling

– the inner drive tubes of each elevator

EFFECTIVITY : AIRCRAFT WITHOUT SB No. 730 (SSIP)
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DESCRIPTION OF OPERATION MM REFERENCE

MAXIMUM TIME LIMIT

THRESHOLD REPEAT

INTERVAL

55 STABILIZER (CONT’D)

– Non–destructive test of fitting lugs:

– A – Eddy currents on:

 Horizontal stabilizer hinges (on

horizontal stabilizer side)

 fuselage stub–to–vertical stabilizer rear

connection (on vertical stabiliser side)

– B – Ultrasonic on:

 All fuselage stub/fin/horizontal

stabilizer fittings (stabilizers installed)

55–50–03

55–50–01

NOTE (2)

M.C.I.

NOTE (1)

12 years

or

7500 Flights

76 ENGINE CONTROLS

– Functional tests of fuel and hydraulic shut–off

valves (check for non–jamming in “open”

position)

76–20–1

929.0 (S/N 397)

10000 hours

NOTE (1) : Tolerance: to avoid aircraft down time for logistic reasons, the manufacturer authorizes

exceptionally a maximum tolerance of plus 6 months on the repeat interval of the Major 

Corrosion Inspection (M.C.I., 12 years). No tolerance can be granted for the first M.C.I. 

at 24 years.

NOTE (2) : The recommended repeat interval for operation 55–50–01 (stabilizers installed) is:

– For A/C without SB 711: “every 4 years”

– For A/C with SB 711: C inspection

See also Chapter 5–10–00

NOTE (3) : These inspections require the mandatory SB 701 to be complied with in accordance with E.A.S.A.

Airworthiness Directive to be issued.

NOTE (4) : Only EASA approved.

EFFECTIVITY : AIRCRAFT WITHOUT SB No. 730 (SSIP)