# F

ALCON 20





 	


ORIGINAL: NOVEMBER 1986 REVISION 15: MARCH 2012
Copyright  1986 by Dassault A viation. 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 A

viation. 

### PUB.: 081Y DGT 13102809004000805750f7 - RELEASED - Certification Repository0900400080464ea6 - RELEASED - Certification Repository

# F ALCON 20 MAINTENANCE MANUAL

Reference DGT 131028 Rev . Date: 03/2012 

# CONTENTS

Page 1/1 CHAPTER 5-40 CONTENTS


### TITLE P AGE 03/2012 Reference DGT 131028 

### 05-40: AIR WORTHINESS LIMIT A TIONS (Reference DGT 131028) 05-40-00 NOTE T O USERS

CHAPTER 5 SECTION 5-40 03/2012 Reference DGT 131028 05-40-00 AIR WORTHINESS LIMIT ATIONS 03/2012 Reference DGT 131028

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

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# 5
–

# 40
–

# 00 AIR WORTHINESS LIMIT ATIONS CHAPTER 5–40–00
NOTE T O USERS

Please find enclosed revision No. 15 of Chapter 5-40-00. Main modifications and corrections contained in this revision are listed hereafter. AT A 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 : AIRCRAFTWITHOUT SB No. 730 (SSIP)

“DASSAUL T A VIA TION Proprietary Data”

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# 5-40-00 Page 1/9 AIR WORTHINESS LIMIT ATIONS 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 A viation Safety Agency (E.A.S.A.). For U.S. Registered aircraft, the Airworthiness Limitations section is E.A.S.A. approved on behalf of F AA and specifies maintenance required under paragraphs 43.16 and 91.409 of the Federal A viation Regulations, unless an alternative program has been F AA 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 1 1: September 23, 2002 Revision 12: February 10, 2003 Revision 13: EASA approved under EASA reference 05782 on July 31, 2007.

“DASSAUL T A VIA TION Proprietary Data” EFFECTIVITY : AIRCRAFT WITHOUT SB No. 730 (SSIP)

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# 5-40-00 Page 2/9 AIR WORTHINESS LIMIT ATIONS 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 authorityby reference R5010. This approval means that the revision has been prepared exclusively with already EASAapproved data and is released under DOA procedures. Effective date of this revision: February 28, 201 1. Revision 15: This revision 15 supersedes:

– the document F20 DMD 1 1755 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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# 5-40-00 Page 3/9 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 complywith these instructions will lead to the immediate suspension of the Airworthiness certificate. The mandatory nature of these instructions does not in anyway 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. Ifan 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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# 5-40-00 Page 4/9 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 DASSAUL T A VIA TION 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 SER VICE LIFE REMARKS 32 LANDING GEAR/ BRAKES F ALCON 20 Nose landing gear Magnesium barrel MESSIER C48884–9 C48884–10 20 000 landings NOTE (1) (Aircraft with SB 535) – T elescopic 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) F ALCON 20GF (S/N 397) – Leg MESSIER A10-23659-12 or A11-23659-12 20 000 landings – T elescopic 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)

EFFECTIVITY : AIRCRAFT WITHOUT SB No. 730 (SSIP)

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# 5-40-00 Page 5/9 COMPONENT IDENTIFICATION PART NUMBER LIMITED SER VICE 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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# 5-40-00 Page 6/9 B – M andatory maintenance operations
DESCRIPTION OF OPERA TION 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 – 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 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 – T ail 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 27-35-1 1 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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# 5-40-00 Page 7/9 DESCRIPTION OF OPERA TION 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 53–30–1 1 (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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# 5-40-00 Page 8/9 DESCRIPTION OF OPERA TION 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 V isual 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 71 1) 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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# 5-40-00 Page 9/9 DESCRIPTION OF OPERA TION MM REFERENCE MAXIMUM TIME LIMIT THRESHOLD REPEAT

INTERVAL 55 ST ABILIZER (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) : T

olerance: 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 71 1: “every 4 years” – For A/C with SB 71 1: 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)